Quad Rotor Aircraft With Fixed Wing And Variable Tail Surfaces

• US 20170113795A1
• Filed: 07/14/2016
• Published: 04/27/2017
• Est. Priority Date: 07/14/2015
• Status: Active Grant

• Current Assignee: Jeremy Duque
• Original Assignee: Jeremy Duque
• Inventors: Duque, Jeremy
• Granted Patent: US 10,343,774 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/40 Empennages, e.g. V-tails foldable or collapsible UAVs B64U20/50
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20

Abstract

An aircraft with four rotors, a fixed wing, and an adjustable v-tail to allow for both vertical take-off and landing and the capability to fly in straight and level flight. The angle of each rotor and engine, with respect to the airfoil surfaces to which they are attached, is adjustable, allowing for thrust to be directed either downwards, allowing the craft to hover, or backwards, allowing the aircraft to travel horizontally while lift is provided and controlled by the wing and v-tail.

Claims

1. An aircraft comprising:

a wing attached to a fuselage;

an empennage having two tail surfaces;

a forward source of thrust mounted to the wing; and

a rear source of thrust mounted to at least one of the two tail surfaces.

2. The aircraft of claim 1 wherein the two tail surfaces extend horizontally at an angle substantially parallel to the wing when the aircraft is in a vertical propulsion configuration, and fold into a v-tail when the aircraft is in a horizontal propulsion configuration.

3. The aircraft of claim 2 wherein the two tail surfaces are equal in length and size.

4. The aircraft of claim 1 further comprising:

two forward sources of thrust mounted to the wing equidistant from a center of the fuselage, and

wherein the two forward sources of thrust direct thrust downwards in a vertical propulsion configuration and rotate substantially forward to direct propulsion towards a rear of the aircraft in a horizontal propulsion configuration.

5. The aircraft of claim 1 further comprising:

two rear sources of thrust mounted to one each of the two tail surfaces, and

wherein the two rear sources of thrust direct thrust downwards in a vertical propulsion configuration and rotate substantially forward to direct propulsion towards a rear of the aircraft in a horizontal propulsion configuration.

6. The aircraft of claim 1 further comprising:

a front end of the fuselage and a rear end of the fuselage, and

wherein the wing is mounted near the front end of the fuselage; and

the empennage is mounted near the rear end of the fuselage.

7. The aircraft of claim 1 further comprising:

a front end of the fuselage and a rear end of the fuselage, and

wherein the empennage is mounted near the front end of the fuselage; and

the wing is mounted near the rear end of the fuselage.

8. The aircraft of claim 1 wherein the wing folds along the chord length at a point beyond the forward source of thrust.

9. The aircraft of claim 1 further comprising:

a retractable portion in the wing under the forward source of thrust, and

wherein when the aircraft is in a vertical propulsion configuration the retractable portion retracts to allow air flow through an opening in the retractable portion.

10. The aircraft of claim 2 wherein an angle of the v-tail is adjustable during horizontal flight.

11. The aircraft of claim 4 further comprising:

two rear sources of thrust mounted to one each of the two tail surfaces,

wherein the two rear sources of thrust direct thrust downwards in a vertical propulsion configuration and rotate substantially forward to direct propulsion towards a rear of the aircraft in a horizontal propulsion configuration, and

wherein the two forward sources of thrust and two rear sources of thrust may rotate substantially simultaneously such that a transition from the vertical propulsion configuration to the horizontal propulsion configuration may be made while the aircraft is in flight.