Multiple satellite locating system

• US 4,975,707 A
• Filed: 07/13/1989
• Issued: 12/04/1990
• Est. Priority Date: 07/13/1989
• Status: Expired due to Fees

• Current Assignee: Energetics Satellite Corporation
• Original Assignee: Energetics Satellite Corporation
• Inventors: Smith, Jordan R.
• Primary Examiner(s): Tarcza, Thomas H.
• Assistant Examiner(s): Hellner, Mark
• Application Number:
  US07/380,177
• Time in Patent Office: 509 Days
• Field of Search: 342/354, 342/357
• US Class Current: 342/357.48
• CPC Class Codes: G01S 5/04 Position of source determined by a plurality of spaced direction-finders

Abstract

A locating system employs a multiple satellite configuration employing rotating scanning patterns for generating peak signal data which can be used to calculate the position of a signal source within a scanned region. One preferred embodiment utilizes two spaced satellites in high earth geosynchronous orbit and simultaneous narrow antenna beam rotation patterns to scan a substantial portion of the earth'"'"'s surface. The invention is particularly advantageous for locating stolen vehicles and for tracking inventory. The system may also be used for determining altitude of a signal source that may, for example, be located on an aircraft in flight.

An alternative embodiment employs a peak-detecting ground-based receiver and satellite or other scanning devices which generate and transmit a signal to the receiver indicating the precise current position of the antenna of each satellite. The ground-based receiver is equipped with a computer for calculating its own position by repeatedly correlating the time of peak signal detection and the data from the received satellite signals. Such an alternative embodiment would enable precise self-position determination without the use of a command center.

Claims

1. A system for determining the location of a first transmitter on the Earth'"'"'s surface;

the system comprising;

at least two satellites in spaced-apart geosynchronous orbits;

each such satellite having an antenna which produces a rotating beam, said beam being substantially longer in a first cross-sectional plane than in a second orthogonal cross-sectional plane;

each such satellite also having a receiver responsive to the signal of said first transmitter and a second transmitter for re-transmitting a signal representative of said received first transmitter signal;

the rotating antenna beam of said satellites scanning overlapping patterns in a region of the Earth'"'"'s surface in which said first transmitter is positioned;

means for receiving said re-transmitted signals of said second transmitter and calculating the precise location of said first transmitter by determining the intersection point of the peak signal strength of the signal received by each of said satellite receivers.

2. The system recited in claim 1 further comprising means on each said satellite for determining the precise orientation of said antenna beam upon receiving said first transmitter signal.

3. The system recited in claim 1 further comprising at least one reference transmitter positioned at a precisely known location in said Earth surface region for calibrating said system.

4. The system recited in claim 1 further comprising means in said first transmitter for generating a coded signal which identifies said first transmitter.

5. The system recited in claim 1 wherein each said satellite antenna comprises a segment of a parabolic surface.

6. The system recited in claim 1 wherein said satellites are positioned substantially above the Earth'"'"'s equator and wherein the spacing between said satellites is in the range of ten to forty-five degrees measured circumferentially about the Earth'"'"'s surface.

7. The system recited in claim 1 wherein the dimension of each said antenna for producing said second cross-sectional plane of said beam is approximately 165 feet.

8. The system recited in claim 1 wherein the rate of rotation of each of said antenna beams is about 0.5 RPM.

9. The system recited in claim 1 wherein the frequency of said first transmitter signal is approximately 24 GHz.

10. The system recited in claim 1 wherein the frequency of said second transmitter signal is approximately 19 GHz.

11. A system for determining the precise location of a source of energy in a selected region of the Earth'"'"'s surface;

the system comprising;

at least two geosynchronous satellite-based receivers responsive to said source of energy;

means, also based on said satellites, for simultaneously scanning overlapping respective line patterns in said region;

for and means calculating of said precise location by determining the point of intersection of said respective line patterns corresponding to peak energy detection by said respective receivers.

12. The system recited in claim 11 wherein said scanning line patterns are rotated at a pre-determined rate.

13. The system recited in claim 11 further comprising means on each said satellite for determining the precise orientation of each said line pattern upon reception by said receiver of said energy.

14. The system recited in claim 11 further comprising at least one reference transmitter positioned at a precisely known location in said Earth surface region for calibrating said system.

15. The system recited in claim 11 further comprising means in said source of energy for modulating said energy for uniquely identifying said source.

16. The system recited in claim 11 wherein said satellites are positioned substantially above the Earth'"'"'s equator and wherein the spacing between said satellites is in the range of ten to forty-five degrees measured circumferentially about the Earth'"'"'s surface.

17. The system recited in claim 11 wherein said energy is radio frequency electromagnetic energy.

18. The system recited in claim 12 wherein said rate is about 0.5 RPM.