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A Regenerative Rocket Conformal Antenna Configuration

A conformal antenna and thermal storage technology, which is applied in the direction of weapon types, offensive equipment, projectiles, etc., can solve the problems of harsh thermal environment of the antenna, achieve the effects of reducing the volume and contact area, simplifying the processing, and suppressing the effect of heat conduction

Active Publication Date: 2018-11-30
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The technical problem to be solved by the present invention is to provide a rocket conformal antenna configuration suitable for long-term high-temperature flight environment to solve the problem of severe thermal environment experienced by the antenna.

Method used

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  • A Regenerative Rocket Conformal Antenna Configuration
  • A Regenerative Rocket Conformal Antenna Configuration
  • A Regenerative Rocket Conformal Antenna Configuration

Examples

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Embodiment Construction

[0034] Below in conjunction with accompanying drawing and embodiment a kind of that the present invention provides is introduced:

[0035] A regenerative rocket conformal antenna configuration, including a base 1, a microstrip plate 2, a cover plate 3, an outer surface 4, a mounting surface 5, an inner surface 6, mounting screw holes 8, sockets 9, and a thermal storage module 10. Gasket 11, first back-shaped groove 12, second back-shaped groove 13, third back-shaped groove 14, negative tolerance forming gap 15 and microstrip board and base mounting surface 20, wherein The base 1 and the cover plate 3 are fixed by the screws passing through the mounting screw holes 8. The periphery of the mounting screw holes 8 is provided with gaskets 11, and the microstrip board 2 is located at the center of the cover plate 3. The microstrip board 2 There is a negative tolerance gap 15 between the cover plate 3 and a heat storage module 10 on the microstrip plate 2. The inner ring of the heat...

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PUM

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Abstract

The invention belongs to the technical field of rocket conformal antenna structures, and provides a heat-storage type rocket conformal antenna structure applicable to flight in the hot environment for a long time. The problem that the antenna suffers from heat is solved. The heat-storage type rocket conformal antenna comprises a base (1), a microstrip plate (2), a cover plate (3), an outer surface (4), a mounting surface (5), an inner surface (6), a mounting screw hole (8), an insert (9), a heat storage module (10), a gasket (11), a first square groove (12), a second square groove (13), a third square groove (14), a negative allowance formation gap (15), a conical opening (19), and a microstrip plate and base mounting surface (20), wherein the base (1) and the cover plate (3) are fixedly mounted through a screw penetrating the mounting screw hole (8), the gasket (11) is arranged on the periphery of the screw hole (8), the microstrip plate (2) is arranged at the center of the cover plate (3), and the negative allowance formation gap (15) is arranged between the microstrip plate (2) and the cover plate (3).

Description

technical field [0001] The invention belongs to the technical field of conformal antenna configurations for rockets, and in particular relates to a conformal antenna configuration and a design method for heat storage type rockets. Background technique [0002] Due to the limited internal space of the rocket, various microwave communication antennas on the rocket are generally installed conformally with the curved surface of the metal rocket body, and have the characteristics of low profile. They generally include three parts: the base, the microstrip board, and the cover plate, and the total height does not exceed 20mm. configured as figure 1 shown. The supersonic cruise rocket is subjected to a severe aerodynamic heating environment during the long-term flight, and the antenna is also subjected to the following severe thermal environment: [0003] 1) The outer surface is directly subjected to pneumatic heating; [0004] 2) The installation contact surface is affected by ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/00
Inventor 盛江李静王振峰刘波张丽娜马伟石蕊马鸣吴宗霖
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST