Auxiliary power system for rotorcraft with folding propeller arms and crumple zone loading gear

Patent metadata

Field	Value
Publication number	US-11059598-B2
Application number	US-201815994185-A
Country	US
Kind code	B2
Filing date	May 31, 2018
Priority date	Jun 1, 2017
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

A vertical take-off and loading (VTOL) rotary aircraft or helicopter has eight propellers in a quad propeller arm configuration where each propeller arm has two counter-rotating propellers. Folding propeller arms are designed to allow storage in a single car sized garage. Each propeller may be powered by a three-phase alternating current motor. The main power plant for the aircraft is a gas combustion engine that generates electricity. If the gas engine fails, a battery backup system will safely bring the aircraft down for a controlled landing. The direct current bus is redundant in that even with a gas combustion engine failure the direct current bus battery pack will safely bring down the aircraft. Various embodiments of this invention may also include a landing gear crumple zone designed to soften a hard landing.

First claim

We claim:

1. A non-fixed wing rotary aircraft comprising:
a fuselage;
a cockpit sized and adapted to accommodate a human pilot of the non-fixed wing rotary aircraft and having a pilot seat for the human pilot and a cockpit door for access to the cockpit by the human pilot;
at least one rotor coupled to the fuselage which lifts the fuselage from the ground upon rotation of the rotor and provides thrust to the aircraft;
an electric motor coupled to the rotor to rotate the rotor about a rotor axis of rotation;
an internal combustion engine;
a generator operably coupled to the internal combustion engine and the electric motor;
the at least one rotor arm having a fixed proximal portion and a collapsible distal portion joined to the fixed proximal portion by a hinge assembly;
the hinge assembly configured to allow the collapsible distal portion to pivot about a hinge pivot axis relative to the fixed primal portion and the hinge pivot axis being nonparallel to the rotor axis of rotation;
wherein the at least one rotor arm is collapsible from an operational extended position to a collapsed storage position external of the fuselage.

2. The rotary aircraft of claim 1 further comprising:
a landing gear adapted to crumple in an emergency landing situation to thereby provide protection to the fuselage.

3. The rotary aircraft of claim 2 wherein the landing gear further comprises:
a plurality of crumple zones each deforming in response to a different load on the landing gear during the emergency landing situation.

4. The rotary aircraft of claim 1 further comprising:
a battery electrically coupled to the motor and the internal combustion engine, the battery configured to power the at least one rotor during normal flight operation of the aircraft.

5. The rotary aircraft of claim 4 further comprising:
a converter coupled to the generator and the motor.

6. The rotary aircraft of claim 5 further comprising:
an inverter coupled to the converter and to the motor.

7. The rotary aircraft of claim 1 further comprising:
a plurality of rotors;
a plurality of motors each rotationally driving one of the plurality of rotors.

8. The rotary aircraft of claim 7 wherein a first set of the plurality of rotors rotate in an opposite direction of a second set of the plurality of rotors.

9. The rotary aircraft of claim 8 wherein an axis of rotation of each of the rotors of the first set of the plurality of rotors is coincident with an axis of rotation of one of the rotors of the second set of the plurality of rotors.

10. The rotary aircraft of claim 7 further comprising:
a plurality of rotor arms, each rotor arm having a distal end and a proximal end, the proximal end being mounted to the fuselage and at least one of the motors and at least one of the rotors being mounted proximate the distal end of each rotor arm.

11. The rotary aircraft of claim 10 wherein two of the plurality of rotors and two of the plurality of motors are mounted proximate the distal end of each rotor arm.

12. The rotary aircraft of claim 10 further comprising at least four rotor arms.

13. The rotary aircraft of claim 12 wherein a first set of the plurality of rotors rotate in an opposite direction of a second set of the plurality of rotors and an axis of rotation of each of the rotors of the first set of the plurality of rotors is coincident with an axis of rotation of one of the rotors of the second set of the plurality of rotors; and
each of the at least four rotor arms having one of the rotors of the first set and one of the rotors of the second set mounted proximate the distal end thereof.

14. The rotary aircraft of claim 10 wherein each of the rotor arms is spaced no more than ninety degrees from an adjacent rotor arm.

15. The rotary aircraft of claim 10 wherein each of the rotor arms of the plurality of rotor arms are collapsible from an operational extended position to a collapsed storage position external of the fuselage.

16. The rotary aircraft of claim 15 further comprising:
a landing gear adapted to crumple in an emergency landing situation to thereby provide protection to the fuselage.

17. A non-fixed wing rotary aircraft comprising:
a fuselage;
a cockpit sized and adapted to accommodate a human pilot of the non-fixed wing rotary aircraft and having a pilot seat for the human pilot and a cockpit door for access to the cockpit by the human pilot;
a plurality of at least four rotor arms, each rotor arm having a distal end and a proximal end, the proximal end of each of the plurality of rotor arms being mounted to the fuselage;
a plurality of at least eight rotors, each of the plurality of rotor arms having two of the plurality of rotors mounted to the distal end thereof, each rotor contributing to both lift and thrust to the aircraft;
wherein a first set of the plurality of rotors rotate in an opposite direction of a second set of the plurality of rotors;
wherein an axis of rotation of each of the rotors of the first set of the plurality of rotors is coincident with an axis of rotation of one of the rotors of the second set of the plurality of rotors;
a plurality of at least eight electric motors each coupled to one of the plurality of rotors;
a plurality of batteries each electrically coupled to one of the plurality of electric motors, the plurality of batteries configured to power the plurality of at least eight electric motors during normal flight operation of the aircraft;
an inverter coupled to the plurality of batteries;
a converter coupled to the inverter;
a generator coupled to the converter;
an internal combustion engine coupled to the generator to generate electrical energy to charge the plurality of batteries and thereby power the plurality of motors to rotate the plurality of rotors.

18. The rotary aircraft of claim 17 further comprising:
at least one of the rotor arms having a fixed proximal portion and a collapsible distal portion joined to the fixed proximal portion by a hinge assembly;
the hinge assembly configured to allow the collapsible distal portion to pivot about a hinge pivot axis relative to the fixed primal portion and the hinge pivot axis being nonparallel to the rotor axis of rotation;
wherein the at least one rotor arm is collapsible from an operational extended position to a collapsed storage position external of the fuselage.

Assignees

• Surefly Inc
• Moog Inc

Inventors

• Arkus Alan J
• Burns Stephen S
• Conners Patrick
• Wei Wei

Classifications

• B64D27/32

  within, or attached to, fuselages · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64D27/357

  using batteries · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64C1/063 Primary

  Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms · CPC title