Rocket vehicle with integrated attitude control and thrust vectoring

Patent metadata

Field	Value
Publication number	US-9429105-B2
Application number	US-201313912837-A
Country	US
Kind code	B2
Filing date	Jun 7, 2013
Priority date	Jun 7, 2013
Publication date	Aug 30, 2016
Grant date	Aug 30, 2016

Abstract

A rocket vehicle includes a controller that integrates operation of a variable-vector main thruster and attitude control thrusters. When the main thruster is firing and roll is commanded, the controller can provide roll moment by firing only a single attitude control thruster, while changing the thrust vector of the main thruster to offset any pitch/yaw moments induced by the firing of the single attitude control thruster. The single attitude control thruster may be a thruster on the leeward side of the rocket vehicle. Since there is a lower wall pressure on the leeward side of the rocket vehicle, the thruster efficiency is improved by accomplishing roll by use of a single thruster (which may be one of a pair of thrusters used to achieve roll in one direction). A significant reduction in fuel use may be accomplished.

First claim

What is claimed is:

1. A rocket vehicle comprising:
a fuselage;
a main thruster coupled to the fuselage, wherein the main thruster provides forward thrust to the rocket vehicle;
an attitude control system that includes pairs of attitude control thrusters for providing roll moments in opposite directions; and
a controller operatively coupled to the attitude control system and the main thruster,
wherein the main thruster is a vector control thruster that allows variation in thrust direction of the main thruster; and
wherein the controller, at least when the rocket vehicle is operating in atmosphere, changes the thrust direction of the main thruster to compensate for the lateral moment created when developing the roll moment by using only one attitude control thruster of the one of the pairs of attitude control thrusters.

2. The rocket vehicle of claim 1 , wherein the controller is part of an autopilot of the rocket vehicle.

3. The rocket vehicle of claim 1 , further comprising an orientation sensor operatively coupled to the controller.

4. The rocket vehicle of claim 1 , wherein the pairs of attitude control thrusters are each diametrically opposed on opposite sides of the rocket vehicle.

5. The rocket vehicle of claim 1 , wherein the attitude control thrusters include at least four attitude control thrusters.

6. The rocket vehicle of claim 1 , wherein the rocket vehicle is a multi-stage rocket vehicle.

7. The rocket vehicle of claim 1 , wherein the rocket vehicle includes a booster that includes the main thruster.

8. A rocket vehicle comprising:
a fuselage;
a main thruster coupled to the fuselage, wherein the main thruster provides forward thrust to the rocket vehicle;
an attitude control system that includes pairs of attitude control thrusters for providing roll moments in opposite directions; and
a controller operatively coupled to the attitude control system and the main thruster;
wherein the main thruster is a vector control thruster that allows variation in thrust direction of the main thruster;
wherein the controller changes the thrust direction of the main thruster to compensate for the lateral moment created when developing the roll moment by using only one attitude control thruster of the one of the pairs of attitude control thrusters; and
wherein the controller, at least sometimes when roll is commanded, selectively uses only a leeward attitude control thruster of one of the pair of attitude control thrusters.

9. The rocket vehicle of claim 8 , wherein the controller selectively uses the leeward attitude control thruster only when the main thruster is already firing.

10. The rocket vehicle of claim 9 , wherein the controller, when only the leeward attitude control thruster is used changes the thrust direction of the main thruster to compensate for pitch moment and/or yaw moment induced by the leeward attitude control thruster.

11. The rocket vehicle of claim 8 , wherein the controller is part of an autopilot of the rocket vehicle.

12. The rocket vehicle of claim 8 , further comprising an orientation sensor operatively coupled to the controller.

13. The rocket vehicle of claim 8 , wherein the pairs of attitude control thrusters are each diametrically opposed on opposite sides of the rocket vehicle.

14. The rocket vehicle of claim 8 , wherein the attitude control thrusters include at least four attitude control thrusters.

15. The rocket vehicle of claim 8 , wherein the rocket vehicle is a multi-stage rocket vehicle.

16. The rocket vehicle of claim 8 , wherein the rocket vehicle includes a booster that includes the main thruster.

Assignees

• Raytheon Co

Inventors

• Barker Michael A
• Smith Dean W
• Marquart Edward J
• Corrado Joseph R

Classifications

• F02K9/80 Primary

  characterised by thrust or thrust vector control (burning control of solid propellants F02K9/26; feeding control of liquid or gaseous propellants F02K9/56; re-ignitable, restartable or intermittently operated rocket-engine plants F02K9/94) · CPC title

• F42B10/66 Primary

  Steering by varying intensity or direction of thrust (thrust vector control of rocket engine plants F02K9/80 {; guiding or controlling apparatus using jets adapted for cosmonautic vehicles B64G1/26}) · CPC title