Carrier rocket attitude control method, device and equipment and storage medium

Abstract

The invention discloses a carrier rocket attitude control method, device and equipment and a storage medium, and the method comprises the steps: determining whether a carrier rocket is in a separation prediction control state, the separation prediction control state comprises a contact sub-state and a separation sub-state, and when the carrier rocket enters the separation sub-state from the contact sub-state, determining whether the carrier rocket is in the separation prediction control state; the carrier rocket is separated into a residual body and a separated body; determining the total detachment duration when the carrier rocket is in the detachment sub-state; when the carrier rocket is in the separation sub-state, control instructions are sequentially sent to the remaining body in the first to (N-1) th control periods of the separation sub-state, and the control instructions are used for controlling the attitude angle and the attitude angular speed of the remaining body to reach set values in the next control period. The attitude control method not only can meet the separation safety requirement of the carrier rocket, but also can achieve the purpose of optimizing attitude control.

Description

technical field [0001] The present invention relates to the technical field of launch vehicles, in particular to an attitude control method, device, equipment and storage medium of a launch vehicle. Background technique [0002] Launch vehicle refers to various vehicles manufactured by people to push spacecraft into space, and is used to send artificial earth satellites, manned spacecraft, space stations or interplanetary probes into predetermined orbits. Due to the problems of interference and parameter changes in the launch vehicle itself, its attitude control has always been the focus of researchers. [0003] The attitude control structure of the traditional launch vehicle usually adopts the method of proportional differential joint correction network, and is designed separately by adjusting the parameters according to the difference of the nominal flight state. And in the attitude control method of the traditional launch vehicle, the strategy of stopping the control bef...

AI Technical Summary

Problems solved by technology

[0004] However, during the separation process, the attitude angle and attitude angle rate of the separation body of the launch vehicle have large uncertainties. It is difficult to meet the attitude control of different separation situations by using the method of delaying the start-up control after stopping the control, and there is a risk of collision.

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