阅读说明：本技术 一种飞行器动力测试装置 (Aircraft power testing arrangement ) 是由 张凯 张世隆 邓丽敏 葛航 和林 甄龙豹 王天培 于 2018-06-06 设计创作，主要内容包括：本发明提供了一种飞行器动力测试装置,具体包括：转速测试模块、扭矩测试模块、升力测试模块以及控制器；其中,所述转速测试模块,用于测试所述飞行器动力系统的转速,得到转速信号；所述扭矩测试模块,用于测试所述飞行器动力系统的扭矩,得到扭矩信号；所述升力测试模块包括杠杆组件和升力测试子模块,所述杠杆组件连接在所述扭矩测试模块和所述升力测试子模块之间；所述升力测试模块用于测试所述飞行器动力系统的升力,得到升力信号；所述控制器根据所述转速信号、所述扭矩信号、所述升力信号,得到所述飞行器动力系统的转速参数、扭矩参数、升力参数。本发明所述的飞行器动力测试装置可以同时测试所述飞行器动力系统的转速参数、扭矩参数、升力参数,测试效率较高,测试精度高。(the invention provides an aircraft power testing device, which specifically comprises: the device comprises a rotating speed testing module, a torque testing module, a lift force testing module and a controller; the rotating speed testing module is used for testing the rotating speed of the aircraft power system to obtain a rotating speed signal; the torque testing module is used for testing the torque of the aircraft power system to obtain a torque signal; the lift force testing module comprises a lever assembly and a lift force testing sub-module, and the lever assembly is connected between the torque testing module and the lift force testing sub-module; the lift force testing module is used for testing the lift force of the aircraft power system to obtain a lift force signal; and the controller obtains a rotating speed parameter, a torque parameter and a lift parameter of the aircraft power system according to the rotating speed signal, the torque signal and the lift signal. The aircraft power testing device can simultaneously test the rotating speed parameter, the torque parameter and the lift force parameter of the aircraft power system, and has high testing efficiency and high testing precision.)

1. An aircraft power testing device for testing performance parameters of an aircraft power system, the aircraft power system comprising: the motor is fixedly connected with the propeller; aircraft driving system power test device includes: the device comprises a rotating speed testing module, a torque testing module, a lift force testing module and a controller; wherein

the rotating speed testing module is arranged on the aircraft power system and used for testing the rotating speed of the aircraft power system to obtain a rotating speed signal;

the torque testing module is connected with the motor and used for testing the torque of the aircraft power system to obtain a torque signal;

the lift force testing module comprises a lever assembly and a lift force testing sub-module, and the lever assembly is connected between the torque testing module and the lift force testing sub-module; the lift force testing module is used for testing the lift force of the aircraft power system to obtain a lift force signal;

The controller is respectively connected with the rotating speed testing module, the torque testing module and the lift force testing module and is used for obtaining a rotating speed parameter, a torque parameter and a lift force parameter of the aircraft power system according to the rotating speed signal, the torque signal and the lift force signal.

2. the aircraft dynamics testing apparatus of claim 1, wherein the torque testing module comprises: an adaptor and a torque sensor; wherein

the adaptor is respectively connected with the motor and the torque sensor and is used for transmitting the torque of the propeller connected with the motor to the torque sensor;

The torque sensor is used for testing the torque of the propeller to obtain the torque signal.

3. the aircraft dynamics testing apparatus of claim 2, wherein the torque testing module further comprises: a thrust bearing and a bearing cap; wherein

the thrust bearing is positioned between the torque sensor and the bearing cover;

one end of the bearing cover is connected with the thrust bearing and used for fixing the thrust bearing.

4. The aircraft dynamic testing device of claim 3, wherein the lever assembly comprises: the device comprises a cross beam, a rotating shaft, a bearing and a bearing seat; wherein

The middle of the cross beam is rotationally connected with the rotating shaft;

The inner ring and the outer ring of the bearing are respectively connected with the rotating shaft and the bearing seat;

One end of the cross beam is connected with the bearing cover, and the other end of the cross beam is connected with the lift force testing submodule.

5. The aircraft dynamic testing device of claim 4, wherein the lift test submodule comprises: the pressure sensor and the fixed base; wherein

the pressure sensor is respectively connected with the cross beam and the fixed base and used for testing the lift force of the propeller to obtain the lift force signal.

6. The aircraft dynamics testing apparatus of claim 5, wherein the rotational speed testing module comprises: the device comprises a light reflecting structure, a photoelectric sensor and a photoelectric sensor bracket; wherein

the reflecting structure is arranged on the propeller or the motor;

The photoelectric sensor is used for receiving the photoelectric pulse generated by the reflecting structure to obtain the rotating speed signal;

The photoelectric sensor support is used for fixing the photoelectric sensor.

7. the aircraft dynamic testing device of claim 6, wherein the input of the controller is connected to the photoelectric sensor, the torque sensor, and the pressure sensor, respectively; wherein

the controller is used for processing the rotating speed signal obtained by the photoelectric sensor, the torque signal obtained by the torque sensor and the lift force signal obtained by the pressure sensor to obtain the rotating speed parameter, the torque parameter and the lift force parameter.

8. The aircraft dynamics testing apparatus of claim 7, wherein the aircraft power system further comprises: an electronic governor; wherein

one end of the electronic speed regulator is connected with the output end of the controller, and the other end of the electronic speed regulator is connected with the motor and used for supplying power to the motor and regulating the rotating speed of the motor according to a motor control command of the controller.

9. The aircraft dynamics testing apparatus of claim 7, further comprising: a first signal amplifier and a second signal amplifier; wherein

The first signal amplifier is positioned between the torque sensor and the controller and is used for amplifying the torque signal;

The second signal amplifier is positioned between the pressure sensor and the controller and is used for amplifying the lift force signal.

10. The aircraft dynamics testing apparatus of claim 1, further comprising: and the upper computer is connected with the controller and is used for displaying the rotating speed parameter, the torque parameter and the lift force parameter obtained by the controller.

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft power testing device.

Background

Along with the high-speed development of aircraft technique, the aircraft has more and more been used in each field of production, life, and many rotor crafts as a neotype aircraft, can be extensive use in aspects such as agricultural plant protection, aerial photography, patrolling and examining, survey and drawing, investigation.

in the existing multi-rotor aircraft, a rotor system is often required to provide lift force to enable the multi-rotor aircraft to achieve maneuvering functions such as take-off, cruise, hovering and landing, the rotor system is used as a power source of the multi-rotor aircraft, and performance parameters of the rotor system play a vital role in the effective load and the dynamic performance of the whole aircraft, so that in practical application, an aircraft power testing device is often required to test the performance parameters of the rotor system.

The rotating speed parameter, the torque parameter and the lift parameter are used as more key parameters in the performance parameters of the rotor wing system, and can be used for comprehensively evaluating the dynamic performance of the rotor wing system. The existing aircraft power testing device is often difficult to test the three performance parameters simultaneously, so that the testing efficiency is not high easily; or, the torque parameter testing module and the lift parameter testing module in the aircraft power testing device interfere with each other, so that the testing precision of the torque parameter and the lift parameter is influenced, and the testing result error is larger.

Disclosure of Invention

In view of this, the present invention provides an aircraft power testing apparatus, so as to solve the problems of low testing accuracy and large testing result error of the existing aircraft power testing apparatus.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

An aircraft power testing apparatus for testing performance parameters of an aircraft power system, the aircraft power system comprising: the motor is fixedly connected with the propeller; the aircraft dynamic testing device comprises: the device comprises a rotating speed testing module, a torque testing module, a lift force testing module and a controller; wherein

the rotating speed testing module is arranged on the aircraft and used for testing the rotating speed of the aircraft power system to obtain a rotating speed signal;

The torque testing module is connected with the motor and used for testing the torque of the aircraft power system to obtain a torque signal;

the lift force testing module comprises a lever assembly and a lift force testing sub-module, and the lever assembly is connected between the torque testing module and the lift force testing sub-module; the lift force testing module is used for testing the lift force of the aircraft power system to obtain a lift force signal;

the controller is respectively connected with the rotating speed testing module, the torque testing module and the lift force testing module and is used for obtaining a rotating speed parameter, a torque parameter and a lift force parameter of the aircraft power system according to the rotating speed signal, the torque signal and the lift force signal.

Further, the torque testing module includes: an adaptor and a torque sensor; wherein

the adaptor is respectively connected with the motor and the torque sensor and is used for transmitting the torque of the propeller connected with the motor to the torque sensor;

The torque sensor is used for testing the torque of the propeller to obtain the torque signal.

further, the torque testing module further comprises: a thrust bearing and a bearing cap; wherein

The thrust bearing is positioned between the torque sensor and the bearing cover;

One end of the bearing cover is connected with the thrust bearing and used for fixing the thrust bearing.

further, the lever assembly includes: the device comprises a cross beam, a rotating shaft, a bearing and a bearing seat; wherein

The middle of the cross beam is rotationally connected with the rotating shaft;

the inner ring and the outer ring of the bearing are respectively connected with the rotating shaft and the bearing seat;

One end of the cross beam is connected with the bearing cover, and the other end of the cross beam is connected with the lift force testing submodule.

Further, the lift test sub-module comprises: the pressure sensor and the fixed base; wherein

The pressure sensor is respectively connected with the cross beam and the fixed base and used for testing the lift force of the propeller to obtain the lift force signal.

Further, the rotation speed testing module comprises: the device comprises a light reflecting structure, a photoelectric sensor and a photoelectric sensor bracket; wherein

the reflecting structure is arranged on the propeller or the motor;

The photoelectric sensor is used for receiving the photoelectric pulse generated by the reflecting structure to obtain the rotating speed signal;

The photoelectric sensor support is used for fixing the photoelectric sensor.

further, the input end of the controller is respectively connected with the photoelectric sensor, the torque sensor and the pressure sensor; wherein

the controller is used for processing the rotating speed signal obtained by the photoelectric sensor, the torque signal obtained by the torque sensor and the lift force signal obtained by the pressure sensor to obtain the rotating speed parameter, the torque parameter and the lift force parameter.

Further, the aircraft power system further comprises: an electronic governor; wherein

one end of the electronic speed regulator is connected with the output end of the controller, and the other end of the electronic speed regulator is connected with the motor and used for supplying power to the motor and regulating the rotating speed of the motor according to a motor control command of the controller.

Further, the aircraft dynamic testing device further comprises: a first signal amplifier and a second signal amplifier; wherein

The first signal amplifier is positioned between the torque sensor and the controller and is used for amplifying the torque signal;

The second signal amplifier is positioned between the pressure sensor and the controller and is used for amplifying the lift force signal.

Further, the aircraft dynamic testing device further comprises: and the upper computer is connected with the controller and is used for displaying the rotating speed parameter, the torque parameter and the lift force parameter obtained by the controller.

Compared with the prior art, the aircraft power testing device has the following advantages:

First, in the aircraft power testing device according to the embodiment of the present invention, the rotation speed testing module, the torque testing module, and the lift force testing module may be respectively configured to test a rotation speed, a torque, and a lift force of the aircraft power system to obtain corresponding rotation speed signals, torque signals, and lift force signals, and the controller may obtain a rotation speed parameter, a torque parameter, and a lift force parameter of the aircraft power system according to the rotation speed signals, the torque signals, and the lift force signals.

in addition, in the aircraft power testing device according to the embodiment of the present invention, the lift force testing module may include a lever assembly and a lift force testing sub-module, and the lever assembly may be connected between the torque testing module and the lift force testing sub-module, and in practical applications, the lever assembly may be configured to isolate the torque and the lift force generated by the aircraft power system, and prevent the torque of the torque testing module from being transmitted to the lift force testing sub-module, so that the torque testing module and the lift force testing sub-module may be prevented from interfering with each other, the testing errors of the torque parameter and the lift force parameter may be reduced, and the testing accuracy may be improved.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 is a block diagram of an aircraft dynamics testing apparatus according to an embodiment of the present invention;

FIG. 2 is a schematic structural diagram of an aircraft dynamic testing apparatus according to an embodiment of the present invention;

FIG. 3 is a schematic structural diagram of a rotational speed testing module according to an embodiment of the present invention;

FIG. 4 is a schematic structural diagram of a torque testing module according to an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of a lift force testing module according to an embodiment of the present invention;

FIG. 6 is a schematic structural diagram of a lever assembly according to an embodiment of the present invention;

Fig. 7 is a block diagram of another aircraft dynamics testing apparatus according to the present invention.

Description of reference numerals:

10-rotating speed testing module, 101-reflecting structure, 102-photoelectric sensor, 103-photoelectric sensor bracket, 11-torque testing module, 111-adaptor, 112-torque sensor, 113-thrust bearing, 114-bearing cover, 12-lift force testing module, 121-lever component, 1211-beam, 1212-rotating shaft and 1213-bearing. 1214, a bearing seat, 122, a lift force testing submodule, 1221, a pressure sensor, 1222, a fixed base, 13, a controller, 141, a motor, 142, a propeller, 143, an electronic speed regulator, 15, a first signal amplifier, 16, a second signal amplifier and 17, and an upper computer.

Detailed Description

it should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.

the present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

Referring to fig. 1, a block diagram of an aircraft power testing apparatus according to an embodiment of the present invention is shown, configured to test power performance parameters of an aircraft power system, where the aircraft power system may include: a motor; the aircraft dynamic testing device may include: the device comprises a rotating speed testing module 10, a torque testing module 11, a lift force testing module 12 and a controller 13; wherein the content of the first and second substances,

the rotating speed testing module 10 is arranged on the aircraft power system and can be used for testing the rotating speed of the aircraft power system to obtain a rotating speed signal;

the torque testing module 11 is connected with the motor and can be used for testing the torque of the aircraft power system to obtain a torque signal;

The lift testing module 12 may include a lever assembly and a lift testing sub-module, the lever assembly being connected between the torque testing module 11 and the lift testing sub-module; the lift force test module 11 can be used for testing the lift force of the aircraft power system to obtain a lift force signal;

The controller 13 is respectively connected with the rotating speed testing module 10, the torque testing module 11 and the lift force testing module 12, and is used for obtaining a rotating speed parameter, a torque parameter and a lift force parameter of the aircraft power system according to the rotating speed signal, the torque signal and the lift force signal.

In the aircraft power testing device according to the embodiment of the present invention, the rotation speed testing module 10, the torque testing module 11, and the lift force testing module 12 may be respectively configured to test the rotation speed, the torque, and the lift force of the aircraft power system to obtain corresponding rotation speed signals, torque signals, and lift force signals, and the controller 13 may obtain the rotation speed parameters, the torque parameters, and the lift force parameters of the aircraft power system according to the rotation speed signals, the torque signals, and the lift force signals.

In addition, in the aircraft power testing device according to the embodiment of the present invention, the lift force testing module 12 may include a lever assembly and a lift force testing sub-module, and the lever assembly may be connected between the torque testing module 11 and the lift force testing sub-module, and in practical applications, the lever assembly may be configured to isolate the torque and the lift force generated by the aircraft power system, and prevent the torque of the torque testing module 11 from being transmitted to the lift force testing sub-module, so that mutual interference between the torque testing module 11 and the lift force testing sub-module may be avoided, test errors of the torque parameter and the lift force parameter may be reduced, and test accuracy may be improved.

Referring to fig. 2, a schematic structural diagram of an aircraft dynamic testing device according to an embodiment of the present invention is shown, where the aircraft dynamic system may include: electric machine 141, the aircraft dynamic testing device may include: a rotation speed test module 10, a torque test module 11, a lift force test module 12 and a controller (not shown in the figure); wherein the content of the first and second substances,

The rotating speed testing module 10 is arranged on the aircraft power system and can be used for testing the rotating speed of the aircraft power system to obtain a rotating speed signal;

the torque testing module 11 is connected with the motor 141 and can be used for testing the torque of the aircraft power system to obtain a torque signal;

The lift testing module 12 may include a lever assembly 121 and a lift testing sub-module 122, the lever assembly 121 being connected between the torque testing module 11 and the lift testing sub-module 122; the lift force test module 11 can be used for testing the lift force of the aircraft power system to obtain a lift force signal;

the controller is respectively connected with the rotating speed testing module 10, the torque testing module 11 and the lift force testing module 12 and is used for obtaining a rotating speed parameter, a torque parameter and a lift force parameter of the aircraft power system according to the rotating speed signal, the torque signal and the lift force signal.

In an embodiment of the invention, the aircraft power system may further comprise a propeller 142; the propeller 142 and the motor 141 are fixedly connected, and in practical application, the propeller 142 and the motor 141 can be fixedly connected through connection modes such as snap connection and threaded connection.

Referring to fig. 3, a schematic structural diagram of a rotational speed testing module according to an embodiment of the present invention is shown, which may specifically include: a light reflecting structure 101, a photosensor 102, and a photosensor holder 103; wherein, the light reflecting structure 101 is arranged on the propeller 142 or the motor 141; the photoelectric sensor 102 is used for receiving photoelectric pulses generated by the light reflecting structure 101 to obtain the rotating speed signal; the photosensor holder 103 may be used to hold the photosensor 102.

specifically, the light reflecting structure 101 may be a light reflecting sheet, and since the light reflecting sheet has the advantages of small mass and large light reflecting area, if the light reflecting structure 101 employs the light reflecting sheet, the light reflected by the light reflecting structure 101 may be more. In practical applications, the light reflecting structure 101 may be fixed to the propeller 142 or the motor 141 by an adhesive connection, a rivet connection, or the like. Fig. 1 shows only an example that the light reflecting structure 101 is fixed on the motor 141, and it is understood that the light reflecting structure 101 may be fixed on the propeller 142 in practical applications.

In the embodiment of the invention, since the light reflecting structure 101 is fixed on the propeller 142 or the motor 141, when the propeller 142 and the motor 141 rotate, the light reflecting structure 101 can rotate together with the propeller 142 and the motor 141, and when the light emitting structure 101 rotates, light reflected by the light reflecting structure 101 can generate corresponding photoelectric pulses at the receiving end of the photoelectric sensor 102, and the photoelectric sensor 102 can be used for receiving the photoelectric pulses to obtain the rotating speed signal and sending the rotating speed signal to the controller 13, so that the controller 13 obtains the rotating speed parameter of the aircraft power system according to the rotating speed signal.

For example, during the rotation of the light reflecting structure 101 together with the propeller 142 and the motor 141, the light reflected by the light reflecting structure 101 may generate a photoelectric pulse at the receiving end of the photoelectric sensor 102 once every rotation, and the photoelectric sensor 102 may be configured to receive the photoelectric pulse, obtain a rotation speed signal, and send the rotation speed signal to the controller 13. The controller 13 may obtain the speed parameter of the aircraft power system by counting the number of times the speed signal is received.

Referring to fig. 4, a schematic structural diagram of a torque testing module according to an embodiment of the present invention is shown, which may specifically include: an adaptor 111, a torque sensor 112; the adaptor 111 is respectively connected with the motor 141 and the torque sensor 112, and is used for transmitting the torque of the propeller 142 connected with the motor 141 to the torque sensor 112; the torque sensor 112 may be used to test the torque of the propeller 142, resulting in the torque signal.

In practical applications, the adaptor 111 may be fixedly connected at a top end thereof to a stator of the motor 141, and at the other end thereof to the torque sensor 112, so as to transmit torque generated during rotation of the propeller 142 connected to the motor 141 to the torque sensor 112. The torque sensor 112 may be used to test the torque of the propeller 142, derive the torque signal, and send the torque signal to the controller 13, such that the controller 13 derives a torque parameter of the aircraft powertrain from the torque signal.

In an alternative embodiment of the present invention, the torque testing module 11 may further include: a thrust bearing 113 and a bearing cap 114; wherein, the thrust bearing 113 is positioned between the torque sensor 112 and the motor 141; one end of the bearing cover 114 is connected with the thrust bearing 113 for fixing the thrust bearing 113, and the other end of the bearing cover 114 is connected with the lift force testing module 12. In practical application, in the process of rotating the propeller 142, a pulling force may be generated on the torque sensor 112, so as to avoid interference of the pulling force on the torque sensor 112 and reduction of the testing accuracy of the torque sensor 112, in the embodiment of the present invention, a thrust bearing 113 is disposed between the torque sensor 112 and the bearing cap 114, and the thrust bearing 113 may be used to bear the pulling force, so as to avoid interference of the pulling force on the torque sensor 112, improve the testing accuracy of the torque sensor 112, and further improve the testing accuracy of the torque parameter of the aircraft power system.

Referring to fig. 5, a schematic structural diagram of a lift test module according to an embodiment of the present invention is shown, which may specifically include: the lever assembly 121 is connected between the torque testing module 11 and the lift testing submodule 122; the lift test module 12 may be configured to test the lift of the aircraft power system to obtain a lift signal.

Referring to fig. 6, a schematic structural diagram of a lever assembly according to an embodiment of the present invention is shown, which may specifically include: beam 1211, shaft 1212, bearing 1213 and bearing seat 1214; wherein, the middle of the cross beam 1211 is rotatably connected with the rotating shaft 1212; the inner ring and the outer ring of the bearing 1213 are respectively connected with the rotating shaft 1212 and the bearing seat 1214; one end of the beam 1211 is connected to the bearing cap 114, and the other end of the beam 1211 is connected to the lift test submodule 122.

In the embodiment of the invention, as the middle of the cross beam 1211 is rotatably connected with the rotating shaft 1212, the rotating freedom degree of the cross beam 1211 in the horizontal plane can be limited through the rotating shaft 1212, and the torque of the torque testing module 11 is prevented from being transmitted to the lift force testing sub-module 122, so that the mutual interference between the torque testing module 11 and the lift force testing sub-module 122 can be avoided, the testing errors of the torque parameter and the lift force parameter are reduced, and the testing precision is improved.

in practical applications, the inner ring and the outer ring of the bearing 1213 may be connected to the rotating shaft 1212 and the bearing seat 1214, respectively, and the bearing 1213 may be used to bear the radial force of the rotating shaft 1212, and support the rotating shaft 1212, so that the cross beam 1211 can rotate around the rotating shaft 1212.

in the embodiment of the present invention, since one end of the cross beam 1211 is connected to the bearing cap 114, and the other end of the cross beam 1211 is connected to the lift force testing submodule 122, in a specific application, the end of the cross beam 1211 connected to the bearing cap 114 may be used as a force application end, specifically, the force application end may be used to bear the lift force generated by the propeller 142 during the rotation process, and the end of the cross beam 1211 connected to the lift force testing submodule 122 may be used as a force bearing end, the pressure applied to the force bearing end is balanced with the lift force generated by the propeller 142 applied to the force application end with respect to the moment of the rotating shaft 1212, and in an actual application, the lift force generated by the propeller 142 applied to the force application end may be calculated by measuring the pressure applied to the force bearing end.

In another alternative embodiment of the present invention, the lift test sub-module 122 may specifically include: a pressure sensor 1221 and a fixed base 1222; wherein, the pressure sensor 1221 is respectively connected with the cross beam 1211 and the fixed base 1222, and is used for testing the lift force of the propeller 142 to obtain the lift force signal, and the fixed base 1222 can be used for fixedly supporting the pressure sensor 1221.

In the embodiment of the present invention, since the end of the cross beam 1211, which is connected to the pressure sensor 1221, can be used as a force-bearing end, and the pressure applied to the force-bearing end is in moment balance with the lift force generated by the propeller 142 applied to the force-applying end with respect to the rotating shaft 1212, in practical applications, the lift force generated by the propeller 142 applied to the force-applying end can be calculated by measuring the pressure applied to the force-bearing end and performing reverse thrust. Therefore, the pressure sensor 1221 tests the lift force of the propeller 142 to obtain the lift force signal, the lift force signal may directly reflect the magnitude of the lift force generated by the propeller 142 during the rotation process, and in a specific application, the pressure sensor 1221 may send the lift force signal to the controller 13, so that the controller 13 obtains the lift force parameter of the aircraft power system according to the lift force signal.

Referring to fig. 7, which shows a block diagram of another aircraft dynamic testing apparatus according to the present invention, as shown in fig. 7, the input terminals of the controller 13 may be connected to the photoelectric sensor 102, the torque sensor 112, and the pressure sensor 1221; the controller 13 may be configured to process the rotation speed signal obtained by the photoelectric sensor 102, the torque signal obtained by the torque sensor 112, and the lift force signal obtained by the pressure sensor 1221 to obtain the rotation speed parameter, the torque parameter, and the lift force parameter.

In practical application, because the torque signal and the lift force signal belong to analog quantity signals and are weak, the torque signal and the lift force signal can be conveniently received by the controller 13 for amplification, and in specific application, the torque signal and the lift force signal can be amplified by a signal amplifier.

In an optional embodiment of the present invention, the aircraft dynamics testing apparatus may further include: a first signal amplifier 15 and a second signal amplifier 16; the first signal amplifier 15 is located between the torque sensor 112 and the controller 13, and is configured to amplify the torque signal obtained by the torque sensor 112; a second signal amplifier 16 may be located between the pressure sensor 1221 and the controller 13 for amplifying said lift force signal obtained by the pressure sensor 1221.

It is understood that the first signal amplifier 15 and the second signal amplifier 16 may be analog signal amplifiers, which may directly amplify the torque signal and the lift signal, or the first signal amplifier 15 and the second signal amplifier 16 may also be signal conversion amplifiers, which may convert and amplify the torque signal and the lift signal into digital signals for the controller 13 to receive. The specific types of the first signal amplifier 15 and the second signal amplifier 16 are not limited in the embodiment of the present invention.

Optionally, in order to supply power to the first signal amplifier 15 and the second signal amplifier 16, in this embodiment of the present invention, a separate power supply may be provided to supply power to the first signal amplifier 15 and the second signal amplifier 16, or a power management system may be provided to supply power to the first signal amplifier 15 and the second signal amplifier 16, where the power supply type of the first signal amplifier 15 and the second signal amplifier 16 is not specifically limited in the present invention.

In practical applications, the aircraft power system may further include: an electronic governor 143. In the embodiment of the present invention, one end of the electronic governor 143 may be connected to the output end of the controller 13, and the other end is connected to the motor 141, and is configured to supply power to the motor 141 according to a motor control command of the controller 13 and adjust the rotation speed of the motor 141.

In yet another optional embodiment of the present invention, the aircraft dynamics testing apparatus further comprises: and the upper computer 17 is connected with the controller and is used for displaying the rotating speed parameter, the torque parameter and the lift force parameter which are obtained by the controller 13. In this way, it is convenient for a user to view the speed parameter, the torque parameter, and the lift parameter of the aircraft power system.

The following provides a working example of the aircraft dynamic testing device:

First, the controller 13 may output a motor control command to the electronic governor 143, and the electronic governor 143 may supply power to the motor 141 according to the motor control command and adjust a rotation speed of the motor 141, so that the motor 141 starts to rotate, and since the motor 141 is fixedly connected to the propeller 142, the rotation of the motor 141 may drive the propeller 142 to rotate.

During the rotation of the propeller 142, the rotation speed testing module 10, the torque testing module 11 and the lift force testing module 12 of the aircraft power testing device also start to work. The photoelectric sensor 102 may test the rotation speed of the propeller 142 to obtain the rotation speed signal, and directly send the rotation speed signal to the controller 13; the torque sensor 112 may test the torque of the propeller 142 to obtain the torque signal, and the torque signal may be amplified by the first signal amplifier 15 and then sent to the controller 13; the pressure sensor 1221 may test the lift force of the propeller 142 to obtain the lift force signal, which may be amplified by the second signal amplifier 16 and then sent to the controller 13.

The controller 13 may process the rotation speed signal obtained by the photoelectric sensor 102, the torque signal obtained by the torque sensor 112, and the lift force signal obtained by the pressure sensor 1221 to obtain the rotation speed parameter, the torque parameter, and the lift force parameter. And the rotating speed parameter, the torque parameter and the lift force parameter are displayed on an upper computer 17 connected with the controller 13, so that a user can conveniently view the rotating speed parameter, the torque parameter and the lift force parameter of the aircraft power system.

in conclusion, the aircraft power testing device provided by the invention has the following advantages:

First, in the aircraft power testing device according to the embodiment of the present invention, the rotation speed testing module, the torque testing module, and the lift force testing module may be respectively configured to test a rotation speed, a torque, and a lift force of the aircraft power system to obtain corresponding rotation speed signals, torque signals, and lift force signals, and the controller may obtain a rotation speed parameter, a torque parameter, and a lift force parameter of the aircraft power system according to the rotation speed signals, the torque signals, and the lift force signals.

in addition, in the aircraft power testing device according to the embodiment of the present invention, the lift force testing module may include a lever assembly and a lift force testing sub-module, and the lever assembly may be connected between the torque testing module and the lift force testing sub-module, and in practical applications, the lever assembly may be configured to isolate the torque and the lift force generated by the aircraft power system, and prevent the torque of the torque testing module from being transmitted to the lift force testing sub-module, so that the torque testing module and the lift force testing sub-module may be prevented from interfering with each other, the testing errors of the torque parameter and the lift force parameter may be reduced, and the testing accuracy may be improved.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.