Guidance control method for carrier rocket

Abstract

The invention relates to a guidance control method for a carrier rocket, which is characterized by comprising the following steps: binding standard values such as a standard speed module value v, guidance constant coefficients kuPhi(v) and kuPhi(v) corresponding to the standard speed module value v, and guidance amplification coefficients Kd<Phi> and Kd<Psi>, and the like; according to linear interpolation of two points, calculating the guidance constant coefficients k'uPhi(v) and k'uPsi'(v) of the current point; calculating the guidance weight function I(t) of the current point; further calculating the guidance quantity UPhi(v) and UPsi (v) of the current point, and carrying out amplitude limiting on Uphi(v) and UPsi (v) and then outputting to an attitude control system. By directly adopting rocket speed (or apparent velocity) for replacing the existing universal speed and taking flying time as independent variable, the guidance control method leads guidance calculation process not tobe influenced by each-class shutdown, separation and injection time deviation anymore and improves accuracy of guidance.

Description

technical field [0001] The invention relates to the field of launch vehicle control systems, in particular to a guidance control method for a launch vehicle. Background technique [0002] The standard flight trajectory of the launch vehicle can be determined in advance through theoretical calculations under standard conditions, assuming that the actual flight trajectory deviates from the predetermined standard trajectory by a small amount. Based on this feature, it is allowed to use shutdown characteristic quantities, such as range deviation or other quantities, in the vicinity of the standard trajectory according to the Taylor level The number expands. In principle, the expansion points of the Taylor series should be selected at all points of the predetermined trajectory. Such expansion coefficients are time-varying. Since the motion parameters at the moment of shutdown play a decisive role in the range and the feasibility of engineering implementation, the Taylor series ex...

AI Technical Summary

Problems solved by technology

In actual flight, when the shutdown point deviates greatly from the standard ballistic shutdown point, the guidance effect will drop significantly. According to the flight time, the actual flight trajectory will be guided to the vicinity of the "standard trajectory", starting from the physical meaning of guidance: The root cause of the deviation between the "current trajectory" and the "standard trajectory" is the deviation of speed and position between the two, especially the deviation of speed, rather than the deviation of time. Considering that various deviations that may occur in actual flight will cause There are large deviations in the shutdown, separation, and orbital time of all levels, resulting in a large impact on the guidance effect

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