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Method for changing spacecraft attitude through memory alloy

A memory alloy and spacecraft technology, applied in the aerospace field, can solve problems such as magnetic barriers and poor communication, and achieve cost savings, prevent mechanism damage from opening, and strong real-time performance

Inactive Publication Date: 2019-11-08
昆明研顶技术开发有限公司
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  • Abstract
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Problems solved by technology

However, due to the high speed of the spacecraft, there will be a magnetic barrier, and the communication of the satellite recovery at the end position is not smooth, and the parachute cannot be opened accurately

Method used

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  • Method for changing spacecraft attitude through memory alloy

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Embodiment Construction

[0026] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in combination with specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are exemplary only, and are not intended to limit the scope of the present invention. Also, in the following description, descriptions of well-known structures and techniques are omitted to avoid unnecessarily obscuring the concept of the present invention.

[0027] see figure 1, a method for changing the attitude of a spacecraft by using memory alloys, specifically, setting memory alloys at the joints of the parts where the spacecraft needs to be deployed, and setting a semiconductor film 3 and a temperature sensor 1 that can be used for temperature control on the inner layer of the memory alloys; The temperature at the predetermined orbit sets a stable deformation structure...

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Abstract

The invention relates to a method for changing the spacecraft attitude through memory alloy, and belongs to the technical field of aerospace. The memory alloy is arranged at the joint of a spacecraftpart needing to be unfolded, a semiconductor film and a temperature sensor which can achieve temperature control are arranged on the inner layer of the memory alloy, under high temperature conditions,a spacecraft is in a unfolded state due to the structure of the memory alloy, when the spacecraft reaches a predetermined orbit, the temperature of the memory alloy is lowered, and the memory alloy can perfectly return to the desired shape and structure. Meanwhile, a control mechanical part opened by a control umbrella is provided with memory alloy, before the spacecraft needs to be recycled, thememory alloy is exposed to the outside for atmosphere rubbing and automatically changed into a predetermined structure after reaching a predetermined temperature, and the spacecraft is recycled. Theprocess does not require energy, control is not needed, a large amount of remote sensing resources does not need to be occupied, the magnetic barrier problem is solved, the cost is reduced, and meanwhile, the situation that a mechanism is damaged and cannot be opened can be avoided.

Description

technical field [0001] The invention relates to a method for changing the attitude of a spacecraft by using a memory alloy, which belongs to the technical field of aerospace. Background technique [0002] With the development of society and science and technology, many civilian small satellites have been born, but because of the limited use of such satellites, the cost of using existing remote sensing equipment to control their deployment after entering orbit is relatively high. The attitude control method of the aircraft that automatically unfolds after the predetermined orbit will have great application value. [0003] Traditional spacecraft need to be deployed after reaching the predetermined orbit, but the current deployment structure adopts electromechanical control, and the deployment mechanism is controlled by the control system for deployment. Due to the complexity of the deployment mechanism, the situation that it cannot be deployed will occur for various reasons b...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/22B64G1/24B64G1/62
CPCB64G1/222B64G1/24B64G1/62B64G1/245
Inventor 不公告发明人
Owner 昆明研顶技术开发有限公司
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