A two-dimensional solar wing deployment timing control mechanism

Abstract

The application provides a two-dimensional solar wing unfolding timing control mechanism and belongs to the technical field of aerospace. The mechanism solves the interference problem of a solar wing base plate during unfolding. The mechanism comprises a spacecraft, an upper base plate, a lower base plate, a middle base plate, a timing control mechanism and a rotating connection assembly. The spacecraft is rotationally connected to the lower end of the middle base plate at one side end face, and the lower base plate and the upper base plate are rotationally connected to the left and right ends of the middle base plate. When the solar wing is in a folded state, the upper base plate, the lower base plate and the middle base plate are arranged from the spacecraft side to the outside in sequence, and the upper ends of the upper base plate and the lower base plate are connected to the timing control mechanism. The timing control mechanism is used for reducing the unfolding speed of the lower base plate when the upper base plate and the lower base plate are opened. The mechanism is mainly used for the unfolding control of the solar wing.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, and in particular relates to a two-dimensional solar array deployment timing control mechanism. Background Technology

[0002] Solar panels are an important structural component of spacecraft, typically covered with solar cells to provide energy to the spacecraft. A solar panel generally consists of multiple substrates. Before launch, these substrates need to be locked and pressed firmly onto the spacecraft's surface. After the spacecraft reaches its designated orbit, the solar panels unlock and deploy. To prevent inconsistent deployment rates among the substrates, a linkage mechanism is often installed to synchronize the deployment rates of each substrate.

[0003] Conventional linkage mechanisms cannot control the timing of the two-dimensional deployment of the solar panels, which can easily cause interference with the substrate during deployment. Summary of the Invention

[0004] In view of this, the present invention aims to propose a two-dimensional solar array deployment timing control mechanism to solve the interference problem during solar array substrate deployment.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a two-dimensional solar array deployment timing control mechanism, comprising a spacecraft, an upper base plate, a lower base plate, a middle base plate, a timing control mechanism, and a rotating connection assembly. One end face of the spacecraft is rotatably connected to the lower end of the middle base plate, and the lower base plate and the upper base plate are rotatably connected to the left and right ends of the middle base plate. When the solar array is in the folded state, the upper base plate, the lower base plate, and the middle base plate are arranged sequentially from the side closest to the spacecraft outwards. The upper ends of the upper base plate and the lower base plate are both connected to the timing control mechanism, which is used to reduce the deployment speed of the lower base plate when the upper base plate and the lower base plate are opened.

[0006] Furthermore, the timing control mechanism also includes a clamping component and a secondary clamping component, both of which are separate structures. The clamping component is used for unlocking and separating the middle base plate from the spacecraft. One part of the clamping component is connected to the spacecraft, and the other part is connected to the middle base plate. The secondary clamping component is used for unlocking and separating the upper base plate from the lower base plate. One part of the secondary clamping component is connected to the upper base plate, and the other part is connected to the lower base plate.

[0007] Furthermore, both the lower substrate and the upper substrate are rotatably connected to the middle substrate via a rotating connector.

[0008] Furthermore, the rotating connector includes two hinges arranged symmetrically on the upper and lower sides relative to the middle base plate.

[0009] Furthermore, the timing control mechanism includes a guide slide and a pulley assembly. The guide slide is connected to the upper end of the upper substrate near the middle substrate, and the pulley assembly is connected to the upper end of the lower substrate away from the middle substrate. The guide slide is arc-shaped. When the solar panel is folded, the pulley assembly is connected in the guide slide. When the solar panel is unfolded, the pulley assembly slides along the guide slide and then disengages from the guide slide.

[0010] Furthermore, the pulley assembly includes a roller and a bracket. The roller is rotatably connected to the bracket, and the bracket is fixedly connected to the lower base plate. When the solar panel is folded, the roller is slidably connected in the guide groove.

[0011] Furthermore, the inner surface of the guide groove is coated with a polytetrafluoroethylene coating.

[0012] Furthermore, the outer surface of the roller is coated with a polytetrafluoroethylene coating.

[0013] Furthermore, the resistance torque of the roller and the guide groove is 0.1 N·m.

[0014] Furthermore, the ratio K of the unfolding speed of the lower substrate to the unfolding speed of the upper substrate is adjustable within a range of 1:6 to 1:1.

[0015] Compared with the prior art, the beneficial effects of the present invention are:

[0016] 1. This solar panel, by setting a timing control mechanism, can reduce the unfolding speed of the lower substrate when the upper and lower substrates are opened, thereby preventing the lower substrate from opening upwards too quickly and interfering with the upper substrate, thus avoiding wear problems;

[0017] 2. This solar array avoids cold welding in the space environment by coating the inner surface of the guide groove and the outer surface of the roller with polytetrafluoroethylene. Attached Figure Description

[0018] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0019] Figure 1 This is a schematic diagram of the structure of the two-dimensional solar array deployment timing control mechanism of the present invention when it is folded.

[0020] Figure 2 This is a schematic diagram of a two-dimensional solar array deployment timing control mechanism and a one-dimensional deployment in the X direction, as described in this invention.

[0021] Figure 3 This is a schematic diagram of a two-dimensional solar array deployment timing control mechanism in the ±Y direction, as described in this invention.

[0022] Figure 4 This is a schematic diagram of the deployment completion structure of a two-dimensional solar array deployment timing control mechanism according to the present invention;

[0023] Figure 5 This is a schematic diagram of the front view structure of the timing control mechanism described in this invention;

[0024] Figure 6 This is a cross-sectional view of the timing control mechanism described in this invention.

[0025] Figure 7 This is a schematic diagram illustrating the angle change during the deployment process of a two-dimensional solar array deployment timing control mechanism according to the present invention.

[0026] Figure 8 This is a schematic diagram of the critical state when the guide groove and roller disengage as described in this invention.

[0027] Spacecraft 1; Hinge 2; Upper base plate 3; Lower base plate 4; Middle base plate 5; Timing control mechanism 6; Clamping assembly 7; Guide slide 8; Roller 9; Bracket 10; Secondary clamping assembly 11. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of the present invention can be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.

[0029] Referring to the accompanying drawings, this embodiment describes a two-dimensional solar array deployment timing control mechanism, including a spacecraft 1, an upper base plate 3, a lower base plate 4, a middle base plate 5, a timing control mechanism 6, and a rotating connection assembly. One end face of the spacecraft 1 is rotatably connected to the lower end of the middle base plate 5, and the lower base plate 4 and the upper base plate 3 are rotatably connected to the left and right ends of the middle base plate 5. When the solar array is folded, the upper base plate 3, the lower base plate 4, and the middle base plate 5 are arranged sequentially from the side closest to the spacecraft 1 outwards. The upper ends of the upper base plate 3 and the lower base plate 4 are both connected to the timing control mechanism 6, which is used to reduce the deployment speed of the lower base plate 4 when the upper base plate 3 and the lower base plate 4 are opened.

[0030] In this embodiment, the timing control mechanism further includes a clamping component 7 and a secondary clamping component 11. Both the clamping component 7 and the secondary clamping component 11 are separate structures. The clamping component 7 is used for unlocking and separating the middle base plate 5 from the spacecraft 1. One part of the clamping component 7 is connected to the spacecraft 1, and the other part is connected to the middle base plate 5. The secondary clamping component 11 is used for unlocking and separating the upper base plate 3 from the lower base plate 4. One part of the secondary clamping component 11 is connected to the upper base plate 3, and the other part is connected to the lower base plate 4. Both the clamping component 7 and the secondary clamping component 11 are existing technologies, and their specific structures and mechanisms of action are not described in detail here.

[0031] In this embodiment, both the lower substrate 4 and the upper substrate 3 are rotatably connected to the middle substrate 5 via rotating connectors. The rotating connectors include two hinges 2 arranged symmetrically on the upper and lower sides relative to the middle substrate 5.

[0032] In this embodiment, the timing control mechanism 6 includes a guide groove 8 and a pulley assembly. The guide groove 8 is connected to the upper end of the upper substrate 3 near the middle substrate 5, and the pulley assembly is connected to the upper end of the lower substrate 4 away from the middle substrate 5. The guide groove 8 is arc-shaped. When the solar panel is folded, the pulley assembly is connected in the guide groove 8. When the solar panel is unfolded, the pulley assembly slides along the guide groove 8 and then disengages from the guide groove 8.

[0033] In this embodiment, the pulley assembly includes a roller 9 and a bracket 10. The roller 9 is rotatably connected to the bracket 10, and the bracket 10 is fixedly connected to the lower base plate 4. When the solar panel is in the folded state, the roller 9 is slidably connected in the guide groove 8.

[0034] In this embodiment, the inner surface of the guide groove 8 is coated with a polytetrafluoroethylene (PTFE) coating, and the outer surface of the roller 9 is coated with a PTFE coating. This avoids cold welding in the space environment.

[0035] In this embodiment, the resistance torque of the roller 9 and the guide groove 8 is 0.1 N·m, and the torque margin of the conventional hinge 2 of the solar wing can meet the requirements.

[0036] In this embodiment, the ratio K of the unfolding speed of the lower substrate 4 to the unfolding speed of the upper substrate 3 is adjustable in the range of 1:6 to 1:1.

[0037] In use, after the spacecraft reaches its predetermined orbit, the clamping assembly 7 releases its clamping force, and the solar array, driven by the hinge, unfolds in a one-dimensional +X direction. At this time, the middle base plate 5 unfolds until it forms a 90° angle with the spacecraft surface, at which point the one-dimensional unfolding of the solar array is complete.

[0038] Then, the secondary clamping assembly 11 releases its clamping force, and the upper substrate 3 and lower substrate 4 unfold in two dimensions along ±Y. At this time, the roller 9 connected to the lower substrate 4 slides within the guide groove 8, causing the unfolding angle of the lower substrate 4 to be constrained by the guide groove 8 to only a small angle. Meanwhile, the upper substrate 3 unfolds normally. When the roller 9 is about to disengage from the guide groove 8, the constraint of the timing control mechanism 6 reaches its limit position. At this point, the subsequent unfolding process of the lower substrate 4 does not interfere with the upper substrate 3, and the constraint effect of the timing control mechanism 6 is released.

[0039] During the unfolding process, the guide groove 8 limits the movement of the roller 9. When the unfolding angle of the upper substrate 3 is α, the unfolding angle of the lower substrate 4 is only β. This allows the lower substrate 4 and the upper substrate 3 to have an angular velocity ratio K, where K = angular velocity of the lower substrate / angular velocity of the upper substrate. This prevents the lower substrate 4 from unfolding too quickly and interfering with the upper substrate 3. When the unfolding angle of the upper substrate 3 is γ, the roller 9 in the timing control mechanism 6 is about to disengage from the guide groove 8. This position is the limit angle of the timing control mechanism 6. If the unfolding continues, the roller 9 will completely disengage from the constraint of the guide groove 8, and the lower substrate 4 will unfold normally.

[0040] By changing the curvature and radius of the guide groove 8, and the initial contact position between the roller 9 and the guide groove 8 in the timing control mechanism 6 during the clamping state, the unfolding angular velocity ratio K and the limiting angle γ can be adjusted. This allows for the design of different unfolding angular velocity ratios K and limiting angle γ values ​​according to actual needs, thus preventing interference during the two-dimensional unfolding of the solar panel substrate.

[0041] This application has been successfully applied to a ground test of two-dimensional deployment of solar panels on a certain type of satellite. During the two-dimensional deployment process, the angular velocity ratio of the solar panel substrates was K = 1:4 and γ = 60°. The deployment process was smooth and no interference occurred between the substrates.

[0042] The embodiments of the present invention disclosed above are merely illustrative of the invention. These embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention.

Claims

1. A two-dimensional solar array deployment timing control mechanism, characterized in that: The system includes a spacecraft (1), an upper base plate (3), a lower base plate (4), a middle base plate (5), a timing control mechanism (6), and a rotating connection assembly. One end face of the spacecraft (1) is rotatably connected to the lower end of the middle base plate (5). The lower base plate (4) and the upper base plate (3) are rotatably connected to the left and right ends of the middle base plate (5). When the solar panels are folded, the upper base plate (3), the lower base plate (4), and the middle base plate (5) are arranged sequentially from the side closest to the spacecraft (1) outwards. The upper ends of the upper base plate (3) and the lower base plate (4) are both connected to the timing control mechanism (6). The timing control mechanism (6) is used to reduce the unfolding speed of the lower base plate (4) when the upper base plate (3) and the lower base plate (4) are opened. The timing control mechanism (6) includes a guide groove (8) and a pulley assembly. The guide groove (8) is connected to the upper end of the upper substrate (3) near the middle substrate (5), and the pulley assembly is connected to the upper end of the lower substrate (4) away from the middle substrate (5). The guide groove (8) is arc-shaped. When the solar panel is folded, the pulley assembly is connected in the guide groove (8). When the solar panel is unfolded, the pulley assembly slides along the guide groove (8) and then disengages from the guide groove (8). The pulley assembly includes a roller (9) and a bracket (10). The roller (9) is rotatably connected to the bracket (10). The bracket (10) is fixedly connected to the lower base plate (4). When the solar panel is folded, the roller (9) is slidably connected in the guide groove (8). The ratio K of the unfolding speed of the lower substrate (4) to the unfolding speed of the upper substrate (3) is adjustable in the range of 1:6 to 1:

1.

2. The two-dimensional solar array deployment timing control mechanism according to claim 1, characterized in that: The timing control mechanism further includes a clamping component (7) and a secondary clamping component (11). Both the clamping component (7) and the secondary clamping component (11) are separate structures. The clamping component (7) is used to unlock and separate the middle base plate (5) from the spacecraft (1). A part of the clamping component (7) is connected to the spacecraft (1), and the other part of the clamping component (7) is connected to the middle base plate (5). The secondary clamping component (11) is used to unlock and separate the upper base plate (3) from the lower base plate (4). A part of the secondary clamping component (11) is connected to the upper base plate (3), and the other part of the secondary clamping component (11) is connected to the lower base plate (4).

3. A two-dimensional solar array deployment timing control mechanism according to claim 1 or 2, characterized in that: The lower substrate (4) and the upper substrate (3) are both rotatably connected to the middle substrate (5) through a rotating connector.

4. The two-dimensional solar array deployment timing control mechanism according to claim 3, characterized in that: The rotating connector includes two hinges (2) arranged symmetrically on the upper and lower sides relative to the middle base plate (5).

5. The two-dimensional solar array deployment timing control mechanism according to claim 1, characterized in that: The inner surface of the guide groove (8) is coated with polytetrafluoroethylene.

6. The two-dimensional solar array deployment timing control mechanism according to claim 1, characterized in that: The outer surface of the roller (9) is coated with polytetrafluoroethylene.

7. The two-dimensional solar array deployment timing control mechanism according to claim 1, characterized in that: The resistance torque of the roller (9) and the guide groove (8) is 0.1 N·m.

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