Dynamic modeling method of missile in-orbit movement

Abstract

The invention discloses a dynamic modeling method of missile in-orbit movement. The method includes (1) simplifying an in-orbit mounting missile into an extensional beam with one end clamped and one end hinged; (2) performing a movement state analysis in an unlocking moment on the simplified in-orbit mounting missile, and resolving the movement state into translation in an X direction, rotation inan XY plane, rotation in an XZ plane, collision in the XY plane and collision in the XZ plane, X being a heading direction, Y being a normal direction and Z being a side direction in a missile coordinate system; (3) building a dynamics equation containing the translation in the X direction, the rotation in the XY plane and the rotation in the XZ plane according to the Newton's second law and a rigid body motion equation, and building a collision dynamics equation in the XY plane and a collision dynamics equation in the XZ plane according to a collision equation; and (4) combining the above equation set to build a dynamic model of missile in-orbit movement according to whether the influence of engine thrust eccentricity is considered.

Description

technical field [0001] The invention relates to a dynamic modeling method, which is suitable for on-orbit motion analysis of an airborne guide rail missile after it is launched and unlocked. Aiming at airborne air-to-ground or air-to-air missiles using guide-rail launch technology, the dynamics of the missile movement during the period when the missile moves on the orbit after the engine is ignited and the lock is successfully unlocked until the front slider leaves the guide rail is disclosed modeling method. Background technique [0002] Usually the work of the launch phase is irreversible and the launch procedure cannot be performed again. Launch safety is a key to the missile weapon system, and its core is to ensure the safety of the separation of the missile and the carrier aircraft, including the separation process of the missile carrier and the safety of the system after separation. [0003] The safety of the shell separation process refers to various safety factors ...

AI Technical Summary

Problems solved by technology

The size of the gap between the slider and the guide rail mainly affects two aspects: one is the risk of the missile being stuck in orbit, and the other is the stability of the missile when it is off-orbit. At present, there is no general standard or standard for the gap between the slider and the guide rail in the industry. It is stipulated in the document that at the same time, most studies on the safety of launch separation at home and abroad conduct macro-analysis, which is reflected in the launch timing, off-orbit separation attitude, etc., and the on-orbit motion of the missile is simplified to a single linear acceleration motion. microscopic analysis

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