Atmosphere data measurement method of hypersonic flight vehicle

Abstract

The invention relates to an atmosphere data measurement method of a hypersonic flight vehicle. The method comprises that a reference coordinate system is defined, the speed, position, attitude, wind speed and inertia device zero offset of the flight vehicle are selected as system state quantities, and front-end surface pressure distribution and position and speed measuring values of the flight vehicle serve as system observed quantities; a system dynamic model is established based on dynamic and kinetic equations of the hypersonic flight vehicle, and a system observation model is established by using mapping relation between system measurement data and atmosphere data; nonlinear Kalman filtering is used to estimate the system state quantity; and an estimated value of the state quantity isused to obtain an atmosphere data estimated value. Compared with a traditional method, the method of the invention can be used to estimate atmosphere data precisely in the hypersonic speed flight environment, a result can be applied to hypersonic flight vehicle control and flight test evaluation and identification, and the flight robustness and evaluation accuracy are improved.

Description

technical field [0001] The invention belongs to the technical field of hypersonic aircraft, in particular to a method for measuring atmospheric data of a hypersonic aircraft. Through this method, a high-precision measurement method of atmospheric data in a hypersonic flight environment can be realized. Background technique [0002] Hypersonic aircraft has the unique advantage of flying in adjacent space at a speed greater than 5 Ma. It is the core key technology for long-term, long-distance, high-speed flight and free access to space in the near space in the future. It has a strong military-civilian background. High-precision atmospheric data and flight parameter measurement technology is one of the most important technologies for air-breathing hypersonic vehicles, which is embodied in the following aspects: [0003] (1) Requirements for flight test testing and evaluation and test database construction. Flight test is the best means of research, verification, assessment an...

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Problems solved by technology

However, due to the error of the inertial device itself and its recursive navigation algorithm, the errors of the flight parameters such as the angle of attack, sideslip angle, and Mach number will gradually increase with time, and the differences between the angle of attack and the angle of sideslip The influence of wind speed was not considered in the calculation process

[0010] 4) Although the GPS (Global Position System) system can provide the position and velocity vector of the aircraft in the inertial space coordinate system, it cannot provide atmospheric data such as the aircraft's angle of attack, sideslip angle, and Mach number.

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