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US 11,492,106 B2Granted
Vertical take-off and landing vehicle
AssigneeBlueflight Inc.
InventorsFrank Noppel, Gerrit Michael Becker
Life of this patent
Estimating the term…
Abstract
Methods, apparatus, systems and a vertical take-off and landing (VTOL) vehicle are provided. The VTOL vehicle includes: a fuselage having longitudinally a front section, a central section and a rear section; a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage; where each wing comprises at least one engine module, each of the engine modules being pivotally coupled to the wing and each engine module being independently controlled for transitioning between a vertical mode of flight and a horizontal mode of flight.
Claims12
A vertical take-off and landing, VTOL, vehicle comprising:
- a fuselage having longitudinally a front section, a central section, and a rear section;
- a first lifting surface comprising two rear wings respectively secured to opposite sides of the rear section of the fuselage, each respective rear wing comprising a respective cut-out along a respective trailing edge of the respective rear wing, each respective cut-out of the respective trailing edge mounted with a respective engine module, each respective engine module pivotable along a respective tilting axis perpendicular to the longitudinal axis of the fuselage and configured to be independently controlled to transition between a vertical mode of flight and a horizontal mode of flight;
- a second lifting surface comprising two front wings respectively secured to opposite sides of the front section of the fuselage, each respective front wing comprising a respective cut-out along a leading edge of the respective front wing, each respective cut-out of the respective leading edge mounted with a respective engine module, each respective engine module pivotable along a respective tilting axis perpendicular to the longitudinal axis of the fuselage and configured to be independently controlled to transition between a vertical mode of flight and a horizontal mode of flight,
- wherein a direction of a front opening of the respective cutout along the leading edge of the respective front wing is opposite a second direction of a rear opening of the respective cutout along the trailing edge of the respective rear wing.
1 more element
A vertical take-off and landing, VTOL, vehicle comprising:
- a fuselage having longitudinally a front section, a central section and a rear section;
- a first lifting surface comprising two rear wings respectively secured to opposite sides of the rear section of the fuselage;
- a second lifting surface comprising two front wings respectively secured to opposite sides of the front section of the fuselage;
- a first tiling mechanism connected to the first lifting surface utilizing at least one rear strut, the first tilting mechanism comprising two or more rear engine modules, each of the two or more rear engine modules pivotable about a tilting axis perpendicular to the longitudinal axis of the fuselage;
- and
- a second tilting mechanism connected to the second lifting surface utilizing at least one front strut, the second tilting mechanism comprising two or more front engine modules, each of the two or more front engine modules pivotable about a tilting axis perpendicular to the longitudinal axis of the fuselage,
- wherein the at least one rear strut extending longitudinally from a trailing edge of the two rear wings and the at least one front strut extending longitudinally, opposite from a longitudinal direction of the at least one rear strut, from a leading edge of the two front wings.
4 more elements
A vertical take-off and landing, VTOL, vehicle comprising:
- a fuselage having longitudinally a front section, a central section and a rear section;
- a first lifting surface comprising two rear wings respectively secured to opposite sides of the rear section of the fuselage;
- a second lifting surface comprising two front wings respectively secured to opposite sides of the front section of the fuselage;
- and
- at least one first support strut coupled to a rear portion of the rear section of the fuselage for supporting a first set of engine modules, the at least one first support strut extending longitudinally away from a respective trailing edge of a respective wing of the two rear wings;
- at least one second support strut coupled to a front portion of the front section of the fuselage for supporting a second set of engine modules, the at least one second support strut extending longitudinally away from a respective leading edge of a respective wing of the two front wings,
- wherein each of the engine modules of the sets of engine modules being pivotally coupled to corresponding support struts and each engine module configured to be independently controlled to transition between a vertical mode of flight and a horizontal mode of flight, and
- wherein the first lifting surface is positioned in a staggered spaced apart configuration with respect to the second lifting surface.
5 more elements
Dependencies are inferred from the claim text.