Systems and methods for determining a rotational position of an object

• US 20100052981A1
• Filed: 08/29/2008
• Published: 03/04/2010
• Est. Priority Date: 08/29/2008
• Status: Active Grant

• Current Assignee: L3harris Interstate Electronics Corporation (L3Harris Technologies, Inc.)
• Original Assignee: INTERSTATE ELECTRONICS CORPORATION, A SUBSIDIARY OF L-3 COMMUNICATIONS CORPORATION
• Inventors: Alexander, Steven B., Redhead, Richard
• Granted Patent: US 7,986,265 B2
• Time in Patent Office: Days
• US Class Current: 342/357.360
• CPC Class Codes: G01S 19/53 Determining attitude
• CPC Class Codes: G01S 3/22 derived from different combinations of signals from separate antennas, e.g. comparing sum with difference

Abstract

Apparatus and methods determine the rotational position of a spinning object. A satellite positioning system can be used to determine the spatial position of an object, which in turn can be used to guide the object. However, when the object is spinning, such as an artillery shell, then the rotational orientation should be known in order to properly actuate the control surfaces, such as fins, which will also be spinning.

Claims

1. A method of estimating a rotational position of an object, the method comprising:

prior to flight of the object during which the object spins, preloading the object from external to the object with a preloaded intended trajectory, a preloaded space vehicle ephemeris data, and a preloaded system time of a satellite positioning system;

initializing a timer based on the preloaded system time;

during flight, maintaining a timer-based time via the timer without input from satellite positioning system signals;

calculating line-of-sight (LOS) vectors based on the preloaded intended trajectory, the preloaded space vehicle ephemeris data, and the timer-based time;

acquiring satellite positioning signals from a plurality of space vehicles and generating at least one of a correlated in-phase measurement or a correlated quadrature-phase measurement from each of the acquired plurality of satellite positioning signals; and

determining a roll phase relative to each of the space vehicles corresponding to at least a selected group of the acquired plurality of satellite positioning signals by phase locking to an amplitude modulation of at least one of the correlated in-phase output signal or the correlated quadrature-phase output signal for each of the selected group of the acquired plurality of satellite positioning signals, wherein the amplitude modulation is caused by rolling of the object.

2. The method of claim 1, further comprising:

extrapolating a plurality of next up times based at least partly on the determined roll phases for each of the space vehicles corresponding to the selected group, wherein the next up times each represent a future time in which the object is expected to spin about its longitudinal axis such that an antenna of the object is pointed to the corresponding space vehicle; and

averaging the plurality of next up times to generate an averaged up time for the object, wherein the averaged up time indicates an expected time for a rotational position pointing away from Earth.

3. The method of claim 1, further comprising:

determining aspect angles between the object and the selected group of space vehicles;

selecting a second group of space vehicles from the selected group of space vehicles, wherein the second group comprises a smaller subset of the selected group, wherein the second group is selected based at least partly on an aspect angle to the space vehicles;

extrapolating a plurality of next up times based at least partly on the determined roll phases for each of the space vehicles corresponding to the second group, wherein the next up times each represent a future time in which the object is expected to spin about its longitudinal axis such that an antenna of the object is pointed to the corresponding space vehicle; and

averaging the plurality of next up times to generate an averaged up time for the object, wherein the averaged up time indicates an expected time for a rotational position pointing away from Earth.

4. The method of claim 1, wherein determining the roll phase further comprises compensating for asymmetry in an antenna pattern when determining the roll phase.

5. The method of claim 1, further comprising:

calculating first velocities for the object based on the preloaded intended trajectory and the timer-based time; and

calculating line-of-sight (LOS) vectors based on the preloaded intended trajectory, the preloaded space vehicle ephemeris data, and the timer-based time.

6. The method of claim 1, further comprising:

calculating second positions, second velocities, and second times based on received satellite positioning signals, wherein none of the second positions, second velocities, and second times is used for determining rotational position; and

providing the second positions, second velocities, and second times to a guidance computer.

7. The method of claim 1, wherein the object is an artillery shell and the satellite positioning system signals are Global Positioning System (GPS) signals.

8. An apparatus for estimating a rotational position of an object, the apparatus comprising:

an interface configured to retrieve data from external to the object to preload a memory with a preloaded intended trajectory, a preloaded space vehicle ephemeris data, and a preloaded system time of a satellite positioning system prior to flight of the object, wherein the object spins during flight;

a timer configured to be initialized based on the preloaded system time, wherein the timer is configured to maintain time during flight without input from satellite positioning system signals;

an LOS estimator configured to calculate line-of-sight (LOS) vectors based on the preloaded intended trajectory, the preloaded space vehicle ephemeris data, and the timer-based time;

a positioning processor configured to acquire satellite positioning signals from a plurality of space vehicles and to generate at least one of a correlated in-phase measurement or a correlated quadrature-phase measurement from each of the acquired plurality of satellite positioning signals; and

a SV power modulation tracker configured to determine a roll phase relative to each of the space vehicles corresponding to at least a selected group of the acquired plurality of satellite positioning signals by phase locking to an amplitude modulation of at least one of the correlated in-phase output signal or the correlated quadrature-phase output signal for each of the selected group of the acquired plurality of satellite positioning signals, wherein the amplitude modulation is caused by rolling of the object.

9. The apparatus of claim 8, further comprising:

a current roll estimate generator configured to extrapolate a plurality of next up times based at least partly on the determined roll phases for each of the space vehicles corresponding to the selected group, wherein the next up times each represent a future time in which the object is expected to spin about its longitudinal axis such that an antenna of the object is pointed to the corresponding space vehicle; and

a next up time estimator configured to average the plurality of next up times to generate an averaged up time for the object, wherein the averaged up time indicates an expected time for a rotational position pointing away from Earth.

10. The apparatus of claim 8, wherein the LOS estimator is further configured to determine aspect angles between the object and the selected group of space vehicles, the apparatus further comprising:

a measurement enabler configured to select a second group of space vehicles from the selected group of space vehicles, wherein the second group comprises a smaller subset of the selected group, wherein the second group is selected based at least partly on an aspect angle to the space vehicles;

a current roll estimate generator configured to extrapolate a plurality of next up times based at least partly on the determined roll phases for each of the space vehicles corresponding to the second group, wherein the next up times each represent a future time in which the object is expected to spin about its longitudinal axis such that an antenna of the object is pointed to the corresponding space vehicle; and

a next up time estimator configured to average the plurality of next up times to generate an averaged up time for the object, wherein the averaged up time indicates an expected time for a rotational position pointing away from Earth.

11. The apparatus of claim 8, wherein further comprising a roll compensator and a projectile antenna up estimator, wherein the roll compensator is configured to compensate for asymmetry in an antenna pattern, and wherein the projectile antenna up estimator is configured to combine the roll phase and an azimuth angle to a corresponding space vehicle.

12. The apparatus of claim 8, wherein the LOS estimator is further configured to calculate first velocities for the object based on the preloaded intended trajectory and the timer-based time, and to calculate line-of-sight (LOS) vectors based on the preloaded intended trajectory, the preloaded space vehicle ephemeris data, and the timer-based time.

13. The apparatus of claim 8, wherein the positioning processor is configured to calculate second positions, second velocities, and second times based on received satellite positioning signals, wherein none of the second positions, second velocities, and second times is used for determining rotational position, and wherein the positioning processor is configured to provide the second positions, second velocities, and second times to a guidance computer.

14. The apparatus of claim 8, wherein the object is an artillery shell and the satellite positioning system signals are Global Positioning System (GPS) signals.

15. An apparatus for estimating a rotational position of an object, the apparatus comprising:

means for preloading the object from external to the object with a preloaded intended trajectory, a preloaded space vehicle ephemeris data, and a preloaded system time of a satellite positioning system prior to flight of the object, wherein the object spins during flight;

means for initializing a timer based on the preloaded system time;

means for maintaining a timer-based time during flight via the timer without input from satellite positioning system signals;

means for calculating line-of-sight (LOS) vectors based on the preloaded intended trajectory, the preloaded space vehicle ephemeris data, and the timer-based time;

means for acquiring satellite positioning signals from a plurality of space vehicles and generating at least one of a correlated in-phase measurement or a correlated quadrature-phase measurement from each of the acquired plurality of satellite positioning signals; and

means for determining a roll phase relative to each of the space vehicles corresponding to at least a selected group of the acquired plurality of satellite positioning signals by phase locking to an amplitude modulation of at least one of the correlated in-phase output signal or the correlated quadrature-phase output signal for each of the selected group of the acquired plurality of satellite positioning signals, wherein the amplitude modulation is caused by rolling of the object.

16. The apparatus of claim 15, further comprising:

means for extrapolating a plurality of next up times based at least partly on the determined roll phases for each of the space vehicles corresponding to the selected group, wherein the next up times each represent a future time in which the object is expected to spin about its longitudinal axis such that an antenna of the object is pointed to the corresponding space vehicle; and

means for averaging the plurality of next up times to generate an averaged up time for the object, wherein the averaged up time indicates an expected time for a rotational position pointing away from Earth.

17. The apparatus of claim 15, further comprising:

means for determining aspect angles between the object and the selected group of space vehicles;

means for selecting a second group of space vehicles from the selected group of space vehicles, wherein the second group comprises a smaller subset of the selected group, wherein the second group is selected based at least partly on an aspect angle to the space vehicles;

means for extrapolating a plurality of next up times based at least partly on the determined roll phases for each of the space vehicles corresponding to the second group, wherein the next up times each represent a future time in which the object is expected to spin about its longitudinal axis such that an antenna of the object is pointed to the corresponding space vehicle; and

means for averaging the plurality of next up times to generate an averaged up time for the object, wherein the averaged up time indicates an expected time for a rotational position pointing away from Earth.

18. The apparatus of claim 15, wherein the roll phase determining means further comprises means for compensating for asymmetry in an antenna pattern when determining the roll phase.

19. The apparatus of claim 15, further comprising:

means for calculating first velocities for the object based on the preloaded intended trajectory and the timer-based time; and

means for calculating line-of-sight (LOS) vectors based on the preloaded intended trajectory, the preloaded space vehicle ephemeris data, and the timer-based time.

20. The apparatus of claim 15, further comprising:

means for calculating second positions, second velocities, and second times based on received satellite positioning signals, wherein none of the second positions, second velocities, and second times is used for determining rotational position; and

means for providing the second positions, second velocities, and second times to a guidance computer.

21. The apparatus of claim 15, wherein the object is an artillery shell and the satellite positioning system signals are Global Positioning System (GPS) signals.