Effector having morphing airframe and method

Patent metadata

Field	Value
Publication number	US-11796291-B2
Application number	US-202217842200-A
Country	US
Kind code	B2
Filing date	Jun 16, 2022
Priority date	Jan 11, 2022
Publication date	Oct 24, 2023
Grant date	Oct 24, 2023

Abstract

An effector having an extendible range and a method for extending the range of an effector includes using an axially translatable center body that is movable from a stowed position, in which the center body is stowed in an outer body of the effector, to a deployed position in which the center body extends out of the outer body to extend the axial length of the effector. The effector includes a ramjet assembly and the subsystems of the effector are contained in the center body. The movement of the center body exposes radially positioned ramjet fuel in the outer body, such that the air entering the ramjet inlet may be heated by combusting the air with the fuel for additional fuel and propulsion of the effector.

First claim

What is claimed is:

1. An effector comprising:
an outer body; and
a center body movable from a stowed position, in which the center body is stowed in the outer body, to a deployed position, in which the center body extends out of the outer body to extend an axial length of the effector;
further comprising a ramjet inlet having annular ducting into which intake air initially enters;
wherein the annular ducting is defined by an outer surface of the center body and an inner surface of the outer body,
wherein the annular ducting radially surrounds an aft end of the center body when the center body is moved to the deployed position; and
wherein the annular ducting is arranged proximate the aft end of the center body when the center body is moved to the deployed position.

2. The effector according to claim 1 , wherein an aft portion of the center body is arranged radially inwardly relative to the ramjet ducting and includes locking interfaces that engage with corresponding locking interfaces of the outer body when the center body is moved to the deployed position.

3. The effector according to claim 2 , wherein the aft portion of the center body is surrounded by the outer body when the center body is in the deployed position.

4. The effector according to claim 2 , wherein the ramjet inlet is in fluid communication with a ramjet fuel chamber arranged in the outer body when the center body is in the deployed position, and wherein the ramjet fuel is positioned radially outward from the center body.

5. The effector according to claim 1 , wherein the center body includes deployable control surfaces that are deployed when the center body moves to the deployed position.

6. The effector according to claim 1 , wherein the center body includes a plurality of subsystems of the effector.

7. The effector according to claim 1 , wherein the center body moves in a forward direction relative to a direction of travel of the effector.

8. The effector according to claim 1 , wherein an axial length of the center body is more than half of an axial length of the outer body.

9. The effector according to claim 1 , further comprising a pusher plate that is released from an aft end of the effector after the center body moves to the deployed position.

10. The gun-launched effector assembly according to claim 9 , wherein the effector includes fins that are arranged at the aft end of the effector and are deployed after the pusher plate is released.

11. An effector according to claim 1 , wherein the center body is entirely contained within the outer body while in the stowed position.

12. The effector according to claim 1 , wherein the center body and the outer body have corresponding interfaces that engage when the center body is moved to the deployed position to lock the center body and the outer body together.

13. An effector according to claim 12 , wherein the interfaces of the outer body include forward-facing wedges.

14. An effector according to claim 1 ,
wherein the center body and the outer body have corresponding interfaces that engage when the center body is moved to the deployed position to lock the center body and the outer body together; and
wherein the air intake is circumferentially between interfaces of the outer body.

15. The effector according to claim 1 , wherein the center body is axially translatable relative to the outer body.

16. The effector according to claim 1 , wherein the effector includes a ramjet assembly.

17. The effector according to claim 16 , wherein the outer body contains a ramjet fuel chamber that is opened when the center body is moved to the deployed position.

18. An effector according to claim 12 , wherein the corresponding interfaces have corresponding step shapes.

19. The effector according to claim 12 , wherein the corresponding interfaces are formed as conical interfaces that have a tapering shape in an axial direction.

20. The effector according to claim 19 , wherein the conical interfaces are circumferentially spaced about a longitudinal axis of the effector.

21. The effector according to claim 19 , wherein the conical interfaces of the outer body are arranged at a forward end of the outer body and the conical interfaces of the center body are arranged at an aft end of the center body.

22. A gun-launched effector assembly comprising:
a launcher; and
an effector that is fired from the launcher, the effector having an outer body and a center body that is movable from a stowed position, in which the outer body is stowed in the outer body, to a deployed position, in which the center body is moved out of the outer body to extend an axial length of the effector, the center body moving from the stowed position to the deployed position after a muzzle exit of the effector from the launcher;
wherein the effector further includes a ramjet inlet having annular ducting into which intake air initially enters;
wherein the annular ducting is defined by an outer surface of the center body and an inner surface of the outer body,
wherein the annular ducting radially surrounds an aft end of the center body when the center body is moved to the deployed position; and
wherein the annular ducting is arranged proximate the aft end of the center body when the center body is moved to the deployed position.

Assignees

• Raytheon Co

Inventors

• Merems Paul A
• Burke Shawn Patrick

Classifications

• B62D29/043

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