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Rocket propellant filling butt joint system

A rocket propellant and filling port technology, which is applied in aerospace equipment, space navigation ground equipment, transportation and packaging, etc., can solve the problems of complex docking and locking operations, large docking force, and large terminal load, etc., to achieve Realize the effects of automatic filling and docking, large carrying capacity and easy operation

Active Publication Date: 2020-11-27
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of mechanical arm has the disadvantages of poor rigidity of the body, large end load, complicated docking and locking operation, and large docking force

Method used

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  • Rocket propellant filling butt joint system
  • Rocket propellant filling butt joint system
  • Rocket propellant filling butt joint system

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Embodiment Construction

[0050] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments. Advantages and features of the present invention will be apparent from the following description and claims. It should be noted that the drawings are all in a very simplified form and use imprecise ratios, which are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention.

[0051] see Figures 1 to 3, the core of the present invention is to provide a rocket propellant filling and docking system, including a base 1, at least two filling pipes 2, a docking assembly 3 and several rotating assemblies 4, all filling pipes 2 are connected in sequence, and adjacent The adjacent ports of the filling pipeline 2 are connected in a rotary seal. The filling pipeline 2 at the head end is set on the base 1 and communicates with the filling medium output pipeline. The docking component 3 is set ...

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Abstract

The invention discloses a rocket propellant filling butt joint system. The system comprises a base fixedly connected to a mounting structure, at least two filling pipelines, a butt joint assembly, andseveral rotating assemblies, wherein axes of end openings in the two ends of each filling pipeline do not coincide, all the filling pipelines are sequentially connected, the adjacent end openings ofevery two adjacent filling pipelines are connected in a rotating and sealing mode, and the filling pipeline at a head end is arranged on the base and connected with a filling medium output pipeline; the butt joint assembly is arranged on the filling pipeline at a tail end, and the butt joint assembly is used for being in butt joint with a filling port so that the filling pipeline at the tail end is connected with the filling port; and the rotating assemblies are arranged between the adjacent filling pipelines and used for driving the adjacent filling pipelines to rotate relatively so that thebutt joint assemblies move to the filling port to achieve butt joint connection. The system can achieve automatic filling and butt joint, and is simpler in structure and easy and convenient to operate.

Description

technical field [0001] The invention belongs to the technical field of propellant filling, in particular to a rocket propellant filling docking system. Background technique [0002] The automation level of the launch site preparation process of active launch vehicles is relatively low, especially in the pre-launch filling, pre-launch status inspection and many other links that still require a lot of manual operations. The development of unattended refueling technology can greatly improve the level of rocket automation testing, and effectively change the technical status quo of low automation, many support personnel, and low operating efficiency at the rocket launch site. Through the automatic docking and disengagement technology of the connector, it can effectively avoid the on-site operation of personnel, especially after the conventional propellant liquid rocket connector falls off, when the rocket body fails, the connector needs to be quickly and automatically re-docked a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G5/00
CPCB64G5/00
Inventor 蒋赞洪刚朱亮聪马璎李建强徐鹏里
Owner SHANGHAI AEROSPACE SYST ENG INST
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