The Boeing Company

Other

David W Kirkbride

Mithra M K V Sankrithi

Sergey D Barmichev

Bradley James Mitchell

Frederick Theodore Calkins

Thamir R Al-Alusi

Andrew David Clark

Jerald C Baillie, Jr

David John Paisley

Darrell S Jolliffe

Thermal control system for aircraft main landing gear wheel wells and related methods are disclosed. An example thermal control system includes a conduit defining a fluid passageway between an inlet and an outlet. The inlet of the conduit positioned in fluid communication with a landing gear wheel well and the outlet of the conduit positioned in fluid communication with the atmosphere. The conduit generates a pressure differential through the fluid passageway between the inlet and the outlet to exhaust heat from the landing gear wheel well to the atmosphere.

Thermal control systems for aircraft landing gear wheel wells and related methods

An unmanned aerial vehicle (UAV) cluster includes a plurality of mission UAVs and a plurality of core UAVs arranged in a cluster. One or more of the mission UAVs is configured for controlled independent flight. The plurality of core UAVs are distributed throughout the cluster according to a selected distribution pattern that distributes the core UAVs according to a predefined mission characteristic of the UAV cluster.

Self-aligning docking mechanism for an unmanned aerial vehicle (UAV)

A propulsion system is provided. The propulsion system comprises a ducted electric bypass fan and an electrical generator powered by a turbine in an engine and configured to provide electricity to the electric bypass fan.

Synergistic hybrid propulsion

A brake assembly for landing gear of an aircraft includes a caliper member and a carrier member. The caliper member includes a gas inlet configured to receive a cooling gas supplied by an on board fuel inerting gas supply system of the aircraft, and a manifold fluidly coupled to the gas inlet. The manifold is configured to distribute the cooling gas to one or more outlet ports of the caliper member. The carrier member is configured to be coupled to the caliper member. The carrier member includes a cylindrical section configured to receive a stacked arrangement of stators and rotors. The cylindrical section defines one or more interior passages configured to fluidly couple the outlet ports of the caliper member to one or more outlet ports of the cylindrical section. The outlet ports of the cylindrical section are arranged proximate the stacked arrangement of stators and rotors to facilitate forced convective cooling of the stacked arrangement of stators and rotors with the cooling gas supplied by the on board fuel inerting gas supply system.

Active cooling system for landing gear brakes

An actuator system for controlling a control surface of an aircraft, which includes a control structure which defines the control surface and the control structure has an axis of rotation about which the control structure can rotate relative to the aircraft. A first actuator assembly has a first actuator arm and a second actuator assembly has a second actuator arm. The first actuator assembly and the second actuator assembly are spaced apart from one another along the axis of rotation. The first actuator arm is connected to a first band member and the first band member is connected to the control structure on a first side of the axis of rotation and the second actuator arm is connected to a second band member and the second band member is connected to the control structure on a second opposing side of the axis of rotation.

Hydraulic actuation system for imparting rotation

Systems and methods provide airflow to a first area from a second area within a vehicle. The system includes a fan mounted within a door separating the first area from the second area. The fan is configured to direct airflow from the second area into the first area. The fan having a shield positioned adjacent to the second area that is configured to conceal the fan.

Systems and methods providing airflow within a vehicle

Disclosed are aircraft configured to perform tethered and untethered flights as well as methods of operating such aircraft. During a tethered flight, the aircraft is connected to a power line using its connecting module. While tethered, the aircraft can receive electrical energy from the power line and use this energy for propulsion and/or storage. The aircraft comprises a propulsion module for providing vertical and horizontal thrusts. In some examples, the aircraft comprises a transport module. The transport module may be removably attached to the propulsion module and be replaceable with another transportation module. During an untethered flight, the electrical energy is supplied to the propulsion module from a battery and/or a generator on board of the aircraft. The untethered flight capability can be used for landing and takeoff, flying away from power lines or when the power line is not operational, and other like examples.

Aircraft and methods of performing tethered and untethered flights using aircraft

An apparatus, systems comprising the apparatus, and methods of using and making the apparatus are disclosed, with the apparatus comprising an inlet, at least one oxygen membrane separator in communication with the inlet and in communication with an ambient airflow, with the ambient airflow comprising an ambient oxygen concentration, at least one piezoelectric pump in communication with the at least one oxygen membrane separator, and an outlet for emitting an enhanced oxygen concentration airflow.

Personal oxygen enhanced breathing system

A non-pyrotechnic flare system and method includes at least one flare member that is configured to be deployed. The flare member(s) includes a head having a light-emitting diode (LED) that is configured to emit light when activated, and a wing-shaped appendage extending from the head. In at least one embodiment, a casing retains the flare member(s) in a stowed position. The flare member(s) is configured to be deployed from the casing.

Non-pyrotechnic flare systems and methods

Systems and methods provide airflow to a flight deck from a passenger entry area. The system includes a fan mounted within a door separating a flight deck from a passenger entry area. The fan is configured to direct airflow from the passenger entry area into the flight deck. The fan having a shield positioned adjacent to the passenger entry area that is configured to conceal the fan.

Systems and methods providing airflow to a flight deck

An aerodynamic cover panel for a landing gear wheel well in an undercarriage of an aircraft includes at least one embodiment having a peripheral lip that defines a plane. Movements of the cover panel to open and close the wheel well are confined to pivotal rotation within the plane, and occur within an aerodynamic boundary layer of the undercarriage about a pivot axis in one rotational direction to open the wheel well, and in an opposite rotational direction to close the wheel well. The cover panel includes a flange, to which a rotary shaft is secured at one end for rotation about the pivot axis. The other end of the rotary shaft is secured to an actuator fixed within the undercarriage. In one embodiment, the cover panel rotates about an arc of least 75&#xb0; between fully opened and fully closed positions of the wheel well.

Cover panel for aircraft landing gear wheel well

A system for detecting an overheat condition in a confined space includes a sensing device and one or more processors. The sensing device is attached to a wall of the confined space. The sensing device includes a laser range sensor, a thermal imaging sensor, and a wireless communication circuit. The laser range sensor measures a distance from the sensing device to a target object within the confined space. The thermal imaging sensor measures thermal radiation emitted from the target object. The wireless communication circuit remotely communicates distance data representing the distance measured by the laser range sensor and radiation data representing the thermal radiation measured by the thermal imaging sensor. The one or more processors are configured to determine a temperature of the target object based on the distance data and the radiation data.

Overheat detection systems and methods

An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.

Aircraft engine mounting system

Systems and methods for mitigating the risk of and/or suppressing fires caused by lithium battery-powered personal computing devices used on the flight deck or in crew and passenger compartments onboard an aircraft. A fire detection and suppression pack is attached to a lithium-ion battery-powered portable personal computing device. The fire detection and suppression pack has a weight and volume consistent with and does not impair the use of the portable personal computing device. The fire detection and suppression pack is a full-time fire suppression system that is on hot standby at all times, independent of the computing device's power mode. The fire detection and suppression pack uses gases stored in canisters to provide cool-down, displacement suppressant to control and extinguish any fire source and associated burnable fuel required to sustain the fire event.

Fire detection and suppression pack for battery-powered personal computing devices

According to one embodiment, an apparatus for cooling at least one landing gear brake of an aircraft in flight is described. The apparatus includes an air handling assembly that is coupled to the aircraft. The air handling assembly includes at least one air inlet port. The apparatus also includes an air delivery assembly that is in air receiving communication with the air handling assembly. The air delivery assembly includes at least one nozzle that is configured to direct air into a first space adjacent a first side of the landing gear brake to create an air pressure differential across the landing gear brake.

Growing community of inventors

Allyn, WA, United States of America

David W Kirkbride