CN114872931A - Integrated detection method for general assembly system of airplane - Google Patents

Abstract

The invention relates to an integrated detection method for an aircraft general assembly system, belonging to the field of aircraft assembly detection. According to the aircraft emergency rescue system, the aircraft flight control system, the aircraft human-sensing control system and its three inspection and measurement states, the entire workflow of the integrated inspection of the aircraft assembly system includes: the installation of the safety valve products of the emergency rescue system, and the Monitor the working pressure of the emergency rescue system, measure the unlocking stroke of the emergency rescue system; carry out the assembly inspection and measurement of the rod parts of the flight control system, carry out the dynamic detection of the stroke of the servo actuating device of the flight control system, and carry out the flight control system. The inspection and measurement of the deflection angle of the long-rod rocker arm parts; the measurement of the deflection force of the joystick device of the human-sensing control system, the measurement of the deflection stroke and deflection force of the pedal device of the human-sensing control system, and the man-sensing control system The rod system drive free travel measurement work.

Description

Integrated testing method for aircraft assembly system

technical field

The technology of the invention is suitable for the research fields of the integrated detection before and after the assembly of important system components in the general assembly link of the aircraft and the verification of related system functions. The on-board inspection area, inspection content and indicators are reasonably divided by inspection status and system ownership, and through the implementation of special tools and innovative process methods, the ultimate goal of greatly improving inspection and measurement accuracy and assembly verification efficiency is achieved.

Background technique

After the military fighter enters the general assembly stage, the functional components of each system are installed one after another. The accurate detection and verification of the installation position, working process and performance parameters of each component is a necessary step to ensure the realization of the functions of each system.

The aircraft emergency rescue system is an important system related to the personal safety of the pilot. When an emergency occurs in the aircraft, the system can eject the pilot from the plane through emergency measures, which is the last line of defense for the pilot's safety. The installation and functional verification of its system accessories have very strict and strict requirements, and effective control of its installation and adjustment errors will greatly ensure that the system has qualified working ability.

The aircraft flight control system is an important system that directly affects the flight performance of the aircraft. The system receives the pilot's manipulation or the instructions of the automatic flight control system, and controls the aircraft attitude, flight trajectory and flight speed by controlling the movement of the rudder surface of the aircraft. Match the air movement of the aircraft to the expectations of the pilot or automatic flight control system. The mechanical connection between its related accessories has high-precision, high-reliability installation testing requirements. Through the accurate measurement of the relevant parameters such as the deflection angle, adjustment length, and free travel of the relevant components, the working ability and flight performance of the aircraft flight control system will be effectively improved.

The aircraft human-sensing control system is an important system to realize the control function of the aircraft pilot. The system provides the pilot with the control feeling by providing the control stick force and the pedal force, and at the same time converts the pilot's control command into the corresponding electrical signal, so as to provide the pilot with a sense of control. The flight control system provides valid control command input. The parameter indicators and overall working ability of its manipulation accessories require scientific and efficient measurement methods. Through the ingenious transformation of simple measurement methods, the pilot's real scene restoration can be realized, which can effectively verify the function of the system and the degree of compliance.

At present, the testing processes and methods of each system in the general assembly link of aircraft in most similar industries in China are relatively simple, and most assembly verification processes are mainly based on the mixed application of straightedge, angle ruler, and dynamometer. This adjustment method has problems such as low measurement accuracy, difficult operation, many human factors, and long debugging period. Although it can meet the requirements of the existing design indicators, it also restricts the accuracy of the functional testing and verification of various aircraft systems to a certain extent. degree and convenience. At the same time, due to the continuous integration and upgrading of various functional modules of the new aircraft and the increasing production technology, some traditional inspection and measurement technologies are not fully capable of realizing the accuracy and efficiency of aircraft assembly and debugging at this stage. Therefore, a new type of aircraft is urgently needed. The integrated testing process method and the comprehensive application technology of special tooling equipment can optimize the current aircraft assembly, installation, testing and debugging process.

SUMMARY OF THE INVENTION

In view of the above reasons, an innovative testing technology method for the integration of the aircraft general assembly system has been invented, and the technology has been applied to the above three systems. From different testing periods, the working state of accessories can be scientifically and reasonably optimized and perfected during the general assembly process of the aircraft. The advanced inspection and measurement method can not only complete the relevant assembly status inspection and work performance verification work accurately and efficiently, but also strictly control the production cycle of the aircraft.

Technical scheme of the present invention:

The integrated detection method of the aircraft general assembly system, according to the aircraft emergency rescue system, the aircraft flight control system, the aircraft human-sensing control system and its three inspection and measurement states, the overall workflow steps of the integrated inspection of the aircraft general assembly system are as follows:

Step 1. The integrated detection process of the emergency life-saving system

(1) Installation of finished safety valves for emergency rescue systems

The finished safety valve of the aircraft's emergency rescue system is installed at the perforation of the aircraft cabin wall panel to keep the cabin pressure at the pilot's comfortable state. The main view of the finished product is a circle, and the side is a conical arc transition. When installing the finished product, install the auxiliary installation device of the aircraft safety valve on the finished product correctly in advance, install the safety valve with the auxiliary installation device of the aircraft safety valve on the machine according to the relevant requirements and complete the clamp fixing, and check the finished product and the clamping clamp. Edge clearance should meet relevant requirements. After the installation and inspection work, the auxiliary installation device of the aircraft safety valve should be kept installed. During the follow-up inspection of the working performance of the safety valve, there should be no obvious change in the edge clearance after repeated inspection. After recording the value, remove the aircraft safety valve auxiliary mounting device from the finished product.

(2) Monitor the working pressure of the emergency rescue system

After the installation of the safety valve products of the whole aircraft emergency rescue system, the air tightness of the cockpit, the structural strength of the cockpit, the function of the hatch cover control system, the air tightness of the hatch cover control system, the air tightness of the emergency rescue system, and the emergency rescue system shall be performed. Aircraft portable inflation and inspection test equipment can be used for performance-related inspections. Before the test of each item, if the gas filling work is involved, one end of the aircraft portable inflation and testing test equipment is connected to the inflatable nozzle connector on the aircraft through the optional joint, and the other end is connected to the special inflatable tooling equipment. Connect the port of the aircraft's portable inflation and testing test equipment to the testing pipeline port of the on-board system through the optional connector, and close the manual shut-off valve.

The air pressure is supplied to the on-board system through the inflatable device of the aircraft portable inflation and detection test equipment. At this time, the gas inlet pressure can be judged according to the value shown on the digital display pressure gauge on the aircraft's portable inflation and detection test equipment. The gas pressure in the system is judged by the value shown on the digital pressure gauge on the portable inflatable and detection test equipment of the aircraft at the outlet end, the relevant data records are completed, and the function inspection and performance index detection of each system are successively carried out through the detection device.

(3) Carry out the measurement of the unlocking stroke of the emergency rescue system

This work can be carried out in conjunction with the inspection work related to the working pressure performance of the emergency rescue system. Through the inflatable device of the portable inflatable and testing equipment of the aircraft, the emergency rescue system is co-pressurized to the stable working index range, and the inspection and explosion mechanism can be normally unlocked within the allowable pressure range. If all the inspections related to inflation have been completed at this time, the connection of the aircraft parts unlocking stroke measuring device can be disconnected after exhausting and the installation state on the original aircraft can be restored.

Install the aircraft parts unlocking stroke measuring device on the restored blasting mechanism, record the initial scale value, and operate the measuring tool to make the components of the blasting mechanism move to the just unlocked state. At this time, the difference between the scale value and the initial scale value The value is the part unlocking stroke. Record this value and remove the aircraft parts unlocking travel measuring device, and restore the installation of the explosion mechanism.

Step 2. Flight control system integration testing process

(1) Carry out the inspection and measurement of the rod parts assembly of the flight control system

Before the installation of the rod parts related to the flight control system, the precise measurement test bench of the aircraft special-shaped joystick is used to accurately ensure the assembly length of various rod parts. According to the type and size of the connecting rod joint to be tested, select the joints of the aircraft special-shaped joystick accurate measurement test bench, and adjust the extension of the connecting rod joint to change the length of the connecting rod according to the measurement results. After the length meets the requirements of the assembly drawings Complete insurance work and install connections. Complete the installation of all the adjustable rods with fixed length requirements of the flight control system in the same way.

(2) Carry out the dynamic detection of the travel of the servo actuator of the flight control system

During the debugging and testing, the protruding amount of the piston rod of the servo actuator is verified by the aircraft actuator piston rod protruding amount measuring device. Make sure that the flight control system has the full state debugging and testing conditions, select the appropriate upper and lower snap rings according to the outer dimensions of the servo actuator to be tested and its piston rod, and install the aircraft actuator piston rod extension measuring device to the test device to be tested. On the servo actuating device, the servo actuating device is made to perform telescopic motion through the system command input, and it is verified that its dynamic stroke meets the relevant performance index requirements in real time.

(3) Carry out the inspection and measurement of the deflection angle of the long-rod rocker arm parts of the flight control system

This work can be carried out in conjunction with the inspection work related to the working performance of the flight control system servo actuating device. During the debugging and testing of the aircraft flight control system, some aircraft types need to measure and verify the deflection angles of some long-rod rocker arm parts controlled by hydraulic pressure under different working pressures. The arm part deflection angle measuring instrument assists. After the flight control system has the full-state debugging and testing conditions, place the long-rod rocker arm part deflection angle measuring instrument in the measurement area, operate the measured part to move it to the initial position, and measure the long-rod rocker arm part deflection angle The instrument is fixed on the measuring point of the long rod type rocker arm part. Accurately install the integrated inclination indicator and adjust it to the zero position. After operating the measured part to move it to another state, the actual deflection angle of the part is recorded through the numerical change of the inclination synchronization indicator. Continue to make precise measurements of other deflection angular positions of this part in the same manner.

Step 3. The integrated detection process of the human-sensing control system

(1) Measure the deflection force of the joystick-like device of the human-sensing control system

In the human-sensing control system, after the handle device is installed, it is necessary to check that its control force should meet the operating comfort range. The manual operating mechanism force measuring device can not only be applied to the operating force measurement of the canopy opening mechanism, but also can be applied to the operating force measurement of the handle parts of other operating systems. Install the handle sleeve in the force measuring device of the manual operating mechanism on the measuring point of the handle to be tested, turn on the power of the equipment and deflect the handle device to the designated position according to the test requirements, record and check whether the operating force conforms to the value shown on the force value display. related requirements.

(2) Measure the deflection stroke and deflection force of the pedal device of the human-sensing control system

The pedal device in the human-sensing control system is an important control accessory, and the difficulty in its debugging and detection lies in the synchronous measurement of deflection stroke and deflection force. On the pedal mechanism assembly, the connection of the numerical display, the digital angle measuring device and the pressure sensor is completed. Fix the pedal system in the neutral position with the neutral positioning rod, and adjust the scale indicator and the pressure value display to zero at this time. Remove the neutral positioning rod and manipulate the pedal mechanism to deflect until the value of the scale indicator reaches the measurement position and stop the deflection and record the pressure value shown on the numerical display at this time. Complete the test and comparison of all deflection positions and corresponding deflection forces successively.

(3) Carry out the measurement of the free travel of the rod system of the human-sensing control system

This work can be performed in conjunction with the deflection stroke and deflection force measurement of the pedal device of the human-sensing control system. After installing the relevant measuring equipment on the pedal mechanism, combine and install the joystick drive system idle travel measuring instrument on the measuring position of the joystick, fasten the remote drive feedback part on the structure around the actuator of the terminal, and slowly drive the The joystick moves until the remote actuator is just actuated. At this time, the displacement of the joystick is read through the indicator, and the free stroke measurement of each channel of the joystick is completed successively.

The aircraft safety valve auxiliary installation device is installed between the safety valve and the clamping clamp, and includes a backing plate 1-1, a fixed bolt support slider 1-2, a baffle support slider 1-3, a baffle plate Plate support 1-4, fixing bolt support 1-5, adjusting bolt 1-6, fixing nut 1-7, shaft sleeve 1-8, shaft sleeve felt pad 1-9, baffle felt pad 1-10, stopper Plate support adjustment screw 1-11, fixing bolt support adjustment screw 1-12 and backing plate felt pad 1-13;

The backing plate 1-1 is an arc-shaped plate with an L-shaped cross-section, including horizontal and vertical sides. The intersection of the two is an indented chute, which is used to limit and clamp the clamp; fixed bolt support slider 1-2 and the baffle support slider 1-3 move in the chute; on the fixed bolt support slider 1-2, the fixed bolt support 1 with the through slot is installed through the fixed bolt support adjustment screw 1-12 -5; Adjusting bolts 1-6 are fixed by fixing nuts 1-7 after passing through the through grooves of fixing bolt supports 1-5 and sleeves 1-8; baffle support sliders 1-3 are supported by baffle plates The seat adjustment screw 1-11 is installed with the baffle support 1-4, and the baffle support 1-4 is used to cooperate with the shaft sleeve 1-8 to limit the safety valve bracket.

Further, the bottom of the horizontal side of the backing plate 1-1 is stuck with a backing plate felt pad 1-13, and the baffle felt pad 1-10 and the shaft sleeve felt pad 1-9 are respectively pasted on the baffle support 1-4 and the shaft. Opposite sides of sets 1-8.

The aircraft portable inflatable and detection test equipment includes an inflatable device and a detection device, and the inflatable device and the detection device can be used independently or in combination;

The inflatable device is used for the input and output of gas, including the aircraft end joint 2-1, the aircraft end hose 2-2, the three-way joint 2-3, the combined conduit B2-7, and the adapter B2-8 connected in sequence. , one-way valve 2-9, adapter C2-10, combined conduit C2-11, manual stop valve 2-12, air source end hose 2-13, air source end connector 2-14; The third joint of -3 is connected to the combined conduit A2-4, the adapter A2-5, and the digital pressure gauge A2-6 in turn; the air source end connector 2-14 is connected to the air source, and the aircraft end connector 2 -1 is connected to the aircraft through the air source end hose 2-13, manual stop valve 2-12, combined conduit C2-11, adapter C2-10, one-way valve 2-9, adapter B2-8, combination Conduit B2-7, tee joint 2-3, aircraft end hose 2-2, aircraft end joint 2-1 Fill the gas in the air source to the position where the aircraft needs to be filled with gas; digital pressure gauge A2-6 It is used to visually display the change of gas pressure; the manual stop valve 2-12 can manually control the inflation rate according to the pressure change of the digital pressure gauge A2-6; the one-way valve 2-9 can prevent the airflow in the system from backflowing;

The detection device includes a digital pressure gauge B2-15, an adapter D2-16, a combined conduit D2-17, a manual stop valve 2-18, a detection end hose 2-19 and a detection end connector 2-20 connected in sequence. ; The detection end joint 2-20 is connected with the aircraft pressure detection end, through the detection end hose 2-19, manual stop valve 2-18, combined conduit D2-17, adapter D2-16, digital display pressure gauge B2-15 is used to detect the gas pressure of the air-filled part of the aircraft; the digital pressure gauge B2-15 is turned on by the screw switch of the manual stop valve 2-18 to observe the change of the gas pressure at the air-filled position of the aircraft and related detection items air tightness.

The aircraft part unlocking stroke measuring device includes a clamping mechanism, a fixed base mechanism and a driving mechanism;

The left fixing frame 3-1 and the right fixing frame 3-2 are both semi-circular rings, and the two are connected by the rotating pin 3-16 to form a clamping mechanism, which is used to clamp the unlocking stroke measuring tool of the aircraft part to the surface of the part shell , and then lock by quick release bolt 3-3 and turning nut 3-4;

The fixed base mechanism includes a lower stop base 3-5, a lead screw 3-8, a driven gear 3-9, an upper stop base 3-10, a scale rod 3-12 and a polished rod 3-13; the end of the clamping mechanism is connected The lower stop base 3-5; between the lower stop base 3-5 and the upper stop base 3-10 are installed two lead screws 3-8, scale rods 3-12 and polished rods 3-13; moving brackets 3-6 The screw is connected to the two lead screws 3-8 for reciprocating motion, and there is a long slot on it; each lead screw 3-8 is equipped with a driven gear 3-9; on the moving bracket 3-6 There is a scale pointer, which cooperates with the scale rod 3-12 to obtain the scale;

The driving mechanism includes a rotating handle 3-11, a rotating shaft 3-14 and a main gear 3-15, which are connected in sequence; the rotating shaft 3-14 passes through the through hole of the upper stop base 3-10, and the main gear 3-15 is connected with each slave The moving gears 3-9 are engaged.

Further, the mounting points of the two lead screws 3-8 are respectively located at one diameter end point of the two bases, the mounting points of the scale rod 3-12 and the polished rod 3-13 are respectively located at the other diameter end points of the two bases, and the two diameters are perpendicular to each other.

Further, the contact surface of the moving bracket 3-6 is pasted with a felt pad 3-7.

Further, the lower stop base 5 is provided with an elongated slot for it to be installed directly on one side of the aircraft part.

Further, the quick-release bolts 3-3 are cylinders, the head of which is provided with a slot, and the side cylindrical surface is embossed.

The aircraft special-shaped joystick precision measurement test bench includes an equipment base 4-1, a scale 4-2, a grooved slide rail 4-3, a moving pointer 4-4, a small fixing screw 4-5, and a large fixing screw 4- 6. Base baffle 4-7, outer slide rail 4-8, sliding support 4-9, extension link 4-10, optional joint 4-11, fixed support 4-12, detachable joint 4-13 , information signs 4-14, sliding rollers 4-15 and roller pins 4-16;

The device base 4-1 is provided with a non-slip pad, which can be placed on the tool table smoothly without relative sliding; the fixed support 4-12 is provided with a freely replaceable detachable joint 4-13, Sliding supports 4-9 are provided with optional joints 4-11 which can be freely selected according to the fixing form of the tie rod to be measured, and lengthened connecting rods 4-10 of different lengths can be freely installed on the fixed supports 4-12 and/or Or above the sliding support 4-9, which is convenient for measuring non-straight rod-type parts; the grooved slide rail 4-3 and the outer slide rail 4-8 are arranged on both sides of the equipment base 4-1, as the sliding support of the sliding support 4-9. Channel, the slotted slide rail 4-3 has a long flat hole in the center; as a sliding channel for the moving pointer 4-4, the slotted slide rail 4-3 closes to the scale 4-2 side to fix the moving pointer 4-4, move The pointer 4-4 passes through the long flat hole, which is convenient for intuitive reading on the scale 4-2; the scale 4-2 is fixed on the equipment base 4-1, and the "0" scribe line of the scale 4-2 is detachable The central axes of the joints 4-13 are coincident, the fixed support 4-12 is set at the beginning of the grooved slide rail 4-3 and the outer slide rail 4-8, and the base baffle 4-7 is set on the grooved slide rail 4-3 and the outer side. The end of the slide rail 4-8 can be freely disassembled and used to limit the position of the sliding support 4-9; the sliding roller 4-15 is installed on the bottom end of the sliding support 4-9 through the roller pin 4-16.

The device for measuring the protruding amount of the piston rod of the aircraft operating cylinder includes an open-type operating cylinder cover snap ring, a piston rod snap ring, a slide rail, a slider 5-6, a fixed support 5-7 and a digital vernier caliper 5- 9;

The open-type actuator cover snap ring is connected by the actuator cover upper snap ring 5-1 and the actuator cover lower snap ring 5-2 through the actuator cover snap ring fixing bolts 5-14, and is sleeved on the actuator cover. Up; the piston rod snap ring is connected by the piston rod upper snap ring 5-3 and the piston rod lower snap ring 5-4 through the piston rod snap ring fixing bolt 5-13, which is sleeved on the piston rod nut; the snap ring on the actuator cover 5-1 is provided with a double-hole lug, and the snap ring 5-3 on the piston rod is provided with a single-hole lug. The snap ring 5-1 on the actuator cover and the snap ring 5-3 on the piston rod are located at the same level. The hole is used for the long slide rail 5-5 to pass through, the snap ring 5-1 on the actuator cover is fixed on the long slide rail 5-5 by the slide rail fixing nut 5-15, and the snap ring 5-3 on the piston rod is longer than the long slide rail 5-5. The slide rail 5-5 reciprocates; the fixed support 5-7 and the slider 5-6 are sleeved on the long slide rail 5-5, located between the actuator cover snap ring and the piston rod snap ring, the slider 5-6 It is fixed by the slider top wire 5-12; one end of the short slide rail 5-8 is fixed in the other hole of the snap ring 5-1 on the actuator cover through the slide rail fixing nut 5-15, and the other end passes through the fixed support The seat 5-7 is fixed by the support top wire 5-11;

There are grooves on the slider 5-6 and the fixed support 5-7, respectively fixing the front teeth and the rear teeth of the digital vernier caliper 5-9, wherein the rear teeth of the digital vernier caliper 5-9 pass through the caliper top wire 5- 10 to be fixed.

Further, the short slide rails 5-8 are located above the long slide rails 5-5 and the two are parallel.

Further, the surfaces of the open-type actuating cylinder cover snap ring and the piston rod snap ring are both pasted with a felt pad structure.

The long-rod rocker arm parts deflection angle measuring instrument includes a circular rubber suction cup 6-1, a suction cup pull rod 6-2, a pin shaft 6-3, a mounting support 6-4, a pressure handle 6-5, and a comprehensive indication of the inclination angle. 6-6, tilt angle integrated indicator 6-7, upper splint 6-8, lower splint 6-9, fastening screw 6-10, tilt angle synchronization indicator 6-11, transfer cable 6-12, lock Tightening bolts 6-13, horizontal columns 6-14, fixing screws 6-15 and tightening bolts 6-16;

The installation support 6-4 is the main body of the installation, and its lower two ends are symmetrically dug with "bowl-shaped" depressions for arranging two circular rubber suction cups 6-1. The upper two ends of the installation support 6-4 are symmetrically provided with fork supports Arm; one end of the suction cup pull rod 6-2 is connected to the circular rubber suction cup 6-1 through the upper splint 6-8, the lower splint 6-9 and the fastening screw 6-10, and the other end is connected to one end of the pressure handle 6-5 through the pin 6 -3 is installed on the fork arm of the mounting support 6-4;

The inclination angle integrated indicator support base 6-6 is fixed on the installation support 6-4 for installing the inclination angle integrated indicator 6-7; the locking bolt 6-13 is located in the through hole on one side of the inclination angle integrated indicator support base 6-6 Inside, it is used to move and fix the integrated inclination indicator 6-7; the integrated inclination indicator 6-7 is a device that integrates measurement and indication functions, with a strong magnetic shell structure on one side, and an electronic indicator for real-time indication. The deflection angle of the long-rod rocker arm parts; the inclination synchronization indicator 6-11 is connected with the inclination comprehensive indicator 6-7 through the transfer cable 6-12, and the indication signal is transmitted in real time;

The horizontal column 6-14 is mounted on the mounting support 6-4 for leveling.

Further, the upper clamp plate 6-8 and the lower clamp plate 6-9 are respectively located on both sides of the circular rubber suction cup 6-1, and the fastening screws 6-10 pass through the three in turn to connect the suction cup pull rod 6-2.

Further, the transfer cables 6-12 are high-conductivity cables with shielding layers.

The manual control mechanism force measuring device includes a hand-held control box 7-1, a data transmission line 7-2, a box body 7-5, a support rod 7-6, a connecting hinge mechanism 7-7, a transmission rod 7-8, and an execution rod 7-9, load bearing parts 7-10, force sensor 7-11 and handle bushing 7-12;

The box 7-5 is used to place the drive equipment and power supply wiring harness of the equipment. There are data receiving interfaces 7-3 and reserved interfaces 7-4 on the outside, and batteries 7-13, driving motors 7-14 and electric mechanisms are arranged inside. 7-15; The handheld control box 7-1 is connected to the data receiving interface 7-3 through the data transmission line 7-2, and the reserved interface 7-4 is used to connect external devices to realize data transmission; the battery 7-13 is the driving motor 7-14 Power supply for driving motor mechanism 7-15;

The electric mechanism 7-15 is connected to one end of the support rod 7-6, the other end of the support rod 7-6, the transmission rod 7-8, and the execution rod 7-9 are supported and connected by a connecting hinge mechanism 7-7, and the support rod 7-6 is connected to the The transmission rod 7-8, the transmission rod 7-8 and the execution rod 7-9 are in a mutually vertical position relationship; the connecting hinge mechanism 7-7 is a right-angle adapter; the execution rod 7-9, the force-bearing part 7-10, the force value The sensor 7-11 and the handle bushing 7-12 are connected in sequence; the execution rod 7-9 transmits the force, which is used to drive the force-bearing part 7-10, the force sensor 7-11 and the handle bushing 7-12 to move, the force sensor 7-11 realizes the force value measurement and displays the force value, the handle bushing 7-12 is used to connect and fix the device to the handle of the hand-opening mechanism; the battery 7-13 is used to provide electrical energy for the device;

The handheld control box 7-1 is provided with a power display, a power switch and a device drive microswitch.

The comprehensive measuring device for the pedals of the aircraft control system includes a dial 8-1, a scale indicator 8-2, a mooring rope 8-3, a stroke measuring rod 8-4, a fixing bolt 8-5, and a craft pedal 8-6 , pressure sensor 8-7, digital display angle measuring device 8-8, fixed support 8-9, signal output cable 8-10 and numerical display 8-11;

One end of the stroke measuring rod 8-4 is fixed on the process pedal 8-6, the other end is provided with a dial 8-1, and the scale indicator 8-2 is connected to the stroke measuring rod 8-4 through the mooring rope 8-3 to prevent loss , and slide in the area of the dial 8-1; one side of the process pedal 8-6 is used to withstand the external force applied by the operator, and the other side is connected to the pressure sensor 8-7; the fixed support 8-9 is L-shaped and fixed on the aircraft pedal On one side, the pressure sensor 8-7 is connected, and the other side is connected to the digital display angle measuring device 8-8; the pressure sensor 8-7 and the digital display angle measuring device 8-8 are connected through the signal output cable 8-10 To the numerical display 8-11, it is used to display the bearing force and deflection angle of the pedals of the aircraft.

The joystick transmission system idle travel measuring instrument includes a comprehensive measurement indicating device 11, a moving contact state acquisition device and a static contact state acquisition device;

The comprehensive measurement indicating device 11 displays the deflection and displacement of the measurement object in real time through the digital display device, which is fixed on the joystick in the transmission rod system through the fixing device; the fixing device includes a clamping fixing device 1, an opening adjuster 2, a locking Nut a3, flexible support arm clamping device 4, flexible adjustment support arm a5, ball head arm locking device 6, ball head connecting support arm 7, locking nut b8, integrated measurement indicating device holder 9 and locking screw 10 ; Clamping and fixing device 1 and opening adjuster 2 constitute a clamping device as the fixed end of the fixing device; one end of the flexible adjusting arm a5 is connected to the clamping and fixing device 1 through the locking nut a3, and the other end is connected to the clamping and fixing device 1 through the ball head arm The locking device 6 is connected to the ball head connecting arm 7; the flexible arm clamping device 4 is installed on the flexible adjusting arm a5 for fixing; the ball head connecting arm 7 is connected to the comprehensive measurement indicating device through the locking nut b8 The fixing base 9, the integrated measurement indicating device 11 is fixed under the integrated measuring indicating device fixing base 9 through the locking screw 10;

The movable contact state acquisition device 13 is L-shaped, the movable contact elastic support arm adjuster 12 passes through one side thereof, and the movable contact elastic support arm 14 is fixed on the other side; the movable contact elastic support arm adjuster 12 It is used to adjust the position of the movable contact elastic support arm 14. The movable contact elastic support arm 14 converts the mechanical displacement signal into an electrical signal and transmits it to the movable contact state acquisition device 13; the remote synchronization indicator 15 is installed in the movable contact state The collecting device 13 is used to sense the contact between the elastic support arm 14 of the movable contact and the elastic support arm 24 of the static contact; the installation device of the moving contact state collecting device 13 includes a clamping device 16, a tension adjusting device 17, a locking device Nut c18, spherical adjustment locking device 19, universal connection arm 20, locking nut d21, flexible arm locking device 22 and flexible adjusting arm b23; clamping device 16 and tension adjusting device 17 constitute a measuring support One end of the flexible adjustment arm b23 is connected to the clamping device 16 through the locking nut c18, and the other end is connected to the universal connection arm 20 through the spherical adjustment locking device 19; the flexible arm locker 22 is installed on the flexible adjustment arm On b23, it is used for fixing; the universal connection arm 20 is connected to the moving contact state acquisition device 13 through the locking nut d21;

The static contact state acquisition device 25 is installed on the execution part of the transmission rod system terminal, one side of which is connected to the static contact elastic support arm 24, and the other side is fixed on the static contact fixed support 28 through the fixing screw 26; the static contact The elastic support arm 24 converts the mechanical displacement signal into an electrical signal and transmits it to the static contact state acquisition device 25; the static contact fixed support 28 and the clamping lock 27 constitute a fixed device;

Both the moving contact state collecting device 13 and the static contact state collecting device 25 are connected to the comprehensive measurement indicating device 11 through the transfer cable 29 to transmit electrical signals.

Further, the clamping and fixing device 1, the clamping device 16 and the stationary contact fixing support 28 are all U-shaped, including two parallel sides and a vertical side; the clamping and fixing device 1, the clamping device 16 and the One of the parallel sides of the stationary contact fixing support 28 passes through the opening adjuster 2, the tension adjusting device 17 and the clamping lock 27 respectively, and the vertical sides respectively fix the lock nut a3, the lock nut c18 and the static contact Head state acquisition device 25 .

Further, the ball joint support arm 7 and the universal joint support arm 20 can be rotated arbitrarily within a range of 360°. After rotating to the target angle, the ball joint support arm locking device 6 and the spherical adjustment locking device are respectively used. 19 Positioning.

Further, when the elastic support arm 14 of the movable contact and the elastic support arm 24 of the static contact ensure the original position, they overlap up and down; the circular probes of the two ensure stress-free contact during measurement.

Beneficial effects of the present invention:

(1) The invention technology is a comprehensive application technology for the integration and testing of the aircraft emergency rescue system, flight control system and human-sensing control system. It divides the testing content of the aircraft's general assembly through scientific and reasonable quadrant rules, and designs and improves special tools and equipment. It is applied in various fields of various systems to break down the existing inspection points and difficulties of the aircraft general assembly system one by one, which not only optimizes the existing measurement methods and operation procedures, not only ensures that the accuracy of the inspection results data is increased by more than 3 times, but also makes The overall work efficiency is increased by at least 2 times.

(2) The main advantage of technical application in the field of accurate component assembly and inspection is to verify the accuracy and stability of the measurement and inspection of each system component, and to use special tools to perform the pre-installation or post-installation status of the components to be tested in each system more efficiently and conveniently. , more accurate measurement and verification, so that its main functions can be better played.

(3) The main advantage of technical application in the field of real-time dynamic monitoring is to convert the dynamic detection data of each system into more intuitive and accurate easy-to-read values, and to display the real-time update parameters that need to be compared and tested synchronously, making the detection environment closer in the real operating environment.

(4) The main advantage of technical application in the field of precise variable detection is the efficient and convenient measurement of the movement of various system components to generate process quantity data. Using the cooperation of the assembly and debugging environment and special tools and equipment, the complex data that is difficult to be measured by traditional tools can be obtained, and the goal of improving the measurement efficiency and detection accuracy is achieved.

(5) The inventive technology replaces the conventional detection difficulties in a number of measurement items with tools and equipment, realizes the inter-professional and cross-field tool interoperability, and integrates the previous general tool measurement methods into an integrated innovative scientific measurement method, effectively Reduce routine measurement errors and improve assembly inspection efficiency.

(6) From the advanced nature of measurement technology and the multi-facetedness, convenience, and accuracy of measurement tooling, the inventive technology comprehensively solves various difficult detection technical problems in the current aircraft assembly system. It can not only greatly reduce the operator's work intensity and the number of personnel, but also assist the operator to complete various production tasks with high quality and high efficiency on the premise of improving the accuracy of assembly and adjustment and safety and reliability.

Description of drawings

Fig. 1 is the left side view of the auxiliary installation device of the aircraft safety valve;

Fig. 2 is the right side view of the auxiliary installation device of the aircraft safety valve;

Figure 3 is a schematic diagram of the installation of the auxiliary installation device of the aircraft safety valve;

Fig. 4 is the relative position diagram of the auxiliary installation device of the aircraft safety valve and the safety valve bracket;

FIG. 5 is an overall schematic diagram of the auxiliary installation device of the aircraft safety valve, the safety valve bracket and the clamping clamp.

FIG. 6 is a schematic diagram of the apparatus 1 of the present invention.

FIG. 7 is a schematic diagram of the apparatus 2 of the present invention.

Fig. 8 is the overall schematic diagram of the unlocking stroke measuring device for aircraft parts;

9 is a schematic diagram of a clamping mechanism;

Figure 10 is a schematic diagram of the application reading of the unlocking stroke measuring device for aircraft parts.

Figure 11 Overall design of the equipment.

Figure 12 Schematic diagram of the structure of the sliding roller and the roller pin.

Figure 13 is a schematic diagram of the structure of the moving pointer.

Figure 14 Parts measurement state.

Fig. 15 is the overall schematic diagram of the device for measuring the extension of the piston rod of the aircraft actuating cylinder;

Fig. 16 is the partial schematic diagram of the aircraft actuating cylinder piston rod extension measuring device;

Figure 17 is a schematic diagram of the installation of the device for measuring the extension of the piston rod of the aircraft actuator.

18 is a front view of the present invention;

Figure 19 is a top view of the present invention;

FIG. 20 is a schematic diagram of the connection of the tilt synchronization indicator according to the present invention.

Figure 21 is a schematic diagram of a manual operating mechanism force measuring device;

Figure 22 is a top view of the force measuring device of the manual operating mechanism.

FIG. 23 is a schematic diagram of a comprehensive measuring device for pedals of an aircraft control system according to the present invention.

Figure 24 is a schematic diagram of a comprehensive measurement indicating device and its fixing device;

25 is a schematic diagram of a moving contact state acquisition device and an installation device thereof;

Figure 26(a) is a schematic diagram of a static contact state acquisition device and its fixing device;

Figure 26(b) is a schematic diagram of the transfer cable.

FIG. 27 is a specific flow chart of a specific embodiment of the present invention.

In the picture: 1-1 backing plate, 1-2 fixing bolt support slider, 1-3 baffle support slider, 1-4 baffle support, 1-5 fixing bolt support, 1-6 adjusting bolt , 1-7 fixing nut, 1-8 bushing, 1-9 bushing felt pad, 1-10 baffle felt pad, 1-11 baffle support adjusting screw, 1-12 fixing bolt support adjusting screw, 1 -13 pad felt pads.

2-1 Aircraft End Connector, 2-2 Aircraft End Hose, 2-3 Tee Connector, 2-4 Combination Conduit A, 2-5 Adapter A, 2-6 Digital Pressure Gauge A, 2-7 Combination Conduit B, 2-8 adapter B, 2-9 one-way valve, 2-10 adapter C, 2-11 combined conduit C, 2-12 manual shut-off valve, 2-13 gas source end hose, 2-14 gas Source end connector, 2-15 digital pressure gauge B, 2-16 adapter D, 2-17 combined conduit D, 2-18 manual stop valve, 2-19 detection end hose, 2-20 detection end connector.

3-1 Left fixing frame, 3-2 Right fixing frame, 3-3 Quick release bolt, 3-4 Turning nut, 3-5 Lower stop base, 3-6 Moving bracket, 3-7 Felt pad, 3- 8 lead screw, 3-9 driven gear, 3-10 upper stop base, 3-11 rotary handle, 3-12 scale rod, 3-13 polished rod, 3-14 shaft, 3-15 main gear, 3-16 Turn the pin.

4-1 equipment base; 4-2 scale; 4-3 slide rail with groove; 4-4 moving pointer; 4-5 small fixing screw; 4-6 large fixing screw; 4-7 base bezel; 4-8 Outer slide rail; 4-9 sliding support; 4-10 extension link; 4-11 optional joint; 4-12 fixed support; 4-13 detachable joint; 4-14 information plate; 4-15 sliding roller ; 4-16 roller pins.

5-1 Upper snap ring of actuator cover, 5-2 Lower snap ring of actuator cover, 5-3 Upper snap ring of piston rod, 5-4 Lower snap ring of piston rod, 5-5 Long slide rail, 5-6 Slider, 5-7 fixed support, 5-8 short rail, 5-9 digital vernier caliper, 5-10 caliper top wire, 5-11 support top wire, 5-12 slider top wire, 5-13 Piston rod snap ring fixing bolt, 5-14 actuator cover snap ring fixing bolt, 5-15 slide rail fixing nut.

6-1 round rubber suction cup, 6-2 suction cup pull rod, 6-3 pin shaft, 6-4 mounting support, 6-5 pressure handle, 6-6 inclination angle integrated indicator support base, 6-7 inclination angle integrated indicator , 6-8 upper splint, 6-9 lower splint, 6-10 fastening screws, 6-11 inclination synchronization indicator, 6-12 transfer cable, 6-13 locking bolt, 6-14 horizontal column, 6- 15 fixing screws, 6-16 fastening bolts.

7-1 Handheld control box, 7-2 Data transmission line, 7-3 Data receiving interface, 7-4 Reserved interface, 7-5 Box, 7-6 Support rod, 7-7 Connecting hinge mechanism, 7-8 Transmission Rod, 7-9 executive rod, 7-10 load bearing parts, 7-11 force sensor, 7-12 handle bushing, 7-13 battery, 7-14 drive motor, 7-15 motor mechanism.

8-1 dial, 8-2 scale indicator, 8-3 mooring rope, 8-4 stroke measuring rod, 8-5 fixing bolt, 8-6 craft pedal, 8-7 pressure sensor, 8-8 digital display Angle measuring device, 8-9 fixed support, 8-10 signal output cable, 8-11 numerical display.

1 clamping device, 2 opening adjuster, 3 locking nut a, 4 flexible arm clamping device, 5 flexible adjusting arm a, 6 ball joint arm locking device, 7 ball joint connecting arm, 8 Lock nut b, 9 fixed seat of comprehensive measurement indication device, 10 locking screw, 11 comprehensive measurement indication device, 12 movable contact elastic support arm adjuster, 13 movable contact state acquisition device, 14 movable contact elastic support arm, 15 remote synchronization indicating device, 16 clamping device, 17 tension adjusting device, 18 locking nut c, 19 spherical adjusting locking device, 20 universal connecting arm, 21 locking nut d, 22 flexible arm locking device , 23 flexible adjustment arm b, 24 static contact elastic support arm, 25 static contact state acquisition device, 26 fixed screw, 27 clamping lock, 28 static contact fixed support, 29 transfer cable.

Detailed ways

The technical solutions of the present invention are further described below through the examples.

The invention integrates and summarizes the relevant requirements of the important assembly inspection of the emergency rescue system, the flight control system and the human-sensing control system in the general assembly stage, divides the quadrant according to the inspection method and state and the corresponding system, and rationally optimizes and integrates the special inspection tools and equipment. , so that it can be applied to all types of inspection processes under the corresponding system state, so as to realize the application of innovative process methods for integrated scientific inspection and measurement.

The integrated detection method of the aircraft general assembly system, according to the aircraft emergency rescue system, the aircraft flight control system, the aircraft human-sensing control system and its three inspection and measurement states, the whole workflow of the integrated inspection of the aircraft general assembly system is divided into 3 × 3 quadrants , and the corresponding relationship is shown in Table 1:

Table 1 Division of the three major system detection work quadrants

Precise inspection of components Real-time dynamic monitoring Precise variable detection emergency rescue system Precise installation of the finished life-saving system Lifesaving system working pressure monitoring Lifesaving system unlocking stroke measurement flight control system Precise inspection of flight control system rods Precise detection of flight control system servo Flight control system deflection angle measurement human control system Control system joystick force measurement Control system pedal comprehensive test Control system free travel measurement

Among them, the abscissa is the inspection and measurement state and method, and the ordinate is the three major systems involved in the inspection work. According to the abscissa, the innovative process method application analysis of integrated scientific inspection and measurement is carried out:

(1) The field of precise assembly and inspection of components

This field is used in the precise measurement and auxiliary assembly of the installed finished products, parts, assemblies and other components during the installation process. In the initial installation stage of each system component, the assembly accuracy is guaranteed, the assembly and inspection efficiency is improved, and the scientific and standardized inspection method can effectively ensure the accuracy, reliability and consistency of the component positioning. Through scientific and innovative detection methods, the installed status of components is reasonably verified to ensure that each component can perform its performance stably and effectively.

(2) Real-time dynamic monitoring field

This field is used in the debugging and testing link after the assembly of related components is completed. In this link, the difficulty of inspection and acceptance lies in real-time recording and comparison of changing experimental data, and converting the generated data into more intuitive, more accurate, and easier-to-read information during the operation of each component of the system according to the preset instructions. , which will effectively improve the efficiency and accuracy of debugging and detection, and reduce the frequency of system failures and the difficulty of system adjustment.

(3) The field of precise variable detection

This field is applied to the verification of results after each functional accessory of the system executes relevant instructions. When the component is deflected, displaced and deformed according to the system command, its position and state are more difficult to measure with general-purpose testing tools than the original state. In order to obtain the state change of the component to be measured before and after the execution of the command more efficiently, conveniently and accurately, special fixtures are designed for different system components in this field to improve the accuracy and efficiency of process change data acquisition.

The integrated detection method of the aircraft general assembly system, the specific method is as follows:

Step 1. The integrated innovative installation and detection process of the emergency rescue system is mainly realized from the following relevant steps:

(1) Installation of finished safety valves for emergency rescue systems:

The finished safety valve of the aircraft's emergency rescue system is installed at the perforation of the aircraft cabin wall panel to keep the cabin pressure at the pilot's comfortable state. The main view of the finished product is a circle, and the side is a conical arc transition, so its installation position, matching relationship, fixed clearance and other indicators have relatively precise and strict requirements. When installing the finished product, install the auxiliary installation device of the aircraft safety valve on the finished product correctly in advance, install the safety valve with the device according to the relevant requirements and complete the clamp fixing, check the edge clearance between the finished product and the clamping clamp, which should meet the related requirements. The installation of the device shall be maintained after the installation and inspection work is completed, and during the subsequent inspection of the performance of the safety valve, the edge clearance shall not be significantly changed after repeated inspections. After recording the value, remove the aircraft safety valve auxiliary mounting device from the finished product.

(2) To monitor the working pressure of the emergency rescue system:

After the installation of the safety valve products of the whole aircraft emergency rescue system, the air tightness of the cockpit, the structural strength of the cockpit, the function of the hatch cover control system, the air tightness of the hatch cover control system, the air tightness of the emergency rescue system, and the emergency rescue system shall be performed. Aircraft portable inflatable and testing equipment can be used for performance and other related inspections. Before the test of each item, if the gas filling work is involved, one end of the aircraft portable inflation and testing test equipment is connected to the inflatable nozzle connector on the aircraft through the optional joint, and the other end is connected to the special inflatable tooling equipment. Connect the port of the aircraft's portable inflation and testing test equipment to the testing pipeline port of the on-board system through the optional connector, and close the manual shut-off valve.

Provide air pressure to the onboard system through the inflatable equipment. At this time, the gas inlet pressure can be judged according to the value shown on the digital display pressure gauge on the portable inflatable and detection test equipment of the aircraft (the pressure value is only used as an auxiliary reference for the operation of the gas input terminal, and does not mean that the system works After the system works stably, the gas pressure in the system is judged by the value shown on the digital pressure gauge on the portable inflatable and testing equipment of the gas outlet, and the relevant data records are completed and the function inspection and performance indicators of each system are carried out successively. detection.

(3) Carry out the measurement of the unlocking stroke of the emergency rescue system:

This work can be performed in conjunction with the above-mentioned work performance of the emergency rescue system and other related inspections. Use the inflatable equipment to co-pressurize the emergency rescue system to the stable working index range, and check that the explosion and explosion mechanism can be unlocked normally within the allowable pressure range. If all the inspections related to inflation have been completed at this time, the connection of the aircraft parts unlocking stroke measuring device can be disconnected after exhausting and the installation state on the original aircraft can be restored.

Install the aircraft parts unlocking stroke measuring device on the restored blasting mechanism, record the initial scale value, and operate the measuring tool to make the components of the blasting mechanism move to the just unlocked state. At this time, the difference between the scale value and the initial scale value The value is the part unlocking stroke. Record this value and remove the aircraft parts unlocking travel measuring device, and restore the installation of the explosion mechanism.

Step 2. The integrated innovative installation and detection process of the flight control system is mainly realized from the following relevant steps:

(1) Carry out the assembly inspection and measurement of the flight control system rod parts:

There are various shapes of rod-like parts of the flight control system, which play a key role in the transmission of signals and instructions in the whole system. Before the relevant supporting installation work, the precise measurement test bench for the special-shaped joystick of the aircraft can be used to accurately ensure the accuracy of various types of rod-like parts. Assembly length. According to the type and size of the connecting rod joint to be tested, the test bench joint is selected, and the extension of the connecting rod joint to be tested is adjusted according to the measurement results to change the length of the connecting rod. After the length meets the requirements of the assembly drawings, the insurance work is completed and the connection is installed. . Complete the installation of all the adjustable rods with fixed length requirements of the flight control system in the same way.

(2) Carry out the dynamic detection of the flight control system servo actuator stroke:

As an executive component in the flight control system, the working performance of the servo actuating device directly affects the working state of each rudder surface of the aircraft, and is an important part of the aircraft's basic flight ability. During the commissioning and testing, the protruding amount of the piston rod of the servo actuator can be verified by the aircraft actuator piston rod protruding amount measuring device. Make sure that the flight control system has the full-state debugging and testing conditions, select the appropriate upper and lower snap rings according to the outer dimensions of the servo actuation device to be tested and its piston rod, install the measuring device on the servo actuation device to be tested, and pass the system command The input makes the servo actuating device perform telescopic movement, and it is verified that its dynamic stroke meets the relevant performance index requirements in real time.

(3) Carry out the inspection and measurement of the deflection angle of the long-rod rocker arm parts of the flight control system:

This work can be carried out in conjunction with the above-mentioned inspections related to the working performance of the servo actuating devices of the flight control system. During the debugging and testing of the aircraft flight control system, some aircraft types need to measure and verify the deflection angles of some long-rod rocker arm parts controlled by hydraulic pressure under different working pressures. The arm part deflection angle measuring instrument is assisted. After the flight control system has the full-state debugging and testing conditions, place the long-rod rocker arm part deflection angle measuring instrument in the measurement area, operate the measured part to move it to the initial position, and fix the measuring instrument on the long-rod rocker arm on the measuring point of the part. Accurately install the integrated inclination indicator and adjust it to the zero position. After operating the measured part to move it to another state, the actual deflection angle of the part is recorded through the numerical change of the inclination synchronization indicator. Continue to make precise measurements of other deflection angular positions of this part in the same manner.

Step 3. The integrated innovative installation and detection process of the human-sensing control system is mainly realized from the following relevant steps:

(1) Measure the deflection force of the handle device of the control system:

In the human-sensing control system, the handle-like device is used to provide the driver with a manipulation feeling and transmit the manipulation command to the link mechanism. The manual operating mechanism force measuring device can not only be applied to the operating force measurement of the canopy opening mechanism, but also can be applied to the operating force measurement of the handle parts of other operating systems. Install the handle sleeve in the equipment on the measuring point of the handle to be tested, turn on the power of the equipment and deflect the handle device to the designated position according to the test requirements, record and check whether the operating force meets the relevant requirements through the value shown on the force value display.

(2) Measure the deflection stroke and deflection force of the pedal device of the control system:

The pedal device in the human-sensing control system is an important control accessory, and the difficulty in its debugging and detection lies in the synchronous measurement of the deflection stroke and deflection force. During this work, the comprehensive measurement device for the pedal of the aircraft control system will greatly Reduce operational difficulty and improve measurement accuracy. First, install the equipment on the pedal mechanism assembly, and complete the connection of the numerical display, the digital display angle measuring device, the sensor, etc. Fix the pedal system in the neutral position with the neutral positioning rod, and adjust the scale indicator and the pressure value display to zero at this time. Remove the neutral positioning rod and manipulate the pedal mechanism to deflect until the value of the scale indicator reaches the measurement position and stop the deflection and record the pressure value shown on the numerical display at this time. Complete the test and comparison of all deflection positions and corresponding deflection forces successively.

(3) Carry out the measurement of the free travel of the lever system of the control system:

This work can be performed in combination with the above-mentioned work of measuring the deflection stroke and deflection force of the pedal device of the manipulation system. The aircraft control system is a complex multi-rod combined transmission mechanism. Due to its main mechanical connection and the manufacturing tolerances of the connecting rods and related parts, there will be a small gap in the connection method between the fixed points. After the full state assembly, due to this tolerance The accumulation of clearance results in a certain amount of free travel (ie, idle travel) for the entire rod system. The free travel of the effective control lever system helps the control system to tend to the advantages of high precision and high response. After installing the relevant measuring equipment on the pedal mechanism, combine and install the joystick drive system idle travel measuring instrument on the measuring position of the joystick, fasten the remote drive feedback part on the structure around the actuator of the terminal, and slowly drive the The joystick moves until the remote actuator is just actuated. At this time, the displacement of the joystick is read through the indicator, and the free stroke measurement of each channel of the joystick is completed successively.

An auxiliary installation method for an aircraft safety valve, comprising the following steps:

1) When supporting on the ground, install the auxiliary installation device of the aircraft safety valve on the safety valve bracket, and move the fixed bolt support slider 1-2 and the baffle support slider 1-3 on the backing plate 1-1;

2) According to the position of the safety valve bracket, move the position of the groove of the adjusting bolt 1-6 on the fixing bolt support 1-5;

3) Adjust the baffle support adjustment screw 1-11 and the fixing bolt support adjustment screw 1-12, determine the height of the baffle support 1-4 and the fixing bolt support 1-5, so that the clamping clamp is away from the safety valve The gap value Amm;

4) After confirming that the bushing felt pads 1-9 on the bushings 1-8 and the damper pads 1-10 on the damper support 1-4 completely limit the safety valve bracket, tighten the adjusting bolts 1-6 and Fixing nuts 1-7;

5) The operator holds the safety valve with the auxiliary device and enters the rear panel of the cockpit in the rear equipment compartment; connects the safety valve with the flange to ensure the coaxiality;

6) Install the edge of the clamping clamp against the backing plate 1-1 to ensure the deflection of the clamping clamp;

7) Tighten the self-locking nut to complete the installation of the safety valve.

The method of using the aircraft portable inflatable and testing test equipment, the steps are as follows:

1) Check that the overall connection of the portable inflatable and testing equipment of the aircraft should be stable and reliable, the inside and outside of the test equipment shell, the system pipeline and the outside of the components should be clean, and the hose connection should be in good condition and free from damage, aging, cracking, etc. , digital pressure gauge A2-6, digital pressure gauge B2-15 should be within the regular inspection cycle, the above should meet the needs of use;

2) Rotate the screw switch of the manual stop valve 2-12 to the closed state, after removing the plug connecting the air supply pressure end connector, connect the aircraft end connector 2-1 to the air body inflation end; after removing the connecting air source end connector After plugging the cap, connect the air source end connector 2-14 to the air source end;

3) Rotate the manual shut-off valve 2-18 screw switch to the closed state, after removing the plug connecting the aircraft pressure detection end connector, connect the detection end connector 2-20 to the aircraft pressure detection end;

4) Check that the connections at the aircraft end connector 2-1, the air source end connector 2-14 and the detection end connector 2-20 should be tightened to avoid air leakage;

5) Rotate the screw switches of manual stop valve 2-18 and manual stop valve 2-12 to the open state, slowly supply pressure to the aircraft, and observe the air supply through digital pressure gauge A2-6 and digital pressure gauge B2-15 respectively. The end pressure is P1 MPa and the internal pressure of the aircraft is P2 MPa. When the test requirements are met, the manual stop valve 2-12 screw switch can be turned to the closed state to stop the pressure supply; The air tightness test is carried out for the change of the pressure P3 MPa of the digital pressure gauge B2-15;

6) After completing the relevant work, disconnect the connecting end, put away the portable inflatable and testing equipment of the aircraft, restore the installation of the plug cap at the joint, ensure the sealing, prevent dust and liquid pollution, and restore the aircraft state.

A method for measuring the unlocking stroke of aircraft parts, comprising the following steps:

1) Loosen the quick release bolts 3-3, turn the left fixing frame 3-1 and the right fixing frame 3-2, and open the clamping area of the part unlocking stroke measuring device; first move the right fixing frame 3-2 close to the cylinder to be installed face, turn it along the cylindrical surface, move the left fixing frame 3-1 to the desired position; fix the quick release bolt 3-3;

2) Install the lower stop base 3-5 with moving bracket 3-6, felt pad 3-7, lead screw 3-8 and turning handle 3-11 to the aircraft part from one side, rotate the turning handle 3 -11 Adjust the position of the moving bracket 3-6 so that it is below the moving end of the part and has a certain gap with the part;

3) Pre-tighten the work before the inspection, first turn the rotating handle 3-11 counterclockwise, so that the moving bracket 3-6 slowly approaches the moving end of the part, and stop rotating the rotating handle 3-11 when the two are in contact;

4) Carry out the inspection of the unlocking stroke of the parts, first read the current position data Amm through the scale line engraved on the scale rod 3-12 and the scale pointer on the moving bracket 3-6, and then turn the rotary handle 3-11 counterclockwise , the moving bracket 3-6 drives the moving end of the part to move, until the moment of unlocking stops rotating the rotating handle 3-11, and the scale data B mm is read at this time. At this time, the unlocking stroke of the part is C=B-A mm.

How to use the aircraft special-shaped joystick accurate measurement test bench, the steps are as follows:

1) Before the pre-installation measurement of the special-shaped joystick of the aircraft, it is necessary to obtain the joystick parts and check that the surface should be free from damage and the stability of the assembly, and select the detachable joints 4-13 and 4-13 according to the fixed form and aperture at both ends of the joystick. Matching connector 4-11;

2) Put the aircraft special-shaped joystick precise measurement test bench on the flat table, and install the selected detachable joint 4-13 and optional joint 4-11 on the fixed support 4-12 and the sliding support 4-9 respectively. , if necessary, install the extension connecting rod 4-10;

3) Freely rotate the detachable joint 4-13 to match the position of the special-shaped joystick joint of the aircraft;

4) Freely slide the sliding support 4-9, so that the optional joint 4-11 can be smoothly inserted into another joint of the joystick under test;

5) Install the joystick to be measured on the test bench from top to bottom, read out the length of the joystick at the position of the scale 4-2 by moving the pointer 4-4 to be A ₁ mm, and complete the record;

6) When the length of the joystick A ₁ mm does not meet the requirements, remove the lever and complete the adjustment work, re-measure according to steps 3-5, read out the value of A ₂ mm and compare until the length of the joystick meet the parameter requirements;

7) The insurance work of the joystick can be completed directly on the equipment, and the parts can be removed after the insurance is completed, and the connection on the machine can be completed according to the relevant requirements.

A method for measuring the extension of a piston rod of an aircraft actuating cylinder, which specifically includes the following steps:

1) The operator shakes the handle of the manual opening mechanism and slowly opens the movable canopy; when the "close canopy" signal light on the display panel turns from on to off, install the aircraft actuator piston rod extension measuring device on the on the actuator cover and the piston rod nut;

2) Straighten the digital display vernier caliper 5-9, tighten the caliper top wire 5-10 to fix it on the fixed support 5-7; tighten the support top wire 5-11 to fix the fixed support 5-7;

3) Turn on the power button 5-9 of the digital vernier caliper and reset to zero;

4) The operator continues to shake the handle of the manual opening mechanism and slowly open the movable canopy until it is fully opened;

5) Open the reading on the digital vernier caliper 5-9, that is, the extension of the piston rod from the dead point of the open state is A mm.

A method for measuring the deflection angle of a long-rod rocker arm part, which specifically includes the following steps:

1) The operator on the aircraft prepares the aircraft for ground debugging according to the requirements of the debugging document, and powers up the entire aircraft. The operator on the ground debugging platform adjusts the working pressure of the debugging platform to P1 to provide a pressure source for the aircraft;

2) The operator on the plane controls the button of the corresponding long-rod rocker arm part on the aircraft to the "down" position, and the long rod-type part will be driven by the hydraulic source to be in the "down" position;

3) The operator of the ground debugging platform reduces the working pressure of the debugging platform to "0MP";

4) The operator of the ground debugging platform adjusts the position of the pressure handle 6-5 so that the horizontal bubble of the horizontal column 6-14 is in the middle position, and then presses the adjustment pressure handle 6-5 to fix the measuring instrument on the long-rod rocker arm on the measuring point of the part;

5) Connect the transition cables of the inclination comprehensive indicator 6-7 and the inclination synchronization indicator 6-11 according to the cable numbers X1 and X2, and then adjust the locking bolts 6-13 to install the inclination comprehensive indicator 6-7 accurately Put it on the support base 6-6 of the comprehensive inclination angle indicator and lock it, and then turn on the power through the "ON/OFF" button of the comprehensive inclination angle indicator 6-7, and the "ZERO" button will reset its initial position to zero;

6) The operator holds the inclination synchronization indicator 6-11 to the ground hydraulic debugging platform, and informs the operator on the machine to switch the button switch of the long-rod rocker arm part to the "retracted" position;

7) The operator of the ground hydraulic debugging platform gradually increases the working pressure of the debugging platform. At this time, the operator pays attention to observe the deflection change of the long-rod rocker arm parts through the inclination angle synchronization indicator 6-11. When the deflection angle ∠A1 is reached, the Record the working pressure P2 of the hydraulic debugging platform in time;

8) The operator continues to gradually increase the working pressure of the debugging table, and in turn completes the deflection state of the long-rod rocker arm parts in the deflection state of ∠A2, ∠A3, ∠A4, and ∠A5, and records the corresponding working pressure of the ground hydraulic debugging table P3, P4, P5, P6;

9) When the measurement work is over, first reduce the working pressure P1 of the ground hydraulic debugging platform to 0, and then the operator on the plane discharges the pressure to power off the aircraft;

10) The operator of the ground debugging platform adjusts the position of the pressure handle 6-5, removes the measuring instrument from the machine, and puts it in the designated position, that is, the whole measuring work is over.

A method for measuring force of a manual operating mechanism, comprising the following steps:

1) Install the handle bushing 7-12 on the handle of the mechanism to be opened;

2) Turn the power switch to the "on" position, "zero" the force sensor 7-11, and check that the force value is "0N" through the force display;

3) Drive the micro switch by adjusting the device, and drive the electric mechanism 7-15 to move up and down, thereby driving the handle of the mechanism to be opened; during the entire movement process, check the force value through the force value display, and record the force value A1 in each state , A2, A3....;

4) After the inspection work, turn the power switch to the "off" position, and remove the handle bushing 7-12.

A method for comprehensively measuring pedals of an aircraft control system, which specifically includes the following steps:

1) Install the neutral device in the vertical hole of the pedal mechanism, so that the pedal is in a neutral position, and the pedal cannot move in this state;

2) After assembling the comprehensive measuring device of the pedal of the aircraft control system, install it on the pedal of the aircraft through the fixed supports 8-9;

3) The operator holds the numerical display 8-11 and the scale indicator 8-2, manually sets the zero position, and records the corresponding position A1 of the scale indicator 8-2 on the dial 8-1 at this time;

4) Turn on the switches 8-11 of the numerical display, at this time the display shows the force value and the angle value. After selecting the real-time force value mode or the peak force value mode as required, press the zero adjustment button to adjust the initial zero position;

5) Remove the neutral device from the pedal;

6) The operator places the foot on the craft pedal and applies force to make the pedal move;

7) The displacement generated by the stroke measuring rod 8-4 drives the dial 8-1 to move. The operator reads the scale indicator 8-2 on the scale according to the relative displacement generated by the dial 8-1 and the scale indicator 8-2. The corresponding position value A2 on the plate 8-1, at this time, the pedal stroke A=A1-A2;

8) When the pedal displacement value is in accordance with the technical requirements of aircraft debugging, the force value displayed by the numerical display 8-11 is the force value under the displacement of the pedal, and the displayed angle value is the pedal under the modified displacement. The deflection angle is obtained by the operator directly observing the display screen.

A method for measuring idle travel of a joystick transmission system, comprising the following steps:

1) Adjust the opening adjuster 2 to clamp the clamping fixture 1 on the mechanical structure near the joystick;

2) Adjust the locking screw 10, clamp the probe rod of the integrated measurement indicating device 11 in the mounting hole of the integrated measuring indicating device holder 9, and then lock it by the locking screw 10;

3) Adjust the joystick in the transmission rod system of the mechanical equipment to the neutral position, and then adjust the probe of the comprehensive measurement indicating device 11 to the measuring point of the joystick so that the two are in contact, and then adjust the flexible arm to clamp it. The locking device 4 and the ball head arm locking device 6 fix the position of the comprehensive measurement indicating device 11 and lock them;

4) Press "ON/OFF" of the comprehensive measurement indicating device 11 to enter the boot interface;

5) Adjust the tension adjusting device 17 so that the clamping device 16 is fastened on the surrounding structure of the actuator at the end of the transmission rod system;

6) Adjust the clamping lock 27 so that the stationary contact fixing support 28 is fixed on the measurement point of the actuator at the end of the transmission rod system;

7) Adjust the position of the moving contact state acquisition device 13 so that the circular probe of the elastic support arm 14 of the moving contact and the circular probe of the elastic support arm 24 of the static contact contact each other on the motion track of the actuator at the end of the transmission rod system , and then adjust the spherical adjustment locking device 19 and the flexible arm locking device 22 to lock it;

8) Adjust the movable contact elastic support arm adjuster 12 so that the circular probe of the movable contact elastic support arm 14 is just in contact with the circular probe of the static contact elastic support arm 24, and the indicator light of the remote synchronization indicating device 15 is at this time. Just in the "burning" state;

9) According to the operation and debugging requirements, first clear the data through the "ZERO" key of the comprehensive measurement indicating device 11, and then slowly move the joystick by hand. At this time, pay attention to observe the indicator light of the comprehensive measuring indicating device 11 and the remote synchronization indicating device 15. In the status of the indicator light with the same function, when the indicator light is "off", stop moving the joystick, record the displacement value S1 in the comprehensive measurement indicating device 11, and then judge whether S1 is between the specified value X1-X2; Between the two, that is, the idle stroke of the rod system meets the requirements; the value S1 is the idle stroke from the joystick of a certain transmission rod system of the mechanical equipment to the terminal execution part; if the value S1 is not within the specified value X1-X2 , it is necessary to readjust the joystick system or replace the relevant transmission rod until S1 is between the specified value X1-X2.

Table 2 Schematic diagram of the quadrant of integrated detection technology solutions

Claims (10)

1. the integrated detection method of the aircraft general assembly system, it is characterized in that, according to the aircraft emergency rescue system, the aircraft flight control system, the aircraft human-sensing control system and its three kinds of inspection and measurement states, the whole work flow of the integrated detection of the aircraft general assembly system Proceed as follows: Step 1. The integrated detection process of the emergency life-saving system (1) Installation of finished safety valves for emergency rescue systems The finished product of the safety valve of the emergency rescue system of the aircraft is installed at the perforation of the aircraft cabin wall to keep the cabin pressure in a comfortable state for the pilot; the main view of the finished product is a circle, and the side is a conical arc transition; after installing the finished product When the aircraft safety valve auxiliary installation device is installed correctly on the finished product in advance, install the safety valve with the aircraft safety valve auxiliary installation device according to the relevant requirements and complete the clamp fixing. Check the edge clearance between the finished product and the clamping clamp. Meet the relevant requirements; keep the auxiliary installation device of the aircraft safety valve installed after the installation and inspection work is completed. During the subsequent inspection of the working performance of the safety valve, the edge clearance should not change significantly; after recording the value, remove the auxiliary installation device of the aircraft safety valve from the finished product. remove; (2) Monitor the working pressure of the emergency rescue system After the installation of the safety valve products of the whole aircraft emergency rescue system, the air tightness of the cockpit, the structural strength of the cockpit, the function of the hatch cover control system, the air tightness of the hatch cover control system, the air tightness of the emergency rescue system, and the emergency rescue system shall be performed. During the performance-related inspections, the aircraft portable inflation and testing equipment can be used; before each item test, if gas filling is involved, connect one end of the aircraft portable inflation and testing equipment to the on-board inflation nozzle through the optional joint. The other end is connected to the special inflatable tooling equipment; the port of the portable inflatable and testing equipment of the aircraft is connected to the inspection pipeline port of the on-board system through the optional joint, and the manual stop valve is closed; The air pressure is supplied to the on-board system through the inflatable device of the aircraft portable inflation and detection test equipment. At this time, the gas inlet pressure can be judged according to the value shown on the digital display pressure gauge on the aircraft's portable inflation and detection test equipment. The value shown on the digital pressure gauge on the portable inflatable and detection test equipment of the aircraft at the export end judges the gas pressure in the system, completes the relevant data recording, and successively performs the function inspection and performance index detection of each system through the detection device; (3) Carry out the measurement of the unlocking stroke of the emergency rescue system This work can be carried out in conjunction with the inspection work related to the working pressure performance of the emergency rescue system; the inflatable device of the aircraft portable inflatable and testing equipment is used to co-pressurize the emergency rescue system to the stable working index range, and the explosion mechanism can be checked within the allowable pressure range. Unlock normally; if all inspections related to inflation have been completed at this time, the connection of the aircraft parts unlocking stroke measuring device can be disconnected after exhausting and the installation state on the original aircraft can be restored; Install the aircraft parts unlocking stroke measuring device on the restored blasting mechanism, record the initial scale value, and operate the measuring tool to make the components of the blasting mechanism move to the just unlocked state. At this time, the difference between the scale value and the initial scale value The value is the part unlocking stroke; record the value and remove the aircraft parts unlocking stroke measuring device to restore the installation of the explosion mechanism; Step 2. Flight control system integration testing process (1) Carry out the inspection and measurement of the rod parts assembly of the flight control system Before the relevant supporting installation of the rod parts of the flight control system, use the aircraft special-shaped joystick to accurately measure the test bench to accurately ensure the assembly length of each type of rod parts; according to the type and size of the connecting rod joint to be measured The measurement test bench joint is optional, adjust the extension of the connecting rod joint to change the length of the connecting rod according to the measurement results, and complete the insurance work and install the connection after the length meets the requirements of the assembly drawing; complete the flight control system in the same way. Installation work of adjustable rods with fixed length requirements; (2) Carry out the dynamic detection of the travel of the servo actuator of the flight control system During the debugging and testing, verify the protruding amount of the servo actuator piston rod using the aircraft actuator piston rod protruding amount measuring device; ensure that the flight control system has the full-state commissioning and testing conditions, according to the servo actuator to be tested and its Select the appropriate upper and lower snap rings for the outer dimension of the piston rod, install the aircraft actuator piston rod extension measuring device on the servo actuating device to be tested, and make the servo actuating device perform telescopic motion through the system command input to check its The dynamic stroke meets the requirements of relevant performance indicators in real time; (3) Carry out the inspection and measurement of the deflection angle of the long-rod rocker arm parts of the flight control system This work can be carried out in conjunction with the inspection work related to the working performance of the servo actuating device of the flight control system; in the debugging and testing process of the aircraft flight control system, some aircraft types need to perform different inspections on some long-rod rocker arm parts controlled by hydraulic pressure. The deflection angle under the working pressure is measured and verified. This work can be assisted by the deflection angle measuring instrument of the long-rod rocker arm parts; after the flight control system has the full-state debugging and testing conditions, the long-rod rocker arm parts are deflected The angle measuring instrument is placed in the measuring area, and the measured part is operated to move to the initial position, and the deflection angle measuring instrument of the long-rod rocker arm part is fixed on the measuring point of the long-rod rocker arm part; Adjust to the zero position, operate the measured part to move to another state, record the actual deflection angle of the part through the numerical change of the inclination synchronization indicator; continue to accurately measure the other deflection angle positions of the part in the same way; Step 3. The integrated detection process of the human-sensing control system (1) Measure the deflection force of the joystick-like device of the human-sensing control system In the human-sensing control system, after the handle device is installed, it is necessary to check that its control force should meet the operating comfort range; the manual control mechanism force measuring device can not only be applied to the control force measurement of the canopy opening mechanism, but also to other control In the operation force measurement of system handle parts; install the handle bushing in the force measuring device of the manual operation mechanism on the measuring point of the handle to be tested, turn on the power of the equipment and deflect the handle device to the designated position according to the test requirements, and pass the force value Record the value shown on the display and check whether the operating force meets the relevant requirements; (2) Measure the deflection stroke and deflection force of the pedal device of the human-sensing control system The pedal device in the human-sensing control system is an important control accessory, and the difficulty in its debugging and detection lies in the synchronous measurement of deflection stroke and deflection force. On the pedal mechanism component, the connection of the numerical display, the digital display angle measuring device and the pressure sensor is completed; the pedal system is fixed in the neutral position through the neutral positioning rod, and the scale indicator and the pressure numerical display are adjusted to zero at this time; Neutralize the positioning rod and control the deflection movement of the pedal mechanism, until the scale indicator value reaches the measurement position, stop deflection and record the pressure value shown on the numerical display at this time; complete the test and comparison of all deflection positions and corresponding deflection forces successively; (3) Carry out the measurement of the free travel of the rod system of the human-sensing control system This work can be performed in combination with the measurement of the deflection stroke and deflection force of the pedal device of the human-sensing control system; after the relevant measuring equipment is installed in the pedal mechanism, the joystick transmission system idle travel measuring instrument is combined and installed at the measurement position of the joystick , fasten the remote transmission feedback part on the surrounding structure of the actuator of the terminal, and slowly drive the joystick to move until the remote actuator is just actuated. The free travel measurement of each channel of the joystick works. 2. The integrated detection method of the aircraft general assembly system according to claim 1, wherein the auxiliary installation device for the aircraft safety valve is installed between the safety valve and the clamping clamp, and comprises a backing plate (1- 1), fixing bolt support slider (1-2), baffle support slider (1-3), baffle support (1-4), fixing bolt support (1-5), adjusting bolt ( 1-6), fixing nut (1-7), shaft sleeve (1-8), shaft sleeve felt pad (1-9), baffle felt pad (1-10), baffle support adjustment screw (1- 11), the fixing bolt support adjustment screw (1-12) and the pad felt pad (1-13); The backing plate (1-1) is an arc-shaped plate with an L-shaped cross-section, including a horizontal side and a vertical side. The intersection of the two is an indented chute, which is used for limiting and clamping the clamp; fixing bolt support The slider (1-2) and the baffle support slider (1-3) move in the chute; the fixing bolt support slider (1-2) is installed with the fixing bolt support adjustment screw (1-12) The fixing bolt support (1-5) with the through slot; the adjusting bolt (1-6) is fixed by the fixing nut (1-7) after passing through the through slot of the fixing bolt support (1-5) and sleeved with a shaft sleeve (1-8); The baffle support (1-4) is installed on the baffle support slider (1-3) through the baffle support adjustment screw (1-11), and the baffle support (1-4) It is used to cooperate with the shaft sleeve (1-8) to limit the safety valve bracket. 3. The integrated detection method of the aircraft general assembly system according to claim 1 is characterized in that, the portable inflatable and detection test equipment of the aircraft comprises an inflation device and a detection device, and the inflation device and the detection device can be used independently, or can be used independently. Use in combination; The inflator is used for the input and output of gas, and includes an aircraft end joint (2-1), an aircraft end hose (2-2), a three-way joint (2-3), and a combined conduit B (2-2) connected in sequence. -7), adapter B (2-8), one-way valve (2-9), adapter C (2-10), combined conduit C (2-11), manual stop valve (2-12), air The source end hose (2-13), the air source end connector (2-14); and the combined conduit A (2-4) and the adapter A connected to the third connector of the tee connector (2-3) in sequence (2-5), digital display pressure gauge A (2-6); the air source end connector (2-14) is connected with the air source, and the aircraft end connector (2-1) is connected with the aircraft, through the air Source hose (2-13), manual stop valve (2-12), combined conduit C (2-11), adapter C (2-10), one-way valve (2-9), adapter B ( 2-8), combined conduit B (2-7), tee joint (2-3), aircraft end hose (2-2), aircraft end joint (2-1) to charge the gas in the air source to the The position where the aircraft needs to be filled with gas; the digital pressure gauge A (2-6) is used to visually display the change of gas pressure; the manual stop valve (2-12) is based on the pressure change of the digital pressure gauge A (2-6) , the inflation rate can be manually controlled; the one-way valve (2-9) can prevent the airflow in the system from flowing backwards; The detection device includes a digital pressure gauge B (2-15), an adapter D (2-16), a combined conduit D (2-17), a manual stop valve (2-18), a detection end soft The pipe (2-19) and the detection end connector (2-20); the detection end connector (2-20) is connected with the aircraft pressure detection end, and the detection end hose (2-19), the manual stop valve ( 2-18), combined conduit D (2-17), adapter D (2-16), digital display pressure gauge B (2-15) to realize the gas pressure detection of the gas filling part of the aircraft; digital display pressure gauge B (2-15) is opened by the screw switch of the manual shut-off valve (2-18) to observe the change of the gas pressure at the position where the aircraft is filled with gas and the air tightness of the relevant test items. 4. The integrated detection method of the aircraft assembly system according to claim 1, wherein the aircraft part unlocking stroke measuring device comprises a clamping mechanism, a fixed base mechanism and a driving mechanism; The left fixing frame (3-1) and the right fixing frame (3-2) are both semi-circular rings, and the two are connected by the rotating pin (3-16) to form a clamping mechanism, which is used for unlocking the travel measurement tool clamp for aircraft parts Hold it on the surface of the part shell, and then lock it with the quick release bolt (3-3) and the turning nut (3-4); The fixed base mechanism includes a lower stop base (3-5), a lead screw (3-8), a driven gear (3-9), an upper stop base (3-10), a scale rod (3-12) and a polished rod (3-13); the end of the clamping mechanism is connected to the lower stop base (3-5); two lead screws (3-10) are installed between the lower stop base (3-5) and the upper stop base (3-10). 8), the scale rod (3-12) and the polished rod (3-13); the moving bracket (3-6) is threadedly connected to the two lead screws (3-8) for reciprocating motion, and there is a long strip on it. Slotted; a driven gear (3-9) is installed on each lead screw (3-8); a scale pointer is provided on the moving bracket (3-6), which cooperates with the scale rod (3-12) to obtain the scale ; The driving mechanism includes a rotating handle (3-11), a rotating shaft (3-14) and a main gear (3-15), and the three are connected in sequence; Holes, the main gear (3-15) meshes with each driven gear (3-9). 5. The integrated detection method of the aircraft assembly system according to claim 1, characterized in that, the aircraft special-shaped joystick precision measurement test bench comprises an equipment base (4-1), a scale (4-2), Slide rail with groove (4-3), moving pointer (4-4), small fixing screw (4-5), large fixing screw (4-6), base plate (4-7), outer slide rail (4) -8), sliding support (4-9), extension link (4-10), optional joint (4-11), fixed support (4-12), detachable joint (4-13), information plate (4-14), sliding roller (4-15) and roller pin (4-16); The device base (4-1) is provided with a non-slip pad, so that the device can be stably placed on the tool table without relative sliding; the fixed support (4-12) is provided with a freely replaceable detachable joint (4-13), the sliding support (4-9) is provided with an optional joint (4-11) that can be freely selected according to the fixing form of the tie rod to be measured, and the lengthened connecting rods (4-10) of different lengths can be freely selected Optionally mounted over fixed supports (4-12) and/or sliding supports (4-9) for easy measurement of non-straight rod-type components; grooved slides (4-3) and outboard slides (4-8) ) are arranged on both sides of the equipment base (4-1) as the sliding channel of the sliding support (4-9), and the slotted slide rail (4-3) has a long flat hole in the center; as the moving pointer (4-4) The sliding channel with grooves (4-3) is close to the side of the scale (4-2) and the moving pointer (4-4) is fixed, and the moving pointer (4-4) passes through the long flat hole, which is convenient for the scale (4-2) for intuitive reading; the scale (4-2) is fixed on the equipment base (4-1), the “0” engraved line of the scale (4-2) and the detachable joint (4-13) The central axes of the slides are coincident, the fixed support (4-12) is arranged at the beginning of the slotted slide rail (4-3) and the outer slide rail (4-8), and the base baffle (4-7) is arranged at the slotted slide rail (4-7). 4-3) and the end of the outer slide rail (4-8), which can be freely disassembled to limit the sliding support (4-9); the sliding roller (4-15) passes through the roller pin (4-16) Installed on the bottom end of the sliding support (4-9). 6 . The integrated detection method of an aircraft general assembly system according to claim 1 , wherein the device for measuring the extension of the piston rod of the aircraft jack comprises an open jack cover snap ring, a piston rod snap ring , slide rail, slider (5-6), fixed support (5-7) and digital vernier caliper (5-9); The open-type actuator cover snap ring is connected by the actuator cover upper snap ring (5-1) and the actuator cover lower snap ring (5-2) through the actuator cover snap ring fixing bolts (5-14), Set on the actuator cover; the piston rod snap ring is connected by the piston rod upper snap ring (5-3) and the piston rod lower snap ring (5-4) through the piston rod snap ring fixing bolts (5-13), set on the On the piston rod nut; the snap ring (5-1) on the actuator cover is provided with a double-hole lug, the snap ring (5-3) on the piston rod is provided with a single-hole lug, and the snap ring on the actuator cover ( 5-1) The hole at the same level as the snap ring (5-3) on the piston rod is used for the long slide rail (5-5) to pass through, and the snap ring (5-1) on the actuator cover is fixed by the slide rail The nut (5-15) is fixed on the long slide rail (5-5), and the snap ring (5-3) on the piston rod reciprocates on the long slide rail (5-5); the fixed support (5-7) and The slider (5-6) is placed on the long slide rail (5-5), and is located between the snap ring of the actuator cover and the snap ring of the piston rod. The slider (5-6) passes through the slider top wire (5-12) Fix; one end of the short slide rail (5-8) is fixed in the other hole of the snap ring (5-1) on the actuator cover through the slide rail fixing nut (5-15), and the other end passes through the fixed support (5-15). 5-7) and fixed by the support top wire (5-11); The slider (5-6) and the fixed support (5-7) are both provided with grooves to respectively fix the front teeth and rear teeth of the digital vernier caliper (5-9). The rear teeth are fixed by the caliper top wire (5-10). 7. The integrated detection method of the aircraft assembly system according to claim 1, wherein the long-rod type rocker arm part deflection angle measuring instrument comprises a circular rubber suction cup (6-1), a suction cup pull rod (6 -2), pin shaft (6-3), mounting support (6-4), pressure handle (6-5), integrated inclination indicator support seat (6-6), integrated inclination indicator (6-7) , Upper splint (6-8), Lower splint (6-9), Fastening screws (6-10), Inclination synchronization indicator (6-11), Transfer cable (6-12), Locking bolts (6 -13), horizontal column (6-14), fixing screw (6-15) and fastening bolt (6-16); The installation support (6-4) is the main body of the installation, and the lower two ends of the mounting support (6-4) are symmetrically dug with "bowl-shaped" depressions for arranging two circular rubber suction cups (6-1). The upper two ends of the installation support (6-4) A fork-shaped support arm is symmetrically arranged; one end of the suction cup pull rod (6-2) is connected to the circular rubber suction cup (6-1) through the upper splint (6-8), the lower splint (6-9) and the fastening screw (6-10). ), the other end and one end of the pressure handle (6-5) are mounted on the fork-shaped support arm of the mounting support (6-4) through the pin (6-3); The support base (6-6) of the integrated inclination angle indicator is fixed on the installation support (6-4) and used to install the integrated inclined angle indicator (6-7); the locking bolt (6-13) is located on the support of the integrated inclination angle indicator The through hole on one side of the seat (6-6) is used to move and fix the integrated inclination indicator (6-7). Strong magnetic shell structure, with electronic indicator for real-time indication of the deflection angle of the long-rod rocker arm parts; the inclination synchronization indicator (6-11) is connected with the inclination angle comprehensive indicator (6-7) through the transfer cable (6-12) ) are connected, and the indication signal is transmitted in real time; The horizontal column (6-14) is installed on the mounting support (6-4) for leveling. 8 . The integrated detection method of the aircraft assembly system according to claim 1 , wherein the force measuring device of the manual control mechanism comprises a hand-held control box (7-1), a data transmission line (7-2), a box Body (7-5), support rod (7-6), connecting hinge mechanism (7-7), transmission rod (7-8), executive rod (7-9), load-bearing parts (7-10), force Value sensor (7-11) and handle bushing (7-12); The box (7-5) is used to place the drive equipment and power supply wiring harness of the equipment, and is provided with a data receiving interface (7-3) and a reserved interface (7-4) on the outside, and a battery (7-13), The drive motor (7-14) and the electric mechanism (7-15); the hand-held control box (7-1) is connected to the data receiving interface (7-3) through the data transmission line (7-2), and the reserved interface (7-4) ) is used to connect external devices to realize data transmission; the battery (7-13) supplies power for the drive motor (7-14), which is used to drive the motor mechanism (7-15); The electric mechanism (7-15) is connected to one end of the support rod (7-6), and the other end of the support rod (7-6), the transmission rod (7-8), and the execution rod (7-9) are connected by a hinge mechanism (7-9). 7) Support connection, and the support rod (7-6) and the transmission rod (7-8), the transmission rod (7-8) and the execution rod (7-9) are in a mutually perpendicular positional relationship; the connection hinge mechanism (7-7) ) is a right-angle adapter; the actuator rod (7-9), the load-bearing part (7-10), the force sensor (7-11) and the handle sleeve (7-12) are connected in sequence; the actuator rod (7-9) ) to transmit force to drive the force-bearing parts (7-10), the force sensor (7-11) and the handle sleeve (7-12) to move, and the force sensor (7-11) can measure the force and display the force value, the handle bushing (7-12) is used to connect and fix the device to the handle of the hand opening mechanism; the battery (7-13) is used to supply power to the device; The hand-held control box (7-1) is provided with a power display, a power switch and a device driving microswitch. 9 . The integrated detection method for an aircraft assembly system according to claim 1 , wherein the integrated measuring device for the pedals of the aircraft control system comprises a dial (8-1), a scale indicator (8-2) 9 . , mooring rope (8-3), stroke measuring rod (8-4), fixing bolt (8-5), process pedal (8-6), pressure sensor (8-7), digital display angle measuring device (8) -8), fixed support (8-9), signal output cable (8-10) and numerical display (8-11); One end of the stroke measuring rod (8-4) is fixed on the process pedal (8-6), the other end is provided with a dial (8-1), and the scale indicator (8-2) is connected to the On the stroke measuring rod (8-4), it is prevented from being lost, and slides in the area of the dial (8-1); one side of the process pedal (8-6) is used to withstand the external force applied by the operator, and the other side is connected to the pressure sensor (8- 7); The fixed support (8-9) is L-shaped, fixed on the pedal of the aircraft, one side is connected to the pressure sensor (8-7), and the other side is connected to the digital display angle measuring device (8-8) ; The pressure sensor (8-7) and the digital display angle measuring device (8-8) are connected to the numerical display (8-11) through the signal output cable (8-10), which are used to display the bearing force value of the aircraft pedal and deflection angle. 10. The integrated detection method for an aircraft assembly system according to claim 1, wherein the joystick transmission system idle travel measuring instrument comprises a comprehensive measurement indicating device (11), a moving contact state acquisition device and a static Contact state acquisition device; The comprehensive measurement indicating device (11) displays the deflection and displacement of the measurement object in real time through a digital display device, and is fixed on a joystick in the transmission rod system through a fixing device; the fixing device includes a clamping and fixing device (1), an opening adjuster (2), locking nut a (3), flexible arm clamping device (4), flexible adjusting arm a (5), ball joint arm locking device (6), ball joint arm (7) , the locking nut b (8), the comprehensive measurement indicating device fixing seat (9) and the locking screw (10); the clamping fixing device (1) and the opening adjuster (2) constitute a clamping device, which is used as the fixing device. Fixed end; one end of the flexible adjusting arm a(5) is connected to the clamping and fixing device (1) through the locking nut a(3), and the other end is connected to the ball joint arm through the ball joint arm locking device (6) (7); The flexible support arm clamping device (4) is installed on the flexible adjustment support arm a (5) for fixing; the ball joint support arm (7) is connected to the comprehensive measurement indicator through the lock nut b (8) The device fixing seat (9), the comprehensive measurement indicating device (11) is fixed under the comprehensive measurement indicating device fixing seat (9) by the locking screw (10); The moving contact state acquisition device (13) is L-shaped, the moving contact elastic support arm adjuster (12) passes through one side of the moving contact elastic support arm (14), and the moving contact elastic support arm (14) is fixed on the other side; The elastic support arm adjuster (12) is used to adjust the position of the movable contact elastic support arm (14), and the movable contact elastic support arm (14) converts the mechanical displacement signal into an electrical signal and transmits it to the movable contact state acquisition device ( 13); the remote synchronization indicator light (15) is installed on the moving contact state acquisition device (13) for sensing the contact between the moving contact elastic support arm (14) and the static contact elastic support arm (24); the moving contact The installation device of the head state collecting device (13) includes a clamping device (16), a tension adjusting device (17), a locking nut c (18), a spherical adjusting locking device (19), and a universal connection support arm (20). ), lock nut d (21), flexible arm locker (22) and flexible adjustment arm b (23); clamping device (16) and tension adjustment device (17) constitute a measuring support; flexible adjustment One end of the support arm b (23) is connected to the clamping device (16) through the lock nut c (18), and the other end is connected to the universal connection support arm (20) through the ball adjustment locking device (19); the flexible support arm lock The tightener (22) is installed on the flexible adjusting arm b (23) for fixing; the universal connection arm (20) is connected to the moving contact state acquisition device (13) through the locking nut d (21); The static contact state acquisition device (25) is installed on the executive component of the transmission rod system terminal, one side of which is connected to the static contact elastic support arm (24), and the other side is fixed to the static contact fixed support through fixing screws (26) (28); the static contact elastic support arm (24) converts the mechanical displacement signal into an electrical signal and transmits it to the static contact state acquisition device (25); the static contact fixed support (28) and the clamping lock ( 27) constitute a fixing device; Both the moving contact state acquisition device (13) and the static contact state acquisition device (25) are connected to the comprehensive measurement indicating device (11) through a transfer cable (29) to transmit electrical signals.

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