Flight control of an airborne vehicle at low velocity

• US 5,875,993 A
• Filed: 07/10/1997
• Issued: 03/02/1999
• Est. Priority Date: 07/17/1996
• Status: Expired due to Term

• Current Assignee: Rafael - Armament Development Authority Ltd.
• Original Assignee: State of Israel--Ministry of Defence Armament Development Authority Rafael
• Inventors: Benshabat, Daniel G., Weiss, Haim
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): Wesson, Theresa M.
• Application Number:
  US08/891,040
• Time in Patent Office: 600 Days
• Field of Search: 244/3.22, 244/3.21, 244/3.15, 244/164, 244/165
• US Class Current: 244/3.22
• CPC Class Codes: G05D 1/107 specially adapted for missiles

Abstract

A control system for controlling an airborne vehicle at a time of low aerodynamic moment is provided. The control system includes combined aerodynamic and thrust vector control actuators, a quaternion generator which determines a quaternion error value defining the error between the quaternion of the vehicle and the commanded quaternion; and a controller which controls the actuators based on the quaternion error value, an aerodynamic control gain and a thrust vector control gain.

Claims

1. A control system for controlling an airborne vehicle at a time of low aerodynamic moment, the control system comprising:

a. a plurality of actuators;

b. combined aerodynamic and thrust vector control surfaces controlled by said actuators;

c. means for determining a quaternion error value defining the error between a quaternion of the vehicle and a commanded quaternion; and

d. control means for controlling said actuators based on said quaternion error value, an aerodynamic control gain and a thrust vector control gain.

2. A control system according to claim 1, wherein said aerodynamic control gain is a velocity dependent gain function which changes state in accordance with the velocity of said vehicle.

3. A control system according to claim 2, wherein said control means adds said aerodynamic control gain and said thrust vector control gain to produce a control gain for said control means.

4. A control system according to claim 3, wherein said vehicle is a missile, and wherein said means for determining and said control means form an inner control loop providing commands to said actuators, and wherein said control system additionally comprise:

a. an outer position control loop for controlling the linear position of said missile;

b. a middle linear velocity control loop for controlling the linear velocity of said missile and for generating pitch and yaw commands; and

c. an external roll command generator for generating roll commands.

5. A control system according to claim 2, wherein said thrust vector control gain is a time dependent function.

6. A control system according to claim 5, wherein said control means adds said aerodynamic control gain and said thrust vector control gain to produce a control gain for said control means.

7. A control system according to claim 6, wherein said vehicle is a missile, and wherein said means for determining and said control means form an inner control loop providing commands to said actuators, and wherein said control system additionally comprises:

a. an outer position control loop for controlling the linear position of said missile;

b. a middle linear velocity control loop for controlling the linear velocity of said missile and for generating pitch and yaw commands; and

c. an external roll command generator for generating roll commands.

8. A control system according to claim 5, wherein said vehicle is a missile, and wherein said means for determining and said control means form an inner control loop providing commands to said actuators, and wherein said control system additionally comprises:

a. an outer position control loop for controlling the linear position of said missile;

b. a middle linear velocity control loop for controlling the linear velocity of said missile and for generating pitch and yaw commands; and

c. an external roll command generator for generating roll commands.

9. A control system according to claim 2, wherein said vehicle is a missile, and wherein said means for determining and said control means form an inner control loop providing commands to said actuators, and wherein said control system additionally comprises:

a. an outer position control loop for controlling the linear position of said missile;

b. a middle linear velocity control loop for controlling the linear velocity of said missile and for generating pitch and yaw commands; and

c. an external roll command generator for generation roll commands.

10. A control system according to claim 1, wherein said thrust vector control gain is a time dependent function.

11. A control system according to claim 10, wherein said control means adds said aerodynamic control gain and said thrust vector control gain to produce a control gain for said control means.

12. A control system according to claim 11, wherein said vehicle is a missile, and wherein said means for determining and said control means form an inner control loop providing commands to said actuators, and wherein said control system additionally comprises:

a. an outer position control loop for controlling the linear position of said missile;

b. a middle linear velocity control loop for controlling the linear velocity of said missile and for generating pitch and yaw commands; and

c. an external roll command generator for generating roll commands.

13. A control system according to claim 10, wherein said vehicle is a missile, and wherein said means for determining and said control means form an inner control loop providing commands to said actuators, and wherein said control system additionally comprises:

a. an outer position control loop for controlling the linear position of said missile;

b. a middle linear velocity control loop for controlling the linear velocity of said missile and for generating pitch and yaw commands; and

c. an external roll command generator for generation roll commands.

14. A control system according to claim 1, wherein said vehicle is a missile.

15. A control system according to claim 14, wherein said means for determining and said control means form an inner control loop providing commands to said actuators and wherein said control system additionally comprises:

a. an outer position control loop for controlling the linear position of said missile;

b. a middle linear velocity control loop for controlling the linear velocity of said missile and for generating pitch and yaw commands; and

c. an external roll command generator for generating roll commands.