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A method for realizing centralized loading of propellant in a spacecraft propulsion system

A technology of a propulsion system and a realization method, which is applied in the field of aerospace engineering aircraft to achieve the effects of light weight, elimination of hidden dangers of resonance with the whole vehicle, and good structural stability

Inactive Publication Date: 2014-10-22
SHANGHAI INST OF SPACE PROPULSION
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Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a method for realizing centralized propellant loading of a spacecraft propulsion system, which can effectively solve the problem of centralized propellant loading of a target aircraft propulsion subsystem in manned spaceflight engineering

Method used

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  • A method for realizing centralized loading of propellant in a spacecraft propulsion system
  • A method for realizing centralized loading of propellant in a spacecraft propulsion system
  • A method for realizing centralized loading of propellant in a spacecraft propulsion system

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Embodiment Construction

[0022] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0023] In this embodiment, under the condition of satisfying the relatively strict envelopment restrictions in the cabin, four propellant storage tanks need to be carried. The 1400kg propellant as the main load part is concentrated near the center of the carrying device, and the The installation form also needs to be installed in the form of a large opening, so the design is more difficult.

[0024] See Figure 1(a) and Figure 1(b) together, in the figure, 1 is the conical shell, 2 is the I-shaped cross-section cross beam, 3 is the upper panel, 4 is 28 aluminum alloy angle braces, 5 is the mounting flange, 6 is 16 hat-shaped ribs, 7 is the aluminum honeycomb core layer, 8 is the upper skin of M40 carbon fiber composite material, 9 is the lower skin of M40 carbon fiber composite material, and 10 is 4 aluminum alloy reinforcement rings. The stru...

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Abstract

The invention relates to a propellant carrying device in a propulsion system of an aerospace engineering aircraft. The technical problem to be solved is to provide a method for realizing the centralized carrying of propellant of a spacecraft propulsion system, which can effectively solve the problem of centralized propellant carrying of a propulsion subsystem of a certain target aircraft of a manned spaceflight project. It is characterized in that: a bearing device in the form of a truncated cone; the upper part is an upper panel (3) of a flat plate structure, and a plurality of installation holes are opened on it for installing a propellant storage tank; the lower part of the bearing device is a composite material carbon fiber cone shell (1), and mounted on the cabin through the lower mounting flange (5). The invention adopts the form of honeycomb flat plate structure and composite material cone shell structure, and is supplemented by various forms of structural reinforcement, such as large-sized I-shaped cross beams, hat-shaped reinforcing ribs, triangular aluminum alloy angle braces and variable thickness steps It has good structural stability, and has the advantages of high structural efficiency and light weight.

Description

technical field [0001] The invention relates to an aerospace engineering aircraft, and mainly relates to a propellant bearing structure device in the propulsion system of the aerospace engineering aircraft. technical background [0002] The present invention is designed for a certain type of propulsion sub-system of manned spaceflight engineering to solve the problem of concentrated propellant loading. In the past, the propellant carrying capacity of the propulsion system of manned spacecraft in my country was relatively small, and the installation position of the propellant storage tank container was relatively small. Scattered, never encountered the problem of centralized load bearing, so the metal material plate structure or composite material structure load-bearing device used in the past is not suitable for this system. At present, there is no propellant with large openings with high load and concentrated load carrying device. [0003] While the system has relatively str...

Claims

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Application Information

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IPC IPC(8): B64G1/40
Inventor 苏翠娥刘永琪郑东晓吴剑
Owner SHANGHAI INST OF SPACE PROPULSION
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