Spin-stabilized falling-area precise control system and method for rocket separator remains

Abstract

The invention relates to a spin-stabilized falling-area precise control system for rocket separator remains. The spin-stabilized falling-area precise control system for rocket separator remains comprises a spinning system, a grid fin system and a separating body, wherein the separating body comprises a separating body head and a separating body; one end, close to the separating body head, of the separating body is equipped with a spinning engine system, and the tail part of the other end is equipped with the grid fin system; the spinning engine system comprises two spinning engines; and spray tubes of the two spinning engines are distributed in an axisymmetric mode along the axis of the separating body. Two symmetrical engines are adopted for spinning a rocket, so that higher spinning rotation speed can be obtained, influences of interference factors such as pneumatic asymmetry and process errors can be effectively reduced, and flying stability of an object is kept; and a combined control way of spin-stabilizing and the grid fin, so that the falling-area range of the rocket remains can be effectively reduced to 100 square kilometers (10 km*10km), and adverse effect on an emitting task of the falling-area problem can be reduced and even avoided.

Description

technical field [0001] The invention belongs to the technical field of overall design and control, and in particular relates to a spin-stabilized rocket separation body wreckage landing zone precise control system and method. Background technique [0002] Modern rockets adopt a multi-stage structure. After the rocket is launched, in order to reduce the dead weight during the flight, the fuel-exhausted sub-stages will be thrown away. The part that is thrown away, that is, the separated body, has no power and no control system. It only has an initial velocity after separation, and it will fall to the ground under the joint action of aerodynamic force and gravity. Due to the randomness of the wind, the landing area will be a A large area where the landing points are scattered, the wreckage landing area of ​​the second and third stage separation bodies of the solid rocket and the second stage separation body of the liquid rocket is generally about 1500 square kilometers (30km×50...

AI Technical Summary

Problems solved by technology

However, in the technology for controlling the rocket separation body, there is no report on the combination of spin stabilization technology and grid rudder technology to achieve a small spread of the landing zone

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