Vehicle for Aerial Delivery of Fire Retardant

• US 20100065288A1
• Filed: 09/12/2008
• Published: 03/18/2010
• Est. Priority Date: 09/12/2008
• Status: Active Grant

• Current Assignee: Lonestar Inventions LP
• Original Assignee: Lonestar Inventions LP
• Inventors: Akcasu, Osman Ersed
• Granted Patent: US 7,975,774 B2
• Time in Patent Office: Days
• US Class Current: 169/53
• CPC Class Codes: A62C 3/025 Fire extinguishing bombs; Projectiles and launchers therefor launching apparatus for projectiles, missiles or torpedoes in general F41F1/00, F41F3/00, F41F7/00
• CPC Class Codes: A62C 99/009 Methods or equipment not provided for in groups A62C99/0009 - A62C99/0081
• CPC Class Codes: B64D 1/16 Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting jettisoning fuel B64D37/26
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 2201/104 using satellite radio beacon positioning systems, e.g. GPS
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: F41G 7/30 Command link guidance systems homing F41G7/2206
• CPC Class Codes: F41G 7/346 using global navigation satellite systems, e.g. GPS, GALILEO, GLONASS
• CPC Class Codes: F41G 7/36 using inertial references
• CPC Class Codes: F42B 12/36 for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
• CPC Class Codes: F42B 12/50 by dispersion
• CPC Class Codes: F42B 15/105 Air torpedoes, e.g. projectiles with or without propulsion, provided with supporting air foil surfaces

Abstract

A guided fire-retardant-containing bomb comprises a container with retractable wings, tail and elevators having the form factor of a conventional release vehicle, where the control surfaces are coupled via a controller to a GPS with inertial guidance control and an ability to receive external instructions, and a charge core to disintegrate and disperse the fire retardant or water.

Claims

1. A guided fire-retardant-containing delivery vehicle for release from an aircraft comprising:

a container having a form factor approximating a conventional air-released vehicle;

retractable wings, tail and elevators pivotally attached to said container and having movable control surfaces;

a core charge for disintegrating said vehicle; and

a control system, said control system including an internal servo controller, a GPS unit, an inertial navigation unit, and a point-to-multipoint-capable two-way communication unit,

wherein the communication unit is configured to receive external instructions and wherein the internal servo controller is coupled to the movable control surfaces, to the GPS unit and to the inertial guidance unit, said internal servo controller being operative to process said external instructions, input from said GPS unit, and input from said internal guidance unit to provide operational commands to said control surfaces in order to guide said delivery vehicle according to a predetermined trajectory to a target, and to detonate the charge core at a predetermined height to disintegrate and disperse the fire retardant.

2. The delivery vehicle according to claim 1 wherein

said retractable wings have a chord length less than the chord length of said container, said wings when fully deployed being substantially normal to said container,

each said retractable wing comprising:

an airfoil having a trailing edge, a leading edge, a top surface and a bottom surface, said trailing edge being substantially parallel to said leading edge, said top surface defined by a convex profile between said leading edge and said trailing edge, said bottom surface having a profile between said leading edge and said trailing edge with first section and a second section, said first section defined by a concave profile and said second section forming a surface with a relatively upward taper and lesser angle of attack as compared with said first section such that said airfoil promotes a soft stall characteristic of said vehicle in order to maximize gliding flight maneuverability in a turbulent atmosphere.

3. The delivery vehicle according to claim 2 wherein said retractable wings are pivotably attached to said container at a point behind the center of mass of a filled container in order to simplify requirements of said control system.

4. The delivery vehicle according to claim 3 wherein said container comprises a nose section, a midsection and a tail section, said container when loaded having a density in said tail section that is one-seventh of density in said mid-section and one-tenth of density in said nose section.

5. The delivery vehicle according to claim 2 wherein said airfoil approximates a type FX 61-184 wing.

6. The delivery vehicle according to claim 5 wherein said container approximates a type NACA 00025 airfoil.

7. The delivery vehicle according to claim 6 wherein said tail assembly approximates a type NACA 00025 0009 tail upon deployment.

8. The delivery vehicle according to claim 7 wherein said retractable wings are pivotably attached to said container at a point behind the center of mass of a filled container in order to simplify requirements of said control system.

9. The delivery vehicle according to claim 1 wherein said retractable wings are pivotably attached to said container at a point behind the center of mass of a filled container in order to simplify requirements of said control system.

10. The delivery vehicle according to claim 3 wherein said container comprises a nose section, a midsection and a tail section, said container when loaded having a density in said tail section that is one-seventh of density in said mid-section and one-tenth of density in said nose section.