# US 2014/0197280 A1 · Delta Wing Unmanned Aerial Vehicle (UAV) and Method of Manufacture of the Same

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- Number: US 2014/0197280 A1
- Document ID: US20140197280A1
- Status: Published application
- Kind: A1
- Application number: 13/572,877
- Filed: 2012-08-13
- Published: 2014-07-17
- Earliest claimed: 2011-11-22
- Inventors: Donald Earl Smith; Mark D. Herres
- Web page: https://patentgrep.com/patent/US20140197280A1

## CPC

- B64C 3/10: Shape of wings
- B64F 1/027: {using net or mesh}
- B64F 1/0297: {adjustable to align with aircraft trajectory}
- B64F 1/06: using catapults
- B64U 70/30: for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net
- B64U 70/70: Launching or landing using catapults, tracks or rails (launching from storage containers B64U70/50)
- G06K 7/10366: {the interrogation device being adapted for miscellaneous applications}
- B64U 2201/20: Remote controls
- B64C: AEROPLANES; HELICOPTERS
- B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- G06K: GRAPHICAL DATA READING (image or video recognition or understanding G06V); PRESENTATION OF DATA; RECORD CARRIERS; HANDLING RECORD CARRIERS

## Abstract

This disclosure pertains to the field of small-unmanned aerial vehicles (UAVs). The delta wing vehicle consists of an isosceles triangular shaped lifting body milled from Styrofoam. The longitudinal axis is approximately 65% of the lateral axis. The horizontal wing projections, or tiplets, are attached to the main lifting body at an approximately 10 degree upward angle from horizontal, have a 30 degree sweep back leading edge, and each one comprises 5% of the total wing area. The airfoil is a rhomboid or diamond shape. The chord is swept back at a 45-degree angle from the longitudinal centerline. The airfoil is symmetrical about the longitudinal center. The aircraft is controlled by a set of combined elevator/aileron surfaces (elevons) at the rear as well as a vertical stabilizer/rudder combination. This resulting lightweight UAV can make flat (unbanked) unbanked turns, fly in high winds, and has superior flexibility in payload capability.

## Claims

### Claim 1

A lightweight unmanned aerial vehicle comprised of a Styrofoam scalable delta wing lifting body with attached Styrofoam horizontal wing projections, or tiplets, creating a dihedral surface and diamond/rhomboid-shaped symmetrical airfoil controlled with a rudder/vertical stabilizer assembly and a set of rear combined elevator/aileron surfaces (elevons), in which the vehicle's longitudinal axis is approximately sixty-five percent (65%) of the lateral axis and the tiplets are attached to the main lifting body at an approximately 10 degree upward angle from horizontal and have a 30 degree sweep back leading edge, and each tiplet comprises approximately 5% of the total wing area.

### Claim 2 (depends on 1)

A method of manufacture in which body, airfoil and tiplets of the lightweight unmanned aerial vehicle of claim 1 are milled from a Styrofoam block, and the rudder/vertical stabilizer and elevons are attached to the lifting body.

### Claim 3 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 on which a carbon fiber skin covering is applied.

### Claim 4 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 on which a reinforced packing tape covering is applied.

### Claim 5 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 on which a solar power panel skin covering is applied.

### Claim 6 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 in which a radio remote control device is installed.

### Claim 7 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 in which an autopilot control device is installed.

### Claim 8 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 in which the lifting body and tiplets are composed of expanded polystyrene plastic.

### Claim 9 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 in which the tiplets, wings, fuselage and rudder are detachable for rapid assembly and disassembly.

### Claim 10 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 in which a camera is installed.

### Claim 11 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1 in which an RFID transmitter and sensors are installed.

### Claim 12 (depends on 1)

The lightweight unmanned aerial vehicle of claim 1, in which the chord is swept back at a 45-degree angle from the longitudinal centerline.