Mission configurable aircraft having VTOL and biplane orientations

Patent metadata

Field	Value
Publication number	US-10618647-B2
Application number	US-201816154173-A
Country	US
Kind code	B2
Filing date	Oct 8, 2018
Priority date	Jul 1, 2016
Publication date	Apr 14, 2020
Grant date	Apr 14, 2020

Abstract

A mission configurable aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween. A two-dimensional distributed thrust array is attached to the airframe. The thrust array including a plurality of inboard propulsion assemblies coupled to first and second inboard nacelle stations of the first and second wings. The thrust array also includes a plurality of outboard propulsion assemblies coupled to first and second outboard nacelle stations of the first and second wings. A flight control system is operable to independently control each of the propulsion assemblies. A payload is coupled to the airframe. The inboard propulsion assemblies have a thrust type that is different from the thrust type of the outboard propulsion assemblies.

First claim

What is claimed is:

1. A mission configurable aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation, the aircraft comprising:
an airframe having first and second wings with first and second pylons extending therebetween, the first and second wings each having first and second inboard nacelle stations and first and second outboard nacelle stations;
a two-dimensional distributed thrust array attached to the airframe, the thrust array including a plurality of inboard propulsion assemblies and a plurality of outboard propulsion assemblies, the inboard propulsion assemblies coupled to the first and second inboard nacelle stations of the first and second wings, the outboard propulsion assemblies coupled to the first and second outboard nacelle stations of the first and second wings;
a flight control system coupled to the airframe and operable to independently control each of the propulsion assemblies; and
a payload coupled to the airframe;
wherein, the inboard propulsion assemblies have a first thrust type and the outboard propulsion assemblies have a second thrust type that is different from the first thrust type.

2. The aircraft as recited in claim 1 wherein each of the inboard propulsion assemblies generates a greater maximum thrust output than each of the outboard propulsion assemblies.

3. The aircraft as recited in claim 1 wherein each of the outboard propulsion assemblies generates a greater maximum thrust output than each of the inboard propulsion assemblies.

4. The aircraft as recited in claim 1 wherein the inboard propulsion assemblies are thrust vectoring propulsion assemblies and wherein the outboard propulsion assemblies are non thrust vectoring propulsion assemblies.

5. The aircraft as recited in claim 1 wherein the outboard propulsion assemblies are thrust vectoring propulsion assemblies and wherein the inboard propulsion assemblies are non thrust vectoring propulsion assemblies.

6. The aircraft as recited in claim 1 wherein the inboard propulsion assemblies are longitudinal thrust vectoring propulsion assemblies and wherein the outboard propulsion assemblies are lateral thrust vectoring propulsion assemblies.

7. The aircraft as recited in claim 6 wherein each of the inboard and outboard propulsion assemblies further comprises:
a nacelle;
a gimbal coupled to the nacelle and operable to tilt about a single axis; and
a propulsion system coupled to and operable to tilt with the gimbal, the propulsion system including an electric motor having an output drive and a rotor assembly having a plurality of rotor blades, the rotor assembly rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector;
wherein, actuation of the gimbal tilts the propulsion system relative to the nacelle to change the rotational plane of the rotor assembly relative to the nacelle, thereby controlling the direction of the thrust vector.

8. The aircraft as recited in claim 1 wherein the outboard propulsion assemblies are longitudinal thrust vectoring propulsion assemblies and wherein the inboard propulsion assemblies are lateral thrust vectoring propulsion assemblies.

9. The aircraft as recited in claim 8 wherein each of the inboard and outboard propulsion assemblies further comprises:
a nacelle;
a gimbal coupled to the nacelle and operable to tilt about a single axis; and
a propulsion system coupled to and operable to tilt with the gimbal, the propulsion system including an electric motor having an output drive and a rotor assembly having a plurality of rotor blades, the rotor assembly rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector;
wherein, actuation of the gimbal tilts the propulsion system relative to the nacelle to change the rotational plane of the rotor assembly relative to the nacelle, thereby controlling the direction of the thrust vector.

10. The aircraft as recited in claim 1 wherein the inboard propulsion assemblies are omnidirectional thrust vectoring propulsion assemblies and wherein the outboard propulsion assemblies are non thrust vectoring propulsion assemblies.

11. The aircraft as recited in claim 10 wherein each of the inboard propulsion assemblies further comprises:
a nacelle;
a gimbal coupled to the nacelle and operable to tilt about first and second orthogonal axes;
first and second actuators operable to tilt the gimbal respectively about the first and second axes; and
a propulsion system coupled to and operable to tilt with the gimbal, the propulsion system including an electric motor having an output drive and a rotor assembly having a plurality of rotor blades, the rotor assembly rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector;
wherein, actuation of the gimbal tilts the propulsion system relative to the nacelle to change the rotational plane of the rotor assembly relative to the nacelle, thereby controlling the direction of the thrust vector within a thrust vector cone.

12. The aircraft as recited in claim 1 wherein the outboard propulsion assemblies are omnidirectional thrust vectoring propulsion assemblies and wherein the inboard propulsion assemblies are non thrust vectoring propulsion assemblies.

13. The aircraft as recited in claim 12 wherein each of the outboard propulsion assemblies further comprises:
a nacelle;
a gimbal coupled to the nacelle and operable to tilt about first and second orthogonal axes;
first and second actuators operable to tilt the gimbal respectively about the first and second axes; and
a propulsion system coupled to and operable to tilt with the gimbal, the propulsion system including an electric motor having an output drive and a rotor assembly having a plurality of rotor blades, the rotor assembly rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector;
wherein, actuation of the gimbal tilts the propulsion system relative to the nacelle to change the rotational plane of the rotor assembly relative to the nacelle, thereby controlling the direction of the thrust vector within a thrust vector cone.

14. The aircraft as recited in claim 1 wherein the inboard propulsion assemblies are omnidirectional thrust vectoring propulsion assemblies and wherein the outboard propulsion assemblies are unidirectional thrust vectoring propulsion assemblies.

15. The aircraft as recited in claim 1 wherein the outboard propulsion assemblies are omnidirectional thrust vectoring propulsion assemblies and wherein the inboard propulsion assemblies are unidirectional thrust vectoring propulsion assemblies.

16. The aircraft as recited in claim 1 wherein each of the first and second inboard nacelle stations of the first and second wings is positioned opposite one of the first and second pylons.

17. The aircraft as recited in claim 1 wherein each of the first and second wings has first and second wing tips and wherein the first and second outboard nacelle stations of the first and second wings are respectively positioned at the first and second wing tips of the first and second wings.

18. The aircraft as recited in claim 1 wherein each of the first and second pylons includes an inboard nacelle station and wherein the plurality of inboard propulsion assemblies includes an inboard propulsion assembly coupled to each of the inboard nacelle stations of the first and second pylons.

Assignees

• Textron Innovations Inc

Inventors

• Mccullough John Richard
• Oldroyd Paul K

Classifications

• B64C29/00

  Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft (rotorcraft B64C27/00) · CPC title

• B64C2211/00

  Modular constructions of airplanes or helicopters · CPC title

• B64C11/46 Primary

  Arrangements of, or constructional features peculiar to, multiple propellers {(B64C11/306 takes precedence)} · CPC title

• B64C2201/108

  Operations & Transport · mapped topic

• B64C2201/088

  Operations & Transport · mapped topic