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US 12,515,791 B2Granted
Vertical take-off box wing aircraft
AssigneeOrb Aerospace, Inc.
InventorAlexander James Taylor
Life of this patent
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Abstract
An aircraft frame includes a fuselage, at least one boom and a wing structure including a first lifting surface having a first root portion located proximate the at least one boom and a first tip portion where at least a portion of the first tip portion is located forwardly from at least a portion of the first root portion, a second lifting surface having a second root portion located proximate the fuselage, and a second tip portion located spaced from the first tip portion where at least a portion of the second tip portion is located rearwardly from at least a portion of the second root portion, and a connector surface extending between the first and second tip portions.
Claims23
An aircraft, comprising:
- an aircraft structure, comprising:
- an aircraft body including a fuselage having a forward end and a rearward end;
- and
- a wing structure including a first lifting surface having a first root portion located proximate the aircraft body, a first tip portion located distally from the first root portion, a leading edge and a trailing edge;
- and
- a first propulsion arrangement positioned within the wing structure at the first root portion of the first lifting surface, wherein the first propulsion arrangement includes a plurality of propulsion devices substantially aligned with one another along a length of the aircraft structure, wherein at least one propulsion device of the plurality of propulsion devices is movable between a first configuration wherein a thrust vector of the at least one propulsion device is directed substantially vertically downward and a second configuration wherein the thrust vector of the at least one propulsion device is directed substantially horizontally rearward, and wherein the at least one propulsion device is positioned closer to the leading edge of the first lifting surface than the trailing edge.
3 more elements
An aircraft, comprising:
- an aircraft structure, comprising:
- an aircraft body including a fuselage having a forward end and a rearward end;
- and
- a wing structure including a first lifting surface having a first root portion located proximate the aircraft body, and a first tip portion located distally from the first root portion;
- a first propulsion arrangement positioned within the wing structure at the first root portion of the first lifting surface, wherein the first propulsion arrangement includes at least one propulsion device movable between a first configuration wherein a thrust vector of the at least one propulsion device is directed substantially vertically downward and a second configuration wherein the thrust vector of the at least one propulsion device is directed substantially horizontally rearward;
- and
- a second propulsion device arrangement located rearward of the fuselage, where a thrust vector of the second propulsion device is substantially collinear with a longitudinal axis of the fuselage.
4 more elements
An aircraft, comprising:
- an aircraft structure, comprising:
- an aircraft body including a fuselage having a forward end and a rearward end;
- and
- a wing structure including a first lifting surface having a first root portion located proximate the aircraft body, and a first tip portion located distally from the first root portion, a leading edge and a trailing edge;
- and
- a first propulsion arrangement coupled to the aircraft structure and including a plurality of propulsion devices substantially aligned with one another along a length of the aircraft structure, wherein at least two propulsion devices of the plurality of propulsion devices are movable between a first configuration wherein a thrust vector of each of the at least two propulsion devices is directed substantially vertically downward and a second configuration wherein the thrust vector of each of the at least two propulsion devices is directed substantially horizontally rearward and wherein the thrust vector of the plurality of propulsion devices is horizontally offset from a longitudinal axis of the fuselage, and wherein the at least two propulsion devices of the plurality of propulsion devices are located rearward of the leading edge and forward of the trailing edge;
- and
- a second propulsion arrangement coupled to the aircraft structure and having a thrust vector that is substantially collinear with the longitudinal axis of the fuselage.
5 more elements
Dependencies are inferred from the claim text.