The Boeing Company

Stephen Roger Amorosi

Robert James Miller

Matthew Leroy Anderson

Mark A Barr

Vyacheslav Khozikov

Gregory M Santini

Rangasamy Elangovan

James Miller Wheaton

Michael R Severance

Ramon Augustin Burin

Marc Rollo Matsen

John Ralph Hull

Mark John Gardner

Flint Matthew Jamison

Jeffrey Michael Burton

Flint M Jamison

Morteza Safai

Kevin Raylin Tsai

Seiya Sakurai

Frederick Theodore Calkins

Mark Steven Good

Michael Strasik

Sahrudine Apdalhaliem

Moushumi Shome

Christopher Andrew Konings

Adam P Malachowski

Matthew A Moser

Michael E Renzelmann

Paul M Vijgen

Michael K Klein

Michael R Finn

Robert Graham Albers

Bruce Alfin Dahl

Kyle J Johnson

Jeffrey P Baucum

Douglas J Silva

Dan Onu

Walter J Jarecki

Charles E Jokisch

George Moy

Peter Angel Padilla

Paul Hungwai Lai

Gregory E Rupert

Nicholas I Bennett

Scott N Rampton

Brian E Geppert

Kevin Mark Johnsen

William Suhail Hanna

Eric J Selby

Monica E Thommen

Carl F Osaki

Quang Minh Pham

Steve C Hinrichs

Sean C Omeara

Dennis Chin

Douglas James Silva

Mark J Gardner

Robert J Miller

Structure for aircraft

Aero dynamic structure with fastener arrangement

Systems and methods for an aerodynamic device with a lap splice that includes an edge panel is described herein. In edge panel can include a tapered section. A portion of a skin of the aerodynamic device can be disposed below the tapered section. One or both of the edge panel or the skin can be composite. The tapered section of the edge panel can be formed by decreasing the ply thickness of the edge panel.

Aerodynamic surface lap splice

Continuous skin leading edge slats are disclosed. A disclosed example leading edge slat for use with an aircraft includes a single-piece nose skin defining upper and lower external surfaces of the leading edge slat, where the single-piece nose skin is to extend between a fore end and an aft end of the leading edge slat, and a box spar coupled to an inner surface of the single-piece nose skin. The box spar includes lateral walls extending away from the inner surface of the single-piece nose skin. The lateral walls define at least one compartment of the box spar.

Continuous skin leading edge slats

An anti-ice system is disclosed, including an airfoil structure having a leading-edge portion facing a wind direction. The airfoil structure includes an outer skin and an inner skin which form a plurality of channels, each channel having an air inlet and an air outlet. An air delivery duct inside the airfoil structure extends transverse to the wind direction and has a plurality of openings directed toward the air inlets of the channels. A heat exchanger is configured to provide hot air to the air delivery duct.

Leading-edge thermal anti-ice systems and methods

A trailing edge flap actuation mechanism has a flap drive link with a first end pivotally coupled to a fore flap structure of a flap and a second end pivotally coupled to an underwing support structure. An aft tension link has a leading end pivotally coupled proximate an aft end of the underwing support structure and a trailing end coupled to a mid-section structure of the flap. An actuator, when actuated, rotates the flap drive link about a first pivot axle to move the flap between a retracted position and a deployed lowered position. The actuator, including a ball-screw drive shaft having a universal joint, is positioned in a cove above the underwing support structure whereby the extent that the underwing support structure protrudes below the wing is reduced.

Flap support mechanism&#x2014;C bar

An induction heating system employs a ferromagnetic susceptor mounted proximate an exterior of flight surface of an aircraft. At least one electrically conductive coil is mounted proximate the ferromagnetic susceptor. The at least one electrically conductive coil is powered by a first power source with a first frequency. At least one compensating coil is mounted proximate the ferromagnetic susceptor having a geometry determined to provide substantially net-zero flux with respect to the at least one electrically conductive coil and positioned to induce induction heating where the first plurality of electrically conductive coils lacks induced inductive heating coverage. The at least one compensating coils is powered by a second AC power source with a second frequency.

Induction heating coils with uniform heating

Aerodynamic structures having lower surface spoilers are described herein. One disclosed example apparatus includes a first spoiler of an aerodynamic structure of an aircraft, where the first spoiler is to deflect away from a first side of the aerodynamic structure and a second spoiler on a second side of the aerodynamic structure opposite of the first side, where the second spoiler is to deflect away from the second side to reduce a load on at least one of the first spoiler or a flap of the aerodynamic structure.

Aerodynamic structures having lower surface spoilers

A wing leading edge architecture designed to enable laminar flow on passenger jets or other aircraft. The embodiments disclosed herein comprise a metallic fixed leading edge skin panel that is bonded to internal support structure without fasteners except for limited fastening along side edge portions adjacent to side edge portions of adjacent leading edge skin panels and along an aft edge portion overlapping a wing skin. In addition, the embodiments disclosed herein integrate a low-drag bleed-air anti-icing (i.e., vent) system and a Krueger flap assembly (e.g., a two-position, high-height, variable-camber Krueger flap assembly).

Wing leading edge architecture suitable for laminar flow

A system for heating a shape memory alloy (SMA) actuator may include an SMA actuator, a smart susceptor, a plurality of induction coils, and a control module. The SMA actuator may have at least one layup. The SMA actuator may be selectively heated to a transition temperature. The smart susceptor may be in thermal contact with the at least one layup of the SMA actuator. The induction heating coils may be configured to receive an alternating current and generate a magnetic field based on the alternating current. The magnetic field may create an eddy current in at least one of the SMA actuator and the smart susceptor to heat the SMA actuator to the transition temperature. The control module may be configured to drive the alternating current supplied to the induction heating coils.

Smart susceptor for a shape memory alloy (SMA) actuator inductive heating system

An ice protection system and method are provided that facilitate the prevention or reduction in ice formation upon an aerodynamic surface. The ice protection system may include an aerodynamic surface that includes a susceptor formed of a ferromagnetic material that is located proximate an outer mold line of a leading edge of the aerodynamic surface. The ice protection system may also include at least one induction coil and a signal source configured to provide alternating current to the at least one induction coil to thereby generate an electromagnetic field. The electromagnetic field creates an eddy current in the susceptor so as to heat the leading edge of the aerodynamic surface. A corresponding ice protection method is also provided.

Ice protection system and method

A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.

Slidable divergent trailing edge device

A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions conducive to, or indicating, ice formation. The ice detection and deicing system may further use eddy currents induced in one or more layers of the system to increase the temperature of the one or more layers to reduce the amount of ice formation or reduce the probability of ice being formed.

Systems and methods for predicting and controlling ice formation

A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.

Leading edge variable camber system and method

An apparatus comprises a sensor system, a flexible line, and a sensor. The sensor system is capable of detecting skew in at least some of a plurality of control surfaces for a vehicle. The flexible line extends across a number of interfaces for a portion of the plurality of control surfaces. The sensor is connected to the flexible line and is capable of detecting the skew in the portion of the plurality of control surfaces in response to a selected amount of movement of the flexible line.

Slat skew detection system

Growing community of inventors

Seattle, WA, United States of America

Stephen Roger Amorosi