Aero-engine starting torque measuring device

Abstract

The invention relates to an aero-engine starting torque measuring device. The power dividing shaft comprises a rotating part transmission shaft and a static part protection cover arranged on the rotating part transmission shaft in a covering mode. The sensor module is mounted on the rotating part transmission shaft; the channel signal collecting and transmitting module is mounted on the rotating part transmission shaft and is connected with the sensor module; the receiving antenna is connected with the channel signal acquisition and emission module; the signal receiver is respectively connected with the receiving antenna and an airborne power supply, and the signal receiver is used for converting a direct current power supply of the airborne power supply into a low-voltage direct current power supply; the receiving antenna is used for receiving the radio frequency signal transmitted from the receiving antenna; the conversion power supply box is used for converting the low-voltage direct current into alternating current; and the induction power supply module comprises an induction power supply receiving coil and an induction power supply excitation coil. According to the invention, normalized measurement of the actual starting torque of the aero-engine in an installed state can be realized.

Description

Technical Field

[0001] The invention relates to the technical field of torque measurement, in particular to an aircraft engine starting torque measurement device. Background Art

[0002] The measurement of the starting torque of an aircraft engine (FDJ) is a key link in the engine performance test, and it is also an important indicator for evaluating the starting characteristics of an aircraft. The measurement results not only provide important data for the performance analysis of the engine starting system, but also provide a load boundary for the design of the entire engine accessory transmission system. However, due to the compact structure and limited space of the engine compartment, in addition to the starter, the compartment also contains a variety of accessory transmission systems such as fuel pumps, hydraulic pumps and accessory casings. Common torque measurement equipment is difficult to install and use directly. In addition, due to fluctuations under different working conditions and between different flight sorties, the torque test in the installed state needs to meet the aircraft's installation index requirements to ensure that it will not affect the normal flight of the aircraft and can be installed for a long time for real-time monitoring.

[0003] At present, the acquisition of aircraft engine starting torque has the following shortcomings: Theoretical calculation method: mainly relies on empirical parameters, but due to the complexity of influencing factors, the accuracy of the calculation results is low; Indirect measurement method: measurement is performed by adding special equipment such as a torque measuring disc, but this method affects the actual working performance of the engine and does not fully consider the loss of accessories, so the test results are not accurate; Direct measurement method: Although more accurate data can be obtained, the existing test equipment cannot meet the installation requirements and cannot perform measurements in the actual working environment of the aircraft.

[0004] Therefore, for the measurement of aircraft engine starting torque, there is an urgent need to find a solution that can adapt to narrow spaces, meet installation requirements, and provide accurate measurement. Summary of the invention

[0005] To this end, the present invention provides an aircraft engine starting torque measurement device, which can realize normalized measurement of the actual starting torque of the aircraft engine in an installed state.

[0006] In order to solve the above technical problems, the present invention provides an aircraft engine starting torque measuring device, comprising: A power take-off shaft is installed between the aircraft accessory casing and the engine accessory casing, and comprises a rotating part transmission shaft and a stationary part protection cover provided on the rotating part transmission shaft; A sensor module, mounted on the transmission shaft of the rotating member, for obtaining a torque signal of the transmission shaft of the rotating member; A channel signal acquisition and transmission module is installed on the transmission shaft of the rotating part and connected to the sensor module, and is used to receive and process the torque signal and then transmit a radio frequency signal; A receiving antenna, connected to the channel signal acquisition and transmission module, for receiving the radio frequency signal; A signal receiver is connected to the receiving antenna and the airborne power supply, respectively, and is used to convert the DC power supply of the airborne power supply into low-voltage DC power; and is used to receive the radio frequency signal transmitted from the receiving antenna, demodulate and convert it into a voltage signal, and then output it to the airborne data acquisition system; A conversion power supply box, used for converting the low voltage direct current into alternating current; An induction power supply module, comprising an induction power supply receiving coil and an induction power supply exciting coil, wherein the induction power supply exciting coil is used to form a magnetic field from the alternating current, and the induction power supply receiving coil receives the magnetic field and forms an alternating voltage source through electromagnetic induction; Wherein, the channel signal acquisition and transmission module is also connected to the induction power receiving coil, and after converting the AC voltage source, supplies power to the sensor module; The induction power receiving coil is installed on the transmission shaft of the rotating member; The induction power supply excitation coil and the receiving antenna are installed on the stationary part protection cover.

[0007] In one embodiment of the present invention, the stationary part protection cover is overlapped between the aircraft accessory casing and the outer shell of the engine accessory casing, and the rotating part transmission shaft is connected to the extension shafts of the aircraft accessory casing and the engine accessory casing.

[0008] In one embodiment of the present invention, the sensor module has two design margins, and a single design margin includes a connected Wheatstone bridge and a self-compensation circuit. The Wheatstone bridge and the self-compensation circuit are pasted on the surface of the transmission shaft of the rotating part and form a full-bridge structure in the form of a plate group.

[0009] In one embodiment of the present invention, the exterior of the sensor module is covered with high temperature protective glue.

[0010] In one embodiment of the present invention, the channel signal acquisition and transmission module includes a first channel signal acquisition and transmission module and a second channel signal acquisition and transmission module, and the first channel signal acquisition and transmission module and the second channel signal acquisition and transmission module both include an AC / DC conversion unit, a first DC / DC conversion unit, a signal amplification unit, a signal modulation unit and a ring transmitting antenna; The first channel signal acquisition and transmission module and the second channel signal acquisition and transmission module are respectively connected to a design redundancy in the sensor module and the induction power receiving coil; The AC / DC conversion unit is used to convert the AC voltage source obtained from the induction power receiving coil into a DC voltage, and further adjust it to a required voltage level through the first DC / DC conversion unit; The signal amplification unit is used to receive and amplify the torque signal to obtain an amplified signal; The signal modulation unit is used to modulate the amplified signal to obtain a modulated signal suitable for wireless transmission via radio frequency; The loop transmitting antenna is used to transmit the modulated signal to the receiving antenna in a radio frequency form.

[0011] In one embodiment of the present invention, the first channel signal acquisition and transmission module and the second channel signal acquisition and transmission module are both installed on the transmission shaft of the rotating member by means of dual epoxy resin and bundling fibers.

[0012] In one embodiment of the present invention, the signal receiver includes an EMI filter unit, a second DC / DC conversion unit, a signal demodulation unit, a signal output unit, and a communication interface unit; The EMI filter unit is used to perform electromagnetic interference filtering on the DC power supply from the onboard power supply; The second DC / DC conversion unit converts the filtered DC power into the low-voltage DC power; The signal demodulation unit is used to demodulate the radio frequency signal transmitted from the receiving antenna and restore the modulated signal to the original torque signal; The signal output unit is used to convert the demodulated signal into a voltage signal; The communication interface unit is interconnected with the airborne data acquisition system for data transmission, and is used to send the voltage signal to the airborne data acquisition system.

[0013] In one embodiment of the present invention, the induction power receiving coil is mounted on the rotating member transmission shaft through dual epoxy resin and bundling fibers.

[0014] In one embodiment of the present invention, the inductive power excitation coil and the receiving antenna are both arc-shaped structures, and are both provided with a shell made of polytetrafluoroethylene or nylon material, and the shell is connected to the stationary part protective cover by screws.

[0015] In one embodiment of the present invention, the conversion power box is installed on the frame of the aircraft engine compartment, and the signal receiver is installed in the main weapon compartment of the aircraft.

[0016] The above technical solution of the present invention has the following advantages compared with the prior art: The aircraft engine starting torque measuring device described in the present invention is suitable for torque measurement in limited space in an aircraft engine compartment. Through the reasonable arrangement of various modules, it can solve the problem that the existing torque measurement is difficult to install in a compact space, and will not interfere with the operation of the engine accessory system. The sensor module is used to directly obtain the torque signal of the rotating part transmission shaft, and the starting torque of the engine under different working conditions can be monitored in real time to ensure the accuracy of the measurement. In addition, the device transfers the energy from the stationary part to the rotating part through the inductive power supply technology, realizing contactless power supply to the sensor module on the rotating part transmission shaft, ensuring the normal measurement in actual flight and installation conditions.

[0017] The present invention adopts a direct measurement method and realizes the measurement of the starting torque of the generator in the installed state based on the existing aircraft components, and can complete the aircraft ground starting torque measurement and aircraft air auxiliary starting measurement. By adopting the direct measurement method, the measurement result avoids the measurement error caused by the loss of the casing.

[0018] The present invention can simultaneously meet the torque measurement requirements of the aircraft when starting on the ground and flying in the air. The sensor module adopts high temperature protection measures to ensure the long-term stable operation of the sensor module in the high temperature environment of the engine. Each functional module (sensor module, signal acquisition and transmission module, induction power supply module, etc.) is independently designed to facilitate the maintenance and replacement of the equipment, ensuring the long-term use of the device and low maintenance cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to make the contents of the present invention more clearly understood, the present invention is further described in detail below based on specific embodiments of the present invention in conjunction with the accompanying drawings.

[0020] Figure 1 The invention is a schematic diagram of the composition of the aircraft engine starting torque measuring device.

[0021] Figure 2 It is a schematic diagram of the layout of the aircraft engine starting torque measuring device of the present invention.

[0022] Figure 3 It is a structural schematic diagram of the power split shaft of the present invention.

[0023] Figure 4 yes Figure 3 Lateral view from the CC.

[0024] Figure 5It is a schematic diagram of the composition of the channel signal acquisition and transmission module of the present invention.

[0025] Figure 6 It is a schematic diagram of the composition of the signal receiver of the present invention.

[0026] Figure 7 It is a side view of the induction power supply excitation coil of the present invention.

[0027] Figure 8 FIG. 4 is a circuit diagram of the sensor module of the present invention.

[0028] Description of the Figures in the Specification: 1. Power split shaft; 2. Stationary part protection cover; 3. Rotating part transmission shaft; 4. Sensor module; 50. Channel signal acquisition and transmission module; 5. First channel signal acquisition and transmission module; 6. Second channel signal acquisition and transmission module; 61. AC / DC conversion unit; 62. First DC / DC conversion unit; 63. Signal amplification unit; 64. Signal modulation unit; 65. Ring transmitting antenna; 7. Inductive power supply excitation coil; 8. Receiving antenna; 9. Inductive power supply receiving coil; 10. Power conversion box; 11. Signal receiver; 110. EMI filtering unit; 120. Second DC / DC conversion unit; 130. Signal demodulation unit; 140. Signal output unit; 150. Communication interface unit; 12. Airborne data acquisition system; 13. Airborne power supply; 14. Aircraft engine compartment; 15. Main weapon compartment. DETAILED DESCRIPTION

[0029] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments so that those skilled in the art can better understand the present invention and implement it, but the embodiments are not intended to limit the present invention.

[0030] In the present invention, if directions (up, down, left, right, front and back) are described, it is only for the convenience of describing the technical solution of the present invention, and does not indicate or imply that the technical features referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, it cannot be understood as a limitation of the present invention.

[0031] In the present invention, "several" means one or more, "multiple" means more than two, "greater than", "less than", "exceed" and the like are understood to exclude the number itself; "above", "below", "within" and the like are understood to include the number itself. In the description of the present invention, if there is a description of "first" or "second", it is only used for the purpose of distinguishing technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0032] In the present invention, unless otherwise clearly defined, the words "set", "install", "connect" and the like should be understood in a broad sense, for example, they can be directly connected or indirectly connected through an intermediate medium; they can be fixedly connected or detachably connected or integrally formed; they can be mechanically connected or electrically connected or able to communicate with each other; they can be the internal connection of two elements or the interaction relationship between two elements. Those skilled in the art can reasonably determine the specific meanings of the above words in the present invention in combination with the specific content of the technical solution.

[0033] Reference Figure 1 , Figure 2 As shown, an aircraft engine starting torque measuring device of the present invention comprises: The power take-off shaft 1 is installed between the aircraft accessory casing and the engine accessory casing, and comprises a rotating part transmission shaft 3 and a stationary part protection cover 2 which is arranged on the rotating part transmission shaft 3; the power take-off shaft 1 is a part of the aircraft accessory transmission system, is a flexible transmission shaft, and can transmit the engine power and compensate for the misalignment and misalignment between the aircraft and the engine during the operation of the aircraft; A sensor module 4 is installed on the rotating member transmission shaft 3 and is used to obtain a torque signal of the rotating member transmission shaft 3; A channel signal acquisition and transmission module 50 is installed on the rotating member transmission shaft 3 and connected to the sensor module 4, and is used to receive and process the torque signal and then transmit a radio frequency signal; A receiving antenna 8, connected to the channel signal acquisition and transmission module 50, for receiving the radio frequency signal; A signal receiver 11 is connected to the receiving antenna 8 and the airborne power supply 13 respectively, and the signal receiver 11 is used to convert the DC power of the airborne power supply 13 into low-voltage DC power; and is used to receive the radio frequency signal transmitted from the receiving antenna 8, demodulate and convert it into a voltage signal, and then output it to the airborne data acquisition system 12; A conversion power supply box 10, used for converting the low voltage direct current into alternating current; The induction power supply module comprises an induction power supply receiving coil 9 and an induction power supply exciting coil 7, wherein the induction power supply exciting coil 7 is used to form a magnetic field from the alternating current, and the induction power supply receiving coil 9 receives the magnetic field and forms an alternating voltage source through electromagnetic induction; The channel signal acquisition and transmission module 50 is also connected to the induction power receiving coil 9, and converts the AC voltage source to power the sensor module 4; The induction power receiving coil 9 is installed on the rotating member transmission shaft 3; The induction power excitation coil 7 and the receiving antenna 8 are installed on the stationary part protection cover 2 .

[0034] Through the above settings, the induction power excitation coil 7 can form a magnetic field with the alternating current transmitted by the conversion power box 10, and power the induction power receiving coil 9 through electromagnetic induction. The induction power receiving coil 9 receives the magnetic field and forms a power supply through electromagnetic induction. Through the above induction power supply method, the energy on the stationary part can be transferred to the rotating part, and the sensor module 4 on the transmission shaft 3 of the rotating part can be powered contactlessly, ensuring that the measurement is carried out normally in the actual flight and installation state.

[0035] The torque measuring device can realize torque measurement when the aircraft is started on the ground and flying in the air, ensuring that the torque measurement task can be completed in the installed state.

[0036] Specifically, the stationary part protection cover 2 is positioned by pins and fixed by clamps, overlapped between the aircraft accessory casing and the outer shell of the engine accessory casing, and the rotating part transmission shaft 3 is connected to the extended shafts of the aircraft accessory casing and the engine accessory casing by connecting screws.

[0037] In one embodiment, referring to Figure 7 As shown, the sensor module 4 is responsible for directly measuring the torque on the transmission shaft and compensating for other interference factors such as temperature and bending. The sensor module 4 has two design margins. A single design margin includes a connected Wheatstone bridge and a self-compensation circuit. The Wheatstone bridge and the self-compensation circuit are pasted on the surface of the rotating part transmission shaft 3 and form a full-bridge structure in the form of a sheet group.

[0038] Specifically, the Wheatstone bridge includes a test resistor strain gauge (C1-C4) and a compensation strain gauge (T1-T4), and the self-compensation circuit includes a temperature compensation resistor (Rm1-Rm4), a normalization resistor (Rs1-Rs4), a zero point compensation resistor Rzb, and a zero point temperature drift compensation resistor Rzc.

[0039] Take one of the redundancies as an example, wherein the test resistance strain gauge C1 and the compensation strain gauge T1 are connected in series to form one branch of the bridge, and the test resistance strain gauge C3 and the compensation strain gauge T3 are connected in series to form another branch of the bridge.

[0040] The temperature compensation resistor Rm1 and the normalization resistor Rs1 are connected in series and are respectively connected between the test resistance strain gauge C1 and the compensation strain gauge T1 and the positive electrode of the power supply (B+); The temperature compensation resistor Rm3 and the normalization resistor Rs2 are connected in series and are respectively connected between the test resistance strain gauge C3 and the compensation strain gauge T3 and the negative pole of the power supply (B-); The test resistance strain gauge C1 and the compensation strain gauge T3 are connected to the signal positive electrode (S+); The zero compensation resistor Rzb is connected between the compensation strain gauge T1 and the signal negative electrode (S-); The zero temperature drift compensation resistor Rzc is connected between the test resistor strain C3 and the signal cathode (S-).

[0041] It can be understood that the test resistance strain gauge is pasted on the surface of the transmission shaft to detect the tiny deformation of the transmission shaft caused by torque, sense the torque changes on the transmission shaft in real time, and reflect the strain conditions on the shaft through resistance changes.

[0042] The compensation resistor strain gauge is used to compensate for signal errors caused by other environmental factors (such as temperature changes or mechanical stress). The compensation resistor strain gauge and the test resistor work together to eliminate unnecessary noise signals and ensure the purity and accuracy of the torque signal.

[0043] The temperature compensation resistor Rm is used to compensate for changes in the ambient temperature around the drive shaft to ensure that the measurement results will not be affected by temperature fluctuations; the standardization resistor Rs is used to ensure the standardization of the bridge output signal, reduce errors, improve measurement accuracy, and standardize the torque signal under different working conditions for subsequent signal processing; the zero point compensation resistor Rzb is used to compensate for the initial offset of the sensor to ensure that the measurement displays a zero signal in the no-torque state; the zero point temperature drift compensation resistor Rzc is used to compensate for the zero point drift problem caused by temperature changes to prevent the measurement reference point from drifting with changes in ambient temperature.

[0044] In addition, the entire sensor module 4 is covered with a layer of high temperature protective glue, which is used to protect the sensor module 4 from damage in a high temperature environment, especially when the engine is working, the ambient temperature around the transmission shaft will rise significantly. This protective layer ensures the reliability and long-term stability of the sensor under high temperature conditions.

[0045] Reference Figure 5 As shown, the channel signal acquisition and transmission module 50 includes a first channel signal acquisition and transmission module 5 and a second channel signal acquisition and transmission module 6. The first channel signal acquisition and transmission module 5 and the second channel signal acquisition and transmission module 6 both include an AC / DC conversion unit 61, a first DC / DC conversion unit 62, a signal amplification unit 63, a signal modulation unit 64 and a ring transmitting antenna 65; the first channel signal acquisition and transmission module 5 and the second channel signal acquisition and transmission module 6 are used to amplify the torque signal of the sensor module 4, and transmit the processed data to the receiving antenna 8 through a radio frequency signal. Each channel module has independent signal acquisition, processing and transmission functions to ensure the redundancy and stability of signal transmission.

[0046] The first channel signal acquisition and transmission module 5 and the second channel signal acquisition and transmission module 6 are respectively connected to a design redundancy in the sensor module 4 and the induction power receiving coil 9; The AC / DC conversion unit 61 is used to convert the AC voltage source obtained from the induction power receiving coil 9 into a DC voltage, and further adjust it to the required voltage level through the first DC / DC conversion unit 62; The signal amplifying unit 63 is used to receive and amplify the torque signal to obtain an amplified signal; The signal modulation unit 64 is used to modulate the amplified signal to obtain a modulated signal suitable for wireless transmission via radio frequency; reduce interference and attenuation in signal transmission; The annular transmitting antenna 65 is used to transmit the modulated signal to the receiving antenna 8 in the form of radio frequency; the annular antenna design can adapt to the complex environment of transmission shaft rotation and ensure stable signal transmission.

[0047] It should be noted that the first channel signal acquisition and transmission module 5 and the second channel signal acquisition and transmission module 6 share a conversion power box 10, and are each separately configured with a signal receiver 11. The conversion power box 10 is respectively connected to the signal receiver 11 and the induction power excitation coil 7, and includes a resonance unit, which can convert the low-voltage direct current transmitted from the signal receiver 11 into alternating current through the resonance unit, thereby providing an excitation signal for the induction power excitation coil 7.

[0048] In one embodiment, referring to Figure 4 As shown, the first channel signal acquisition and transmission module 5 and the second channel signal acquisition and transmission module 6 are both installed on the rotating member transmission shaft 3 through double epoxy resin and bundling fiber.

[0049] In one embodiment, referring to Figure 6 As shown, the signal receiver 11 includes an EMI filter unit 110 (EMI, electromagnetic interference), a second DC / DC conversion unit 120, a signal demodulation unit 130, a signal output unit 140, and a communication interface unit 150; The EMI filter unit 110 is used to perform electromagnetic interference filtering on the DC power supply (28V) from the onboard power supply 13; remove unnecessary noise and interference signals, ensure the purity of the power supply, and avoid interference with the signal reception and processing process; The second DC / DC conversion unit 120 converts the filtered DC power into the low-voltage DC power for use by the internal circuit of the signal receiver 11 and the conversion power box 10; The signal demodulation unit 130 is used to demodulate the radio frequency signal transmitted by the receiving antenna 8 and restore the modulated signal to the original torque signal; it can extract torque data from the wirelessly transmitted radio frequency signal to ensure data integrity; The signal output unit 140 is used to convert the demodulated signal into a (±10V) voltage signal, which facilitates data transmission and interface connection with the airborne data acquisition system 12. The communication interface unit 150 is interconnected with the airborne data acquisition system 12 for data transmission, so as to send the voltage signal to the airborne data acquisition system 12 .

[0050] It should be noted that the onboard power supply 13 (28V DC power supply) and the onboard data acquisition system 12 are both existing structures on the aircraft.

[0051] In one embodiment, the induction power receiving coil 9 is mounted on the rotating member transmission shaft 3 by means of dual epoxy resin and bundled fibers.

[0052] In one embodiment, referring to Figure 7 As shown, the inductive power excitation coil 7 and the receiving antenna 8 are both arc-shaped structures, specifically 140° arc-shaped, which can meet the inductive power supply strength and facilitate installation. The inductive power excitation coil 7 and the receiving antenna 8 are both provided with a shell made of polytetrafluoroethylene or nylon material, and the shell is connected to the stationary part protective cover 2 by screws. The receiving antenna 8 is installed on the stationary part and connected to the signal receiver 11 to ensure the stable transmission of torque data in the installed state.

[0053] It should be noted that the annular transmitting antenna 65 and the arc-shaped receiving antenna 8 can ensure stable signal transmission. Dual epoxy resin is a high-strength, chemically resistant adhesive material that can provide stable bonding and fixation for components such as the sensor module 4 and the inductive power receiving coil 9 in the high temperature and strong vibration environment of the aircraft engine. It helps to ensure that these key components do not shift or fall off during long-term use, ensuring the reliability and stability of the device. The bundling fiber further enhances the fixing effect. The bundling fiber (a high-strength material such as aramid fiber or glass fiber) has a high tensile strength and can effectively resist mechanical stress and prevent components from loosening due to high-speed rotation of the rotating drive shaft or external vibration.

[0054] In addition, double epoxy resin and bundled fiber are used to install it on the power take-off shaft, avoiding the use of bolts and other connecting structures. The total weight is no more than 150g, and does not affect the operating speed requirements of the existing transmission system.

[0055] In one embodiment, the conversion power box 10 is installed on a frame of an aircraft engine compartment 14 , and the signal receiver 11 is installed in a main weapon compartment 15 of the aircraft.

[0056] In one embodiment, the distance between the induction power excitation coil 7 and the induction power receiving coil 9 is 7-9 mm. Overall working process: The sensor module 4 is installed on the rotating part transmission shaft 3 to detect the slight deformation on the shaft in real time and generate a torque signal; The torque signal of the sensor is processed by the channel signal acquisition and transmission module 50, and the signal is amplified and transmitted to the receiving antenna 8 via radio frequency; The induction power supply excitation coil 7 generates a magnetic field, and the induction power supply receiving coil 9 receives the magnetic field and converts it into power to supply power to the sensor module 4; The signal receiver 11 receives the radio frequency signal through the receiving antenna 8, and after demodulation and conversion, outputs it as a voltage signal, which is transmitted to the airborne data acquisition system 12 for real-time analysis of the engine starting torque; The signals are stored and analyzed by the onboard data acquisition system 12, and the aircraft's control system can use them to evaluate engine performance and flight status.

[0057] Finally, it should be noted that the above specific implementation methods are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to examples, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the spirit and scope of the technical solution of the present invention, which should be included in the scope of the claims of the present invention.

Claims

1. An aircraft engine starting torque measuring device, characterized in that: include: A power take-off shaft (1) is installed between an aircraft accessory casing and an engine accessory casing, and comprises a rotating part transmission shaft (3) and a stationary part protection cover (2) which is arranged on the rotating part transmission shaft (3); A sensor module (4) is mounted on the rotating member transmission shaft (3) and is used to obtain a torque signal of the rotating member transmission shaft (3); A channel signal acquisition and transmission module (50) is installed on the rotating member transmission shaft (3) and connected to the sensor module (4), and is used for receiving and processing the torque signal and then transmitting a radio frequency signal; A receiving antenna (8), connected to the channel signal acquisition and transmission module (50), and used for receiving the radio frequency signal; A signal receiver (11) is connected to the receiving antenna (8) and the onboard power supply (13), respectively, and the signal receiver (11) is used to convert the DC power supply of the onboard power supply (13) into low-voltage DC power; and is used to receive the radio frequency signal transmitted from the receiving antenna (8), demodulate and convert the radio frequency signal into a voltage signal, and then output it to the onboard data acquisition system (12); A conversion power supply box (10), used for converting the low-voltage direct current into alternating current; An induction power supply module, comprising an induction power supply receiving coil (9) and an induction power supply exciting coil (7), wherein the induction power supply exciting coil (7) is used to form a magnetic field from the alternating current, and the induction power supply receiving coil (9) receives the magnetic field and forms an alternating current voltage source through electromagnetic induction; The channel signal acquisition and transmission module (50) is also connected to the induction power receiving coil (9), and converts the AC voltage source to supply power to the sensor module (4); The induction power receiving coil (9) is mounted on the rotating member transmission shaft (3); The induction power supply excitation coil (7) and the receiving antenna (8) are mounted on the stationary part protection cover (2).

2. The aircraft engine starting torque measuring device according to claim 1, characterized in that: The stationary part protection cover (2) is overlapped between the aircraft accessory casing and the outer shell of the engine accessory casing, and the rotating part transmission shaft (3) is connected to the extended shafts of the aircraft accessory casing and the engine accessory casing.

3. The aircraft engine starting torque measuring device according to claim 1, characterized in that: The sensor module (4) has two design margins, a single design margin comprising a connected Wheatstone bridge and a self-compensation circuit, the Wheatstone bridge and the self-compensation circuit being adhered to the surface of the rotating member transmission shaft (3) and forming a full bridge structure in the form of a sheet group.

4. The aircraft engine starting torque measuring device according to claim 3, characterized in that: The outside of the sensor module (4) is covered with high temperature protective glue.

5. The aircraft engine starting torque measuring device according to claim 3, characterized in that: The channel signal acquisition and transmission module (50) comprises a first channel signal acquisition and transmission module (5) and a second channel signal acquisition and transmission module (6), and the first channel signal acquisition and transmission module (5) and the second channel signal acquisition and transmission module (6) both comprise an AC / DC conversion unit (61), a first DC / DC conversion unit (62), a signal amplification unit (63), a signal modulation unit (64) and a ring-shaped transmitting antenna (65); The first channel signal acquisition and transmission module (5) and the second channel signal acquisition and transmission module (6) are respectively connected to a design redundancy in the sensor module (4) and the induction power receiving coil (9); The AC / DC conversion unit (61) is used to convert the AC voltage source obtained from the induction power receiving coil (9) into a DC voltage, and further adjust the voltage to a required level through the first DC / DC conversion unit (62); The signal amplification unit (63) is used to receive and amplify the torque signal to obtain an amplified signal; The modulation unit (64) is used to modulate the amplified signal to obtain a modulated signal suitable for wireless transmission via radio frequency; The annular transmitting antenna (65) is used to transmit the modulated signal to the receiving antenna (8) in a radio frequency form.

6. The aircraft engine starting torque measuring device according to claim 5, characterized in that: The first channel signal acquisition and transmission module (5) and the second channel signal acquisition and transmission module (6) are both mounted on the rotating member transmission shaft (3) by means of double epoxy resin and bundled fibers.

7. The aircraft engine starting torque measuring device according to claim 1, characterized in that: The signal receiver (11) comprises an EMI filtering unit (110), a second DC / DC conversion unit (120), a signal demodulation unit (130), a signal output unit (140), and a communication interface unit (150); The EMI filtering unit (110) is used to perform electromagnetic interference filtering processing on the direct current power supply from the onboard power supply (13); The second DC / DC conversion unit (120) converts the filtered DC power into the low-voltage DC power; The signal demodulation unit (130) is used to demodulate the radio frequency signal transmitted by the receiving antenna (8) and restore the modulated signal to the original torque signal; The signal output unit (140) is used to convert the demodulated signal into a voltage signal; The communication interface unit (150) is interconnected with the onboard data acquisition system (12) for data transmission, and is used to send the voltage signal to the onboard data acquisition system (12).

8. The aircraft engine starting torque measuring device according to claim 1, characterized in that: The induction power receiving coil (9) is mounted on the rotating member transmission shaft (3) via dual epoxy resin and bundled fibers.

9. The aircraft engine starting torque measuring device according to claim 1, characterized in that: The induction power excitation coil (7) and the receiving antenna (8) are both arc-shaped structures, and are both provided with a shell made of polytetrafluoroethylene or nylon material outside the induction power excitation coil (7) and the receiving antenna (8), and the shell is connected to the stationary part protection cover (2) by screws.

10. The aircraft engine starting torque measuring device according to claim 1, characterized in that: The conversion power box (10) is installed on a frame of an aircraft engine compartment (14), and the signal receiver (11) is installed in a main weapon compartment (15) of the aircraft.

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