Attitude determining system for use with global positioning system

• US 5,534,875 A
• Filed: 06/18/1993
• Issued: 07/09/1996
• Est. Priority Date: 06/18/1993
• Status: Expired due to Fees

• Current Assignee: Adroit Systems, Inc. (General Dynamics Corporation)
• Original Assignee: Adroit Systems, Inc. (General Dynamics Corporation)
• Inventors: Rodgers, Charles E., Diefes, Debra L., Fan, Leopold C.
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US08/077,734
• Time in Patent Office: 1,117 Days
• Field of Search: 342/357, 342/359, 342/352, 342/419, 455/12.1
• US Class Current: 342/357.59
• CPC Class Codes: G01S 19/54 using carrier phase measurements; using long or short baseline interferometry
• CPC Class Codes: G01S 3/48 the waves arriving at the antennas being continuous or intermittent and the phase difference of signals derived therefrom being measured

Abstract

An attitude determining system based upon the global positioning system is disclosed, and is adapted to provide dynamic, real time three-dimensional attitude, position, and time information on any vehicle in which it is located. The system is adapted to work at high latitudes, and be immune to magnetic deviations. The attitude determining system makes use of certain hardware configurations and mathematical algorithms to overcome the limitations of the prior art, and eliminate errors related to the motion of the vehicle platform.

Claims

1. A system employing telemetry and other electronic signals provided by a series of orbiting satellites to provide a real-time solution of direction of travel;

and attitude, which is comprised of heading, pitch, and roll, of a platform on which said system is located, said system comprising;

antenna array means comprising at least two discrete antennae, each antenna forming at least one baseline with another of said antenna, said antenna array adapted to collect said telemetry and electronic signals transmitted by the series of orbiting satellites, wherein said discrete antennae are spaced such that the length of at least one of said baselines is less than the carrier wavelength being received from said orbiting satellites;

receiver means electrically communicating with each said discrete antenna, and adapted to interpret telemetry and electronic signals collected by said antenna array means;

mathematical algorithmic comparing means adapted to comparing information received from each said receiver means, to calculate heading, pitch, and roll and to reduce errors inherent in said received telemetry and electronic signals, wherein said algorithmic comparing means further includes a coarse attitude determining means for determining a first, general attitude, with accuracy between about +/-30°

, and a fine attitude determining means for improving the accuracy of said first determination to within about +/-0.5°

, which occurs within the same solution time-frame, said algorithmic comparing means further including a satellite selecting regime for selecting one or more preferred satellites from among said series of orbiting satellites, and wherein said attitude is determined by carrier phase interferometry; and

microprocessor means for processing said information with said algorithm to accurately determine the attitude, heading, pitch, and roll of the platform.

2. A system as defined in claim 1 further comprising an inclinometer means wherein said mathematical algorithm comparing means compares information received from said receiver means and said inclinometer means to reduce error.

3. A system as defined in claim 1, and further comprising:

input/output means for receiving input by a user and electronically transmitting said input to said microprocessor means to enable a user to interact and define parameters of said system.

4. A system as defined in claim 3, wherein said input/output means comprise a touch-sensitive liquid crystal display.

5. A system as defined in claim 1, and wherein said antenna array means further comprises:

three antennae arranged in a triangular configuration, each of said antennas forming a baseline with another of said antennae.

6. A system as defined in claim 5, wherein said three antennae are arranged on a ground plane in an equilateral triangle.

7. A system as defined in claim 6, wherein the length of each arm of the equilateral triangle is less than the wavelength of the telemetry and electronic signals provided from said orbiting satellites.

8. A system as defined in claim 5, wherein said antennae ground plane is substantially circular in shape and has a rounded flanged edge;

and

said antennae being arranged in said circular ground plane such that said antennae are substantially equal distance from said edges of said ground plane.

9. A system as defined in claim 1, wherein said antenna array further comprises three discrete antenna arranged in two co-linear baselines.

10. A system as defined in claim 1, wherein said attitude is determined by double differenced, carrier phase interferometry.

11. A system for calculating the location, attitude, and direction of a platform, said system comprising:

means adapted to collect and receive telemetry and other electronic signals transmitted at a preselected wavelength from a plurality of earth orbiting satellites, said collecting and receiving means comprising at least three antenna, each antenna electrically communicating with a receiver;

satellite selection means embedded in a microprocessor and adapted to select at least four satellites from among the plurality of orbiting satellites from which to receive telemetry;

error correcting means embedded in said microprocessor to reduce errors inherent in said received telemetry and electronic signals attributable to said antennae and the location of said satellites; and

an algorithm employing double differenced carrier phase interferometry to determine location, attitude and direction of travel based upon the telemetry and electronic signals received from said selected satellites, wherein said algorithm further includes a coarse attitude determining means for determining a first, general attitude, with accuracy between about +/-30°

, and a fine attitude determining means for improving the accuracy of said first determination to within about +/-0.5°

.

12. A system as in claim 11, wherein said three antenna are arranged in an equilateral triangle, the distance between each such antenna being less than the wavelength of the transmitted telemetry.

13. A system as in claim 11, wherein said antenna are arranged in two co-linear baselines.

14. A system as in claim 11, further including at least one inclinometer operatively associated with such system for establishing the orientation of such system, said orientation information being combined with said telemetry and said other electronic signals to more accurately determine attitude.

15. A system as in claim 11, further including input/output means for receiving input from a system user, and electronically transmitting said input to said microprocessor means to enable said user to interact with, and to define parameters within said system.

16. A system as in claim 15, wherein said input/output means comprise a touch sensitive liquid crystal display.

17. A system as in claim 11, wherein said error correction means further comprises means adapted to correct for antenna differential phase error due to antenna phase center migration;

electrical path length difference attributable to differences in spacing between said antenna; and

multi-path induced phase error resulting from reception of said telemetry and electronic signals reflected off of objects other than said antenna.

18. A system as in claim 11, wherein said satellite selection means selects said satellites by comparing the relative strength of signals received from each one of said plurality of satellites.

19. A system as in claim 12, wherein said antennae are arranged in a ground plane which is substantially circular in shape and has a rounded flanged edge, said antennae being arranged in said circular ground plane such that said antennae are substantially equal distance from said edges of said ground plane.

20. A method of determining location, attitude, and direction of travel information from signals transmitted from one or more earth orbiting satellites, said method comprising the steps of:

providing means adapted to collect and receive telemetry and other electronic signals transmitted at a preselected wavelength from said plurality of earth orbiting satellites, said collecting and receiving means comprising at least three antenna, each antenna electrically communicating with a receiver;

providing an algorithm imbedded in a microprocessor, said algorithm employing carrier phase interferometry to interpret said received telemetry and electronic signals, said algorithm comprising;

satellite selection means embedded in said microprocessor and adapted to select at least four satellites from among the plurality of orbiting satellites from which to receive telemetry; and

error correcting means embedded in said microprocessor to reduce errors inherent in said received telemetry and electronic signals;

relaying information received by said antenna and receiver to said microprocessor for calculation of attitude, location, and direction of travel information by said algorithm;

establishing a first coarse measurement of attitude, with accuracy between about +/-30°

, and subsequently establishing a second, fine measurement of attitude improving the accuracy of said first determination to within about +/-0.5°

; and

displaying attitude, location, and direction of travel information on an output device.

21. A method as in claim 20, including the further step of calculating said attitude by employing double differenced carrier phase interferometry.

22. A method as in claim 20, including the further step of providing said three antenna arranged in an equilateral triangle, the distance between each such antenna being less than the wavelength of the transmitted telemetry.

23. A method as in claim 20, wherein the output means comprise a touch sensitive liquid crystal display.

24. A method as in claim 20, including the further step of arranging said antenna in two co-linear baselines.