Solar wing and satellite configuration comprising same

Abstract

The utility model provides a solar wing and a satellite configuration comprising the same, the solar wing can be folded or unfolded on the side part of a satellite body, the solar wing comprises a plurality of adjusting assemblies and a plurality of substrates arranged in sequence, every two adjacent substrates are rotatably connected through the adjusting assembly, and the satellite body is rotatably connected with the corresponding substrate through the adjusting assembly; the solar wing is arranged on one side of the satellite body. The beneficial effects of the utility model are that the solar wing can be folded at the side part of the satellite body so as to reduce the folding envelope of the solar wing and the occupation of satellite resources, and the solar wing is simple in structure, small in size, light in weight, extensible and low in manufacturing cost.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of space technology, especially relates to a solar wing and a satellite configuration comprising the solar wing. BACKGROUND

[0002] In the prior art, the solar wing is one of the most important single machines in the satellite subsystem, has certain structure supporting function and unfolding function, mainly provides structure support for the solar cell, ensures that it is not damaged in the on-orbit and launching stage, and normally works. With the rapid development of commercial space satellite technology, miniaturization, light weight and low cost of satellites are major trends in future space development, and the traditional satellite solar wing structure product has large envelope, heavy weight, high cost and complex overall structure, which has been difficult to meet the application requirements of current commercial microsatellites. There are technical problems of large envelope, heavy weight and high cost of the solar wing product. SUMMARY

[0003] To solve the above technical problems, the utility model provides a solar wing and a satellite configuration comprising the solar wing, which is especially suitable for the demand of miniaturization, light weight and low cost of microsatellites.

[0004] The technical scheme adopted by the utility model is: a solar wing can be folded or unfolded on the side of a satellite body, comprising a plurality of adjusting assemblies and a plurality of sequentially arranged substrates, each adjacent substrate is rotationally connected through the adjusting assembly, and the satellite body is rotationally connected with the corresponding substrate through the adjusting assembly.

[0005] Further, when the solar wing is folded, the plurality of substrates are sequentially stacked on the side of the satellite body, and the substrate farthest from the satellite body is provided with a solar cell on the side away from the satellite body.

[0006] Further, when the solar wing is unfolded, a first included angle is formed between the satellite body and its adjacent substrate, and a second included angle is formed between each adjacent substrate, the first included angle is 90°, and the second included angle is 180°.

[0007] Further, the utility model further comprises a compression release mechanism, the compression release mechanism comprises a compression part, when the solar wing is folded, the compression part can be arranged through the plurality of substrates, and the two ends of the compression part are connected with the satellite body and the substrate farthest from the satellite body respectively.

[0008] Further, the utility model further comprises an unfolding detection mechanism, the unfolding detection mechanism comprises a micro switch connected with the satellite body, when the solar wing is unfolded, the micro switch can be triggered by the corresponding substrate to prompt.

[0009] Further, the adjusting assembly comprises a central shaft, an adjusting spring, a first hinge unit and a second hinge unit corresponding to the first hinge unit, the first hinge unit is arranged on the satellite body or the base plate, the second hinge unit is rotationally connected with the first hinge unit through the central shaft and arranged on the corresponding base plate, and the adjusting spring is sleeved on the central shaft and connected with the first hinge unit and the second hinge unit.

[0010] Further, each base plate comprises a polyimide film, an upper carbon fiber grid skin, an aluminum honeycomb core and a lower carbon fiber grid skin, the polyimide film is formed on the surface of the upper carbon fiber grid skin, and the aluminum honeycomb core is bonded between the upper carbon fiber grid skin and the lower carbon fiber grid skin.

[0011] Further, the adjusting assembly comprises a central shaft, an adjusting spring, a first hinge unit and a second hinge unit corresponding to the first hinge unit, the first hinge unit is arranged on the satellite body or the base plate, the second hinge unit is rotationally connected with the first hinge unit through the central shaft and arranged on the corresponding base plate, and the adjusting spring is sleeved on the central shaft and connected with the first hinge unit and the second hinge unit.

[0012] Further, the adjusting assembly comprises a central shaft, an adjusting spring, a first hinge unit and a second hinge unit corresponding to the first hinge unit, the first hinge unit is arranged on the satellite body or the base plate, the second hinge unit is rotationally connected with the first hinge unit through the central shaft and arranged on the corresponding base plate, and the adjusting spring is sleeved on the central shaft and connected with the first hinge unit and the second hinge unit.

[0013] A satellite configuration comprises a solar wing as described above, and the solar wing is arranged on one side of the satellite body.

[0014] The utility model discloses have the advantages and positive effect is: because adopting above -mentioned technical scheme, solar wing can be folded in satellite body side portion to reduce solar wing folding envelope, satellite resource occupation, with simple structure, miniaturization, light weight, extensible and low -cost advantage such as. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is the front structure schematic diagram of one embodiment of the utility model when unfolding;

[0016] Figure 2 It is the back structure schematic diagram of one embodiment of the utility model when unfolding;

[0017] Figure 3 It is convenient for watching Figure 1 It is the partial enlarged schematic diagram of one linkage structure;

[0018] Figure 4 It is the enlarged schematic diagram of another linkage structure in one embodiment of the utility model;

[0019] Figure 5 It is the structure schematic diagram of one embodiment of the utility model when folding;

[0020] Figure 6 is for convenient viewing Figure 5 is a partial enlarged view of one linkage structure in the embodiment of the present application;

[0021] Figure 7 is a schematic view of another linkage structure when folding in the embodiment of the present application;

[0022] Figure 8 is a schematic view of the adjusting assembly in the embodiment of the present application;

[0023] Figure 9 is a longitudinal section schematic view of the adjusting assembly in the embodiment of the present application;

[0024] Figure 10 is a schematic view of the micro switch in the embodiment of the present application;

[0025] Figure 11 is a schematic view of the base plate structure in the embodiment of the present application;

[0026] Figure 12 is a longitudinal section schematic view of the base plate structure in the embodiment of the present application;

[0027] In the figure:

[0028] 1, satellite body 3, adjusting assembly 6, micro switch

[0029] 21, inner base plate 22, middle base plate 23, outer base plate

[0030] 2-1, polyimide film 2-2, upper layer carbon fiber grid 2-3, aluminum honeycomb core

[0031] skin

[0032] 2-4, lower layer carbon fiber grid 2-5, adhesive 31, first hinge unit

[0033] skin

[0034] 32, second hinge unit 33, center shaft 34, adjusting spring

[0035] 41, pressing part 42, pressing seat 43, pressing cap

[0036] 44, pressing bushing 51, first roller 52, second roller

[0037] 53, guide part 54, linkage rope DETAILED DESCRIPTION

[0038] The embodiments of the present application will be described below in conjunction with the drawings, and the described embodiments are only some of the embodiments of the present application, but not all the embodiments.

[0039] The embodiments of the present application are described below in detail, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements having the same or similar functions throughout. The embodiments described below by reference to the drawings are exemplary only, and are merely intended to explain the present application, and cannot be understood as limiting the present application.

[0040] In the description of the present application, it should be understood that the terms "mounting", "connecting", "fixing" and the like should be interpreted in a broad sense, which can be direct connection, mounting or fixing, or indirect connection, mounting or fixing, and the present application does not limit this.

[0041] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the structure or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0042] As shown in Figures 1 to 12 The present application provides a solar wing and a satellite configuration comprising the same, which can be folded on the side of a satellite body, can reduce the folding envelope of the solar wing and the occupation of satellite resources, has a simple structure, is small, light, low-cost and expandable to be applicable to micro-satellite applications.

[0043] The solar wing can be folded or unfolded on the side of the satellite body 1, and the solar wing comprises a plurality of adjusting assemblies 3 and a plurality of sequentially arranged substrates, each adjacent substrate is rotationally connected through the adjusting assembly 3, and the satellite body 1 is rotationally connected with the corresponding substrate through the adjusting assembly 3. In this embodiment, the number of substrates is three, which are an inner substrate 21, a middle substrate 22 and an outer substrate 23; in other embodiments, the number of substrates can be adjusted or expanded as required, the patch area of the substrate is increased, and thus the power supply of the solar cell is increased, and the folding can ensure a small folding envelope and reduce the occupation of space resources. In this embodiment, the satellite body 1 and the inner substrate 21, the inner substrate 21 and the middle substrate 22, and the middle substrate 22 and the outer substrate 23 are connected and locked through the adjusting assembly 3.

[0044] In the embodiment, when the solar wing is folded, the plurality of substrates are sequentially stacked on the side of the satellite body 1, the solar wing is folded into a plate-shaped configuration, and the side of the substrate farthest from the satellite body 1 is provided with a solar cell. In the embodiment, in the folded state of the solar wing, the back of the inner substrate 21 is stacked on the satellite body 1, the inner substrate 21 and the middle substrate 22 are face-to-face, the middle substrate 22 and the outer substrate 23 are back-to-back, and the outer substrate 23 is outwardly provided with a solar cell to ensure that the satellite can still be powered in the folded state. That is, after the satellite is launched into orbit, if the solar wing cannot be successfully unfolded due to a fault, the satellite can still output a certain amount of power to ensure the operation of the on-board motor; the plurality of substrates can be sequentially stacked to ensure a small folding envelope.

[0045] In the embodiment, when the solar wing is unfolded, a first included angle is formed between the satellite body 1 and the adjacent substrate, and a second included angle is formed between each adjacent substrate. The first included angle and the second included angle can be set according to actual needs. In the embodiment, the first included angle is 90°, and the second included angle is 180°. After the solar wing is unfolded, a "I" shape perpendicular to the satellite body 1 can be formed.

[0046] In the embodiment, the pressing release mechanism further includes a pressing member 41, which is arranged on the substrate farthest from the satellite body 1 and can be connected with the satellite body 1 to be fixed when the solar wing is folded and stored on the side of the satellite body 1. The pressing release mechanism further includes a pressing seat 42 and a pressing cap 43. The pressing seat 42 is mounted on the satellite body 1 to be connected with the pressing member 41. The substrate farthest from the satellite body 1 is provided with a mounting hole, a pressing bushing 44 is mounted in the mounting hole, the pressing member 41 is mounted in the mounting hole and is connected with the outermost substrate through the pressing bushing 44, and the pressing cap 43 is also mounted on the outermost substrate to limit the pressing member 41, preventing the pressing member 41 from falling out of the mounting hole during unfolding of the solar wing. In the embodiment, the pressing cap 43 is mounted on the outer substrate 23 through a gasket and a screw. After the pressing member 41 passes through the plurality of substrates, the pressing member 41 is connected with the pressing seat 42, which can make full use of the resources between the substrates and reduce the occupied space. The design of the pressing release mechanism can press the plurality of substrates against the side wall of the satellite body 1 in the folded state of the solar wing. When the solar wing needs to be unfolded, the pressing member 41 can be disconnected by a disconnecting device connected with the pressing seat 42. Compared with the traditional explosive device, the unlocking impact is small, the maintenance and transportation are convenient, and the cost is low. The design, installation, and unlocking mode of the pressing release mechanism not only reduce the space resources between the satellite body 1 and the substrates and between the adjacent substrates, but also reduce the folding envelope of the solar wing without affecting the installation of the equipment and single machines between the satellite body 1 and the inner substrate 21.

[0047] The embodiment further comprises a deployment detection mechanism, which comprises a micro switch 6 connected with the satellite body 1. When the solar wing is deployed, the micro switch 6 can be triggered by the corresponding substrate to prompt. After the satellite is launched into orbit, the solar wing is deployed after receiving the unlocking instruction. The solar wing can be triggered with the micro switch 6 after being deployed to the position. The micro switch 6 can feed back the solar wing deployment to the position indication through the satellite telemetry control circuit after being triggered, thereby providing a deployment to the position signal, ensuring that the solar cell normally provides power for the satellite. The embodiment adopts a mechanical contact type structure, accesses the satellite body 1 through the solar wing cable, and feeds back the in-place indication by the system telemetry circuit, thereby improving the accuracy of determining the solar wing deployment. In the embodiment, the substrate for triggering the micro switch 6 is an inner substrate 21.

[0048] In the embodiment, the adjusting assembly 3 comprises a center shaft 33, an adjusting spring 34, a first hinge unit 31, and a second hinge unit 32 corresponding to the first hinge unit 31. The first hinge unit 31 is arranged on the satellite body 1 or the substrate. The second hinge unit 32 is rotationally connected with the first hinge unit 31 through the center shaft 33 and arranged on the corresponding substrate. The adjusting spring 34 is sleeved on the center shaft 33 and connected with the first hinge unit 31 and the second hinge unit 32. In the embodiment, the first hinge unit 31 is arranged on the satellite body 1 / inner substrate 21 / middle substrate 22. The second hinge unit 32 is arranged on the inner substrate 21 / middle substrate 22 / outer substrate 23 and corresponds to the first hinge unit 31. The corresponding first hinge unit 31 and second hinge unit 32 can form a coaxial structure through the center shaft 33. The adjusting spring 34 adopts a torsion spring, which can drive multiple substrates to be deployed. After the solar wing is deployed to the position, the first hinge unit 31 can abut and engage with the second hinge unit 32 port and be pre-tightened by the adjusting spring 34 to realize angle retention and fixation, so that each substrate does not rotate to maintain the required deployment state. The adjusting assembly 3 has simple structure, low manufacturing cost, and small space occupation, and is more suitable for microsatellite application requirements.

[0049] In the embodiment, each substrate has the same composition and size, and each substrate comprises, from top to bottom, a polyimide film 2-1, an upper carbon fiber grid skin 2-2, an aluminum honeycomb core 2-3, and a lower carbon fiber grid skin 2-4, the polyimide film 2-1 is formed on the surface of the upper carbon fiber grid skin 2-2 by an adhesive 2-5 to adhere the solar cell, the polyimide film 2-1 and the upper carbon fiber grid skin 2-2 are integrally formed by a co-curing process, which can effectively avoid bubbles and protrusions on the panel caused by post-film pasting, ensure the adhesion quality of the solar cell, and the aluminum honeycomb core 2-3 is bonded between the upper carbon fiber grid skin 2-2 and the lower carbon fiber grid skin 2-4 by the adhesive 2-5, the upper or lower carbon fiber grid skin is made of 0.2*2mm M40 carbon fiber composite laminated layer, and is laid according to the horizontal / vertical spacing of 6*6mm, which can meet the structural strength requirement of the substrate and reduce the overall weight of the substrate. The compression sleeve 44 is installed on the corresponding substrate by the way of glueing pre-buried, and the substrate of the embodiment has the advantages of light weight, fatigue resistance, high temperature resistance, and high reliability.

[0050] In the embodiment, a plurality of first rollers 51, second rollers 52, guide members 53, and linkage ropes 54 are also included, the satellite star body 1 and the two substrates closest to the satellite star body 1 are sequentially installed with the first roller 51, the guide member 53, and the second roller 52 and form a linkage structure through the linkage rope 54, and each three sequentially connected substrates are also sequentially installed with the first roller 51, the guide member 53, and the second roller 52 and form a linkage structure through the linkage rope 54. After the satellite is launched into orbit, the compression release mechanism can be unlocked by the ground command signal power supply, the plurality of adjustment assemblies 3 and the plurality of linkage structures cooperate together, the corresponding first roller 51 and second roller 52 are jointly rotated through the linkage rope 54, and the plurality of substrates are simultaneously rotated relative to the satellite star body 1 to be synchronously unfolded. In the embodiment, the first roller 51, the second roller 52, and the guide member 53 are installed on the edge, do not occupy the space resources between the substrates and between the substrate and the satellite star body 1, the guide member 53 can limit the direction of the first roller 51 and the second roller 52, and prevent the linkage rope 54 from touching the substrate, the embodiment can ensure the synchronous unfolding of the plurality of substrates, the linkage design prevents the collision between the substrates during the unfolding process of the solar wing, protects the substrates and the solar cell, and improves the stability and safety during the unfolding process of the solar wing.

[0051] In the embodiment, the linkage rope 54 in each linkage structure is arranged around the first roller 51 and the second roller 52 through the corresponding guide member 53. The linkage rope 54 transmits force through the guide member 53. During the unfolding stage of the solar wing, the plurality of substrates are rotated relative to the satellite star body 1 under the driving of the adjustment assembly 3; under the constraint of the linkage structure design, the plurality of substrates are synchronously unfolded, and then the final unfolding is ensured to be in place.

[0052] The utility model also provides a kind of satellite configuration, it includes the solar wing as described above, solar wing is located in satellite star body 1 one side. Single wing configuration is adopted, simple structure, easy to install, solar wing is folded and is pressed in satellite star body 1 one side before satellite launch, reduces launch risk, is applicable to small satellite.In addition, by the solar wing structure design of foldable, unfolding or extension, the area area of patch of substrate can be increased, the structure envelope of being folded and being folded in satellite star body 1 one side is small, more applicable to small satellite application demand.

[0053] The above detailed description of the embodiments of the present utility model, but the content described is only the preferred embodiment of the present utility model, and cannot be considered to limit the scope of the present utility model. Any equivalent changes and improvements made within the scope of the present utility model application shall still belong to the patent coverage of the present utility model.

Claims

1. A solar wing foldable or deployable to the side of a satellite body, characterized in that: The satellite body is rotatably connected with corresponding base plates through the adjusting assembly.

2. Solar wing according to claim 1, characterized in that When the solar wing is folded, a plurality of the base plates are sequentially stacked on the side of the satellite body and the base plate farthest from the satellite body is provided with a solar cell on the side away from the satellite body.

3. The solar wing of claim 1, wherein: When the solar wing is unfolded, a first included angle is formed between the satellite body and its adjacent base plate, and a second included angle is formed between each adjacent base plate, the first included angle is 90°, and the second included angle is 180°.

4. The solar wing of claim 1, wherein: The compact release mechanism further includes a compacting member, which can pass through the plurality of base plates when the solar wing is folded, and the two ends of the compacting member are respectively connected with the satellite body and the base plate farthest from the satellite body.

5. The solar wing of claim 1, wherein: The unfolding detection mechanism further includes a micro switch connected with the satellite body, which can be triggered by the corresponding base plate when the solar wing is unfolded.

6. The solar wing of claim 1, wherein: The adjusting assembly includes a central shaft, an adjusting spring, a first hinge unit, and a second hinge unit corresponding to the first hinge unit, the first hinge unit is arranged on the satellite body or the base plate, the second hinge unit is rotatably connected with the first hinge unit through the central shaft and arranged on the corresponding base plate, and the adjusting spring is sleeved on the central shaft and connected with the first hinge unit and the second hinge unit.

7. The solar wing of claim 1, wherein: Each base plate includes a polyimide film, an upper carbon fiber grid skin, an aluminum honeycomb core, and a lower carbon fiber grid skin, the polyimide film is formed on the surface of the upper carbon fiber grid skin, and the aluminum honeycomb core is bonded between the upper carbon fiber grid skin and the lower carbon fiber grid skin.

8. The solar wing of claim 1, wherein: The first roller, the second roller, the guide, and the linkage rope are adaptively arranged, the satellite body and the two base plates closest to the satellite body are sequentially installed with the first roller, the guide, and the second roller respectively, and form a linkage structure through the linkage rope, and each three sequentially connected base plates are also sequentially installed with the first roller, the guide, and the second roller respectively and form another linkage structure through the linkage rope.

9. Solar wing in accordance with claim 8, characterized in that The linkage rope in each linkage structure passes through the corresponding guide to be arranged around the first roller and the second roller.

10. A satellite constellation, characterized by The solar wing is arranged on one side of the satellite body.

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