Delta Wing Unmanned Aerial Vehicle (UAV) and Method of Manufacture of the Same

• US 20140197280A1
• Filed: 08/13/2012
• Published: 07/17/2014
• Est. Priority Date: 11/22/2011
• Status: Abandoned Application

• Current Assignee: Donald Earl Smith, Mark D. Herres
• Original Assignee: Donald Earl Smith, Mark D. Herres
• Inventors: Smith, Donald Earl, Herres, Mark D.
• Application Number:
  US13/572,877
• Publication Number:
  US 20140197280A1
• Time in Patent Office: Days
• US Class Current: 244/35.R
• CPC Class Codes: B64C 3/10 Shape of wings
• CPC Class Codes: B64F 1/027 using net or mesh
• CPC Class Codes: B64F 1/0297 adjustable to align with aircraft trajectory
• CPC Class Codes: B64F 1/04 for launching aircraft
• CPC Class Codes: B64F 1/06 using catapults
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 70/30 for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net
• CPC Class Codes: B64U 70/70 Launching or landing using catapults, tracks or rails launching from storage containers B64U70/50
• CPC Class Codes: G06K 7/10366 the interrogation device being adapted for miscellaneous applications

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

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.

2. 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.

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

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

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

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

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

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

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

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

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

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