Installation method of spacecraft high temperature heat shield
An installation method and technology of heat shields, which are applied in spaceflight vehicle heat protection devices, aerospace safety/emergency devices, etc., can solve problems such as increasing the weight of stars, and achieve less additional structures and supporting parts, enhanced strength, and tight installation Effect
Active Publication Date: 2017-03-15
SHANGHAI INST OF SATELLITE EQUIP
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Problems solved by technology
[0004] At present, the installation of high-temperature heat shields of domestic high-thrust engines mostly adopts integrated mounting brackets, such as Chang'e orbiter, etc. The integrated mounting brackets can increase the installation strength of the heat shield and simplify the installation process, but large-scale mounting brackets will inevitably increase the number of stars. Weight, excessive weight gain obviously outweighs the gain, which requires a reasonable increase in the necessary structural and supporting components to achieve the intended installation target
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[0023] In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will describe in detail with reference to the drawings and specific embodiments.
[0024] Such as Figure 1-3 As shown, the embodiment of the present invention provides a method for installing a spacecraft high-temperature heat shield, including the following steps:
[0025] S1. On the basis of the original 6 groups of 12 M5 threaded holes on the inner wall of the load-bearing cylinder, use 420 structural glue to evenly paste six 20mm×20mm threaded holes along the inner wall of the bearing cylinder in the middle of each two sets of threaded holes. Small pads, the described pads with screw holes are small pads of about 20mm×20mm×20mm, and each pad center has a screw hole of M5;
[0026] S2. Process 12 carbon fiber struts according to the relevant dimensions of the actual object. The 12 struts are made of aluminum alloy or titanium allo...
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The invention discloses a method for mounting a high-temperature heat shield of a spacecraft. A high-temperature heat shield body and an engine flange, as well as the high-temperature heat shield body and the wall surface of a bearing cylinder, are tightly mounted through the interface mounting method. The strength of the high-temperature heat shield body is enhanced by the body support method, the high-temperature heat shield body is supported between an engine and the bearing cylinder, auxiliary structures and support components are less, and tight installation is realized.
Description
technical field [0001] The invention relates to the technical field of installation and design of thermal control products for spacecraft, in particular to a method for installing a high-temperature heat shield of a spacecraft. Background technique [0002] Today's spacecraft field has entered a period of rapid development. Due to the increasing requirements of customers for satellite functions, the payload has gradually increased, and the satellite platform has expanded accordingly. The thrust of the engine is gradually increasing, and the high temperature shielding and heat dissipation of the engine are problems that must be solved. High-temperature heat shields made of high-temperature materials are increasingly used for heat insulation of high-thrust engines. The high-temperature heat shields usually have a large area, and the interface reserved for the thermal control subsystem near the engine is very limited. For the sake of reducing the weight of the entire star, add...
Claims
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IPC IPC(8): B64G1/58
Inventor 庞乐史以敏代善良
Owner SHANGHAI INST OF SATELLITE EQUIP