Folding and unfolding solar wing device

Abstract

The utility model relates to the field of spaceflight, in particular to a solar wing folding and unfolding device which comprises a supporting shell and a solar wing unfolding device, the supporting shell comprises a bottom end plate face, a peripheral plate face, a limiting vertical plate, a top end plate and a supporting column, the bottom end plate face is fixed to the bottom of a cubesat, and the peripheral plate face is hinged to the periphery of the bottom end plate face. The top end plate is connected with the peripheral plate surface through a disconnectable connecting rope, the supporting column is arranged at the center of the bottom end plate surface, the solar wing unfolding device comprises a control driving part, an extension part and a flexible solar wing, the control driving part is provided with a spring rod, a torsional spring rod and a limiting groove, the spring rod is located above the bottom end plate surface, the torsional spring rod is located above the spring rod and fixedly connected with the spring rod, and the limiting groove is formed in the bottom end plate surface. Through mutual arrangement of the spring rod, the torsion spring rod, the limiting groove and the limiting vertical plate, the purpose of automatically controlling the torsion spring rod is achieved, meanwhile, the torsion spring rod which accumulates force in advance drives the tail end rod to be unfolded in a fan-shaped mode, and the purpose of automatically unfolding the solar wing is achieved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of spacecraft, in particular to a folding and unfolding solar wing device. BACKGROUND

[0002] CubeSat is a kind of standardized small satellite, usually composed of 10 cm side length of cubic unit, common specifications include 1U, 3U, etc. Due to its small size, low cost and short development cycle, CubeSat has been widely used in scientific research, education, business and other fields. However, the volume and mass limitations of CubeSat pose a serious challenge to its design, especially in the technology of deployment and stowage. How to efficiently stow equipment in limited space and reliably deploy in space is one of the core problems in CubeSat design. During the launch phase, all equipment of CubeSat must be compactly stowed inside or on the surface of the satellite to meet the space and mass limitations of the launch vehicle. This requires deployment and stowage technology to achieve efficient layout of equipment in limited space. For example, solar panels, antennas and sensors, and other key equipment are usually stowed in a folded, coiled or telescopic manner to maximize space utilization. After launch, these devices need to be deployed in space by deployment mechanisms according to the plan to ensure the normal operation of the satellite. The core of deployment and stowage technology is space utilization, reliability and lightweight. First, the equipment needs to be stowed in the smallest volume during the launch phase, while ensuring that the function after deployment is not affected. Second, the deployment mechanism must work reliably in the extreme environment of space, including vacuum, temperature difference and radiation. Common deployment driving methods include spring, motor, shape memory alloy (SMA) and inflatable structure, etc. Deployed by mechanical devices or inflation. In addition, lightweight design is also critical, and the deployment mechanism needs to use high-strength lightweight materials (such as carbon fiber) to reduce weight. SUMMARY

[0003] Therefore, the present application is a folding and unfolding solar wing device, which controls the spatial position of the top end plate by setting the support column, drives the solar wing to automatically control, and achieves the purpose of automatic deployment of the solar wing by setting the tail end rod, tail end limiting spring, middle section rod, middle section limiting spring and front end rod. The present application achieves the above-mentioned purposes through the following technical solutions:

[0004] A retractable and deployable solar array device includes: a support shell and a solar array deployment device. The support shell includes a bottom plate, four surrounding plates, a limiting vertical plate, a top plate, and a support column. The bottom plate is fixed to the bottom of a cubesat. The four surrounding plates are hinged to the outer periphery of the bottom plate. The top plate is connected to the four surrounding plates via a disconnectable connecting rope. The support column is located at the center of the bottom plate. The solar array deployment device includes a control drive unit, an extension unit, and a flexible solar array. The control drive unit is provided with a spring rod, a torsion spring rod, and a limiting groove. The spring rod is located above the bottom plate, and the torsion spring rod is located above the spring rod and fixedly connected. The limiting groove is located on the outer ring plate of the torsion spring rod. The extension unit includes a tail rod, a middle rod, a front rod, a tail limiting spring, and a middle limiting spring. Multi-segment deployment is achieved through spring linkage. The flexible solar array is segmentally fixed to the extension unit.

[0005] Preferably, the four sides are divided into four groups, each group consisting of two hinged panels, which, when unfolded, form a horizontal plane with the bottom panel.

[0006] Preferably, the torsion spring rod includes an inner ring plate, an intermediate torsion spring, and an outer ring plate. The outer ring plate engages with a limiting vertical plate via a limiting groove, and the inner ring plate is fixedly connected to the spring rod.

[0007] Preferably, the tail rod is divided into two tracks, left and right. One track is fixedly connected to the torsion spring rod, and the other track is rotatably connected to the tail rod on the horizontal plane. The tail end limiting spring is located inside one end of the tail end rod and is fixedly connected to the side of the tail end rod near the torsion spring rod. The other end is fixedly connected to the middle section rod. The middle section rod is located at one end of the tail end limiting spring and is fixedly connected. The middle section limiting spring is located at the slot of the middle section rod and is fixedly connected to each other. One end of the middle section limiting spring is fixedly connected to one side of the tail end rod, and the other side is fixedly connected to the front end rod. The front end rod is located on the side of the middle section limiting spring away from the middle section rod.

[0008] Preferably, the flexible solar array includes: a tail solar array, a middle solar array, and a front solar array. The tail solar array is located on the tail rod and is fixedly connected to each other. The middle solar array is located on the middle rod and is fixedly connected to each other. The front solar array is located on the front rod and is fixedly connected to each other.

[0009] Preferably, the lifting action of the support column is triggered by an electrical signal, and the connecting rope adopts a heat-melting or mechanical breakage design.

[0010] Beneficial effects of this invention:

[0011] 1. This utility model controls the spatial position of the top plate by setting support columns, and then breaks the connecting rope between the top plate and the surrounding plates. After separation, the surrounding plates rotate to a position horizontal with the bottom plate. The surrounding plates are no longer in the compressed extension part, and the extension part is driven to automatically extend. In addition, the raised top plate is no longer in the compressed control drive part, and the control drive part is driven to automatically lift. The purpose of automatic unfolding is achieved through the above two aspects.

[0012] 2. This utility model achieves automatic control of the torsion spring rod through the mutual arrangement of the spring rod, torsion spring rod, limiting groove, and limiting vertical plate. At the same time, the torsion spring rod, which has been pre-charged, drives the tail rod to unfold in a fan shape, thereby achieving the purpose of automatically unfolding the solar panels.

[0013] 3. This utility model uses a tail end rod, a tail end limiting spring, a middle section rod, a middle section limiting spring, and a front end rod. The tail end limiting spring and the middle section limiting spring control the deployment of the middle section rod and the front end rod. When the tail end rod is deployed, the middle section solar panels and the front end solar panels on the middle section rod and the front end rod are also deployed. Attached Figure Description

[0014] Figure 1 This is the front view of the present invention.

[0015] Figure 2 This is a schematic diagram of the structure of this utility model.

[0016] Figure 3 This is a schematic diagram of the support shell of this utility model.

[0017] Figure 4 This is a schematic diagram of the solar panel deployment device of this utility model.

[0018] Figure 5 This is a schematic diagram of the control drive unit of this utility model.

[0019] Figure 6 This is a schematic diagram of the extension part of this utility model.

[0020] Figure 7 This is a schematic diagram of the control drive unit of this utility model.

[0021] Figure 8 This is a schematic diagram of the flexible solar panel of this utility model.

[0022] Explanation of reference numerals in the attached figures:

[0023] 1. Support shell; 11. Bottom plate; 12. Surrounding plates; 13. Restricting vertical plate; 14. Top plate; 15. Support column; 2. Solar wing deployment device; 21. Control drive unit; 211. Spring rod; 212. Torsion spring rod; 213. Restricting groove; 22. Extension part; 221. Tail end rod; 222. Tail end restricting spring; 223. Mid-section rod; 224. Mid-section restricting spring; 225. Front end rod; 23. Flexible solar wing; 231. Tail end solar wing; 232. Mid-section solar wing; 233. Front end solar wing. Detailed Implementation

[0024] Preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, which will make it easy for those skilled in the art to implement these embodiments. However, the present invention can also 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, parts not connected to the present invention will be omitted from the drawings.

[0025] like Figure 1 As shown, a retractable and deployable solar array device includes: a support housing 1 and a solar array deployment device 2;

[0026] like Figure 2 , 3 As shown, the supporting shell 1 includes: a bottom plate 11, a surrounding plate 12, a limiting vertical plate 13, a top plate 14, and a supporting column 15;

[0027] The bottom plate 11 is located at the bottom of the cube star and is used to support the surrounding plates 12, limit the vertical plate 13, and support the column 15.

[0028] The four surrounding panels 12 are located on the outer periphery of the bottom panel 11 and are hinged to each other. The four surrounding panels 12 are divided into four groups, each group consisting of two hinged panels, which are used to form a closed space with the bottom panel 11.

[0029] The limiting vertical plate 13 is located on the bottom plate surface 11 and is fixedly connected to each other, and is used to limit the control drive unit 21;

[0030] The support column 15 is located at the center of the bottom plate 11 and is fixedly connected to each other. The support column 15 is controlled by power to lift upward. When the support column 15 is lifted, the connecting rope between the top plate 14 and the surrounding plates 12 will be broken, which is used to support the top plate 14 and control the spatial position of the top plate 14.

[0031] The top plate 14 is located above the support column 15 and is fixedly connected to each other. At the same time, the top plate 14 and the surrounding plate surface 12 are connected to each other by a tearable connecting rope. The connection rope is designed to be heat-fused or mechanically broken by an electrical signal trigger, ensuring reliable separation in the space environment.

[0032] like Figure 4 As shown, the solar array deployment device 2 includes: a control drive unit 21, an extension unit 22, and a flexible solar array 23;

[0033] The control drive unit 21 is located above the bottom plate 11 and is fixedly connected to each other. It is equipped with a spring inside to support the extension unit 22.

[0034] The extension portion 22 is located on the outer peripheral surface of the control drive portion 21 and is fixedly connected to each other, and is used to support the flexible solar panel 23.

[0035] The flexible solar panels 23 are located above the extension 22 and are fixedly connected to each other for absorbing solar energy;

[0036] like Figure 5 As shown, the control drive unit 21 includes: a spring rod 211, a torsion spring rod 212, and a limiting groove 213;

[0037] The spring rods 211 are located above the bottom plate 11 and are fixedly connected to each other, and are used to support and limit the spatial position of the torsion spring rods 212.

[0038] The torsion spring rod 212 is located above the spring rod 211 and is fixedly connected. The torsion spring rod 212 is divided into three parts: an inner ring plate, a middle torsion spring, and an outer ring plate. The inner ring plate is fixedly connected to the spring rod 211 and is used to support the middle torsion spring and the outer ring plate. It can also store energy in advance to drive the extension part 22.

[0039] The limiting groove 213 is located on the outer ring plate of the torsion spring rod 212. It is mutually limited by the limiting vertical plate 13 and the limiting groove 213. The mating surface of the limiting vertical plate 13 and the limiting groove 213 is provided with an anti-friction coating to adapt to stable separation under vacuum and temperature difference environments. It can achieve the purpose of controlling the control drive unit 21. As the spring rod 211 is lifted upward, the limiting vertical plate 13 and the limiting groove 213 separate and no longer mutually limit each other. The torsion spring rod 212 releases torque to drive one side of the extension part 22 to rotate, thereby achieving the purpose of deploying the solar wing.

[0040] like Figure 6 As shown, the extension 22 includes: a tail end rod 221, a tail end limiting spring 222, a middle section rod 223, a middle section limiting spring 224, and a front end rod 225;

[0041] The tail rod 221 is fixedly connected to the torsion spring rod 212. The tail rod 221 is divided into two tracks, left and right. One track is fixedly connected to the torsion spring rod 212, and the other track is rotatably connected to the tail rod 221 on the horizontal plane. At the same time, a slot is provided on the outer side of the tail rod 221 to accommodate the tail end limiting spring 222. When the spring rod 211 rises, the torsion spring rod 212 is driven to rise and at the same time, the torsion spring rod 212 separates from the limiting vertical plate 13. The tail rod 221 is driven and lifted as a whole. Then the torsion spring rod 212 rotates, driving the tail rod 221 on one side to rotate, driving the tail rod 221 to unfold, thus completing the deployment of the solar wing.

[0042] The tail end limiting spring 222 is located inside the tail end rod 221. One end is fixedly connected to the side of the tail end rod 221 near the torsion spring rod 212, and the other end is fixedly connected to the middle section rod 223, which is used to control the opening of the middle section rod 223.

[0043] The middle section rod 223 is located at one end of the tail end limiting spring 222 and is fixedly connected. The middle section rod 223 has slots on both sides to accommodate the middle section limiting spring 224 and to support the middle section solar fin 232.

[0044] The middle section limiting spring 224 is located at the slot of the middle section rod 223 and is fixedly connected to each other. One end of the middle section limiting spring 224 is fixedly connected to the side of the slot of the middle section limiting spring 224 near the tail end rod 221, and the other end is fixedly connected to the front end rod 225, which is used to control the spatial position of the front end rod 225.

[0045] The front end rod 225 is located on the side of the middle section limiting spring 224 away from the middle section rod 223. The front end rod 225 is divided into two groups, left and right, and is slidably connected to the middle section rod 223 to support the front end solar panel 233.

[0046] like Figure 7 As shown, the flexible solar array 23 includes: a tail solar array 231, a mid-section solar array 232, and a front solar array 233;

[0047] The tail end solar fin 231 is located on the tail end rod 221 and is fixedly connected to each other for absorbing solar energy;

[0048] The mid-section solar fin 232 is located on the mid-section rod 223 and is fixedly connected to each other for absorbing solar energy;

[0049] The front solar array 233 is located on the front rod 225 and is fixedly connected to each other for absorbing solar energy.

[0050] Working principle of this invention:

[0051] When the CubeSat solar panels deploy, the support column 15 is first raised via power control. During this raising, the connecting ropes between the top plate 14 and the surrounding panels 12 are severed. The separated surrounding panels 12 rotate to a position level with the bottom plate 11. The surrounding panels 12 are no longer compressed by the extension section 22, causing it to automatically extend. Furthermore, the raised top plate 14 is no longer compressed by the control drive unit 21, causing it to automatically raise. Then, as the spring rod 211 rises, the limiting vertical plate 13 and the limiting groove 213 separate and no longer restrict each other. The torsion spring rod 212 releases torque to drive one side of the extension 22 to rotate, causing the tail rod 221 to unfold, thus achieving the purpose of unfolding the solar wing. At the same time, the tail limiting spring 222 and the middle limiting spring 224 control the unfolding of the middle rod 223 and the front rod 225. Then, when the tail rod 221 is driven to unfold, the middle solar wing 232 and the front solar wing 233 on the middle rod 223 and the front rod 225 also complete the unfolding.

Claims

1. A stow and deploy solar wing arrangement, characterised in that, The utility model relates to a kind of solar wing deployment device, including: support shell (1) and solar wing deployment device (2), support shell (1) includes bottom end plate surface (11), peripheral plate surface (12), limiting vertical plate (13), top end plate (14) and support column (15), bottom end plate surface (11) is fixed to the bottom of cube star, peripheral plate surface (12) is hinged to the periphery of bottom end plate surface (11), top end plate (14) is connected with peripheral plate surface (12) by detachable connecting rope, support column (15) is arranged in the center of bottom end plate surface (11), solar wing deployment device (2) includes control drive part (21), extension part (22) and flexible solar wing (23), control drive part (21) is provided with spring rod (211), torsion spring rod (212) and limiting groove (213), spring rod (211) is located above bottom end plate surface (11), torsion spring rod (212) is located above spring rod (211) and is fixedly connected, limiting groove (213) is located on the outer ring plate surface of torsion spring rod (212), extension part (22) includes tail end rod (221), middle section rod (223), front end rod (225) and tail end limiting spring (222), middle section limiting spring (224) are achieved by spring linkage multi-section expansion, flexible solar wing (23) is fixed on extension part (22) in section. The peripheral plate surface (12) is divided into four groups, each group is composed of two hinged plate surfaces, and forms a horizontal plane with the bottom end plate surface (11) after deployment.

2. A stow and deploy solar wing arrangement according to claim 1, characterised in that: The torsion spring rod (212) includes an inner ring plate surface, a middle torsion spring and an outer ring plate surface, the outer ring plate surface is clamped with the limiting vertical plate (13) through the limiting groove (213), and the inner ring plate surface is fixedly connected with the spring rod (211).

3. A stow and deploy solar wing apparatus as claimed in claim 1, wherein: The tail end rod (221) is divided into left and right two tracks, one side track is fixedly connected with the torsion spring rod (212), and the other side is rotatably connected with the tail end rod (221) in a horizontal plane, the tail end limiting spring (222) is located at one end inside the tail end rod (221) and is fixedly connected with the tail end rod (221) near the torsion spring rod (212), the other end is fixedly connected with the middle section rod (223), the middle section rod (223) is located at one end of the tail end limiting spring (222) and is fixedly connected, the middle section limiting spring (224) is located at the slotted portion of the middle section rod (223) and is fixedly connected with each other, one end of the middle section limiting spring (224) is fixedly connected with one side of the tail end rod (221), and the other side is fixedly connected with the front end rod (225), and the front end rod (225) is located at the side of the middle section limiting spring (224) away from the middle section rod (223).

4. A stow and deploy solar wing apparatus as claimed in claim 1, characterised in that: The flexible solar wing (23) includes: tail end solar wing (231), middle section solar wing (232) and front end solar wing (233), the tail end solar wing (231) is located on the tail end rod (221) and is fixedly connected with each other, the middle section solar wing (232) is located on the middle section rod (223) and is fixedly connected with each other, and the front end solar wing (233) is located on the front end rod (225) and is fixedly connected with each other.

5. A stow and deploy solar wing arrangement according to claim 4, characterised in that: The lifting action of the support column (15) is triggered by electrical signal, and the connecting rope adopts hot melting or mechanical fracture design.

6. A stow and deploy solar wing apparatus as claimed in claim 1, characterised in that: ​

Images