Novel hinge for spacecraft unfolding mechanism
By designing a novel hinge structure comprising a first fixing component, a long folding plate, a U-shaped plate, a second fixing component, an L-shaped folding plate, a connecting component, and a telescopic cylinder, the problems of complex structure, large mass, and severe vibration of existing hinges in spacecraft deployment devices are solved, achieving stable and safe deployment movement.
Patent Information
- Application Number
- CN202520613542.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-02
- Publication Date
- 2025-12-23
- Estimated Expiration
- 2035-04-02
AI Technical Summary
Existing spacecraft deployment devices have limited power sources for their hinges, resulting in complex structures, large mass, large space occupation, and severe vibrations in microgravity environments. Furthermore, passively driven hinges release too quickly, causing impacts.
A novel hinge structure is adopted, which includes a first fixing component, a long folding plate, a U-shaped plate, a second fixing component, an L-shaped folding plate, a connecting component, and a telescopic cylinder. The telescopic cylinder provides power, enabling the unfolding plate to move stably and smoothly in retraction and unfolding.
It achieved stable and safe deployment of the spacecraft deployment device, reduced structural complexity and mass, and avoided severe vibration and impact.
Smart Images
Figure CN223708290U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of deployment hinge technology, and more specifically, to a novel hinge for spacecraft deployment mechanisms. Background Technology
[0002] In the aerospace field, many spacecraft have deployable devices. These deployable devices are driven by hinges to unfold. For example, when a satellite is launched, the deployable device is in a retracted state and locked by a locking and releasing device. After entering orbit, it unfolds to the working state according to instructions and is locked.
[0003] Currently common hinges have many problems: there are limitations in terms of power source. Although active drive hinges are reliable and stable, they occupy a lot of space, have a complex structure, are heavy, and are prone to electromagnetic interference. Passive drive hinges use torsion springs as the main power source. If they release too quickly, they will cause a large impact on the spacecraft's deployment device. Moreover, the vibration is more intense in the microgravity environment of space, and the power decays quickly, so they cannot provide a stable power source.
[0004] There are currently no effective solutions to the problems in the relevant technologies. Utility Model Content
[0005] In view of the problems in the related technologies, this utility model proposes a novel hinge for spacecraft deployment mechanisms to overcome the aforementioned technical problems existing in the existing related technologies.
[0006] Therefore, the specific technical solution adopted by this utility model is as follows:
[0007] A novel hinge for a spacecraft deployment mechanism includes a first fixing member, an elongated folding plate rotatably mounted on the inner side of the first fixing member, a U-shaped plate rotatably mounted on the inner side of the other end of the elongated folding plate, a second fixing member rotatably mounted on the other end of the U-shaped plate, an L-shaped folding plate rotatably connected to the inner side of the second fixing member, a connecting member rotatably connected to the outer side of the L-shaped folding plate, and a telescopic cylinder installed between the U-shaped plate and the L-shaped folding plate.
[0008] As a further embodiment of this utility model, an unfolding plate is fixedly installed on the outer side of the first fixing member and the second fixing member respectively.
[0009] As a further embodiment of this utility model, both ends of the telescopic cylinder are fixedly connected to rotating shafts. The rotating shaft at one end of the telescopic cylinder is located inside the U-shaped plate, and the rotating shaft at the other end of the telescopic cylinder is located inside the L-shaped folding plate.
[0010] As a further embodiment of this utility model, the connector is provided in two sets, and the two sets of connectors are respectively located on both sides of the L-shaped folding plate.
[0011] As a further embodiment of this utility model, the other end of the connector is rotatably connected to the first fixing member.
[0012] The beneficial effects of this utility model are as follows:
[0013] This utility model, through the inclusion of a first fixing component, a long folding plate, a U-shaped plate, a second fixing component, an L-shaped folding plate, a connecting component, and a telescopic cylinder, etc., allows the first and second fixing components of this unfolding hinge to be fixedly connected to the unfolding plate. Different arrangement designs can create different unfolding shapes. Buckles are installed on the unfolding plate to connect it to the spacecraft. When the unfolding hinge is in operation, the telescopic cylinder pushes the L-shaped folding plate to move, which in turn drives the connecting component to move the first fixing component. The first and second fixing components are linked through the U-shaped plate and the long folding plate. This unfolding hinge allows adjacent unfolding plates to move relative to each other, forming a closing and unfolding motion. The hinge structure moves stably and smoothly, has a reasonable structure, and makes unfolding safer. Attached Figure Description
[0014] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0015] Figure 1 This is a schematic diagram of the overall structure of a novel hinge for a spacecraft deployment mechanism according to an embodiment of the present utility model;
[0016] Figure 2 This is a schematic diagram of the installation structure of a first fixing member, an L-shaped folding plate, a connecting member, and a second fixing member for a spacecraft deployment mechanism according to an embodiment of the present utility model;
[0017] Figure 3 This is a schematic diagram of the installation structure of a U-shaped plate and a long folding plate for a spacecraft deployment mechanism according to an embodiment of the present utility model;
[0018] Figure 4 This is a schematic diagram of the overall structure of a telescopic cylinder for a spacecraft deployment mechanism according to an embodiment of the present utility model;
[0019] Figure 5 This is an overall bottom view of a spacecraft deployment mechanism according to an embodiment of the present utility model;
[0020] Figure 6 This is an example diagram of the installation of a deployment hinge and deployment plate for a spacecraft deployment mechanism according to an embodiment of the present utility model.
[0021] In the picture:
[0022] 1. First fixing component; 2. Long folding plate; 3. U-shaped plate; 4. Second fixing component; 5. L-shaped folding plate; 6. Connecting component; 7. Telescopic cylinder. Detailed Implementation
[0023] To further illustrate the various embodiments, the present invention provides accompanying drawings, which are part of the disclosure of the present invention. These drawings are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, those skilled in the art should be able to understand other possible implementation methods and the advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are usually used to represent similar components.
[0024] According to an embodiment of the present invention, a novel hinge for a spacecraft deployment mechanism is provided.
[0025] Please refer to the instruction manual appendix. Figure 1-6 According to an embodiment of the present invention, a novel hinge for a spacecraft deployment mechanism includes a first fixing member 1, an elongated folding plate 2 rotatably mounted on the inner side of the first fixing member 1, a U-shaped plate 3 rotatably mounted on the inner side of the other end of the elongated folding plate 2, a second fixing member 4 rotatably mounted on the other end of the U-shaped plate 3, an L-shaped folding plate 5 rotatably connected to the inner side of the second fixing member 4, a connecting member 6 rotatably connected to the outer side of the L-shaped folding plate 5, and a telescopic cylinder 7 installed between the U-shaped plate 3 and the L-shaped folding plate 5.
[0026] The first and second fixing components of this unfolding hinge are fixedly connected to the unfolding plate. Different placement designs can create different unfolding shapes. Buckles are installed on the unfolding plate to connect it to the spacecraft. When the unfolding hinge is working, the L-shaped folding plate is pushed by the telescopic cylinder, which in turn drives the connecting component to move the first fixing component. The first and second fixing components are linked by the U-shaped plate and the long folding plate. This unfolding hinge allows adjacent unfolding plates to move relative to each other, forming a closing and unfolding motion. The hinge structure moves stably and smoothly, with a reasonable structure, making unfolding safer.
[0027] In one embodiment, please refer to the appendix to the specification. Figure 1-6 As a further embodiment of this utility model, an unfolding plate is fixedly installed on the outer side of the first fixing member 1 and the second fixing member 4 respectively.
[0028] This set of unfolding hinges is fixed to the unfolding plate by the first fixing part 1 and the second fixing part 4, so that the two adjacent unfolding plates can be linked together.
[0029] In one embodiment, please refer to the appendix to the specification. Figure 1-6As a further embodiment of this utility model, both ends of the telescopic cylinder 7 are fixedly connected to rotating shafts. The rotating shaft at one end of the telescopic cylinder 7 is located inside the U-shaped plate 3, and the rotating shaft at the other end of the telescopic cylinder 7 is located inside the L-shaped folding plate 5.
[0030] This hinge is powered by a telescopic cylinder 7, which enables the hinge to work.
[0031] In one embodiment, please refer to the appendix to the specification. Figure 1-6 As a further embodiment of this utility model, the connector 6 is provided in two sets, and the two sets of connector 6 are respectively located on both sides of the L-shaped folding plate 5.
[0032] The L-shaped folding plate 5 and the first fixing member 1 are linked by the connector 6.
[0033] In one embodiment, please refer to the appendix to the specification. Figure 1-6 As a further embodiment of this utility model, the other end of the connector 6 is rotatably connected to the first fixing member 1.
[0034] In use, the first fixing component 1 and the second fixing component 4 of this set of unfolding hinges are fixedly connected to the unfolding plate, forming different unfolding shapes through different placement designs. Buckles are installed on the unfolding plate to connect with the spacecraft. When the unfolding hinge is working, the telescopic cylinder 7 pushes the L-shaped folding plate 5 to move, and then the L-shaped folding plate 5 drives the connecting component 6 to move the first fixing component 1. The first fixing component 1 and the second fixing component 4 are linked through the U-shaped plate 3 and the long folding plate 2. This set of unfolding hinges allows two adjacent unfolding plates to move relative to each other, forming a closing and unfolding motion. The hinge structure moves stably and smoothly, with a reasonable structure, making unfolding safer.
[0035] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.
Claims
1. A novel hinge for a spacecraft deployment mechanism, comprising a first fixing member (1), characterized in that: A long folding plate (2) is rotatably installed on the inner side of the first fixing member (1). A U-shaped plate (3) is rotatably installed on the inner side of the other end of the long folding plate (2). A second fixing member (4) is rotatably installed on the other end of the U-shaped plate (3). An L-shaped folding plate (5) is rotatably connected to the inner side of the second fixing member (4). A connecting member (6) is rotatably connected to the outer side of the L-shaped folding plate (5). A telescopic cylinder (7) is installed between the U-shaped plate (3) and the L-shaped folding plate (5).
2. A novel hinge for a spacecraft deployment mechanism according to claim 1, characterized in that: An unfolding plate is fixedly installed on the outer side of the first fixing member (1) and the second fixing member (4).
3. A novel hinge for a spacecraft deployment mechanism according to claim 1, characterized in that: Both ends of the telescopic cylinder (7) are fixedly connected to rotating shafts. The rotating shaft at one end of the telescopic cylinder (7) is located inside the U-shaped plate (3), and the rotating shaft at the other end of the telescopic cylinder (7) is located inside the L-shaped folding plate (5).
4. A novel hinge for a spacecraft deployment mechanism according to claim 1, characterized in that: The connector (6) is provided in two sets, and the two sets of connectors (6) are located on both sides of the L-shaped folding plate (5).
5. A novel hinge for a spacecraft deployment mechanism according to claim 1, characterized in that: The other end of the connector (6) is rotatably connected to the first fixing member (1).