Remote solid rocket instantaneous orbit drop point closed-loop optimal feedback guidance method

Abstract

The invention relates to a remote solid rocket instantaneous orbit drop point closed-loop optimal feedback guidance method. The method comprises the following steps of calculating a drop point range angle and a current drop point radius vector derivative according to a position vector, a velocity vector and the acceleration of a rocket, and calculating a current drop point radius vector and a droppoint control motion vector according to the drop point range angle; and calculating a feedback control equation coefficient according to the current drop point radius vector derivative and the droppoint control motion vector, obtaining the optimal control command acceleration, and finally obtaining a command gesture. According to the remote solid rocket instantaneous orbit drop point closed-loop optimal feedback guidance method provided by the invention, due to the feedback design form, the guidance law has very strong robustness to errors from various sources.

Description

technical field [0001] The invention belongs to the inertial landing point closed-loop guidance technology of a remote solid rocket in the mode of guidance shutdown or exhaustion shutdown, and specifically relates to an optimal feedback guidance method for a remote solid rocket instantaneous orbit drop point closed-loop guidance. Background technique [0002] The main research idea of ​​domestic long-range solid rocket guidance technology is the hybrid guidance method of closed-circuit guidance combined with speed control. For the exhaustion shutdown mode, the remaining apparent velocity increment that the engine can produce is determined by the remaining fuel, and the excess energy that the rocket needs to dissipate is given by the to-be-accelerated velocity vector and the remaining apparent velocity increment. The existing methods mainly focus on the following points: 1. An iterative guidance method suitable for solid rockets is designed by taking the velocity vector as th...

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Problems solved by technology

However, this method has the problem of infinite solutions in the process of solving kinematics that requires velocity vectors, that is, there is a zero-range line vector and the velocity can be controlled through energy management, and a unified long-range solid rocket closed-loop guidance method has not been formed.

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