Satellite configuration design method adapting to one-rocket multi-satellite launching

A technology of satellite configuration and design method, applied in the field of satellite development, can solve problems such as single pointing direction and inability to adapt to the layout requirements of fixed solar cell arrays

Active Publication Date: 2016-10-26
AEROSPACE DONGFANGHONG DEV LTD
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Problems solved by technology

[0006] The disadvantages of the existing triangular or trapezoidal satellite configurations are: the outer surface has a single pointing dir

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  • Satellite configuration design method adapting to one-rocket multi-satellite launching
  • Satellite configuration design method adapting to one-rocket multi-satellite launching
  • Satellite configuration design method adapting to one-rocket multi-satellite launching

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Embodiment Construction

[0034] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0035] Such as figure 1 As shown, the satellite configuration design method proposed by the present invention is suitable for the configuration design of a low-inclination orbit fixed solar cell array-to-ground three-axis stabilized satellite. The main purpose is to efficiently utilize the envelope space of the carrier fairing, and to design the configuration of multiple satellites of the same type that are launched into orbit through a carrier.

[0036] The idea of ​​the present invention is: in order to make full use of the envelope space in the carrier fairing, under the constraints of a safe distance, for the number of satellites launched with one arrow and multiple satellites (N≥3), determine the maximum envelope of the satellite section, such as figure 1 shown.

[0037] The available envelope space after considering the safety distance ...

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Abstract

The invention relates to the field of satellite development, in particular to a satellite configuration design method adapting to one-rocket multi-satellite launching. According to the method, for the illumination characteristic that the solar angle of a low-dip-angle orbit changes in a large range, an outer surface corresponding to the lower bottom of a satellite trapezoidal cross section is improved to be an arch formed by three panels in an enclosing mode to serve as an installing surface for fixing a solar cell array, and iterative optimization is conducted on included angles of the three cell panels. A satellite configuration designed through the method can be equivalent to the satellite configuration formed by a prismoid with a trapezoidal cross section and two slant prismoids with trapezoidal cross sections. The satellite configuration design method adapting to one-rocket multi-satellite launching has the main advantages that a solar wing spreading and driving mechanism is not arranged for each satellite, the weights of the satellites are reduced, and the reliability of the satellites is improved; a flight mission of long-time over-the-ground three-axis stable operation of a low-oblique-angle orbit can be met.

Description

technical field [0001] The invention relates to the field of satellite research and development, in particular to a satellite configuration design method suitable for launching multiple satellites with one rocket. Background technique [0002] "Global Star" (G10bal-star) satellite, "Earth Gravity Test Satellite" (GRACE) and "Teledisco" (Teledesic) satellite. These satellites adopt a trapezoidal prism in cross-section and a deployed solar wing configuration. [0003] Existing satellite configuration designs include: [0004] 1. Triangular shape: The triangular shape means that the cross-sectional shape of the satellite is a triangle, and the body of the satellite is a triangular prism. Satellites using this shape mainly include the US Landsat-4, "Iridium" satellite and "ELLIPS0" (ELLIPS0) satellite. -2 rocket for "five stars with one arrow" launch or "seven stars with one arrow" launch with Proton rocket. [0005] 2. Trapezoidal shape: The trapezoidal shape means that the...

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Application Information

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IPC IPC(8): B64G1/10B64G1/44B64F5/00
CPCB64F5/00B64G1/10B64G1/443
Inventor 李成魏世隆
Owner AEROSPACE DONGFANGHONG DEV LTD
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