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Inertia drop point control closed-loop guidance method under solid carrier rocket exhaustion shutdown mode

A launch vehicle, exhaust shutdown technology, applied in the aerospace field, can solve the problems of inability to bind elliptical orbit parameters, insufficient self-adaptability of guidance methods, etc.

Active Publication Date: 2021-01-29
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention mainly solves the shortcomings of the current classical closed-circuit guidance, that is, it is impossible to pre-bind the best elliptical orbit parameters in the elliptical orbit clusters that meet the range constraints through offline design under the rapid launch condition, which makes the guidance method insufficient in autonomous adaptability

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  • Inertia drop point control closed-loop guidance method under solid carrier rocket exhaustion shutdown mode
  • Inertia drop point control closed-loop guidance method under solid carrier rocket exhaustion shutdown mode
  • Inertia drop point control closed-loop guidance method under solid carrier rocket exhaustion shutdown mode

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Embodiment Construction

[0064] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0065] 1. The analytical form of the instantaneous orbit drop point and its derivative

[0066] In the absence of external forces such as thrust or aerodynamic force on a solid launch vehicle, the instantaneous orbital landing point of the Kepler orbit (defined as the latitude and longitude of the current flight state mapped to the ground landing point along the Kepler orbit) should remain constant. However, once the rocket is subjected to an external force, the instantaneous orbital landing point will move on the Earth's surface in a manner determined by the derivative of the instantaneous orbital landing point's latitude and longitude.

[0067] 1.1 Analytical function of the instantaneous orbit drop point

[0068] According to the particle dynamics formula (1) of the launch vehicle, the instantaneous ballistic landing point without the action of thrust and ae...

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Abstract

The invention relates to an inertia drop point control closed-loop guidance method in a solid carrier rocket depletion shutdown mode, and the method comprises the steps of deducing an analytical solution of an instantaneous orbit drop point related derivative in a free flight process according to the differential derivative relation of an instantaneous orbit drop point, and building a mapping relation between a current point and the orbit drop point; determining the current acceleration instruction vector according to the current remaining flight time of the solid carrier rocket, and it is guaranteed that the instantaneous orbit drop point moves to the target point when an engine of the solid carrier rocket is exhausted and shut down, the carrier rocket continues to slide to the target drop point along the Kepler orbit, and meanwhile the invention has very high guidance precision.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and in particular relates to an inertial landing point closed-loop guidance technology of a long-range solid rocket in the exhausted shutdown mode. 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-increased 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 the iterative variable, and the terminal accuracy is improved through the form of closed-loop iterative c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F30/15F42B15/01G06F111/10
CPCG06F30/20G06F30/15F42B15/01G06F2111/10
Inventor 张迁许志张源刘家宁杨垣鑫
Owner NORTHWESTERN POLYTECHNICAL UNIV
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