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Self-compensation type free up-down pitching coupling mechanism

A technology of ups and downs, pitching and coupling mechanisms, which is applied in the testing of machines/structural components, measuring devices, instruments, etc., can solve the problems of difficult longitudinal short-period motion response characteristics, inability to effectively simulate linear displacement motion, etc., and achieve high repeatability, The effect of short cycle and low risk

Active Publication Date: 2018-03-09
中国航空工业集团公司哈尔滨空气动力研究所
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AI Technical Summary

Problems solved by technology

In view of the fact that the full-scale flight test is limited by economy, safety and attendance rate in evaluating flight quality, and the existing wind tunnel virtual flight test device can only realize free rotation around the axis of the model body, and cannot effectively simulate linear displacement motion. Difficult to be directly used to obtain longitudinal short-period motion response characteristics

Method used

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  • Self-compensation type free up-down pitching coupling mechanism
  • Self-compensation type free up-down pitching coupling mechanism
  • Self-compensation type free up-down pitching coupling mechanism

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Embodiment Construction

[0017] The present invention will be further described in detail below in conjunction with examples, but the embodiments of the present invention are not limited thereto.

[0018] A self-compensating free-floating-pitching coupling mechanism of the present invention is used for flight simulation tests, including a free-floating pitching mechanism and a forced sinking-floating mechanism;

[0019] Such as figure 2 , image 3 As shown, the free-floating pitching mechanism consists of a pitching support frame 3, a pitching shaft 5, a low-damping bearing 1, a set screw 2, a pitching angle limit baffle 4, a free-floating joint 6, a pin 7, a free-floating shaft 8, and an inner hexagon Screw 9, flange-type linear bearing 10, mechanical limit baffle 13, high-precision displacement sensor 12; the top of the free-floating pitch mechanism is connected to the aircraft model through the pitch axis 5, and a low-damping bearing 1 is installed on the top of the inner hole of the pitch suppor...

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Abstract

The invention relates to a self-compensation type free up-down pitching coupling mechanism used for carrying out a flight simulation test; the coupling mechanism comprises a free up-down pitching mechanism and a forced up-down mechanism. The coupling mechanism can greatly extend a vertical line displacement motion scope, thus realizing free up-down and pitching coupling vertical short period motions of a plane model in a horizontal wind tunnel, and satisfying vertical pneumatic / motion coupling characteristics and flight quality research demands. Compared with a flight simulator or test flightmeans, the self-compensation type free up-down pitching coupling mechanism is high in repeatability, short in period, low in risks, thus making up disadvantages of existing wind tunnel test means.

Description

technical field [0001] The invention belongs to the field of aircraft wind tunnel tests, and relates to a special test device for a novel virtual flight test system. Background technique [0002] The aircraft wind tunnel test is an aerodynamic experimental method that places an aircraft or other object model in a wind tunnel to study the gas flow and its interaction with the model to understand the aerodynamic characteristics of the actual aircraft or other objects. The flight quality of an aircraft is related to flight safety and flight performance. The improvement of the longitudinal short-period motion mode is an important content in the design of aircraft flight control laws and the evaluation of closed-loop control quality. In view of the fact that the full-scale flight test is limited by economy, safety and attendance rate in evaluating flight quality, and the existing wind tunnel virtual flight test device can only realize free rotation around the axis of the model bo...

Claims

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Application Information

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IPC IPC(8): G01M9/04G01M9/08
CPCG01M9/04G01M9/08
Inventor 牟伟强卜忱杨文吴佳莉
Owner 中国航空工业集团公司哈尔滨空气动力研究所
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