Short takeoff and landing aircraft

• US 9,771,163 B2
• Filed: 03/31/2014
• Issued: 09/26/2017
• Est. Priority Date: 12/31/2013
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Ouellette, Rich P.
• Primary Examiner(s): Bonzell, Philip J
• Assistant Examiner(s): KREINER, MICHAEL B
• Application Number:
  US14/231,003
• Publication Number:
  US 20150183522A1
• Time in Patent Office: 1,275 Days
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: B64F 1/04 for launching aircraft
• CPC Class Codes: B64F 3/02 with means for supplying electricity to aircraft during flight
• CPC Class Codes: B64U 50/34 In-flight charging photovoltaics B64U50/31
• CPC Class Codes: B64U 70/00 Launching, take-off or landing arrangements
• CPC Class Codes: B64U 70/92 Portable platforms
• CPC Class Codes: Y10S 903/902 Prime movers comprising electrical and internal combustion motors

Abstract

Short takeoff and landing aircraft are disclosed. An example fixed wing aircraft includes a primary power source to provide power to a propulsion unit, a secondary power source to provide power to the propulsion unit, and a detachable power coupling to transfer power to the secondary power source from a source external to the fixed wing aircraft during takeoff.

Claims

1. A fixed wing aircraft, comprising:

a propulsion unit;

a primary power source configured to provide mechanical power to the propulsion unit;

a secondary power source configured to provide mechanical power to the propulsion unit; and

a detachable power coupling configured to transfer electrical power to the secondary power source from a source external to the fixed wing aircraft during takeoff, wherein the detachable power coupling is coupled to the source external to the aircraft via a cable, wherein the detachable power coupling is detached from the aircraft when the aircraft is a distance away from the source external to the aircraft that exceeds a length of the cable.

2. A fixed wing aircraft as defined in claim 1, wherein the secondary power source comprises an electric motor.

3. A fixed wing aircraft as defined in claim 2, wherein the primary power source is configured to provide power to the electric motor following takeoff, the electric motor is configured to generate and provide electrical power to an aircraft subsystem when receiving power from the primary power source.

4. A fixed wing aircraft as defined in claim 1, wherein the detachable power coupling comprises at least one of an electrical plug, a breakaway coupling, or a magnetic induction coil.

5. A fixed wing aircraft as defined in claim 1, wherein the primary power source comprises two or more fuel-based engines.

6. A fixed wing aircraft as defined in claim 5, wherein the fuel-based engines are cross-shafted to the secondary power source.

7. A fixed wing aircraft as defined in claim 5, wherein the primary power source further comprises an energy storage device to store electrical energy and to provide the electrical energy to the propulsion unit.

8. A fixed wing aircraft as defined in claim 5, wherein the primary power source is configured to disable at least one of the fuel-based engines during at least one of cruise stage or a loiter stage of flight.

9. A fixed wing aircraft as defined in claim 1, wherein the primary power source is capable of providing sufficient power for a cruise stage of flight but is not capable of providing sufficient power for a takeoff stage of flight.

10. A method to launch a fixed wing aircraft from a short takeoff platform, the method comprising:

providing a fixed wing aircraft having an electrical connection configured to provide power to a propulsion unit of the fixed wing aircraft;

connecting the electrical connection of the fixed wing aircraft to an electrical power source associated with a takeoff platform; and

providing electrical power to the fixed wing aircraft via the electrical connection during launch of the aircraft from the takeoff platform, wherein the electrical connection is connected to the electrical power source associated with the takeoff platform via a cable, wherein the cable is detached from the aircraft when the aircraft is a distance away from the electrical power source that exceeds a length of the cable.

11. A method as defined in claim 10, further comprising recovering the electrical connection after launch of the aircraft.

12. A method as defined in claim 10, further comprising configuring the electrical power source to provide power to the takeoff platform.

13. A method as defined in claim 10, wherein connecting the electrical connection of the fixed wing aircraft to an electrical power source comprises plugging the cable into the electrical connection of the fixed wing aircraft, the electrical connection comprising an electrical plug.

14. A method as defined in claim 10, wherein a primary power source of the fixed wing aircraft is capable of providing sufficient power for a cruise stage of flight but is not capable of providing sufficient power for a takeoff stage of flight.