CN216050691U - Multichannel coordinated loading electric feedback type unmanned helicopter transmission test system - Google Patents
Multichannel coordinated loading electric feedback type unmanned helicopter transmission test system Download PDFInfo
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- CN216050691U CN216050691U CN202023023730.3U CN202023023730U CN216050691U CN 216050691 U CN216050691 U CN 216050691U CN 202023023730 U CN202023023730 U CN 202023023730U CN 216050691 U CN216050691 U CN 216050691U
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Abstract
The utility model discloses a multichannel coordinated loading electric feedback type unmanned helicopter transmission test system which comprises a power output mechanism, a main rotor load simulation mechanism, a main reducing output shaft loading unit, a tail rotor load simulation mechanism, a tail reducing output shaft loading unit, a data acquisition and processing unit and a control unit, wherein the main reducing output shaft loading unit is connected with the tail rotor load simulation mechanism; the power output mechanism is used for providing simulated input drive for the transmission mechanism of the unmanned helicopter; the main rotor load simulation mechanism is used for simulating the main rotor torque of the unmanned helicopter; the main reducer output shaft loading unit is used for simulating lift force, lateral force and bending moment in actual flight; the tail reduction output shaft loading unit is used for simulating tail shaft thrust in actual flight; the tail rotor load simulation mechanism is used for simulating tail rotor torque in actual flight. Not only can the torque applied by the engine and the main tail blades be applied, but also the lift force and the bending moment from the main tail rotor system can be applied, and almost all actual loads applied to a transmission mechanism in the flight process can be simulated.
Description
Technical Field
The utility model relates to an unmanned helicopter transmission test system, in particular to an electric feedback type unmanned helicopter transmission test system with multi-channel coordinated loading, and belongs to the field of unmanned helicopter manufacturing.
Background
The transmission system of the unmanned helicopter is one of three major dynamic components, bears complex static load and fatigue load brought by a rotor wing, a tail rotor, an operating system and an engine system, and does not adopt redundancy technology or compound force transmission conditions. The flight safety of the unmanned helicopter is directly threatened once the transmission system components are fatigued. Both military and civilian airworthiness specifications require that the transmission system have a very low probability of fatigue failure during the life cycle of the helicopter. In order to avoid catastrophic consequences caused by fatigue, fatigue tests must be conducted on the transmission system, and repair and replacement of transmission system components are scientifically managed in combination with repair intervals to ensure flight safety.
The transmission system of the unmanned helicopter is different from traditional moving parts such as rotor blades, and the fatigue test of the transmission box cannot be carried out by the traditional moving part fatigue test system. The transmission system of the unmanned helicopter is complex in structure, and the borne load is different from moving parts such as a helicopter rotor and a control, and the transmission system not only bears the torque applied by an engine and a main tail rotor blade, but also bears the lift force and the bending moment brought by a main tail rotor system, so that the construction of the test system is more complex, and more factors need to be considered.
29/5/2020, chinese utility model patent 202010321911X, discloses a cross twin rotor unmanned helicopter transmission test stand, comprising a transmission, a rotor shaft and a support assembly, wherein the transmission to be detected is used for connecting with a power source; the two rotor shafts correspond to the two output ends of the transmission device one by one; the support assembly is used to support the transmission and the rotor shaft. Support transmission and rotor shaft through supporting component, and realize the installation of two rotor shafts, when needs carry out experimental test, the operation of transmission can be realized to the lug connection power supply, transmission moving state under the different rotational speeds of effective simulation, thereby carry out transmission simulation capability test, and is simple and convenient, can carry out before the final assembly or effectively inspect transmission's performance and maintenance result after the maintenance at unmanned helicopter, avoid the situation that can't be retrieved because of transmission trouble brews. But the function is single, and the performance test, the running-in test, the efficiency test, the flight front frame test, the fatigue test, the batch acceptance test and the like cannot be met.
SUMMERY OF THE UTILITY MODEL
The utility model aims to overcome the technical problem of the prior art and provide an electric feedback type unmanned helicopter transmission test system which can simultaneously apply multichannel coordinated loading of the torque of an engine and a main tail rotor, the lift force and the bending moment of a main rotor system and the thrust of a tail rotor system to an unmanned helicopter transmission mechanism.
In order to solve the technical problems, the multichannel coordinated-loading electric feedback type unmanned helicopter transmission test system comprises a power output mechanism, a main rotor load simulation mechanism, a main reducing output shaft loading unit, a tail rotor load simulation mechanism, a tail reducing output shaft loading unit, a data acquisition and processing unit and a control unit;
the power output mechanism is used for providing simulated input drive for the transmission mechanism of the unmanned helicopter to be tested;
the main rotor load simulation mechanism is used for simulating main rotor torque in actual flight of the transmission mechanism of the unmanned helicopter to be tested;
the main reducer output shaft loading unit is used for simulating lift force, lateral force and bending moment of the transmission mechanism of the unmanned helicopter to be tested in actual flight;
the tail reduction output shaft loading unit is used for simulating tail shaft thrust of the transmission mechanism of the unmanned helicopter to be tested in actual flight;
the tail rotor load simulation mechanism is used for simulating tail rotor torque in actual flight of the transmission mechanism of the unmanned helicopter to be tested;
the data acquisition and processing unit is used for acquiring data of the main rotor load simulation mechanism, the main reducing output shaft loading unit and the tail reducing output shaft loading unit;
and the power output mechanism, the main rotor load simulation mechanism, the main reducing output shaft loading unit, the tail rotor load simulation mechanism, the tail reducing output shaft loading unit and the data acquisition and processing unit are all connected with the control unit.
In the utility model, the main reducer output shaft loading unit comprises a main shaft loading compensation mechanism, a main shaft radial force loading mechanism and a main shaft axial force loading mechanism, wherein the main shaft loading compensation mechanism and the main shaft radial force loading mechanism are connected with a main shaft of an unmanned helicopter transmission mechanism to be tested; the main shaft axial force loading mechanism is connected with the main shaft loading compensation mechanism.
In the utility model, the main shaft radial force loading mechanism and the main shaft axial force loading mechanism are electric cylinders.
According to the utility model, the main rotor load simulation mechanism comprises a main rotor load simulation motor, a gearbox and a second torque sensor, wherein the main rotor load simulation motor is connected with the gearbox, and the gearbox is connected with the second torque sensor.
In the utility model, the main rotor load simulation motor is connected with an inversion unit.
In the utility model, the tail reduction output shaft loading unit comprises a tail rotor wing load simulation motor, a third torque sensor, a tail shaft loading compensation mechanism and a tail shaft axial force loading mechanism; the tail rotor load simulation motor is connected with the tail shaft loading compensation mechanism, and a third torque sensor is connected between the tail rotor load simulation motor and the tail shaft loading compensation mechanism; the tail shaft loading compensation mechanism is connected with a tail shaft simulating a transmission mechanism of the unmanned helicopter to be tested; the tail shaft axial force loading mechanism is arranged on two sides of the tail shaft loading compensation mechanism.
In the utility model, the tail rotor load simulation motor is connected with an inversion unit.
In the utility model, the tail shaft loading compensation mechanism is an electric cylinder.
The utility model has the beneficial effects that: (1) the test system can meet various test requirements of the transmission mechanism of the unmanned helicopter, can apply torque applied by an engine and a main tail blade, can also apply lift force and bending moment brought by a main tail rotor system, can simulate almost all actual loads applied to the transmission mechanism by the unmanned helicopter in flight, and can more truly reflect the loading condition of the transmission mechanism of the unmanned helicopter; (2) load loading such as lifting force, thrust force, bending moment and the like in the test system is realized through the electric cylinder, a hydraulic system is not needed, the use is safe, convenient and tidy, and the risk of oil leakage of the hydraulic system is avoided; (3) the utility model adopts an electric feedback type test, and has the advantages of less power consumption, energy saving, environmental protection and high efficiency; (4) the modular design is adopted, different tool clamp interfaces are designed, and the test device can be suitable for various unmanned helicopter transmission system tests; (5) the test system disclosed by the utility model has various test capabilities of developing the transmission system of the unmanned helicopter, such as performance tests, running-in tests, efficiency tests, flight front frame tests, fatigue tests, batch acceptance tests and the like, so that the test cost is greatly reduced, the test efficiency is improved, and the test integrity can be effectively improved.
Drawings
FIG. 1 is a schematic diagram of a testing system of the present invention;
FIG. 2 is a block diagram of the test system of the present invention;
FIG. 3 is an isometric view of a testing system of the present invention;
FIG. 4 is a front view of the testing system of the present invention;
FIG. 5 is a rear view of the testing system of the present invention;
FIG. 6 is a partial schematic view of a tail reducer of the test system of the present invention;
FIG. 7 is a schematic diagram of the control unit of the testing system of the present invention;
FIG. 8 is a schematic diagram of a servo loading mechanism of the test system of the present invention.
In the figure, 1-main reducer, 2-main shaft, 3-tail transmission shaft, 4-tail reducer, 5-tail shaft, 6-driving motor, 7-first gearbox, 8-first torque sensor, 9-high speed coupler, 10-main rotor load simulation motor, 11-second gearbox, 12-second torque sensor, 13-main shaft loading compensation mechanism, 14-main shaft radial force loading mechanism, 15-main shaft axial force loading mechanism, 16-tail rotor load simulation motor, 17-third torque sensor, 18-tail shaft loading compensation mechanism, 19-tail shaft axial force loading mechanism, 20-test bench and 21-test platform.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1 to 8, the multichannel coordinated-loading electric feedback unmanned helicopter transmission test system of the present invention includes a driving motor 6, a first gearbox 7, a first torque sensor 8, a high-speed coupler 9, a main rotor load simulation motor 10, a second gearbox 11, a second torque sensor 12, a main shaft loading compensation mechanism 13, a main shaft radial force loading mechanism 14, a main shaft axial force loading mechanism 15, a tail rotor load simulation motor 16, a third torque sensor 17, a tail shaft loading compensation mechanism 18, a tail shaft axial force loading mechanism 19, a test bench 20, a test platform 21, and a control unit.
The transmission mechanism of the unmanned helicopter to be tested comprises a main speed reducer 1, a main shaft 2, a tail transmission shaft 3, a tail speed reducer 4 and a tail shaft 5, wherein the main shaft 2 and the tail transmission shaft 3 are respectively arranged on the main speed reducer 1, and the tail transmission shaft 3 is connected with the tail shaft 5 through the tail speed reducer 4.
The driving motor 6 is connected with a first gearbox 7, the first gearbox 7 is connected with a high-speed coupler 9, a first torque sensor 8 is arranged between the first gearbox 7 and the high-speed coupler 9, and the high-speed coupler 9 can be connected with a main reducer 1 of a transmission mechanism of the unmanned helicopter to be tested. The driving motor 6, the first gearbox 7, the first torque sensor 8 and the high-speed coupler 9 form a power output mechanism which is used for simulating an engine system of the unmanned helicopter and providing simulated input drive for a transmission mechanism of the unmanned helicopter to be tested. The driving motor 6, the first gearbox 7 and the high-speed coupler 9 are all installed on the test platform 21.
The lower part of the main shaft loading compensation mechanism 13 is connected with a main shaft 2 of the transmission mechanism of the unmanned helicopter to be tested, the upper part of the main shaft loading compensation mechanism is connected with a second gearbox 11 through a second torque sensor 12, and the second gearbox 11 is connected with a main rotor load simulation motor 10. The main rotor load simulation motor 10, the second gearbox 11 and the second torque sensor 12 form a main rotor load simulation mechanism, and the main rotor load simulation mechanism is used for simulating the torque of the main rotor system of the unmanned helicopter in actual flight. Main rotor load simulation motor 10, the equal fixed mounting of second gearbox 11 are on test bench 20, and test bench 20 fixes on test platform 21.
The main shaft radial force loading mechanism 14 is connected with the main shaft 2 of the transmission mechanism of the unmanned helicopter to be tested and is positioned below the main shaft loading compensation mechanism 13. The main shaft radial force loading mechanism 14 is used for simulating the bending moment of the main rotor system of the unmanned helicopter to the main shaft in actual flight.
The main shaft axial force loading mechanism 15 is connected with the main shaft loading compensation mechanism 13 and is positioned below the second torque sensor 12. The spindle axial force loading mechanism 15 includes two electric cylinders, and the two electric cylinders are respectively disposed on two sides of the spindle loading compensation mechanism 13. The main shaft axial force loading mechanism 15 is used for simulating the lift force and the lateral force of the main rotor system to the main shaft in actual flight.
The tail rotor load simulation motor 16 is connected with a tail shaft loading compensation mechanism 18 through a third torque sensor 17, and the tail shaft loading compensation mechanism 18 is connected with a tail shaft 5 of the transmission mechanism of the unmanned helicopter to be tested. The tail shaft loading compensation mechanism 18 is connected with a tail shaft axial force loading mechanism 19. The tail shaft axial force loading mechanism 19 comprises two electric cylinders, and the two electric cylinders are respectively arranged on two sides of the tail shaft loading compensation mechanism 18. The tail shaft axial force loading mechanism 19 is used for simulating the thrust of the tail rotor system of the unmanned helicopter to the tail shaft in actual flight.
The tail rotor load simulation motor 16 is fixed to the test rig 20.
The main rotor load simulation motor 10 and the tail rotor load simulation motor 16 are both connected with an inversion driving unit. During testing, the input energy of the testing system is generated by the main rotor load simulation motor 10 and the tail rotor load simulation motor 16 at the same time, and is fed back to the direct current bus through the inversion driving unit, the load simulation motor obtains power from the direct current bus through the inversion driving unit, the insufficient electric energy is input into the direct current bus after being supplemented and rectified from a power grid through the rectification unit, and the feedback efficiency is high.
In this embodiment, the first torque sensor 8, the second torque sensor 12 and the third torque sensor 17 form a data acquisition and processing system, which is used for acquiring data of the main rotor load simulation mechanism, the main reducing output shaft loading unit and the tail reducing output shaft loading unit.
The driving motor 6, the first torque sensor 8, the main rotor load simulation motor 10, the second torque sensor 12, the main shaft loading compensation mechanism 13, the main shaft radial force loading mechanism 14, the main shaft axial force loading mechanism 15, the tail rotor load simulation motor 16, the third torque sensor 17, the tail shaft loading compensation mechanism 18 and the tail shaft axial force loading mechanism 19 are all connected with the control unit.
As shown in fig. 7, the test control unit is composed of a control computer, an operation table, a loading transducer and a load loading servo control system. The loading frequency converter mainly controls the motor to apply torque to the test piece, and the load loading servo control system controls the electric cylinder to apply loads such as lift force, bending moment and thrust to the test piece. The operation table is placed in a control room and is responsible for the control and operation of the whole system. In the figure, EL5151 is an encoder interface terminal module, and EL1008 is a digital quantity input terminal module.
As shown in fig. 8, the load loading servo control system mainly comprises a servo controller, an embedded lower computer, a tension pressure sensor and a servo electric cylinder, and is used for loading the lift force of the main rotor, the lateral force, the bending moment of the main shaft and the thrust force of the tail rotor. Wherein, servo controller, draw pressure sensor and servo electric cylinder one-to-one.
In the embodiment, the electric feedback type unmanned helicopter transmission test system with the coordinated loading of the channels can be further provided with an emergency power supply Unit (UPS), so that the electric power requirements for stopping the test and saving data are provided when the main power grid fails.
In the actual use process, the multichannel coordinated-loading electric feedback type unmanned helicopter transmission test system can be provided with a torque overload protection function, a safety protection device (protecting personnel and other systems), a video monitoring function and other protection functions.
The application method of the multichannel coordinated loading electric feedback type unmanned helicopter transmission test system comprises the following steps:
1) and preparing the transmission mechanism of the unmanned helicopter to be tested.
2) Connecting the transmission mechanism of the unmanned helicopter to be tested prepared in the step 1) with the test system through a test fixture. Fixing the main speed reducer 1 and a test bench in a manner consistent with that of mounting on the unmanned helicopter; the main shaft 2 is connected with the main shaft loading compensation mechanism 13, the main shaft radial force loading mechanism 14 and the main shaft axial force loading mechanism 15 through a test tool, the tail shaft 5 is connected with the tail shaft loading compensation mechanism 18 and the tail shaft axial force loading mechanism 19 through the test tool, and meanwhile, the main speed reducer 1 is connected with the driving motor 6 through the high-speed coupler 9.
3) The coaxiality of the main shaft 2, the tail transmission shaft 3 and the tail shaft 5 is adjusted, and the technical requirement is not lower than the use requirement of the unmanned helicopter.
4) And (4) checking whether all the protective covers and protective windows of the test system are closed and locked, and whether the test bench 20 and the test platform 21 are fixed firmly.
5) And starting the test system, and editing the test input load spectrum according to the test type.
6) And (4) test loading, namely monitoring the rotating speed, the torque, the load, the vibration data and the video monitoring image in real time to ensure the test safety.
7) And (5) closing the test system after the test is finished.
Therefore, through the technical scheme of the embodiment, the multichannel coordinated-loading electric power closed-type unmanned helicopter transmission test system can realize performance test, running-in test, efficiency test, front flight cradle test, fatigue test, batch production acceptance test and the like of the unmanned helicopter transmission system. The test bench and the interface of the tool clamp and the power and the rotating speed of the simulation motor are changed, and various tests of transmission systems of unmanned helicopters of different types can be realized.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, variations and modifications can be made without departing from the principle of the present invention, and these should also be considered as falling within the scope of the present invention.
Claims (8)
1. A multichannel coordinated loading electric feedback type unmanned helicopter transmission test system is characterized in that: the main rotor wing load simulation device comprises a power output mechanism, a main rotor wing load simulation mechanism, a main reducing output shaft loading unit, a tail rotor wing load simulation mechanism, a tail reducing output shaft loading unit, a data acquisition and processing unit and a control unit;
the power output mechanism is used for providing simulated input drive for the transmission mechanism of the unmanned helicopter to be tested;
the main rotor load simulation mechanism is used for simulating main rotor torque in actual flight of the transmission mechanism of the unmanned helicopter to be tested;
the main reducer output shaft loading unit is used for simulating lift force, lateral force and bending moment of the transmission mechanism of the unmanned helicopter to be tested in actual flight;
the tail reduction output shaft loading unit is used for simulating tail shaft thrust of the transmission mechanism of the unmanned helicopter to be tested in actual flight;
the tail rotor load simulation mechanism is used for simulating tail rotor torque in actual flight of the transmission mechanism of the unmanned helicopter to be tested;
the data acquisition and processing unit is used for acquiring data of the main rotor load simulation mechanism, the main reducing output shaft loading unit and the tail reducing output shaft loading unit;
and the power output mechanism, the main rotor load simulation mechanism, the main reducing output shaft loading unit, the tail rotor load simulation mechanism, the tail reducing output shaft loading unit and the data acquisition and processing unit are all connected with the control unit.
2. The multichannel coordinated-loading electric-feedback-type unmanned helicopter transmission test system according to claim 1, characterized in that: the main reducer output shaft loading unit comprises a main shaft loading compensation mechanism, a main shaft radial force loading mechanism and a main shaft axial force loading mechanism, and the main shaft loading compensation mechanism and the main shaft radial force loading mechanism are connected with a main shaft of the transmission mechanism of the unmanned helicopter to be tested; the main shaft axial force loading mechanism is connected with the main shaft loading compensation mechanism.
3. The multichannel coordinated-loading electric-feedback-type unmanned helicopter transmission test system of claim 2, characterized in that: the main shaft radial force loading mechanism and the main shaft axial force loading mechanism are electric cylinders.
4. The multichannel coordinated-loading electric-feedback-type unmanned helicopter transmission test system according to claim 1, characterized in that: the main rotor load simulation mechanism comprises a main rotor load simulation motor, a gearbox and a second torque sensor, wherein the main rotor load simulation motor is connected with the gearbox, and the gearbox is connected with the second torque sensor.
5. The multichannel coordinated-loading electric-feedback-type unmanned helicopter transmission test system of claim 4, characterized in that: the main rotor load simulation motor is connected with the inversion unit.
6. The multichannel coordinated-loading electric-feedback-type unmanned helicopter transmission test system according to claim 1, characterized in that: the tail reduction output shaft loading unit comprises a tail rotor wing load simulation motor, a third torque sensor, a tail shaft loading compensation mechanism and a tail shaft axial force loading mechanism; the tail rotor load simulation motor is connected with the tail shaft loading compensation mechanism, and a third torque sensor is connected between the tail rotor load simulation motor and the tail shaft loading compensation mechanism; the tail shaft loading compensation mechanism is connected with a tail shaft simulating a transmission mechanism of the unmanned helicopter to be tested; the tail shaft axial force loading mechanism is arranged on two sides of the tail shaft loading compensation mechanism.
7. The multichannel coordinated-loading electric-feedback-type unmanned helicopter transmission test system of claim 6, characterized in that: the tail rotor load simulation motor is connected with the inversion unit.
8. The multichannel coordinated-loading electric-feedback-type unmanned helicopter transmission test system of claim 6, characterized in that: the tail shaft loading compensation mechanism is an electric cylinder.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114955001A (en) * | 2022-06-17 | 2022-08-30 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114955001A (en) * | 2022-06-17 | 2022-08-30 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
| CN114955001B (en) * | 2022-06-17 | 2024-05-31 | 重庆大学 | Helicopter tail transmission system simulation experiment system |
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