Real-time orbital maneuvering control method based on target orbital parameters

Abstract

The invention discloses a real-time orbital maneuvering control method based on target orbital parameters, and relates to the technical field of control-and-guide controlling. The method comprises thesteps that target orbital elements are always taken as computation conditions in each iteration computation period, a theoretical shutdown point is deduced according to the initial values of launch data of a carrier, the distance from the Earth's center to a celestial body, absolute velocity, local ballistic pitch and an orbital pitch of the theoretical shutdown point are calculated, and the deflection amount relative to a target nominal value and a corresponding Jacobian matrix are resolved; the pitch program angle correction, yaw program angle correction, remaining flight time correction and pitch program angle variation rate correction in the current iteration computation period are resolved according to the Jacobian matrix, correction is conducted, and the correction results are takenas the initial values of the next iteration computation period; attitude control and shutdown control are conducted according to the computer flight program angle and the remaining flight time in thecurrent iteration computation period. The method has the advantages that real-time computation of a control-and-guide controlling system of the carrier is achieved, and the method has a higher 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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