An Unmanned Aerial Vehicle

• US 20160272313A1
• Filed: 12/24/2013
• Published: 09/22/2016
• Est. Priority Date: 12/24/2013
• Status: Active Grant

• Current Assignee: ST Engineering Aerospace Ltd. (Singapore Technologies Engineering Limited)
• Original Assignee: Singapore Technologies Aerospace Limited (Government of Singapore)
• Inventors: Chan, Keen Ian
• Granted Patent: US 10,005,554 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: B64C 11/48 Units of two or more coaxial propellers
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/65 Composite materials
• CPC Class Codes: B64U 2101/20 for use as communications relays, e.g. high-altitude platforms
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/24 Coaxial rotors
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/23 with each propulsion means having an individual motor
• CPC Class Codes: B64U 50/32 generated by fuel cells
• CPC Class Codes: B64U 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20

Abstract

An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

Claims

1. An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, comprising:

an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point;

a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and

at least three sets of propellers, each set of propellers having at least two propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

2. The UAV as claimed in claim 1, wherein the at least two propellers in each set of propellers are arranged in a co-axial and contra-rotating configuration.

3. The UAV as claimed in claim 1, wherein two sets of propellers are mounted on the connecting structure, the two sets of propellers being separated by the elongated wing structure.

4. The UAV as claimed in claim 3, comprising three sets of propellers, wherein the remaining set of propellers is mounted at the second position, the second position being a position on the elongated axis.

5. The UAV as claimed in claim 1 wherein each propeller is independently drivable.

6. The UAV as claimed in claim 1 wherein each propeller is independently controllable.

7. The UAV as claimed in claim 1, further comprising a flight control module for controlling the at least three sets of propellers, the flight control module using the same set of controls for both vertical and horizontal flight modes.

8. The UAV as claimed in claim 7, wherein the flight control module is configured to control the at least three sets of propellers for autonomous transition of the UAV between vertical and horizontal flight modes, and vice versa, based on a predetermined range of angles-of-attack.

9. The UAV as claimed in claim 8, wherein the predetermined range of angles-of-attack are within a linear aerodynamic regime.

10. The UAV as claimed in claim 7, wherein the flight control module is configured to control the at least three sets of propellers for autonomous compensation to maintain flight when at least one propeller of the at least three sets of propellers malfunctions.

11. The UAV as claimed in claim 1, further comprising a fuselage disposed at the middle location on the elongated axis of the elongated wing structure.

12. The UAV as claimed in claim 1, wherein at least portions of respective trailing edges of the elongated wing structure and the connecting structure are disposed on the same plane for contacting a ground in a sitting position.

13. The UAV as claimed in claim 1, wherein the same flight controls are used for both vertical and horizontal flight modes.

14. The UAV as claimed in claim 13, wherein flight controls for roll, pitch and yaw in vertical and horizontal flight modes are decoupled.

15. The UAV as claimed in claim 1, configured for vertical take off and landing independent of a runway or other launch and recovery equipment.

16. A method for assembling an unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, the method comprising the steps of:

providing an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location substantially halfway along the elongated axis;

attaching a connecting structure to the elongated wing structure at a first position along the elongated axis offset from the middle location such that the connecting structure extends substantially perpendicularly from the elongated wing;

mounting at least two sets of propellers on the connecting structure; and

mounting at least one set of propellers at a second position offset from the middle location in the opposite direction away from the connecting structure,

wherein each set of propellers having at least two propellers.

17. The method as claimed in claim 16, wherein mounting at least one set of propellers comprises arranging the at least two propellers in a co-axial and contra-rotating configuration.

18. The method as claimed in claim 16, further comprising the step of attaching a fuselage in the middle location on the elongated axis of the elongated wing structure.

19. A kit for assembling an unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, the kit comprising:

an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point;

a connecting structure adapted to be attached to the wing structure at a first position along the elongated axis offset from the middle location of the elongated wing structure such that the connecting structure extends substantially perpendicularly from the elongated wing;

and

at least three sets of propellers, each set of propellers having at least two propellers, wherein at least two sets of propellers are adapted to be mounted on the connecting structure, and wherein at least one set of propellers is adapted to be mounted at a second position offset from the middle location in the opposite direction away from the connecting structure.