Multicopter with detachable wing

• US 9,623,969 B2
• Filed: 01/17/2015
• Issued: 04/18/2017
• Est. Priority Date: 01/17/2015
• Status: Expired due to Fees

• Current Assignee: Brian Dale Nelson
• Original Assignee: Brian Dale Nelson
• Inventors: Nelson, Brian Dale
• Primary Examiner(s): Badawi, Medhat
• Assistant Examiner(s): ANDONYAN, GEORGE A
• Application Number:
  US14/599,464
• Publication Number:
  US 20160272316A1
• Time in Patent Office: 822 Days
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/14 detachable
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An unmanned aerial vehicle (UAV) that can operate both as a conventional multicopter with no wing attached, or, it can operate as a winged multicopter. The detachable wing design used in the invention provides versatility without compromising performance; the wing attachment receptacles add no weight to the wingless multicopter configuration because they also function as the leg receptacles. In one embodiment, the base multicopter configuration is a quad-copter with four propeller drives. Four tubular receptacles, two forward and two aft, provide attachment points for the vertical struts of a detachable rectangular shaped wing, these vertical struts also function as the legs of the multicopter. The wing is fabricated using lightweight struts and rip stop nylon fabric which can be easily folded into a compact shape using quick release pins. In another embodiment, the wing is fabricated using a foam core. In both embodiments, the angle of the detachable wing can be adjusted to optimize lift and drag in the forward thrust, tilted position of the multicopter.

Claims

1. A quad-copter assembly of an unmanned aerial vehicle, comprising:

a plurality of propeller drives each comprising a propeller attached to an electric motor;

a rigid frame where said plurality of propeller drives is mounted;

said plurality of propeller drives where each drive further comprises a rotor axis that is oriented vertically;

said plurality of propeller drives provide vertical ascent and descent;

a wing mounted to said rigid frame wherein said wing is angled from horizontal when said vehicle is at rest and where said wing provides lift during forward motion of said unmanned aerial vehicle;

a plurality of vertically orientated spars securing the wing to the rigid frame;

where said plurality of vertically orientated spars each traverses through a respective motor mount;

wherein said plurality of vertically orientated spars include a plurality of front spars and a plurality of rear spars;

wherein the plurality of front spars and the plurality of rear spars are varied at different lengths such that the wing is positionable at an angle from horizontal;

where each of said plurality of vertically orientated spars also function as legs of the unmanned aerial vehicle;

said wing is detachable from said rigid frame; and

said quad-copter assembly of an unmanned aerial vehicle ascends, descends, hovers, and moves forward with or without the detachable wing.

2. The quad-copter assembly of the unmanned aerial vehicle of claim 1, wherein the detachable wing further comprises a plurality of rigid spars and a sheet sail.

3. The quad-copter assembly of the unmanned aerial vehicle of claim 2, wherein the sheet sail is comprised of a synthetic fabric material.

4. The quad-copter assembly of the unmanned aerial vehicle of claim 2, wherein said plurality of rigid spars each applies quick-release pins as a means of disassembly to form a more compact shape for storage and transportation.

5. The quad-copter assembly of the unmanned aerial vehicle of claim 1, wherein the said detachable wing comprises a rigid foam.