A Real-time Orbit Maneuvering Control Method Based on Target Orbit Parameters

Abstract

The invention discloses a real-time track maneuver control method based on target track parameters and relates to the technical field of guidance control. In each iterative calculation cycle, the number of target orbit elements is always taken as the calculation condition, and the initial values ​​of the launch parameters of the vehicle are extrapolated to the theoretical shutdown point, and the geocentric longitude, absolute velocity, and local trajectory of the theoretical shutdown point are calculated. Inclination angle and orbital inclination angle, calculate the deviation relative to the target nominal value and the corresponding Jacobian matrix; calculate the pitch program angle correction amount, yaw program angle correction amount, and remaining flight time in the current iteration calculation cycle according to the Jacobian matrix The time correction amount and the pitch program angle change rate correction amount are corrected and used as the initial value of the next iterative calculation cycle; attitude control and shutdown control are performed according to the calculated flight program angle and remaining flight time in the current iterative calculation cycle. The real-time calculation of the guidance and control system of the vehicle is realized, which has strong engineering application value.

Description

technical field [0001] The invention relates to the technical field of guidance control, in particular to a real-time orbital maneuver control method based on target orbital parameters. Background technique [0002] With the development of the aerospace industry, space launch tasks tend to be more and more diversified and complex, and higher requirements are put forward for the mobility, flexibility, adaptability and final orbital accuracy of the vehicle. Therefore, it is necessary to develop An adaptive guidance method with higher guidance precision and stronger adaptability. The traditional iterative guidance method is inherited from the early polynomial guidance idea. It is an adaptive guidance method developed by the optimal control theory. By controlling the shutdown time and thrust direction of the engine, the three velocity components and three The terminal constraint of the five components in the position component adjusts the program angle and remaining flight time...

AI Technical Summary

Problems solved by technology

[0004] When the thrust provided by the vehicle flight segment is small, especially when the acceleration provided is much smaller than the acceleration of gravity or the theoretical start-up time of the engine is short, and the theoretical speed increment provided is relatively small, the current traditional iterative guidance scheme is not suitable for The adaptability of the above flight states is poor, and the adaptability to ballistic deviation is weak, and there is a risk that the calculation cannot converge during the calculation process

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