CN212267874U - On-orbit deployable main bearing structure suitable for microsatellite - Google Patents
On-orbit deployable main bearing structure suitable for microsatellite Download PDFInfo
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- CN212267874U CN212267874U CN202020097173.0U CN202020097173U CN212267874U CN 212267874 U CN212267874 U CN 212267874U CN 202020097173 U CN202020097173 U CN 202020097173U CN 212267874 U CN212267874 U CN 212267874U
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Abstract
The utility model relates to the technical field of aerospace structures, in particular to an on-orbit deployable main bearing structure suitable for a microsatellite, which comprises a body consisting of an upper fixed bearing cabin plate, a lower fixed bearing cabin plate, a front fixed bearing cabin plate and a rear fixed bearing cabin plate, and deployable bearing cabin plates positioned on the left side and the right side of the body; the two expandable bearing cabin plates are hinged with the fixed bearing cabin plate positioned below through hinges respectively, a supporting mechanism for supporting the expandable bearing cabin plates is arranged between the expandable bearing cabin plates and the body, explosive initiating explosive devices are arranged between the expandable bearing cabin plates and the body, a satellite-rocket butt joint device for connecting with a rocket is arranged at the bottom of the body, and a power supply device is further arranged on the body. The utility model discloses a satellite provides great ground and great cooling surface, realizes the low cost of high-power satellite.
Description
Technical Field
The utility model discloses space flight technical field especially relates to a can expand main load structure in orbit suitable for microsatellite.
Background
The microsatellite has the advantages of low cost, capability of carrying and launching and the like, is widely applied to the field of commercial aerospace, and particularly has the advantages of low cost and short period as a test verification satellite. Similarly, microsatellites also have certain disadvantages:
(1) the satellite body is small, and the verification is insufficient;
(2) the device is generally cubic, the area of a specific direction is small, and particularly the area of a communication satellite and the like which needs to be pointed to the ground is large and cannot meet the requirement;
(3) the heat dissipation surface of the satellite is small, and some high-power satellites cannot meet the heat dissipation requirement.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a can expand main load structure in the orbit suitable for microsatellite can carry out the expansion in the orbit of partial structure to compensate some microsatellite to the directional and less shortcoming of heat radiating area in ground.
In order to solve the technical problem, the utility model discloses a following technical scheme:
an on-orbit deployable main bearing structure suitable for a microsatellite comprises a body consisting of an upper fixed bearing cabin plate, a lower fixed bearing cabin plate, a front fixed bearing cabin plate and a rear fixed bearing cabin plate, and deployable bearing cabin plates positioned on the left side and the right side of the body; the two expandable bearing cabin plates are respectively hinged with a fixed bearing cabin plate positioned below through hinges, the body and the expandable bearing cabin plates form a cabin body, a single machine/high-power device/load is installed on the expandable bearing cabin plates, a supporting mechanism for supporting the expandable bearing cabin plates is installed between the expandable bearing cabin plates and the body, explosive initiating explosive devices are installed between the expandable bearing cabin plates and the body, a star-rocket butt joint device for connecting with a rocket is installed at the bottom of the body, and a power supply device is also installed on the body.
In the technical scheme, the main body is a satellite main bearing structure and is used for supporting most of single machines; the deployable bearing deck plate is used for supporting a ground load, a small part of single machines and high-power devices, can realize configuration changes of two states of launching and in-orbit, and is used as a part of a bearing structure during launching to realize the direction of the load to the ground; the supporting mechanism is used as a part of a satellite bearing structure and plays a role in reinforcement; the satellite and rocket butt joint device is used for connecting a satellite and a rocket and launching the satellite, the rocket is separated from the satellite body after launching, the load outside the cabin and the load in the cabin are satellite effective loads, and the power supply device provides power for the satellite.
Preferably, the power supply device is a solar sailboard, and the solar sailboard is hinged to the top of the body through a hinge.
In this way, the solar sailboard provides power for the satellite and can be unfolded in orbit.
Preferably, the explosive initiating explosive devices are 4 explosive bolts, and the two explosive bolts are respectively arranged on the two expandable bearing cabin plates.
Thus, the explosive bolt is an existing product, is easy to purchase and is used for on-track expansion of the expandable bearing cabin plate.
Preferably, the number of the supporting mechanisms is 4, the left side and the right side of the body are respectively provided with two supporting mechanisms, each supporting mechanism comprises a pressing elastic rod and two fixed rotating shafts, the pressing elastic rods are fixedly connected with the two fixed rotating shafts, and the two fixed rotating shafts are respectively hinged with the body and the expandable bearing cabin plate.
Therefore, the fixed rotating shaft is used for translational limiting of the deployable bearing cabin plate, the pressing elastic rod provides unfolding power for the deployable bearing cabin plate and structural support after unfolding, the structure is simple, and the bearing plate and the fixed bearing cabin plate can be connected more stably.
And optimally, the fixed bearing cabin plate and the expandable bearing cabin plate are processed by a thermal control integrated technology.
Thus, both the fixed bearing cabin plate and the expandable bearing cabin plate have good thermal conductivity.
Preferably, the satellite and rocket docking device is a satellite and rocket docking ring.
Therefore, the star-arrow butt-joint ring is an existing product and is easy to purchase.
Compared with the prior art, the on-orbit deployable main bearing structure applicable to the microsatellite has the following technical effects:
(1) the utility model discloses from the connection before the satellite transmission, fixed, to the expansion of the expanding in orbit of expansion load cabin board after the transmission, carried out the omnidirectional and considered, realized the safe and reliable of satellite transmission and the safe convenience that expands in orbit, adopt the scheme that the invention provided can be simultaneously low-cost, carry on the transmission, greatly reduced the emission cost, provide great to ground and great cooling surface for the satellite simultaneously, realize the low cost of high-power satellite;
(2) the design meets the convenience and reliability of the satellite, and facilitates the type-spectrum design of the satellite;
(3) the on-orbit unlocking device has the advantages that the on-orbit unfolding simplicity and safety of the satellite are met, the satellite is convenient to assemble before being launched, the requirement is loose, the safety requirement is met in the launching process, and the on-orbit unlocking is safe and convenient.
Drawings
Fig. 1 is a structural diagram of an emitting state of an on-orbit deployable main bearing structure suitable for a microsatellite of the present invention;
fig. 2 is an in-orbit expansion state structure diagram of the in-orbit expandable main bearing structure applicable to the microsatellite of the present invention;
fig. 3 is a schematic structural diagram of a supporting mechanism in a launching state of an on-orbit deployable main bearing structure suitable for a microsatellite of the present invention;
fig. 4 is a schematic structural diagram of the support mechanism in the on-orbit expansion state of the on-orbit expandable main bearing structure of the present invention, which is suitable for a microsatellite;
fig. 5 is a schematic connection diagram of the supporting mechanism in the launching state of the on-orbit deployable main bearing structure suitable for a microsatellite, a fixed bearing deck plate and a deployable bearing deck plate;
fig. 6 is a schematic diagram of the connection between the in-orbit expansion state supporting mechanism of the in-orbit expansion main bearing structure applicable to the microsatellite and the fixed bearing deck plate and the expandable bearing deck plate.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings. In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the orientation words such as "upper, lower, front, rear, left, right" and "top, bottom" etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplification of description, and in the case of not making a contrary explanation, these orientation words do not indicate and imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be interpreted as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself. The fixed connection in this embodiment may be understood as being fixed by welding, or may be fixed by bolts or screws.
In order to solve the technical problem, the utility model discloses a following technical scheme:
as shown in fig. 1-6, an on-orbit deployable main bearing structure suitable for a microsatellite comprises a body consisting of four fixed bearing deck boards 1, namely an upper fixed bearing deck board, a lower fixed bearing deck board, a front fixed bearing deck board and a rear fixed bearing deck board, and deployable bearing deck boards 3 positioned on the left side and the right side of the body; the two expandable bearing cabin plates 3 are hinged with a fixed bearing cabin plate positioned below through hinges respectively, the body and the expandable bearing cabin plates 3 form a cabin body, a single machine/load 2 is installed on the expandable bearing cabin plates 3, a supporting mechanism 6 for supporting the expandable bearing cabin plates is installed between the expandable bearing cabin plates 3 and the body, explosive initiating explosive devices 5 are installed between the expandable bearing cabin plates 3 and the body, a satellite-rocket butt joint device for connecting with a rocket is installed at the bottom of the body, and a power supply device is further installed on the body.
Thus, the main body is a satellite main bearing structure and is used for supporting most satellite single machines; the deployable bearing deck plate is used for supporting a ground load and a high-power device, can realize the configuration change of two states of launching and in-orbit, is used as a part of a bearing structure during launching, can realize unilateral deployment in the orbit, realizes the direction of the load to the ground and realizes double-sided heat dissipation; the supporting mechanism is used as a part of a satellite bearing structure and plays a role in reinforcement; the satellite and rocket butt joint device is used for connecting a satellite and a rocket and launching the satellite, the rocket is separated from the satellite body after launching, the load outside the cabin and the load in the cabin are satellite effective loads, and the power supply device provides power for the satellite.
In this embodiment, the power supply device is a solar panel 7, and the solar panel 7 is hinged to the top of the body through a hinge.
In this way, the solar sailboard provides power for the satellite and can be unfolded in orbit.
In this embodiment, the explosive initiating explosive device 5 is an explosive bolt, and there are 4 explosive bolts, and two explosive bolts are respectively arranged on the two expandable bearing cabin plates 3.
Thus, the explosive bolt is an existing product, is easy to purchase and is used for on-track expansion of the expandable bearing cabin plate.
In this embodiment, there are 4 support mechanisms 6, two support mechanisms are respectively disposed on the left and right sides of the body, and each support mechanism includes a pressing elastic rod 62 and two fixed rotating shafts 61, the pressing elastic rod 62 is fixedly connected with the two fixed rotating shafts 61, and the two fixed rotating shafts 61 are respectively hinged to the body and the expandable bearing deck 3.
Therefore, the fixed rotating shaft is used for translational limiting of the deployable bearing cabin plate, the pressing elastic rod provides unfolding power for the deployable bearing cabin plate and structural support after unfolding, the structure is simple, and the bearing plate and the fixed bearing cabin plate can be connected more stably.
In this embodiment, both the fixed bearing deck and the expandable bearing deck are processed by a thermal control integration technology.
Thus, both the fixed bearing cabin plate and the expandable bearing cabin plate have good thermal conductivity.
In this embodiment, the satellite and arrow docking device is a satellite and arrow docking ring 4.
Therefore, the star-arrow butt-joint ring is an existing product and is easy to purchase.
Adopt the utility model provides a scheme can realize simultaneously that small envelope sends out and the directional and heat dissipation demand of high-power load, especially directional to ground to requiring the load, and the great communication satellite of heat loss has great advantage. The utility model discloses can be used to the microsatellite below 100 kilograms, when realizing low-cost carrying, realize the function of great satellite load.
The principle of the utility model is as follows:
as shown in fig. 1, in a satellite launching state, a main bearing structure of the satellite is composed of a fixed bearing deck plate 1 and an expandable bearing deck plate 3, wherein the expandable bearing deck plate 3 and the fixed bearing deck plate 1 are fixed by an explosive initiating explosive device 5. The satellite is pointed to the ground and the high-power single machine/load 2 is installed on the deployable bearing cabin plate 3, and the whole satellite is connected with the rocket through a satellite-rocket butt joint ring 4; after the satellite is launched into the orbit, the satellite and arrow butt-joint ring 4 falls off along with the separation of the satellite and the arrow, after the attitude of the satellite is stable, the satellite sends out an instruction, the explosive initiating explosive device 5 is electrified, the expandable bearing cabin plate 3 is separated from the fixed bearing cabin plate 1, and the expandable bearing cabin plate is expanded to a specified position under the action of the supporting mechanism 6, so that the on-orbit deployment of each ground direction and the high-power single machine/load 2 is completed.
The embodiments of the present invention have been described in detail with reference to the drawings, but the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Finally, it should be noted that: various modifications and alterations of this invention may be made by those skilled in the art without departing from the spirit and scope of this invention. Thus, to the extent that such modifications and variations of the present invention fall within the scope of the present claims and their equivalents, it is intended that the present invention encompass such modifications and variations as well.
Claims (6)
1. An on-orbit deployable main bearing structure suitable for a microsatellite is characterized by comprising a body consisting of four fixed bearing cabin plates (1) which are arranged at the upper part, the lower part, the front part and the rear part and deployable bearing cabin plates (3) which are arranged at the left side and the right side of the body; the two expandable bearing cabin plates (3) are hinged with a fixed bearing cabin plate (1) located below through hinges respectively, a single machine/load (2) is mounted on each expandable bearing cabin plate (3), a supporting mechanism (6) is mounted between each expandable bearing cabin plate (3) and the body, each expandable bearing cabin plate (3) is supported by the corresponding supporting mechanism (6), explosive initiating explosive devices (5) are mounted between each expandable bearing cabin plate (3) and the body, a satellite-rocket butt joint device used for being connected with a rocket is mounted at the bottom of the body, and a power supply device is further mounted on the body.
2. The on-orbit deployable main bearing structure suitable for microsatellites according to claim 1, wherein the power supply device is a solar panel (7), and the solar panel (7) is hinged on the top of the body through a hinge.
3. The primary on-orbit deployable bearing structure for microsatellites according to claim 1, wherein the explosive initiating explosive devices (5) are explosive bolts, and 4 explosive bolts are arranged, and 4 explosive bolts are respectively arranged on two deployable bearing deck plates (3) in pairs.
4. The primary on-orbit deployable bearing structure for microsatellites according to claim 1, wherein there are 4 supporting mechanisms (6), two supporting mechanisms are respectively arranged on the left and right sides of the body, the supporting mechanism (6) comprises a pressing elastic rod (62) and two fixed rotating shafts (61), the pressing elastic rod (62) is fixedly connected with the two fixed rotating shafts (61), and the two fixed rotating shafts (61) are respectively hinged with the body and the deployable bearing deck (3).
5. The primary force-bearing structure capable of being unfolded in orbit for the microsatellite according to claim 1, wherein the fixed force-bearing deck boards (1) and the unfolded force-bearing deck boards (3) are processed by a thermal control integration technology.
6. The on-orbit deployable main bearing structure for microsatellites according to claim 1, wherein the satellite docking device is a satellite docking ring (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020097173.0U CN212267874U (en) | 2020-01-16 | 2020-01-16 | On-orbit deployable main bearing structure suitable for microsatellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020097173.0U CN212267874U (en) | 2020-01-16 | 2020-01-16 | On-orbit deployable main bearing structure suitable for microsatellite |
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| Publication Number | Publication Date |
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| CN212267874U true CN212267874U (en) | 2021-01-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020097173.0U Active CN212267874U (en) | 2020-01-16 | 2020-01-16 | On-orbit deployable main bearing structure suitable for microsatellite |
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| CN (1) | CN212267874U (en) |
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- 2020-01-16 CN CN202020097173.0U patent/CN212267874U/en active Active
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Address after: 401120 39-1, Building 1, No. 64, Middle Huangshan Avenue, Yubei District, Chongqing Patentee after: China Star Network Application Co.,Ltd. Address before: 401135 No. 618 Liangjiang Avenue, Longxing Town, Yubei District, Chongqing Patentee before: Dongfanghong Satellite Mobile Communication Co.,Ltd. |
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