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Return capsule and return satellite

A return capsule and cargo compartment technology, applied in the field of aerospace, can solve problems such as unfavorable satellite safe operation, unreasonable return capsule structure design, poor aerodynamic stability, etc., to meet static stability requirements, ensure stable safety, and good aerodynamic stability Effect

Pending Publication Date: 2020-09-18
北京航天方舟空间技术有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing returnable satellites have poor aerodynamic stability due to unreasonable structural design of the return capsule, which is not conducive to the safe operation of the satellite

Method used

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  • Return capsule and return satellite

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Embodiment Construction

[0043] Features and exemplary embodiments of various aspects of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by showing examples of the present invention. In the drawings and the following description, at least some well-known structures and techniques have not been shown in order to avoid unnecessarily obscuring the present invention; and, for clarity, the dimensions of some structures may have been exaggerated. Furthermore, the features, structures, or characteristics described hereinafter may be combined in any suitable manner in one or more embodiments.

[0044] The orient...

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Abstract

The invention relates to a return capsule and a return satellite. The return capsule comprises a capsule body which has a preset length and comprises a windward section and a tail skirt section whichare sequentially distributed in the length direction of the capsule body, a windward body that is arranged at one end of the capsule body in the length direction and is connected to the windward section, and a leeward body arranged at the other end, in the length direction, of the capsule body and connected with the tail skirt section. In the length direction, the leeward body and the windward body are oppositely arranged, and the orthographic projection area of the leeward body is larger than that of the windward body; the tail skirt section and the windward section are arranged in an intersecting mode, the windward body points to the leeward body in the length direction, and the cross section of the tail skirt section is gradually increased. According to the return capsule and the returnsatellite provided by the embodiment of the invention, the return capsule has better aerodynamic stability, and the safe operation of the return satellite can be ensured.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a return capsule and a return satellite. Background technique [0002] A returnable satellite refers to an artificial satellite that returns to the ground after completing its mission in orbit. Returnable satellites are mainly used to obtain various earth observation information, which can be brought back to the ground for analysis, processing and detailed research. All countries are vigorously researching and developing. The returnable satellite mainly includes the launch stage, the operation stage, and the re-entry return stage. The main task requirements of each stage are as follows: [0003] Launch stage: The satellite rocket is ready at the launch site, the carrier rocket sends the satellite into the predetermined orbit, the satellite and the carrier rocket are separated, and the satellite enters the orbit. [0004] Operation section: The time when the satellite and the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/22B64G1/62B64G1/58
CPCB64G1/22B64G1/58B64G1/62
Inventor 张刚孙愻梁栋吴涛贺国宏
Owner 北京航天方舟空间技术有限公司
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