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Trapezoid type small satellite structure suitable for carrying

A technology of satellite structure and form, applied in the field of spacecraft structure, can solve problems such as reducing the volume of the whole satellite, and achieve the effect of reducing weight, simple and convenient connection, and saving space in the satellite

Active Publication Date: 2018-11-13
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

In addition, small satellites are generally launched by carrier rockets carrying large satellites. In order not to affect the normal launch of the main satellite, they can only be installed on the cone section of the carrier. Therefore, it is difficult to adapt to small satellites in the traditional cube or gyratory configuration. Can only reduce the size of the whole star

Method used

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  • Trapezoid type small satellite structure suitable for carrying
  • Trapezoid type small satellite structure suitable for carrying
  • Trapezoid type small satellite structure suitable for carrying

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Embodiment Construction

[0018] The calculation method of the geostationary satellite imaging yaw steering angle proposed by the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0019] Such as Figure 1-Figure 2 As shown, in order to meet the space envelope constraint requirements of the launch fairing, the small satellite structure 1 adopts a trapezoidal configuration as a whole, and is installed on the cone section of the launch vehicle support cabin through a three-point connection. The setting of the connection point 2 way like Figure 2-Figure 3 shown.

[0020] In order to maximize the internal layout space of the structure, during the structural design process, no additional force-transmitting components such as partitions, bulkheads or struts are installed inside the cabin. At the same time, in order to obtain the rigidity of the entire star, in the process of structural design, the embedded frame is laid in ...

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Abstract

The invention discloses a trapezoid type small satellite structure suitable for carrying. A trapezoid type structure is adopted in the small satellite structure. The trapezoid type small satellite structure suitable for the carrying is composed of a honeycomb sandwich plate, an inner embedded frame and a honeycomb embedded part and can be directly installed on a cone section of a carrier rocket supporting cabin in a point-mode manner. An aluminum skin honeycomb sandwich structure is adopted in the honeycomb sandwich plate. According to the trapezoid type small satellite structure suitable forcarrying, through the design, inner embedded beams in the structure form a relatively continuous closed structure, so that effective mechanical supporting and mechanical transmission are realized; andmeanwhile, circuit cables needed for the whole satellite are laid in the inner embedded beams, so that the cables in the cabin are less under in the whole satellite state and the whole satellite inner cabin is effective and concise. The small satellite body structure with special structure has the characteristics of high adaptability to carrying, large internal space, light weight and low processing cost, and the trapezoid type small satellite structure suitable for the carrying is a structural form with high application value on carrying small satellites.

Description

technical field [0001] The invention relates to a spacecraft structure, in particular to a trapezoidal small satellite structure suitable for carrying. Background technique [0002] With the development of aerospace technology, human beings have more and more needs for space exploration. Traditional large satellites have a long development cycle and high cost, which is difficult to meet intensive space exploration tasks; small satellites are low in cost and short in development cycle, especially suitable for scientific experiments. space exploration missions. In addition, small satellites are generally launched by carrier rockets carrying large satellites. In order not to affect the normal launch of the main satellite, they can only be installed on the cone section of the carrier. Therefore, it is difficult to adapt to small satellites in the traditional cube or gyratory configuration. It can only reduce the size of the entire star. In view of this carrying situation, the ...

Claims

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Application Information

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IPC IPC(8): B64G1/10
CPCB64G1/10
Inventor 王智磊袁野薛景赛聂斌斌成飞张国强
Owner SHANGHAI SATELLITE ENG INST
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