Axial restraining device for folded state of winding type flexible solar wing substrate

Abstract

The invention provides an axial restraining device for a folded state of a winding type flexible solar wing substrate. The axial restraining device comprises a flexible substrate side lug, a winding storage conical barrel, a winding wire and a wire tensioning device. The plurality of flexible substrate side lugs are arranged at different positions on the two sides of the flexible substrate; the winding storage conical cylinders are coaxially arranged at the two ends of a winding cylinder of the flexible substrate, and a winding wire is connected with the wire tensioning device and sequentially penetrates through a plurality of flexible substrate side lugs located on the side portion of the flexible substrate; during winding, the wire tensioning device is tightened to drive the winding wire to be wound and folded on the winding storage conical barrel in the circumferential direction, and the flexible substrate side lug is fixed to the winding storage conical barrel. According to the winding type flexible solar wing, the structural characteristics of the winding type flexible wing are fully utilized, the side edges of the flexible substrate are provided with the side lugs, the side lugs are connected with the winding storage conical barrels on the winding shafts in the winding state, the winding type flexible solar wing substrate is axially restrained in the closed state, it is guaranteed that no relative motion exists between layers of the flexible substrate when the flexible wing emits vibration, and the reliability of the winding type flexible solar wing is improved. And the solar cell is prevented from being broken and damaged.

Description

Technical Field

[0001] The present invention relates to the field of space flexible solar wings, and more specifically, to an axial constraint device for a retracted state of a wound flexible solar wing substrate. Background Art

[0002] Solar wings are the main power supply devices of spacecrafts. Flexible solar wings, especially wound flexible solar wings, have the characteristics of small retracted volume, large deployed area, and high power-to-mass ratio, and are suitable for use in constellation stacked satellites and high-power spacecrafts.

[0003] Wound flexible solar wings generally use retractable carbon fiber booms with openable ends as the drive deployment devices, and glass fiber cloth coated with polyimide film as the flexible substrate. Patent document US9604737B2 discloses a directionally deployable flexible wound solar wing, and proposes to arrange a spring group between the flexible substrate and the root mounting plate to realize the tensioning of the flexible substrate in the stretching direction before and after the deployment of the flexible wing.

[0004] However, this solution only connects and tensions the flexible substrate at both ends, and there is no axial constraint for the flexible substrate in the winding state along the winding axis. During the whole satellite launch stage, vibration can easily cause axial movement between layers of the flexible substrate, resulting in wear or even breakage of the solar cells pasted on the flexible substrate, reducing the power generation of the flexible wing, and seriously affecting the execution of satellite missions. Summary of the Invention

[0005] Aiming at the deficiencies in the prior art, the purpose of the present invention is to provide an axial constraint device for a retracted state of a wound flexible solar wing substrate.

[0006] The axial constraint device for a retracted state of a wound flexible solar wing substrate provided by the present invention includes flexible substrate side ears, a winding and storage cone, a winding wire, and a wire tensioner;

[0007] There are a plurality of the flexible substrate side ears, and the plurality of flexible substrate side ears are respectively arranged at different positions on both sides of the flexible substrate;

[0008] The winding and storage cone is coaxially arranged at both ends of the winding cylinder of the flexible substrate. The winding wire is connected to the wire tensioner and sequentially passes through a plurality of flexible substrate side ears located on the side of the flexible substrate;

[0009] During winding, the wire tensioner tightens, drives the winding wire to wind and gather circumferentially on the winding and storage cone, and fixes the flexible substrate side ears on the winding and storage cone.

[0010] Preferably, grooves corresponding to the plurality of flexible substrate side ears are provided on the winding and storage cone. In the winding state, the flexible substrate side ears are pressed into the grooves at corresponding positions of the winding and storage cone.

[0011] Preferably, the protruding lengths of the flexible substrate side ears at different positions of the flexible substrate are different, and the protruding lengths match the distances between the corresponding grooves on the winding storage conical cylinder after the flexible substrate is wound.

[0012] Preferably, threading holes are provided along the width direction at the ends of the flexible substrate side ears for the coiled wire to pass through.

[0013] Preferably, it further includes a stretching rod, which is coaxially and fixedly connected to the winding cylinder, and the end of the stretching rod is fixedly connected to the base mounting plate to which the flexible substrate is connected;

[0014] When unfolding, driven by the release of its own elastic potential energy, the stretching rod drives the winding cylinder to rotate and stretches away from the base mounting plate until the flexible substrate unfolds to a planar state, and multiple flexible substrate side ears at the end of the flexible substrate sequentially disengage from the winding storage conical cylinder following the coiled wire.

[0015] Preferably, there are two stretching rods, symmetrically arranged at both ends of the winding cylinder and coaxially arranged with the winding cylinder.

[0016] Preferably, multiple flexible substrate side ears are provided on both sides of the flexible substrate, and the flexible substrate side ears on both sides are symmetrically distributed with respect to the flexible substrate;

[0017] There are two winding storage conical cylinders, symmetrically arranged on both sides of the flexible substrate and fixedly connected to the winding cylinder.

[0018] Preferably, the winding storage conical cylinder is provided with rotation grooves with equal cross-sections, and its trajectory is an Archimedean spiral that gradually changes in space for the coiled wire to be wound and stored.

[0019] Preferably, one end of the coiled wire is connected to the innermost circle of the winding storage conical cylinder, and the other end of the coiled wire is connected to the wire tensioner.

[0020] Preferably, the coiled wire includes a Kevlar aramid rope.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. The present invention makes full use of the structural characteristics of the wound flexible wing, arranges multiple side ears on the side of the flexible substrate, and connects them to the winding storage conical cylinder on the winding shaft in the wound state, realizing the axial constraint of the wound state of the wound flexible solar wing substrate, ensuring that there is no relative movement between the flexible substrate layers during the launch vibration of the flexible wing, and ensuring that the solar cells are not broken or damaged.

[0023] 2. The flexible substrate side ears of the present invention can be used as hanging points during the vertical suspension and unfolding test of the flexible wing at the same time, having the characteristic of dual functions.

[0024] 3. The axial constraint device of the winding flexible wing of the present invention has a simple and reliable structure and does not affect the winding and stretching of the original flexible wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Other features, objects, and advantages of the present invention will become more apparent by reading the following detailed description of non - restrictive embodiments with reference to the accompanying drawings:

[0026] Figure 1 It is a schematic structural diagram of the winding state of the winding flexible wing in the present invention;

[0027] Figure 2 It is a schematic structural diagram of multiple flexible substrate side ears at the end of the flexible substrate in the present invention;

[0028] Figure 3 It is a schematic structural diagram of the winding storage cone in the present invention;

[0029] Figure 4 It is a schematic structural diagram of the flexible substrate side ear in the present invention.

[0030] As shown in the figure:

[0031] Flexible substrate side ear 1 Flexible substrate 6

[0032] Winding storage cone 2 End tensioning device 7

[0033] Coiled wire 3 Base mounting plate 8

[0034] Wire tensioner 4 Winding cylinder 9

[0035] Extension rod 5 DETAILED DESCRIPTION OF THE EMBODIMENTS

[0036] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those of ordinary skill in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0037] The present application discloses an axial constraint device for the winding state of a winding flexible solar wing substrate, which makes full use of the structural characteristics of the winding flexible wing, arranges multiple side ears on the side of the flexible substrate, and connects them to the winding storage cone on the winding shaft during the winding state, realizing the axial constraint of the winding flexible solar wing substrate in the winding state, ensuring that there is no relative movement between the flexible substrate layers during the launch vibration of the flexible wing, and ensuring that the solar cells are not broken or damaged.

[0038] The axial constraint device for the retracted state of the wound flexible solar wing substrate provided by the present invention acts on the flexible substrate 6. The end of the flexible substrate 6 is installed on the basic mounting plate 8 through the end tensioning device 7 and can be wound or unfolded around the winding cylinder 9.

[0039] As Figure 1 , Figure 2 shown, the axial constraint device includes flexible substrate side ears 1, winding wire storage conical cylinders 2, coiled wires 3, and wire tensioners 4. There are multiple flexible substrate side ears 1, and the multiple flexible substrate side ears 1 are respectively arranged at different positions on both sides of the flexible substrate 6. The winding wire storage conical cylinders 2 are coaxially arranged at both ends of the winding cylinder 9 of the flexible substrate 6. The coiled wire 3 is connected to the wire tensioner 4 and sequentially passes through multiple flexible substrate side ears 1 located on the side of the flexible substrate 6.

[0040] In a preferred example, the wire tensioner 4 fixes the coiled wire 3 and maintains a certain tension. One end of the coiled wire 3 is connected to the innermost circle of the winding wire storage conical cylinder 2, and one end is connected to the wire tensioner. The coiled wire 3 is made of a material resistant to temperature and creep, such as Kevlar aramid rope, to ensure long-term tension without relaxation.

[0041] When the flexible solar wing is in the wound state, multiple flexible side ears 1 on both sides of the flexible substrate 6 are retracted with the flexible substrate 6 around the circumference of the winding cylinder 9. The coiled wires 3 on both sides sequentially pass through the holes in the flexible substrate side ears 1, and the ends of all flexible substrate side ears 1 are pressed into the grooves at corresponding positions of the winding wire storage conical cylinder 3. The coiled wire 3 is tightened through the wire tensioner 4, and then the flexible substrate 6 is connected to the winding wire storage conical cylinder 3 through the substrate side ears 1 at both ends, realizing the fixed constraint of the flexible substrate 6 along the axis of the winding cylinder 9 in the wound state.

[0042] In a preferred example, it further includes extension rods 5. There are two extension rods 5, which are symmetrically arranged at both ends of the winding cylinder 9 and are coaxially arranged with the winding cylinder 9. The ends of the extension rods 5 are fixedly connected to the basic mounting plate 8 connected to the flexible substrate 6.

[0043] When the flexible solar wing unfolds, the two extension rods 5 drive the winding cylinder 9 to rotate and extend away from the basic mounting plate 8 under the drive of the release of their own elastic potential energy. The flexible substrate 6 gradually unfolds from the wound state to the planar state with the movement of the winding cylinder 9, and multiple flexible substrate side ears 1 on both sides sequentially disengage from the grooves of the winding wire storage conical cylinder 2 following the coiled wires 3.

[0044] As Figure 2As shown, there are multiple flexible substrate side ears 1 arranged at both ends of the flexible substrate 6. The protruding lengths of the flexible substrate side ears 1 at different positions on the flexible substrate 6 are different, which are determined according to the distance between the wound flexible substrate 6 and the corresponding grooves on the winding and storage conical cylinder 2, so as to ensure that the flexible substrate 6 is in an axially constrained state at the position of each flexible substrate side ear 1 in the wound state.

[0045] As Figure 3 shown, the winding and storage conical cylinder 2 is provided with rotating grooves with equal cross-sections, and its trajectory is an Archimedean spiral with a spatially varying pitch, which is used for winding and storing the winding wire 3.

[0046] As Figure 4 shown, the flexible substrate side ear 1 is provided with a wire passing hole for the winding wire 3 to pass through.

[0047] In a preferred example, the flexible substrate side ear 1 can be used as a hanging point during the vertical suspension and deployment test of the flexible wing at the same time.

[0048] The present invention makes full use of the structural characteristics of the wound flexible wing, symmetrically arranges multiple side ears on both sides of the flexible substrate, and connects them to the winding and storage conical cylinder on the winding shaft in the wound state, realizing the axially constrained state of the wound flexible solar wing substrate, ensuring that there is no relative movement between the flexible substrate layers during the launch vibration of the flexible wing, and ensuring that the solar cells are not broken or damaged. The flexible substrate side ear can be used as a hanging point during the vertical suspension and deployment test of the flexible wing at the same time, having the characteristic of dual functions. At the same time, as an axially constrained method for the wound flexible wing, the present invention has a simple and reliable structure and does not affect the winding and stretching of the original flexible wing.

[0049] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0050] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A winding type flexible solar wing substrate retracted state axial constraint device, characterized in that It includes flexible substrate side ears (1), winding storage conical cylinders (2), coiled wires (3) and wire tensioners (4); There are multiple flexible substrate side ears (1), and the multiple flexible substrate side ears (1) are respectively arranged at different positions on both sides of the flexible substrate (6); The winding storage conical cylinders (2) are coaxially arranged at both ends of the winding cylinder (9) of the flexible substrate (6). The coiled wire (3) is connected to the wire tensioner (4) and sequentially passes through multiple flexible substrate side ears (1) located on the side of the flexible substrate (6); During winding, the wire tensioner (4) tightens, driving the coiled wire (3) to wind and converge circumferentially on the winding storage conical cylinder (2), and fixing the flexible substrate side ear (1) to the winding storage conical cylinder (2).

2. The axial restraint device for the retracted state of the wound flexible solar wing substrate according to claim 1, characterized in that Grooves corresponding to the multiple flexible substrate side ears (1) are provided on the winding storage conical cylinder (3). In the winding state, the flexible substrate side ear (1) is pressed into the groove at the corresponding position of the winding storage conical cylinder (3).

3. The axial restraint device in the stowed state of the wound flexible solar wing substrate according to claim 2, wherein, The protruding lengths of the flexible substrate side ears (1) at different positions on the flexible substrate (6) are different, and the protruding lengths match the distances from the corresponding groove positions on the winding storage conical cylinder (3) after the flexible substrate (6) is wound.

4. The axial restraint device for the retracted state of the wound flexible solar wing substrate according to claim 1, wherein A wire passing hole is provided at the end of the flexible substrate side ear (1) along the width direction for the coiled wire (3) to pass through.

5. The axial restraint device in the stowed state of the wound flexible solar wing substrate according to claim 1, characterized in that, It further includes an extension rod (5). The extension rod (5) is coaxially and fixedly connected to the winding cylinder (9), and the end of the extension rod (5) is fixedly connected to the base mounting plate (8) connected to the flexible substrate (6); When unfolding, the extension rod (5) is driven by the release of its own elastic potential energy, driving the winding cylinder (9) to rotate and extending in a direction away from the base mounting plate (8) until the flexible substrate (6) is unfolded to a planar state, and multiple flexible substrate side ears (1) at the end of the flexible substrate (6) sequentially disengage from the winding storage conical cylinder (3) following the coiled wire (3).

6. The axial restraint device for the retracted state of the wound flexible solar wing substrate according to claim 5, characterized in that, There are two extension rods (5), which are symmetrically arranged at both ends of the winding cylinder (9) and are coaxially arranged with the winding cylinder (9).

7. The axial restraint device in the retracted state of the wound flexible solar wing substrate according to claim 1, wherein Multiple flexible substrate side ears (1) are provided on both sides of the flexible substrate (6), and the flexible substrate side ears (1) on both sides are symmetrically distributed with respect to the flexible substrate (6); There are two winding storage conical cylinders (2), which are symmetrically arranged on both sides of the flexible substrate (6) and are fixedly connected to the winding cylinder (9).

8. The axial restraint device for the retracted state of the wound flexible solar wing substrate according to claim 1, characterized in that, Equal-section rotating grooves are formed on the winding storage conical cylinder (2), and the trajectory thereof is an Archimedean spiral with a spatial gradient, for the winding and storage of the coiled wire (3).

9. The axial restraint device in the retracted state of the wound flexible solar wing substrate according to claim 1, characterized in that, One end of the coiled wire (3) is connected to the innermost circle of the winding storage conical cylinder (2), and the other end of the coiled wire (3) is connected to the wire tensioner (4).

10. The axial restraint device for the retracted state of the wound flexible solar wing substrate according to claim 1, wherein The coiled wire (3) includes a Kevlar aramid rope.

Images