A wearable thermal protection method for an aerospace servo mechanism

Abstract

The invention provides a bonding type wearable thermal protection method of an aerospace servo mechanism. The method comprises the steps: (1) performing thermal protection for the front segment and rear segment of the servo mechanism according to the product appearance and spatial layout of the aerospace servo mechanism; (2) designing thermal protective clothing; wherein, a structure B is used for thermal protection of the rear segment of the servo mechanism, and a structure A is used for thermal protection of the front segment of the servo mechanism; the structure A comprises a bypass valve thermal protection block, an electronic box thermal protection block, an actuating cylinder thermal protection block and a casing thermal protection block; the structure A and the structure B are made of thermal protection materials; the bypass valve thermal protection block, the electronic box thermal protection block, the casing thermal protection block and the structure B are of coated structure determined according to the minimum envelope of a part to be protected; the appearance of the actuating cylinder thermal protection block is matched with that of the actuating cylinder, and both ends of the actuating cylinder thermal protection block are of open structure; the contact parts between the casing thermal protection block and the bypass valve thermal protection block, the electronic box thermal protection block and the actuating cylinder thermal protection block are provided with windows of the corresponding shape; (3) installing the structure A and the structure B on the front segment and the rear segment of the servo mechanism.

Description

technical field [0001] The invention relates to a thermal protection scheme of a carrier rocket servo mechanism, in particular to a fit-type and wearable thermal protective clothing technology for a redundant valve-controlled servo mechanism used for thrust vector control of a carrier rocket liquid hydrogen and liquid oxygen engine. Background technique [0002] Servo mechanism is the collective name for the flight control actuators of launch vehicles in my country. The typical application is to implement thrust vector control of swing engines. The servo mechanism is located in the tail compartment of the rocket engine, and is subjected to the strong heat flow brought by the engine's ultra-high temperature tail flame. If no protective measures are taken, the surface temperature of the servo mechanism can reach up to 500°C, which is unbearable; [0003] The second-level servo mechanism of domestic launch vehicles in active service adopts a thermal protection scheme of hanging...

AI Technical Summary

Problems solved by technology

However, the servo mechanism involved in the present invention is used in a certain liquid hydrogen and liquid oxygen engine. Due to the limitation of the installation space layout of the servo mechanism, this solution cannot be adopted.

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