A ground effect craft having a ground effect wing, a plurality of sponsons, and a control system is disclosed. The ground effect wing may include a fore ground effect wing and an aft ground effect wing. The ground effect wing may generate a stabilizing moment on at least one sponson to stabilize the ground effect craft. The plurality of sponsons may be dynamically coupled to the body. The plurality of sponsons may be dynamically coupled to each other. The dynamic coupling may permit the sponsons to move relatively independent of the body and each other, thereby stabilizing the ground effect craft. The ground effect craft may include a stabilizing wing.

An aircraft fairing includes a fairing body having an exterior fairing wall and at least one wheel bin. The at least one wheel bin has a side wall extending from an opening in the exterior fairing wall to an end wall. The side wall and the end wall define a cavity of the at least one wheel bin in fluid communication with the opening in the exterior fairing wall. An acoustic resonator is mounted to an outer surface of the side wall of the at least one wheel bin and is in fluid communication with the cavity. The acoustic resonator has a resonant frequency substantially similar to a cavity modal frequency of the at least one wheel bin at an aircraft flight condition.

An aircraft with folding mechanism, the aircraft including a fuselage, optionally a payload and/or landing gear attached to the fuselage, at least two longitudinal beams attached to the fuselage that preferably extend parallel to each other and parallel to a first aircraft axis, with lifting units attached to each of the longitudinal beams. At least one crossbeam is attached to the fuselage, and preferably extending parallel to a second aircraft axis and at right angles with respect to the longitudinal beams, with lifting units attached to the crossbeam. The longitudinal beams are rotatably attached to the fuselage by at least one respective first pivot joint configured for pivoting the longitudinal beams around a respective first pivot axis to a pivoted position. The crossbeam is rotatably attached to the fuselage, preferably by at least one second pivot joint, for pivoting the crossbeam around a second pivot axis to a pivoted position.

An aircraft landing gear assembly including a plurality of noise-inducing elements, at least one of the noise-inducing elements comprising a brake assembly or electric drive assembly, and a noise reduction fairing arranged to shield only at least a portion of the brake assembly from incident airflow.

An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, a line having one end coupled to the chassis and an opposite free end, wherein the free end is positioned below the chassis, and a severing mechanism operable to sever the line under control of the control system.

A quench and temper steel alloy is disclosed having the following composition in weight percent. TABLE-US-00001 C 0.1-0.4 Mn 0.1-1.0 Si 0.1-1.2 Cr 9.0-12.5 Ni 3.0-4.3 Mo   1-2 Cu 0.1-1.0 Co   1-4 W  0.2 max. V 0.1-0.6 Ti  0.1 max. Nb up to 0.01 Ta up to 0.01 Al   0-0.25 N 0.1-0.35 Ce 0.006 max. La 0.006 max.
The balance of the alloy is iron and the usual impurities found in similar grades of quench and temper steels intended for similar use or service, including not more than about 0.01% phosphorus and not more than about 0.010% sulfur. A quenched and tempered steel article made from this alloy is also disclosed. Further disclosed is a method of making the alloy.

A quench and temper steel alloy is disclosed having the following composition in weight percent. TABLE-US-00001 C 0.1-0.4 Mn 0.1-1.0 Si 0.1-1.2 Cr 9.0-12.5 Ni 3.0-4.3 Mo   1-2 Cu 0.1-1.0 Co   1-4 W  0.2 max. V 0.1-0.6 Ti  0.1 max. Nb up to 0.01 Ta up to 0.01 Al   0-0.25 N 0.1-0.35 Ce 0.006 max. La 0.006 max.
The balance of the alloy is iron and the usual impurities found in similar grades of quench and temper steels intended for similar use or service, including not more than about 0.01% phosphorus and not more than about 0.010% sulfur. A quenched and tempered steel article made from this alloy is also disclosed. Further disclosed is a method of making the alloy.

A wheel well fairing for reducing drag on an aircraft fuselage configured with an open wheel well for stowing landing gear of the aircraft. The wheel well fairing includes a Coanda fairing having a convex-shaped lower portion and an upper portion. The upper portion is configured for positioning adjacent an interior vertically-orientated sidewall of the wheel well, and the convex-shaped lower portion has a bottom surface configured to extend substantially parallel to and positioned adjacent with an outer hull surface of the fuselage. The convex-shaped lower portion is curved inwardly within the wheel well between the upper portion and bottom surface. The Coanda fairing is positioned at an aft portion of the wheel well to redirect airflow out of the wheel well in a rearward direction along the bottom hull surface of the fuselage.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

A tool for adjusting an orientation of a nose landing gear of an aircraft is disclosed herein. The nose landing gear has an axle to which a wheel is mounted. The axle has an opening extending therethrough. The opening is defined by an inner surface of the axle. The tool includes, but is not limited to, a unitary member having a handle portion at a first end of the unitary member and an axle-engaging portion at a second end of the unitary member. The handle portion is configured for engagement with a hand of an operator. The axle-engaging portion is configured to be inserted into the opening and to engage with the inner surface.