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Satellite comprising optical photography instrument

An optical instrument, satellite technology, used in the field of observation or measurement of satellites

Active Publication Date: 2018-06-08
AIRBUS DEFENCE & SPACE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0015] in prior art designs the length of the satellite is already partially occupied by the support structure, so the length of the instrument and thus the diameter of the instrument is limited by the diameter of the payload fairing or dual launch structure

Method used

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  • Satellite comprising optical photography instrument
  • Satellite comprising optical photography instrument
  • Satellite comprising optical photography instrument

Examples

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Embodiment Construction

[0040] figure 1 It has been explained in the introduction.

[0041] exist figure 2 and image 3 , a first embodiment of a satellite 1 according to the invention is illustrated, comprising a launch vehicle interface system 2 to be detachably fixed to a image 3 The satellite interface system 2' of the satellite launch vehicle indicated by the dotted line in . Interface system 2 is usually an interface ring with axis A, which is the case in the following description. The diameter of the interface ring 2 is usually selected from standard spatial dimensions, namely: 937mm, 1194mm and 1666mm. The satellite interface system 2' is annular and has complementary dimensions. The two rings 2, 2' are secured by means of a locking mechanism, not shown here, for example in the form of a clamping strap, also called a strap, which is integral with one of the two rings, which Preferably it is the launch vehicle interface ring 2 of the satellite 1 .

[0042] The satellite 1 includes an ...

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Abstract

The invention relates to a satellite (1) which comprises: at least one optical photography instrument (3) comprising a main lens having an optical axis (V) and the optical instrument (3) having a field of view; at least one launcher interface system (2), intended for being removably secured to a satellite interface system (2') of a launcher of the satellite; and a linking device (7) between the launcher interface (2) and the optical instrument (3) extending substantially parallel to the optical axis (V) of the main lens between an upper end (9) and a lower end (10). The launcher interface system (2) is connected to the linking device (7) by the lower end (10) and the optical axis (V) of the optical instrument (3) is directed from the upper end (9) towards the lower end (10) of the linkingdevice (7), the launcher interface system being outside the field of view of the instrument.

Description

technical field [0001] The invention relates to the field of space vehicles, in particular satellites whose tasks involve the presence of optical instruments, such as satellites for observation or measurement. Background technique [0002] In order to release a satellite in space, the satellite must first be installed and fixed on a launch vehicle. The launch vehicle is then propelled into space, and the satellite is then separated from the launch vehicle for release in its defined orbit. [0003] Before release, and during the release phase, a satellite on a launch vehicle is subjected to a number of stresses related to shock and vibration, the attachment of the satellite to the launch vehicle and the satellite itself must be able to withstand said stresses. However, the transfer of stress to the satellite must be carefully controlled, especially if the satellite has delicate optical instruments that can be deflected or damaged by shock and vibration. [0004] Optical ins...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10B64G1/64
CPCB64G1/405B64G1/10B64G1/641B64G1/1021B64G1/402B64G1/1028G02B23/02G03B15/006G02B23/16
Inventor 弗雷德里克·法耶埃里克·博菲梅杰克奎斯·科蒂厄
Owner AIRBUS DEFENCE & SPACE
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