Method for estimating separation trajectory of stage separation wind tunnel free flight test model

Abstract

The invention discloses a method for estimating a separation trajectory of a stage separation wind tunnel free flight test model. The method comprises the following steps of 1, determining an attack angle-mechanical coefficient table of an aircraft model before separation and separated body models after separation; 2, setting initial launching parameters and an initial launching position of a freeflight test of the aircraft model before separation, and setting the separation position of the aircraft model before separation; 3, estimating flight trajectory data of the free flight test of the aircraft model before separation; 4, determining initial launching positions and launching parameters of the separated models; 5, estimating separation trajectory data of the separated models; and 6, judging whether the separation trajectory data of the separated body models meet the test requirements or not, and if not, resetting the initial launching parameters / launching position values in the step 2, starting execution from the step 3 again, until the separation trajectory data of the separated body models meet the test requirements; or readjusting the separation position, and starting execution from the step 4, until the separation trajectory data of the separated body model meets the test requirements.

Description

technical field [0001] The invention belongs to the field of special wind tunnel tests, and in particular relates to a method for predicting the separation trajectory of a free flight test model in an inter-stage separation wind tunnel. Background technique [0002] Wind tunnel free flight test is an important method in the study of aircraft dynamic characteristics and multi-body separation problems. The test principle is to truly reproduce the dynamic characteristics of the aircraft under the action of unsteady aerodynamic force or the multi-body interference during the separation process under the condition of ensuring that the wind tunnel test is similar to the dynamics of the flight state. Directly record and observe the movement characteristics or separation process of the aircraft. At the same time, based on the aerodynamic parameter identification technology, according to the angular displacement and linear displacement data of the model recorded by the high-speed cam...

AI Technical Summary

Problems solved by technology

[0006] Since the test model of the wind tunnel free flight test is lossy, one model will be lost for each test, so if the separation process of the model cannot be displayed in the wind tunnel observation window area, the effective number of tests will be reduced or invalid times, which will result in a waste of wind tunnel blowing times and test models, increasing test costs

However, if the launch speed and launch position are repeatedly adjusted through the actual wind tunnel free flight test results again and again, it will also cause a large waste of wind tunnel blowing times and test models. Therefore, if certain launch parameters and launch positions can be adjusted before the test In this case, the separation process of the aircraft model and the situation of the flight trajectory passing through the observation window area after separation are estimated, and then the entire separation process of the aircraft model and the certain flight trajectory of each separation body after separation are observed in the wind tunnel. The required initial launch parameters and initial launch position of the aircraft model within the window range will be of great significance to ensure the test effect and reduce the cost of the wind tunnel free flight test

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