Flexible solar wing supporting and unloading device for spacecraft

Abstract

The flexible solar wing supporting and unloading device for the spacecraft is characterized in that a first supporting plate is arranged at the top of a first supporting framework, a first positioning hole is formed in the first supporting plate, a first limiting device is arranged on one side of the first supporting framework, and a first limiting plate of the first limiting device is arranged above the first supporting plate; a second supporting plate is arranged at the top of the second supporting framework, a second positioning hole is formed in the second supporting plate, the second limiting device is arranged on one side of the second supporting framework, and a second limiting plate of the second limiting device is arranged below the second supporting plate; the first supporting framework and the second supporting framework are connected through a connecting piece, and a gap exists between the first supporting framework and the second supporting framework which are connected. According to the invention, precision maintenance of composite substrates with different thicknesses in a horizontal unloading state and a narrow space stitching area and simultaneous tension loading of the two substrates are realized.

Description

Technical Field

[0001] The invention belongs to the field of aerospace equipment, and in particular relates to a flexible solar wing supporting and unloading device for a spacecraft. Background Art

[0002] The solar wing is made of multiple polyimide films connected to a fiber fabric composite substrate. In order to ensure the long-term safe operation of the solar wing in orbit, the solar wing in orbit is required to maintain tension. In order to meet the surface accuracy of the solar wing in orbit, the dimensional accuracy and surface tension consistency of each sector substrate are required to be controlled during the ground assembly of the solar wing. A set of mechanisms is required for substrate shape retention and surface tension loading. When the substrate is connected, the solar wing support unloading and blanket surface tension device are required; when investigating the same type of solar wings abroad, there is no public literature reporting on the process content of solar wing substrate connection and substrate tension control; in the traditional textile industry, the common methods for fabric tensioning include multiple clips, roller structures or telescopic devices to tension single-layer fabrics or multi-layer fabrics; except for the connection edge and the binding edge, the rest of the solar wing composite substrate is pasted with battery cells, which are fragile structures and difficult to replace. The binding edge is connected to the support frame. Based on the safety protection of the battery cells, the tension loading process does not allow the battery cell pasting area to be suspended, bent, or squeezed, and the accuracy of the solar wing composite substrate must be maintained before stitching; the existing fabric tensioning device does not meet the battery cell safety protection conditions to tension the two composite substrates separately, and does not have the ability to maintain the dimensional accuracy of the composite substrate. Summary of the invention

[0003] In view of this, the present invention aims to propose a flexible solar wing support and unloading device for spacecraft, which solves the requirements of precision maintenance and tension loading of the solar wing composite substrate.

[0004] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0005] A flexible solar wing supporting and unloading device for a spacecraft, characterized in that: it comprises a No. 1 supporting frame, a No. 2 supporting frame, a No. 1 supporting plate, a No. 2 supporting plate, a No. 1 limiting device, and a No. 2 limiting device, wherein a No. 1 supporting plate is provided on the top of the No. 1 supporting frame, a No. 1 positioning hole is provided on the No. 1 supporting plate, the No. 1 limiting device is provided on one side of the No. 1 supporting frame, and the No. 1 limiting plate of the No. 1 limiting device is provided above the No. 1 supporting plate; a No. 2 supporting plate is provided on the top of the No. 2 supporting frame, a No. 2 positioning hole is provided on the No. 2 supporting plate, the No. 2 limiting device is provided on one side of the No. 2 supporting frame, and the No. 2 limiting plate of the No. 2 limiting device is provided below the No. 2 supporting plate; the No. 1 supporting frame and the No. 2 supporting frame are connected by a connecting piece, and there is a gap between the No. 1 supporting frame and the No. 2 supporting frame after the connection.

[0006] Furthermore, the No. 1 support frame and the No. 2 support frame are both composed of a number of steel beams to form a frame structure, and the bottoms of the No. 1 support frame and the No. 2 support frame are both provided with universal wheels.

[0007] Furthermore, the No. 1 support plate and the No. 2 support plate are both fan-shaped structures that fit with the blades of the solar wing. The No. 1 support plate is installed to the No. 1 support frame through countersunk screws, and the No. 2 support plate is also installed to the No. 1 support frame through countersunk screws.

[0008] Furthermore, the No. 1 limiting device includes a No. 1 double lifting mechanism, a No. 1 front mounting plate, a No. 1 rear mounting plate, a No. 1 front connecting frame, a No. 1 rear connecting frame, a No. 1 connecting rod and a No. 1 limiting plate; the two ends of the No. 1 double lifting mechanism are installed on the No. 1 supporting frame through the No. 1 front mounting plate and the No. 1 rear mounting plate, the bottom of the No. 1 front connecting frame is connected to one lifting end of the No. 1 double lifting mechanism, and the bottom of the No. 1 rear connecting frame is connected to the other lifting end of the No. 1 double lifting mechanism; the No. 1 double lifting mechanism is provided with a hand wheel for controlling the simultaneous lifting of the No. 1 front connecting frame and the No. 1 rear connecting frame, the No. 1 front connecting frame and the No. 1 rear connecting frame are connected through the No. 1 connecting rod, and the No. 1 connecting rod is provided with a No. 1 limiting plate.

[0009] Furthermore, the No. 1 front mounting plate is provided with a No. 1 front guide column, and the bottom end of the No. 1 front connecting frame is provided with a guide ring, and the guide ring connects the No. 1 front connecting frame and the No. 1 front guide column to realize the linear movement of the No. 1 front connecting frame.

[0010] Furthermore, the No. 2 limiting device includes a No. 2 double lifting mechanism, a No. 2 front mounting plate, a No. 2 rear mounting plate, a No. 2 front connecting frame, a No. 2 rear connecting frame, a No. 2 connecting rod and a No. 2 limiting plate; both ends of the No. 2 double lifting mechanism are installed on the No. 2 supporting frame through the No. 2 front mounting plate and the No. 2 rear mounting plate, the bottom of the No. 2 front connecting frame is connected to one lifting end of the No. 2 double lifting mechanism, and the bottom of the No. 2 rear connecting frame is connected to the other lifting end of the No. 2 double lifting mechanism; the No. 2 double lifting mechanism is provided with a hand wheel for controlling the simultaneous lifting of the No. 2 front connecting frame and the No. 2 rear connecting frame, the No. 2 front connecting frame and the No. 2 rear connecting frame are connected through the No. 2 connecting rod, and the No. 2 connecting rod is provided with a No. 2 limiting plate.

[0011] Furthermore, the No. 2 front mounting plate is provided with a No. 2 front guide column, and the bottom end of the No. 2 front connecting frame is provided with a guide ring, and the guide ring connects the No. 2 front connecting frame and the No. 2 front guide column to realize the linear movement of the No. 2 front connecting frame.

[0012] Furthermore, the first limiting plate and the second limiting plate are both tilted, and the tilt angle is 45 degrees.

[0013] Compared with the prior art, the flexible solar wing support and unloading device for spacecraft described in the present invention has the following advantages:

[0014] The flexible solar wing support and unloading device for spacecraft described in the present invention realizes horizontal unloading of two composite substrates and dimensional accuracy maintenance of the support plate and the positioning holes thereon, and the limit device realizes horizontal bonding of non-horizontally tensioned composite substrates in the suture area. It realizes the precision maintenance of composite substrates of different thicknesses and suture areas in narrow spaces in the horizontal unloading state, and the simultaneous tension loading of two substrates. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0016] Figure 1 This is a schematic diagram of a flexible solar wing support and unloading device for a spacecraft according to an embodiment of the present invention;

[0017] Figure 2 This is a schematic diagram of a No. 1 limiting device according to an embodiment of the present invention;

[0018] Figure 3 This is a schematic diagram of a second limiting device according to an embodiment of the present invention;

[0019] Figure 4 For the embodiment of the present invention Figure 1 A partial enlarged view of middle A.

[0020] Description of reference numerals:

[0021] 1. Support frame No. 1; 2. Support frame No. 2; 3. Support plate No. 1; 4. Support plate No. 2; 5. Limiting device No. 1; 51. Double lifting mechanism No. 1; 52. Front mounting plate No. 1; 53. Rear mounting plate No. 1; 54. Front connecting frame No. 1; 55. Rear connecting frame No. 1; 56. Connecting rod No. 1; 57. Limiting plate No. 1; 6. Limiting device No. 2; 61. Double lifting mechanism No. 2; 62. Front mounting plate No. 2; 63. Rear mounting plate No. 2; 64. Front connecting frame No. 2; 65. Rear connecting frame No. 2; 66. Connecting rod No. 2; 67. Limiting plate No. 2; 7. Universal wheel. DETAILED DESCRIPTION

[0022] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0023] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention 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 cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0024] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0025] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0026] A flexible solar wing support and unloading device for a spacecraft, such as Figure 1-Figure 4 As shown, it includes a No. 1 support frame 1, a No. 2 support frame 2, a No. 1 support plate 3, a No. 2 support plate 4, a No. 1 limiting device 5, and a No. 2 limiting device 6. The top of the No. 1 support frame 1 is provided with a No. 1 support plate 3, the No. 1 support plate 3 is provided with a No. 1 positioning hole, the No. 1 limiting device 5 is arranged on one side of the No. 1 support frame 1, and the No. 1 limiting plate 57 of the No. 1 limiting device 5 is arranged above the No. 1 support plate 3; the top of the No. 2 support frame 2 is provided with a No. 2 support plate 4, the No. 2 support plate 4 is provided with a No. 2 positioning hole, the No. 2 limiting device 6 is arranged on one side of the No. 2 support frame 2, and the No. 2 limiting plate 67 of the No. 2 limiting device 6 is arranged below the No. 2 support plate 4; the No. 1 support frame 1 and the No. 2 support frame 2 are connected by a connecting piece, and there is a gap between the No. 1 support frame 1 and the No. 2 support frame 2 after connection.

[0027] Preferably, the No. 1 positioning hole and the No. 2 positioning hole can be one or more; the positioning holes are used to maintain the shape and position accuracy of the composite substrate; the composite substrate A of the solar wing is fixed to the No. 1 support plate 3, and the composite substrate B is fixed to the No. 2 support plate 4; the process edge of the composite substrate A is fitted under the limiting device and connected to apply tension, and the process edge of the composite substrate B is fitted on the limiting device and connected to apply tension; the lifting mechanism of the No. 1 limiting device 5 and the No. 2 limiting device 6 is adjusted to ensure that the overlapping areas of the tensioned composite substrates A and B are horizontally fitted.

[0028] Preferably, the No. 1 support frame 1 and the No. 2 support frame 2 are both composed of a number of steel beams to form a frame structure, and the bottoms of the No. 1 support frame 1 and the No. 2 support frame 2 are both provided with universal wheels 7 for pushing the entire device.

[0029] Preferably, the No. 1 support plate 3 and the No. 2 support plate 4 are both fan-shaped structures that fit with the blades of the solar wing. The No. 1 support plate 3 is installed to the No. 1 support frame 1 through countersunk screws, and the No. 2 support plate 4 is also installed to the No. 1 support frame 1 through countersunk screws. The countersunk screws are used to allow the screws to fully enter the support plates, so that the surface of the support plates is flat and free of protrusions.

[0030] Preferably, the No. 1 limiting device 5 includes a No. 1 double lifting mechanism 51, a No. 1 front mounting plate 52, a No. 1 rear mounting plate 53, a No. 1 front connecting frame 54, a No. 1 rear connecting frame 55, a No. 1 connecting rod 56 and a No. 1 limiting plate 57; both ends of the No. 1 double lifting mechanism are installed on the No. 1 supporting frame 1 through the No. 1 front mounting plate 52 and the No. 1 rear mounting plate 53, the bottom of the No. 1 front connecting frame 54 is connected to one lifting end of the No. 1 double lifting mechanism 51, and the bottom of the No. 1 rear connecting frame 55 is connected to the other lifting end of the No. 1 double lifting mechanism 51; the No. 1 double lifting mechanism 51 is provided with a hand wheel for controlling the simultaneous lifting of the No. 1 front connecting frame 54 and the No. 1 rear connecting frame 55, the No. 1 front connecting frame 54 and the No. 1 rear connecting frame 55 are connected by a No. 1 connecting rod 56, and the No. 1 connecting rod 56 is provided with a No. 1 limiting plate 57, and the No. 1 double lifting mechanism 51 is a common linkage lifting mechanism on the market.

[0031] Preferably, the No. 1 front mounting plate 52 is provided with a No. 1 front guide column, and the bottom end of the No. 1 front connecting frame 54 is provided with a guide ring, and the guide ring connects the No. 1 front connecting frame 54 and the No. 1 front guide column to realize the linear movement of the No. 1 front connecting frame 54.

[0032] Preferably, the No. 2 limiting device 6 includes a No. 2 double lifting mechanism 61, a No. 2 front mounting plate 62, a No. 2 rear mounting plate 63, a No. 2 front connecting frame 64, a No. 2 rear connecting frame 65, a No. 2 connecting rod 66 and a No. 2 limiting plate 67; both ends of the No. 2 double lifting mechanism are installed on the No. 2 supporting frame 2 through the No. 2 front mounting plate 62 and the No. 2 rear mounting plate 63, the bottom of the No. 2 front connecting frame 64 is connected to one lifting end of the No. 2 double lifting mechanism 61, and the bottom of the No. 2 rear connecting frame 65 is connected to the other lifting end of the No. 2 double lifting mechanism 61; the No. 2 double lifting mechanism 61 is provided with a hand wheel for controlling the simultaneous lifting of the No. 2 front connecting frame 64 and the No. 2 rear connecting frame 65, the No. 2 front connecting frame 64 and the No. 2 rear connecting frame 65 are connected through the No. 2 connecting rod 66, and the No. 2 connecting rod 66 is provided with a No. 2 limiting plate 67.

[0033] Preferably, the No. 2 front mounting plate 62 is provided with a No. 2 front guide column, and the bottom end of the No. 2 front connecting frame 64 is provided with a guide ring, and the guide ring connects the No. 2 front connecting frame 64 and the No. 2 front guide column to realize the linear movement of the No. 2 front connecting frame 64.

[0034] Preferably, the first limiting plate 57 and the second limiting plate 67 are both inclined, and the inclination angle is 45 degrees.

[0035] Working principle: adjust the position status of the No. 1 support plate 3 and the No. 2 support plate 4 to ensure that the hole position accuracy of the positioning holes meets the index requirements; transfer the composite substrate A to the No. 1 support plate 3, and the support frame of the composite substrate A is connected and fixed to the No. 1 positioning hole through the positioning pin; transfer the composite substrate B to the No. 2 support plate 4, and the support frame of the composite substrate B is connected and fixed to the No. 2 positioning hole through the positioning pin; the process edge of the composite substrate A is fitted under the limiting device and connected to apply tension, and the process edge of the composite substrate B is fitted on the limiting device and connected to apply tension to ensure flatness.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A flexible solar wing support and unloading device for a spacecraft, characterized in that: It includes a No. 1 support frame, a No. 2 support frame, a No. 1 support plate, a No. 2 support plate, a No. 1 limiting device, and a No. 2 limiting device. The top of the No. 1 support frame is provided with a No. 1 support plate, the No. 1 support plate is provided with a No. 1 positioning hole, the No. 1 limiting device is provided on one side of the No. 1 support frame, and the No. 1 limiting plate of the No. 1 limiting device is provided above the No. 1 support plate; the top of the No. 2 support frame is provided with a No. 2 support plate, the No. 2 support plate is provided with a No. 2 positioning hole, the No. 2 limiting device is provided on one side of the No. 2 support frame, and the No. 2 limiting plate of the No. 2 limiting device is provided below the No. 2 support plate; the No. 1 support frame and the No. 2 support frame are connected by a connecting piece, and there is a gap between the No. 1 support frame and the No. 2 support frame after connection.

2. The flexible solar wing support and unloading device for a spacecraft according to claim 1, characterized in that: The No. 1 support frame and the No. 2 support frame are both composed of a number of steel beams to form a frame structure, and the bottoms of the No. 1 support frame and the No. 2 support frame are both provided with universal wheels.

3. The flexible solar wing support and unloading device for a spacecraft according to claim 1, characterized in that: The No. 1 support plate and the No. 2 support plate are both fan-shaped structures that fit with the blades of the solar wing. The No. 1 support plate is installed to the No. 1 support frame through countersunk screws, and the No. 2 support plate is also installed to the No. 1 support frame through countersunk screws.

4. The flexible solar wing support and unloading device for a spacecraft according to claim 1, characterized in that: The No. 1 limiting device includes a No. 1 double lifting mechanism, a No. 1 front mounting plate, a No. 1 rear mounting plate, a No. 1 front connecting frame, a No. 1 rear connecting frame, a No. 1 connecting rod and a No. 1 limiting plate; both ends of the No. 1 double lifting mechanism are installed on the No. 1 supporting frame through the No. 1 front mounting plate and the No. 1 rear mounting plate, the bottom of the No. 1 front connecting frame is connected to one lifting end of the No. 1 double lifting mechanism, and the bottom of the No. 1 rear connecting frame is connected to the other lifting end of the No. 1 double lifting mechanism; the No. 1 double lifting mechanism is provided with a hand wheel for controlling the simultaneous lifting of the No. 1 front connecting frame and the No. 1 rear connecting frame, the No. 1 front connecting frame and the No. 1 rear connecting frame are connected through the No. 1 connecting rod, and the No. 1 connecting rod is provided with a No. 1 limiting plate.

5. The flexible solar wing support and unloading device for a spacecraft according to claim 4, characterized in that: The No. 1 front mounting plate is provided with a No. 1 front guide column, and the bottom end of the No. 1 front connecting frame is provided with a guide ring, and the guide ring connects the No. 1 front connecting frame and the No. 1 front guide column to realize the linear movement of the No. 1 front connecting frame.

6. The flexible solar wing support and unloading device for a spacecraft according to claim 1, characterized in that: The No. 2 limiting device comprises a No. 2 double lifting mechanism, a No. 2 front mounting plate, a No. 2 rear mounting plate, a No. 2 front connecting frame, a No. 2 rear connecting frame, a No. 2 connecting rod and a No. 2 limiting plate; both ends of the No. 2 double lifting mechanism are mounted on the No. 2 supporting frame through the No. 2 front mounting plate and the No. 2 rear mounting plate, the bottom of the No. 2 front connecting frame is connected to one lifting end of the No. 2 double lifting mechanism, and the bottom of the No. 2 rear connecting frame is connected to the other lifting end of the No. 2 double lifting mechanism; the No. 2 double lifting mechanism is provided with a hand wheel for controlling the simultaneous lifting of the No. 2 front connecting frame and the No. 2 rear connecting frame, the No. 2 front connecting frame and the No. 2 rear connecting frame are connected through the No. 2 connecting rod, and the No. 2 connecting rod is provided with a No. 2 limiting plate.

7. A flexible solar wing support and unloading device for a spacecraft according to claim 6, characterized in that: The No. 2 front mounting plate is provided with a No. 2 front guide column, and the bottom end of the No. 2 front connecting frame is provided with a guide ring, and the guide ring connects the No. 2 front connecting frame and the No. 2 front guide column to realize the linear movement of the No. 2 front connecting frame.

8. The flexible solar wing support and unloading device for a spacecraft according to claim 1, characterized in that: The first limiting plate and the second limiting plate are both tilted, and the tilt angles are both 45 degrees.

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