Method and apparatus for determining the position and orientation of a missile
AssigneeAstrium GmbH
InventorsSven Martin, Dieter Dragon
Life of this patent
Estimating the term…
Abstract
A system for determining the position and orientation of a flying object such as a missile includes a ground segment having at least one pseudolite station located on the earth's surface which transmits into space a navigation signal that uniquely identifies the pseudolite station, and a user segment having at least one sensor which is situated in the missile and is designed to receive the navigation signal from the at least one pseudolite station and to determine its absolute position and orientation in space on the basis of the received navigation signal.
Claims20
A system for determining the position and orientation of a flying object, said system comprising:
- a ground segment having at least one pseudolite station which is located on the earth's surface and transmits a navigation signal into space, which navigation signal uniquely identifies the pseudolite station;
- and
- a user segment having at least one sensor which is situated in the object and is designed to receive the navigation signal from the at least one pseudolite station and to determine its absolute position and orientation in space on the basis of the received navigation signal, wherein
- the ground segment comprises multiple pseudolite stations,
- the ground segment is configured on the earth's surface according to a specified geometry, such that navigation signals from at least five different pseudolite stations are received during all phases of flight of the object, and
- the pseudolite stations are configured in such a way that a maximum number of navigation signals that can be received by the sensor are received from the pseudolite stations during the launch of the object from the earth's surface.
A method for determining the position of a flying object, said method comprising:
- at least one pseudolite station of a ground segment which is located on the earth's surface transmitting a navigation signal into space, which navigation signal uniquely identifies the pseudolite station;
- and
- at least one sensor for a user segment, provided in the object, receiving the navigation signal from the at least one pseudolite station, and determining absolute position of the sensor in space based on the received navigation signal, wherein
- the ground segment comprises multiple pseudolite stations,
- the ground segment is configured on the earth's surface according to a specified geometry, such that navigation signals from at least five different pseudolite stations are received during all phases of flight of the object, and
- the pseudolite stations are configured in such a way that a maximum number of navigation signals that can be received by the sensor are received from the pseudolite stations during the launch of the object from the earth's surface.
Dependencies are inferred from the claim text.