Rapid slew and settle systems for small satellites

Patent metadata

Field	Value
Publication number	US-9745082-B2
Application number	US-201615140065-A
Country	US
Kind code	B2
Filing date	Apr 27, 2016
Priority date	Jun 2, 2015
Publication date	Aug 29, 2017
Grant date	Aug 29, 2017

Abstract

A new approach for rapid slew and settle of small satellites is based on four single degree-of-freedom control moment gyroscopes with variable speed flywheels (or reaction wheels) in a pyramid configuration, combined with path and endpoint constraint time-optimal control. The path and endpoint constrained time-optimal control can be augmented with momentum management without the use of additional actuators.

First claim

What is claimed is:

1. A satellite attitude control system for a satellite, the satellite attitude control system comprising:
four hybrid control moment gyroscopes arranged in a pyramid configuration, each hybrid control moment gyroscope including a control moment gyroscope actuator and a reaction wheel actuator; and
a retargeting controller for retargeting the satellite from an initial state through a desired slew and settle maneuver to a desired final state using path and endpoint constrained time-optimal control, the retargeting controller configured to determine a set of gimbal angular rate vectors based on the initial state, the desired final state, and a predetermined set of path and endpoint constraints selected to avoid control moment gyroscope actuator singularities and reaction wheel actuator singularities and to ensure that the hybrid control moment gyroscopes will complete the slew maneuver in a configuration capable of performing the settle maneuver using the reaction wheel actuators and to produce retargeting commands for the hybrid control moment gyroscopes based on the set of gimbal angular rate vectors.

2. A satellite attitude control system according to claim 1 , wherein the gimbal angles of each hybrid control moment gyroscope k are constrained by an endpoint constraint:
C LE ≦|sin(δ k ( t f ))|≧ C UE

where δ k is the k-th gimbal angle t f is the total slew and settle time, C LE is a lower bound and C UE is an upper bound.

3. A satellite attitude control system according to claim 2 , wherein the gimbal angles at the end of the slew maneuver are constrained to be between 10 and 20 degrees, and wherein C LE =sin(10°) and C UE =sin(20°).

4. A satellite attitude control system according to claim 1 , wherein the retargeting controller comprises:
a PEC-TOC control problem formulator configured to formulate a control problem based on the initial state, the desired final state, and the predetermined set of path and endpoint constraints;
a PEC-TOC control problem solver configured to solve the formulated control problem to determine the set of gimbal angular rate vectors; and
a steering controller configured to produce the retargeting commands based on the set of gimbal angular rate vectors.

5. A satellite attitude control system according to claim 4 , wherein the PEC-TOC control problem solver includes an embedded optimizer configured to use, as the initial state, one of:
final state information from a prior control problem solution;
a previous slew profile with similar beginning and ending conditions; or
information from a lookup table that contains a set of pre-computed initialization states.

6. A satellite attitude control system according to claim 1 , wherein the retargeting controller is further configured to determine a set of reaction wheel angular rate vectors for controlling flywheel spin rates of the reaction wheel actuators for performing momentum management during slew without the use of external actuators and to produce the retargeting commands based on the set of gimbal angular rate vectors and the set of reaction wheel angular rate vectors.

7. A satellite attitude control system according to claim 6 , wherein the flywheel acceleration for each hybrid control moment gyroscope k is formulated as a constraint on desired final flywheel spin rate and is modeled as:

Ω
.

=

1

τ
RW

⁢

(

u
RW

-
Ω

)

where Ω is the reaction wheel spin rate, {dot over (Ω)} is the derivative of the reaction wheel spin rate, T RW is the reaction wheel actuator motor time constant and u RW is the reaction wheel actuator acceleration.

8. A retargeting controller for retargeting a satellite from an initial state through a desired slew and settle maneuver to a desired final state using path and endpoint constrained time-optimal control, the satellite having four hybrid control moment gyroscopes arranged in a pyramid configuration, each hybrid control moment gyroscope including a control moment gyroscope actuator and a reaction wheel actuator, the retargeting controller comprising:
a PEC-TOC control problem formulator configured to formulate a control problem based on the initial state, the desired final state, and a predetermined set of path and endpoint constraints selected to avoid control moment gyroscope actuator singularities and reaction wheel actuator singularities and to ensure that the hybrid control moment gyroscopes will complete the slew maneuver in a configuration capable of performing the settle maneuver using the reaction wheel actuators; and
a PEC-TOC control problem solver configured to solve the formulated control problem to determine a set of gimbal angular rate vectors for the hybrid control moment gyroscopes.

9. A retargeting controller according to claim 8 , further comprising:
a steering controller configured to produce retargeting commands for the hybrid control moment gyroscopes based on the set of gimbal angular rate vectors.

10. A retargeting controller according to claim 8 , wherein the PEC-TOC control problem solver includes an embedded optimizer configured to use, as the initial state, one of:
final state information from a prior control problem solution;
a previous slew profile with similar beginning and ending conditions; or
information from a lookup table that contains a set of pre-computed initialization states.

11. A retargeting controller according to claim 8 , wherein the gimbal angles of each hybrid control moment gyroscope k are constrained by an endpoint constraint:
C LE ≦|sin(δ k ( t f ))|≧ C UE

where δ k is the k-th gimbal angle, t f is the total slew and settle time, C LE is a lower bound and C UE is an upper bound.

12. A retargeting controller according to claim 11 , wherein the gimbal angles at the end of the slew maneuver are constrained to be between 10 and 20 degrees, and wherein C LE =sin(10°) and C UE =sin(20°).

13. A retargeting controller according to claim 8 , wherein the retargeting controller is further configured to determine a set of reaction wheel angular rate vectors for controlling flywheel spin rates of the reaction wheel actuators for performing momentum management during slew without the use of external actuators and to produce the retargeting commands based on the set of gimbal angular rate vectors and the set of reaction wheel angular rate vectors.

14. A retargeting controller system according to claim 13 , wherein the flywheel acceleration for each hybrid control moment gyroscope k is formulated as a constraint on desired final flywheel spin rate and is modeled as:

Ω
.

=

1

τ
RW

⁢

(

u
RW

Assignees

• Charles Stark Draper Laboratory Inc

Inventors

• Lim Sungyung
• Tuohy Seamus
• Dionne Daniel
• Duchesne Laurent
• Breger Louis

Classifications

• G05D1/0883

  Physics · mapped topic

• B64G1/242

  Orbits and trajectories · CPC title

• B64G1/283

  using reaction wheels · CPC title

• B64G2001/245

  Operations & Transport · mapped topic

• B64G1/286 Primary

  using control momentum gyroscopes (CMGs) · CPC title