UNMANNED AERIAL VEHICLE LAUNCH SYSTEM

• US 20160137312A1
• Filed: 05/06/2014
• Published: 05/19/2016
• Est. Priority Date: 05/06/2014
• Status: Abandoned Application

• Current Assignee: Osterhout Design Group
• Original Assignee: Osterhout Design Group
• Inventors: Osterhout, Ralph F.
• Application Number:
  US14/271,028
• Publication Number:
  US 20160137312A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/293 Foldable or collapsible rotors or rotor supports
• CPC Class Codes: B64U 80/70 in containers B64U80/60 takes precedence
• CPC Class Codes: G02B 27/0172 characterised by optical features
• CPC Class Codes: G05D 1/0016 characterised by the operator's input device input arrangements for computing systems in general G06F3/00
• CPC Class Codes: G05D 1/0022 characterised by the communication link data switching networks in general H04L12/00
• CPC Class Codes: G05D 1/0038 by providing the operator with simple or augmented images from one or more cameras located onboard the vehicle, e.g. tele-operation images analyzed by a computer and used for automatic navigation G05D1/0246
• CPC Class Codes: G05D 1/0202 specially adapted to aircraft
• CPC Class Codes: G05D 1/102 specially adapted for vertical take-off of aircraft
• CPC Class Codes: H04L 12/00 Data switching networks interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units G06F13/00

Abstract

Aspects of the present invention relate to unmanned aerial vehicle launch technologies.

Claims

1. An unmanned aerial vehicle (UAV) launch system, comprising:

a. A retained propellant case adapted to be loaded into a grenade launcher and to be retained by the grenade launcher following launch of the UAV, comprising;

i. a propellant in a propellant cavity; and

ii. a gas pressure containment cavity;

wherein the propellant cavity further includes a vent connecting the propellant cavity and the pressure containment cavity;

iii. a piston arranged to move by a force caused by an increase in gas pressure in the gas pressure containment cavity resulting from a triggered propellant, the piston further arranged to move towards the UAV for a pre-determined distance, the piston further including a seal that substantially contains the increase in gas pressure in the gas pressure containment cavity as the piston moves to the pre-determined distance; and

b. A separable launch case adapted to be loaded into the grenade launcher, wherein the separable launch case is secured to the retained propellant case in a position such that the separable launch case is pushed by the piston as the piston moves towards the UVA, the separable launch case further comprising a UAV cavity adapted to hold the UVA in a launch position and to separate from the UAV in flight after launch.

2. An unmanned aerial vehicle (UAV) launch system, comprising:

a. A retained propellant case adapted to be loaded into a grenade launcher and to be retained by the grenade launcher following launch of the UAV, comprising;

i. a gas pressure containment cavity adapted to contain, for a period of time after launch of the UAV, substantially all of an expanding gas that is used to push the UAV out of the grenade launcher, the period of time used to suppress a sound that would result if the expanding gas expanded outside of the gas pressure cavity and into an uncontained environment;

b. A separable launch case adapted to be loaded into the grenade launcher, wherein the separable launch case is secured to the retained propellant case in a position such that the expanding gas causes the separable launch case to be projected from the grenade launcher, the separable launch case further comprising a UAV cavity adapted to hold the UVA in a launch position and to separate from the UAV in flight after launch.

3. The system of claim 2 wherein the grenade launcher comprises a 40 mm launcher.

4. The system of claim 2 wherein the UAV comprises a copter with counter rotating blades.

5. The system of claim 2 wherein the UAV is adapted to communicate with an HWC within a proximity of the UAV after the UAV is launched from a grenade launcher.

6. The system of claim 5 wherein the HWC is adapted to communicate with other HWC'"'"'s in an ad-hoc self healing network.

7. The system of claim 2 wherein the gas pressure containment cavity comprises a piston that substantial seals an expanding gas in the pressure containment cavity for at least a period of time to prevent a loud noise from the expanding gas.

8. The system of claim 2 wherein the UAV is flight controlled through a control command captured by a HWC.