公开(公告)号：US10659159B2

公开(公告)日：2020-05-19

申请号：US16341274

申请日：2017-09-28

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Jean Sperandei ,  Gilles Planche

IPC: H04B10/118 ,  H04B10/50

Abstract: A combined system for imaging and communication by laser signals including a telescope (10) in which the primary (1) and secondary (2) mirrors are shared between an imaging function and a function involving the emission of laser transmission signals. The accuracy required for the direction of emission (DE) of the laser transmission signals is obtained by additionally placing a geolocation device on board a satellite carrying the combined system. No coarse pointing assembly is used and it is also possible for the system to be devoid of any fine pointing assembly and target acquisition and tracking detector.

公开(公告)号：US09988162B2

公开(公告)日：2018-06-05

申请号：US15039018

申请日：2014-11-24

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Nicolas Cuilleron ,  Jean Sperandei ,  Philippe Laurens

IPC: B64G1/28 ,  B64G1/44 ,  B64G1/40 ,  B64G1/24

CPC classification number: B64G1/443 ,  B64G1/222 ,  B64G1/242 ,  B64G1/283 ,  B64G1/286 ,  B64G1/405

Abstract: A method to control a sunlight acquisition phase of a spacecraft with a nonzero angular momentum of an axis DH. The spacecraft includes a solar generator configured to rotate about an axis Y. The spacecraft actuators are controlled to place the spacecraft in an intermediate orientation in which the axis Y is substantially orthogonal to the axis DH. The solar generator is controlled to orientate the solar generator towards the sun. The spacecraft actuators are controlled to reduce the angular momentum of the spacecraft. The actuators of the spacecraft engine are controlled to place the spacecraft in an acquisition orientation in which the axis Y is substantially orthogonal to the direction of the sun with respect to the spacecraft.