The Boeing Company

Eric J Schulze

Roger W Lacy

Joshua B Jarvis

Douglas Reinhard Ludin

Matthew S Stauffer

Michael J Duffy

Brandon R Brown

David H Mason

Justin Fowler Rogers

Eric Hathaway

Brian Charles Gray

David M Neely

Douglas Mikita

Corey Seidel

Akif O Bolukbasi

Mohammad Barakatain

Mohssen Mohaghegh

Example methods and systems for coupling and controlling transport of cargo using an unmanned aerial vehicle (UAV) are provided, comprising coupling at least one electronically-controllable attachment device positioned on an underside of the UAV to a sling cable, the sling cable being secured to the cargo. The UAV flies to a predetermined area above the cargo, and responsive to determining that the UAV is positioned within the predetermined area, the UAV elevates above the initial operating height to lift the cargo and navigates to a target location.

Unmanned aerial vehicle and cargo attachment system for the unmanned aerial vehicle

Multi-rotor rotorcraft comprise a fuselage, and at least four rotor assemblies operatively supported by and spaced-around the fuselage. Each of the at least four rotor assemblies defines a spin volume and a spin diameter. Some multi-rotor rotorcraft further comprise at least one rotor guard that is fixed relative to the fuselage, that borders the spin volume of at least one of the at least four rotor assemblies, and that is configured to provide a visual indication of the spin volume of the at least one of the at least four rotor assemblies. Various configurations of rotor guards are disclosed.

Multi-rotor rotorcraft

Unmanned aerial vehicle sling load

A composite structural member and an arrangement of such composite structural members are constructed to provide a multi-functional under-floor airframe that reacts flight, handling and internal cargo loads, and is capable of absorbing energy when subjected to vertically applied compression loads, such as loads that may be applied in hard landing or crash situations. The composite structural member and arrangement of such composite structural members adds no parasitic weight to the aircraft, i.e., there is no need for additional energy-absorbing systems, structures or mechanism; and is lighter weight as compared to metal. The composite structural member and related parts of the arrangement of such composite structural members are designed to progressively collapse throughout the stroke (or displacement) that occurs when a dynamic compressive load is applied to the structural member and to work together with crashworthy seats to mitigate injuries to occupants.

Energy-absorbing under-floor airframe

A rib structure for use in an aircraft is provided. The rib structure includes a web portion, a plurality of hat stiffener portions coupled to the web portion, and at least one chord portion coupled to the web portion. The plurality of hat stiffener portions extend substantially parallel, and the at least one chord portion extends substantially perpendicularly relative to the plurality of hat stiffener portions. Moreover, the web portion, the plurality of hat stiffener portions, and the at least one chord portion are fabricated from composite material, and include features such that the rib structure has a buckling ratio of at least about 4.

Rib structure and method of forming thereof

A corner fitting may include a male fitting having a convex portion and a female fitting having a concave portion configured complementary to the convex portion. In addition, the corner fitting may include a strap having a strap radius portion and a pair of strap planar portions extending from opposite ends of the strap radius portion. The strap planar portions may be parallel to one another when the strap radius portion is clamped between the convex portion and the concave portion and the corner fitting is viewed from a side, and non-parallel to one another when the corner fitting is viewed from an end.

Corner tension fitting

An energy absorbing fitting is constructed to absorb tension, shear and compression loads at a joint between two composite material beams of a composite material frame. The fitting is constructed with a band of composite material having an inverted U-shape, a panel of composite material having a U-shaped cross-section configuration that is assembled into the inverted U-shaped configuration of the band, and a sheet of composite material having an inverted L-shape configuration that is secured to the band and to the panel. The fitting is positioned at the intersection of the beams and is secured to the joint between the beams, thereby reinforcing the joint against tension, shear and compression loads.

Energy-absorbing composite tension-shear fitting

Growing community of inventors

Hockessin, DE, United States of America

Eric J Schulze