Recoverable airship heat-proof and bearing integrated structure

A returnable spaceship and load-bearing structure technology, which is applied in the fields of aerospace vehicle heat protection devices, aircraft, chemical instruments and methods, can solve the problem that the heat-proof material of the spaceship return cabin does not have the load-bearing function, and achieves a wide range of sizes and structures. multi-type effect

CN109927943AActive Publication Date: 2019-06-25BEIJING SATELLITE MFG FACTORY
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Publication Date
2019-06-25

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Abstract

The invention discloses a recoverable airship heat-proof and bearing integrated structure. The structure comprises a heat-proof layer, a bonding layer and a bearing structure, the heat-proof layer isconnected with the bearing structure through the bonding layer, connecting holes are formed in the bearing structure, and threaded holes corresponding to the connecting holes are formed in the heat-proof layer; screws penetrate through the connecting holes and the threaded holes in sequence to make the heat-proof layer connected with the bearing structure; the bearing structure is connected with an inner cabin structure and is used for being connected with internal instrument equipment. According to the structure, the heat-proof performance and the bearing performance are achieved, and the function of being detachable and reusable is achieved.
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Description

technical field

[0001] The invention belongs to the technical field of thermal protection systems for returnable spacecraft at the second cosmic speed, and in particular relates to an integrated structure of heat protection and load bearing for returnable spacecraft. Background technique

[0002] The reentry spacecraft re-enters the flight process at the second spaceflight speed, most of the kinetic energy is converted into heat energy of the air, and these heat energy forms a very high aerodynamic heating environment on the surface of the spacecraft in the form of boundary layer convection and shock wave radiation. The outer surface of the spacecraft There must be a reliable, erosion-resistant thermal protection system to protect the life safety of astronauts and the equipment inside the spacecraft. The structural stability and integrity of the heat-resistant material on the surface have higher requirements. At the same time, the heat-resistant layer is connected with the i...

Examples

preparation example Construction

[0032] This embodiment also provides a method for preparing a heat-proof and load-bearing integrated structure of a returnable spacecraft, the method including the following steps:

[0033] (1) Select the raw material of the heat-resistant layer according to the target performance and size of the product (the raw material of the heat-resistant layer can be selected as coating material, non-ablative heat-resistant material or ablative heat-resistant material).

[0034] (2) Prepare the blank of the heat-proof layer according to the raw materials of the heat-proof layer.

[0035] (3) Machining and processing the blank of the heat-proof layer to obtain the inner surface of the heat-proof layer.

[0036] (4) Select the raw material of the load-bearing structure according to the target performance and size of the product.

[0037] (5) Prepare the load-bearing structure.

[0038] (6) The heat-proof layer in step (3) and the load-bearing structure in step (5) are glued together as a...