Jetzero, Inc.

Blended Wing Aircraft, Inc.

Dzyne Technologies Incorporated

The Boeing Company

The Mitre Corporation

Swift Engineering, Inc.

Mcdonnell Douglas Corporation

Thomas & Betts International LLC

Mark Allan Page

Blaine Knight Rawdon

Brendan Kennelly

Jennifer Whitlock

Cristina Donastorg

Joshua B Long

Matthew Robert McCue

Myles Leonard Baker

Steen A Parl

Robert Anthony Godlasky

Jennifer Phillips Whitlock

Neil Wayne Roberts

John Winkler

Matthew W Wilks

Scott Zhao

Daniel Tran

Jay Fletcher Kempf

Daniel Sean Stuewe

Brent Tyler Scheneman

John Charles Vassberg

Daniel K Michaelis

Adrian Fazio

Raphael Diaz

Doug McLarty

Christopher John Page

Christian Durand

Bob Emerick

Michael Karl Kohl

Ewald Schuster

Tom Huschilt

Patrick Quincey Stout

Brian Kane

Jennifer P Whitlock

A landing gear apparatus for an aircraft including at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are in communication with one another.

Aircraft with outboard-stowed landing gear

A system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

Systems and methods for modular aircraft

Technologies for providing emergency egress routes for a blended wing body aircraft are described herein. In some examples, the emergency egress routes are through a side cabin bulkhead and aft one or more cargo holds. In some examples, the blended wing body aircraft has wings that are high geometry wings. In these examples, the emergency egress routes do not penetrate an aft spar, reducing weight and increasing the integrity of the aircraft.

Emergency egress in a blended wing body aircraft

Systems and methods for mechanically rotating an aircraft about its center-of-gravity (C) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive angle of attack for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

Tilting landing gear systems and methods

A composite assembly for a blended wing body aircraft, the composite assembly comprising: a first assembly comprising a first molded part, wherein the first molded part comprises a first plurality of fibers, the first molded part partially infused with a first resin, a second assembly oriented relative to the first assembly, the second assembly comprising a second molded part wherein the second molded part comprises a second plurality of fibers, the second molded part partially infused with a second resin, and a joining region, the joining region comprising at least a portion of first plurality of fibers and at least a portion of second plurality of fibers, the at least a portion of first plurality of fibers and the at least a portion of second plurality of fibers substantially adjacent and infused with a third resin.

Aircraft with composite assembly and a method of manufacture

A modular blended wing body (BWB) aircraft includes common components containing a nose structure having a left aft edge and a right aft edge intersecting on a centerline of the BWB on one end and intersecting on a leading edge of the BWB on another end, and two wing structures attached to the nose structure, wherein the at least two rear structures includes a left-wing structure arranged on the left side of the centerline, wherein the left-wing structure includes a left forward edge, and a right-wing structure arranged on the right side of the centerline, wherein the right-wing structure includes a right forward edge, and wherein the left-wing structure and the right-wing structure are laterally symmetrical to the centerline, and wherein there is no clear demarcation between the at least two wing structures and the nose structure of the plurality of common components of the BWB aircraft.

Modular blended wing body (BWB) aircraft and method of manufacture

An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.

Apparatus for ingesting boundary layer flow for an aircraft

A coupled landing gear apparatus for an aircraft including at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are in communication with one another.

Coupled landing gear and methods of use

A system for manufacturing modular aircraft includes at least at least a common tooling component, including at least one or more of a first component in a shape of a nose and a second component in a shape of a wing. The system further including at least a modular tooling component in a shape of a main body, wherein connecting the at least a common tooling components to the at least modular component forms a mold in a shape of at least a portion of a blended wing body (BWB) aircraft with no clear demarcation between the shape of the wing and a shape of a main body along an edge of the shape of the BWB.

Systems and methods for manufacture of a modular aircraft

A freighter aircraft for long-distance travel, the freighter aircraft comprising a blended wing body having a main body, a transition, and wings with no clear demarcation between the wings and the main body along a leading edge of the freighter aircraft, at least a propulsor, the at least a propulsor attached to a portion of the main body and configured to propel the freighter aircraft through air, a fuel storage located within the blended wing body, the fuel storage having a fuel capacity wherein the fuel capacity is configured for long-range flight, and a cargo bay located within the main body; the cargo bay configured to have a freighter capacity, wherein freighter aircraft is a long-range aircraft, the freighter aircraft including a ton-miles per sortie between 135,000 and 450,000.

Long range freighter aircraft

A composite assembly for an aircraft, the composite assembly including a first carbon fiber material structured for a portion of an outer skin surface of an aircraft, a second carbon fiber material stitched to the first carbon fiber material, wherein the second carbon fiber material is structured for a structural component of the aircraft, and wherein the stitching is configured to bind the first carbon fiber material and the second carbon fiber material, and wherein the aircraft further includes a single deck, wherein a cargo compartment and a passenger compartment are located on or above the single deck.

Aircraft with carbon fiber material and a method of manufacture

Aircraft

Described herein is a blended wing body aircraft. In some embodiments, a blended wing body aircraft may include a passenger cabin separated into two or more cabin bays. In some embodiments, two or more cabin bays may be separated by a structural element that runs through the passenger cabin along the longitudinal axis of the aircraft.

Blended wing body aircraft

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

Drag recovery scheme using boundary layer ingestion

Systems and methods for mechanically rotating an aircraft about its center-of-gravity (C) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

Growing community of inventors

Cypress, CA, United States of America

Mark Allan Page