Remote controlled aerial reconnaissance vehicle

• US 9,527,596 B1
• Filed: 05/19/2015
• Issued: 12/27/2016
• Est. Priority Date: 03/01/2011
• Status: Active Grant

• Current Assignee: Richard D. Adams
• Original Assignee: Richard D. Adams
• Inventors: Adams, Richard D.
• Primary Examiner(s): Xavier, Valentina
• Application Number:
  US14/716,785
• Time in Patent Office: 588 Days
• Field of Search: 244/3.1, 244/3.14, 244/147, 244/152, 244/138.R, 244/142, 244/137.1, 244/139, 244/145, 244/190
• US Class Current: 1/1
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/50 Glider-type UAVs, e.g. with parachute, parasail or kite for landing B64U70/83
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 50/14 ducted or shrouded
• CPC Class Codes: B64U 70/20 for releasing or capturing UAVs in flight by another aircraft
• CPC Class Codes: B64U 70/83 using parachutes, balloons or the like
• CPC Class Codes: B64U 80/60 by wearable objects, e.g. garments or helmets

Abstract

A remotely controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propulsion source, and in another embodiment the power and control module is suspended from a point above a propulsion source. The UAV may be flown under a parachute and guided by remote control, or the control module (fuselage) may be released from the parachute and extendable fixed wings deployed to enable the UAV to be flown as a fixed wing vehicle.

Claims

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

a parachute having a plurality of control lines comprising at least one first control line attached to one portion of said parachute and at least one second control line attached to another portion of said parachute, said parachute configured to be steered by vertical movement of said at least one first control line and said at least one second control line,

a power and control module of an elongated, generally cylindrical configuration suspended in a vertical orientation below said parachute, said power and control module further comprising;

a receiver of control signals, for remotely controlling operation of said UAV,

a propulsion device responsive to said control signals and mounted at an upper portion of said power and control module, said propulsion device configurable in a first orientation while said power and control module is suspended in said vertical orientation by said parachute to enable said power and control module and said parachute to gain altitude and maintain altitude following launch of said power and control module and said parachute,

a control mechanism in said power and control module, said control mechanism attached to said at least one first control line and said at least one second control line, said control mechanism controlling direction and maneuverability of said power and control module and said parachute responsive to said control signals,

a selectively controllable release mechanism responsive to said control signals, for releasing said power and control module from said parachute,

extendable wings folded into said power and control module, said extendable wings deployed to an extended, fixed wing configuration for powered fixed wing flight after said power and control module is released from said parachute,

wherein when said power and control module is released from said parachute and said extendable wings are deployed, said propulsion device is reconfigured from said first orientation for parachute operation to a second orientation for powered fixed wing flight of said power and control module wherein speed, direction and altitude of said control module is controlled by said propulsion device in accordance with said control signals.

2. The UAV as set forth in claim 1 wherein said propulsion device is a ducted fan.

3. The UAV as set forth in claim 2 wherein said ducted fan is at an upper end of said power and control module when in said generally vertical orientation under said parachute.

4. The UAV as set forth in claim 3 wherein when said power and control module is in said generally vertical orientation under said parachute, said first orientation of ducted fan provides thrust generally perpendicular to a long axis of said power and control module, and when said power and control module is configured for fixed wing flight in said generally horizontal orientation, said second orientation of said ducted fan provides thrust generally along said long axis of said power and control module.

5. The UAV as set forth in claim 4 wherein said ducted fan is mounted for controlled rotation about said long axis of said power and control module, and further mounted for angular rotation with respect to said long axis of said power and control module, whereby thrust from said ducted fan is controllably vectored to control altitude and direction of said power and control module.

6. An unmanned aerial vehicle comprising:

a parachute having a plurality of control lines,

a cylindrical power and control module suspended vertically below said parachute, said cylindrical power and control module further comprising;

a receiver of control signals, for remotely controlling operation of said cylindrical power and control module and said parachute,

a propulsion device having directable thrust responsive to received said control signals,

at least one control mechanism attached to said plurality of control lines and responsive to said received control signals, for selectively controlling direction of said parachute and power and control module while said power and control module is suspended by said parachute,

a selectively controllable release mechanism responsive to said received control signals, for releasing said cylindrical power and control module from said parachute,

extendable wings attached to said cylindrical power and control module, said extendable wings deployed to an extended, fixed wing configuration for powered fixed wing flight after said cylindrical power and control module is released from said parachute,

whereby when said aerial vehicle is flying with said parachute, said propulsion device is oriented for powering and controlling altitude of said aerial vehicle and direction of said aerial vehicle is controlled by said control mechanism, and after said cylindrical power and control module is released from said parachute and said extendable wings are deployed, said propulsion device is reoriented to control both altitude and direction of said cylindrical power and control module.

7. An unmanned aerial vehicle as set forth in claim 6 wherein said propulsion device is located at an upper end of said cylindrical power and control module when said cylindrical power and control module is suspended from said parachute.

8. An unmanned aerial vehicle as set forth in claim 7 wherein said propulsion device is configured to provide thrust generally perpendicular to a long axis of said cylindrical power and control module when said cylindrical power and control module is suspended from said parachute.

9. An unmanned aerial vehicle as set forth in claim 8 wherein said propulsion device is reconfigured to provide thrust generally along a long axis of said cylindrical power and control module when said cylindrical power and control module is released from said parachute.

10. An unmanned aerial vehicle as set forth in claim 6 wherein said extendable wings are folded into said cylindrical power and control module, and unfolded and locked in position for said powered fixed wing flight.