Load simulator of plane booster dummy assembly

A technology of load simulation and booster, applied in the field of fatigue test of aircraft control system, can solve problems such as failure to meet the requirements of fatigue test, and achieve the effect of speeding up the progress of fatigue test

Active Publication Date: 2012-08-22
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

Therefore, in the general aircraft main control system or aircraft body fatigue test, the aircraft booster dummy is only designed as a simple dummy that fixes the aircraft aileron, horizontal tail or rudder surface and bears the fatigue load of the rudder surface, and does not involve aircraft control. The system itse

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  • Load simulator of plane booster dummy assembly
  • Load simulator of plane booster dummy assembly
  • Load simulator of plane booster dummy assembly

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Embodiment Construction

[0013] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0014] The aircraft booster dummy load simulator of the present invention comprises a base 1, a front joint 2, a rear joint 3, a middle joint 4 and an oil distribution valve simulator 5. The aircraft booster is a general term for aircraft boosters or composite steering gears, and the aircraft booster dummy of the present invention is used for fatigue tests of aircraft hard mechanical irreversible control systems.

[0015] The problems to be solved by the present invention are: 1. Simulate and provide actual booster or compound steering gear oil distribution valve place for the whole machine main control system (aileron, horizontal tail or rudder control system) before the aircraft booster or composite steering gear 2. Adjust and fix the rear control system of the aircraft booster or composite steering gear, and then support the aircraft aileron, horizontal tail or ru...

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Abstract

The invention belongs to a flight control system fatigue test technology and relates to a load simulator of a plane booster dummy assembly. The load simulator comprises a base, a front connector, a back connector, a middle connector and a distributing valve simulator, wherein the distributing valve simulator comprises an outer cylinder, a piston rod, an outer cylinder connector and a piston rod connector. According to the invention, controlling load and controlling run of a plane booster or a composite steering engine distributing valve can be simulated and provided, a requirement on a main control system fatigue test of a whole plane under a plane control load and control displace spectrum is met, at the same time, the load simulator is fixed according to an appointed airplane control surface position, and fatigue tests are carried out on a control system behind the plane booster or the composite steering engine and a plane body simultaneously, so that the main control system fatigue test of the whole plane and the plane body fatigue test can be carried out simultaneously on the same fatigue test plane, the fatigue performance of the plane main control system is truly reflected, and the progress of the main control system fatigue test of the whole plane is accelerated.

Description

technical field [0001] The invention belongs to the fatigue test technology of an aircraft control system, and relates to an aircraft booster dummy load simulator. Background technique [0002] In the past, the fatigue test of the main control system of the whole aircraft was carried out separately, and it was not tested at the same time as the fatigue test of the aircraft body. In addition, the control system before the aircraft booster or the composite steering gear is generally subjected to fatigue tests on the steering column or pedals in a fixed state, and the rear control system of the booster or the composite steering gear is generally carried out on the ground alone stress test. Therefore, in the general aircraft main control system or aircraft body fatigue test, the aircraft booster dummy is only designed as a simple dummy that fixes the aircraft aileron, horizontal tail or rudder surface and bears the fatigue load of the rudder surface, and does not involve aircra...

Claims

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Application Information

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IPC IPC(8): B64F5/00B64F5/60
Inventor 卢京明任孟娣牟瑾刚陈咸彤喻杰
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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