Rudder pedal assembly for controlling aircraft and aircraft
A technology for rudders and aircraft, which is applied in the control of starting methods, aircraft parts, aircraft control, etc. It can solve the problems of poor control accuracy, loss of spring force feeling and return ability of the pedals, long transmission route of the rudder pedals, etc., and achieve reduction Effects of overshoot or oscillation, increased stiffness, and increased safety
Active Publication Date: 2022-05-13
COMAC +1
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Problems solved by technology
However, this construction, while significantly reducing pedal weight, increases the risk of common mode failure
On the other hand, the transmission path of the rudder pedals in the distributed offset layout is long, the control accuracy is poor, and the breakage of the tie rod will cause the pedals on one side to lose the sense of spring force and the ability to return to the center
[0006] Therefore, prior art aircraft rudder pedal assemblies are not entirely satisfactory
Method used
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[0026] Next, the inventive concept of the present invention will be described in detail with reference to the accompanying drawings. What is described here is only a preferred embodiment of the present invention, those skilled in the art can think of other ways to realize the present invention on the basis of the preferred embodiment, and other ways also fall within the scope of the present invention.
[0027] figure 2 A schematic diagram showing a rudder pedal assembly according to one embodiment of the present invention. according to figure 2 It can be seen that the rudder pedal assembly includes: the first rudder pedal unit 11, which is the forward driving rudder pedal unit; the second rudder pedal unit 13, which is the copilot rudder pedal unit; Driving and damping module 12. The trim back drive and damping module 12 is arranged between the first rudder pedal unit 11 and the second rudder pedal unit 13 and is connected with the first rudder pedal unit and the second r...
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The invention relates to a rudder pedal assembly for controlling an aircraft and an aircraft, the rudder pedal assembly includes a first rudder pedal unit, a second rudder pedal unit and a trim back drive and damping module, wherein, relative to the rudder pedal The installation position of the pedal assembly in the aircraft, the trim back drive and damping module is arranged between the first and the second rudder pedal unit, and is connected with the first direction and the second rudder pedal unit through corresponding coupling links , wherein the first and second rudder pedal units respectively include a pair of pedals and a spring, and the spring can provide corresponding force feedback in response to the action of the pedals; the trim back drive and damping module includes a main shaft and a parallel connection The trim driveback motor and damper for this main shaft are assigned to the first and second rudder pedal units.
Description
technical field [0001] The present invention relates to a rudder pedal assembly for controlling an aircraft, such as an airplane, and to an aircraft comprising such a rudder pedal assembly. Background technique [0002] The fly-by-wire flight control system of the aircraft uses the rudder pedal assembly as the pilot's manipulation input to control the heading attitude of the aircraft; on the ground, it can also be used for deceleration and braking of the aircraft. The rudder pedal assembly converts the pilot's mechanical control into an electrical signal through a displacement sensor and outputs it to the flight control computer to realize aircraft yaw control. [0003] In the technical field of aircraft, in order to provide fixed force feedback and damping force, a force feedback mechanism composed of, for example, a spring and a damper or a force feedback device including a driveback motor is generally provided. In situations where the pilot is required to control the air...
Claims
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IPC IPC(8): B64C13/04B64C13/50
CPCB64C13/044B64C13/50
Inventor 李剑薛瀛郭海新郭建伟杨夏勰罗鑫
Owner COMAC