CN110803278B - Novel redundancy integrated type airplane side lever control device - Google Patents
Novel redundancy integrated type airplane side lever control device Download PDFInfo
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- CN110803278B CN110803278B CN201911124298.6A CN201911124298A CN110803278B CN 110803278 B CN110803278 B CN 110803278B CN 201911124298 A CN201911124298 A CN 201911124298A CN 110803278 B CN110803278 B CN 110803278B
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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
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/042—Initiating means actuated personally operated by hand
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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
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/14—Initiating means actuated personally lockable
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
Abstract
A novel redundancy integrated type airplane side lever control device belongs to the field of airplane structural design. In order to solve the problems that the conventional central rod control system of the airplane is large in size, heavy in weight and poor in maintainability, and the leg space of a pilot is limited, the invention provides a novel redundancy integrated airplane side rod control device: the device comprises a handle, a shell, a spring load mechanism, a cross shaft assembly, a gear, an angular displacement sensor, a damper, a locking mechanism and a filter, wherein the handle is connected with a longitudinal rocker arm in the spring load mechanism, the longitudinal rocker arm forms a universal coupling through a transverse rocker arm in the spring load mechanism and the cross shaft assembly, the longitudinal rocker arm and the transverse rocker arm in the spring load mechanism transmit the transverse and longitudinal swinging of the handle to the angular displacement sensor through the gear, and the angular displacement sensor feeds back a movement displacement instruction of the handle to an airplane. The invention has small volume, light weight, high reliability and good maintainability, can effectively reduce the complexity of the airplane control system and improve the safety of the pilot.
Description
Technical Field
The invention belongs to the field of airplane structure design, and relates to a novel redundancy integrated airplane side lever operating device.
Background
At present, the conventional central rod control system of an airplane has the defects of large volume, heavy weight, poor maintainability and limited leg space of a pilot, so that a technical scheme for improving the problems is urgently needed. The novel redundancy integrated type airplane side rod control device provided by the invention has the advantages of small volume, light weight, high reliability and good maintainability, can effectively reduce the complexity of an airplane control system, obtains better flight quality and improves the safety of a driver.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a novel redundancy integrated type airplane side rod control device.
The technical scheme adopted by the invention is as follows:
the utility model provides a novel redundancy integrated form aircraft side lever controlling device which characterized in that: the device comprises a handle, a shell, a spring loading mechanism, a cross shaft assembly, a gear, an angular displacement sensor, a damper, a locking mechanism and a filter.
The handle is connected with the upper end part of the longitudinal rocker arm through a screw, a through hole of the eccentric wheel is connected with an output shaft of the vibration rod motor, the small cover plate is arranged on the handle and covers the upper part of the vibration rod motor, when an airplane stall warning signal is received, the vibration rod motor works to drive the eccentric wheel to rotate, the handle vibrates, and a pilot senses airplane stall through the handle.
The shell is a square box structure consisting of an upper cover plate, a bottom plate and four side wall plates, and other components are all positioned in the square box structure except a handle penetrating through the upper cover plate.
The spring load mechanism is arranged on four side wall plates through a transverse shaft and a longitudinal shaft in the cross shaft assembly, so that the transverse rotation and the longitudinal rotation are not interfered with each other.
The spring load mechanism is a transverse and longitudinal load force dual-redundancy structure consisting of a transverse rocker arm, 2 transverse springs, 2 transverse rollers, 2 transverse cams, a longitudinal rocker arm, 2 longitudinal springs, 2 longitudinal rollers and 2 longitudinal cams, and provides transverse and longitudinal force displacement characteristics for the handle. The transverse spring is rotationally connected with the transverse rocker arm through a bolt to form a rotational relation, the transverse roller is connected with the transverse rocker arm through a bolt to form a rotational relation and rotates in the transverse cam profile, and the transverse cam is fixedly connected with the transverse rocker arm; the longitudinal spring is rotationally connected with the longitudinal rocker arm through a bolt to form a rotational relation, the longitudinal roller is connected with the longitudinal rocker arm through a bolt to form a rotational relation and rotates in the longitudinal cam profile, and the longitudinal cam is fixedly connected with the longitudinal rocker arm; the transverse cam is fixedly connected with the transverse rocker arm, and the longitudinal cam is fixedly connected with the longitudinal rocker arm. The load mechanism consisting of the double cams and the double springs realizes the force displacement characteristics with different gradients, and when one spring or one cam structure is damaged, the control requirement of a pilot can be realized.
The transverse rocker arm and the longitudinal rocker arm are respectively provided with 4 angular displacement sensors to form a transverse and longitudinal displacement signal four-redundancy structure, transverse and longitudinal rotation angles of the handle are transmitted to the angular displacement sensors through the gears, and the angular displacement sensors convert the rotation angles into displacement instructions and feed the displacement instructions back to the airplane. 4 angular displacement sensors which are transversely or longitudinally distributed are convenient to debug, have the same function as a single angular displacement sensor with four redundancies, but have simple structure and high reliability.
The damper comprises a transverse damper and a longitudinal damper, the lower end of the transverse damper is fixed on the bottom plate and forms a rotating relation, and the upper end of the transverse damper is connected with the transverse rocker arm to provide damping for the transverse rotation of the handle; the lower end of the longitudinal damper is fixed on the bottom plate and forms a rotating relation, and the upper end of the longitudinal damper is connected with the longitudinal rocker arm to provide damping for the longitudinal rotation of the handle; . The damper is a hydraulic damper, and compared with an eddy current damper, the damper is large in damping force and low in power consumption.
The locking mechanism is fixed on the bottom plate, and the filter is fixed on the side wall plate.
Preferably, a rubber sleeve is fixed between the handle and the shell through a pressure plate and is used for sealing a gap between the handle and the shell. Through the rubber sleeve, other structures in the shell are in a sealed environment, and the environmental adaptability is improved.
Preferably, the rotation angles of the transverse rocker arm and the longitudinal rocker arm in the spring loading mechanism can be adjusted to the maximum rotation angle by a limit screw fixed on a side wall plate of the shell.
Preferably, the handle is held in a neutral position, i.e. a transverse and longitudinal rotation angle of 0 °, in automatic flight, i.e. when the pilot is not operating the handle, by the action of the spring-loaded mechanism, and is locked by a locking mechanism to prevent incorrect operation. The locking mechanism consists of a bidirectional self-holding electromagnet and an anti-clamping spring rocker component. The locking mechanism realizes that the handle can get rid of locking within a certain force range when the electromagnet fails through the anti-blocking spring rocker arm component, so that the handle achieves the aim of anti-blocking operation.
Preferably, the vibration rod motor and the bidirectional self-holding electromagnet have slight electromagnetic interference on an airplane system when working, but the function of inhibiting the electromagnetic interference is realized through a designed filter. And because the lightning stroke effect in the flight can be transmitted to the vibrating rod motor and the bidirectional self-holding type electromagnet through the cable, the lightning protection function is realized through the designed filter.
The invention provides a novel redundancy integrated type airplane side lever operating device, which is convenient for simplifying the structure, reducing the volume and the weight, improving the reliability and maintainability, obtaining better flight quality and improving the safety of a driver.
Drawings
FIG. 1 is an external structural view of the present invention;
FIG. 2 is a schematic view of the internal structure of the present invention;
fig. 3 is a schematic diagram of the structure of the spring-loaded mechanism.
The device comprises a handle 1, a screw 1a, an eccentric wheel 1b, a vibrating rod motor 1c, a small cover plate 1d, a shell 2, an upper cover plate 2a, a bottom plate 2b, a side wall plate 2c, a pressure plate 2d, a rubber sleeve 2e, a limit screw 2f, a spring load mechanism 3e, a transverse rocker arm 3a, a transverse spring 3b, a transverse roller 3c, a transverse cam 3d, a longitudinal rocker arm 3e, a longitudinal spring 3f, a longitudinal roller 3g, a longitudinal rocker arm 3e, a cross shaft assembly 4a, a transverse shaft 4b, a longitudinal shaft 5-gear 6-angular displacement sensor 7-damper 7a, a transverse damper 7b, a longitudinal damper 8-locking mechanism 8a bidirectional self-holding electromagnet 8 b-anti-clamping spring rocker arm assembly and a filter 9. .
Detailed Description
For a further understanding of the invention, reference will now be made to the preferred embodiments of the invention by way of example, and it is to be understood that the description is intended to further illustrate features and advantages of the invention, and not to limit the scope of the claims.
The utility model provides a novel redundancy integrated form aircraft side lever controlling device which characterized in that: the device comprises a handle 1, a shell 2, a spring loading mechanism 3, a cross shaft assembly 4, a gear 5, an angular displacement sensor 6, a damper 7, a locking mechanism 8 and a filter 9.
The handle 1 is connected with the upper end of a transverse rocker arm 3a through a screw 1a, a through hole of an eccentric wheel 1b is connected with an output shaft of a vibrating rod motor 1c, and a small cover plate 1d is arranged on the handle 1 and covers the upper part of the vibrating rod motor 1 c. When the stall warning signal of the airplane is received, the vibration rod motor works to drive the eccentric wheel to rotate, so that the handle vibrates, and the pilot senses the stall of the airplane through the handle.
The shell 2 is a square box structure composed of an upper cover plate 2a, a bottom plate 2b and four side wall plates 2c, and except that the handle 1 penetrates through the upper cover plate 2a, all the other components are located inside the square box structure.
The spring loading mechanism 3 is arranged on four side wall plates 2c through a transverse shaft 4a and a longitudinal shaft 4b in a cross shaft assembly 4, so that transverse rotation and longitudinal rotation are not interfered with each other.
The spring load mechanism 3 is a transverse and longitudinal load force dual-redundancy structure consisting of a transverse rocker arm 3a, 2 transverse springs 3b, 2 transverse rollers 3c, 2 transverse cams 3d, a longitudinal rocker arm 3e, 2 longitudinal springs 3f, 2 longitudinal rollers 3g and 2 longitudinal cams 3h, and provides transverse and longitudinal force displacement characteristics for the handle 1. The transverse spring 3b is rotationally connected with the transverse rocker arm 3a through a bolt to form a rotational relation, the transverse roller 3c is connected with the transverse rocker arm 3a through a bolt to form a rotational relation and rotates in a molded surface of the transverse cam 3d, and the transverse cam 3d is fixedly connected with the transverse rocker arm 3 a; the longitudinal spring 3f is rotationally connected with the longitudinal rocker arm 3e through a bolt to form a rotational relation, the longitudinal roller 3g is connected with the longitudinal rocker arm 3e through a bolt to form a rotational relation, the longitudinal roller rotates in the profile of the longitudinal cam 3h, the longitudinal cam 3h is fixedly connected with the longitudinal rocker arm 3e through a load mechanism consisting of double cams and double springs, the force displacement characteristics of different gradients are realized, and when one spring or one cam structure is damaged, the operating requirement of a pilot can also be realized.
The transverse rocker arm 3a and the longitudinal rocker arm 3e are respectively provided with 4 angular displacement sensors 6 to form a transverse and longitudinal displacement signal four-redundancy structure, transverse and longitudinal rotation angles of the handle 1 are transmitted to the angular displacement sensors 6 through the gear 5, and the angular displacement sensors 6 convert the rotation angles into displacement instructions to be fed back to the airplane. 4 angular displacement sensors which are transversely or longitudinally distributed are convenient to debug, have the same function as a single angular displacement sensor with four redundancies, but have simple structure and high reliability.
The damper 7 comprises a transverse damper 7a and a longitudinal damper 7b, the lower end of the transverse damper 7a is fixed on the bottom plate 2b and forms a rotating relation, and the upper end of the transverse damper 7a is connected with the transverse rocker arm 3a to provide damping for transverse rotation of the handle 1; the lower end of a longitudinal damper 7b is fixed on the bottom plate 2b and forms a rotating relation, and the upper end of the longitudinal damper 7b is connected with a longitudinal rocker arm 3e to provide damping for the longitudinal rotation of the handle 1; the damper is a hydraulic damper, and compared with an eddy current damper, the damper is large in damping force and low in power consumption.
The latch mechanism 8 is fixed to the bottom plate 2b, and the filter 9 is fixed to the side wall plate 2 c.
A rubber sleeve 2e is fixed between the handle 1 and the shell 2 through a pressing plate 2d, and the rubber sleeve 2e is used for sealing a gap between the handle 1 and the shell 2. Through the rubber sleeve, other structures in the shell are in a sealed environment, and the environmental adaptability is improved.
The rotation angle of the lateral rocker arm 3a and the longitudinal rocker arm 3e in the spring loading mechanism 3 can be adjusted to the maximum rotation angle by a limit screw 2f fixed to the side wall plate 2c of the housing.
The handle 1 can be kept in a neutral position, i.e. a transverse and longitudinal rotation angle of 0 deg., in automatic flight, i.e. when the pilot is not operating the handle 1, by the action of the spring-loaded mechanism 3, and can be locked by the locking mechanism 8, preventing misoperation. The locking mechanism 8 consists of a bidirectional self-holding electromagnet 8a and an anti-seize spring rocker arm assembly 8 b. The locking mechanism consists of a bidirectional self-holding electromagnet and an anti-clamping spring rocker component. The locking mechanism realizes that the handle can get rid of locking within a certain force range when the electromagnet fails through the anti-blocking spring rocker arm component, so that the handle achieves the purpose of anti-blocking operation.
The vibration rod motor 1c and the bidirectional self-holding electromagnet 8a have slight electromagnetic interference on an airplane system when working, but the function of inhibiting the electromagnetic interference is realized through the designed filter 9. And because the lightning stroke effect in flight can be transmitted to the vibrating rod motor 1c and the bidirectional self-holding type electromagnet 8a through cables, the lightning protection function is realized through the designed filter 9.
Claims (8)
1. The utility model provides a novel redundancy integrated form aircraft side lever controlling device which characterized in that: the device comprises a handle (1), a shell (2), a spring load mechanism (3), a cross shaft assembly (4), a gear (5), an angular displacement sensor (6), a damper (7), a locking mechanism (8) and a filter (9); the handle (1) is connected with the upper end part of the transverse rocker arm (3 a), a through hole of the eccentric wheel (1 b) is connected with an output shaft of the vibration rod motor (1 c), a small cover plate (1 d) is arranged on the handle (1) and covers the upper part of the vibration rod motor (1 c), the shell (2) is of a square box structure consisting of an upper cover plate (2 a), a bottom plate (2 b) and four side wall plates (2 c), and the handle (1) penetrates through the upper cover plate (2 a); the spring load mechanism (3) is arranged on four side wall plates (2 c) through a transverse shaft (4 a) and a longitudinal shaft (4 b) in the cross shaft assembly (4), so that the transverse rotation and the longitudinal rotation are not interfered with each other; the spring load mechanism (3) consists of a transverse rocker arm (3 a), 2 transverse springs (3 b), 2 transverse rollers (3 c), 2 transverse cams (3 d), a longitudinal rocker arm (3 e), 2 longitudinal springs (3 f), 2 longitudinal rollers (3 g) and 2 longitudinal cams (3 h), a transverse and longitudinal load force dual-redundancy structure is formed, and transverse and longitudinal force displacement characteristics are provided for the handle (1); the transverse spring (3 b) is rotationally connected with the transverse rocker arm (3 a) through a bolt to form a rotational relation, the transverse roller (3 c) is connected with the transverse rocker arm (3 a) through a bolt to form a rotational relation and rotates in a molded surface of the transverse cam (3 d), and the transverse cam (3 d) is fixedly connected with the transverse rocker arm (3 a); the longitudinal spring (3 f) is rotationally connected with the longitudinal rocker arm (3 e) through a bolt to form a rotational relation, the longitudinal roller (3 g) is connected with the longitudinal rocker arm (3 e) through a bolt to form a rotational relation and rotates in the molded surface of the longitudinal cam (3 h), and the longitudinal cam (3 h) is fixedly connected with the longitudinal rocker arm (3 e); the transverse rocker arm (3 a) and the longitudinal rocker arm (3 e) are respectively provided with 4 angular displacement sensors (6) to form a transverse and longitudinal displacement signal four-redundancy structure, transverse and longitudinal rotation angles of the handle (1) are transmitted to the angular displacement sensors (6) through the gear (5), and the rotation angles are converted into displacement instructions by the angular displacement sensors (6) and fed back to the airplane; the damper (7) comprises a transverse damper (7 a) and a longitudinal damper (7 b), the lower end of the transverse damper (7 a) is fixed on the bottom plate (2 b) and forms a rotating relation, and the upper end of the transverse damper (7 a) is connected with the transverse rocker arm (3 a) to provide damping for transverse rotation of the handle (1); the lower end of the longitudinal damper (7 b) is fixed on the bottom plate (2 b) and forms a rotating relation, and the upper end of the longitudinal damper (7 b) is connected with the longitudinal rocker arm (3 e) to provide damping for the longitudinal rotation of the handle (1); the locking mechanism (8) is fixed on the bottom plate (2 b), and the filter (9) is fixed on the side wall plate (2 c).
2. The novel redundancy integrated airplane sidestick manipulator of claim 1, characterized in that: a rubber sleeve (2 e) is fixed between the handle (1) and the shell (2) through a pressing plate (2 d), and the rubber sleeve (2 e) is used for sealing a gap between the handle (1) and the shell (2).
3. The novel redundancy integrated airplane sidestick manipulator of claim 1, characterized in that: the rotation angles of a transverse rocker arm (3 a) and a longitudinal rocker arm (3 e) in the spring loading mechanism (3) can be adjusted to the maximum rotation angle through a limiting screw (2 f) fixed on a side wall plate (2 c) of the shell.
4. The novel redundancy integrated aircraft side pole handling device of claim 1, wherein: the handle (1) can be kept at a neutral position, namely a transverse and longitudinal rotation angle is 0 degrees, when the pilot does not operate the handle (1) under the action of the spring loading mechanism (3), and at the moment, the handle can be locked by a locking mechanism (8) to prevent misoperation, wherein the locking mechanism (8) consists of a bidirectional self-holding electromagnet (8 a) and an anti-jamming spring rocker arm assembly (8 b).
5. The novel redundancy integrated airplane sidestick manipulator of claim 1, characterized in that: the vibrating rod motor (1 c) and the bidirectional self-holding type electromagnet (8 a) can realize the functions of inhibiting electromagnetic interference and protecting thunder and lightning through the filter (9).
6. The novel redundancy integrated airplane sidestick manipulator of claim 1, characterized in that: the handle (1) is connected with the upper end part of the longitudinal rocker arm (3 a) through a screw (1 a).
7. The novel redundancy integrated airplane sidestick manipulator of claim 1, characterized in that: the shell (2) is of a square box structure.
8. The novel redundancy integrated airplane sidestick manipulator of claim 1, characterized in that: except for the handle (1), the cover plate (2 a), the bottom plate (2 b) and the four side wall plates (2 c), other components are all positioned inside the shell (2) structure.
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| CN201911124298.6A CN110803278B (en) | 2019-11-15 | 2019-11-15 | Novel redundancy integrated type airplane side lever control device |
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| CN201911124298.6A CN110803278B (en) | 2019-11-15 | 2019-11-15 | Novel redundancy integrated type airplane side lever control device |
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| CN110803278A CN110803278A (en) | 2020-02-18 |
| CN110803278B true CN110803278B (en) | 2023-01-17 |
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| CN112228838B (en) * | 2020-09-22 | 2022-05-24 | 兰州万里航空机电有限责任公司 | Spring tightening device for illuminating lamp of refueling area of airplane |
| CN113277067B (en) * | 2021-05-26 | 2022-11-01 | 贵州华阳电工有限公司 | Mechanical structure with speed reducing plate handle capable of adjusting operating force |
| CN114104268B (en) * | 2021-12-21 | 2024-03-15 | 中国商用飞机有限责任公司 | Aircraft control device |
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