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

A solid rocket, landing technology, applied in the direction of projectiles, self-propelled missiles, offensive equipment, etc., can solve the problem of not forming a closed-loop guidance method for long-range solid rockets

Active Publication Date: 2020-08-07
NORTHWESTERN POLYTECHNICAL UNIV
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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

Method used

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

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Embodiment Construction

[0050] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0051] In order to improve the adaptive ability of the algorithm and meet the needs of rapid launch missions, according to the differential derivative relationship of the instantaneous orbital landing point, the analytical solution of the derivatives related to the instantaneous orbital landing point during free flight is deduced, thus the relationship between the current point and the orbital landing point is established. mapping relationship. The physical mechanism of the landing point range control is revealed by the shortest moving vector and the zero range vector, and the optimal feedback closed-loop guidance method is designed in combination with the characteristics of the solid launch vehicle’s unadjustable thrust and exhaustion shutdown, so as to realize the high-precision landing point control of large and small ranges .

[0052] 1. The analytical form ...

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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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Application Information

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IPC IPC(8): F42B15/01
CPCF42B15/01
Inventor 许志张迁张皓张子祯
Owner NORTHWESTERN POLYTECHNICAL UNIV
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