Aircraft orbit injection control method using space vector matching

Abstract

The invention discloses an aircraft orbit injection control method using space vector matching. The method includes the following steps of initiating state parameters of an aircraft, calculating the root and geocentric radius vector of a current orbit of the aircraft and the rotating angle of the current orbit relative to a standard orbit, obtaining a standard orbit speed vector which a current orbit state should have according to the geocentric radius vector and the rotating angle of the current orbit relative to the standard orbit, calculating the deviation value of the speed vector, the residual flight time DT, the pitching program angel and the yaw program angle according to the standard orbit speed vector and a current actual orbit speed vector, and conducting posture control and shutdown control through the calculated residual flight time DT, pitching program angel and yaw program angle. The invention relates to the technical field of orbit control. The method is high in real-time performance, high in guidance precision and high in orbit adjusting capacity, flight software on the aircraft is simple, and the work requirements for preparing and calculating various elements on the ground are low.

Description

technical field [0001] The invention relates to the technical field of orbit control, in particular to a control method for spacecraft orbit entry by using space vector matching. Background technique [0002] Aiming at space missions for spacecraft to achieve precise orbital entry, the basic stage generally adopts multi-stage engines connected in series, and the energy deviation of the engines at each stage will accumulate to the final orbital stage, which will have a large impact on the program angle control of the final stage orbital stage. Influence, especially for the spacecraft with solid engine at the basic level, the engine generally adopts the exhaustion shutdown mode, and the engine cannot adjust the shutdown time of the engine according to the current actual situation, so it may produce a relatively large position velocity compared with the theoretical situation Deviation, the program angle calculated by the final stage when re-planning the orbit may vary greatly r...

AI Technical Summary

Problems solved by technology

[0002] Aiming at space missions for spacecraft to achieve precise orbital entry, the basic stage generally uses multi-stage engines connected in series, and the energy deviation of the engines at each stage will accumulate to the final orbital stage, which will have a large impact on the program angle control of the final stage orbital stage. Influence, especially for the spacecraft with solid engine at the base level, the engine generally adopts the exhaustion shutdown mode, and the engine cannot adjust the shutdown time of the engine according to the current actual situation, so it may produce a relatively large position velocity compared with the theoretical situation Deviation, the program angle calculated by the final stage when re-orbit planning may vary greatly relative to the standard program angle

On the other hand, in order to improve the accuracy of the final stage orbiting, the spacecraft generally adopts the iterative guidance control method, but the traditional iterative guidance method generally takes the terminal orbit as the control target, and adapts to the large attitude adjustment in the small overload state during the flight process. Sex is not strong

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