General inertial navigation test method based on flight simulation

Abstract

The invention discloses a general inertial navigation test method based on flight simulation. The method comprises the following steps: establishing a flight control simulation module based on a control rate design, designing the flight path, aiming inertial navigation initial conditions, implementing a flight simulation process, and outputting the flight state data of flights; inversely solving and calculating the specific force and angular rate data by utilizing the flight state data; solving and calculating the flight state data of the flights in real time according to the specific force and angular rate; and comparing the flight state data output by the flight control simulation module and the flight state data output by an inertial navigation system according to consistent time shot,and comparing the different information of the data, thus detecting the inertial navigation performance. Through the method provided by the invention, not only can dynamic continuous inertial navigation performance test be intensified, but also the method accords with the test requirements of the complex working environment in the air on the inertial navigation system, and has great significance to engineering practical application of the inertial navigation system performance testing.

Description

technical field [0001] The invention relates to an inertial navigation system testing method under continuous and dynamic simulation of actual flight in the air, and is a general inertial navigation system performance testing method oriented to engineering applications. Background technique [0002] For the performance test of the inertial navigation system, it is generally necessary to test various indicators on a multi-axis turntable or test equipment. For example, Liu Yuhao et al. (Chinese Journal of Inertial Technology, 2008) proposed a Automatic test and calibration system based on turntable. Chen Cai et al. (System Engineering and Electronic Technology, 2010) proposed an identification method for the error coefficient of the inertial navigation platform based on the centrifuge test based on the error of the turntable. The traditional inertial navigation test can only be tested under discrete state conditions, and cannot test the inertial navigation performance of the ...

AI Technical Summary

Problems solved by technology

The traditional inertial navigation test can only be tested under discrete state conditions, and cannot test the inertial navigation performance of the aircraft in continuous flight under various factors in the real air

[0003] However, in the actual flight test, the inertial navigation performance test can carry out continuous flight tests under various complex conditions in the air, but there are many problems such as high cost, long test cycle, and poor flexibility.

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