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Space-borne complex radar antenna high-rigidity biased-type fixed direction pointing mechanism

A radar antenna and pointing mechanism technology, applied to antennas, antenna parts, antennas suitable for movable objects, etc., can solve problems such as inability to meet the development needs of spacecraft, large vibration response in the transmitting section, and difficulty in pressing and installing , to achieve the effect of increasing the rigidity, improving the mechanical bearing capacity, and reducing the number of pressing points

Active Publication Date: 2017-10-10
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] With the continuous increase of radar antenna caliber and the complex development of structure, after the radar antenna is installed with a traditional pointing machine, there are problems such as large envelope size, large vibration response in the transmitting section, difficult installation and long installation period, which cannot meet the needs of modern spacecraft. development needs

Method used

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  • Space-borne complex radar antenna high-rigidity biased-type fixed direction pointing mechanism
  • Space-borne complex radar antenna high-rigidity biased-type fixed direction pointing mechanism
  • Space-borne complex radar antenna high-rigidity biased-type fixed direction pointing mechanism

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Embodiment Construction

[0020] The present invention is described in detail below in conjunction with accompanying drawing: Illustration:

[0021] 1—Active deployment locking mechanism, 2—Extending arm, 3—Two-dimensional servo mechanism, 4—Clamping release mechanism, 5—Floating bracket, 6—Satellite mounting plate, 7—Radar antenna, 301—Drive joint, 401— Compression cup, 402—support component, 403—compression rod, 404—compression headgear, 405—vibration reduction headgear, 701—carbon fiber reinforcement, 702—rigid beam, 703—antenna flange

[0022] The present invention provides a high-rigidity offset fixed pointing mechanism for space-borne complex radar antennas, which is characterized in that the mechanism includes: an active deployment locking mechanism 1, an extension arm 2, a two-dimensional servo mechanism 3, and a compression release mechanism 4 And the floating bracket 5; the compression release mechanism 4 includes: a compression cup 401, a support assembly 402, a compression rod 403, a compre...

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Abstract

The invention discloses a space-borne complex radar antenna high-rigidity biased-type fixed direction pointing mechanism, comprising: an active unfolding locking mechanism, an extension arm, a two-dimensional servo mechanism, a pressing releasing mechanism, and a floating bracket. The pressing releasing mechanism comprises a pressing cup, a supporting component, a pressing rod, a pressing head cover and a vibration damping head cover. The invention provides an effective solution for the installing and fixing of a space-borne complex radar antenna and the tracking and positioning of an in-orbit target. The mechanism has the advantages of small size in envelope, high rigidity in structure and convenience in installation.

Description

technical field [0001] The invention relates to the field of aerospace electromechanical technology, in particular to a high-rigidity offset fixed pointing mechanism for a space-borne complex radar antenna. technical background [0002] One of the core components of the antenna pointing mechanism radar system is the actuator for the radar antenna to track and orient the target. With the continuous expansion of the radar functions of modern spacecraft, the radar antenna has developed from a flat plate antenna with a diameter of less than half a meter to a parabolic antenna with a diameter of more than 2 meters. Therefore, the radar antenna is folded and pressed tightly on the side of the satellite to meet the requirements of the envelope and mechanical conditions during the satellite launch phase. After entering orbit, it is lifted to a position away from the side plate of the satellite and then the target is tracked and positioned. [0003] With the continuous increase of r...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01Q1/28H01Q3/02
CPCH01Q1/288H01Q3/02
Inventor 赵明宣陈占胜杨金平崔琦峰钱志源王学强李源黄庆平
Owner SHANGHAI AEROSPACE SYST ENG INST
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