Shroud geometry for unmanned aerial vehicles

• US 5,150,857 A
• Filed: 08/13/1991
• Issued: 09/29/1992
• Est. Priority Date: 08/13/1991
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Owen, Stephen J., Moffitt, Robert C.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US07/744,560
• Time in Patent Office: 413 Days
• Field of Search: 244/12.2, 244/23.6, 244/26, 244/17.23, 244/17.11, 244/34 A, 416/128, 416/129
• US Class Current: 244/12.2
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 20/65 Composite materials
• CPC Class Codes: B64U 20/70 Constructional aspects of the UAV body
• CPC Class Codes: B64U 30/24 Coaxial rotors
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 30/296 Rotors with variable spatial positions relative to the UAV body foldable or collapsible rotors B64U30/293
• CPC Class Codes: B64U 50/11 using internal combustion piston engines

Abstract

An unmanned aerial vehicle having a toroidal fuselage that surrounds a pair of coaxial, multi-bladed, counter-rotating rotors. The toroidal fuselage has an airfoil profile that is optimized to provide high hover efficiency and produce a pressure distribution that provide high lift forces. The airfoil profile is further optimized to counteract the undesirable nose-up pitching moments experienced by ducted rotary-type UAVs in forward translational flight.

Claims

1. An unmanned aerial vehicle, comprising:

a toroidal fuselage having a coaxial fuselage axis, said toroidal fuselage defining an inner duct flow channel; and

rotor assembly means for providing collective and cyclic pitch to control flight operations of said unmanned aerial vehicle, said rotor assembly means including a pair of multi-bladed, counter-rotating rotors coaxially mounted in said inner duct flow channel to provide high hover efficiency, said multi-bladed, counter-rotating rotors having an axis of rotation coaxial with said fuselage axis;

said toroidal fuselage having an outer aerodynamic surface optimized to retain said high hover efficiency provided by said pair of multi-bladed, counter-rotating rotors coaxially mounted in said inner duct flow channel, to produce a pressure distribution that provides high lift forces in translational flight, to counteract the undesirable nose-up pitching moment produced by lift generated by said rotor assembly means by reducing lift required from said rotor assembly means in translational flight, and to reduce the need for superimposed cyclic pitch for trimmed translational flight;

said outer aerodynamic surface including a leading edge and a trailing edge defined by the lower edge of said inner duct flow channel wherein said trailing edge lies in a plane above the plane of said leading edge.

2. The unmanned aerial vehicle of claim 1 wherein said outer aerodynamic surface of said toroidal fuselage has a chord defined by the orthogonal distance between said leading edge and the plane of said trailing edge, and wherein said outer aerodynamic surface is a highly cambered airfoil profile.

3. The unmanned aerial vehicle of claim 2 wherein said outer aerodynamic surface has a dorsal surface including a droop portion adjacent said leading edge, said droop portion comprising an arcuate surface projecting downwardly from said chord.

4. The unmanned aerial vehicle of claim 3 wherein said pair of multi-bladed, counter-rotating rotors have a predetermined radius, and wherein said arcuate surface comprising said droop portion is defined by a normalized radius of about 0.175 times said predetermined radius of said pair of multi-bladed, counter-rotating rotors.

5. The unmanned aerial vehicle of claim 1 wherein said outer aerodynamic surface further includes a ventral surface having a convex configuration with respect to said trailing edge, a lateral surface having a convex configuration with respect to said trailing edge, and a dorsal surface having a reflex camber defining the airfoil surface between said leading edge and said trailing edge.

6. The unmanned aerial vehicle of claim 5 wherein said reflex camber of said dorsal surface is defined by values of X/C and Y/C, with reference to said leading edge, as presented in Table II.

7. The unmanned aerial vehicle of claim 1 wherein said outer aerodynamic surface has an airfoil profile defined by values of X/C and Y/C, with respect to said leading edge, as presented in Table II.