CN113184168A - Elevator adjustment sheet control system - Google Patents
Elevator adjustment sheet control system Download PDFInfo
- Publication number
- CN113184168A CN113184168A CN202110531996.9A CN202110531996A CN113184168A CN 113184168 A CN113184168 A CN 113184168A CN 202110531996 A CN202110531996 A CN 202110531996A CN 113184168 A CN113184168 A CN 113184168A
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- CN
- China
- Prior art keywords
- steel cable
- elevator
- deflection
- deflection mechanism
- bias
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Lift-Guide Devices, And Elevator Ropes And Cables (AREA)
- Types And Forms Of Lifts (AREA)
Abstract
The invention belongs to the technical field of airplane control systems, and discloses an elevator adjustment sheet control system which comprises an elevator adjustment sheet trim steering engine, a steel cable, a guide pulley, a support, a steel cable and an elevator adjustment sheet deflection mechanism, wherein the elevator adjustment sheet is controlled by a trim electric steering engine. The left and right steering wheels of the steering cabin are provided with adjusting sheet control switches which control the operation of the trim electric steering engine and then drive the steel cable and the elevator adjusting sheet deflection mechanism to control the adjusting sheet on each elevator control surface. The device has simple structure, light weight and convenient installation.
Description
Technical Field
The invention belongs to the technical field of airplane control systems, and particularly relates to an elevator adjustment sheet control system.
Background
The elevator control system is one of three main flight control systems of the airplane, and the elevator standby adjusting sheet control system is one of secondary flight control systems, and is used for balancing the airplane, reducing the fatigue of a pilot and lightening the control force on a steering column when the airplane takes off and lands. When the elevator deflects, the steering elevator tab automatically deflects in the opposite direction to the elevator to reduce the joystick force of the elevator. And among the prior art, the driving of elevator trimmer is mostly distributed independent drive, hardly guarantees the elevator trimmer and deflects the uniformity, influences aircraft flight quality.
Disclosure of Invention
The invention overcomes the disadvantages of the prior art and provides an elevator trim tab control system.
The technical scheme of the invention is as follows:
an aircraft elevator tab steering system comprising: a left elevator adjusting sheet 1, a right elevator adjusting sheet 2, a left elevator 3, a right elevator 4, a machine body structure 5, a motor 8, a left upper deflection steel cable, a left lower deflection steel cable, a right upper deflection steel cable, a right lower deflection steel cable, a left deflection mechanism 22 and a right deflection mechanism 23;
the left deflection mechanism is connected with the left elevator adjusting sheet and is used for controlling the left elevator adjusting sheet to deflect, and the right deflection mechanism is connected with the right elevator adjusting sheet and is used for controlling the right elevator adjusting sheet to deflect;
the motor is arranged in the machine body structure and is connected with the left deflection mechanism through a left deflection steel cable and drives the left deflection mechanism to stretch so as to drive the left elevator adjustment sheet to deflect up and down;
the motor is connected with the right deflection mechanism through a right deflection steel cable and drives the right elevator adjusting sheet to deflect up and down by driving the right deflection mechanism to stretch;
the motor is used for synchronously driving the left deflection steel cable and the right deflection steel cable to move so as to control the left elevator adjusting sheet and the right elevator adjusting sheet to synchronously deflect.
Further, the left yaw cable includes: a left upper partial wire rope and a left lower partial wire rope; the left upper piece steel cable is used for driving the left elevator adjusting piece to deflect upwards, and the left lower piece steel cable is used for driving the left elevator adjusting piece to deflect downwards; the right deflection wire rope includes: a right upper partial wire rope and a right lower partial wire rope; the right upper piece steel cable is used for driving the right elevator adjusting piece to deflect upwards, and the right lower piece steel cable is used for driving the right elevator adjusting piece to deflect downwards.
Furthermore, four annular grooves are formed in an output shaft of the motor, and the left upper inclined steel cable, the left lower inclined steel cable, the right upper inclined steel cable and the right lower inclined steel cable are respectively wound and fixed in the four annular grooves. The four annular grooves are used for distributing four deflection steel cables which are arranged at the upper left, the lower left, the upper right and the lower right so as to avoid mutual interference.
Further, the left upper-bias steel cable comprises a first left upper-bias steel cable 14 and a second left upper-bias steel cable 16, the right end of the first left upper-bias steel cable is connected with the motor, the left end of the second left upper-bias steel cable is connected with the left deflection mechanism, the left end of the first left upper-bias steel cable is connected with the right end of the second left upper-bias steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the left upper-bias steel cable;
the left lower-deviation steel cable comprises a first left lower-deviation steel cable 15 and a second left lower-deviation steel cable 17, the right end of the first left lower-deviation steel cable is connected with the motor, the left end of the second left lower-deviation steel cable is connected with the left deviation mechanism, the left end of the first left lower-deviation steel cable is connected with the right end of the second left lower-deviation steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the left lower-deviation steel cable;
the right upper inclined steel cable comprises a first right upper inclined steel cable 19 and a second right upper inclined steel cable 21, the right end of the first right upper inclined steel cable is connected with the motor, the right end of the second right upper inclined steel cable is connected with the right deflection mechanism, the right end of the first right upper inclined steel cable is connected with the right end of the second right upper inclined steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the right upper inclined steel cable;
the right downward-biased steel cable comprises a first right downward-biased steel cable 18 and a second right downward-biased steel cable 20, the right end of the first right downward-biased steel cable is connected with the motor, the right end of the second right downward-biased steel cable is connected with the right deflection mechanism, the right end of the first right downward-biased steel cable is connected with the right end of the second right downward-biased steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the right downward-biased steel cable.
Furthermore, the system also comprises a left pulley bracket and a right pulley bracket, the left deflection steel cable is connected with the left deflection mechanism by bypassing the left pulley bracket, the right deflection steel cable is connected with the right deflection mechanism by bypassing the right pulley bracket, and the left pulley bracket and the right pulley bracket are used for steel cable steering.
Further, the left upper inclined steel cable and the right upper inclined steel cable are wound and fixed on the motor output shaft along the clockwise direction, and the left lower inclined steel cable and the right lower inclined steel cable are wound and fixed on the motor output shaft along the anticlockwise direction. When the output shaft of the motor rotates anticlockwise, the left lower deviation steel cable and the right lower deviation steel cable are released, and the left upper deviation steel cable and the right upper deviation steel cable are contracted to drive the left elevator adjusting sheet and the right elevator adjusting sheet to simultaneously deflect upwards; when the output shaft of the motor rotates clockwise, the left upper inclined steel cable and the right upper inclined steel cable are released, and the left lower inclined steel cable and the right lower inclined steel cable contract to drive the left elevator adjusting sheet and the right elevator adjusting sheet to simultaneously deflect downwards
Further, the left pulley bracket and the right pulley bracket are symmetrically arranged about a plane of symmetry of the aircraft; the left deflection mechanism and the right deflection mechanism are symmetrically arranged about a plane of symmetry of the aircraft.
Further, the motor is arranged on the plane of symmetry inside the fuselage. The synchronous deflection of the left deflection control surface and the right deflection control surface is ensured by the symmetrical arrangement.
Furthermore, the left deflection steel cable and the right deflection steel cable are the same in material and total length.
In one aspect of the invention, elevator trim deflection is achieved. On the other hand, synchronous movement of the elevator adjustment sheets on two sides of the airplane can be realized.
Drawings
FIG. 1 is a schematic view of an elevator tab handling system;
in the figure, 1 a left elevator adjustment sheet, 2 a right elevator adjustment sheet, 3 a left elevator, 4 a right elevator, 5 a fuselage structure, 6 a fuselage left side longitudinal beam, 7 a fuselage right side longitudinal beam, 8 a motor, 9 a motor output shaft, 10 a first left pulley bracket, 11 a first right pulley bracket, 12 a second left pulley bracket, 13 a second right pulley bracket, 14 a first left upper deflection steel rope, 15 a first left lower deflection steel rope, 16 a second left upper deflection steel rope, 17 a second left lower deflection steel rope, 18 a first right lower deflection steel rope, 19 a first right upper deflection steel rope, 20 a second right lower deflection steel rope, 21 a second right upper deflection steel rope, 22 a left deflection mechanism and 23 a right deflection mechanism.
Detailed Description
An aircraft elevator tab steering system comprising: a left elevator adjusting sheet 1, a right elevator adjusting sheet 2, a left elevator 3, a right elevator 4, a machine body structure 5, a motor 8, a left upper deflection steel cable, a left lower deflection steel cable, a right upper deflection steel cable, a right lower deflection steel cable, a left deflection mechanism 22 and a right deflection mechanism 23;
the left deflection mechanism is connected with the left elevator adjusting sheet and is used for controlling the left elevator adjusting sheet to deflect, and the right deflection mechanism is connected with the right elevator adjusting sheet and is used for controlling the right elevator adjusting sheet to deflect;
the motor is arranged in the machine body structure and is connected with the left deflection mechanism through a left deflection steel cable and drives the left deflection mechanism to stretch so as to drive the left elevator adjustment sheet to deflect up and down;
the motor is connected with the right deflection mechanism through a right deflection steel cable and drives the right elevator adjusting sheet to deflect up and down by driving the right deflection mechanism to stretch;
the motor is used for synchronously driving the left deflection steel cable and the right deflection steel cable to move so as to control the left elevator adjusting sheet and the right elevator adjusting sheet to synchronously deflect.
The elevator trim tab is operated by a trim electric steering engine. The left and right steering wheels of the steering cabin are provided with adjusting sheet control switches which control the operation of the trim electric steering engine and then drive the steel cable and the elevator adjusting sheet deflection mechanism to control the adjusting sheet on each elevator control surface.
Further, the left yaw cable includes: a left upper partial wire rope and a left lower partial wire rope; the left upper piece steel cable is used for driving the left elevator adjusting piece to deflect upwards, and the left lower piece steel cable is used for driving the left elevator adjusting piece to deflect downwards; the right deflection wire rope includes: a right upper partial wire rope and a right lower partial wire rope; the right upper piece steel cable is used for driving the right elevator adjusting piece to deflect upwards, and the right lower piece steel cable is used for driving the right elevator adjusting piece to deflect downwards.
Furthermore, four annular grooves are formed in an output shaft of the motor, and the left upper inclined steel cable, the left lower inclined steel cable, the right upper inclined steel cable and the right lower inclined steel cable are respectively wound and fixed in the four annular grooves.
Further, the left upper-bias steel cable comprises a first left upper-bias steel cable 14 and a second left upper-bias steel cable 16, the right end of the first left upper-bias steel cable is connected with the motor, the left end of the second left upper-bias steel cable is connected with the left deflection mechanism, the left end of the first left upper-bias steel cable is connected with the right end of the second left upper-bias steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the left upper-bias steel cable;
the left lower-deviation steel cable comprises a first left lower-deviation steel cable 15 and a second left lower-deviation steel cable 17, the right end of the first left lower-deviation steel cable is connected with the motor, the left end of the second left lower-deviation steel cable is connected with the left deviation mechanism, the left end of the first left lower-deviation steel cable is connected with the right end of the second left lower-deviation steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the left lower-deviation steel cable;
the right upper inclined steel cable comprises a first right upper inclined steel cable 19 and a second right upper inclined steel cable 21, the right end of the first right upper inclined steel cable is connected with the motor, the right end of the second right upper inclined steel cable is connected with the right deflection mechanism, the right end of the first right upper inclined steel cable is connected with the right end of the second right upper inclined steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the right upper inclined steel cable;
the right downward-biased steel cable comprises a first right downward-biased steel cable 18 and a second right downward-biased steel cable 20, the right end of the first right downward-biased steel cable is connected with the motor, the right end of the second right downward-biased steel cable is connected with the right deflection mechanism, the right end of the first right downward-biased steel cable is connected with the right end of the second right downward-biased steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the right downward-biased steel cable.
Furthermore, the system also comprises a left pulley bracket and a right pulley bracket, the left deflection steel cable is connected with the left deflection mechanism by bypassing the left pulley bracket, the right deflection steel cable is connected with the right deflection mechanism by bypassing the right pulley bracket, and the left pulley bracket and the right pulley bracket are used for steel cable steering.
Further, the left upper inclined steel cable and the right upper inclined steel cable are wound and fixed on the motor output shaft along the clockwise direction, and the left lower inclined steel cable and the right lower inclined steel cable are wound and fixed on the motor output shaft along the anticlockwise direction.
4 steel cables are wound on an output shaft of the motor, wherein two steel cables which are left when viewed along the heading are turned by the guide pulleys and pass through the hollow shaft of the elevator pipe shaft to the left elevator deflection mechanism, two steel cables which are right are turned by the guide pulleys and pass through the hollow shaft of the elevator pipe shaft to the right elevator deflection mechanism, a steel cable winding drum of the deflection mechanism rotates, and the stay bar is retracted through a thread mechanism on the stay bar, so that the adjusting piece is driven to deflect upwards by 9 degrees +/-1 degrees maximally and deflect downwards by 11.5 degrees +/-1 degrees maximally.
Further, the left pulley bracket and the right pulley bracket are symmetrically arranged about a plane of symmetry of the aircraft; the left deflection mechanism and the right deflection mechanism are symmetrically arranged about a plane of symmetry of the aircraft.
Further, the motor is arranged on the plane of symmetry inside the fuselage.
Furthermore, the left deflection steel cable and the right deflection steel cable are the same in material and total length.
Claims (9)
1. An aircraft elevator tab handling system, the system comprising: the elevator comprises a left elevator adjusting sheet (1), a right elevator adjusting sheet (2), a left elevator (3), a right elevator (4), a machine body structure (5), a motor (8), a left upper deviation steel cable, a left lower deviation steel cable, a right upper deviation steel cable, a right lower deviation steel cable, a left deflection mechanism (22) and a right deflection mechanism (23);
the left deflection mechanism is connected with the left elevator adjusting sheet and is used for controlling the left elevator adjusting sheet to deflect, and the right deflection mechanism is connected with the right elevator adjusting sheet and is used for controlling the right elevator adjusting sheet to deflect;
the motor is arranged in the machine body structure and is connected with the left deflection mechanism through a left deflection steel cable and drives the left deflection mechanism to stretch so as to drive the left elevator adjustment sheet to deflect up and down;
the motor is connected with the right deflection mechanism through a right deflection steel cable and drives the right elevator adjusting sheet to deflect up and down by driving the right deflection mechanism to stretch;
the motor is used for synchronously driving the left deflection steel cable and the right deflection steel cable to move so as to control the left elevator adjusting sheet and the right elevator adjusting sheet to synchronously deflect.
2. An aircraft elevator tab steering system according to claim 1 wherein the left yaw cable comprises: a left upper partial wire rope and a left lower partial wire rope; the left upper piece steel cable is used for driving the left elevator adjusting piece to deflect upwards, and the left lower piece steel cable is used for driving the left elevator adjusting piece to deflect downwards; the right deflection wire rope includes: a right upper partial wire rope and a right lower partial wire rope; the right upper piece steel cable is used for driving the right elevator adjusting piece to deflect upwards, and the right lower piece steel cable is used for driving the right elevator adjusting piece to deflect downwards.
3. The aircraft elevator tab maneuvering system as recited in claim 2, wherein the output shaft of the motor has four annular grooves, and the left upper-bias cable, the left lower-bias cable, the right upper-bias cable and the right lower-bias cable are respectively wound and fixed in the four annular grooves.
4. An aircraft elevator adjustment tab control system according to claim 2, wherein the left upper-bias steel cable comprises a first left upper-bias steel cable (14) and a second left upper-bias steel cable (16), the right end of the first left upper-bias steel cable is connected with the motor, the left end of the second left upper-bias steel cable is connected with the left deflection mechanism, the left end of the first left upper-bias steel cable is connected with the right end of the second left upper-bias steel cable through a turnbuckle, and the turnbuckle is used for adjusting the tension and the length of the left upper-bias steel cable;
the left lower-deviation steel cable comprises a first left lower-deviation steel cable (15) and a second left lower-deviation steel cable (17), the right end of the first left lower-deviation steel cable is connected with the motor, the left end of the second left lower-deviation steel cable is connected with the left deflection mechanism, the left end of the first left lower-deviation steel cable is connected with the right end of the second left lower-deviation steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the left lower-deviation steel cable;
the right upper inclined steel cable comprises a first right upper inclined steel cable (19) and a second right upper inclined steel cable (21), the right end of the first right upper inclined steel cable is connected with the motor, the right end of the second right upper inclined steel cable is connected with the right deflection mechanism, the right end of the first right upper inclined steel cable is connected with the right end of the second right upper inclined steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the right upper inclined steel cable;
the right downward-biased steel cable comprises a first right downward-biased steel cable (18) and a second right downward-biased steel cable (20), the right end of the first right downward-biased steel cable is connected with the motor, the right end of the second right downward-biased steel cable is connected with the right deflection mechanism, the right end of the first right downward-biased steel cable is connected with the right end of the second right downward-biased steel cable through an elastic threaded sleeve, and the elastic threaded sleeve is used for adjusting the tension and the length of the right downward-biased steel cable.
5. An aircraft elevator tab steering system according to claim 1 further comprising a left pulley bracket and a right pulley bracket, wherein the left deflection cable is routed around the left pulley bracket and connected to the left deflection mechanism, and wherein the right deflection cable is routed around the right pulley bracket and connected to the right deflection mechanism, and wherein the left and right pulley brackets are used for cable steering.
6. An aircraft elevator tab steering system according to claim 2 wherein the left and right upper bias cables are wound and secured to the motor output shaft in a clockwise direction and the left and right lower bias cables are wound and secured to the motor output shaft in a counter-clockwise direction.
7. An aircraft elevator tab handling system according to claim 5 wherein the left and right pulley brackets are symmetrically arranged about a plane of symmetry; the left deflection mechanism and the right deflection mechanism are symmetrically arranged about a plane of symmetry of the aircraft.
8. An aircraft elevator tab steering system according to claim 7 wherein the motor is disposed in the fuselage interior plane of symmetry.
9. An aircraft elevator tab steering system according to claim 8 wherein the left and right deflector cables are of the same material and have the same overall length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110531996.9A CN113184168B (en) | 2021-05-14 | 2021-05-14 | Elevator adjusting piece control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110531996.9A CN113184168B (en) | 2021-05-14 | 2021-05-14 | Elevator adjusting piece control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113184168A true CN113184168A (en) | 2021-07-30 |
| CN113184168B CN113184168B (en) | 2023-07-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110531996.9A Active CN113184168B (en) | 2021-05-14 | 2021-05-14 | Elevator adjusting piece control system |
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| Country | Link |
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| CN (1) | CN113184168B (en) |
Citations (15)
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| GB482080A (en) * | 1936-06-11 | 1938-03-23 | Pierre Ernest Mercier | Improvements in or relating to aircraft control systems |
| GB485794A (en) * | 1937-03-04 | 1938-05-25 | William Edward Back | Improvements in or relating to aircraft |
| RU94036379A (en) * | 1994-09-26 | 1996-07-27 | Экспериментальный машиностроительный завод им.В.М.Мясищева | Aircraft manual control system |
| US5551652A (en) * | 1994-03-28 | 1996-09-03 | Mcdonnell Douglas Corporation | Standby control system |
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| CN208530834U (en) * | 2018-06-15 | 2019-02-22 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of light aerocraft aileron control device |
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| CN109502012A (en) * | 2018-12-29 | 2019-03-22 | 福建野马飞机制造有限公司 | A kind of control system of light-duty sport plane |
| CN209441617U (en) * | 2018-12-29 | 2019-09-27 | 福建野马飞机制造有限公司 | A kind of rudder control system of light-duty sport plane |
| CN110450940A (en) * | 2019-06-24 | 2019-11-15 | 陕西飞机工业（集团）有限公司 | A kind of elevator trimming control circuit of aircraft |
| CN110498061A (en) * | 2019-08-28 | 2019-11-26 | 中国科学院工程热物理研究所 | There is the man-machine method for changing unmanned plane based on rudder control system modification |
| US20200115038A1 (en) * | 2018-10-12 | 2020-04-16 | Rolls-Royce North American Technologies Inc. | Electrified mechanical control cables |
| CN211124498U (en) * | 2019-12-16 | 2020-07-28 | 天津中德应用技术大学 | Mechanical type aircraft control system maintains training equipment |
| CN111572758A (en) * | 2020-06-24 | 2020-08-25 | 重庆恩斯特龙通用航空技术研究院有限公司 | Soft operating device for light aircraft elevator |
| CN212386681U (en) * | 2020-06-24 | 2021-01-22 | 重庆恩斯特龙通用航空技术研究院有限公司 | Soft steering device for light airplane rudder |
-
2021
- 2021-05-14 CN CN202110531996.9A patent/CN113184168B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB482080A (en) * | 1936-06-11 | 1938-03-23 | Pierre Ernest Mercier | Improvements in or relating to aircraft control systems |
| GB485794A (en) * | 1937-03-04 | 1938-05-25 | William Edward Back | Improvements in or relating to aircraft |
| US5551652A (en) * | 1994-03-28 | 1996-09-03 | Mcdonnell Douglas Corporation | Standby control system |
| RU94036379A (en) * | 1994-09-26 | 1996-07-27 | Экспериментальный машиностроительный завод им.В.М.Мясищева | Aircraft manual control system |
| CN104554710A (en) * | 2014-11-19 | 2015-04-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Servo actuation system for leading edge flap of mechanical double-redundancy airplane |
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| US20200115038A1 (en) * | 2018-10-12 | 2020-04-16 | Rolls-Royce North American Technologies Inc. | Electrified mechanical control cables |
| CN109436300A (en) * | 2018-12-29 | 2019-03-08 | 福建野马飞机制造有限公司 | A kind of steerable system of light-duty sport plane |
| CN209441617U (en) * | 2018-12-29 | 2019-09-27 | 福建野马飞机制造有限公司 | A kind of rudder control system of light-duty sport plane |
| CN109502012A (en) * | 2018-12-29 | 2019-03-22 | 福建野马飞机制造有限公司 | A kind of control system of light-duty sport plane |
| CN110450940A (en) * | 2019-06-24 | 2019-11-15 | 陕西飞机工业（集团）有限公司 | A kind of elevator trimming control circuit of aircraft |
| CN110498061A (en) * | 2019-08-28 | 2019-11-26 | 中国科学院工程热物理研究所 | There is the man-machine method for changing unmanned plane based on rudder control system modification |
| CN211124498U (en) * | 2019-12-16 | 2020-07-28 | 天津中德应用技术大学 | Mechanical type aircraft control system maintains training equipment |
| CN111572758A (en) * | 2020-06-24 | 2020-08-25 | 重庆恩斯特龙通用航空技术研究院有限公司 | Soft operating device for light aircraft elevator |
| CN212386681U (en) * | 2020-06-24 | 2021-01-22 | 重庆恩斯特龙通用航空技术研究院有限公司 | Soft steering device for light airplane rudder |
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| Publication number | Publication date |
|---|---|
| CN113184168B (en) | 2023-07-21 |
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