CN-121973928-A - Fly-by-wire aircraft cockpit control system based on gear universal joint transmission

CN121973928ACN 121973928 ACN121973928 ACN 121973928ACN-121973928-A

Abstract

The invention discloses a fly-by-wire aircraft cockpit control system based on gear universal joint transmission, which belongs to the technical field of aircraft cockpit control systems and comprises a steering control assembly, a longitudinal control assembly, a transverse balancing assembly and a vibration rod device, wherein the longitudinal control assembly is in transmission connection with a steering rod and is used for realizing longitudinal control force sense provision, damping effect and mechanical interconnection and fault isolation, the transverse control assembly is in transmission connection with the steering rod and is used for realizing transverse control force sense provision, damping effect and mechanical interconnection and fault isolation, the transverse balancing assembly and the transverse control assembly are used for realizing transverse balancing function, the fly-by-wire aircraft cockpit control system adopts gear universal joint hard transmission, functional components are modularly integrated in a load module, and longitudinal control and transverse control realize motion decoupling through universal joints. The invention has the advantages of relatively compact structure, higher integration level, light weight, high rigidity and better maintainability and environmental applicability.

Inventors

WANG JINWEI
ZHANG MING
LI XIAOPENG
LIU JIAN
WENG JIE
JIN JIALONG
KONG WEIYU
WANG JUNJUN

Assignees

中航电测仪器(西安)有限公司

Dates

Publication Date: 20260505
Application Date: 20260327

Claims (10)

1. The fly-by-wire aircraft cockpit control system based on the gear universal joint transmission is characterized by comprising a steering control assembly, a longitudinal control assembly, a transverse trimming assembly and a vibration rod device (9), wherein: The steering control assembly comprises a left steering wheel (1), a right steering wheel (10) and a steering rod (2), wherein the left steering wheel (1) and the right steering wheel (10) are respectively connected with the steering rod (2), and the steering rod (2) is arranged on an airplane structure; the transverse balancing component is connected with the transverse control component and used for achieving a transverse balancing function, the vibration rod device (9) is arranged at the lower part of the steering column (2), the fly-by-wire aircraft cockpit control system adopts hard transmission of a gear universal joint, functional components are integrated in a load module in a modularized mode, and longitudinal control and transverse control achieve motion decoupling through the universal joint.
2. The fly-by-wire aircraft cockpit control system based on the gear universal joint transmission according to claim 1, wherein the longitudinal control assembly comprises a left steering column force sensor (3), a right steering column force sensor (8), a left longitudinal load module (4), a right longitudinal load module (7), a longitudinal release device (5) and a longitudinal damper (6), one end of the left steering column force sensor (3) is connected with the steering column (2), the other end of the left steering column force sensor is connected with the left longitudinal load module (4), one end of the right steering column force sensor (8) is connected with the steering column (2), the other end of the right steering column force sensor is connected with the right longitudinal load module (7), two ends of the longitudinal release device (5) are respectively connected with the left longitudinal load module (4) and the right longitudinal load module (7), and the longitudinal damper (6) is assembled on the left longitudinal load module (4) and the right longitudinal load module (7).
3. The gear-gimbal-drive-based fly-by-wire cockpit control system of claim 2 wherein the left longitudinal load module (4) includes a longitudinal input rocker arm (401), a longitudinal neutral pin (402), a longitudinal main housing (403), a longitudinal stop (406), a longitudinal main shaft (407), a longitudinal load mechanism (408), a longitudinal drive gear train (409), a longitudinal sensor interface (4010) and a back-up longitudinal sensor interface (4011), the longitudinal input rocker arm (401) being coupled to the longitudinal main shaft (407), the longitudinal stop (406) providing mechanical stop for the longitudinal input rocker arm (401).
4. The fly-by-wire aircraft cockpit control system based on a gear universal joint transmission according to claim 1, characterized in that the transversal steering assembly comprises a left steering wheel force sensor (11), a right steering wheel force sensor (16), a left transversal load module (12), a right transversal load module (15), a transversal release device (13) and a transversal damper (14), wherein one end of the left steering wheel force sensor (11) is connected with a steering column (2) and the other end is connected with the left transversal load module (12) and the transversal release device (13), one end of the right steering wheel force sensor (16) is connected with the steering column (2) and the other end is connected with the transversal release device (13), the transversal release device (13) is connected with the right transversal load module (15) at one end far from the left steering wheel force sensor (11), and the transversal damper (14) is assembled with the left transversal load module (12) and the right transversal load module (15).
5. The gear-universal-drive-based fly-by-wire aircraft cockpit management system of claim 4 wherein the left lateral load module (12) includes a lateral input rocker arm (1201), a lateral neutral pin (1202), a lateral main housing (1203), a lateral stop (1206), a lateral main shaft (1207), a lateral load mechanism (1208), a lateral drive gear train (1209), a lateral sensor interface (1210), a backup lateral sensor interface (1211), and a left lateral trim mechanism interface (1212), the lateral input rocker arm (1201) being coupled to a lateral main shaft (1207), the lateral stop (1206) providing a mechanical stop for the lateral input rocker arm (1201).
6. The fly-by-wire aircraft cockpit control system based on the gear universal joint transmission according to claim 1, wherein the transverse trimming assembly comprises a left transverse trimming mechanism (17), a right transverse trimming mechanism (19) and a trimming corrugated pipe (18), the left transverse trimming mechanism (17) is arranged on a left transverse load module (12), the right transverse trimming mechanism (19) is arranged on a right transverse load module (15), and two ends of the trimming corrugated pipe (18) are respectively connected with the left transverse trimming mechanism (17) and the right transverse trimming mechanism (19).
7. The fly-by-wire aircraft cockpit control system of claim 1 based on gear universal joint transmission, wherein the steering column (2) comprises an upper arm (201), a sleeve (202), a longitudinal steering rocker arm (203), a counterweight (204), a bevel gear set (205), a transmission tube shaft (206), a first universal joint (207), a second universal joint (208), a support (209), a ball (2010) and a transverse rocker arm (2011), the bevel gear set (205) and the transmission tube shaft (206) are sequentially connected with the first universal joint (207) in a transmission way, the first universal joint (207) is connected with a second universal joint (208), and the second universal joint (208) is connected with the transverse rocker arm (2011).
8. The gear-cardan drive-based fly-by-wire cockpit control system according to claim 7, wherein the centre points of the first and second gimbals (207, 208) are located on the rotation axis of the steering column (2) in order to achieve a decoupling of the movements of the longitudinal and transverse steering.
9. The gear-universal-joint-transmission-based fly-by-wire cockpit control system according to claim 1, characterized in that the longitudinal release means (5) enable mechanical interconnection and jamming fault isolation of the left longitudinal load module (4) and the right longitudinal load module (7), and the transverse release means (13) enable mechanical interconnection and jamming fault isolation of the left transverse load module (12) and the right transverse load module (15).
10. The gear-gimbal-drive-based fly-by-wire cockpit control system of claim 1 wherein the left lateral trim mechanism (17) comprises a motor (1705), a left worm gear assembly (1706), and a resolver (1708), the right lateral trim mechanism (19) comprises a right worm gear assembly (1901), and the left lateral trim mechanism (17) and right lateral trim mechanism (19) each provide a force sensing anchor for a corresponding lateral load module.

Description

Fly-by-wire aircraft cockpit control system based on gear universal joint transmission Technical Field The invention belongs to the technical field of aircraft cockpit control systems, and particularly relates to a fly-by-wire aircraft cockpit control system based on gear universal joint transmission. Background At present, most airplanes in and out of the industry adopt fly-by-wire operation modes, and a fly-by-wire aircraft cockpit operation system is characterized in that a pilot uses a steering column/disk and pedals as human interfaces, when the pilot operates the steering column/disk, a mechanical instruction is generated, an instruction displacement sensor is responsible for converting the mechanical instruction into an electric signal and sending the electric signal to a flight control computer, and the flight control computer controls a control surface actuator to realize pitching, rolling and yawing operation of the airplane. The fly-by-wire aircraft cockpit control system mainly comprises a steering column/disk, a force sensor, a load mechanism, a sensor, a damper, a balancing device and the like. As an improvement, in the existing cockpit control system, one thought is to adopt a large number of pull rods and rocker arms in a distributed layout, the structure is complex, the problems of poor linearity of a system transmission ratio, heavy system weight, large installation occupied space, difficult on-board installation, poor trafficability, inconvenient inspection and maintenance, poor battle viability and the like exist, and the other thought is to adopt a large number of soft-hard combined integrated layout, so that the structure is relatively simple, but the transverse control adopts soft control, and the problems of poor system rigidity, high friction force, the requirement for periodic inspection and replacement of steel ropes and the like exist. Therefore, in the comprehensive view, in the existing cockpit control system, the integration level and compactness of the structure are insufficient, the installation and maintenance are inconvenient, the transmission linearity and rigidity are insufficient, the control stability of a pilot can be influenced, and the use requirement of a high-performance fly-by-wire aircraft is difficult to adapt. Disclosure of Invention The invention provides a fly-by-wire aircraft cockpit control system based on gear universal joint transmission, which aims to solve the problems that the existing cockpit control system has insufficient structural integration level and compactness, inconvenient installation and maintenance, insufficient transmission linearity and rigidity, possibly influencing the control stability of a pilot and difficult to adapt to the use requirement of a high-performance fly-by-wire aircraft. In order to achieve the above purpose, the invention adopts the following technical scheme: the invention provides a fly-by-wire aircraft cockpit control system based on gear universal joint transmission, which comprises a steering control assembly, a longitudinal control assembly, a transverse balancing assembly and a vibrating rod device, wherein: The steering control assembly comprises a left steering wheel, a right steering wheel and a steering rod, wherein the left steering wheel and the right steering wheel are respectively connected with the steering rod, and the steering rod is arranged on an aircraft structure; The transverse balancing component is connected with the transverse control component and used for realizing the transverse balancing function, the vibration rod device is arranged at the lower part of the steering column, the steering system of the fly-by-wire aircraft cockpit adopts the hard transmission of a gear universal joint, the functional components are integrated in the load module in a modularized manner, and the longitudinal control and the transverse control realize the motion decoupling through the universal joint. In some embodiments, the longitudinal handling assembly comprises a left steering column force sensor, a right steering column force sensor, a left longitudinal load module, a right longitudinal load module, a longitudinal releasing device and a longitudinal damper, wherein one end of the left steering column force sensor is connected with the steering column, the other end of the left steering column force sensor is connected with the left longitudinal load module, one end of the right steering column force sensor is connected with the steering column, the other end of the right steering column force sensor is connected with the right longitudinal load module, two ends of the longitudinal releasing device are respectively connected with the left longitudinal load module and the right longitudinal load module, and the longitudinal damper is assembled on the left longitudinal load module and the right longitudinal load module. Further, the left longitudinal load module comprises a longitudinal input rocker arm, a