Ballistic Extrapolation and Filtering Method of Rocket Launching Unpowered Flight

Abstract

The invention discloses a trajectory prediction and value filtration method for a rocket launching unpowered flight segment. An instant orbit injection Kepler parameter of a trajectory is calculated according to a set of credible trajectory measurement data or two sets of position-speed vector data, and then trajectory data after the moment is predicted according to the orbit parameter. A trajectory data result is calculated according to multiple sets of the predicted data and credibility weighting, and the result can be used for displaying the trajectory and measuring anomalous point filtration of the trajectory data in real time. By adopting the trajectory prediction and value filtration method for the rocket unpowered flight segment on the basis of a spacecraft orbit determination method, the display effect and precision of the trajectory are significantly improved.

Description

technical field [0001] The invention relates to rocket trajectory processing and display technology, in particular to a trajectory extrapolation and filtering method for the unpowered flight of a rocket, which is suitable for rockets in the unpowered flight process based on existing measurement data (at least one set of position velocity vectors or two group time position or time velocity vector), calculate its instantaneous orbital parameters, and then extrapolate ballistic data and filter abnormal points of subsequent real-time measurement data, and use the ballistic extrapolation results and filter value results generated by the high-precision orbit determination method The accuracy is greatly improved compared with traditional methods. Background technique [0002] During the flight of the rocket, according to its flight characteristics, the engine is often shut down in the gliding section of the unpowered flight, so as to ensure that the key flight actions of the rocket...

AI Technical Summary

Problems solved by technology

When the rocket is outside the measurement and control range, its flight trajectory data cannot be obtained. In order to ensure the data display requirements, the rocket trajectory must be supplemented. The traditional method is to use the speed within the measurement and control range as its speed outside the measurement and control range. Theoretical ballistics are outside the range of measurement and control, and the display effect and accuracy are poor

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