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A Hybrid Lateral Control System for Large Aircraft

A lateral control and hybrid technology, applied in the field of flight control, can solve the problems of lack of rudder surface return mechanism, return to neutral effect, etc., and achieve the effect of simple implementation, light weight, and reduced flight burden.

Active Publication Date: 2017-10-31
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

In addition, these aircraft are all medium-sized aircraft. Large aircraft with lateral systems that can be operated mechanically and with full-authority fly-by-wire control are currently blank in China. Foreign large aircraft lateral control systems have this kind of hybrid control, but in mechanical mode There is no centering mechanism for the rudder surface, the centering of the lateral control rudder surface mainly depends on the spring load mechanism in the cockpit, and the rudder surface is very far away from the cockpit, and the return to neutrality will be affected

Method used

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  • A Hybrid Lateral Control System for Large Aircraft

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Embodiment Construction

[0022] The driver’s lateral main control device is the steering wheel, and the driver’s lateral mechanical manipulation command is linked with the precision gear through the steering wheel, and the mechanical manipulation command is simultaneously converted into a voltage signal and a mechanical transmission command through the hard rod rocker arm transmission and the lateral command sensing system. in,

[0023] The voltage signal is sent to the actuator controller (ACE), the actuator controller converts it into a digital quantity and sends it to the main flight control computer (PFC) through the GJB289A bus, and the main flight control computer (PFC) performs all input signals Vote and monitor between channels, and calculate the control law to form a control command, and then vote and monitor the output command between channels, and then send the control command to the actuator controller (ACE) through the GJB289A bus; each action The actuator controller (ACE) receives the co...

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Abstract

The invention belongs to the technical field of flight control, in particular to a lateral control system. The invention utilizes the driver's main control device with instructions, the irreversible full-assist electromechanical control integrated actuation system, the long-wire cable transmission device, the centering spring near the rudder surface, etc., so that the implementation of the mechanical and telex hybrid lateral control system is simple. , light weight, high degree of system integration, two different control methods to increase the redundancy design, with a control backup function, which improves the safety of the aircraft. In the mechanical mode, the attitude control of the aircraft is easy.

Description

technical field [0001] The invention belongs to the technical field of flight control, in particular to a lateral control system Background technique [0002] In the aviation field, the lateral control systems of existing aircraft are all simple control methods, one is pure mechanical control or mechanical control with stability enhancement control, such as Air Police 200 aircraft, Air Police 2000 aircraft, and one is pure telex Manipulation, such as J-10 aircraft. In addition, these aircraft are all medium-sized aircraft. Large aircraft with lateral systems that can be operated mechanically and with full-authority fly-by-wire control are currently blank in China. Foreign large aircraft lateral control systems have this kind of hybrid control, but in mechanical mode There is no centering mechanism for the rudder surface, the centering of the lateral control rudder surface mainly depends on the spring load mechanism in the cockpit, and the centering of the rudder surface tha...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C13/00
Inventor 贺蕊亲喻杰刘波王慧
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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