The Boeing Company

J Everett Groat

Jeffrey Joseph White

David K Toy

Eric Y Chan

Dennis Gary Koshinz

Tuong Kien Truong

Michael Simmons

Raymond H Horstman

Thomas R Hasenoehrl

Sham S Hariram

Sigvard Johann Wahlin

Richard J Nesting

Quy Lam

Arshad Nazir

Dennis D Chung

Edward M Ducheane

Howard S Veith

Peter K Louden

Todd C Thomas

Kevin K Longwell

John L Vento

Luc Tu Kha

Joseph M Buchholz

Matthew E Leahy

Paul J Maue

Sigvard J Wahlin

Michael L Simmons

Keith K Longwell

Systems and methods that use an optical impedance sensor that eliminates electricity for measuring fuel quantity in fuel tanks. The optical impedance sensor comprises two optical fibers spaced apart inside a meniscus tube, one to transmit light along its length and the other to receive light along its length. The meniscus tube minimizes the sloshing of fuel level. The fuel level in the tank modulates the optical impedance between the two optical fibers, resulting in changes in the total light received by an optical detector. Depending on fuel tank height, the optical impedance sensor may comprise different embodiments in which the detection apparatus shapes the light to be unidirectional (emitted and collected only on one side of the fiber) or omnidirectional (all directions).

Optical impedance modulation for fuel quantity measurement comprising a fiber encased by a tube having a longitudinal slot with a lens

Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational.

Systems and methods for controlling aircraft electrical power

An aircraft fuel scavenge system incorporates a scavenge pump receiving fuel from a center tank and depositing the fuel in a wing tank. A water separator receives fuel through an inlet tube providing a plurality of momentum changes to incoming fuel, the water separator having a fuel outlet connected to the scavenge pump and a water outlet. A water manifold is connected from the water outlet to an input to a fuel supply line to an engine.

Fuel scavenge water removal system

An alternate ventilation system for an aircraft having a body structure and a plurality of electronic devices is provided. The ventilation system includes a ventilation conduit, an inboard supply valve, a first outflow valve and a second outflow valve. The ventilation conduit is adapted to be coupled to the body structure for directing a ventilation flow of air along a predetermined flow path. The inboard supply valve is coupled to the ventilation conduit and adapted for drawing air from the cabin into the ventilation conduit when positioned in the open condition. The first outflow valve is coupled to the ventilation conduit and adapted for discharging at least a portion of the ventilation flow from the ventilation conduit to a point outside the body structure when positioned in the open condition. The second outflow valve is coupled to the body structure and operable in a first mode and a second mode. The first mode is adapted to selectively enable a discharge airflow from the cabin and the second mode is adapted to selectively enable an input airflow into the cabin. A method for ventilating an aircraft is also provided herein.

Alternate ventilation system

Growing community of inventors

Snohomish, WA, United States of America

J Everett Groat