阅读说明：本技术 一种民用超远程卫星雷达系统及设备 (Civil ultra-long-range satellite radar system and equipment ) 是由 吴清萍 于 2021-07-07 设计创作，主要内容包括：本发明涉及卫星雷达设备技术领域,具体为一种民用超远程卫星雷达系统及设备,第一步,在卫星主体外侧的太阳能板上设置有钻石板；第二步,太阳能板通过连接杆与卫星主体相连接；第三步,太阳能板上设置有对钻石板进行限位约束的金属边框；第四步,太阳能板上设置有覆盖在钻石板外侧的透明薄膜,通过太阳能板外侧设置有约束钻石板的金属边框,太阳能板上端对应钻石板的外侧设置有透明薄膜,则能保证太阳光与太阳能板内部发电硅板接触,的同时当太空垃圾撞击到太阳能板时,能利用钻石板的硬度避免太阳能板被直接击穿的同时,能利用钻石板的脆性使其碎裂吸收动能,并且通过使用金属边框与透明薄膜,能避免钻石板在碎裂后向外飘散。(The invention relates to the technical field of satellite radar equipment, in particular to a civil ultra-long range satellite radar system and equipment, wherein in the first step, a diamond plate is arranged on a solar panel on the outer side of a satellite main body; secondly, the solar panel is connected with the satellite main body through a connecting rod; thirdly, a metal frame for limiting and constraining the diamond plate is arranged on the solar panel; the fourth step, be provided with the transparent film that covers in the diamond plate outside on the solar panel, be provided with the metal frame of restraint diamond plate through the solar panel outside, the outside that the solar panel upper end corresponds diamond plate is provided with transparent film, then can guarantee sunlight and the inside electricity generation silicon slab contact of solar panel, when space rubbish strikes solar panel, when can utilize diamond plate's hardness to avoid solar panel by direct puncture, can utilize diamond plate's fragility to make its cracked absorption kinetic energy, and through using metal frame and transparent film, can avoid diamond plate outwards to fly away after cracked.)

1. A civil ultra-long range satellite radar system comprises the following steps:

firstly, a diamond plate (15) is arranged on a solar panel (3) on the outer side of a satellite main body (2);

secondly, the solar panel (3) is connected with the satellite main body (2) through a connecting rod (16);

thirdly, a metal frame for limiting and constraining the diamond plate (15) is arranged on the solar panel (3);

fourthly, a transparent film covering the outer side of the diamond plate (15) is arranged on the solar panel (3);

fifthly, an anti-tilting platform (5) is arranged on the outer side of the lower end of the radar base (4) at the lower end of the radar receiving equipment main body (1).

2. A civil ultra-long range satellite radar device, characterized by: radar receiving equipment (1) is connected with satellite main part (2) utilization electromagnetic wave, install inside solar panel (3) that set up diamond plate (15) on satellite main part (2), still including connecting rod (16) that can drive solar panel (3) rotation on satellite main part (2), radar base (4) the outside of radar receiving equipment (1) lower extreme is provided with prevents inclining platform (5), prevents inclining platform (5) inside and has offered and to let radar base (4) to the cavity of multi-direction slope, prevents inclining platform (5) inside still is provided with prizing of convertible radar base (4) slope effort direction and moves and joins in marriage dull and stereotyped (9), prevent inclining platform (5) low side is provided with bearing ball (11).

3. A civil ultra-long range satellite radar apparatus as claimed in claim 2, wherein: the radar base (4) is internally provided with a stabilizing frame (6), and the inner wall of the anti-tilting platform (5) is connected with a limiting plate (7).

4. A civil ultra-long range satellite radar apparatus as claimed in claim 3, wherein: the stabilizing frame (6) is internally provided with a reinforcing rod (8) with one end penetrating into the inner wall of the anti-tilting platform (5), and the stabilizing frame (6) is internally provided with a trigger block (14).

5. A civil ultra-long range satellite radar apparatus as claimed in claim 2, wherein: a convex block (12) is arranged inside the radar base (4), and inner grooves (13) are formed in two sides of the corresponding convex block (12).

6. A civil ultra-long range satellite radar apparatus as claimed in claim 2, wherein: the prying matching flat plate (9) is arranged in an arc shape.

7. A civil ultra-long range satellite radar apparatus as claimed in claim 2, wherein: and a transparent film is arranged on the outer side of the diamond plate (15).

8. A civil ultra-long range satellite radar apparatus as claimed in claim 2, wherein: a clamping block (17) is arranged in the connecting rod (16).

Technical Field

The invention relates to the technical field of satellite radar equipment, in particular to a civil ultra-long range satellite radar system and equipment.

Background

With the development of human science and technology, satellites are widely applied to civilian use and play an increasingly important role in daily life navigation, and existing intelligent automobiles, intelligent mobile phones and navigation cargo ships need the satellites to conduct navigation and information transfer.

However, the existing civil satellite and satellite receiving equipment lack a protection structure under specific conditions, so that when a solar panel on the satellite is impacted by space rubbish or earthquakes and landslides occur to cause the ground where the radar receiving equipment is placed to incline, the satellite system can be immediately in a paralysis damage state, and the anti-strike capability of the satellite system is reduced.

Disclosure of Invention

A civil ultra-long range satellite radar system and equipment are provided to solve the above problems.

A civil ultra-long range satellite radar device comprises a radar receiving device main body and a satellite main body, wherein the radar receiving device main body is connected with the satellite main body through electromagnetic waves, a radar base is arranged at the lower end of the radar receiving device main body, an anti-tilting platform is installed on the lower outer side of the radar base, a stabilizing frame is arranged at the middle end inside the anti-tilting platform, a limiting plate is arranged on the inner side of the anti-tilting platform and corresponds to the outer side of the stabilizing frame, a reinforcing rod is arranged inside the stabilizing frame, a trigger block is further arranged inside the stabilizing frame, a prying matching plate is installed inside the anti-tilting platform and corresponds to the outer side of the radar base, a fixing rod penetrating through the prying matching plate is arranged on the prying matching plate, a bearing ball contacting with the radar base is arranged at the bottom of the anti-tilting platform, convex blocks are arranged on two sides corresponding to the stabilizing frame inside the radar base, inner grooves are formed in two sides of the opposite convex blocks inside the radar base, solar panel is installed in the satellite main part outside, solar panel passes through the connecting rod and is connected with the satellite main part, the solar panel outside is provided with the diamond plate.

Preferably, the stabilizing frame is arranged inside the radar base and has a cross-shaped structure.

Preferably, one end of the reinforcing rod penetrates out of the inner wall of the anti-tilting platform and enters the stabilizing frame, one end of the reinforcing rod is arranged in an arrow shape with two inclined sides, and the lower end of the trigger block is attached to the inclined surface of the reinforcing rod.

Preferably, the bump corresponds to the trigger block, and the trigger block is provided with a concave part attached to the bump.

Preferably, the inner side of the limit plate is provided with an arc-shaped groove.

Preferably, the prying matching plate is arranged in a semi-cylindrical shape.

Preferably, a metal frame for restraining the diamond plate is arranged on the outer side of the solar panel, and a transparent film is arranged on the upper end of the solar panel corresponding to the outer side of the diamond plate.

Preferably, one end of the connecting rod is arranged inside the solar panel, and a clamping block is arranged on the outer side of the connecting rod.

A civil ultra-long range satellite radar system comprises the following steps:

firstly, arranging a diamond plate on a solar panel outside a satellite main body;

secondly, the solar panel is connected with the satellite main body through a connecting rod;

thirdly, a metal frame for limiting and constraining the diamond plate is arranged on the solar panel;

fourthly, a transparent film covering the outer side of the diamond plate is arranged on the solar panel;

and fifthly, arranging an anti-tilting platform at the outer side of the lower end of the radar base at the lower end of the radar receiving equipment main body.

Compared with the prior art, the invention has the following beneficial effects:

1. the stabilizing frame is arranged in the radar base and is of a cross-shaped structure, the limiting plate is arranged on the inner side of the anti-tilting platform and corresponds to the outer side of the stabilizing frame, the reinforcing rod is arranged in the stabilizing frame, so that the radar base can be kept balanced and stable in the anti-tilting platform by using the stabilizing frame, the prying matching plate is arranged on the inner side of the anti-tilting platform and corresponds to the outer side of the radar base, the fixing rod penetrating through the prying matching plate is arranged on the prying matching plate, after the ground placed on the radar receiving equipment main body is tilted to cause the anti-tilting platform under the ground to tilt, the radar base can move to one side on the stabilizing frame, acting force is applied to the upper end of the prying matching plate on one side, the prying matching plate is semi-cylindrical, the prying matching plate can rotate by using the fixing rod as a circle center to apply upward force to the lower end of the radar base, and the tilting acting force direction of the radar base can be converted, the radar base keeps a balanced effect in an external inclined state, so that connection with a satellite main body is guaranteed, and the anti-strike capacity of a satellite system is improved.

2. Wear out the inside anti-tilt platform inner wall that gets into of steady rest through anchor strut one end, anchor strut one end is the arrow point form setting of both sides slope, and trigger the inclined plane of piece lower extreme and anchor strut and laminate mutually, the lug is corresponding with the trigger block, then when radar base is to the lopsidedness, just can stagger lug and trigger block, make the trigger block get into the inner groovy, remove the blockking to the anchor strut, make the anchor strut can get into inside the steady rest under the effect of spring completely, thereby remove the restriction to the steady rest on the line to reciprocating, let the radar base can drive the steady rest and rotate to one side, reach the effect that makes things convenient for radar base to slope trim to a plurality of directions.

3. The metal frame for restraining the diamond plate is arranged on the outer side of the solar panel, the transparent film is arranged on the upper end of the solar panel corresponding to the outer side of the diamond plate, so that the solar panel can be ensured to be contacted with the power generation silicon plate in the solar panel, when space garbage impacts the solar panel, the hardness of the diamond plate can be utilized to prevent the solar panel from being directly punctured, meanwhile, the diamond plate can be cracked to absorb kinetic energy by utilizing the brittleness of the diamond plate, the diamond plate can be prevented from floating outwards after being cracked by using the metal frame and the transparent film, the clamping block is arranged in the solar panel and on the outer side of the solar panel through one end of the connecting rod, the triangular groove is arranged on the outer side of the solar panel relative to the clamping block, the clamping block with the triangular obtuse angle can be embedded with the groove, the driving device in the satellite body can drive the solar panel to rotate, the power generation efficiency is ensured to be absorbed, and the kinetic energy transmitted after the solar panel is impacted can rapidly drive the clamping block to retract, the solar panel can rotate automatically under the impact force, the damage caused by impact kinetic energy is reduced, and the anti-impact capability of the satellite system is further improved.

Drawings

FIG. 1 is an overall perspective view of the present invention;

FIG. 2 is a top view of the anti-tip stand of the present invention;

FIG. 3 is a front perspective view of the anti-tip stand of the present invention;

FIG. 4 is an enlarged view taken at A of FIG. 3 according to the present invention;

FIG. 5 is a top perspective view of the anti-tip stand of the present invention;

FIG. 6 is a perspective view of a prying fit plate of the present invention;

FIG. 7 is a top view of a solar panel of the present invention;

FIG. 8 is a side perspective view of a solar panel of the present invention;

FIG. 9 is a left hand cross-sectional view of the connecting rod of the present invention.

In FIGS. 1-9: the method comprises the following steps of 1-radar receiving equipment main body, 2-satellite main body, 3-solar panel, 4-radar base, 5-anti-tilting platform, 6-stabilizing frame, 7-limiting plate, 8-reinforcing rod, 9-prying matching plate, 10-fixing rod, 11-bearing ball, 12-convex block, 13-inner groove, 14-triggering block, 15-diamond plate, 16-connecting rod and 17-clamping block.

Detailed Description

Referring to fig. 1 to 9, a schematic plan structure and a schematic perspective structure of a civil ultra-long range satellite radar system and a device thereof are shown.

Example one

A civil ultra-long range satellite radar device comprises a radar receiving device main body 1 and a satellite main body 2, wherein the radar receiving device main body 1 is connected with the satellite main body 2 through electromagnetic waves, a radar base 4 is arranged at the lower end of the radar receiving device main body 1, an anti-tilting platform 5 is arranged at the lower outer side of the radar base 4, a stabilizing frame 6 is arranged at the middle end inside the anti-tilting platform 5, a limiting plate 7 is arranged at the inner side of the anti-tilting platform 5 corresponding to the outer side of the stabilizing frame 6, a reinforcing rod 8 is arranged inside the stabilizing frame 6, a trigger block 14 is further arranged inside the stabilizing frame 6, a prying matching plate 9 is arranged inside the anti-tilting platform 5 corresponding to the outer side of the radar base 4, a fixing rod 10 penetrating through the prying matching plate 9 is arranged on the prying matching plate, a bearing ball 11 in contact with the radar base 4 is arranged at the bottom of the anti-tilting platform 5, and convex blocks 12 are arranged inside the radar base 4 corresponding to the two sides of the stabilizing frame 6, inner groovy 13 has been seted up to the both sides of the inside relative lug of radar base 4, and solar panel 3 is installed in the satellite main part 1 outside, and solar panel 3 is connected with satellite main part 1 through connecting rod 16, and the solar panel 3 outside is provided with diamond plate 15.

In the specific implementation, the stabilizing frame 6 is arranged inside the radar base 4 and has a cross-shaped structure, so that the radar base 4 can be kept balanced and stable in the anti-tilting platform 5 by using the stabilizing frame 6.

In the concrete implementation, 8 one end of anchor strut wears out the inside of steady rest 6 and gets into in 5 inner walls of preventing inclining, 8 one end of anchor strut is the arrow point form setting of both sides slope, and trigger 14 lower extreme and the inclined plane of anchor strut 8 and laminate mutually, lug 12 is corresponding with trigger block 14, and trigger block 14 is last for the indent setting with lug 12 laminating, then when radar base 4 when inclining to one side, just can stagger lug 12 and trigger block 14, make trigger block 14 get into in inner groovy 13, remove the blockking to anchor strut 8, make anchor strut 8 can get into inside steady rest 6 completely under the effect of spring, thereby remove the restriction to on-line steady rest 6 to reciprocating, let radar base 4 can drive steady rest 6 and rotate to one side, reach the effect that makes things convenient for radar base 4 seat to incline to many directions and trim.

In specific implementation, the inner side of the limiting plate 7 is provided with an arc-shaped groove, so that the stabilizing frame can conveniently move up and down at a limited position.

In specific implementation, the upper end of the anti-tilting platform 5 is provided with an elastic waterproof cloth, so that rainwater is prevented from entering the interior of the anti-tilting platform 5 in daily use.

In the concrete implementation, it sets up to prize to join in marriage dull and stereotyped 9 for the semicylindrical setting, make and take place to incline and lead to subaerial anti-tilt platform 5 to produce the slope back when the ground that radar receiving equipment main part 1 placed, will let radar base 4 remove to one side on steady rest 6, and then prize and join in marriage dull and stereotyped 9 upper end and apply the effort to one side, utilize to prize and join in marriage dull and stereotyped 9 semicylindrical setting, make it can use dead lever 10 to rotate as the centre of a circle and apply ascending power with radar base 4 lower extreme, thereby reach conversion radar base 4 slope effort direction, let radar base keep balanced effect under the state of outside slope.

In concrete implementation, the metal frame that solar panel 3 outside was provided with restraint diamond plate 15, the outside that solar panel 3 upper end corresponds diamond plate 15 is provided with transparent film, then can guarantee sunlight and the inside electricity generation silicon plate contact of solar panel 3, when space rubbish strikes solar panel 3, can utilize diamond plate 15's hardness to avoid solar panel 3 by the direct breakdown in the time, can utilize diamond plate 15's fragility to make its cracked absorption kinetic energy, and through using metal frame and transparent film, can avoid diamond plate outwards to drift about after cracked.

In concrete implementation, connecting rod 16 one end sets up and is provided with fixture block 17 in solar panel 3 inside and outside, make can utilize triangle obtuse angle shape's fixture block 17 and recess looks gomphosis, it is rotatory to let the drive arrangement in the satellite main part 2 can drive solar panel 3, when guaranteeing to absorb generating efficiency, kinetic energy that is transmitted after solar panel 3 is strikeed just can order about fixture block 17 internal contraction rapidly, let solar panel 3 rotatory by oneself under the impact, reduce the destruction that striking kinetic energy caused, further improve satellite system's anti-hitting ability.

The civil ultra-long range satellite radar system comprises the following steps:

firstly, a diamond plate 15 is arranged on the solar panel 3 outside the satellite main body 2;

secondly, the solar panel 3 is connected with the satellite main body 2 through a connecting rod 16;

thirdly, a metal frame for limiting and constraining the diamond plate 15 is arranged on the solar panel 3;

fourthly, a transparent film covering the outer side of the diamond plate 15 is arranged on the solar panel 3;

and fifthly, arranging an anti-tilting platform 5 on the outer side of the lower end of the radar base 4 at the lower end of the radar receiving device main body 1.

Example two

By using the diamond plate 15 on the solar panel 3, the diamond is made of the material with the highest heat conduction rate (138.16W/(m.K)), has super heat conductivity different from the electronic heat conduction of metal, is 25 times that of copper at the liquid nitrogen temperature and 5 times that of copper at the room temperature, has super heat conductivity, enables more solar radiation energy to be transmitted to the internal power generation silicon plate, improves the power generation efficiency of the solar panel, and has larger power generation effect as the solar energy is larger.

Meanwhile, the artificial synthetic diamond technology puts natural diamonds as seeds at 2300 ℃ and 15-18 thousands of high temperature and high pressure, high temperature metal liquid is arranged around the diamonds, and graphite is arranged on the upper layer, so that the atoms are arranged in sequence in the environment to move towards the diamonds, thereby forming new artificial synthetic diamonds.

The working principle of the civil ultra-long range satellite radar system and the equipment is as follows.

Firstly, a radar base 4 is placed in an anti-tilting platform 5, the anti-tilting platform 5 is placed under the ground and is arranged in the radar base 4 through a stabilizing frame 6, the anti-tilting platform 5 is of a cross-shaped structure, a limiting plate 7 is arranged on the inner side of the anti-tilting platform 5 corresponding to the outer side of the stabilizing frame 6, a reinforcing rod 8 is arranged in the stabilizing frame 6, the stabilizing frame 6 can be used for ensuring that the radar base 4 keeps balanced and stable in the anti-tilting platform 5, meanwhile, a prying matching plate 9 is arranged on the inner side of the anti-tilting platform 5 corresponding to the outer side of the radar base 4, a fixing rod 10 penetrating through the prying matching plate 9 is arranged on the prying matching plate 9, so that when the ground placed on a radar receiving equipment main body 1 is tilted to cause the anti-tilting platform 5 under the ground to tilt, the radar base 4 can move to one side on the stabilizing frame 6, acting force is applied to the upper end of the prying matching plate 9 on one side, and the semi-cylindrical setting of the prying matching plate 9 is utilized, so that the lower end of the radar base 4 can be rotated by taking the fixed rod 10 as a circle center to apply an upward force to the lower end of the radar base 4, thereby achieving the effect of converting the inclination acting force direction of the radar base 4, keeping the radar base balanced in an externally inclined state, ensuring the connection with the satellite main body 1 and improving the anti-strike capability of a satellite system, wherein one end of the reinforcing rod 8 penetrates through the inside of the stabilizing frame 6 to enter the inner wall of the anti-inclination platform 5, one end of the reinforcing rod 8 is arranged in an arrow shape with two inclined sides, the lower end of the trigger block 14 is attached to the inclined surface of the reinforcing rod 8, the convex block 12 corresponds to the trigger block 14, when the radar base 4 inclines to one side, the convex block 12 and the trigger block 14 can be staggered, so that the trigger block 14 enters the inner groove 13, the blocking of the reinforcing rod 8 is removed, the reinforcing rod 8 can completely enter the stabilizing frame 6 under the action of the spring, and the limitation of the upward and downward movement of the stabilizing frame 6 on one line is removed, the radar base 4 can drive the stabilizing frame 6 to rotate to one side, so that the effect of facilitating the inclined balancing of the radar base 4 to multiple directions is achieved, then a metal frame for restraining the diamond plate 15 is arranged on the outer side of the solar panel 3, a transparent film is arranged on the upper end of the solar panel 3 corresponding to the outer side of the diamond plate 15, so that the sunlight can be ensured to be contacted with a power generation silicon plate inside the solar panel 3, when space garbage impacts the solar panel 3, the hardness of the diamond plate 15 can be utilized to prevent the solar panel 3 from being directly punctured, meanwhile, the diamond plate 15 can be cracked to absorb kinetic energy by utilizing the brittleness of the diamond plate 15, the diamond plate can be prevented from flying outwards after being cracked by using the metal frame and the transparent film, a clamping block 17 is arranged inside the solar panel 3 and on the outer side of the clamping block through one end of a connecting rod 16, and a triangular groove is arranged on the outer side of the solar panel 3 corresponding to the clamping block 17, make and to utilize the obtuse angular fixture block 17 of triangle and recess looks gomphosis, let the drive arrangement in the satellite main part 2 can drive solar panel 3 rotatory, when guaranteeing to absorb generating efficiency, kinetic energy that is transmitted after solar panel 3 is strikeed just can order about rapidly fixture block 17 internal contraction, let solar panel 3 rotate by oneself under the impact, reduce the destruction that striking kinetic energy caused, further improve satellite system's anti-hitting ability.