Shoulder launched unmanned reconnaissance system

• US 6,119,976 A
• Filed: 01/27/1998
• Issued: 09/19/2000
• Est. Priority Date: 01/31/1997
• Status: Expired due to Fees

• Current Assignee: Michael E. Rogers
• Original Assignee: Michael E. Rogers
• Inventors: Rogers, Michael E.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/013,551
• Time in Patent Office: 966 Days
• Field of Search: 244/49, 244/13, 244/46, 244/124, 244/190, 244/3.27, 244/3.28, 244/3.29, 89/1.815, 89/1.816, 89/1.819
• US Class Current: 244/13
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 70/70 Launching or landing using catapults, tracks or rails launching from storage containers B64U70/50
• CPC Class Codes: B64U 80/60 by wearable objects, e.g. garments or helmets

Abstract

A shoulder launched unmanned reconnaissance system for providing overhead visual surveillance of remote targets is disclosed. The present system includes a reconnaissance air vehicle which may be fired from a portable launcher, accelerated to flight speed, and remotely controlled using a ground control system. The vehicle is flown to the target area to enable an onboard wide angle video system to transmit video images of the target by radio or fiber optics link to the ground control system for processing and display. The ground control system enables the reconnaissance vehicle to be flown to a recovery area and to descend in a stall mode after the flight is completed for maintenance prior to reuse. The air vehicle includes collapsible wings which are deployable after launch by a spring actuated mechanism. The fuselage of the air vehicle carries an onboard video camera, an electric motor, a battery, a global positioning system receiver, flight controls, and a data link system.

In an alternative embodiment, the fuselage of the air vehicle includes a storage bay with a rotary mechanism capable of deploying sensors for chemical and biological warfare agents or other dropable payloads such as dye markers for marking fleeing motor vehicles. The present system is capable of conducting overhead surveillance up to a range of approximately 10 kilometers.

Claims

1. An unmanned reconnaissance system for surveying a remote location, comprising:

a portable elongated launch cylinder having an internal cylindrical cavity therein;

a launch vehicle telescopically slidably disposable in said cavity;

means coacting between said launch cylinder and said launch vehicle for ejecting said launch vehicle from said cavity of said launch cylinder, said launch vehicle including an elongated fuselage having a front end and a rear end, collapsible propeller means operatively carried at said front end of said fuselage, power means for operating said propeller means to propel said launch vehicle after said launch vehicle is ejected from said launch cylinder, a pair of collapsible wings carried on said fuselage between said front end and said rear end, each of said wings comprising a rear spar rotatably connected at an inner end to an outboard portion of said rear end of said fuselage at a first pivotal connection, a front spar rotatably connected at an inner end to said fuselage at a longitudinally slidable second pivotal connection located transversely between said first pivotal connections, said second pivotal connection having a pre-launch position adjacent said first pivotal connection and a post-launch position toward said front end of said fuselage, first biasing means for longitudinally shifting said second pivotal connection, from said pre-launch position to said post-launch position, second biasing means for rotating said rear spar outwardly of said fuselage, a third pivotal connection rotatably connecting outer ends of said front spar and said rear spar whereby in said pre-launch condition said rear spar and said front spar are in overlapping relationship along said fuselage, a foldable lightweight material interconnecting said front spar and said rear spar and establishing an airfoil surface in said post-launch condition, fin means pivotally carried on a lower surface of said fuselage and biased downwardly from said fuselage in said post-launch condition, camera means carried on said fuselage for providing video signals regarding said remote location, and operator controlled transceiver means for controlling said propeller means for establishing a flight path for said vehicle toward said remote location and for receiving said video signals from said camera means.

2. The unmanned reconnaissance system as recited in claim 1 wherein elongated pivotally variable elevons are rotatable carried on the trailing edge or said rear spar for effecting pitch and roll control of said launch vehicle.

3. The unmanned reconnaissance system as recited in claim 2 wherein said elevons are controlled by electromechanical servos carried on said fuselage.

4. The unmanned reconnaissance system as recited in claim 3 wherein said fuselage includes a storage bay for carrying a payload.

5. The unmanned reconnaissance system as recited in claim 4 wherein said payload comprises sensors for chemical and biological agents.

6. The unmanned reconnaissance system as recited in claim 5 wherein said payload comprises ground sensor packages and dye markers for marking said remote location and means responsive to said operator controlled transceiver means for ejecting said payload from said storage bay.

7. The unmanned reconnaissance system as recited in claim 3 wherein said means coacting between said launch cylinder and said launch vehicle is a pneumatic/hydraulic.

8. The unmanned reconnaissance system as recited in claim 3 wherein said means coacting between said launch cylinder and said launch vehicle is a pyrotechnic device.

9. The unmanned reconnaissance system as recited in claim 3 wherein said camera means includes color and black and white cameras for increased low-light capability.

10. The unmanned reconnaissance system as recited in claim 3 wherein said front spar is positioned transverse to said fuselage in said post-launch condition.

11. The unmanned reconnaissance system as recited in claim 3 wherein said propeller means are operatively connected to an electric motor.

12. The unmanned reconnaissance system as recited in claim 11 wherein said electric motor is powered by battery means removably carried in said fuselage.

13. An unmanned launch vehicle for surveying a remote location, comprising:

an elongated fuselage having a longitudinal axis;

propeller means operatively carried at a forward end of said fuselage;

power means for operating said propeller means to propel said launch toward said remote location, foldable wing means carried on said fuselage having a first spar rotatably connected at an inner end to an outboard portion of the end of said fuselage at a first pivotal connection;

a second spar rotatably connected at an inner end to said fuselage at a second pivotal connection longitudinally slidable with respect to said longitudinal axis, said second pivotal connection having a pre-launch position adjacent said first pivotal connection and a post-launch position remote therefrom;

first biasing means for longitudinally shifting said second pivotal connection from said pre-launch position to said post-launch position;

second biasing means for rotating said first spar outwardly of said fuselage, a third pivotal connection rotatably connecting outer ends of said first spar and said second spar whereby in said pre-launch condition said first spar and said second spar are in spaced relationship along the sides of said fuselage and in said post-launch condition said first spar, said second spar and said fuselage define a generally triangular shape; and

a foldable lightweight material interconnecting said spars and establishing an airfoil surface in said post-launch condition.