Devices and methods for in flight transition VTOL/fixed wing hybrid aircraft structures and flight modes

• US 10,293,928 B2
• Filed: 01/06/2018
• Issued: 05/21/2019
• Est. Priority Date: 05/28/2015
• Status: Active Grant

• Current Assignee: Eugene H. Vetter, James W. Vetter, Paul A. Vetter
• Original Assignee: Eugene H. Vetter, James W. Vetter, Paul A. Vetter
• Inventors: Vetter, Eugene H, Vetter, James W, Vetter, Paul A
• Primary Examiner(s): Bonzell, Philip J
• Assistant Examiner(s): Kreiner, Michael B.
• Application Number:
  US15/863,884
• Publication Number:
  US 20180215464A1
• Time in Patent Office: 500 Days
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 27/24 with rotor blades fixed in flight to act as lifting surfaces
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings
• CPC Class Codes: B64C 27/30 with provision for reducing drag of inoperative rotor
• 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 30/24 Coaxial rotors
• CPC Class Codes: B64U 40/20 for in-flight adjustment of the base configuration
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans

Abstract

A hybrid VTOL/high speed aircraft may comprise systems and functions for in flight configuration changes from high lift helicopter or VTOL mode to fixed or swing-wing high speed aircraft mode to accommodate a variety of functions or missions.

Claims

1. A method, comprising:

providing an aircraft comprising counter-rotating and co-axially-disposed blades and at least one wing, the aircraft further comprising a lower swashplate coupled to pitch controls and an upper swashplate, controlled by the lower swashplate, attached to leading and trailing blade root edges of the co-axially-disposed blades;

rotating the blades;

flying the aircraft in a first configuration in which the rotating blades provide most of the lift to enable the aircraft to take off or to support the aircraft in sustained flight;

controlling pitch of the co-axially-disposed blades by acting on the leading and trailing blade root edges of the co-axially-disposed blades through the pitch controls;

during sustained flight, causing the blades to cease rotation and to at least partially overlap each other;

continuing to fly the aircraft in a second configuration in which the at least one wing provides most of the lift to support the aircraft in sustained flight.

2. The method of claim 1, further comprising stowing the at least partially overlapped blades during flight of the aircraft.

3. The method of claim 1, wherein causing comprises deploying the at least one wing from a first wing configuration to a second wing configuration.

4. A method, comprising:

providing an aircraft comprising counter-rotating and co-axially-disposed blade sets and at least one wing, the aircraft further comprising, for each blade set, a driven blade portion and a non-driven blade portion, a rotor hub comprising a driven hub portion coupled to the driven blade portion and a non-driven hub portion coupled to the non-driven blade portion;

flying the aircraft in a first configuration in which the at least one wing provides most or all of the lift necessary to support the aircraft in stable flight and in which, for each blade set, the driven hub portion is caused to rotate relative to the non-driven hub portion to cause the driven blade portion and the non-driven blade portion to at least partially overlap such that they do not provide substantial lift; and

during flight, deploying each blade set by rotating the driven hub portion relative to the non-driven hub portion to cause the non-driven blade portion to rotate to a position that is opposite the driven blade portion in a fully deployed position to reconfigure the aircraft in a second configuration in which the deployed blades sets provide most or all of the lift necessary to maintain the aircraft in sustained flight.

5. The method of claim 4, further comprising taking off with the aircraft in the first configuration.

6. The method of claim 4, further comprising taking off with the aircraft in the second configuration and, during flight, reconfiguring the aircraft to the first configuration.

7. The method of claim 4, further comprising reconfiguring the at least one wing from a first wing configuration to a second wing configuration at least during or after reconfiguring the aircraft in the second configuration.