CN107719643B

CN107719643B - Fly-by-wire aircraft side lever control mechanism

Info

Publication number: CN107719643B
Application number: CN201710908536.7A
Authority: CN
Inventors: 王雯; 任毅; 何乃平; 李建; 丁云鹏
Original assignee: Lanzhou Flight Control Co Ltd
Current assignee: Lanzhou Flight Control Co Ltd
Priority date: 2017-09-29
Filing date: 2017-09-29
Publication date: 2020-06-16
Anticipated expiration: 2037-09-29
Also published as: CN107719643A

Abstract

The invention belongs to the field of design of airplane control systems, and particularly relates to a telex airplane side lever control mechanism which comprises a force feedback device. The side rod control feeling force of the prior fly-by-wire aircraft is mostly realized by designing a spring loading mechanism between a moving part and a shell and matching with a limiting mechanism. The disadvantages are that: the appearance is long, the volume is large, and the weight is not easy to reduce; the symmetry of tension and compression is limited, and the generation of bidirectional different force sense and width adjustment cannot be realized. The invention provides a fly-by-wire airplane side lever control force feedback device which is used for generating and adjusting fly-by-wire airplane side lever control manual sensing force. The pilot controls the handle to drive the rocker arm rotating shaft to rotate forward or reversely, the spring is driven to stretch, the larger the rotating angle stroke is, the longer the stretching length of the spring is, and the larger the force sense is, so that the generation of bidirectional manual feeling force is realized.

Description

Fly-by-wire aircraft side lever control mechanism

Technical Field

The invention belongs to the field of design of airplane control systems, and particularly relates to a telex airplane side lever control mechanism which comprises a force feedback device.

Background

With the continuous development of the fly-by-wire control system, the side lever control system is light in weight, occupies small cockpit space, and is easier and more accurate to control by a pilot, thereby being beneficial to improving the control quality of an airplane. Therefore, the use of a sidestick with a smaller steering force/displacement and volume/weight instead of a conventional center stick/disk is an option for fly-by-wire aircraft steering systems, and the ability to feedback the desired steering feel and displacement to the pilot would be a direct criterion for verifying whether the sidestick is of good quality. The side rod control feeling force of the prior fly-by-wire aircraft is mostly realized by designing a spring loading mechanism between a moving part and a shell and matching with a limiting mechanism. The disadvantages are that: the appearance is long, the volume is large, and the weight is not easy to reduce; the symmetry of tension and compression is limited, and the generation of bidirectional different force sense and width adjustment cannot be realized.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the fly-by-wire airplane sidestick control force feedback device is used for generating and adjusting the fly-by-wire airplane sidestick control manual sensing force. The pilot controls the handle to drive the rocker arm rotating shaft to rotate forward or reversely, the spring is driven to stretch, the larger the rotating angle stroke is, the longer the stretching length of the spring is, and the larger the force sense is, so that the generation of bidirectional manual feeling force is realized.

The invention relates to a fly-by-wire airplane side lever control mechanism, which comprises a rotating shaft connected with a handle, a transmission gear, a transmission mechanism between the rotating shaft and the transmission gear, and a force feedback mechanism, wherein the transmission mechanism comprises a cam, and the force feedback mechanism comprises a spring assembly and a rocker arm assembly, wherein

The cam is rotatably arranged on the shell and fixedly connected with the rotating shaft, the outer profile of the cam comprises a cam profile and a fan-shaped tooth, the cam profile is approximately V-shaped, and the fan-shaped tooth is meshed with the transmission gear;

the rocker arm assembly comprises a fork-shaped rocker arm, wherein a fork body is rotatably arranged on the shell, the end part of a left fork body is abutted to the cam profile, the end part of a right fork body is connected with one end of a spring assembly, and the other end of the spring assembly is connected with the shell.

And the middle fork body of the rocker arm assembly is arranged on the shell through a bearing and a flange plate.

And a deep groove ball bearing is arranged at the end part of the left fork body and is fixed by a semi-circular head rivet.

The spring assembly comprises a rod end bearing, a spring stud and an extension spring, the rod end bearing is connected with the inner thread of the spring stud through threads, and the spring stud is connected with the extension spring through outer threads.

Mounting holes for mounting the transmission gear, the cam and the forked rocker arm are arranged on the shell, and the axes of the mounting holes are parallel to each other.

The cam is rotatably mounted on the housing by a bearing.

The cam is fixedly connected with the rotating shaft through a positioning pin.

The cam material is stainless steel.

When the control handle enables the rotating shaft to rotate forwards or reversely, the left fork body moves along the cam profile, so that the fork-shaped rocker arm is driven to rotate forwards, the extension spring is pulled open, and the feedback force and the rotating angle are increased synchronously.

The invention has the beneficial effects that: the bidirectional different force senses of the pilot are generated and adjusted in a wide range, the technical bottleneck of single force sense small-range adjustment is broken through, and the manipulation comfort level is improved to a greater extent.

Drawings

FIG. 1 is a front view of a sidestick control mechanism for a fly-by-wire aircraft in accordance with the present invention;

FIG. 2 is a left side cross-sectional view of the sidestick control mechanism of the fly-by-wire aircraft of the present invention;

FIG. 3 is a front view of the housing;

FIG. 4 is a schematic structural view of a spring assembly;

FIG. 5 is a schematic structural view of the rocker arm assembly;

FIG. 6 is a front view of the cam;

FIG. 7 is a left side view of the cam;

fig. 8 is a rear view of the cam.

Detailed Description

The present invention is described in further detail below. Referring to fig. 1, the sidestick control force feedback device of the fly-by-wire aircraft comprises a housing 1, a spring assembly 2, a rocker arm assembly 3, a rotating shaft 6, a cam 7, a bearing 4 and a transmission gear 8. The shell 1 belongs to a fixed part, the left end mounting lug 1a is fixedly connected with a rod end bearing 2a of the spring component 2 through a fastener, a limiting surface 1b and a limiting surface 1d are two-end mechanical limiting devices of a cam 7, a mounting hole 1c is a rotating center when a control handle drives a rotating shaft 6 to rotate, a mounting hole 1e is a rotating and fixing center of a rocker arm component 3, and a mounting hole 1f is a mounting hole of a transmission gear 8; a rod end bearing 2a in the spring assembly 2 is connected with the shell 1a through a fastener, a rod end bearing 2a at the other end is connected with the rocker arm assembly 3 through a fastener, the rod end bearing 2a is connected with an internal thread of a spring stud 2b through a thread, and the spring stud 2b is connected with an extension spring 2c through an external thread; the rocker arm component 3 is an important component for connecting the shell and the supporting spring component 2, the main part is a fork-shaped rocker arm 3f, three mounting holes are formed in the fork-shaped rocker arm 3f, a bushing 3n is mounted in the mounting hole of the right fork body, and the mounting hole is in threaded connection with the spring component 2 through a fastener; 3j is a half-round head rivet, a deep groove ball bearing 3k is fixed on the fork-shaped rocker arm 3f, and a contact pair at the position is changed into rolling friction through 3k, so that the friction coefficient and the resistance are reduced; 3m is a stainless steel bushing which can enhance the strength and rigidity of the joint; the 3a is an elastic retainer ring for the shaft, which is arranged at the shaft end part of the flange plate 3g, so that the axial distance between the deep groove ball bearing 3c, the deep groove ball bearing 3e, the stainless steel sleeve 3d and the flange plate 3g is fixed; the rocker arm component 3 is ensured to be connected to the mounting hole 1e of the shell 1 through the flange plate 3g to realize circumferential rotation; 3g is a flange plate which is mounted and fastened on the shell 1 through a screw 3 h; the bearing 4 is a deep groove ball bearing; the positioning pin 5 is a hollow cylindrical pin, so that accurate positioning of the cam 7 and the shell 1 in the circumferential direction and the axial direction can be guaranteed; the main shaft 6 is a hollow shaft, the appearance of the main shaft is a cylindrical hollow shaft with a consistent section, and a cylindrical pin hole which is completely penetrated is arranged at a determined position on a cylindrical surface; the cam 7 is made of stainless steel, the outer contour of the cam 7 comprises a cam profile and sector teeth, and in order to meet the requirement that the force sense of the operating lever is inconsistent in the front and back directions, the cam is approximately in an asymmetric V shape, the inconsistent gradient of two sides of the cam can cause the inconsistent rotation angle of the rocker arm assembly 3, the spring assembly 2 is further different in stretching displacement, the displacement of the spring assembly 2 is the centralized embodiment of force feedback, and the cam 7 realizes the axial rotation on the shell 1 through the bearing 4.

The working principle of the invention is as follows: when the fly-by-wire airplane sidestick operation force feedback device works, when a pilot operates the handle assembly to enable the cam 7 to rotate, the bearing of the rocker arm assembly 3 rolls on the cam profile of the cam 7, the rocker arm assembly 3 rotates, the spring assembly 2 moves approximately linearly under the action of the rocker arm assembly 3, meanwhile, the movement is transmitted to the transmission gear 8 through the sector-shaped teeth on the cam 7, the mechanical operation instruction of a pilot is converted into an electric signal to be output through the device, and meanwhile, when the pilot operates the handle assembly, the device feeds back the force feedback of approximately linear gradient change to the pilot along with the sending of the mechanical instruction of the pilot, so that the operation comfort level is improved, and the fly-by-wire airplane sidestick operation force feedback device is more in line with. No matter the pilot pushes the pole or pulls the pole backward, for this device turns into the positive rotation or the negative rotation of cam 7, the rotation of cam 7 will drive the dead axle of rocker arm subassembly 3 to rotate forward, and then drive the extension of spring assembly 2, make the control rod produce the force feedback of approximate linear gradient change when pushing forward or pulling backward.

Claims

1. The utility model provides a fly-by-wire aircraft side lever operating mechanism, includes rotation axis (6) be connected with the handle, drive gear (8), drive mechanism and force feedback mechanism between rotation axis (6) and drive gear (8), its characterized in that: the transmission mechanism comprises a cam (7), and the force feedback mechanism comprises a spring assembly (2) and a rocker arm assembly (3), wherein

The cam (7) is rotatably arranged on the shell (1) and is fixedly connected with the rotating shaft (6), the outer profile of the cam (7) comprises a cam profile and a fan-shaped tooth, the cam profile is approximately V-shaped, and the fan-shaped tooth is meshed with the transmission gear (8);

the rocker arm assembly (3) comprises a fork-shaped rocker arm, wherein a fork body is rotatably arranged on the shell (1), the end part of a left fork body is abutted to the cam profile, the end part of a right fork body is connected with one end of a spring assembly (2), and the other end of the spring assembly (2) is connected with the shell (1).

2. The fly-by-wire aircraft sidestick steering mechanism of claim 1 wherein: the middle fork body of the rocker arm component (3) is arranged on the shell (1) through bearings (3c, 3e) and a flange plate (3 g).

3. The fly-by-wire aircraft sidestick steering mechanism of claim 2 wherein: the end part of the left fork body is provided with a deep groove ball bearing which is fixed by a semi-circular head rivet (3 j).

4. The fly-by-wire aircraft sidestick steering mechanism of claim 1 wherein: the spring assembly (2) comprises a rod end bearing (2a), a spring stud (2b) and an extension spring (2c), the rod end bearing (2a) is connected with the inner thread of the spring stud (2b) through threads, and the spring stud (2b) is connected with the extension spring (2c) through outer threads.

5. The fly-by-wire aircraft sidestick steering mechanism of claim 1 wherein: the shell (1) is provided with mounting holes for mounting the transmission gear (8), the cam (7) and the fork-shaped rocker arm, and the axes of the mounting holes are parallel to each other.

6. The fly-by-wire aircraft sidestick steering mechanism of claim 1 wherein: the cam (7) is rotatably mounted on the housing (1) through a bearing (4).

7. The fly-by-wire aircraft sidestick steering mechanism of claim 1 wherein: the cam (7) is fixedly connected with the rotating shaft (6) through a positioning pin (5).

8. The fly-by-wire aircraft sidestick steering mechanism of claim 1 wherein: the cam (7) is made of stainless steel.

9. The fly-by-wire aircraft sidestick steering mechanism of claim 4, wherein: when the control handle enables the rotating shaft (6) to rotate forwards or reversely, the left fork body moves along the cam profile, so that the fork-shaped rocker arm is driven to rotate forwards, the extension spring (2c) is pulled open, and the feedback force and the rotating angle are increased synchronously.