Closed-form integrator for the quaternion (euler angle) kinematics equations

• US 6,061,611 A
• Filed: 01/06/1998
• Issued: 05/09/2000
• Est. Priority Date: 01/06/1998
• Status: Expired due to Fees

• Current Assignee: National Aeronautics and Space Administration US Government As Represented By The Administrator of The
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Whitmore, Stephen A.
• Primary Examiner(s): Cuchlinski, Jr., William A.
• Assistant Examiner(s): Hernandez, Olga
• Application Number:
  US09/002,871
• Time in Patent Office: 854 Days
• Field of Search: 701/4, 701/38, 434/51, 244/184, 244/194, 244/90 R
• US Class Current: 701/4
• CPC Class Codes: B64C 17/06 by gyroscopic apparatus
• CPC Class Codes: B64G 1/244 Spacecraft control systems

Abstract

The invention is embodied in a method of integrating kinematics equations for updating a set of vehicle attitude angles of a vehicle using 3-dimensional angular velocities of the vehicle, which includes computing an integrating factor matrix from quantities corresponding to the 3-dimensional angular velocities, computing a total integrated angular rate from the quantities corresponding to a 3-dimensional angular velocities, computing a state transition matrix as a sum of (a) a first complementary function of the total integrated angular rate and (b) the integrating factor matrix multiplied by a second complementary function of the total integrated angular rate, and updating the set of vehicle attitude angles using the state transition matrix. Preferably, the method further includes computing a quanternion vector from the quantities corresponding to the 3-dimensional angular velocities, in which case the updating of the set of vehicle attitude angles using the state transition matrix is carried out by (a) updating the quanternion vector by multiplying the quanternion vector by the state transition matrix to produce an updated quanternion vector and (b) computing an updated set of vehicle attitude angles from the updated quanternion vector. The first and second trigonometric functions are complementary, such as a sine and a cosine. The quantities corresponding to the 3-dimensional angular velocities include respective averages of the 3-dimensional angular velocities over plural time frames. The updating of the quanternion vector preserves the norm of the vector, whereby the updated set of vehicle attitude angles are virtually error-free.

Claims

1. In a vehicle such as a flight vehicle, a control system comprising:

acceleration sensors with a angular velocity processor for providing 3-D angular velocities;

a navigation computer for computing trajectory corrections from attitude angles of said vehicle;

a kinematics equations integrator for updating a set of vehicle attitude angles of a vehicle using said 3-dimensional angular velocities of said vehicle, said integrator being connected to said navigation computer and to said angular velocity processor and comprising;

an integrating factor module which computes an integrating factor matrix from quantities corresponding to said 3-dimensional angular velocities;

a total integrated angular rate module which computes a total integrated angular rate from said quantities corresponding to 3-dimensional angular velocities;

a state transition matrix module, connected to said integrating factor module and said total integrated angular rate module, which computes a state transition matrix as a sum of (a) a first complementary function of said total integrated angular rate and (b) said integrating factor matrix multiplied by a second complementary function of said total integrated angular rate; and

an updating module which updates said set of vehicle attitude angles using said state transition matrix for output to said navigation computer.

2. The apparatus of claim 1 wherein said integrator further comprises:

a quaternion module which computes a quaternion vector from said quantities corresponding to said 3-dimensional angular velocities; and

wherein said updating module comprises;

(a) a matrix multiplier which updates said quaternion vector by multiplying said quaternion vector by said state transition matrix to produce an updated quaternion vector;

(b) a reverse transformation module which computes an updated set of vehicle attitude angles from said updated quaternion vector.

4. A computer-readable medium storing computer executable instructions for performing the steps recited in claim 1.

5. The method of claim 1 wherein said quantities corresponding to said 3-dimensional angular velocities comprise respective averages of said 3-dimensional angular velocities over plural time frames.

6. The method of claim 1 further comprising:

computing a quaternion vector from said quantities corresponding to said 3-dimensional angular velocities; and

wherein the updating of said set of vehicle attitude angles using said state transition matrix comprises;

(a) updating said quaternion vector by multiplying said quaternion vector by said state transition matrix to produce an updated quaternion vector;

(b) computing an updated set of vehicle attitude angles from said updated quaternion vector.

7. The method of claim 6 wherein the updating of said quaternion vector preserves the norm of said vector, whereby said updated set of vehicle attitude angles are virtually error-free.

8. The method of claim 1 wherein said first and second trigonometric functions are complementary.

9. The method of claim 8 wherein said first and second trigonometric functions comprise a sine and a cosine, respectively.

3. A method of integrating kinematics equations for updating a set of vehicle attitude angles of a vehicle using 3-dimensional angular velocities of said vehicle, comprising:

computing an integrating factor matrix from quantities corresponding to said 3-dimensional angular velocities;

computing a total integrated angular rate from said quantities corresponding to 3-dimensional angular velocities;

computing a state transition matrix as a sum of (a) a first complementary function of said total integrated angular rate and (b) said integrating factor matrix multiplied by a second complementary function of said total integrated angular rate; and

updating said set of vehicle attitude angles using said state transition matrix.

10. Apparatus for use in integrating kinematics equations for updating a set of vehicle attitude angles of a vehicle using 3-dimensional angular velocities of said vehicle, said apparatus comprising:

a processor;

a memory having executable instructions stored therein; and

wherein said processor, in response to said instructions stored in said memory;

computes an integrating factor matrix from quantities corresponding to said 3-dimensional angular velocities;

computes a total integrated angular rate from said quantities corresponding to 3-dimensional angular velocities;

computes a state transition matrix as a sum of (a) a first trigonometric function of said total integrated angular rate and (b) said integrating factor matrix multiplied by a second trigonometric function of said total integrated angular rate; and

updates said set of vehicle attitude angles using said state transition matrix.

11. The apparatus of claim 10 wherein said quantities corresponding to said 3-dimensional angular velocities comprise respective averages of said 3-dimensional angular velocities over plural time frames.

12. The apparatus of claim 10 wherein said processor further:

computes a quaternion vector from said quantities corresponding to said 3-dimensional angular velocities; and

wherein the updating of said set of vehicle attitude angles using said state transition matrix comprises;

(a) updating said quaternion vector by multiplying said quaternion vector by said state transition matrix to produce an updated quaternion vector;

(b) computing an updated set of vehicle attitude angles from said updated quaternion vector.

13. The apparatus of claim 12 wherein said first and second trigonometric functions are complementary.

14. The apparatus of claim 12 wherein said first and second trigonometric functions comprise a sine and a cosine, respectively.

15. The apparatus of claim 12 wherein the updating of said quaternion vector preserves the norm of said vector, whereby said updated set of vehicle attitude angles are virtually error-free.

16. A kinematics equations integrator for updating a set of vehicle attitude angles of a vehicle using 3-dimensional angular velocities of said vehicle, comprising:

an integrating factor module which computes an integrating factor matrix from quantities corresponding to said 3-dimensional angular velocities;

a total integrated angular rate module which computes a total integrated angular rate from said quantities corresponding to 3-dimensional angular velocities;

a state transition matrix module, connected to said integrating factor module and said total integrated angular rate module, which computes a state transition matrix as a sum of (a) a first complementary function of said total integrated angular rate and (b) said integrating factor matrix multiplied by a second complementary function of said total integrated angular rate; and

an updating module which updates said set of vehicle attitude angles using said state transition matrix.

17. The apparatus of claim 16 wherein said quantities corresponding to said 3-dimensional angular velocities comprise respective averages of said 3-dimensional angular velocities over plural time frames.

18. The apparatus of claim 16 further comprising:

a quaternion module which computes a quaternion vector from said quantities corresponding to said 3-dimensional angular velocities; and

wherein said updating module comprises;

(a) a matrix multiplier which updates said quaternion vector by multiplying said quaternion vector by said state transition matrix to produce an updated quaternion vector;

(b) a reverse transformation module which computes an updated set of vehicle attitude angles from said updated quaternion vector.

19. The apparatus of claim 18 wherein said updating module which updates said quaternion vector preserves the norm of said vector, whereby said updated set of vehicle attitude angles are virtually error-free.

20. The apparatus of claim 16 wherein said first and second trigonometric functions are complementary.

21. The apparatus of claim 20 wherein said first and second trigonometric functions comprise a sine and a cosine, respectively.