An aircraft control system fixing device

Abstract

The invention relates to a fixing device of an aircraft control system, and belongs to the technical field of aeroelastic effect tests. The device comprises pedal fixing units (1), steering wheel fixing units (2), a basis (3) and support bar systems (4), wherein one end of each pedal fixing unit is connected with the basis, and a clamping end is arranged at the other end of each pedal fixing unit and is used for clamping a pedal connecting tube of an aircraft pedal; one end of each support bar system is connected to the basis, and the other end extends toward an aircraft steering wheel to form a hollow tube; each hollow tube is used for muff-coupling and fixing an end part of the corresponding steering wheel fixing unit; a second clamping end is arranged at the other end of each steering wheel fixing unit, and is used for clamping a steering wheel control handle of the aircraft steering wheel. Through the device, whole aircraft control system fixation can be realized in the process of an aircraft ground resonance test, each part is prevented from relative displacement in the fixation process, and measurement of each control surface rotating frequency in the resonance test is ensured.

Description

technical field [0001] The invention belongs to the technical field of aeroelasticity test, in particular to an aircraft control system fixing device. Background technique [0002] General-purpose aircraft usually adopt a reversible control system driven by cables. When conducting the ground resonance test of the whole aircraft, it is difficult to measure the rotation frequency of the rudder surface if each rudder surface is not fixed. Therefore, it is necessary to fix each control surface of the aircraft at a neutral position. This support requires fixing at the control end. In addition to making the steering wheel and pedals unable to move relative to each other under the limited external force of the control surface, the entire control system circuit should also be guaranteed. The control stiffness is not affected, and the appearance and structure of the steering wheel and pedals of the aircraft are not damaged. In the prior art, the general-purpose aircraft ground reson...

AI Technical Summary

Problems solved by technology

In the prior art, the general-purpose aircraft ground resonance test usually uses the simple positioning mechanism of the aircraft itself to fix the control surface at the neutral position, or uses the method of screwing the steering rod and pedals, which is difficult to achieve a stable , constant and gap-free fixation, and may damage the appearance and structure of the steering wheel and pedals. At the same time, when the rudder surface is excited by external force during the test, it is easy to disengage, and the fixing effect is not ideal. In this case, the obtained The experimental data error is relatively large

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