FIELD: astronautics.
SUBSTANCE: invention relates to CubeSat spacecrafts (SC). SC comprises a parallelepiped-shaped body consisting of side panels (18a...18g) fixed to frame (17) of service equipment in the form of a milled plate. On side and top (-Z) panels, as well as on a camera cover, on side of the bottom panel (+Z), solar panels are installed (conditionally removed, like panels +Y and -Y). On plate (17) there are: power supply and control unit (15), USB antenna (4a, 4b), Ka-band transmitter (14), gyroscope and stellar sensors (not visible). Under plate (17), electrooptical system (9), reaction wheel (not visible) and other elements are fastened by means of frame (16). Top panel (19) has GPS antenna (5) and a USB transceiver antenna. Corner ribs in the joints of the side panels play the role of supporting guides (8) when the SC interacts with the transport-launch container.
EFFECT: technical result is miniaturization of design and airborne systems to the dimensions of the CubeSat satellite with a 16U form factor while performing the target task by the SC, which leads to simplification and acceleration of the process of manufacturing, testing and installation of the SC.
9 cl, 7 dwg
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Authors
Dates
2018-04-19—Published
2017-02-09—Filed