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Leak rate design method for sealed cabin of manned spacecraft

A technology of manned spacecraft and design method, which is applied in the field of leak rate design of manned spacecraft airtight cabin, and can solve problems such as the lack of top layer design of airtight cabin

Inactive Publication Date: 2015-11-25
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

[0005] However, in the existing technology, a single-dimensional design method is mostly used, and the leak rate index of the sealed cabin is set based on previous experience. After the engineering inspection meets the requirements, it is reversely recalculated to see if the air volume in the entire task stage meets the requirements. , lacking the top-level design of the leak rate of the sealed cabin

Method used

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  • Leak rate design method for sealed cabin of manned spacecraft
  • Leak rate design method for sealed cabin of manned spacecraft
  • Leak rate design method for sealed cabin of manned spacecraft

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Embodiment Construction

[0020] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0021] in, figure 1 is the specific flow chart of the design method for the cabin leakage rate of manned spacecraft, figure 2 It is a composition diagram of the sealing link of the airtight cabin of the manned spacecraft, image 3 It is a schematic diagram of the conversion relationship between mass leakage and leak rate.

[0022] like figure 1 As shown, the method specifically includes the following steps:

[0023] According to the system scheme design, the mission analysis is carried out on the flight mode of the manned spacecraft in the whole mission stage, and the mission time requirements of each flight stage are obtained;

[0024] Preliminary determination of the gas weight that the system can use for leakage compensation, and system weight analysis for manned spacecraft;

[0025] Preliminarily calculate the mass leakage of the se...

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Abstract

The invention provides a leak rate design method for a sealed cabin of a manned spacecraft. The method is used for covering an overall process of an in-orbit flight. The method comprises the steps as follows: step 1, calculating mass leakage rate of the sealed cabin of the manned spacecraft according to a task time requirement of each flight phase in the overall process of the in-orbit flight and weight of leaked compensation gas; step 2, calculating a standard leak rate index of the sealed cabin according to the mass leakage rate, and step 3, executing engineering process check and iteration to the standard leak rate index so as to determine a sealed cabin leak rate index meeting a preset requirement. Therefore, the leak rate design method for the sealed cabin of the invention covers a gas leakage compensation requirement of all task stages of the manned spacecraft, and takes full advantage of a theoretical basis of an ideal gas state equation, and considers design constraints in a plurality of aspects such as flight mission planning, system weight control and product process so as to solve the problem of achieving a top flight task requirement to a specific sealed cabin leak rate index of the manned spacecraft.

Description

technical field [0001] The invention belongs to the field of overall design of spacecraft, and in particular relates to a design method for leakage rate of a sealed cabin of a manned spacecraft. Background technique [0002] The airtight cabin of a manned spacecraft is the place where astronauts live and work in orbit. Specifically, during the manned period, the sealed cabin of the manned spacecraft should provide a suitable pressure environment for the astronauts to survive on orbit, and during the unmanned period, the cabin of the sealed cabin should also ensure an appropriate pressure to meet the normal pressure of the ventilation and cooling system. running requirements. Therefore, the cabin of the manned spacecraft should have good sealing performance. [0003] The system leak rate is an important index to identify the sealing performance of the sealing system. If the leakage rate index is too large, it will cause a large amount of gas leakage, resulting in a waste o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
Inventor 李兴乾魏传锋张伟吴冰李喆
Owner BEIJING SPACE TECH RES & TEST CENT
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