Digital spacecraft antenna tracking system

• US 5,926,130 A
• Filed: 07/10/1998
• Issued: 07/20/1999
• Est. Priority Date: 07/10/1998
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Original Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Inventors: Werntz, Paul C.
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US09/112,851
• Time in Patent Office: 375 Days
• Field of Search: 342/354, 342/359, 342/372
• US Class Current: 342/354
• CPC Class Codes: H01Q 1/288 Satellite antennas
• CPC Class Codes: H01Q 19/17 the primary radiating source comprising two or more radiating elements H01Q19/15, H01Q25/00 take precedence
• CPC Class Codes: H01Q 3/26 varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture H01Q3/12, H01Q3/22, H01Q3/24 take precedence

Abstract

A digital spacecraft antenna tracking system and method are provided which utilize an array of antenna feed elements oriented relative to a shaped spacecraft reflector antenna system each of which generates an output signal corresponding to a received incident signal. The outputs can be processed by a mixer/multiplexer (M/MUX) before processing by a digital tracking control receiver. The direction of a beacon signal incident on the spacecraft reflector antenna system is obtained by the TCR by comparing the beacon response of the M/MUX to a set of premeasured responses to incident signals having a known direction or orientation relative to a reference tracking grid. The premeasured responses are stored in a memory as a set of reference responses. Once the direction of the signal is obtained, the TCR assigns control voltages which are used by the spacecraft to steer the spacecraft antenna to a desired pointing direction relative to the beacon signal.

Claims

1. A digital spacecraft antenna tracking system comprising:

at least one reflector antenna element positioned on the spacecraft to receive an incident signal transmitted from a ground station;

a tracking array comprising a plurality of array antenna elements oriented relative to the at least one reflector antenna element, each of said plurality of array antenna elements generating an output signal corresponding to a received incident signal; and

a tracking control receiver responsive to each of the outputs of the plurality of array antenna elements, said tracking control receiver comprising a memory for storing a set of predetermined responses generated by a plurality of reference incident signals having a known direction relative to a reference grid, and a processor arranged to compare the output signals to the set of predetermined responses and determine the direction of the received incident signal based on the comparison.

2. The system of claim 1 wherein said tracking control receiver is arranged to convert an amplitude and phase of each array antenna element output into respective i and q terms for each received incident signal.

3. The system of claim 2 wherein said set of predetermined responses comprise a set of reference response vectors formed from a converted i and q term for each output of said plurality of antenna elements, and the processor is arranged to produce a dot product between each i and q term for a received incident signal and each reference response vector.

4. The system of claim 3 wherein the direction of the received incident signal is determined to be the direction of the reference grid for which the dot product is a maximum.

5. The system of claim 1 further comprising a multiplexer connected to each of the plurality of array antenna elements for multiplexing the output signals into a single channel for the tracking receiver.

6. The system of claim 1 wherein said tracking control receiver is further arranged to generate a steering control voltage for use by a spacecraft control system in response to the determined direction of the received incident signal.

7. The system of claim 1 wherein the at least one reflector antenna element comprises a parabolic antenna.

8. The system of claim 1 wherein the received incident signal comprises a beacon signal.

9. The system of claim 1 wherein the at least one reflector antenna element comprises a shaped reflector antenna element.

10. A method for tracking the direction of an incident signal transmitted by a ground station and received by a spacecraft antenna tracking system comprising:

positioning at least one reflector antenna element on the spacecraft to receive the incident signal;

orienting a tracking array comprising a plurality of array antenna elements relative to the at least one reflector antenna element so that each of said plurality of array antenna elements generates an output signal corresponding to the received incident signal;

storing in a memory a set of predetermined responses generated by a plurality of reference incident signals having a known direction relative to a reference grid;

comparing the output signals to the set of predetermined responses; and

determining the direction of the received incident signal bas ed on the comparison.

11. The method of claim 10 further comprising converting an amplitude and phase of each array antenna element output into respective i and q terms for the received incident signal.

12. The method of claim 11 wherein said set of p redetermined responses comprise a set of reference response vectors formed from converting an i and q term for the amplitude and phase of each output of said plurality of antenna elements in response to the incident signals having a known direction, and comparing the output signals to the set of predetermined responses comprises producing a dot product between each i and q term for a received incident signal and each reference response vector.

13. The method of claim 12 wherein the direction of the received incident signal is determined to be the direction of the reference grid for which the dot product is a maximum.

14. The method of claim 10 further comprising generating a steering control voltage for use by a spacecraft control system in response to the determined direction of the received incident signal.

15. The method of claim 10 further comprising increasing memory use efficiency by concentrating the known direction relative to the reference grid near of the reference incident signals to an area of particular interest.

16. The method of claim 10 further comprising multiplexing the outputs of each of the plurality of array antenna elements into a single channel before comparing the output signals to the set of predetermined responses.