Projectile with a range extending wing assembly
An elongate cylindrical projectile including processing circuitry, a head assembly, a tail section assembly, a mid body section positioned between the head assembly and tail assembly, and a wing assembly, the wing assembly including a deployable wing which is stored in a closed position entirely within the mid body section and is deployed, using an actuator, to outside the mid body section in an open position in response to a command from the processing circuitry.
1. An elongate cylindrical projectile, comprising:
processing circuitry;
a head assembly;
a tail section assembly;
a mid body section positioned between the head assembly and tail assembly; and
a wing assembly, the wing assembly including a deployable wing which is stored in a closed position entirely within the mid body section and is deployed, using an actuator, to outside the mid body section in an open position in response to a command from the processing circuitry,
wherein the wing includes a forward wing pivotally attached at a proximal end, and an aft wing pivotally attached at a proximal end, wingtips of the forward wing and the aft wing are attached at a distal pivot, and the proximal ends of the forward wing and aft wing are within the mid body section in the open position.
2. The projectile of claim 1 , wherein the proximal end of the forward wing is pivotally attached to a pivot member and the proximal end of the aft wing is coupled to a carriage that is displaced along a longitudinal axis of the projectile to deploy the wing from the closed position to the open position.
3. The projectile of claim 2 , wherein the wing assembly includes a cylindrical threaded rod configured to be rotated via the actuator, rotation of the cylindrical threaded rod in a first direction displaces the carriage linearly along the projectile, and displacement of the carriage causes the wing to be deployed from the closed position to the open position.
4. The projectile of claim 3 , wherein the cylindrical threaded rod is a ball screw and the carriage includes a nut fixed to the carriage to prevent the nut from rotating such that, when the ball screw is rotated, the nut is slid along the ball screw to displace the carriage linearly.
5. The projectile of claim 3 , wherein the actuator is a motor mounted to the pivot member on a side of the pivot member opposite to the carriage, and the pivot member includes a hole through which the cylindrical threaded rod is positioned to communicate with the motor and the carriage.
6. The projectile of claim 3 , wherein the proximal end of the forward wing is pivotally attached to the pivot member such that the forward wing does not move linearly with the aft wing.
7. The projectile of claim 1 , wherein the forward wing and the aft wing are each a rectilinear member configured to generate aerodynamic lift.
8. The projectile of claim 1 , wherein, when the wing is in the closed position, the forward wing and the aft wing are parallel to each other.
9. The projectile of claim 1 , wherein the mid body includes a slot through which the wing is deployed when the wing is in the open position.
10. The projectile of claim 1 , wherein the projectile is an artillery round, a missile, or a mortar.
11. The projectile of claim 1 , wherein the head assembly includes a warhead and a fuze configured to deliver explosive effects on impact of the projectile.
12. The projectile of claim 1 , wherein the tail section includes one or more fins.
13. A method of deploying a wing of a projectile, the projectile comprising processing circuitry, a head assembly, a tail section assembly, and a mid body section positioned between the head assembly and tail assembly, the method comprising:
storing the wing in a closed position entirely within the mid body section, the wing including a forward wing pivotally attached at a proximal end, and an aft wing pivotally attached at a proximal end, wingtips of the forward wing and the aft wing are attached at a distal pivot, the proximal ends of the forward wing and aft wing are within the mid body section in the open position, and
deploying the wing, via an actuator, to outside the mid body section in an open position in response to a command from the processing circuitry.
14. The method of claim 13 , wherein the deploying comprises actuating a cylindrical threaded rod, which displaces a carriage linearly along a longitudinal axis of the projectile to deploy the wing from the closed position to the open position, and the proximal end of the aft wing is coupled to the carriage such that the aft wing moves linearly with the carriage and pivotally displaces the forward wing.
15. The method of claim 14 , wherein the cylindrical threaded rod is a ball screw and the carriage includes a nut fixed to the carriage to prevent the nut from rotating such that, when the ball screw is rotated, the nut is slid along the ball screw to displace the carriage linearly.
16. The method of claim 14 , wherein the proximal end of the forward wing is pivotally attached to a pivot member such that the forward wing does not move linearly with the aft wing.
17. The method of claim 16 , wherein the actuator is a motor mounted to the pivot member on a side of the pivot member opposite to the carriage, and the pivot member includes a hole through which the cylindrical threaded rod is positioned to communicate with the motor and the carriage.
18. The method of claim 13 , wherein, when the wing is in the closed position, the forward wing and the aft wing are parallel to each other.
19. The method of claim 13 , wherein the projectile is an artillery round, a missile, or a mortar.