Vehicle attitude control using jet paddles and/or movable mass

Patent metadata

Field	Value
Publication number	US-9919792-B2
Application number	US-201414322752-A
Country	US
Kind code	B2
Filing date	Jul 2, 2014
Priority date	Jul 2, 2014
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

Attitude and/or attitude rate of a vehicle may be controlled using jet paddles and/or movable masses. Thrust direction generally may also be controlled using jet paddles. The jet paddles may be moved into and/or sufficiently close to the exhaust flow, and out of the exhaust flow, to change the thrust direction. Movable masses may also be used in addition to, or in lieu of, jet paddles. Movement of the movable masses alters a center-of-mass of the vehicle, generating torque that changes vehicle attitude.

First claim

The invention claimed is:

1. An apparatus, comprising:
a plurality of jet paddles located outside of a nozzle of the apparatus from which an exhaust flow exits the apparatus, the plurality of jet paddles configured to be moved into and/or sufficiently close to the exhaust flow, and configured to be moved away from the exhaust flow, to change a direction of thrust produced by the exhaust flow, wherein
each of the plurality of jet paddles rotates about an axis substantially orthogonal to an axis of symmetry of the nozzle, translates towards and away from the exhaust flow, or moves by a combination of rotation and translation towards and away from the exhaust flow,
the plurality of jet paddles are operably connected to a body of the apparatus, and
an edge of at least one of the plurality of jet paddles is connected to the body before an end of the nozzle from which the exhaust flow exits the nozzle and another edge of the at least one of the plurality of jet paddles extends beyond the end of the nozzle such that a portion of the at least one of the plurality of jet paddles is partially aft of the end of the nozzle.

2. The apparatus of claim 1 , further comprising:
a linkage for each of the jet paddles configured to enable the respective jet paddle to move towards and away from the exhaust flow; and
an actuator for each of the jet paddles operably connected to the respective linkage, jet paddle, or both, and configured to move the respective jet paddle towards and away from the exhaust flow.

3. The apparatus of claim 1 , further comprising:
a computing system configured to monitor a flight of the apparatus, the computing system configured to:
monitor a flight of the apparatus for whether to change attitude and/or attitude rate due to a planned change in attitude, a planned change in attitude rate, and/or due to unknown force perturbations, and
when change is desired, perform thrust vector control by moving one or more of the jet paddles into or sufficiently close to the exhaust flow so as to affect the desired change.

4. The apparatus of claim 3 , wherein the computing system is configured to change pitch by moving at least one jet paddle to generate pitch torque.

5. The apparatus of claim 3 , wherein the computing system is configured to change yaw by moving at least one jet paddle to create a yaw force in a direction.

6. The apparatus of claim 3 , wherein the computing system is configured to control roll by moving two pairs of jet paddles that are opposite one another with the exhaust flow between them, the two pairs of jet paddles positioned and moved to generate positive and negative roll torques.

7. The apparatus of claim 1 , wherein at least two jet paddles are positioned on a same side of the apparatus.

8. A computer-implemented method, comprising:
monitoring, by a computing system, whether to execute thrust direction changes for a vehicle producing thrust with an exhaust flow due to a planned change thrust direction, and/or due to unknown and/or unplanned force perturbations; and
altering the thrust direction of the vehicle, by the computing system, when a thrust direction change is desired by moving at least one jet paddle into and/or sufficiently close to the exhaust flow, and/or moving at least one jet paddle away from the exhaust flow, wherein
the at least one jet paddle is moved by rotation about an axis substantially orthogonal to an axis of symmetry of the nozzle from which the exhaust flow exits the vehicle, moved by translation towards and away from the exhaust flow, or moved by a combination of rotation and translation towards and away from the exhaust flow,
the plurality of jet paddles are operably connected to a body of the vehicle,
the at least one jet paddle is located outside of a nozzle of the vehicle from which an exhaust flow exits the vehicle, and
an edge of at least one of the plurality of jet paddles is connected to the body before an end of the nozzle from which the exhaust flow exits the nozzle and another edge of the at least one of the plurality of jet paddles extends beyond the end of the nozzle such that a portion of the at least one of the plurality of jet paddles is partially aft of the end of the nozzle.

9. The computer-implemented method of claim 8 , further comprising:
changing pitch, by the computing system, by moving at least one of the paddles into or sufficiently close to the exhaust flow to create a force in one direction along a single axis.

10. The computer-implemented method of claim 8 , further comprising:
changing yaw, by the computing system, by moving at least one jet paddle into or sufficiently close to the exhaust flow to create a yaw force in a direction.

11. The computer-implemented method of claim 8 , further comprising:
changing roll, by the computing system, by moving at least two jet paddles that are opposite each other, with the exhaust flow between them, to cause the vehicle to roll.

12. The computer-implemented method of claim 8 , wherein two or more of pitch, yaw, and roll are changed simultaneously.

13. An apparatus, comprising:
a plurality of jet paddles configured to be moved into and/or sufficiently close to an exhaust flow, and configured to be moved away from the exhaust flow, to change a direction of thrust produced by the exhaust flow, wherein the plurality of jet paddles each rotate about an axis substantially orthogonal to an axis of symmetry of a nozzle from which the exhaust flow exits the apparatus, translate towards and away from the exhaust flow, or move by a combination of rotation and translation towards and away from the exhaust flow; and
one or more movable masses that sufficiently move a center-of-mass of the apparatus off a line of action of external forces acting on the apparatus, the external forces comprising a thrust force created by the exhaust flow, to at least in part facilitate flight control of the apparatus while the apparatus is in powered flight, wherein
the plurality of jet paddles are operably connected to a body of the apparatus.

14. The apparatus of claim 13 , further comprising:
a computing system configured to perform attitude and/or attitude rate control for the apparatus by moving one or more of the jet paddles, at least one of the one or more moving masses, or both.

15. A computer-implemented method, comprising:
monitoring, by a computing system, whether to change attitude and/or attitude rate due to a planned correction, and/or due to unknown and/or unplanned force perturbations; and
altering the attitude and/or attitude rate of the vehicle, by the computing system, when a change is desired by moving at least one jet paddle sufficiently close to an exhaust flow such that the attitude and/or attitude rate of the vehicle is sufficiently altered to control flight, wherein
the at least one jet paddle is moved via rotation about an axis substantially orthogonal to an axis of symmetry of a nozzle from which the exhaust flow exits a vehicle, via translation towards and away from an exhaust flow, or via a combination of rotation and translation towards and away from the exhaust flow, and
an edge of the at least one jet paddle is connected to the body before an end of the nozzle from which the exhaust flow exits the nozzle and another edge of the at least one jet paddle extends beyond the end of the nozzle such that a portion of the at least one jet paddle is partially aft of the end of the nozzle.

16. The computer-implemented method of claim 15 , wherein the altering of the attitude and/or attitude rate of the vehicle comprises altering a pitch of the vehicle, altering a y

Assignees

• Aerospace Corp

Inventors

• Zondervan Kevin L
• Fuller Jerome K

Classifications

• F02K1/002

  with means to modify the direction of thrust vector (F02K1/54 takes precedence; thrust vectoring of rockets F02K9/80) · CPC title

• B64C17/00

  Aircraft stabilisation not otherwise provided for · CPC title

• F02K9/90

  using deflectors (F02K9/82 takes precedence) · CPC title

• B64C19/00

  Aircraft control not otherwise provided for · CPC title

• F02K9/80

  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