The Boeing Company

Eric B Gilbert

Timothy LeRoy Skilton

Steve G Mackin

Robert Steven Wright

Russell H Higgins

Andrew Michael Robb

Steven E Klein

Jason A Fraser

Bennett Keith Olson

A hybrid engine including features to meet aircraft thrust, passenger airflow, and fuel cell requirements. The engine includes a combustor burning the same fuel as the fuel cell. The engine has electric motors to utilize the power output of the fuel cell. The engine shafts have sprags to allow motors to drive the compressors and over run the turbines. The engine has variable flowpath geometry to bypass the combustor.

Hybrid electric hydrogen fuel cell engine

A tail-rotor vibration dampener system for an aircraft is provided. The system includes a fuselage and an open rotor assembly including a powerplant and a set of rotor blades. The system further includes at least one actuator unit connecting the open rotor assembly to the fuselage. The actuator unit includes a hydraulic actuator controlling a position of the open rotor assembly in relation to the fuselage and a dampening device operable to cancel a vibration emanating from the open rotor assembly. The system further includes a computerized vibration dampening controller, including programming to determine a frequency of the vibration emanating from the open rotor assembly and control the dampening device to cancel the vibration emanating from the open rotor assembly based upon the frequency.

Tail-rotor vibration dampener system

Hybrid multirotor vehicles and related methods are disclosed herein. An example aircraft includes a battery, a rotor coupled to a wing, a motor operatively coupled to the rotor, and a processor operatively coupled to the motor. The processor to is cause the motor to operate in a first motor operational state. The rotor is to operate in a first rotor operational state when the motor is operating in the first motor operational state. The processor is to cause the motor to switch from operating in the first motor operational state to a second motor operational state. The rotor is to operate in a second rotor operational state when the motor is in the second motor operational state. The motor is to provide electrical energy to the battery in the second motor operational state and the rotor is to autorotate in the second rotor operational state.

Hybrid multirotor vehicles and related methods

A boundary layer ingestion-open rotor system for use with an aircraft having a fuselage, wings, and an empennage includes an open rotor assembly, one or more energy storage systems, and an electronic control unit (ECU). The open rotor assembly includes fan blades connected to and extending radially from a rotor hub, and a linkage assembly connecting the hub to the fuselage aft of the empennage within a predefined boundary layer of airflow around the fuselage. The energy storage systems are connectable to the rotor hub. In response to an electronic control signal, the system(s) selectively energize the open rotor assembly to cause rotation of the hub to occur within the boundary layer. The ECU selectively generates the electronic control signals to energize the open rotor assembly during one or more predetermined flight operating phases of the aircraft, e.g., cruise, takeoff, landing, and descent.

Open rotor boundary layer ingestion booster

A fire extinguisher system. The system includes a first fire extinguisher containing a first agent that is suitable for extinguishing fire, the first fire extinguisher having a first discharge port for discharging the first agent therethrough, and a first actuator for actuating the first discharge port. The system also includes a second, similar fire extinguisher. The system also includes a valve coupled to the first discharge port via a first line and coupled to the second discharge port via a second line, wherein the valve is configured to release the first agent and the second agent into a third line. The system also includes a controller connected to the first actuator and the second actuator, the controller configured to activate the first actuator and the second actuator in a predetermined sequence.

Common array mounting bottles engineered for reuse

An electromagnetic shielding system is configured to shield one or more electrical connections between one or more first electrical cables and one or more second electrical cables. The electromagnetic shielding system includes a base. A first cable coupler is frangibly coupled to the base. The first cable coupler is configured to electrically couple to the first electrical cable(s). A second cable coupler is frangibly coupled to the base. The second cable coupler is configured to electrically couple to the second electrical cable(s). A covering lid is frangibly coupled to the first cable coupler, the second cable coupler, and the base. An electrical connection chamber is defined between the base, the first cable coupler, the second cable coupler, and the covering lid. The first electrical cable(s) are configured to electrically connect to the second electrical cable(s) within the electrical connection chamber.

Electromagnetic shielding systems and methods for aircraft

A system, apparatus, and method for testing a squib circuit. An electrical signature of the squib circuit is monitored when a test switch in the squib circuit is activated. The electrical signature of the squib circuit is based on characterizing resistors electrically connected to squibs in the squib circuit in which each characterizing resistor in the characterizing resistors has a resistance value. A health of each squib in the squib circuit is determined based on the electrical signature of the squib circuit.

Squib circuit for fire protection system

A monolithic three-dimensional fluidic check device is presented. The monolithic three-dimensional fluidic check device comprises a housing surrounding a fluidic flow path and having a first opening at a first end of the housing and a second opening at a second end of the housing, and an elongated center body positioned within and extending along the fluidic flow path. The elongated center body is stationary relative to a flow of fluid.

Three-dimensional fluidic check device

A method for monitoring thermal events in an aircraft engine compartment includes obtaining first sensor data from a first sensor located within an engine compartment of an aircraft. The method also includes determining a time series moving average based at least in part on a subset of the first sensor data. The time series moving average is indicative of an average temperature rate-of-change of the engine compartment. The method further includes determining a standard deviation of the time series moving average and detecting a trend of temperature rates-of-change that satisfy a rate-of-change criterion. The rate-of-change criterion is based on a multiple of the standard deviation, and the temperature rates-of-change are based on temperatures of the engine compartment. The method also includes generating an alert in response to detecting the trend. The alert is indicative of a thermal event associated with the engine compartment.

Thermal event indicator for aircraft engine

A method for avoiding collisions with an aircraft ground-services vehicle includes using a proximity sensor attached to the ground-services vehicle to generate a proximity signal, and using a processor that stores a three-dimensional map of the ground-services vehicle's outer geometry. The three-dimensional map is modifiable upon in-use changes to the 3-D geometry of the ground-services vehicle. The processor uses the three-dimensional map and the proximity signal to determine whether a predetermined 3-D envelope around the vehicle has been breached, and notifies the vehicle of a breach.

Vehicle collision shield

In the present disclosure, systems and methods for preventing collisions between a ground services vehicle and other objects are described. In one embodiment, a system includes a digital three dimensional map of the outer dimensions of the ground vehicle, a micro radar device, a comparator, and an indicator. The micro radar device is secured to the ground vehicle. A comparator signals when an object is within a predetermined envelope around the outer dimensions of the ground vehicle. The comparator receives signals from the micro radar device, and includes dimension data from the three dimensional map. The indicator is responsive to the signal from the comparator. The indicator alerts of possible and pending collision when the predetermined envelope is breached. The indicator may also activate a brake mechanism to stop the ground vehicle. Methods for carrying out the invention by sensing a breach of the envelope and stopping the vehicle are also disclosed.

Growing community of inventors

Seattle, WA, United States of America

Eric B Gilbert