CN220420854U - Satellite - Google Patents

Abstract

The utility model belongs to the technical field of satellite communication, and discloses a satellite which comprises a satellite body, a measurement and control data transmission antenna group, a backup measurement and control data transmission antenna group and a VDES antenna. The measurement and control data transmission antenna group is arranged on the satellite body and used for sending and receiving measurement and control data. The backup measurement and control data transmission antenna group is arranged on the satellite body and serves as a backup of the measurement and control data transmission antenna group. Two ends of the satellite body along the first direction are provided with VDES antennas, and the VDES antennas can be folded and unfolded. According to the satellite, the VDES antenna can be folded in the satellite transmitting stage, so that the satellite volume is reduced, the transmitting cost is reduced, the transmitting efficiency is improved, and the VDES antenna can be unfolded in the satellite working stage, so that the VDES antenna gain is improved, and the communication quality is ensured. In addition, when the measurement and control data transmission antenna group fails, the service life of the satellite can be effectively prolonged by starting the backup measurement and control data transmission antenna group.

Description

Satellite

Technical Field

The utility model relates to the technical field of satellite communication, in particular to a satellite.

Background

The space-based internet of things system has the advantages of wide coverage area, capability of realizing global non-blind area communication, strong time-based system survivability, capability of still working normally under emergency conditions such as natural disasters, emergencies and the like, outstanding application advantages in the aspects of rescue and relief work and emergency guarantee, capability of quickly establishing a communication link and a command system for emergency rescue, capability of providing emergency communication guarantee service for individuals to go out and capability of building life protection wires for people in distress in outdoor exercises.

Because the space-based internet of things requires a large number of satellites, in order to reduce the transmission cost, the volume of the satellites needs to be reduced as much as possible, and the transmission efficiency needs to be improved, however, the internet of things satellites need to communicate with the ground and also need to communicate with other satellites, in order to ensure the communication quality, a VDES (vhf data exchange system, very high frequency data exchange system) antenna is required to have a large antenna gain, and the space-based internet of things satellites with a small volume are difficult to meet the gain requirement of the VDES antenna. In addition, the measurement and control data transmission antenna is a connection link between the space-based internet of things satellite and the ground measurement and control station, once the measurement and control data transmission antenna fails, the scrapping of the space-based internet of things satellite is often meant, and the service life of the existing measurement and control data transmission antenna is not enough, so that the service life of the space-based internet of things satellite is directly prolonged.

Therefore, a satellite is needed to solve the above problems.

Disclosure of Invention

The utility model aims to provide a satellite, which can improve the gain of a VDES antenna 4, ensure the communication quality and prolong the service life of the satellite.

To achieve the purpose, the utility model adopts the following technical scheme:

a satellite, comprising:

a satellite body;

the measurement and control data transmission antenna group is arranged on the satellite body;

the backup measurement and control data transmission antenna group is arranged on the satellite body and is used as a backup of the measurement and control data transmission antenna group;

and the VDES antenna is arranged at two ends of the satellite body along the first direction, and the VDES antenna can be folded and unfolded.

Preferably, the measurement and control data transmission antenna group comprises a first measurement and control data transmission antenna and a first measurement and control data transmission receiving antenna, wherein the first measurement and control data transmission antenna is used for transmitting measurement and control data, and the first measurement and control data transmission receiving antenna is used for receiving the measurement and control data;

the backup measurement and control data transmission antenna group comprises a second measurement and control data transmission antenna and a second measurement and control data transmission receiving antenna, wherein the second measurement and control data transmission antenna is used for transmitting measurement and control data, and the second measurement and control data transmission receiving antenna is used for receiving the measurement and control data.

Preferably, the satellite-rocket separator is arranged on one side of the satellite body along the first direction.

Preferably, the positioning device is fixedly arranged on the satellite body, a positioning hole is formed in the positioning device and is used for being matched with a positioning pin on the rocket to position the relative position of the satellite and the rocket.

Preferably, the solar energy satellite further comprises a solar sailboard, wherein the solar sailboard is arranged on the other side of the satellite body along the first direction.

Preferably, the VDES antenna includes:

a mounting base;

an arm assembly including a first arm, a second arm, and a third arm;

the hinge assembly comprises a first hinge, a second hinge and a third hinge, and one end of the first arm rod is hinged with the mounting seat through the first hinge; one end of the second arm rod is hinged with one end of the first arm rod, which is far away from the mounting seat, through a second hinge; one end of the third arm rod is hinged with one end of the second arm rod, which is far away from the second hinge, through a third hinge;

and the compression release assembly is used for folding the first arm rod, the second arm rod and the third arm rod to enable the first arm rod, the second arm rod and the third arm rod to be parallel to each other and then folded.

Preferably, the compression release assembly includes:

a compressing seat; the pressing cavity is arranged on the bottom surface of the third arm rod and is adapted to the third arm rod;

the supporting seat is arranged on the side surface of the pressing seat;

one end of the wrapping belt is detachably connected with the supporting seat;

the rope is connected with one end of the bag belt far away from the supporting seat;

a fuse disposed at the rope for fusing the rope;

the compressing piece is arranged on the side surface of the compressing seat, which is far away from the supporting seat, and is connected with the rope, and the compressing piece is used for fixing the rope;

the compression seat, the supporting seat, the wrapping belt, the rope and the compression piece are arranged around the arm rod assembly and enclose to form a folding cavity for folding the arm rod assembly.

Preferably, the first hinge, the second hinge, and the third hinge are flexible hinges.

Preferably, the satellite sensor further comprises a star sensor and a GNSS antenna, wherein the star sensor and the GNSS antenna are arranged on the satellite body.

Preferably, the satellite watch further comprises a star watch plug, wherein the star watch plug is arranged on the satellite body.

The utility model has the beneficial effects that:

according to the satellite, the VDES antenna can be folded and unfolded, so that the VDES antenna can be folded in the satellite transmitting stage, the satellite volume is reduced, the transmitting cost is reduced, the transmitting efficiency is improved, and the VDES antenna can be unfolded in the satellite working stage, so that the VDES antenna gain is improved, and the communication quality is ensured. And, both ends of satellite body along the first direction are provided with the VDES antenna, can further improve VDES antenna gain. In addition, by setting the backup measurement and control data transmission antenna group, the service life of the satellite can be effectively prolonged by starting the backup measurement and control data transmission antenna group when the measurement and control data transmission antenna group fails.

Drawings

FIG. 1 is a schematic view of a satellite according to an embodiment of the present utility model;

FIG. 2 is an exploded view of a satellite provided by an embodiment of the present utility model;

fig. 3 is a schematic structural diagram of a folded state of a VDES antenna of a satellite according to an embodiment of the present utility model;

fig. 4 is a schematic structural diagram II of a folded state of a VDES antenna of a satellite according to an embodiment of the present utility model;

FIG. 5 is a schematic view of a portion of a satellite according to an embodiment of the present utility model;

fig. 6 is a schematic diagram of a portion of a satellite according to an embodiment of the present utility model;

fig. 7 is a schematic diagram of a portion of a satellite according to an embodiment of the present utility model;

FIG. 8 is an exploded view of a portion of the structure of a satellite provided by an embodiment of the present utility model;

fig. 9 is an enlarged view at a in fig. 8;

fig. 10 is a schematic structural diagram of a satellite-rocket separator of a satellite according to an embodiment of the present utility model.

In the figure:

1. a satellite body; 11. a first connection base; 12. a second connecting seat; 13. ribs;

2. measuring and controlling the data transmission antenna group; 21. a first measurement and control data transmission antenna; 22. a first measurement and control data transmission receiving antenna;

3. backup measurement and control data transmission antenna groups; 31. the second measurement and control data transmission transmitting antenna; 32. a second measurement and control data transmission receiving antenna;

4. VDES antennas;

41. a mounting base; 42. an arm assembly; 421. a first arm; 422. a second arm; 423. a third arm; 43. a hinge assembly; 431. a first hinge; 432. a second hinge; 433. a third hinge; 44. a compression release assembly; 441. a compressing seat; 442. a support base; 443. a belting; 444. a fuse; 445. a pressing member;

5. a satellite-rocket separator; 51. a base; 52. a connecting piece;

6. a positioning device; 61. positioning holes;

7. a solar sailboard; 71. fixing a sailboard; 72. folding a sailboard;

8. a star sensor;

9. a GNSS antenna;

10. star plug.

Detailed Description

The utility model is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present utility model are shown in the drawings.

In the description of the present utility model, unless explicitly stated and limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.

In the present utility model, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.

In the description of the present embodiment, the terms "upper", "lower", "right", and the like are based on the orientation or positional relationship shown in the drawings, and are merely for convenience of description and simplicity of operation, and do not indicate or imply that the apparatus or element in question must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the utility model. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for distinguishing between them.

As shown in fig. 1-6, the present embodiment provides a satellite, which includes a satellite body 1, a measurement and control data antenna group 2, a backup measurement and control data antenna group 3 and a VDES antenna 4. The measurement and control data transmission antenna group 2 is arranged on the satellite body 1 and is used for sending and receiving measurement and control data. The backup measurement and control data transmission antenna group 3 is arranged on the satellite body 1, and the backup measurement and control data transmission antenna group 3 is used as a backup of the measurement and control data transmission antenna group 2. Both ends of the satellite body 1 along the first direction are provided with VDES antennas 4, and the VDES antennas 4 can be folded and unfolded. In this embodiment, the first direction is the length direction of the satellite. It should be noted that, the satellite in this embodiment is a space-based internet of things satellite.

The satellite provided by this embodiment, the VDES antenna 4 can be folded and unfolded, so that the VDES antenna 4 can be folded in the satellite transmitting stage, the satellite volume is reduced, the transmitting cost is reduced, the transmitting efficiency is improved, and the VDES antenna 4 can be unfolded in the satellite working stage, so that the gain of the VDES antenna 4 is improved, and the communication quality is ensured. In addition, the VDES antenna 4 is disposed at both ends of the satellite body 1 along the first direction, so that the gain of the VDES antenna 4 can be further improved. In addition, by setting the backup measurement and control data transmission antenna group 3, the service life of the satellite can be effectively prolonged by starting the backup measurement and control data transmission antenna group 3 when the measurement and control data transmission antenna group 2 fails.

Alternatively, as shown in fig. 1 to 10, the satellite body 1 has a square structure, so that when a plurality of satellites are launched in batches, occupied rocket space can be reduced, and the launching cost can be reduced.

Optionally, as shown in fig. 1 to 9, the casing of the satellite body 1 includes a plurality of plates, each plate is formed by processing an aluminum alloy, each plate is connected by using a fastener, a plurality of ribs 13 are arranged on the plate, and included angles are formed between the ribs 13, so that the rigidity of the satellite structural casing is improved, better mechanical properties are maintained, and the casing plays a role in protecting an internal system of a satellite.

Optionally, as shown in fig. 5 and fig. 6, the measurement and control data transmission antenna group 2 includes a first measurement and control data transmission antenna 21 and a first measurement and control data reception antenna 22, where the first measurement and control data transmission antenna 21 is used for transmitting measurement and control data, and the first measurement and control data reception antenna 22 is used for receiving measurement and control data. The backup measurement and control data transmission antenna group 3 comprises a second measurement and control data transmission antenna 31 and a second measurement and control data transmission receiving antenna 32, wherein the second measurement and control data transmission antenna 31 is used for transmitting measurement and control data, and the second measurement and control data transmission receiving antenna 32 is used for receiving measurement and control data.

Optionally, as shown in fig. 7 and 8, the satellite further includes a satellite-arrow separator 5, and the satellite-arrow separator 5 is disposed on one side of the satellite body 1 along the first direction. The satellite-rocket separator 5 comprises a base 51, a connecting piece 52 and an explosion bolt, wherein one end of the base 51 is connected with a rocket through the bolt, the connecting piece 52 is arranged at the other end of the base 51, one end of the connecting piece 52 is connected with the satellite body 1, the other end of the connecting piece 52 stretches into the base 51, and one end of the connecting piece 52 stretching into the base 51 is connected with the base 51 through the explosion bolt. When the satellite needs to be separated from the rocket, the explosion bolt is detonated, the connection between the end of the connecting piece 52 extending into the base 51 and the base 51 fails, the satellite is separated from the rocket, and it is noted that after the satellite is separated from the rocket, the connecting piece 52 is still connected to the satellite, and the base 51 is still connected to the rocket. The two components are connected through the explosion bolt, and the separation of the two components is realized through the detonation of the explosion bolt, which is a conventional technical means in the field, and the specific arrangement and placement of the explosion bolt are not repeated here.

Further, as shown in fig. 8, the satellite further includes a positioning device 6, the positioning device 6 is fixedly arranged on the satellite body 1, a positioning hole 61 is provided on the positioning device 6, and the positioning hole 61 is used for being matched with a positioning pin on the rocket, that is, the positioning pin on the rocket is inserted into the positioning hole 61 on the positioning device 6, so as to position the relative position of the satellite and the rocket. The positioning device 6 is provided in plurality, and the plurality of positioning devices 6 are arranged at intervals on the surface of the satellite.

Optionally, as shown in fig. 1 and 2, the satellite further comprises a solar panel 7, and the solar panel 7 is disposed on the other side of the satellite body 1 along the first direction. The solar sailboard 7 is irradiated by sunlight to generate electricity, so that power is supplied to the satellite body 1 and the antenna body, and the electricity demand of the satellite body is met

Further, as shown in fig. 1 and 2, the solar sailboard 7 includes a fixed sailboard 71 and a folding sailboard 72, the fixed sailboard 71 is fixedly arranged on the satellite body 1, one end of the folding sailboard 72 is hinged with one end of the fixed sailboard 71 through a hinge assembly, the other end of the folding sailboard 72 is connected with the satellite body 1 through an explosion bolt, an avoidance hole is formed in the fixed sailboard 71, and the explosion bolt penetrates through the avoidance hole to avoid the fixed sailboard 71 from obstructing the connection between the explosion bolt and the satellite body 1. After the satellite is launched to the orbit, the explosion bolts are exploded, and the hinge assembly drives the folding sailboard 72 to turn over to the corresponding position, so that the area of the solar sailboard 7 is increased, and the generated energy is improved. It should be noted that an actuator is disposed in the hinge assembly, and the folded sailboard 72 is driven to turn over relative to the fixed sailboard 71 by the actuator, and the hinge assembly is in the prior art, and the specific structure thereof is not described herein.

Alternatively, as shown in fig. 3 and 4, the VDES antenna 4 includes a mount 41, an arm bar assembly 42, a hinge assembly 43, and a pinch release assembly 44. The arm assembly 42 includes a first arm 421, a second arm 422, and a third arm 423. The hinge assembly 43 includes a first hinge 431, a second hinge 432, and a third hinge 433, and one end of the first arm 421 is hinged to the mounting seat 41 through the first hinge 431; one end of the second arm 422 is hinged with one end of the first arm 421 away from the mounting seat 41 through a second hinge 432; one end of the third arm 423 is hinged with one end of the second arm 422 remote from the second hinge 432 by a third hinge 433. The compression release assembly 44 is used for folding the first arm 421, the second arm 422, and the third arm 423 to make the three parallel to each other and then fold, and the folding fixation of the arm assembly 42 is achieved through the compression release assembly 44. One end of the satellite body 1 is provided with a first connecting seat 11, the other end is provided with a second connecting seat 12, one of the two VDES antennas 4 is connected with the first connecting seat 11, and the other is connected with the second connecting seat 12, so that the VDES antennas 4 are installed.

Further, as shown in fig. 3 and 4, the compression release assembly 44 includes a compression seat 441, a support seat 442, a strap 443, a rope (not shown), and a fuse 444. The pressing seat 441 is disposed on the bottom surface of the third arm 423, and is provided with a pressing cavity adapted to the third arm 423. The supporting seat 442 is disposed at a side surface of the pressing seat 441. One end of the wrapping belt 443 is detachably connected with the supporting seat 442. The rope is connected to the end of the strap 443 remote from the support base 442. A fuse 444 is provided at the cord and is used to blow the cord. The pressing member 445 is disposed on a side of the pressing seat 441 away from the supporting seat 442 and connected to the rope, and the pressing member 445 is used for fixing the rope. The compression seat 441, the support seat 442, the strap 443, the rope, and the compression member 445 are disposed around the arm assembly 42 and enclose a collapsing cavity for collapsing the arm assembly 42. When deployment of the VDES antenna 4 is desired, the fuse 444 blows the cord such that the strap 443 and cord can no longer bundle the arm bar assembly 42.

Further, the first hinge 431, the second hinge 432, and the third hinge 433 are flexible hinges, and the flexible hinges have elasticity, so that the first arm 421, the second arm 422, and the third arm 423 are unfolded under the restoring force of the first hinge 431, the second hinge 432, and the third hinge 433 when the strap 443 and the rope can not bind the arm assembly 42 any more. In particular, in the present embodiment, the first hinge 431, the second hinge 432 and the third hinge 433 are each composed of a 2-piece C-shaped leaf spring symmetrically installed, and the hinge has good rigidity and is light in weight, and can greatly reduce the weight of the VDES antenna 4.

Optionally, as shown in fig. 4 and 7, the satellite further includes a satellite sensor 8 and a GNSS (Global Navigation Satellite System) antenna 9, and the satellite sensor 8 and the GNSS antenna 9 are both disposed on the satellite body 1. The communication connection is established through the GNSS antenna 9 and the positioning satellite in space, and the position of the positioning satellite in space is adjusted to the correct orbit through a gesture orbit control system in the satellite structure when the satellite orbit deviates. The star sensor 8 provides accurate space orientation and reference for the satellite by detecting the star at different positions on the celestial sphere and resolving the star by taking the star in the sky as a reference system, and when the space orientation is offset, the star sensor is adjusted to the correct attitude by an attitude orbit control system in the satellite structure. The satellite position and the azimuth are accurately positioned through the satellite sensor 8 and the GNSS antenna 9, so that the requirements of diversity of azimuth requirements of different positions on the arrangement of satellites in space are met.

Optionally, as shown in fig. 5 and 6, the satellite further includes a star clock plug 10, where the star clock plug 10 is disposed on the satellite body 1. The star meter plug 10 is connected with ground test equipment by adopting a standard communication protocol, and before the satellite is transmitted, all systems in the satellite are confirmed to work normally, so that no fault exists, the satellite is prevented from being unusable after being transmitted into space, and resources are wasted. After ensuring that all satellites are normal, the star warhead plug 10 is plugged before loading the rocket.

It is to be understood that the above examples of the present utility model are provided for clarity of illustration only and are not limiting of the embodiments of the present utility model. Various obvious changes, rearrangements and substitutions can be made by those skilled in the art without departing from the scope of the utility model. It is not necessary here nor is it exhaustive of all embodiments. Any modification, equivalent replacement, improvement, etc. which come within the spirit and principles of the utility model are desired to be protected by the following claims.

Claims (10)

1. A satellite, comprising:

a satellite body (1);

the measurement and control data transmission antenna group (2) is arranged on the satellite body (1);

the backup measurement and control data transmission antenna group (3) is arranged on the satellite body (1), and the backup measurement and control data transmission antenna group (3) is used as a backup of the measurement and control data transmission antenna group (2);

and the VDES antenna (4) is arranged at two ends of the satellite body (1) along the first direction, and the VDES antenna (4) can be folded and unfolded.

2. The satellite according to claim 1, wherein the measurement and control data transmission antenna group (2) comprises a first measurement and control data transmission antenna (21) and a first measurement and control data reception antenna (22), the first measurement and control data transmission antenna (21) is used for transmitting measurement and control data, and the first measurement and control data reception antenna (22) is used for receiving measurement and control data;

the backup measurement and control data transmission antenna group (3) comprises a second measurement and control data transmission antenna (31) and a second measurement and control data transmission receiving antenna (32), wherein the second measurement and control data transmission antenna (31) is used for transmitting measurement and control data, and the second measurement and control data transmission receiving antenna (32) is used for receiving the measurement and control data.

3. The satellite according to claim 1, further comprising a satellite-arrow separator (5), the satellite-arrow separator (5) being arranged on one side of the satellite body (1) in a first direction.

4. A satellite according to claim 3, further comprising a positioning device (6), wherein the positioning device (6) is fixedly arranged on the satellite body (1), a positioning hole (61) is arranged on the positioning device (6), and the positioning hole (61) is used for being matched with a positioning pin on a rocket to position the satellite and the rocket relative to each other.

5. A satellite according to claim 3, further comprising a solar panel (7), the solar panel (7) being arranged on the other side of the satellite body (1) in the first direction.

6. Satellite according to claim 1, characterized in that the VDES antenna (4) comprises:

a mounting base (41);

an arm assembly (42) comprising a first arm (421), a second arm (422), and a third arm (423);

a hinge assembly (43) including a first hinge (431), a second hinge (432), and a third hinge (433), wherein one end of the first arm (421) is hinged to the mounting base (41) through the first hinge (431); one end of the second arm rod (422) is hinged with one end of the first arm rod (421) away from the mounting seat (41) through a second hinge (432); one end of the third arm lever (423) is hinged with one end of the second arm lever (422) far away from the second hinge (432) through a third hinge (433);

and the compression release assembly (44) is used for folding the first arm lever (421), the second arm lever (422) and the third arm lever (423) to enable the first arm lever, the second arm lever and the third arm lever to be parallel to each other and then folded.

7. The satellite of claim 6, wherein the compression release assembly (44) comprises:

a compression seat (441); the pressing device is arranged on the bottom surface of the third arm rod (423) and is provided with a pressing cavity which is adapted to the third arm rod (423);

a support base (442) provided on the side surface of the pressing base (441);

a wrapping belt (443) one end of which is detachably connected with the supporting seat (442);

a rope connected to one end of the strap (443) remote from the support base (442);

a fuse (444) provided at the rope for fusing the rope;

a pressing member (445) provided on a side surface of the pressing seat (441) away from the supporting seat (442) and connected to the rope, the pressing member (445) being configured to fix the rope;

the compression seat (441), the supporting seat (442), the wrapping belt (443), the rope and the compression piece (445) are arranged around the arm rod assembly (42) and enclose to form a folding cavity for folding the arm rod assembly (42).

8. The satellite of claim 6, wherein the first hinge (431), the second hinge (432), and the third hinge (433) are flexible hinges.

9. The satellite according to claim 1, further comprising a star sensor (8) and a GNSS antenna (9), the star sensor (8) and the GNSS antenna (9) being both arranged on the satellite body (1).

10. Satellite according to claim 1, further comprising a star plug (10), the star plug (10) being arranged on the satellite body (1).