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Rocket fairing recovery system and method

A recovery system and recovery method technology, applied in the direction of transportation and packaging, aircraft parts, projectiles, etc., can solve the problems of power consumption, poor mobility, etc., to ensure safe landing, improve reliability and success rate, and ensure secondary use Effect

Pending Publication Date: 2020-05-19
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Therefore, the technical problem to be solved by the present invention is to overcome the disadvantages of poor maneuverability and high power consumption of the sea receiving ship of the fairing in the prior art, thereby providing a rocket fairing recovery system and method

Method used

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  • Rocket fairing recovery system and method
  • Rocket fairing recovery system and method
  • Rocket fairing recovery system and method

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Embodiment Construction

[0035] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0036] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, ...

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Abstract

The invention provides a rocket fairing recovery system and method, and belongs to the technical field of rocket sublevel recovery. The rocket fairing recovery system provided by the invention comprises a deceleration system, a control system and an aerial grabbing system, wherein the deceleration system comprises a controllable parafoil and a thrust reverser which are arranged on a fairing; the control system is used for controlling operation of the controllable parafoil and the thrust reverser; and the aerial grabbing system comprises an air vehicle which is provided with a mechanical arm for conducting aerial grabbing on the fairing. According to the rocket fairing recovery system, the fairing grabbed in the air does not need to be received on the ground, the aerial grabbing mode has better maneuverability compared with other receiving modes, safe landing of the fairing can be ensured, and secondary use of the fairing is ensured.

Description

technical field [0001] The invention relates to the technical field of launch vehicles, in particular to a recovery system and method for a rocket fairing. Background technique [0002] The rocket fairing is made of high-strength, lightweight, high-temperature-resistant, and radio-transparent materials. It is located on the top of the launch vehicle. While maintaining the aerodynamic shape of the rocket, it puts a solid armor on the payload spacecraft. [0003] Before the rocket takes off, the fairing protects the spacecraft on the ground to ensure the requirements of the spacecraft for temperature, humidity and cleanliness. When the rocket is lifted through the atmosphere, the fairing can protect the spacecraft from damage caused by aerodynamic force and aerodynamic heat. After the launch vehicle flies out of the atmosphere, the fairing will be divided into two halves along the longitudinal direction of the rocket body and thrown away to complete its mission and return to ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B10/48F42B10/56B64D47/00
CPCF42B10/56F42B10/48B64D47/00
Inventor 彭小波郑立伟施发树
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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