Precision aerial delivery of payloads

• US 20070018033A1
• Filed: 03/22/2006
• Published: 01/25/2007
• Est. Priority Date: 03/22/2005
• Status: Abandoned Application

• Current Assignee: KaZak Composites, Incorporated (Kibbutz Sasa)
• Original Assignee: KaZak Composites, Incorporated (Kibbutz Sasa)
• Inventors: Maass, David, Gravelle, Nathan, Fanucci, Jerome
• Application Number:
  US11/386,465
• Publication Number:
  US 20070018033A1
• Time in Patent Office: Days
• US Class Current: 244/3.270
• CPC Class Codes: F42B 10/143 Lattice or grid fins
• CPC Class Codes: F42B 12/625 a single submissile arranged in a carrier missile for being launched or accelerated coaxially; Coaxial tandem arrangement of missiles which are active in the target one after the other with shaped or hollow charges F42B12/16
• CPC Class Codes: F42B 15/22 Missiles having a trajectory finishing below water surface having additional propulsion means for movement through water F42B17/00

Abstract

An aerial deliver system mounts a payload to an air delivery vehicle for aerial deployment by air into water from a location remote from the target region. The air delivery vehicle includes deployable wings and tail fins for gliding or powered flight to a target region. A release mechanism between the air delivery vehicle and the payload provides a clean separation between the two.

Claims

1. An aerial delivery system comprising:

An air delivery vehicle and a payload releasably attached to the air delivery vehicle;

the air delivery vehicle comprising a fuselage;

a pair of wings pivotably mounted to the fuselage for movement from a stowed position against the fuselage to a deployed position extending from the fuselage;

a plurality of tail fins pivotably mounted to the fuselage aft of the wings for movement from a stowed position against the fuselage to a deployed position extending from the fuselage; and

a release mechanism between the air delivery vehicle and the payload.

2. The system of claim 1, wherein the release mechanism comprises a biasing mechanism disposed between the air delivery vehicle and the payload.

3. The system of claim 2, wherein the biasing mechanism comprises a compression spring.

4. The system of claim 1, wherein the release mechanism comprises an air bag assembly disposed between the air delivery vehicle and the payload.

5. The system of claim 4, wherein the release mechanism further comprises a source of gas to inflate an air bag of the air bag assembly.

6. The system of claim 1, wherein the wings are stowed in slots in sides of the fuselage in the stowed position.

7. The system of claim 1, wherein the wings are stowed in slots along a center line of the fuselage in the stowed position.

8. The system of claim 1, wherein the wings are stowed in slots in the fuselage, one slot above a center line of the fuselage, another slot below the center line of the fuselage.

9. The system of claim 1, further comprising a wing deployment mechanism biased to move the wings to the deployed position.

10. The system of claim 1, wherein the wings have an airfoil profile.

11. The system of claim 1, wherein the tail fins are further pivotably mounted for rotation about an axis extending radially from the fuselage.

12. The system of claim 1, wherein the tail fins comprise lattice fins.

13. The system of claim 1, further comprising an actuation system to pivot the tail fins about their associated radially extending axes to effect pitch, yaw, and roll control of the air delivery vehicle during flight.

14. The system of claim 13, wherein the actuation system comprises an actuator associated with each tail fin and connected to the associated tail fin with a linkage mechanism.

15. The system of claim 1, further comprising an autopilot programmable to follow a predetermined flight plan.

16. The system of claim 15, wherein the autopilot further includes a global position system receiver.

17. The system of claim 1, wherein the autopilot further includes a dynamic air pressure sensor for determining air speed, wherein the dynamic air pressure sensor is in communication with a dynamic pressure probe disposed on a surface of the air delivery vehicle extendable beyond a boundary layer.