The Boeing Company

Limit, Inc.

Kevin Bowcutt

Gregory L Blake

Daniel Corbin

Dennis Repp

Matthew Ibarra

Sam Iravantchi

Oscar Dufau

Ahmed Shishegar

Robert M Connell

Thomas Russell Smith

Matthew J Roode

Todd Magee

Eric Unger

Michael F Stoia

Otto R Butsch

Jacob T Needels

John Ralph Hull

Dejan Nikic

James A Grossnickle

Arun Muley

Joseph Steven Silkey

Matthew T Lakebrink

Garrett W Ek

Aircraft

Methods and apparatus for power generation and/or thermal management on a high speed flight vehicle include circulating a power generation loop working fluid through a power generation loop, which absorbs heat associated with the flight vehicle. A generator operably coupled to the power generation loop generates electrical power. Additionally, a heat transport loop working fluid may circulate through a heat transport loop to provide thermal management through heat transfer.

Methods and systems for generating power and thermal management having dual loop architecture

Methods and apparatus for cooling a surface on a flight vehicle and generating power include advancing the vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A first working fluid circulates through a first fluid loop that heats the first working fluid through a first heat intake thermally coupled to the surface and expands the first working fluid in a first thermal engine to generate a first work output. A second fluid loop has a second working fluid that receives heat from the first working fluid and a second thermal engine to generate a second work output. The first and second work outputs are operably coupled to first and second generators, respectively, to power primary or auxiliary systems on the flight vehicle.

Methods and systems for generating power and thermal management having combined cycle architecture

An aerodynamic body includes an upper surface and a lower surface. The upper surface includes a first portion of a first axisymmetric body. The lower surface is mated with the upper surface. The lower surface includes a waverider shape. The waverider shape is derived from the shockwave generated by a second axisymmetric body.

Aerodynamic body for supersonic speed

A system for preventing overflow of a toilet includes a sensor, a processor and an actuator. The sensor senses a parameter caused by fluid dynamics within the toilet during a flush cycle. The parameter may involve vibration, sound, pressure, fluid flow rate or other detectible characteristics of the toilet. The processor uses information regarding the parameter that is gathered by the sensor to evaluate the condition of the flush cycle to determine if an impeded flush condition exists. In the event of an impeded flush condition, the processor directs the actuator to close a valve, which may be the toilet flapper valve in some embodiments. Also disclosed are methods for preventing toilet overflow, detecting an impeded flush condition and calibrating the system.

Toilet overflow prevention system and method

A scramjet includes a converging inlet, a combustor configured to introduce a fuel stream into an air stream in a combustion chamber and to combust the fuel air mixture stream to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream. The combustor includes a fuel injection system including at least one arcjet. A method of creating thrust for an aircraft includes compressing a supersonic incoming air stream in a converging inlet, injecting a fuel stream into the air stream in a combustion chamber to create a fuel air mixture stream, igniting the fuel air mixture stream to create an exhaust stream, and exhausting the exhaust stream from a diverging exit nozzle. The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.

Scramjets and associated aircraft and methods

A hypersonic vehicle has a body, a control surface, and a hypersonic air-breathing engine. The engine includes a converging inlet having a fixed cowling having a first cross-sectional area and a throat having a second cross-sectional area. A flow restrictor is movable between a stowed position and a fully deployed position. The flow restrictor has a third cross-sectional area that is smaller than the first cross-sectional area, such that a consistent gap is formed between a periphery of the flow restrictor and an inner surface of the cowling with the flow restrictor in the fully deployed position and the difference between the first cross-sectional area and the third cross-sectional area is approximately equal to the second cross-sectional area.

Inlet flow restrictor

A vehicle comprises a first stage supersonic aircraft, and a second stage hypersonic aircraft. The second stage aircraft is in tandem with the first stage aircraft.

First and second stage aircraft coupled in tandem

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Aliso Viejo, CA, United States of America

Kevin Bowcutt