Despun wing control system for guided projectile maneuvers

Patent metadata

Field	Value
Publication number	US-12031802-B2
Application number	US-202318107554-A
Country	US
Kind code	B2
Filing date	Feb 9, 2023
Priority date	Jul 26, 2017
Publication date	Jul 9, 2024
Grant date	Jul 9, 2024

Abstract

A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.

First claim

What is claimed is:

1. A munitions assembly for an air-delivered munition, the munitions assembly comprising:
a collar mounted around a control support portion that extends axially along a central axis, the collar rotatably mounted to the control support portion via bearings and having a circumferentially and axially extending exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for generating a rotational force on the collar in response to an oncoming airstream;
a plurality of variable sweep wings, each of the plurality of wings canted, at a fixed angle with respect to the central axis of the projectile, for generating a lifting force on the munitions assembly in response to the oncoming airstream, the plurality of variable sweep wings each having a first end portion pivotally mounted to an interior of the collar and configured to rotate for positioning a second end portion of each of the plurality of variable sweep wings 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 and no portion of the wings extends outwardly beyond an outer envelope of the collar;
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 third position, where the wings are oriented having the lengthwise wing axis at an angle with respect to the central axis such that the wings have an acute wing sweep angle; and

one or more braking components, secured to one or more of the collar and the control support portion, for braking rotation of the collar about the control support portion at one or more of a plurality of rotational positions to apply the lifting force generated by the variable sweep wings in one or more of a plurality of radial directions from the central axis that correspond to the plurality of radial positions; wherein the first position, the second position, and the third position of the variable sweep wings each correspond to a different lift-to-drag ratio for the munitions assembly.

2. The munitions assembly of claim 1 , wherein the munitions assembly is attached to an air-delivered munition including a nose portion with a forward tip, a body portion including a chassis defining a sidewall, a tail portion, and a central axis, wherein the control support portion extends axially from the nose portion to the body portion.

3. The munitions assembly of claim 2 , wherein the air-delivered munition is a medium or large caliber spin-stabilized projectile.

4. The munitions assembly of claim 2 , wherein the air-delivered munition is a fin-stabilized munition.

5. The munitions assembly of claim 2 , wherein the collar assembly is positioned forward of 50% of a total length of the munition and the attached munitions assembly.

6. The munitions assembly of claim 2 , wherein the collar assembly is positioned forward of 60% of a total length of the munition and the attached munitions assembly.

7. The munitions assembly of claim 1 , wherein the munitions assembly is configured as a fuse assembly that is removably attached to a body portion of an air-delivered munition.

8. The munitions assembly of claim 1 , further comprising a wing actuator configured to rotate the plurality of variable sweep wings to one or more of the first position, second position, and third position.

9. The munitions assembly of claim 8 , wherein the wing actuator is configured to rotate the plurality of variable sweep wings to one or more of the first position, second position, and third position based on the altitude of the projectile and a distance of the projectile from a target.

10. The munitions assembly of claim 1 , wherein the plurality of variable swept wings include only two wings arranged on opposing portions of the munitions assembly, the two wings 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. The munitions assembly of claim 1 , wherein the one or more braking components include one or more power generation components secured to one or more of the collar and the control support portion for providing power generation and for braking rotation of the rotatable collar about the control support portion.

12. A projectile system comprising:
a projectile having a collar assembly with a plurality of variable sweep wings, each of the plurality of wings canted, at a fixed angle with respect to the central axis of the munition, for generating a lifting force in response to the oncoming airstream, the plurality of variable sweep wings each having a first end portion pivotally mounted to an interior of the collar assembly and configured to rotate to a plurality of positions including a first position, where the wings are oriented having a lengthwise wing axis generally parallel to the central axis of the projectile and no portion of the wings extends outwardly beyond an outer envelope of the collar assembly, a second position, where a second end portion of the wings are positioned outwardly from the sidewall of the collar assembly and where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile, and a third position, where the wings are oriented having the lengthwise wing axis at an angle with respect to the central axis such that the wings have an acute wing sweep angle, and
a computer program product for configuring the projectile comprising: a computer readable storage medium having program instructions embodied therewith, wherein the computer readable storage medium is not a transitory signal per se, the program instructions executable by a processor, the program instructions comprising:
operation means for determining a target for the projectile and determine target data including an indication of a target location;
operation means for determining projectile deployment data including an indication of a deployment position for the projectile;
operation means for determining, using a predicted ballistic trajectory for the projectile, a flight plan including a set of flight instructions for the projectile that delivers the projectile to the target location; and
operation means for programming the projectile with the set of flight instructions.

13. 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 munitions 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 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 configured to rotate 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;

Assignees

• Northrop Grumman Systems Corp

Inventors

• Wilson Michael J

Classifications

• F42B10/26 Primary

  using spin (F42B10/04, F42B10/12, F42B10/14, F42B10/24, F42B14/02 take precedence) · CPC title

• F42B10/54

  Spin braking means · CPC title

• F42B30/10

  Mortar projectiles · CPC title

• F42B10/64 Primary

  of fins · CPC title