A method for determining the position of a spacecraft in space, includes cyclically÷ repeating steps of capturing distorted star images; processing the distorted star images to form distorted star group data; storing the distorted star group data; determining a current rotation rate by comparing the distorted star group data of two consecutive cycles; transmitting the current rotation rate to a position control system; and/or the following steps are carried out: processing the distorted star images of a current cycle to form rectified star group data; determining position information by matching the rectified star group data with star group catalog data which is carried along; transmitting the position information to the position control system. A method for determining the position of a spacecraft in space, taking into account known system parameters of an optical system, includes: coding star group catalog data with n = 3...4 stars [x.sub.n, y.sub.n, z.sub.n], which are visible in an image field, into representative focal-plane coordinates; forming a scaling-, translation-, and rotation-invariant star group code on the basis of [xPiX,yPiX]n; or coding star group catalog data with n = 3...4 stars [x.sub.n,y.sub.n, z.sub.n], which are visible in an image field, into representative tangent and/or angular coordinates [tan(a),tan(β)].sub.n. The invention further relates to a device for carrying out such methods and to a computer program product for carrying out such methods.

A unit (10) for causing angular momentum (11) about an axis (13a), which unit includes, inflow sequence, an incoming fluid pathway (12), a first fluid pathway (14a) in fluid communication with the incoming fluid pathway (12), a second fluid pathway (16a) in fluid communication with the incoming fluid pathway (12), an outgoing fluid pathway (18) in fluid communication with the first and second fluid pathway (14a, 16a), a flow regulating means (20a) for regulating the proportional flow in the first and second fluid pathways (14a, 16a), and wherein the first and second fluid pathways (14a, 16a) are respectively arranged about the axis (13a) generally in a plane transverse to the axis (13a).

A unit (10) for causing angular momentum (11) about an axis (13a), which unit includes, inflow sequence, an incoming fluid pathway (12), a first fluid pathway (14a) in fluid communication with the incoming fluid pathway (12), a second fluid pathway (16a) in fluid communication with the incoming fluid pathway (12), an outgoing fluid pathway (18) in fluid communication with the first and second fluid pathway (14a, 16a), a flow regulating means (20a) for regulating the proportional flow in the first and second fluid pathways (14a, 16a), and wherein the first and second fluid pathways (14a, 16a) are respectively arranged about the axis (13a) generally in a plane transverse to the axis (13a).

Systems, methods and apparatus related to a self-preservation/self-protection system (SPS). The SPS system includes a local area situation awareness sensor suite (LASASS), multiple central pattern generator (mCPG) decision circuitries and related actuators. The SPS system utilizes the LASASS, mCPG circuitries and actuators to perform the desired processing and effectuate changes in the position of an object to be detected or avoided.

Systems, methods and apparatus related to a self-preservation/self-protection system (SPS). The SPS system includes a local area situation awareness sensor suite (LASASS), multiple central pattern generator (mCPG) decision circuitries and related actuators. The SPS system utilizes the LASASS, mCPG circuitries and actuators to perform the desired processing and effectuate changes in the position of an object to be detected or avoided.

A method of roll steering of a spacecraft to align an aspect of the spacecraft, such as the surface of solar arrays carried by the spacecraft, to the sun, is described. The roll steering occurs only when the sun is at an angle (β) relative to the orbital plane of the spacecraft and when the spacecraft is not eclipsed by a body it is orbiting. This dayside-only roll steering of the spacecraft increases the power efficiency of the spacecraft. A spacecraft may include a controller which causes an attitude control subsystem to steer the spacecraft about a roll axis to position the surface of the solar array such that an axis normal to the surface of the solar array is aligned with the direction to a sun when the sun is visible to the spacecraft, and maintain a fixed orientation of the spacecraft about the roll axis when the sun is not visible to the spacecraft.

A method of roll steering of a spacecraft to align an aspect of the spacecraft, such as the surface of solar arrays carried by the spacecraft, to the sun, is described. The roll steering occurs only when the sun is at an angle (β) relative to the orbital plane of the spacecraft and when the spacecraft is not eclipsed by a body it is orbiting. This dayside-only roll steering of the spacecraft increases the power efficiency of the spacecraft. A spacecraft may include a controller which causes an attitude control subsystem to steer the spacecraft about a roll axis to position the surface of the solar array such that an axis normal to the surface of the solar array is aligned with the direction to a sun when the sun is visible to the spacecraft, and maintain a fixed orientation of the spacecraft about the roll axis when the sun is not visible to the spacecraft.

Aspects presented herein may enable a positioning device or entity to perform PR measurement error detection and classification based on SV geometry via ML. In one aspect, a UE or a location server determines for each SV of a set of SVs at least a geometric orientation with respect to the UE. The UE or the location server determines, based on an ML classifier and the determined geometric orientation with respect to the UE for each SV of at least a subset of the set of SVs, a relative PR weight for each SV of the set of SVs. The UE or the location server estimates a position of the UE based on PR measurements of each SV of the set of SVs and the relative PR weight for each SV of the set of SVs.

Aspects presented herein may enable a positioning device or entity to perform PR measurement error detection and classification based on SV geometry via ML. In one aspect, a UE or a location server determines for each SV of a set of SVs at least a geometric orientation with respect to the UE. The UE or the location server determines, based on an ML classifier and the determined geometric orientation with respect to the UE for each SV of at least a subset of the set of SVs, a relative PR weight for each SV of the set of SVs. The UE or the location server estimates a position of the UE based on PR measurements of each SV of the set of SVs and the relative PR weight for each SV of the set of SVs.

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.