Two-degree-of-freedom solar wing attitude control device suitable for microsatellite

Abstract

The invention relates to the technical field of satellites, in particular to a two-degree-of-freedom solar wing attitude control device suitable for microsatellites, which is characterized in that a base column is arranged in the middle of a base, end seats are arranged at two ends of the base column, four symmetrical support columns are arranged on the end surfaces of the end seats, and an electromagnet I is arranged in the middle of the side surface of each support column; a first fixing plate is arranged on the side faces of the two adjacent supporting columns on the upper portion, a limiting ring is arranged on the outer circumferential face of the foundation column, the rotating base is rotationally arranged on the base, a fixing cylinder is arranged in the middle of the rotating base, a supporting base is arranged on the outer circumferential face of the fixing cylinder, two limiting holes are symmetrically formed in the center of the side face of the supporting base, and shaft holes are formed in the centers of the bottom faces of the limiting holes. Adjustment of the solar wing is controlled in a magnetic control and mechanical combined mode, two-dimensional tracking of the incident angle of sunlight can be achieved, the solar wing can face the sun at the optimal angle all the time due to the accurate tracking capacity, and the utilization efficiency of solar energy is further improved.

Description

Technical Field

[0001] The present invention relates to the field of satellite technology, and particularly to a two-degree-of-freedom solar wing attitude control device suitable for microsatellites. Background Art

[0002] Microsatellites have the advantages of small size, light weight, low cost, and fast R & D. The significant difference from general traditional satellites is the adoption of the idea of modular design and assembly. This facilitates satellite testing and launching, ensures technological continuity and maturity, and reduces costs. However, there is still an important problem in the development of microsatellites - the limitation of energy on the payload capacity of microsatellites. In the technology verification and application of microsatellites, the power demand of payloads is constantly increasing, but the current installation method of solar panels limits the photovoltaic power generation capacity of microsatellites and cannot meet the demand for high-power payloads.

[0003] The photovoltaic power generation capacity of solar wings is mainly affected by factors such as the effective working area of solar panels and the incident angle of sunlight. The current installation methods of solar wings for microsatellites mainly include body-mounted surface-mounted type, folding and unfolding type, folding and unfolding single-axis orientation type, etc. In existing patents, solar wings use single-degree-of-freedom design, which cannot achieve two-dimensional tracking of the incident angle of sunlight and cannot maximize the photovoltaic power generation capacity of solar panels. Summary of the Invention

[0004] Therefore, the present invention is made in view of the above problems. The present invention adopts the body-mounted surface-mounted method for installing solar wings, enabling the solar wings to be installed in a circular manner around the surface of the microsatellite, greatly increasing the solar irradiation area when the solar wings are unfolded, meeting the demand for high-power payloads, and using magnetic control and mechanical methods to control the adjustment of the solar wings to achieve two-dimensional tracking of the incident angle of sunlight, which can maximize the photovoltaic power generation capacity of solar panels:

[0005] A two-degree-of-freedom solar wing attitude control device suitable for microsatellites, comprising: a base column is provided in the middle of the base, end seats are provided at both ends of the base column, four symmetric support columns are provided on the end face of the end seat, an electromagnet one is provided in the middle of the side surface of the support column, a fixing plate one is provided on the side surfaces of two adjacent upper support columns, a limiting ring is provided on the outer circumferential surface of the base column, a rotating seat is rotatably provided on the base, a fixing cylinder is provided in the middle of the rotating seat, a support seat is provided on the outer circumferential surface of the fixing cylinder, two limiting holes are symmetrically provided at the center of the side surface of the support seat, a shaft hole is provided at the center of the bottom surface of the limiting hole, a gear groove is provided at the end of the shaft hole, circumferential teeth are provided on the outer circumferential surface of the upper end of the fixing cylinder, a matching hole is provided inside the circumferential teeth, a fixing plate two is provided on the outer circumferential surface of the lower end of the circumferential teeth, a driving mechanism is fixedly provided inside the base, the driving mechanism includes a driving shaft, an electric cylinder one, an electric cylinder two, a rack one, a rack two and a driving gear, the number of solar wings is two, which are respectively fixedly provided on the driving mechanism, and the solar wing includes a first substrate, a second substrate and a third substrate.

[0006] Preferably, the number of the drive shafts is two, which are respectively rotatably arranged in the limit holes. A fixed platform is provided at the end of the drive shaft, and the fixed platform is rotatably arranged in the limit hole. A rotating shaft is provided at the other end of the drive shaft, and the rotating shaft is rotatably arranged in the shaft hole.

[0007] Preferably, a positioning surface is provided on the side surface of the fixed platform, a limit groove is provided on the end surface of the fixed platform, and a limit post is provided on the end surface of the limit groove.

[0008] Preferably, the number of the first electric cylinders is two, which are respectively fixedly arranged on the second fixing plate, and the second electric cylinder is fixedly arranged on the first fixing plate.

[0009] Preferably, the number of the drive gears is two, which are respectively fixedly arranged at the ends of the rotating shafts and rotatably arranged in the gear grooves. One end of the first rack is fixed to the moving end of the first electric cylinder, the first rack meshes with the drive gear, one end of the second rack is fixed to the moving end of the second electric cylinder, and the second rack meshes with the circumferential teeth.

[0010] Preferably, the first substrate is fixedly arranged on the drive shaft. A support plate is provided at the end of the first substrate, a connecting rotating cylinder one is provided on the side surface of the first substrate, a fixed rotating cylinder is provided on the side surface of the support plate, and the fixed rotating cylinder is sleeved on the limit post and rotatably arranged in the limit groove.

[0011] Preferably, an electromagnet two is provided on the side surface of the support plate, an electromagnetic block one is provided on the other side surface of the support plate, and an electromagnet three is provided on the end surface of the first substrate.

[0012] Preferably, the second substrate is rotatably arranged on the first substrate. A connecting rotating cylinder two is provided on the side surface of the second substrate, a matching shaft one is provided on the other side surface of the second substrate, an electromagnet five is provided on the end surface of the second substrate, and an electromagnetic block two is provided on the side surface of the second substrate adjacent to the connecting rotating cylinder two.

[0013] Preferably, the third substrate is connected to the last second substrate. A matching shaft two is provided on the side surface of the third substrate, and the matching shaft two is rotatably arranged in the connecting rotating cylinder two. An electromagnet four is provided on the end surface of the third substrate.

[0014] Preferably, the electromagnet one has opposite polarity to the electromagnet five and the electromagnet four.

[0015] Advantages of the present invention:

[0016] 1. Through the loop installation of the body-mounted and surface-mounted solar wings, the present invention greatly increases the solar irradiation area when the solar wings are deployed. This design can maximize the capture of sunlight, thereby significantly enhancing the photovoltaic power generation capacity of the solar panels. This is particularly important for meeting the high-power payload requirements of microsatellites, ensuring that the satellite can obtain sufficient power support during on-orbit operation, extending the satellite's service life, and improving the reliability of mission execution.

[0017] 2. The present invention uses a combination of magnetic control and mechanical means to control the adjustment of the solar wings, enabling two-dimensional tracking of the incident angle of sunlight. This precise tracking ability allows the solar wings to always face the sun at the best angle, further improving the utilization efficiency of solar energy. In this way, even when the satellite's orbital position changes or the relative position of the sun changes, the solar wings can continuously and efficiently convert solar energy into electrical energy, thereby maximizing the photovoltaic power generation capacity and enhancing the overall energy management efficiency of the satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of the overall structure of the present invention Figure 1 .

[0019] Figure 2 is a schematic diagram of the overall structure of the present invention Figure 2 .

[0020] Figure 3 is a schematic diagram of the overall internal structure of the present invention.

[0021] Figure 4 is a schematic diagram of the overall structure of the base of the present invention

[0022] Figure 5 is a schematic diagram of the overall structure of the turntable of the present invention.

[0023] Figure 6 is a schematic diagram of the overall structure of the drive shaft of the present invention.

[0024] Figure 7 is a schematic diagram of the overall structure of the first substrate of the present invention Figure 1 .

[0025] Figure 8 is a schematic diagram of the overall structure of the first substrate of the present invention Figure 2 .

[0026] Figure 9 is a schematic diagram of the overall structure of the second substrate of the present invention.

[0027] Figure 10 is a schematic diagram of the overall structure of the third substrate of the present invention.

[0028] Figure 11 is a schematic diagram of the motion state of the present inventionFigure 1 。

[0029] Figure 12 Schematic of the motion state of the present invention Figure 2 。

[0030] Figure 13 Schematic of the motion state of the present invention Figure 3 。

[0031] Figure 14 Schematic of the motion state of the present invention Figure 4 。

[0032] Explanation of reference numerals in the drawings:

[0033] 1. Base; 101. Base column; 102. End seat; 103. Support column; 104. Electromagnet 1; 105. Fixed plate 1; 106. Limiting ring; 2. Rotating seat; 201. Fixed cylinder; 202. Support seat; 203. Limiting hole; 204. Shaft hole; 205. Gear groove; 206. Fitting hole; 207. Peripheral teeth; 208. Fixed plate 2; 3. Driving mechanism; 31. Driving shaft; 311. Fixed table; 312. Rotating shaft; 313. Positioning surface; 314. Limiting groove; 315. Limiting column; 32. Electric cylinder 1; 33. Electric cylinder 2; 34. Rack 1; 35. Rack 2; 36. Driving gear; 4. Solar wing; 41. First substrate; 411. Support plate; 412. Connecting rotating cylinder 1; 413. Fixed rotating cylinder; 414. Electromagnet 2; 415. Electromagnetic block 1; 416. Electromagnet 3; 42. Second substrate; 421. Connecting rotating cylinder 2; 422. Fitting shaft 1; 423. Electromagnet 5; 424. Electromagnetic block 2; 43. Third substrate; 431. Fitting shaft 2; 432. Electromagnet 4. Detailed implementation manners

[0034] Preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. It is easy for those of ordinary skill in the art in the prior art of the field to which the present invention pertains to implement these embodiments. However, the present invention can be implemented in various different forms. Therefore, the present invention is not limited to the embodiments described below. Additionally, in order to more clearly describe the present invention, components not connected to the invention will be omitted from the drawings.

[0035] As Figure 1 、 2 、3 shows, a dual-degree-of-freedom solar wing attitude control device applicable to microsatellites includes: a base 1, a rotating seat 2, a driving mechanism 3, and a solar wing 4;

[0036] The base 1 is a support for the entire structure;

[0037] As Figure 4 shown, a base column 101 is provided in the middle of the base 1;

[0038] Both ends of the base column 101 are provided with end seats 102;

[0039] Four symmetric support columns 103 are provided on the end face of the end seat 102;

[0040] An electromagnet 104 is provided in the middle of the side surface of the support column 103;

[0041] A fixing plate 105 is provided on the side surfaces of two adjacent upper support columns 103;

[0042] A limiting ring 106 is provided on the outer circumferential surface of the base column 101;

[0043] The rotating seat 2 is rotatably arranged on the base 1;

[0044] As Figure 5 shown, a fixing cylinder 201 is provided in the middle of the rotating seat 2;

[0045] A support seat 202 is provided on the outer circumferential surface of the fixing cylinder 201;

[0046] Two symmetric limiting holes 203 are provided at the center of symmetry on the side surface of the support seat 202;

[0047] A shaft hole 204 is provided at the center of the bottom surface of the limiting hole 203;

[0048] A gear groove 205 is provided at the end of the shaft hole 204;

[0049] A circumferential tooth 207 is provided on the outer circumferential surface of the upper end of the fixing cylinder 201;

[0050] A mating hole 206 is provided inside the circumferential tooth 207;

[0051] A fixing plate 208 is provided on the outer circumferential surface of the lower end of the fixing cylinder 201;

[0052] The driving mechanism 3 is fixedly arranged inside the base 1;

[0053] The driving mechanism 3 includes: a driving shaft 31, a first electric cylinder 32, a second electric cylinder 33, a first rack 34, a second rack 35, and a driving gear 36;

[0054] The number of the driving shafts 31 is two, and they are respectively rotatably arranged in the limiting holes 203;

[0055] As Figure 6 shown, a fixing platform 311 is provided at the end of the driving shaft 31, and the fixing platform 311 is rotatably arranged in the limiting hole 203;

[0056] The other end of the drive shaft 31 is provided with a rotating shaft 312, and the rotating shaft 312 is rotatably arranged in the shaft hole 204;

[0057] A positioning surface 313 is provided on the side surface of the fixed table 311 for determining the rotation position of the drive shaft 31;

[0058] A limiting groove 314 is provided on the end surface of the fixed table 311;

[0059] A limiting post 315 is provided on the end surface of the limiting groove 314;

[0060] The number of the first electric cylinders 32 is two, and they are respectively fixedly arranged on the second fixing plate 208;

[0061] The second electric cylinder 33 is fixedly arranged on the first fixing plate 105;

[0062] The number of the driving gears 36 is two, and they are respectively fixedly arranged at the ends of the rotating shafts 312 and rotatably arranged in the gear grooves 205;

[0063] The end of the first rack 34 is fixed on the moving end of the first electric cylinder 32 and is always engaged with the driving gear 36;

[0064] The end of the second rack 35 is fixed on the moving end of the second electric cylinder 33 and is always engaged with the circumferential teeth 207;

[0065] The number of the solar wings 4 is two, and they are respectively fixedly arranged on the driving mechanism 4;

[0066] The solar wing 4 includes: a first substrate 41, a second substrate 42, and a third substrate 43;

[0067] The first substrate 41 is fixedly arranged on the drive shaft 31;

[0068] As Figure 7 、 8 shown, a support plate 411 is provided at the end of the first substrate 41;

[0069] A connecting rotating cylinder 412 is provided on the side surface of the first substrate 41;

[0070] A fixed rotating cylinder 413 is provided on the side surface of the support plate 411, and the fixed rotating cylinder 413 is sleeved on the limiting post 315 and rotatably arranged in the limiting groove 314;

[0071] An electromagnet two 414 is provided on the side surface of the support plate 411 and adjacent to the fixed rotating cylinder 413;

[0072] An electromagnet block one 415 is provided on the other side surface of the support plate 411;

[0073] An electromagnet three 416 is provided on the end surface of the first substrate 41;

[0074] The second substrate 42 is rotatably arranged on the first substrate 41;

[0075] As Figure 9 shown, a connecting rotating cylinder two 421 is arranged on the side surface of the second substrate 42;

[0076] On the other side surface of the second substrate 42, a mating shaft one 422 is arranged, and the mating shaft one 422 is rotatably arranged in the connecting rotating cylinder one 412;

[0077] An electromagnet five 423 is arranged on the end surface of the second substrate 42;

[0078] The number of the second substrates 42 is two (not limited to two, the number of the second substrates 42 of the solar wing 4 can be multiple, depending on the combined power consumption requirements). At a position on the side surface of the second substrate 42 adjacent to the connecting rotating cylinder two 421, an electromagnetic block two 424 is arranged. The electromagnetic block two 424 can limit the relative rotation angle between the second substrate 42 and the first substrate 41, and can also fix the positions of the second substrate 42 and the first substrate 41;

[0079] The third substrate 43 is connected to the last second substrate 42;

[0080] As Figure 10 shown, a mating shaft two 431 is arranged on the side surface of the third substrate 43, and the mating shaft two 431 is rotatably arranged in the connecting rotating cylinder two 421;

[0081] An electromagnet four 432 is arranged on the end surface of the third substrate 43.

[0082] The working principle of the present invention: The initial state of the whole device is as Figure 1 shown. After the microsatellite successfully enters the space orbit, the solar wing 4 needs to be deployed; First, turn on the electromagnet four 432 of the third substrate 43 and the corresponding electromagnet one 104 on the base 1, so that the acting forces of the electromagnet four 432 and the electromagnet one 104 are opposite (the solar wing 4 is attracted to each other when not deployed). The third substrate 43 will bounce outwards under the mutual acting forces of the electromagnet four 432 and the electromagnet one 104. When the side surface of the third substrate 43 contacts the electromagnetic block two 424 of the adjacent second substrate 42, the electromagnetic block two 424 is turned on to limit the third substrate 43. From the Figure 1 shown motion state to the motion state as Figure 11 shown; Secondly, the electromagnets five 423 on the second substrate 42 act on the corresponding electromagnets one 104 respectively to generate a mutual acting force, and the second substrate 42 is bounced off in sequence. When the side surface of the adjacent second substrate 42 contacts the electromagnet block two 424 of the second substrate 42, the electromagnet block two 424 is activated to fix the two adjacent second substrates 42. From the Figure 11 shown motion state to the motion state as shown in Figure 12 and then to the motion state as shown in Figure 13 ; Then, a mutual acting force is generated between the electromagnet three 416 on the first substrate 41 and the corresponding electromagnet one 104, and the first substrate 41 is bounced off. When the electromagnet two 414 on the first substrate 41 contacts the end face of the drive shaft 31, the electromagnet two 414 is activated to attract the drive shaft 31 and fix the first substrate 41 at the same time. At this time, the whole device moves from the Figure 13 shown motion state to the motion state as shown in Figure 14 ; Finally, after the solar wing is deployed, the electric cylinder one 32 is activated. The electric cylinder one 32 drives the drive gear 36 to rotate through the rack one 34, and the drive gear 36 drives the whole solar wing 4 to flip through the drive shaft 31. At this time, the whole device moves from the Figure 14 motion state to the motion state as shown in Figure 2 . At the same time, the electric cylinder two 33 is activated. The electric cylinder two 33 drives the whole turntable 2 to flip radially through the cooperation of the rack two 35 and the circumferential teeth 207, and drives the whole solar wing to rotate axially at the same time. The angle adjustment of the above solar wing can be adjusted in real time according to the different incident angles of sunlight. At this time, the motion process of the whole device is completed.

Claims

1. A dual-degree-of-freedom solar wing attitude control device suitable for micro-satellites, characterized in that: include: A base column (101) is provided in the middle of the base (1), end seats (102) are provided at both ends of the base column (101), four symmetrical support columns (103) are provided on the end surface of the end seat (102), an electromagnet (104) is provided in the middle of the side surface of the support column (103), a fixing plate (105) is provided on the side surface of two upper adjacent support columns (103), a limiting ring (106) is provided on the outer circumferential surface of the base column (101), a rotating seat (2) is rotatably arranged on the base (1), a fixing cylinder (201) is provided in the middle of the rotating seat (2), a support seat (202) is provided on the outer circumferential surface of the fixing cylinder (201), two limiting holes (203) are symmetrically provided at the center of the side surface of the support seat (202), and an axis is provided at the center of the bottom surface of the limiting hole (203). A hole (204) is provided at the end of the shaft hole (204), a gear groove (205) is provided at the end of the upper end of the fixing cylinder (201), a peripheral tooth (207) is provided on the outer circumferential surface, a matching hole (206) is provided on the inner side of the peripheral tooth (207), a fixing plate 2 (208) is provided on the outer circumferential surface of the lower end of the peripheral tooth (207), a driving mechanism (3) is fixedly arranged inside the base (1), the driving mechanism (3) comprises a driving shaft (31), an electric cylinder 1 (32), an electric cylinder 2 (33), a rack 1 (34), a rack 2 (35) and a driving gear (36), the number of the solar wings (4) is two, which are respectively fixedly arranged on the driving mechanism (3), and the solar wings (4) comprise a first substrate (41), a second substrate (42) and a third substrate (43).

2. A dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 1, characterized in that: There are two drive shafts (31), which are rotatably disposed in the limiting holes (203) respectively; a fixing platform (311) is provided at one end of the drive shaft (31), and the fixing platform (311) is rotatably disposed in the limiting hole (203); a rotating shaft (312) is provided at the other end of the drive shaft (31), and the rotating shaft (312) is rotatably disposed in the shaft hole (204).

3. A dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 2, characterized in that: A positioning surface (313) is provided on the side of the fixing platform (311), a limiting groove (314) is provided on the end surface of the fixing platform (311), and a limiting column (315) is provided on the end surface of the limiting groove (314).

4. The dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 1, characterized in that: The number of the electric cylinders one (32) is two, each of which is fixedly mounted on the fixing plate two (208), and the electric cylinder two (33) is fixedly mounted on the fixing plate one (105).

5. The dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 1, characterized in that: The number of the driving gears (36) is two, which are respectively fixedly arranged at the ends of the rotating shaft (312) and rotatably arranged in the gear groove (205); the end of the rack one (34) is fixed at the moving end of the electric cylinder one (32), and the rack one (34) is meshed with the driving gear (36); the end of the rack two (35) is fixed at the moving end of the electric cylinder two (33), and the rack two (35) is meshed with the peripheral teeth (207).

6. The dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 1, characterized in that: The first substrate (41) is fixedly arranged on the driving shaft (31); a support plate (411) is arranged at the end of the first substrate (41); a connecting drum (412) is arranged on the side of the first substrate (41); a fixed drum (413) is arranged on the side of the support plate (411); the fixed drum (413) is sleeved on the limiting column (315) and rotatably arranged in the limiting groove (314).

7. The dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 6, characterized in that: A second electromagnet (414) is provided on the side of the support plate (411), an electromagnet block (415) is provided on the other side of the support plate (411), and a third electromagnet (416) is provided on the end surface of the first substrate (41).

8. The dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 1, characterized in that: The second substrate (42) is rotatably arranged on the first substrate (41); a connecting drum 2 (421) is provided on the side of the second substrate (42); a matching shaft 1 (422) is provided on the other side of the second substrate (42); an electromagnet 5 (423) is provided on the end face of the second substrate (42); and an electromagnet block 2 (424) is provided on the side of the second substrate (42) and adjacent to the connecting drum 2 (421).

9. A dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 8, characterized in that: The third substrate (43) is connected to the last second substrate (42), and a second matching shaft (431) is provided on the side of the third substrate (43). The second matching shaft (431) is rotatably arranged in the second connecting drum (421), and an electromagnet fourth (432) is provided on the end surface of the third substrate (43).

10. A dual-degree-of-freedom solar wing attitude control device suitable for a micro-satellite according to claim 9, characterized in that: The polarity of the electromagnet one (104) is opposite to that of the electromagnet five (423) and the electromagnet four (432).

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