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Small satellite capable of formation flying, and formation of multiple small satellites

一种小型卫星、编队飞行的技术，应用在卫星领域，能够解决没有提供、没有提出防撞特征、外来物体碰撞没有保护等问题，达到避免碰撞、减少可能性、维持寿命的效果

Active Publication Date: 2020-02-04
克劳斯席林
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, collision avoidance with an adaptable collision tube is not described here, and the system is only capable of navigating relative to similar satellites, but has no protection against collisions with foreign objects
the publication does not provide any evidence of how such a change in position or attitude is achieved, and does not propose collision avoidance features

Method used

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  • Small satellite capable of formation flying, and formation of multiple small satellites
  • Small satellite capable of formation flying, and formation of multiple small satellites
  • Small satellite capable of formation flying, and formation of multiple small satellites

Examples

Experimental program
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Embodiment Construction

[0061] exist Figure 1a In , a formation 100 of microsatellites 10 is shown. Formation 100 includes a variety of several spatially adjacent small satellites 10 each capable of observing Earth's surface 108 within a single detection area 102 up to Earth's horizon 106 . By combining the individual detection areas 102 of each small satellite 10, the formation covers a larger detection area 104, which can map a relatively large surface area of ​​the Earth. The center of mass of formation 100 is along orbit 150T above Earth's surface 108 S sports.

[0062] In this figure, a formation 100 is represented as a spatially limited concentration of small satellites 10 to map a large portion of the Earth's surface into a formation's detection region 104 by combining the individual detection regions. Thus, a large area of ​​the Earth's surface 108 may be imaged to the Earth's horizon 106 . A two-way information exchange 110 of the relative attitude / position and trajectory of each satell...

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PUM

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Abstract

The invention relates to a small satellite (10) which is capable of formation flying, in particular a nanosatellite or picosatellite with a mass weight of 10 kg or less, for LEO applications, comprising a housing (12) and at least one insert printed circuit board (14), which is arranged in the housing (12) and comprises a specifiable functionality and a drive system (16) for generating directed impulses in orbit in the direction of a flight trajectory T k . The small satellite (10) comprises an independent and autonomous collision prevention device (18) which is designed to carry out a trajectory correction T kk of the flight trajectory T k by means of the drive system (16) if a collision with a projectile (30) is expected. Another aspect of the invention relates to the formation (100) ofmultiple small satellites (10) which are capable of formation flying, wherein the relative position and the flight trajectory T k of each small satellite (10) can be modified by the independently andautonomously operating collision prevention device (18).

Description

technical field [0001] The invention relates to very small satellites capable of flying in formation, in particular nanosatellites or picometer satellites with a mass of 10 kg or less for LEO (Low Earth Orbit) applications, and several small satellites according to the independent claims formation. Background technique [0002] Small satellites have been known as state-of-the-art since the launch of the first artificial earth satellite with a mass of about 80kg in 1957. Thanks to rapid technological developments, it is now possible to launch small satellites with a mass of less than 10 kg, preferably less than 2 kg, into low earth orbit (LEO) around the Earth, at altitudes between 200 km and a maximum of 1000 km. [0003] In space technology, the clear trend is that traditional large satellites will be supplemented by constellations of distributed smaller satellites. These will be placed in low-Earth orbit with a high inclination for global coverage and a low-latency satel...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10B64G1/24
CPCB64G1/1085B64G1/242G06F11/2038G06F11/2048B64G1/247B64G1/245B64G1/2429B64G1/26B64G1/285B64G1/32B64G1/366
Inventor 克劳斯·席林
Owner 克劳斯席林
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