Condition determining method satisfying multistage full free flight wind tunnel test similarity law

Abstract

The invention discloses a condition determining method satisfying a multistage full free flight wind tunnel test similarity law. A dropping type wind tunnel free flight test similarity law is deducedaccording to dynamics and kinematics. Aiming at lifting body appearance and aiming at a totally-free free flight test of a two-stage, even multi-stage model, the test similarity law is designed for the first time, and a lifting body appearance similarity problem is solved emphatically. When the wind tunnel model satisfies a limiting condition, horizontal line displacement and angular displacementcurves obtained by the wind tunnel test can be guaranteed to be similar as the curves of a real aircraft, and the wind tunnel test is guaranteed to be capable of simulating separation conditions of the real aircraft. A difficult problem of absence of similarity law guidance to the two-stage, even multi-stage full free flight test is solved. For the aspect of the absence of the totally-free wind tunnel free flight test similarity law for two, even more aircrafts, conditions satisfying the multi-stage full free flight wind tunnel test similarity law are obtained in the method provided by the invention.

Description

technical field [0001] The invention relates to the parameter design of a free flight test, in particular to a condition determination method satisfying the similarity law of a multi-level full free flight wind tunnel test, and belongs to the field of aerospace engineering. Background technique [0002] The two-stage orbiting vehicle is in a high Ma and high dynamic pressure environment during the separation between the stages, and there are complex aerodynamic interference phenomena during the separation, which makes the separation safety uncertain. In order to ensure the safety of separation, it is necessary to study the separation characteristics of the two-stage orbiting vehicle. In recent years, the multi-body separation full free flight wind tunnel test is a research hotspot in the field of wind tunnel free flight, especially in recent years, the multi-body separation full free flight test technology has made considerable progress, although the test technology has made...

AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is: to overcome the deficiencies in the prior art, to provide a condition determination method satisfying the similarity law of the multi-level full free-flying wind tunnel test, and for the first time to aim at the shape of the lifting body and the completely free free-flying of the two-level or even multi-level models Experimental design and experimental similarity law, focusing on solving the problem of similarity in the shape of lifting bodies

Solved the problem that the horizontal line displacement, vertical line displacement and angular displacement did not correspond between the previous wind tunnel test and the real aircraft, improved the accuracy of the wind tunnel test, and played a guiding role in the development of the real aircraft

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