A two-degree-of-freedom solar wing attitude control device suitable for microsatellites

Abstract

The application relates to the technical field of satellites, in particular to a two-degree-of-freedom solar wing attitude control device suitable for microsatellites, which comprises the following: a base column is arranged in the middle of a base, end seats are arranged at the two ends of the base column, four symmetrical supporting columns are arranged on the end face of the end seat, electromagnets I are arranged in the middle of the side face of the supporting columns, fixed plates I are arranged on the side face of the upper two adjacent supporting columns, a limiting ring is arranged on the outer circumferential surface of the base column, a rotating seat is rotatably arranged on the base, a fixed cylinder is arranged in the middle of the rotating seat, a supporting seat is arranged on the outer circumferential surface of the fixed cylinder, two limiting holes are symmetrically arranged in the side face of the supporting seat, an axle hole is arranged in the center of the bottom face of the limiting hole, the adjustment of the solar wing is controlled by adopting the mode of combining magnetic control with machinery, two-dimensional tracking of the incident angle of sunlight can be realized, the accurate tracking capability makes the solar wing always face the sun at the best angle, and the utilization efficiency of solar energy is further improved.

Description

Technical Field

[0001] This invention relates to the field of satellite technology, and more specifically to a dual-degree-of-freedom solar array attitude control device suitable for microsatellites. Background Technology

[0002] Microsatellites offer advantages such as small size, light weight, low cost, and rapid development. A significant difference from traditional satellites is their modular design and assembly approach. This facilitates satellite testing and launch, ensures technological continuity and maturity, and reduces costs. However, a crucial issue remains in the development of microsatellites—energy constraints on their payload capacity. The power requirements of payloads are constantly increasing in microsatellite technology verification and applications, but current solar panel installation methods limit the photovoltaic power generation of microsatellites, failing to meet the demands of high-power payloads.

[0003] The photovoltaic (PV) capacity of solar arrays is primarily influenced by factors such as the effective working area of ​​the solar panel and the angle of sunlight incidence. Current installation methods for microsatellite solar arrays mainly include body-mounted surface-mount, foldable deployment, and foldable deployment single-axis directional types. Existing patents use solar arrays with a single degree of freedom design, which cannot achieve two-dimensional tracking of the sunlight incidence angle and therefore cannot maximize the PV capacity of the solar panel. Summary of the Invention

[0004] Therefore, this invention addresses the above-mentioned problems. It employs a body-mounted surface-mount solar array installation method, allowing the solar array to be installed in a circular pattern around the surface of a microsatellite. This significantly increases the solar irradiation area when the solar array is deployed, meeting the demands of high-power loads. Furthermore, it uses magnetic and mechanical control to adjust the solar array, achieving two-dimensional tracking of the solar radiation incident angle, thus maximizing the photovoltaic power output of the solar panel.

[0005] A dual-degree-of-freedom solar panel attitude control device suitable for microsatellites includes: a base column in the middle of a base, end seats at both ends of the base column, four symmetrical support columns on the end faces of the end seats, an electromagnet in the middle of the side of the support column, a fixing plate on the side of the two adjacent upper support columns, a limiting ring on the outer circumference of the base column, a rotating seat rotatably mounted on the base, a fixing cylinder in the middle of the rotating seat, a support seat on the outer circumference of the fixing cylinder, two limiting holes symmetrically arranged on the side of the support seat, a shaft hole at the center of the bottom surface of the limiting hole, a gear groove at the end of the shaft hole, a tooth on the outer circumference of the upper end of the fixing cylinder, a mating hole on the inner side of the tooth, a fixing plate on the outer circumference of the lower end of the tooth, a drive mechanism fixedly mounted inside the base, the drive mechanism including a drive shaft, an electric cylinder, an electric cylinder, a rack, a rack, and a drive gear, and two solar panels, which are fixedly mounted on the drive mechanism respectively, each solar panel including a first base plate, a second base plate, and a third base plate.

[0006] Preferably, there are two drive shafts, which are rotatably disposed in the limiting hole. The end of the drive shaft is provided with a fixed platform, which is rotatably disposed in the limiting hole. The other end of the drive shaft is provided with a rotating shaft, which is rotatably disposed in the shaft hole.

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

[0008] Preferably, there are two electric cylinders, which are fixedly mounted on the fixed plate, and the electric cylinders are fixedly mounted on the fixed plate.

[0009] Preferably, there are two drive gears, which are fixedly mounted at the end of the rotating shaft and rotatably mounted in the gear groove. The end of rack one is fixed to the moving end of electric cylinder one and meshes with the drive gear. The end of rack two is fixed to the moving end of electric cylinder two and meshes with the peripheral teeth.

[0010] Preferably, the first substrate is fixedly mounted on the drive shaft, the end of the first substrate is provided with a support plate, the side of the first substrate is provided with a connecting rotating cylinder, the side of the support plate is provided with a fixed rotating cylinder, the fixed rotating cylinder is sleeved on the limiting post and rotatably mounted in the limiting groove.

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

[0012] Preferably, the second substrate is rotatably mounted on the first substrate, a connecting rotating cylinder is provided on one side of the second substrate, a mating shaft is provided on the other side of the second substrate, an electromagnet is provided on the end face of the second substrate, and an electromagnetic block is provided on the side of the second substrate adjacent to the connecting rotating cylinder.

[0013] Preferably, the third substrate is connected to the last second substrate, the side of the third substrate is provided with a mating shaft two, the mating shaft two is rotatably disposed in the connecting rotating cylinder two, and the end face of the third substrate is provided with an electromagnet four.

[0014] Preferably, the first electromagnet has the opposite polarity to the fifth and fourth electromagnets.

[0015] Beneficial effects of this invention:

[0016] 1. This invention significantly increases the solar irradiation area when the solar panels are deployed by using a circular mounting method with surface-mounted solar panels. This design maximizes the capture of sunlight, thereby significantly improving the photovoltaic power output of the solar panels. This is particularly important for meeting the high-power payload requirements of microsatellites, ensuring sufficient power support during satellite operation, extending the satellite's lifespan, and improving mission reliability.

[0017] 2. This invention employs a combination of magnetic and mechanical control to adjust the solar array, enabling two-dimensional tracking of the angle of sunlight incidence. This precise tracking capability ensures the solar array always faces the sun at the optimal angle, further improving solar energy utilization efficiency. In this way, even with changes in the satellite's orbital position or the relative position of the sun, the solar array can continuously and efficiently convert solar energy into electrical energy, thereby maximizing photovoltaic power generation and improving the satellite's overall energy management efficiency. Attached Figure Description

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

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

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

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

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

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

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

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

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

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

[0028] Figure 11 This is a schematic diagram of the motion state of the present invention. Figure 1 .

[0029] Figure 12 This is a schematic diagram of the motion state of the present invention. Figure 2 .

[0030] Figure 13 This is a schematic diagram of the motion state of the present invention. Figure 3 .

[0031] Figure 14 This is a schematic diagram of the motion state of the present invention. Figure 4 .

[0032] Explanation of reference numerals in the attached figures:

[0033] 1. Base; 101. Base column; 102. End seat; 103. Support column; 104. Electromagnet one; 105. Fixing plate one; 106. Limiting ring; 2. Rotary seat; 201. Fixing cylinder; 202. Support seat; 203. Limiting hole; 204. Shaft hole; 205. Gear groove; 206. Mating hole; 207. Peripheral gear; 208. Fixing plate two; 3. Drive mechanism; 31. Drive shaft; 311. Fixing platform; 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. Drive Gear; 4. Solar Wing; 41. First Base Plate; 411. Support Plate; 412. Connecting Rotary Cylinder 1; 413. Fixed Rotary Cylinder; 414. Electromagnet 2; 415. Electromagnetic Block 1; 416. Electromagnet 3; 42. Second Base Plate; 421. Connecting Rotary Cylinder 2; 422. Mating Shaft 1; 423. Electromagnet 5; 424. Electromagnetic Block 2; 43. Third Base Plate; 431. Mating Shaft 2; 432. Electromagnet 4. Detailed Implementation

[0034] Preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, which will make these embodiments readily achievable by those skilled in the art. However, the present invention can be implemented in various different forms, and therefore the present invention is not limited to the embodiments described below. In addition, for the sake of clearer description of the present invention, components not connected to the invention will be omitted from the drawings.

[0035] like Figure 1 , 2 As shown in Figures 1 and 3, a dual-degree-of-freedom solar array attitude control device suitable for microsatellites includes: a base 1, a rotating base 2, a drive mechanism 3, and a solar array 4.

[0036] The base 1 is the supporting component of the entire structure;

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

[0038] The base column 101 is provided with end seats 102 at both ends;

[0039] The end face of the end seat 102 is provided with four symmetrical support columns 103;

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

[0041] The two adjacent upper support columns 103 are provided with fixing plates 105 on their sides;

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

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

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

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

[0046] The support base 202 is provided with two limiting holes 203 symmetrically arranged on the side center;

[0047] The bottom center of the limiting hole 203 is provided with a shaft hole 204;

[0048] The end of the shaft hole 204 is provided with a gear groove 205;

[0049] The upper end of the fixed cylinder 201 is provided with circumferential teeth 207 on its outer circumferential surface;

[0050] The inner side of the peripheral tooth 207 is provided with a mating hole 206;

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

[0052] The drive mechanism 3 is fixedly installed inside the base 1;

[0053] The drive mechanism 3 includes: a drive shaft 31, an electric cylinder 32, an electric cylinder 33, a rack 34, a rack 35, and a drive gear 36.

[0054] There are two drive shafts 31, which are rotatably disposed in the limiting hole 203;

[0055] like Figure 6 As shown, the end of the drive shaft 31 is provided with a fixed platform 311, which is rotatably disposed in the limiting hole 203.

[0056] The other end of the drive shaft 31 is provided with a rotating shaft 312, which is rotatably disposed in the shaft hole 204.

[0057] The side of the fixed platform 311 is provided with a positioning surface 313 for determining the rotation position of the drive shaft 31.

[0058] The end face of the fixed platform 311 is provided with a limiting groove 314;

[0059] The end face of the limiting groove 314 is provided with a limiting post 315;

[0060] There are two electric cylinders 32, which are fixedly mounted on the fixing plate 208.

[0061] The electric cylinder 33 is fixedly mounted on the fixing plate 105.

[0062] The number of drive gears 36 is two, which are fixedly installed at the end of the rotating shaft 312 and rotatably installed in the gear groove 205.

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

[0064] The end of the rack 2 35 is fixed to the moving end of the electric cylinder 2 33 and is always engaged with the peripheral teeth 207;

[0065] The solar panels 4 are two in number and are fixedly mounted on the drive mechanism 4 respectively;

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

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

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

[0069] The first substrate 41 has a connecting rotating cylinder 412 on its side;

[0070] The side of the support plate 411 is provided with a fixed rotating cylinder 413, which is sleeved on the limiting post 315 and rotatably disposed in the limiting groove 314.

[0071] An electromagnet 414 is provided on the side of the support plate 411 and at a position adjacent to the fixed rotating cylinder 413.

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

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

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

[0075] like Figure 9 As shown, the second substrate 42 has a connecting rotating cylinder 421 on its side;

[0076] The other side of the second substrate 42 is provided with a mating shaft 422, which is rotatably disposed inside the connecting rotating cylinder 412;

[0077] The end face of the second substrate 42 is provided with an electromagnet 5 423;

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

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

[0080] like Figure 10 As shown, the third substrate 43 is provided with a mating shaft 431 on its side, and the mating shaft 431 is rotatably disposed inside the connecting rotating cylinder 421.

[0081] The end face of the third substrate 43 is provided with an electromagnet 432.

[0082] Working principle of this invention: The initial state of the entire device is as follows Figure 1 As shown, once the microsatellite has successfully reached its space orbit, the solar panels 4 need to be deployed. First, the electromagnet 432 on the third substrate 43 and the corresponding electromagnet 104 on the base 1 are activated, so that the electromagnets 432 and 104 exert opposite forces (when the solar array 4 is deployed, they attract each other). The third substrate 43 will spring outward under the interaction force of the electromagnets 432 and 104. When the side of the third substrate 43 contacts the electromagnetic block 424 of the adjacent second substrate 42, the electromagnetic block 424 is activated, limiting the position of the third substrate 43. Figure 1 The motion state shown moves to, as Figure 11 The motion state shown; Secondly, the electromagnets 5 and 423 of the second substrate 42 interact with their corresponding electromagnets 1 and 104, generating an interaction force. The second substrate 42 is then sequentially pushed away. When the side of an adjacent second substrate 42 contacts the electromagnetic block 424 of the second substrate 42, the electromagnetic block 424 is activated, fixing the two adjacent second substrates 42 in place. Figure 11 The motion state shown moves to, as Figure 12 The motion state shown, then the motion to such a state Figure 13 The motion state shown; Then, an interaction force is generated between the electromagnet 3 416 on the first substrate 41 and the corresponding electromagnet 1 104, causing the first substrate 41 to be repelled. When the electromagnet 2 414 on the first substrate 41 contacts the end face of the drive shaft 31, the electromagnet 2 414 is activated, attracting the drive shaft 31 and simultaneously fixing the first substrate 41. At this time, the entire device is... Figure 13 The motion state shown moves to, as Figure 14 The motion state shown; Finally, after the solar array deploys, electric cylinder 32 is activated. Electric cylinder 32 drives drive gear 36 via rack 34, which in turn drives the entire solar array 4 to rotate via drive shaft 31. At this point, the entire device... Figure 14 The state of motion is like... Figure 2 The motion state shown is simultaneously activated by electric cylinder 2 33. Electric cylinder 2 33, through the cooperation of rack 2 35 and peripheral gear 207, drives the entire rotating seat 2 to rotate radially, and at the same time drives the entire solar fin to rotate axially. The angle adjustment of the solar fin can be adjusted in real time according to different incident angles of sunlight. At this time, the motion process of the entire device is completed.

Claims

1. A dual-degree-of-freedom solar array attitude control device suitable for microsatellites, 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 face of the end seat (102). An electromagnet (104) is provided in the middle of the side of the support column (103). A fixing plate (105) is provided on the side of the two adjacent support columns (103) at the top. A limiting ring (106) is provided on the outer circumference of the base column (101). A rotating seat (2) is rotatably mounted 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 circumference of the fixing cylinder (201). The support (202) has two symmetrically arranged limiting holes (203) on its side. The bottom surface of the limiting hole (203) has a shaft hole (204) at its center. The end of the shaft hole (204) has a gear groove (205). The upper end of the fixed cylinder (201) has a toothed ring (207) on its outer circumference. The inner side of the toothed ring (207) has a mating hole (206). The lower end of the toothed ring (207) has a fixing plate (208) on its outer circumference. The drive mechanism (3) is fixedly arranged inside the base (1). The drive mechanism (3) includes a drive shaft (31), an electric cylinder (32), an electric cylinder (33), and a rack. (34), rack two (35) and drive gear (36), the number of drive shafts (31) is two, respectively rotatably set in the limiting hole (203), the end of the drive shaft (31) is provided with a fixed platform (311), the fixed platform (311) is rotatably set in the limiting hole (203), the other end of the drive shaft (31) is provided with a rotating shaft (312), the rotating shaft (312) is rotatably set in the shaft hole (204), the side of the fixed platform (311) is provided with a positioning surface (313), the end face of the fixed platform (311) is provided with a limiting groove (314), the end face of the limiting groove (314) is provided with a limiting groove (314). The number of solar panels (4) is two, which are fixedly mounted on the drive mechanism (3). The solar panels (4) include a first substrate (41), a second substrate (42) and a third substrate (43). The first substrate (41) is fixedly mounted on the drive shaft (31). The end of the first substrate (41) is provided with a support plate (411). The side of the first substrate (41) is provided with a connecting rotating cylinder (412). The side of the support plate (411) is provided with a fixing rotating cylinder (413). The fixing rotating cylinder (413) is sleeved on the limiting post (315) and rotated in the limiting groove (314).

2. The dual-degree-of-freedom solar array attitude control device for microsatellites according to claim 1, characterized in that: There are two electric cylinders (32), which are fixedly mounted on the second fixing plate (208) and the second electric cylinder (33) is fixedly mounted on the first fixing plate (105).

3. The dual-degree-of-freedom solar array attitude control device for microsatellites according to claim 1, characterized in that: There are two drive gears (36), which are fixedly installed at the end of the rotating shaft (312) and rotatably installed in the gear groove (205). The end of rack one (34) is fixed to the moving end of electric cylinder one (32), and rack one (34) meshes with drive gear (36). The end of rack two (35) is fixed to the moving end of electric cylinder two (33), and rack two (35) meshes with peripheral teeth (207).

4. The dual-degree-of-freedom solar array attitude control device for microsatellites according to claim 1, characterized in that: The support plate (411) has an electromagnet two (414) on one side, an electromagnet one (415) on the other side, and an electromagnet three (416) on the end face of the first substrate (41).

5. The dual-degree-of-freedom solar array attitude control device for microsatellites according to claim 1, characterized in that: The second substrate (42) is rotatably mounted on the first substrate (41). A connecting rotating cylinder (421) is provided on the side of the second substrate (42). A mating shaft (422) is provided on the other side of the second substrate (42). An electromagnet (423) is provided on the end face of the second substrate (42). An electromagnetic block (424) is provided on the side of the second substrate (42) and adjacent to the connecting rotating cylinder (421).

6. The dual-degree-of-freedom solar array attitude control device for microsatellites according to claim 5, characterized in that: The third substrate (43) is connected to the last second substrate (42). The side of the third substrate (43) is provided with a mating shaft two (431), which is rotatably disposed in the connecting rotating cylinder two (421). The end face of the third substrate (43) is provided with an electromagnet four (432).

7. A dual-degree-of-freedom solar array attitude control device suitable for microsatellites according to claim 6, characterized in that: The electromagnet one (104) has the opposite polarity to the electromagnet five (423) and electromagnet four (432).

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