CN112623264A - Unmanned aerial vehicle machine carries dynamic test system - Google Patents
Unmanned aerial vehicle machine carries dynamic test system Download PDFInfo
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- CN112623264A CN112623264A CN201910950447.8A CN201910950447A CN112623264A CN 112623264 A CN112623264 A CN 112623264A CN 201910950447 A CN201910950447 A CN 201910950447A CN 112623264 A CN112623264 A CN 112623264A
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- 238000009864 tensile test Methods 0.000 claims abstract description 6
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- 239000003570 air Substances 0.000 description 11
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The utility model provides an unmanned aerial vehicle machine carries dynamic test system, includes the fuselage, the front end of fuselage is provided with the aircraft nose, the both sides of fuselage are provided with the wing, the rear side of fuselage still is provided with the fin, is located the rear end of fuselage still is provided with the screw, still be provided with between fuselage and the screw and move the tensile test device, move the tensile test device pass through the motor with the screw links to each other. In the flight process of the unmanned aerial vehicle, the motor is powered by the power battery to drive the propeller to rotate, the propeller rotates to generate tension and torque, the voltage and the current of an aircraft system are collected by the electric power measuring module, and meanwhile, the dynamic tension testing device on the unmanned aerial vehicle can measure the tension, the power and the efficiency of the power system, can measure the power consumption and the efficiency of an engine of the unmanned aerial vehicle, the propeller efficiency of the propeller and other data information, so that the real-time dynamic test of the unmanned aerial vehicle in the flight state is completed.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle testing, in particular to an airborne dynamic testing system of an unmanned aerial vehicle.
Background
The design and application of unmanned aerial vehicles is an active area in modern society, and is a crucial aspect for the assessment of the overall efficiency and the air performance of unmanned aerial vehicles. At present, the evaluation of parameters of an unmanned aerial vehicle mainly comprises the measurement of data such as tension, torque, voltage, current, system efficiency, airspeed and motor rotating speed of a propeller, and a ground static test is adopted in the prior art. The measurement of the airborne dynamic data of the unmanned aerial vehicle is a scheme for applying and measuring the aircraft in a real flight environment, has engineering application value and reliable measurement results, and is not researched, developed and applied at present aiming at the measurement of the airborne dynamic data of the unmanned aerial vehicle.
Therefore, to the vacancy in the prior art, an unmanned aerial vehicle airborne dynamic test system needs to be designed.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides an unmanned aerial vehicle airborne dynamic test system capable of measuring the tension, power consumption and efficiency of a power system and the tension and torque of a propeller.
The technical problem to be solved by the invention is realized by adopting the following technical scheme:
the utility model provides an unmanned aerial vehicle machine carries dynamic test system, includes the fuselage, the front end of fuselage is provided with the aircraft nose, the both sides of fuselage are provided with wing, its characterized in that: the rear side of the machine body is further provided with a tail wing, the rear end of the machine body is further provided with a propeller, a dynamic tension testing device is further arranged between the machine body and the propeller, and the dynamic tension testing device is connected with the propeller through a motor.
The motor of the unmanned aerial vehicle is connected through the dynamic tension testing device, the motor is connected with the propeller, the tension or the thrust of the propeller of the unmanned aerial vehicle can be detected in real time, the power consumption and the efficiency of the motor of the unmanned aerial vehicle can be measured, the propeller efficiency and other data of the propeller are measured, the dynamic tension testing device is adopted, the unmanned aerial vehicle power system can be evaluated and optimized, and the measurement of the pneumatic parameters of the aircraft can be completed.
Preferably, the motor is electrically connected with a motor speed regulator, and the motor speed regulator is connected with a power battery.
The motor speed regulator can regulate the rotating speed of the motor to meet the flying work of aircrafts with different specifications.
Preferably, the motor speed regulator is connected with an airplane control receiver, the airplane control receiver is connected with a main control box, and the main control box is electrically connected with an electric power measuring module.
The electric power measurement module is mainly used for measuring the current value and the voltage value input by the aircraft system and judging the working state of the unmanned aerial vehicle in the flight process through the measured values.
Preferably, the electric power measuring module is further connected with a testing system battery.
The battery of the test system supplies power for the electric power measurement module.
Preferably, the dynamic tension testing device is integrated with a phase-change rotating speed sensor, a temperature sensor, an air pressure sensor, a voltage and current sensor and a tension and torque sensor.
The rotating speed data of motor is gathered to commutation speed sensor, temperature sensor gather the external environment temperature of unmanned aerial vehicle at the flight during operation, baroceptor gather the atmospheric pressure value that unmanned aerial vehicle received at the flight in-process, voltage current sensor gather the current value and the voltage value of unmanned aerial vehicle electrical power generating system's input, pulling force torque sensor gather the screw moment of torsion and the pulling force at the during operation.
Preferably, the commutation speed sensor, the temperature sensor, the air pressure sensor, the voltage and current sensor and the tension and torque sensor are all electrically connected in the main control box.
The phase-change rotating speed sensor, the temperature sensor, the air pressure sensor, the voltage and current sensor and the tension and torque sensor respectively transmit acquired data information to the main control box, and the data are remotely transmitted to the ground end through the airplane control receiver to be checked by a user.
Preferably, the handpiece is provided with a differential pressure (airspeed) sensor, and the differential pressure (airspeed) sensor is electrically connected in the main control box.
The differential pressure (airspeed) sensor collects the speed value of the aircraft relative to the ambient air and transmits the speed value to the main control box.
Preferably, the voltage measuring range of the power battery is 7-70V, and the current range of the power battery is 0-200A.
The invention has the advantages and positive effects that:
in the flight process of the unmanned aerial vehicle, the motor is powered by the power battery to drive the propeller to rotate, the propeller rotates to generate tension and torque, the voltage and the current of an aircraft system are collected by the electric power measuring module, and meanwhile, the dynamic tension testing device on the unmanned aerial vehicle can measure the tension, the power and the efficiency of the power system, can measure the power consumption and the efficiency of an engine of the unmanned aerial vehicle, the propeller efficiency of the propeller and other data information, so that the real-time dynamic test of the unmanned aerial vehicle in the flight state is completed. And the main control box can collect data such as voltage, current, pulling force, moment of torsion, power and efficiency of the engine of the aircraft, can realize detecting various data information of the aircraft in real time, in order to observe the running state of the aircraft. In addition, the main control box is connected with the airplane control receiver, the dynamic test system can remotely transmit the acquired data to the ground end through the airplane control receiver, the real-time graph display of the data is achieved, the acquired data are stored in real time, and the storage frequency reaches 10 HZ.
Drawings
FIG. 1 is a schematic side elevational view of the present invention;
FIG. 2 is a schematic bottom view of the present invention in an axial side view;
fig. 3 is a schematic diagram of the electrical connections between the components of the present invention.
In the figure: 1. a machine head; 2. a body; 3. an airfoil; 4. a dynamic tension testing device; 5. a motor; 6. a propeller; 7. a tail wing; 8. a master control box; 9. a power battery; 10. a motor speed regulator; 11. an electrical power measurement module.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or intervening components may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
The embodiments of the invention will be described in further detail below with reference to the accompanying drawings:
as shown in fig. 1 and 2, the airborne dynamic test system of the unmanned aerial vehicle comprises a machine body 2, a machine head 1 is arranged at the front end of the machine body 2, wings 3 are arranged on two sides of the machine body 2, a tail wing 7 is further arranged on the rear side of the machine body 2, a propeller 6 is further arranged at the rear end of the machine body 2, a dynamic tension test device 4 is further arranged between the machine body 2 and the propeller 6, and the dynamic tension test device 4 is connected with the propeller 6 through a motor 5. Through moving tensile test device 4 and connecting unmanned aerial vehicle's motor 5 to link to each other motor 5 and screw 6, can real-time detection unmanned aerial vehicle's screw 6 pulling force or thrust, can also measure unmanned aerial vehicle motor 5's consumption and efficiency, and the data such as the oar effect of screw 6, adopt and move tensile test device 4, not only can assess and optimize unmanned aerial vehicle driving system, also can accomplish the measurement of the pneumatic parameter of aircraft.
Further, as shown in fig. 3, the motor 5 is electrically connected with a motor governor 10, and the motor governor 10 is connected with a power battery 9. The motor speed regulator 10 can regulate the rotating speed of the motor 5 to meet the flying work of aircrafts with different specifications.
Further, the motor speed regulator 10 is connected with an aircraft control receiver, the aircraft control receiver is connected with a main control box 8, and the main control box 8 is electrically connected with an electric power measuring module 11. The electric power measuring module 11 is mainly used for measuring current values and voltage values input by an aircraft system, the working state of the unmanned aerial vehicle in the flying process is judged through the measured values, and the communication distance between the aircraft control receiver and the ground end signal transmitter can reach 2 km.
Further, the electric power measuring module 11 is also connected with a testing system battery. The test system battery supplies power to the electric power measurement module 11.
Furthermore, a phase-change rotating speed sensor, a temperature sensor, an air pressure sensor, a voltage and current sensor and a tension and torque sensor are integrated on the dynamic tension testing device 4. Commutation speed sensor gather the rotational speed data of motor 5, temperature sensor gather the external environment temperature of unmanned aerial vehicle at the flight during operation, baroceptor gather the atmospheric pressure value that unmanned aerial vehicle received at the flight in-process, voltage current sensor gather the current value and the voltage value of unmanned aerial vehicle electrical power generating system's input, pulling force torque sensor gather torque force and the pulling force of screw 6 at the during operation.
Furthermore, the commutation speed sensor, the temperature sensor, the air pressure sensor, the voltage and current sensor and the tension and torque sensor are all electrically connected in the main control box 8. The commutation speed sensor, the temperature sensor, the air pressure sensor, the voltage and current sensor and the tension and torque sensor respectively transmit the acquired data information to the main control box 8, and the data are remotely transmitted to the ground end through the airplane control receiver for a user to check.
Further, the aircraft nose 1 on install pressure difference (airspeed) sensor, pressure difference (airspeed) sensor electricity connect in the main control box 8. The differential pressure (airspeed) sensor collects the airspeed, i.e. the value of the aircraft's speed of movement relative to the surrounding air, and transmits it to the main control box 8.
In addition, the voltage measuring range of the power battery 9 is 7-70V, the current range is 0-200A, the temperature value range stored by the main control box 8 is-30 ℃ to +60 ℃, the temperature range when the power battery is used is-20 ℃ to +50 ℃, the range of the air pressure sensor is 50-120kpa, the range of the motor temperature measured by the temperature sensor is-70 ℃ to +350 ℃, and the range of the environment temperature measured by the temperature sensor is-40 ℃ to +125 ℃. The range of the phase change rotation speed sensor is 300-150000RPM, the pull force range of the pull force torque sensor is 5-70kgf, and the torque range is 0-50 N.M.
When the unmanned aerial vehicle aircraft carries out behaviors of severe impact on the sensor, such as heavy landing, severe vibration or sliding landing and oar beating, the sensor needs to be self-checked, and the self-checking steps are as follows: firstly, pulling out a tension torque sensor on a main control box 8, keeping any axial tangent plane of the tension torque sensor and a motor 5 parallel to the ground (namely a main shaft of the motor 5 is parallel to the ground), horizontally oppositely arranging two blades of a propeller 6 (if three blades of the propeller are ensured to be not stressed), electrifying a test system, connecting a computer to observe values of tension and torque, wherein the tension value is within 100g, the torque value is within 0.01, inserting the tension torque sensor back in an electrified state (keeping the tension torque sensor not stressed), observing the indication number on the computer, and if the tension value is greater than 500g, and the torque value is greater than 0.1NM, indicating that the tension torque sensor is damaged; if the indication number on the computer is smaller than the value, the tension torque sensor works normally.
During concrete implementation, all receive main control box 8 with commutation speed sensor, temperature sensor, baroceptor, voltage current sensor, pulling force torque sensor and pressure differential (airspeed) sensor on, open the computer, connect unmanned aerial vehicle's aircraft control receiver, observe whether sensor is in normal operating condition separately through the parameter of each sensor, if there is the trouble, then take off corresponding sensor and maintain, if there is not the trouble problem, then clear zero the processing to each parameter value of unmanned aerial vehicle. When the tension and the torque of the propeller 6 are cleared, the tension torque sensor and any axial tangent plane of the motor 5 are kept parallel to the ground, the propeller 6 is horizontally arranged oppositely, and the propeller is cleared in a stable state. When the airspeed of the unmanned aerial vehicle is clear, the airspeed tube is covered by the airspeed tube sleeve in a windless environment, and the airspeed is cleared. After various data information of the unmanned aerial vehicle is cleared, the unmanned aerial vehicle is started, in the flying process of the unmanned aerial vehicle, a commutation rotating speed sensor acquires rotating speed data of a motor 5, a temperature sensor acquires the external environment temperature of the unmanned aerial vehicle in the flying process, an air pressure sensor acquires the air pressure value borne by the unmanned aerial vehicle in the flying process, a voltage and current sensor acquires the current value and the voltage value of the input end of a power supply system of the unmanned aerial vehicle, a tension and torque sensor acquires the torque force and the tension force of a propeller 6 in the flying process, the sensors transmit the data acquired respectively to a main control box 8, and storing the data, the main control box 8 transmits the collected data to a computer of a ground end user through an airplane control receiver, data are checked on the computer, and the optimal parameters of the unmanned aerial vehicle in the normal working state can be known by measuring the numerical values of the unmanned aerial vehicle at all parts during working. The dynamic test system can record flight data in real time and remotely transmit the flight data to the user terminal for work research of the unmanned aerial vehicle.
In the flying process of the unmanned aerial vehicle, the motor 5 is supplied with power through the power battery 9 to drive the propeller 6 to rotate, the propeller 6 rotates to generate tension and torque, the voltage and the current of an aircraft system are collected through the electric power measuring module 11, meanwhile, the unmanned aerial vehicle airborne dynamic tension testing device 4 can measure the tension, the power and the efficiency of the power system, can measure the power consumption and the efficiency of an engine of the unmanned aerial vehicle aircraft, the propeller effect of the propeller 6 and other data information, and the real-time dynamic test of the unmanned aerial vehicle in the flying state is completed. And the main control box 8 can collect data such as voltage, current, tension, torque, power and efficiency of the engine and the like of the aircraft, and can realize real-time detection of various data information of the aircraft so as to observe the running state of the aircraft. In addition, the main control box 8 is connected with the airplane control receiver, the dynamic test system can remotely transmit the acquired data to the ground end through the airplane control receiver, the real-time graph display of the data is achieved, the acquired data are stored in real time, and the storage frequency reaches 10 HZ.
It should be emphasized that the embodiments described herein are illustrative rather than restrictive, and thus the present invention is not limited to the embodiments described in the detailed description, but other embodiments derived from the technical solutions of the present invention by those skilled in the art are also within the scope of the present invention.
Claims (8)
1. The utility model provides an unmanned aerial vehicle machine carries dynamic test system, includes fuselage (2), the front end of fuselage (2) is provided with aircraft nose (1), the both sides of fuselage (2) are provided with wing (3), its characterized in that: the rear side of fuselage (2) still is provided with fin (7), is located the rear end of fuselage (2) still is provided with screw (6), still be provided with between fuselage (2) and screw (6) and move tensile test device (4), move tensile test device (4) pass through motor (5) with screw (6) link to each other.
2. The system of claim 1, wherein the system further comprises: the motor (5) is electrically connected with a motor speed regulator (10), and the motor speed regulator (10) is connected with a power battery (9).
3. The system of claim 2, wherein the system further comprises: the aircraft control system is characterized in that the motor speed regulator (10) is connected with an aircraft control receiver, the aircraft control receiver is connected with a main control box (8), and the main control box (8) is electrically connected with an electric power measuring module (11).
4. The system of claim 3, wherein the system further comprises: the electric power measuring module (11) is also connected with a testing system battery.
5. The system of claim 3, wherein the system further comprises: and a phase-change rotating speed sensor, a temperature sensor, an air pressure sensor, a voltage and current sensor and a tension and torque sensor are integrated on the dynamic tension testing device (4).
6. The system of claim 5, wherein the system further comprises: the commutation speed sensor, the temperature sensor, the air pressure sensor, the voltage and current sensor and the tension and torque sensor are all electrically connected in the main control box (8).
7. The system of claim 3, wherein the system further comprises: the aircraft nose (1) on install pressure differential (airspeed) sensor, pressure differential (airspeed) sensor electricity connect in main control box (8).
8. The system of claim 2, wherein the system further comprises: the voltage measuring range of the power battery (9) is 7-70V, and the current range is 0-200A.
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| CN201910950447.8A CN112623264A (en) | 2019-10-08 | 2019-10-08 | Unmanned aerial vehicle machine carries dynamic test system |
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| CN201910950447.8A CN112623264A (en) | 2019-10-08 | 2019-10-08 | Unmanned aerial vehicle machine carries dynamic test system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116047193A (en) * | 2022-11-24 | 2023-05-02 | 西安爱生技术集团有限公司 | A ground drone power supply network test system and test method |
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