CN220751445U - Calibration and calibration device of helicopter torque detection system - Google Patents

Abstract

The utility model discloses a calibration and calibration device of a helicopter torque detection system, which comprises a plurality of driving motors, a torque disc assembly, a torque detection assembly, a split torque meter and a total torque meter, wherein the split torque meter is connected with the plurality of driving motors; the torque disc assembly comprises a plurality of torque discs which are disc-shaped, a plurality of windows are uniformly formed in the circumference side of each torque disc, and teeth are arranged in each window; the relative positions of the teeth and the window in each torque disc are different, and different torque values are corresponding to each other; the torque disc is arranged on the rotating shaft of the driving motor, the torque detection component detects the corresponding torque of the torque disc and sends the corresponding torque to the corresponding sub-torque meter, and each sub-torque meter is connected with the total torque meter. The utility model has the advantages of simple structure, simple and convenient operation, stable and reliable calibration and calibration, etc.

Description

Calibration and calibration device of helicopter torque detection system

Technical Field

The utility model mainly relates to the technical field of helicopter testing, in particular to a calibration and calibration device of a helicopter torque detection system.

Background

Three free turbine engines are assembled on a helicopter of a certain model, the torque of a transmission shaft of the free turbine engines is in direct proportion to the output power of the engines, and pilots measure the power of the engines and a main speed reducer through measurement and indication of the torque by a torque detection shaft, a torque sensor, a split torque meter and a total torque meter. Under the current laboratory conditions, because the true standard torsion angle of the torque detection shaft of the turbine engine cannot be simulated, the torque photoelectric sensor, the split torque meter and the total torque meter are not subjected to joint calibration and calibration. When the engine is started, the crew completely calibrates the split torque meter and the total torque meter by experience in a way of zero setting (torque 0 percent) and full setting (torque 100 percent), so that the error is larger, and a certain potential safety hazard exists.

Disclosure of Invention

The technical problem to be solved by the utility model is as follows: aiming at the technical problems existing in the prior art, the utility model provides the calibration and calibration device of the helicopter torque detection system, which has the advantages of simple structure, simplicity and convenience in operation, stability and reliability.

In order to solve the technical problems, the technical scheme provided by the utility model is as follows:

a calibration and calibration device of a helicopter torque detection system comprises a plurality of driving motors, a torque disc assembly, a torque detection assembly, a split torque meter and a total torque meter; the torque disc assembly comprises a plurality of torque discs which are disc-shaped, a plurality of windows are uniformly formed in the circumference side of each torque disc, and teeth are arranged in each window; the relative positions of the teeth and the window in each torque disc are different, and different torque values are corresponding to each other; the torque disc is arranged on the rotating shaft of the driving motor, the torque detection component detects the corresponding torque of the torque disc and sends the corresponding torque to the corresponding sub-torque meter, and each sub-torque meter is connected with the total torque meter.

Preferably, the number of torque discs is two, corresponding to torque values of 0% and 100%.

Preferably, the torque detection assembly is a photoelectric sensor.

Preferably, the number of windows formed on the circumferential side of each torque disc is three.

Preferably, the driving motor is a servo motor.

Compared with the prior art, the utility model has the advantages that:

the calibration and calibration device of the helicopter torque detection system of the utility model calibrates the torque detection assembly, the split torque meter and the zero (0% torque) and full (100% torque) of the total torque meter under laboratory conditions, reassembles calibrated equipment, and provides a standard for engine calibration by 0 bit indication and 100% torque indication. According to the utility model, through the cooperation between the servo motor and the torque disc assembly, different torques of the on-site generator are simulated, the calibration and the calibration under a laboratory are realized, the gap of the periodic calibration of the torque detection system by ground staff is filled, and the device is simple in structure and convenient to operate. The utility model adopts the precisely controllable servo motor to stably simulate the standard rotation speed of the aircraft engine, and ensures the data stability during adjustment.

Drawings

FIG. 1 is a schematic diagram of a calibration and calibration device according to an embodiment of the present utility model.

Fig. 2 is a schematic diagram of a structure of an a-disc in a detecting disc set in the prior art.

Fig. 3 is a schematic diagram of a B-disc structure in a detection disc set in the prior art.

Fig. 4 is a schematic diagram of the overall structure of a detection disc set in the prior art.

Fig. 5 is a schematic structural diagram of a torque zero disc in an embodiment of the utility model.

Fig. 6 is a side view of the torque zero disc of the present utility model in an embodiment.

Fig. 7 is a schematic diagram of a torque-full disc in an embodiment of the present utility model.

Fig. 8 is a schematic diagram of output pulses of the photosensor of the present utility model.

Legend description: 1. a servo motor; 2. a torque disc assembly; 201. torque zero disc; 202. torque full disc; 203. a torque plate; 204. a window; 205. teeth; 3. a torque detection assembly; 4. dividing a torque meter; 5. total torque meter.

Detailed Description

The utility model is further described below with reference to the drawings and specific examples.

As shown in FIG. 1, the calibration and calibration device of the helicopter torque detection system of the present utility model requires calibration and calibration of the helicopter torque detection system. In order to ensure the calibration and calibration precision of the device, the actual use condition of the site needs to be simulated as much as possible. The helicopter torque detection is analyzed as follows:

when the transmission shaft of the helicopter engine is acted by torque, a certain torsion angle is generated, the larger the torque is, the larger the torsion angle is, and each turbine shaft comprises a detection shaft which is integrated with the shaft, namely the torsion angle is detected by the detection shaft. Wherein, A, B on the detector forms a detecting disc group, the disc A and the transmission shaft are integrated, and 3 equidistant windows are arranged in the circumference as shown in figure 2; disc B is fixed to the inner shaft and has 3 equidistant teeth on the circumference, each tooth corresponding to a window of disc a as shown in fig. 3. When the turbine shaft drives the load to rotate, the disc A necessarily falls behind the disc B by an angle due to the action of torque, so that the teeth of the disc B generate a displacement for the window of the disc A, the displacement is the torsion angle, and the displacement corresponds to a torque value with a certain value, as shown in fig. 4.

Based on the analysis, the calibration and calibration device of the helicopter torque detection system specifically comprises a plurality of driving motors (such as a servo motor 1), a torque disc assembly 2, a torque detection assembly 3, a split torque table 4 and a total torque table 5; the torque disc assembly 2 comprises a plurality of torque discs 203, wherein the torque discs 203 are disc-shaped, a plurality of windows 204 are uniformly formed on the circumference side of the torque discs 203, and teeth 205 are arranged in each window 204; the relative positions of the teeth 205 and the windows 204 in each torque disc 203 are different and correspond to different torque values; the torque detection assembly 3 detects the corresponding torque of the torque disc 203 and sends the detected torque to the corresponding sub-torque table 4, and each sub-torque table 4 is connected with the total torque table 5.

Specifically, when calibration and calibration are performed under laboratory conditions, the device corresponds to "zero setting (torque 0%)", and "full setting (torque 100%)" two gears, and according to design standard parameters of the detection shaft when the torque is 0% and the torque is 100%, the device combines the disk a and the disk B on the original machine into one, designs two torque disks 203 respectively, and corresponds to the torque zero disk 201 and the torque full disk 202 respectively.

As shown in fig. 5-6, the basic data of the torque zero disc 201 are: diameter of the disc: dmm; a Cmm window 204 spaced 120 apart; a tooth 205 is left in the window 204, and the width of the tooth 205 is: c1mm; the left edge of tooth 205 is L1mm from the edge of left window 204, with a tolerance of +0.02mm.

As shown in fig. 7, the basic data of the torque full disc 202 are: diameter of the disc: dmm; a Cmm window 204 spaced 120 apart; a tooth 205 is left in the window 204, and the width of the tooth 205 is: c1mm; the left edge of tooth 205 is a distance l1+2.4mm from the edge of left window 204, with a tolerance of +0.02mm.

Of course, in other embodiments, the design of the torque disc 203 corresponding to other torque values may be performed according to actual requirements.

As shown in fig. 1, when a specific calibration and calibration device is set up in a laboratory and the torque detection assembly 3, the split torque table 4 and the total torque table 5 are calibrated by zeroing (torque 0%), a torque zero disc 201 is fixed on a small servo motor 1, the motor revolution is F revolutions per minute, the state of torque 0% when an aircraft engine is started is completely simulated, a window 204 of the torque zero disc 201 and teeth 205 penetrate through a photoelectric sensor, and after the waveform shown in fig. 7 is detected by the photoelectric sensor output, the split torque table 4 is calibrated by zeroing. When the full-adjustment (torque 100%) calibration is performed, the torque full disc 202 is fixed on the small servo motor 1, the motor revolution is F revolutions per minute, the torque 100% state when the aircraft engine is started is completely simulated, the window 204 and the teeth 205 of the torque zero disc 201 pass through the photoelectric sensor, and after the waveform shown in fig. 8 output by the sensor is detected, the full-adjustment calibration is performed on the split torque table 4. The total torque table 5 calculates three pieces of divided torque data as a total torque display, calculated and indicated by the divided torque calculation indicator.

The calibration and calibration device of the helicopter torque detection system of the utility model calibrates the torque detection assembly 3, the split torque table 4 and the zero (torque 0%) and full (torque 100%) of the total torque table 5 under laboratory conditions, reassembles calibrated equipment, and provides a standard for engine calibration by 0 bit indication and torque 100% indication. According to the utility model, through the cooperation between the servo motor 1 and the torque disc assembly 2, different torques of the on-site generator are simulated, the calibration and the calibration under a laboratory are realized, the blank of the periodic calibration of the torque detection system by ground staff is filled, and the device is simple in structure and convenient to operate. The utility model adopts the precisely controllable servo motor 1 to stably simulate the standard rotation speed of the aircraft engine, and ensures the data stability during adjustment.

The above is only a preferred embodiment of the present utility model, and the protection scope of the present utility model is not limited to the above examples, and all technical solutions belonging to the concept of the present utility model belong to the protection scope of the present utility model. It should be noted that modifications and adaptations to the utility model without departing from the principles thereof are intended to be within the scope of the utility model as set forth in the following claims.

Claims (5)

1. The calibrating and calibrating device of the helicopter torque detection system is characterized by comprising a plurality of driving motors, a torque disc (203) assembly (2), a torque detection assembly (3), a split torque meter (4) and a total torque meter (5); the torque disc (203) assembly (2) comprises a plurality of torque discs (203), wherein the torque discs (203) are disc-shaped, a plurality of windows (204) are uniformly formed in the circumference side of each torque disc (203), and teeth (205) are arranged in each window (204); the relative positions of the teeth (205) and the window (204) in each torque disc (203) are different, and different torque values are corresponding; the torque disc (203) is arranged on a rotating shaft of the driving motor, the torque detection assembly (3) detects the corresponding torque of the torque disc (203) and sends the corresponding torque to the corresponding sub-torque meter (4), and each sub-torque meter (4) is connected with the total torque meter (5).

2. The calibration and calibration device of a helicopter torque detection system according to claim 1, characterized in that said number of torque discs (203) is two, corresponding to torque values of 0% and 100%.

3. The calibration and calibration device of a helicopter torque detection system according to claim 1 or 2, characterized in that said torque detection assembly (3) is a photoelectric sensor.

4. The calibration and calibration device of a helicopter torque detection system according to claim 1 or 2, characterized in that the number of windows (204) open on the circumferential side of each of said torque discs (203) is three.

5. Calibration and calibration device of a helicopter torque detection system according to claim 1 or 2, characterized in that said drive motor is a servo motor (1).