Octagonal battery-equipped array upright post micro satellite configuration

A micro-satellite and battery-installed technology, which is applied in artificial satellites and other directions, can solve problems such as weight, power consumption, and envelope size restrictions, and achieve the effects of reducing installation complexity, saving operating time, and ensuring energy supply

Active Publication Date: 2011-04-13
AEROSPACE DONGFANGHONG SATELLITE
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  • Abstract
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  • Claims
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AI Technical Summary

Problems solved by technology

[0003] However, micro-satellites are generally used to carry and launch, and there are strict restrictions on weight, power consumption, and envelope size. It is necessary to flexibly design the satellite configuration according to the specific shape of the given envelope space.

Method used

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  • Octagonal battery-equipped array upright post micro satellite configuration
  • Octagonal battery-equipped array upright post micro satellite configuration
  • Octagonal battery-equipped array upright post micro satellite configuration

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Embodiment Construction

[0014] The present invention will be further described below in conjunction with accompanying drawing.

[0015] Such as figure 2 As shown, it is an exploded view of the composition of the microsatellite-mounted battery array column configuration of the present invention. For the convenience of description, first establish the body coordinate system (O-XYZ) of the microsatellite, which is defined as follows:

[0016] Coordinate origin O: the theoretical center of the lower end frame of the docking ring 104 and the separation surface of the star and arrow;

[0017] Z axis: pointing away from the star along the coordinate origin;

[0018] Y axis: perpendicular to the direction of the bulkhead, the installation direction of the platform cabin + Y bulkhead 113, load compartment + Y bulkhead 115 is positive;

[0019] X-axis: right-handed system with Z and Y axes.

[0020] In order to make full use of the envelope space provided by the launch vehicle and expand the area of ​​the...

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Abstract

The invention relates to an octagonal battery-equipped array upright post micro satellite configuration. A satellite is designed into a non-equilateral symmetrical octagonal upright post structure; simultaneously, the octagonal configuration and the internal space design of the satellite are optimized; the satellite is partitioned into a platform cabin and a load cabin; a cabin section between a top plate and a middle plate is the platform cabin; and a cabin section between the middle plate and a bottom plate is the load cabin. Each cabin section is partitioned into three regions through a +Y clapboard and a -Y clapboard; according to equipment enveloping size, reasonable layout and arrangement are performed, the design of a main force transfer path is optimized and cable direction and the insertion space of an electric connector are fully considered, so that a compact and reasonable structural space can be ensured; simultaneously, an enveloping space provided for carrying rocket is fully utilized and the solar cell installation area of a satellite body is enlarged to the greatest extent.

Description

technical field [0001] The present invention relates to a configuration for piggybacked microsatellites. Background technique [0002] The configuration layout of my country's small satellites is generally a cubic configuration plus double solar wings on both sides. The interior of the star adopts a platform cabin and payload cabin-style sub-compartment design. Like the relatively mature public small satellite platforms such as CAST968 and CAST2000, this configuration can meet the requirements of the weight of the current small satellite, the given envelope space for carrying, and the installation and operation space for equipment. [0003] However, micro-satellites are generally used to carry and launch, and there are strict restrictions on weight, power consumption, and envelope size. It is necessary to flexibly design the satellite configuration according to the specific shape of the given envelope space. The installation position of the microsatellite in the launch vehi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10
Inventor 罗鹰常新亚张晓敏包锦忠蒋炎华
Owner AEROSPACE DONGFANGHONG SATELLITE
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