Solar wing hinge driven by elastic force
An elastic drive and elastic force technology, applied in the field of solar wing hinges, can solve the problems of solar wing damage, large space envelope size, inconvenient adjustment, etc., and achieve the effect of strong unfolding and locking rigidity, small impact, and simple hinge structure
Active Publication Date: 2021-06-22
SHANGHAI ASES SPACEFLIGHT TECH LTD CO
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Problems solved by technology
[0003] The scroll spring hinge has a large torque, but the space envelope size is also large, which is suitable for solar wings with large mass characteristics; the torsion spring hinge has moderate torque, but is inconvenient to adjust, and is suitable for small satellite solar wings; The hinge is suitable for tiny solar wings with low requirements for deployment stiffness
At the same time, these types of solar wing hinges will have a greater impact at the end of the solar wing deployment, which will cause a certain degree of damage to the solar wing
Method used
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[0043] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments. Advantages and features of the present invention will be apparent from the following description and claims. It should be noted that the drawings are all in a very simplified form and use imprecise ratios, which are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention.
[0044] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relationship between the components in a certain posture (as shown in the accompanying drawings). Relative positional relationship, movement conditions, etc., if the specific posture changes, the directional indication will also change accordingly.
[0045] see Figures 1 to 5 , The core of the present invention is to provide a solar...
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The invention discloses a solar wing hinge driven by elastic force. The solar wing hinge comprises a female mounting seat; a male mounting seat which is hinged to the female installation seat through a first hinge assembly, wherein the first hinge assembly is located between the first end and the second end of the public security installation seat, and a locking hole is formed in the first end of the public security installation seat; an elastic driving mechanism, wherein the two ends of the elastic driving mechanism are connected to the female mounting base and the public security mounting base respectively, and the elastic driving mechanism stores elastic energy and is used for driving the second end of the public security mounting base to rotate around the female mounting base; a locking ejector rod which is connected to the female mounting base in a sliding mode, wherein the sliding position of the locking ejector rod is limited through a limiting part, one end face of the locking ejector rod is located on the rotating path of the first end of the female mounting base, and the axis of the locking ejector rod is tangent to the rotating path of the locking hole; and a locking elastic piece which is arranged on the female mounting seat and applies elastic force towards the limiting part to the locking ejector rod. The hinge is simple in structure and small in impact at the end of unfolding.
Description
technical field [0001] The invention belongs to the technical field of hinges, in particular to a solar wing hinge driven by elastic force. Background technique [0002] Micro-nano satellites are constrained by the weight and size envelope, which limits the power supply capability. After the satellite is launched into orbit, the solar wings usually need to be deployed. As the energy storage part of the solar wing motion mechanism, the solar wing hinge provides power for the deployment of the solar wing. The existing solar wing hinges can be divided into scroll spring type, torsion spring type and strip spring type according to the type of energy storage components. According to the rigidity requirements of different satellites for the solar wing, select the hinge of the corresponding energy storage type. [0003] The scroll spring hinge has a large torque, but the space envelope size is also large, which is suitable for solar wings with large mass characteristics; the tors...
Claims
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IPC IPC(8): B64G1/44B64G1/10
CPCB64G1/44B64G1/10
Inventor 熊怀郑琦张振峰戴华杰胡洵郑开明施旻庞玉泽
Owner SHANGHAI ASES SPACEFLIGHT TECH LTD CO