Method, system and apparatus for spacecraft attitude control error reduction in trajectory interpolation

Patent metadata

Field	Value
Publication number	US-12371194-B2
Application number	US-202318537554-A
Country	US
Kind code	B2
Filing date	Dec 12, 2023
Priority date	Dec 12, 2022
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

A method, apparatus and system for controlling an attitude of a spacecraft, the spacecraft including an attitude control system operatively associated with a ground-based spacecraft control system. According to an exemplary embodiment, the spacecraft attitude control system uses a B-spline interpolator for commanding the spacecraft and a Kalman filtering process is used to estimate B-spline interpolator coefficients. The methods and systems disclosed herein can be implemented in, for example, executable machine code and/or integrated circuit hardware.

First claim

What is claimed is:

1. A method for controlling an attitude of a spacecraft, the method comprising:
obtaining, by a ground-based spacecraft control system, an attitude trajectory of the spacecraft, wherein the ground-based spacecraft control system is operatively associated with a spacecraft attitude control system;
down sampling, by the ground-based spacecraft control system, the attitude trajectory and using a Kalman filtering process to determine a state space implementation of spline coefficients for time-tagged spacecraft commands;
transmitting, by the ground-based spacecraft control system, the time-tagged spacecraft commands to the spacecraft after processing the down sampled attitude trajectory;
applying, by the spacecraft attitude control system, a B-spline interpolation filter to a sequence of down-sampled attitude trajectory points to determine a set of interpolated spacecraft commands at an arbitrary upsampling rate;
reconstructing, by the spacecraft attitude control system, a time varying attitude command trajectory by applying a rectangular pulse zero order hold (ZOH) function; and
modifying, by the spacecraft attitude control system, an attitude of the spacecraft based on the interpolated spacecraft commands.

2. The method of claim 1 , wherein each of the time-tagged spacecraft commands is loaded from an absolute time sequence command buffer or relative time sequence command buffer.

3. The method of claim 1 , wherein the time-tagged spacecraft commands are produced at an update rate of the spacecraft attitude control system.

4. The method of claim 1 , wherein the B-spline interpolation filter has an interpolation error controlled by an order of the B-spline interpolation filter.

5. The method of claim 1 , wherein the B-spline interpolation filter has an interpolation error controlled by an expansion factor M.

6. The method of claim 1 , wherein the B-spline interpolation filter is implemented with B-spline polynomial.

7. The method of claim 1 , wherein the B-spline interpolation filter is implemented using a direct form filter structure or a series connection of direct form filter structures.

8. A vehicle guidance system for implementing attitude control of a vehicle, comprising:
a command reduction module for generating a reduced data set corresponding to a time-varying attitude command trajectory for a vehicle;
wherein the command reduction module circuitry is configured to receive at least one time-varying attitude command; wherein the time-varying attitude command trajectory defines an attitude of the vehicle; and reduces the at least one time-varying attitude command trajectory into a vector of B-spline polynomial coefficients using a Kalman filtering process and smoothing process; and
a command reconstruction module for generating data corresponding to the time varying attitude command trajectory;
wherein the command reconstruction module is configured to receive the vector of B-spline polynomial coefficients; and reconstruct at least one time-varying attitude command trajectory by utilizing the vector of B-spline polynomial coefficients to perform a B-spline interpolation operation, and apply a zero order hold (ZOH) function.

9. The vehicle guidance system according to claim 8 , further comprising:
a first communication interface located remote from the vehicle and a second communication interface located on the vehicle, the first communication interface configured to transmit the vector of B-spline polynomial coefficients to the second communication interface.

10. The vehicle guidance system according to claim 8 , further comprising:
an attitude control system including an input for receiving a command trajectory; and

a switching device including an input operatively coupled to the command reconstruction module, and an output operatively coupled to the attitude control system input, the switching device configured to selectively provide the reconstructed time-varying attitude command trajectory to the attitude control system input.

11. The vehicle guidance system according to claim 8 , wherein the circuitry configured to reduce the at least one time-varying attitude command trajectory into the vector B-spline polynomial coefficients is configured to perform the reduction based on a user input.

12. The vehicle guidance system according to claim 8 , wherein the user input comprises at least one of an initial maneuver time or an end maneuver time for the vehicle, time histories of vehicle attitude commands, a predetermined number N of B-spline polynomial coefficients to compute, N being an integer, a tolerance for an acceptable B-spline polynomial approximation error, a set of mathematical basis functions b(t), or a set of distinct time points or nodes.

13. The vehicle guidance system according to claim 8 , wherein the circuitry configured to reduce the at least one time-varying attitude command trajectory is configured to expand N+1 mathematical basis functions b(t) over a selected time grid, compute the values of a set of B-spline polynomial coefficients c for N+1 basis functions using the Kalman filtering process, and evaluate the infinity norm, wherein N is a non-negative integer.

14. The vehicle guidance system according to claim 13 , wherein the circuitry configured to reduce the at least one time-varying attitude command trajectory is configured to
compare the evaluated infinity norm to a predetermined tolerance;
if the evaluated infinity norm is greater than the predetermined tolerance, increment N and repeat the expansion and evaluation steps; and
if the evaluated infinity norm is less than the predetermined tolerance, conclude that the reduction process is complete.

15. The vehicle guidance system according to claim 8 , wherein the circuitry configured to reconstruct the at least one time-varying attitude command trajectory is configured to perform the reconstruction based on at least one of an initial maneuver time for the vehicle, an end maneuver time for the vehicle, an attitude control system sample time, a clock time of the vehicle control system, a set of mathematical basis functions, or a set of distinct time points or nodes.

16. The vehicle guidance system according to claim 15 , wherein the circuitry configured to reconstruct the at least one time-varying attitude command trajectory is configured to use B-spline polynomials as the basis functions b j (t).

17. A method for implementing attitude control of a vehicle, comprising:
receiving, at a remote location from the vehicle data corresponding to at least one time-varying attitude command trajectory defining an attitude of the vehicle;
processing, at the remote location, the at least one time-varying attitude command trajectory using a Kalman filter to determine a state space implementation of spline coefficients and generate a down sampled attitude command trajectory including a vector of B-spline polynomial coefficients;
communicating, at the remote location, the down sampled attitude command trajectory to the vehicle; and
modifying, by the vehicle, an attitude of the vehicle based on the down sampled attitude command trajectory and an interpolation filter operatively associated with the vehicle, wherein the interpolation filter is a B-spline interpolation filter applied to a zero order hold (ZOH) function.

18. The method according to claim 17 , further comprising:
receiving, at the vehicle, the vector of B-spline polynomial coefficients; and
using circuitry of a command reconstruction module to reconstruct the at least one time-varying attit

Assignees

• Us Navy
• Us Gov Sec Navy

Inventors

• Cristi Roberto
• Levitas Joshua
• Karpenko Mark

Classifications

• B64G1/2422 Primary

  using Lagrange points, e.g. halo orbits · CPC title

• B64G1/36

  using sensors, e.g. sun-sensors, horizon sensors · CPC title

• B64G1/244

  Spacecraft control systems · CPC title

• B64G1/245 Primary

  Attitude control algorithms for spacecraft attitude control · CPC title