Split type small-sized manned lunar surface lander sealed cabin

A split-type, lander technology, applied in the direction of aircraft, aerospace vehicles, aerospace equipment, etc., can solve the problems of increased complexity in the implementation process of launch vehicle aircraft system specifications and tasks, and achieve reduced overall weight and light weight , the effect of wide observation field of view

Active Publication Date: 2018-10-12
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

[0002] Lunar exploration has always been a hot spot in the research and development of space technology around the world. Recently, it has been demonstrated that the number of people and the number of stays in lunar exploration missions have increased in different ways. The overall improvement of mission objectives will make the launch vehicle capability, aircraft system specifications and mission implementation process more complicated. A significant increase

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  • Split type small-sized manned lunar surface lander sealed cabin
  • Split type small-sized manned lunar surface lander sealed cabin
  • Split type small-sized manned lunar surface lander sealed cabin

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Embodiment Construction

[0027] The description of the embodiments in this specification should be combined with the corresponding drawings, and the drawings should be regarded as a part of the complete specification. In the drawings, the shapes or thicknesses of the embodiments may be exaggerated and marked for simplification or convenience. Furthermore, parts of each structure in the drawings will be described separately. It should be noted that elements not shown in the drawings or described in words are forms known to those of ordinary skill in the art.

[0028] The descriptions of the embodiments here, any references to directions and orientations are just for convenience of description, and should not be construed as any limitation to the protection scope of the present invention. The following descriptions of the preferred embodiments involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodime...

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Abstract

The invention relates to a split type small-sized manned lunar surface lander sealed cabin. The split type small-sized manned lunar surface lander sealed cabin comprises a docking mechanism, a passage, a main cabin body and a side scuttle, wherein the docking mechanism, the passage and the main cabin body are connected with each other in sequence; the side scuttle is supported on the main cabin body; the side scuttle comprises a first side scuttle part and a second side scuttle part; the first side scuttle part can be opened in a direction far away from the second side scuttle part; and the second side scuttle part can be opened in a direction far away from the first side scuttle part. According to the split type small-sized manned lunar surface lander sealed cabin, as the side scuttle comprises the first side scuttle part and the second side scuttle part which can oppositely opened, the side scuttle can also be used as a sealed cabin door; and therefore, the floor space of the sealedcabin door in the prior art is saved, the structure of the sealed cabin is made more compact and the light of the sealed cabin is made much lighter.

Description

technical field [0001] The invention relates to the technical field of manned space exploration aircraft systems, in particular to a split type small-sized manned lunar lander airtight cabin. Background technique [0002] Lunar exploration has always been a hot spot in the research and development of space technology around the world. Recently, it has been demonstrated that the number of people and the number of stays in lunar exploration missions have increased in different ways. The overall improvement of mission objectives will make the launch vehicle capability, aircraft system specifications and mission implementation process more complicated. A significant increase. If you consider the mission requirements based on a deep-space orbital space station or a manned moon base, as well as the mission goal of launching multiple repeated moon landings in one launch. With the help of the on-orbit system, the task scale of manned lunar landing and take-off can be flexibly share...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/22
CPCB64G1/22
Inventor 孙兴亮梁鲁田林王平黄震杨雷
Owner BEIJING SPACE TECH RES & TEST CENT
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