Granted Patent B1

US 12,209,848 · App. 18/536,527 · Granted Jan 28, 2025

Inventor: Michael J. Wilson (Lakeville, MN)

Assignee: Northrop Grumman Systems Corporation

F42B10/64F42B10/26F42B10/54F42B30/10

Abstract

Claims (34)

1. A projectile having a nose portion with a forward tip, a body portion including a chassis defining a sidewall, a tail portion, and a central axis, the projectile comprising:

a control support portion extending axially from the nose portion to the body portion; and

a collar assembly comprising:

a collar pivotally mounted to the control support portion, the collar having a circumferentially and axially extending exterior sidewall; and

a plurality of variable sweep wings for directional control of the projectile, the plurality of variable sweep wings each have a first end portion pivotally mounted to an interior of the collar and coupled to a wing actuator configured to pivot a second end portion of each of the plurality of variable sweep wings between and including a first position, where the plurality of variable sweep wings are oriented having a lengthwise wing axis generally parallel to the central axis of the projectile, a second position, where the second end portion of the plurality of variable sweep wings are rotated outwardly from the sidewall of the collar and where the lengthwise wing axis of the plurality of variable sweep wings are oriented generally perpendicular to the central axis of the projectile, and a third position, where the lengthwise wing axis of the plurality of variable sweep wings has a wing sweep angle with respect to the central axis of the projectile.

2. The projectile of claim 1 , wherein the exterior sidewall of the collar comprises a plurality of fixed aerodynamic surfaces thereon for spinning the collar, and wherein the collar assembly includes one or more power generation components secured to one or more of the collar and the control support portion for providing power generation in response to the spinning of the collar and for braking the spinning of the collar.

3. The projectile of claim 1 , wherein the collar assembly is positioned forward of 50% of a total length of the projectile or forward of 60% of a total length of the projectile.

4. The projectile of claim 1 , wherein the collar assembly and the control support portion are configured as a portion of a fuse assembly that is removably attached to the projectile.

5. The projectile of claim 1 , wherein each of the plurality of variable sweep wings are canted, at a fixed angle with respect to the central axis of the projectile, for generating a maneuvering torque on the projectile.

6. The projectile of claim 1 , wherein the wing sweep angle is an acute angle.

7. The projectile of claim 6 , wherein the wing actuator is further configured to rotate the second end portion forwardly and rearwardly between and including the first position, second position, and third position.

8. The guided projectile of claim 1 , wherein the wing actuator is further configured to rotate the second end portion to one or more of the first position and the second position based on the altitude of the projectile.

9. The guided projectile of claim 1 , wherein, when in the first position, no portion of the plurality of variable sweep wings extends outwardly beyond an outer envelope of the collar.

10. The guided projectile of claim 1 , wherein the plurality of variable sweep wings include two wings arranged on opposing portions of the collar assembly, the two wings configured each configured to rotate from the first position towards the second position in one of a forward direction and a rearward direction and additionally configured to rotate from the second position towards the first position in the other of the forward direction and the rearward direction.

11. A method of guiding to a target a projectile including a chassis extending from a tail portion to a body portion, the chassis defining a sidewall of the body portion, the projectile further including a control support portion extending axially from a nose portion and connecting to the body portion and a collar assembly having a collar pivotally mounted to the control support portion, the collar having a circumferentially and axially extending exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and the collar having a plurality of variable sweep wings canted at a fixed angle with respect to the central axis of the projectile for directional control of the projectile, the plurality of variable sweep wings each having a first end portion pivotally mounted to an interior of the collar and coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented having a lengthwise wing axis generally parallel to the central axis of the projectile to a second position, where the second end portion of the wings are rotated outwardly from the sidewall of the collar and where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile, the method comprising:

firing the projectile from a projectile firing platform, the projectile having the plurality of variable sweep wings configured in the first position;

determining the projectile has reached a first altitude threshold; and

deploying, in response to determining the projectile has reached the first altitude, the plurality of variable sweep wings from the first position to the second position for gliding and maneuvering.

12. The method of claim 11 , wherein the method further comprises:

determining that the projectile has reached a second altitude threshold; and

configuring, in response to determining the projectile reached the second altitude, the plurality of variable sweep wings from the second position to a third position, between the first and second position, where the longitudinal wing axis has a wing sweep angle with the central axis that is an acute angle.

13. The method of claim 12 , wherein the second altitude threshold is less than the first altitude threshold.

14. The method of claim 11 , wherein the method further comprises acquiring the target, and wherein configuring the plurality of variable sweep wings from the second position to the third position is further in response to acquiring the target.

15. The method of claim 11 , wherein the collar assembly, the nose portion, and the control support portion are configured as a fuse assembly removably attached to the body portion.

16. The method of claim 11 , wherein the collar assembly is positioned forward of 60% of a total length of the projectile.

17. A system for guiding a projectile, the system removably attachable to a chassis of a projectile to configure the projectile for guided flight, the system comprising:

a projectile nose portion and a control support portion extending axially from the nose portion;

a collar assembly having a collar pivotally mounted to the control support portion, the collar having a circumferentially and axially extending exterior sidewall and the collar having a plurality of variable sweep wings for directional control of the projectile, the plurality of variable sweep wings each having a first end portion pivotally mounted to an interior of the collar and coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented having a lengthwise wing axis generally parallel to the central axis of the projectile to a second position, where the second end portion of the wings are rotated outwardly from the sidewall of the collar and where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile; and

a processor and a non-transitory computer readable storage medium, wherein the computer readable storage medium includes a set of instructions executable by the processor to cause the processor to:

determine that the projectile has reached a first altitude threshold, and in response, deploying the plurality of variable sweep wings from the first position to the second position for gliding and maneuvering;

determine that the projectile has reached a second altitude threshold, and in response configuring the plurality of variable sweep wings from the second position to a third position, between the first and second position, where the longitudinal wing axis has a wing sweep angle with the central axis that is an acute angle.

18. The system of claim 17 , wherein the collar assembly includes a plurality of fixed aerodynamic surfaces for spinning the collar and one or more power generation components secured to one or more of the collar and the control support portion for providing power generation in response to the spinning and for braking of the spinning.

19. The system of claim 17 , wherein the instructions are executable by the processor to further cause the processor to acquire the target, and wherein configuring the plurality of variable sweep wings from the second position to the third position is further in response to acquiring the target.

20. The system of claim 17 , wherein the plurality of variable swept wings include only two wings arranged on opposing portions of the collar assembly, the two wings configured each configured to rotate from the first position towards the second position in one of a forward direction and a rearward direction and additionally configured to rotate from the second position towards the first position in the other of the forward direction and the rearward direction.

Assignments (3)

Continuity (3)

References Cited (257)