Wind tunnel free flight test model pose measurement system and measurement method

Abstract

The invention discloses a wind tunnel free flight test model pose measurement system. The system comprises an on-site pose capture subsystem, a remote pose resolving subsystem and a model recovery subsystem. The on-site pose capture subsystem is used for measuring the angular velocity and the acceleration of a wind tunnel free flight test model by utilizing an inertial sensor; the remote pose resolving subsystem is used for resolving the angular velocity and acceleration data of the wind tunnel free flight test model measured by the on-site pose capturing subsystem in real time or off line toobtain the pose information of the wind tunnel free flight test model; and the model recovery subsystem is used for recovering the wind tunnel free flight test model and the on-site pose capture subsystem when the test is finished. The invention further discloses a measurement method of the measurement system. According to the invention, the problems that a traditional high-speed photographing method for the wind tunnel free flight test is small in pose information acquisition freedom degree and short in effective data length are solved, and the system is low in cost and can be repeatedly used.

Description

technical field [0001] The invention belongs to the field of wind tunnel flight tests, and relates to a wind tunnel free flight test model pose measurement system and a measurement method. Background technique [0002] As an important branch of the wind tunnel test field, the wind tunnel free flight test technology is an important means of research on the dynamic characteristics of aircraft. Its characteristic is that there is no support interference, and it can more realistically simulate the actual flight state of the aircraft. The principle of the test is to capture the position and attitude of the test model while ensuring that the dynamics of the wind tunnel test and the flight state are similar, and then obtain the static and dynamic stability derivative coefficients and other related aerodynamic coefficients of the aircraft. [0003] At present, the pose capture of the free flight test model in the wind tunnel is based on the high-speed photography method. Its advant...

AI Technical Summary

Problems solved by technology

However, limited by the wind tunnel test conditions, it currently has the following disadvantages: 1. It can only be imaged on a two-dimensional plane, so it can only capture the pose information of three degrees of freedom. For lateral displacement, sideslip angle and roll angle displacement Unable to obtain, which undoubtedly limits the application range of free flight in wind tunnel tests; 2. Limited by the size range of the observation window in the wind tunnel test section and the size reduction ratio of the model, the time for the model to fly within the observation window is relatively short. This will lead to the inability to obtain a long enough effective shooting and recording time, which will affect the accurate analysis of the test results

Among them, Jiang Zenghui et al. in the patent "A Method for Acquiring Shooting and Recording Time in a Launching Wind Tunnel Free Flight Test (CN 105258906B)" and in the patent "A Method for Predicting the Flight Trajectory of a Wind Tunnel Free Flight Test Model (CN 104458202B)" respectively A flight trajectory prediction method and a launch-type wind tunnel free flight test method are proposed to solve the problem of insufficient data due to the short shooting time of the model, but the amount of data obtained is still limited

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