GPS navigational system and associated process for space applications

• US 6,424,913 B1
• Filed: 02/22/2000
• Issued: 07/23/2002
• Est. Priority Date: 02/19/1999
• Status: Expired due to Term

• Current Assignee: Astrium GmbH (Airbus SE)
• Original Assignee: Astrium GmbH (Airbus SE)
• Inventors: Fichter, Walter, Mittnacht, Michael, Krauss, Peter-Alexander, Gottzein, Eveline
• Primary Examiner(s): LOUIS JACQUES, JACQUES H
• Application Number:
  US09/510,917
• Time in Patent Office: 882 Days
• Field of Search: 701/213, 701/3, 701/13, 701/214, 701/215, 701/226, 701/4, 342/357.12, 342/357.11, 342/357.05, 342/357.01, 342/357.06, 342/357.09, 342/357.1, 342/357.04, 342/352, 342/355, 342/359, 455/12.1, 455/456, 455/552, 455/553, 375/326, 375/343, 375/344
• US Class Current: 701/213
• CPC Class Codes: G01S 19/14 specially adapted for specific applications
• CPC Class Codes: G01S 19/37 Hardware or software details of the signal processing chain

Abstract

The invention provides GPS navigational system for a satellite in space which comprises a front end section having an input for receiving GPS signals from a plurality of satellites, a digital preprocessor connected to the front end section for digitally preprocessing the GPS signals received from the front end section, and a signal processor connected to the digital preprocessor for decoding the GPS signals to determine a position of the satellite. An on-board computer is provided and a first data bus line connects the data processor and the signal processor for bi-directional data exchange therebetween and a second data bus line connects the signal processor and the on-board computer for bi-directional data exchange therebetween.

Claims

1. A GPS navigational system for a satellite having an on-board computer for controlling operation of the satellite, the system comprising a front end section having an input for receiving GPS signals from a plurality of GPS satellites, a digital preprocessor device connected to said front end section for digital reprocessing of the GPS signals received from the front end section, a signal processor connected to said digital preprocessor device for decoding the GPS signals to determine a position of the satellite, a first data bus line connecting said digital preprocessing device and said signal processor for bi-directional data exchange therebetween, and a second data bus line connecting said signal processor and said on-board computer for bi-directional data exchange therebetween such that at least a portion of the operation of determining the position of the satellite by the GPS navigational system is carried out by the on-board computer and data in a data bank in said on-board computer related to satellite propulsion is directed from the on-board computer to said signal processor.

2. The system as claimed in claim 1, wherein said data bank contains specific data related to satellite propulsion, said signal processor being connected to said on-board computer by said second data bus line to communicate with said data bank to receive the data related to the propulsion of the satellite.

3. The system as claimed in claim 1, comprising a clock having an input connected to said front end section and an output connected to said front end section and said digital preprocessor.

4. The system as claimed in claim 1, wherein said on-board computer includes an oscillator for producing a reference oscillator signal which is fed to said front end section.

5. The system as claimed in claim 1, wherein said on-board computer comprises means for determining a navigational position of the satellite by a sequential estimation method.

6. The system as claimed in claim 1, wherein said signal processor comprises means for determining a navigational position of the satellite by a sequential estimation method.

7. The system as claimed in claim 1, wherein the input of the front end section has a plurality of processing channels related to respective GPS satellites, the processing channels being less than four in number.

8. A process for operating a navigational system of a satellite in space based on signals from satellites of a GPS system, said process comprising:

receiving data signals from satellites of a GPS system and transmitting the signals to a front end section of a navigational system on a satellite in space,

digitally preprocessing the signals received by the front end section in a digital preprocessor,

decoding in a signal processor the signals which have been preprocessed in the digital preprocessor,

connecting the digital preprocessor and the signal processor for bi-directional data exchange therebetween,

connecting the signal processor and an on-board computer on the satellite, which controls operation thereof, for bi-directional data exchange therebetween,

transmitting specific data related to propulsion means for driving the satellite from a data bank in said on-board computer to said signal processor, and

determining a position of the satellite in space by said navigation system in combination with said on-board computer and based on data exchange therebetween.

9. A process as claimed in claim 8, wherein said propulsion means comprises jet thrusters, said process further comprising incorporating in said data bank, data relating to thrust direction of the jet thrusters, magnitude of thrust and intervals of operation and shutdown of said jet thrusters.

10. A process as claimed in claim 8, further comprising transmitting data from the on-board computer to the signal processor, related to mass of the satellite.

11. A process as claimed in claim 8, further comprising transmitting data from the on-board computer to the signal processor, related to solar pressure.

12. A process as claimed in claim 8, further comprising producing a reference oscillator signal by the on-board computer and supplying said reference signal to said front end section.

13. A process as claimed in claim 8, further comprising determining navigation position, velocity and GPS time of the space vehicle by a sequential estimation method based on data in the on board computer.

14. A process as claimed in claim 13, wherein the sequential estimation method is expressed by the relation μ

={square root over (M₁₁+L +M₂₂+L ·

M₃₃+L )} where M is the co. variant matrix of estimation error of parameters of the space object.

15. A process as claimed in claim 13, further comprising carrying out the sequential estimation method in the signal processor.

16. A processor as claimed in claim 13, further comprising carrying out the sequential estimation method in the on-board computer.