Satellite module for attitude determination
A satellite module for attitude determination includes a containment body comprising at least one data acquisition board and a connection interface, at least one first-type sensor selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, in communication with the data acquisition board and at least one second-type sensor, different from the first type, selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, and in communication with the data acquisition board. The connection interface may be mounted on a first face of the containment body, the first-type sensor may be mounted on a second face of the containment body, and the second-type sensor may be mounted on a third face of the containment body.
1 . A satellite module for attitude determination comprising:
a polyhedral containment body configured to be mounted on a satellite and comprising at least one data acquisition board and a connection interface for allowing the data acquisition board to be in signal communication and electrical communication with the satellite;
at least one first-type sensor selected from a sun sensor, an earth sensor, a stellar sensor, and a horizon sensor, in communication with the data acquisition board and at least one second-type sensor, different from the at least first type-sensor, selected from a sun sensor, an earth sensor, a stellar sensor, and a horizon sensor, and in communication with the data acquisition board; and
wherein the connection interface is mounted directly on a first face of the polyhedral containment body, the at least one first-type sensor is mounted directly on a second face of the polyhedral containment body, and the at least one second-type sensor is mounted directly on a third face of the polyhedral containment body.
2 . The satellite module according to claim 1 , wherein the at least one first-type sensor comprises an earth sensor or a sun sensor and wherein the at least one second-type sensor comprises a stellar sensor.
3 . The satellite module according claim 1 , wherein the first-type sensor has a field of view having an angular diameter of at least 60 degrees.
4 . The satellite module according to claim 2 , wherein the stellar sensor has a field of view having an angular diameter higher than 15 degrees.
5 . The satellite module according to claim 1 , comprising at least one third-type sensor, different from the at least one first-type sensor and the at least one second-type sensor, directly mounted on a fourth face of the polyhedral containment body, the at least one third-type sensor being selected from a sun sensor, an earth sensor, and a horizon sensor.
6 . The satellite module according to claim 5 , wherein both one of the at least one first-type sensor and one of the at least one third-type sensor are mounted on the second face and on the fourth face.
7 . The satellite module according to claim 5 , wherein the polyhedral containment body comprises a top face and a front face, between which a plurality of connecting faces extend; the second face or the fourth face being identified by two of said plurality of connecting faces, wherein one of the at least one first-type sensor is mounted directly on each connecting face of said plurality of connecting faces.
8 . The satellite module according to claim 7 , wherein both one of the at least one first-type sensor and one of the at least one third-type sensor are directly mounted on each of the plurality of connecting faces.
9 . The satellite module according to claim 7 , wherein the plurality of connecting faces comprises four connecting faces, each of the four connecting faces forming an angle between 10 degrees and 25 degrees with an adjacent connecting face, and wherein each of the at least one first-type sensor is oriented according to an orientation of the connecting face that the at least one first-type sensor is mounted on.
10 . The satellite module according to claim 7 , wherein the polyhedral containment body comprises a lateral face and at least one intermediate face which extends between the lateral face and the front face; at least one of the at least one first-type sensor or at least one of the at least one third-type sensor being directly mounted on the intermediate face.
11 . The satellite module according to claim 10 , comprising two intermediate faces, wherein a first intermediate face forms an angle between 20 degrees and 40 degrees with a second intermediate face, at least one of the at least one first-type sensor or at least one of the third-type sensor being directly mounted on each intermediate face and oriented according to an orientation of the intermediate face.
12 . A satellite of cuboidal shape and having six faces and eight vertices, comprising:
at least eight satellite modules according to claim 1 placed at the eight vertices of the satellite;
each satellite module being oriented so that both the at least one first-type sensor and the at least one second-type sensor are oriented perpendicularly to the six faces of the satellite;
wherein the at least one first-type sensor comprises at least two first-type sensors oriented redundantly; and
wherein the at least one second-type sensor comprises at least two second-type sensors oriented redundantly.
13 . The satellite module according to claim 5 , wherein the at least one first-type sensor, the at least one second-type sensor, and the at least one third-type sensor are mounted externally on the polyhedral containment body so as to face an environment outside of the polyhedral containment body.
14 . A satellite module for attitude determination, comprising:
a polyhedral containment body configured to be mounted on a satellite and comprising at least one data acquisition board and a connection interface for allowing the at least one data acquisition board to be in signal communication and electrical communication with the satellite;
at least one first-type sensor selected from a sun sensor, an earth sensor, a stellar sensor, and a horizon sensor, in communication with the data acquisition board;
at least one second-type sensor, different from the at least one first type sensor, selected from a sun sensor, an earth sensor, a stellar sensor, and a horizon sensor, and in communication with the data acquisition board;
at least one third-type sensor, different from the at least one first-type sensor and the at least one second-type sensor, selected from a sun sensor, an earth sensor, and a horizon sensor;
wherein the connection interface is mounted on a first face of the polyhedral containment body, the at least one first-type sensor is mounted on a second face of the polyhedral containment body, the at least one second-type sensor is mounted on a third face of the polyhedral containment body, and the at least one third-type sensor is mounted on a fourth face of the polyhedral containment body; and
wherein the first-type sensor, the second-type sensor, and the third-type sensor are mounted externally on the polyhedral containment body so as to face an environment outside the polyhedral containment body.
15 . A satellite module for attitude determination comprising:
a polyhedral containment body comprising a top face, a front face perpendicular to the top face, a lateral face perpendicular to the front face and the top face, and a plurality of connecting faces extending between the top face and the front face consecutive to each other, each connecting face of said plurality of connecting faces forming an angle between about 10 degrees and about 25 degrees with an adjacent connecting face of said plurality of connecting faces;
a plurality of first-type sensors, each selected from a sun sensor, an earth sensor, a stellar sensor, and a horizon sensor, at least one first-type sensor of said plurality of first-type sensors being mounted directly on each connecting face so as to have redundant readings of a quantity to which the plurality of first-type sensors are sensitive; and
at least one second-type sensor different from the plurality of first type sensors, said at least one second-type sensor being selected from a sun sensor, an earth sensor, a stellar sensor, and a horizon sensor, the at least one second-type sensor being mounted directly on the lateral face.
16 . The satellite module of claim 15 , wherein the polyhedral containment body comprises at least two intermediate faces extending between the lateral face and the front face consecutive to each other, each of the at least two intermediate faces forming an angle between about 20 degrees and about 40 degrees with an adjacent intermediate face of the at least two intermediate faces; and
wherein at least one of the plurality of first-type sensors is mounted directly on each intermediate face of the at least two intermediate faces.
17 . The satellite module of claim 15 , comprising a plurality of third-type sensors, different from the plurality of first-type sensors and the at least one second-type sensor, selected from a sun sensor, an earth sensor, and a horizon sensor, wherein the at least one third-type sensor of said plurality of third-type sensors is mounted directly on each connecting face.
18 . The satellite module of claim 16 , comprising a plurality of third-type sensors, different from the plurality of first-type sensors and the at least one second-type sensor, selected from a sun sensor, an earth sensor, and a horizon sensor, wherein at least one of the plurality of first-type sensors is mounted directly on each connecting face and on each intermediate face.
19 . The satellite module of claim 15 , wherein the polyhedral containment body comprises a rear face, opposite to the front face; and
the satellite module further comprises one or more detachable connection plugs directly mounted on the rear face and configured to connect to a satellite connector to integrate the satellite module into an attitude determination control system of the satellite.
20 . The satellite module of claim 19 , wherein the rear face is parallel to the front face.