CN218456150U

CN218456150U - Mobile unfolding type synthetic aperture radar satellite antenna unfolding structure

Info

Publication number: CN218456150U
Application number: CN202222653776.6U
Authority: CN
Inventors: 丁强强; 廖祥; 张汉城; 李钦儒; 梁晓华
Original assignee: Shenzhen Magic Cube Satellite Technology Co ltd
Current assignee: Shenzhen Magic Cube Satellite Technology Co ltd
Priority date: 2022-10-10
Filing date: 2022-10-10
Publication date: 2023-02-07
Anticipated expiration: 2032-10-10

Abstract

The utility model relates to a satellite-borne synthetic aperture radar technical field specifically is a remove formula of stretching synthetic aperture radar satellite antenna expansion structure of relaxing, including celestial body, gas receiver and phased array antenna, the bottom both sides terminal surface symmetry of celestial body is equipped with the holding tank, and both ends all symmetry are equipped with the card post around each holding tank is inside, and card post bottom one side is equipped with elastic buckle, and the inside top of holding tank all is equipped with the gas receiver, and the bottom of gas receiver is equipped with the pressure valve port, and the all mobilizable phased array antenna that is equipped with in the holding tank, phased array antenna lie in under the gas receiver, and phased array antenna wholly is flexible memory material; the utility model discloses utilize gaseous thrust to launch phased array antenna earlier after the star then expand for the area of envelope of antenna is littleer, and expansion efficiency is higher.

Description

Mobile unfolding structure of synthetic aperture radar satellite antenna

Technical Field

The utility model relates to a satellite-borne synthetic aperture radar technical field, concretely relates to remove formula synthetic aperture radar satellite antenna expansion structure of relaxing.

Background

A satellite-borne Synthetic Aperture Radar (SAR) satellite is a modern radar satellite capable of acquiring high information of a ground target all day long and all weather, the SAR satellite mainly comprises a satellite body, a solar cell wing, a radar antenna and the like, the radar antenna is the largest part of the effective volume in the whole satellite, the existing SAR satellite antenna is usually folded outside the satellite body when being stored and folded, the folding mode causes the envelope area of the outer side of the satellite body to be larger, the satellite transmitting cost is high, the traditional antenna is mostly unfolded from the inner side or the outer side of the satellite body by depending on the elasticity of the antenna, and the unfolding mode can generate the unfolding faults such as jamming and the like.

SUMMERY OF THE UTILITY MODEL

Therefore, the utility model discloses it is made in view of above problem, the utility model discloses an aim at is through taking in phased array antenna range upon range of in the celestial body bottom to set up the great elasticity buckle of rigidity, utilize gaseous thrust to carry out the expansion and the fixing of antenna, make the envelope area of antenna littleer, it is fixed more firm, it is big to take in envelope area with the radar antenna who solves existence among the prior art, the fixed unstable problem, the utility model discloses a realize above-mentioned purpose through following technical scheme:

the utility model provides a remove formula of relaxing synthetic aperture radar satellite antenna expansion structure, includes the star, air receiver and phased array antenna, the bottom both sides terminal surface symmetry of star is equipped with the holding tank, and the equal symmetry in both ends is equipped with the card post around every holding tank is inside, and card post bottom one side is equipped with the elasticity buckle, and the inside top of holding tank all is equipped with the air receiver, and the bottom of air receiver is equipped with the pressure valve port, and equal mobilizable phased array antenna that is equipped with in the holding tank, phased array antenna are located the air receiver under, and the phased array antenna is whole to be flexible memory material.

Preferably, phased array antenna's one end fixed mounting has the limiting plate, and the limiting plate is rigidity platelike structure, and the shape size of limiting plate and holding groove looks adaptation, the limiting plate is located the gas receiver under.

Preferably, the both ends on the limiting plate length direction are equipped with the draw-in groove with calorie post looks adaptation, and the draw-in groove at phased array antenna accessible limiting plate both ends cooperates with the card post at holding tank both ends.

Preferably, the elastic buckle is of a V-shaped structure, a V-shaped bayonet of the elastic buckle is downward, one end of the elastic buckle is embedded in the clamping column, and the other end of the elastic buckle is an elastic free end.

Preferably, the inside both sides bottom of holding tank just is located the equal fixed mounting of card post bottom and has the limiting plate.

Preferably, the air storage chamber is of a rigid shell structure, and air with certain pressure is filled in the air storage chamber.

Preferably, the outer contour of the star body is square.

The utility model discloses beneficial effect:

1. the phased array antenna is stacked and stored at the bottom of the star body, and the gas storage chamber is arranged to push the phased array antenna out of the star body by using gas thrust and then expand the phased array antenna, so that the antenna has the advantages of smaller envelope area, higher expansion efficiency and smaller risk of expansion failure;

2. through setting up the great elasticity buckle of rigidity, utilize the high-pressure gas in the gas storage chamber to push the limiting plate on the phased array antenna into elasticity buckle lower extreme by force for radar antenna's fixed more stable.

Drawings

Fig. 1 is a schematic view of the folded state of the present invention.

Fig. 2 is the half-section schematic diagram of the folded state structure of the present invention.

Fig. 3 is a schematic view of the present invention showing a part of the structure.

Fig. 4 is a schematic view of the expanded state of the present invention.

Fig. 5 is a half-section schematic view of the structure in the unfolded state of the present invention.

Fig. 6 is an enlarged schematic view of a part of the structure in the unfolded state of the present invention.

Description of reference numerals:

100. a star body; 110. accommodating grooves; 120. clamping the column; 130. elastic buckle; 140. a limiting plate; 200. an air storage chamber; 210. a pressure valve port; 300. a phased array antenna; 310. a limiting plate; 311. a clamping groove.

Detailed Description

The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, however, the present invention can be implemented in various forms, and therefore, the present invention is not limited to the embodiments described hereinafter, and in addition, in order to describe the present invention more clearly, components which are not connected to the present invention will be omitted from the drawings;

as shown in fig. 1 and 2, a mobile flexible synthetic aperture radar satellite antenna deployment structure includes: the star body 100, the gas storage chamber 200 and the phased array antenna 300;

as shown in fig. 2 and 3, the outer contour of the star body 100 is square, two receiving grooves 110 are symmetrically arranged on the bottom end surface of the star body 100, two clamping columns 120 are symmetrically arranged on the front and rear end surfaces of the receiving grooves 110, an elastic buckle 130 is arranged at a position of each clamping column 120 close to the bottom end for a distance, the elastic buckle 130 is of a V-shaped structure, V-shaped bayonets of the elastic buckle 130 are downward, one end of the elastic buckle 130 is embedded in the clamping column 120, the other end of the elastic buckle is an elastic free end, a limiting plate 140 is fixedly arranged at the front and rear bottom ends of the receiving groove 110 and at the bottom end of the clamping column 120, the number of the air storage chambers 200 is two, the air storage chambers 200 are fixedly arranged at the top ends of the two receiving grooves 110, the air storage chambers 200 are of a rigid housing structure, the air storage chambers 200 are filled with air at a certain pressure, the bottom ends of the air storage chambers 200 are further provided with a pressure valve port 210, and when the pressure difference between the pressure valve port 210 is greater than a certain value, the pressure valve port 210 is opened, so that the air in the air storage chambers 200 is ejected into the receiving grooves 110 through the pressure valve port 210;

phased array antenna 300 quantity is two, two phased array antennas 300 are mobilizable the installation respectively in two symmetrical arrangement's holding tank 110, phased array antenna 300 is whole to be flexible memory material, phased array antenna 300's one end fixed mounting has limiting plate 310, limiting plate 310 is the rigidity platelike structure, limiting plate 310's shape size is the same with the shape size of holding tank 110 of star 100 lower extreme, limiting plate 310 is located the air receiver 200 under, and both ends on limiting plate 310 length direction still are equipped with the draw-in groove 311 corresponding with the calorie post 120 on the holding tank 110 both ends face, draw-in groove 311 and the cooperation of the calorie post 120 at holding tank 110 both ends at phased array antenna 300 accessible limiting plate 310 both ends, and mobilizable the installation is inside holding tank 110, when phased array antenna 300 is in fold condition, phased array antenna 300's free end can be laminated each other, then imbed in the holding tank 110 of star 100 bottom.

The utility model discloses the theory of operation:

when a satellite is launched, a shell is arranged outside the satellite body 100, the phased array antenna 300 is in a folded state, a fixed end limiting plate 310 on the phased array antenna 300 is located right below the air storage chamber 200, a free end of the phased array antenna 300 is stacked inside the accommodating tank 110, the folded state is shown in fig. 1 and 2, when the satellite is launched to a preset track to be unfolded, the shell on the outer side falls off, the pressure outside the air storage chamber 200 is instantly reduced, a pressure valve port 210 on the air storage chamber 200 reaches an opened pressure valve value, the pressure valve port 210 is automatically opened, then the gas in the air storage chamber 200 starts to be ejected to the upper portion of the limiting plate 310 through the pressure valve port 210, the limiting plate 310 starts to push the phased array antenna 300 to move downwards along the jamming column 120 after being subjected to the thrust of the gas, when the free end of the phased array antenna 300 moves out of the accommodating tank 110, the free end of the phased array antenna 300 starts to be unfolded in parallel under the memory elasticity of the material of the phased array antenna 300 until the limiting plate 310 on the phased array antenna 300 crosses the jamming column 120 and presses against the limiting plate 140, the phased array antenna 300 stops moving downwards, at the moment, the phased array antenna 300 is completely unfolded, the phased array antenna 300 is also fixed between the whole phased array antenna 300 and the phased array antenna 300 is unfolded and the phased array antenna 300 is unfolded and the phased array antenna 4 and is unfolded as shown in the whole phased array antenna 4.

Claims

1. The utility model provides a remove formula of stretching synthetic aperture radar satellite antenna that stretches out structure, includes star (100), gas receiver (200) and phased array antenna (300), its characterized in that: the bottom both sides terminal surface symmetry of star (100) is equipped with holding tank (110), the equal symmetry in both ends is equipped with card post (120) around every holding tank (110) is inside, card post (120) bottom one side is equipped with elasticity buckle (130), the inside top of holding tank (110) all is equipped with air receiver (200), the bottom of air receiver (200) is equipped with pressure valve port (210), all mobilizable phased array antenna (300) of being equipped with in holding tank (110), phased array antenna (300) are located air receiver (200) under, phased array antenna (300) wholly are flexible memory material.

2. A mobile, deployable structure for a synthetic aperture radar satellite antenna according to claim 1, wherein: phased array antenna's (300) one end fixed mounting has limiting plate (310), and limiting plate (310) are rigidity platelike structure, and the shape size and holding tank (110) looks adaptation of limiting plate (310), and limiting plate (310) are located air receiver (200) under.

3. A mobile, deployable structure for a synthetic aperture radar satellite antenna, according to claim 2, wherein: and clamping grooves (311) matched with the clamping columns (120) are formed at two ends of the limiting plate (310) in the length direction.

4. A mobile, deployable structure for a synthetic aperture radar satellite antenna according to claim 1, wherein: the elastic buckle (130) is of a V-shaped structure, a V-shaped bayonet of the elastic buckle (130) faces downwards, one end of the elastic buckle (130) is embedded in the clamping column (120), and the other end of the elastic buckle is an elastic free end.

5. A mobile, deployable structure for a synthetic aperture radar satellite antenna according to claim 1, wherein: the inside both sides bottom of holding tank (110) just is located the equal fixed mounting of card post (120) bottom and has limiting plate (310).

6. A mobile, deployable structure for a synthetic aperture radar satellite antenna according to claim 1, wherein: the air storage chamber (200) is of a rigid shell structure, and air with certain pressure is filled in the air storage chamber (200).

7. A mobile, deployable structure for a synthetic aperture radar satellite antenna according to claim 1, wherein: the outer contour of the star body (100) is square.