Kinetic energy vehicle with attitude control system having paired thrusters

Patent metadata

Field	Value
Publication number	US-11353301-B2
Application number	US-202016749324-A
Country	US
Kind code	B2
Filing date	Jan 22, 2020
Priority date	Jan 22, 2020
Publication date	Jun 7, 2022
Grant date	Jun 7, 2022

Abstract

A kinetic energy vehicle (or warhead) has a divert thruster system and an attitude control system, both operatively coupled to receive pressurized gasses from a solid rocket motor that is operatively coupled to both systems. The attitude control system may have two pairs of attitude control thrusters, with one of the pairs diametrically opposed from the other pair, on opposite sides of an end (such as a rear end) of the vehicle. The attitude control thrusters all have radial and circumferential components to their thrust, and various combinations of the attitude control thrusters may be used to achieve desired roll, pitch, and/or yaw.

First claim

What is claimed is:

1. A kinetic energy vehicle comprising:
a solid rocket motor;
a divert thruster system; and
an attitude control system;
wherein the divert thruster system and the attitude control system are operatively coupled to the solid rocket motor to receive pressurized gasses output by the solid rocket motor;
wherein the attitude control system includes two pairs of attitude control thrusters, with one pair diametrically opposed to the other pair, and with the attitude control thrusters of each pair having radial thrust components in an outward radial direction and circumferential thrust components in opposite circumferential directions; and
wherein a first flow passage provides pressurized gas from the solid rocket motor to the attitude control thrusters of one of the pairs of attitude control thrusters; and
wherein a second flow passage provides pressurized gas from the solid rocket motor to the attitude control thrusters of another of the pairs of attitude control thrusters.

2. The vehicle of claim 1 , wherein for all of the attitude control thrusters the radial thrust component is nonzero and the circumferential thrust component is nonzero.

3. The vehicle of claim 2 , wherein for each of the attitude control thrusters the circumferential thrust component is greater than the radial thrust component.

4. The vehicle of claim 1 , wherein the radial thrust components of all of the attitude control thrusters are substantially the same.

5. The vehicle of claim 1 , wherein the magnitude of the circumferential thrust components are all substantially the same.

6. The vehicle of claim 1 ,
wherein the first flow passage provides pressurized gas to a first manifold that is mechanically coupled to the attitude control thrusters of the one of the pairs of attitude control thrusters; and
wherein the second flow passage provides pressurized gas to a second manifold that is mechanically coupled to the attitude control thrusters of the another of the pairs of attitude control thrusters.

7. The vehicle of claim 1 ,
further comprising a control loop operatively coupled to the divert thruster system and the attitude control system;
wherein the control loop provides commands regarding the thrust needed at the attitude control thrusters and at divert thrusters of the divert thruster system.

8. The vehicle of claim 7 , wherein the control loop includes a mixing/limiting logic block that receives input from an autopilot, from a guidance system, and from an attitude control block.

9. The vehicle of claim 1 , further comprising a sensor operatively coupled to the divert thruster system and the attitude control system.

10. The vehicle of claim 9 , wherein the sensor is an electro-optical/infra-red (EO/IR) sensor.

11. The vehicle of claim 1 , wherein the vehicle is an exoatmospheric vehicle.

12. The vehicle of claim 1 , wherein the divert thruster system includes three divert thrusters circumferentially substantially evenly spaced about a perimeter of the vehicle.

13. The vehicle of claim 1 ,
wherein the divert thruster system includes divert thrusters located longitudinally substantially at a center of gravity of the vehicle; and
wherein the attitude control thrusters are aft of the divert thrusters, at an aft end of the vehicle.

14. The vehicle of claim 1 , wherein a combined flow passage from the solid rocket motor splits into the first flow passage and the second flow passage.

15. The vehicle of claim 1 , further comprising an axially-aligned thruster operatively coupled to the solid rocket motor to receive pressurized gasses output by the solid rocket motor.

16. A kinetic energy vehicle comprising:
a solid rocket motor;
a divert thruster system;
an attitude control system; and
an axially-aligned thruster operatively coupled to the solid rocket motor to receive pressurized gasses output by the solid rocket motor;
wherein the divert thruster system and the attitude control system are operatively coupled to the solid rocket motor to receive pressurized gasses output by the solid rocket motor; and
wherein the attitude control system includes two pairs of attitude control thrusters, with one pair diametrically opposed to the other pair, and with the attitude control thrusters of each pair having radial thrust components in an outward radial direction and circumferential thrust components in opposite circumferential directions.

17. The vehicle of claim 16 , wherein the axially-aligned nozzle is coincident with a central longitudinal axis of the kinetic energy vehicle.

18. A method of flying a kinetic energy vehicle, the method comprising:
launching the kinetic energy vehicle; and
adjusting orientation by selectively actuating attitude control thrusters of kinetic energy vehicle to produce pitch, yaw, and roll moments;
wherein the attitude control thrusters are in two pairs of attitude control thrusters, with one pair diametrically opposed to the other pair, and with the attitude control thrusters each pair having radial thrust components in an outward radial direction and circumferential thrust components in opposite circumferential directions; and
wherein the adjusting orientation includes providing pressurized gasses from a solid rocket motor of the vehicle to one of the pairs of attitude control thrusters through a first flow passage, and providing pressurized gasses from the solid rocket motor to another of the pairs of attitude control thrusters through a second flow passage.

19. The method of claim 18 , further comprising translating the vehicle during flight using divert thrusters of a divert thruster system of the vehicle.

20. The method of claim 19 ,
wherein the divert thruster system includes three divert thrusters circumferentially substantially evenly spaced about a perimeter of the vehicle; and
wherein the translating includes rolling the vehicle to position one of the divert thrusters to a desired translation direction.

Assignees

• Raytheon Co

Inventors

• Nguyen Huy P
• Fuentes Rob J
• Schmidt Michael

Classifications

• F42B10/663 Primary

  using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves · CPC title