The Boeing Company

Glenn Scott Bushnell

Dan John Clingman

Jonathan Kenji Brown

Frederick Theodore Calkins

James Henry Mabe

Francisco A Navarro

Stefan Richard Bieniawski

Michael W Hardt

Ted Dell Whitley

Eduardo Gallo

Jeffrey H Hunt

David Arthur Whelan

David Christien Soreide

Jack Thiesen

Ordie Dean Butterfield

Bentley Edwin Northon

Stephen A Walls

Daniel John Clingman

Casey Lyn Madsen

Robert Roland Keever

Grant Joseph Atkinson

Edgar Jacobi

Jacklyn Ann Holmes

A method and apparatus for shaping fuselage sections. A first fuselage section is held in a holding structure in a cradle in a cradle system. Force are applied to the first fuselage section with an actuator system to a portion of the first fuselage section such that a first current shape of the first fuselage section changes towards a first desired shape for the first fuselage section to join the first the fuselage section to a second fuselage section.

Cradle system for shaping fuselage sections

Example navigation aids for increasing the accuracy of a navigation system are disclosed herein. An example method disclosed herein identifying, with an aircraft intent description language (AIDL) aid, an AIDL instruction as associated with a first dynamic activity level of a plurality of dynamic activity levels and determining, with the AIDL aid, an aircraft state to be affected by the AIDL instruction. The example method also includes changing, with a navigation filter, a weighting scheme for a measurement of the aircraft state obtained by an inertial navigation system (INS) of the aircraft and estimating, with the navigation filter, a trajectory of the aircraft based on the weighting scheme and the measurement.

Navigation aids for unmanned aerial systems in a GPS-denied environment

A system for changing a shape a structural spar includes, in an exemplary embodiment, a plurality of adjoining structural strips axially aligned to form the structural spar. At least one of the structural strips is formed from a shape memory alloy. The system also includes a temperature control system to control a temperature of the at least one shape memory alloy strip. Heat applied to the at least one shape memory alloy strip causes the structural spar to twist or bend.

Shape memory alloy active spars for blade twist

There is provided a training system capable of performing work. The system has a shape memory alloy (SMA) actuator exhibiting a generally planar transformational behavior. The system further has one or more heating elements for transforming the SMA actuator from an original shape to a trained shape, thereby performing work.

Systems for shape memory alloy structures

Aspects herein describe techniques for synchronizing clocks between two moving platforms using optical signals generated from lasers to measure clock offsets and determine a separation distance between moving platforms. Once the clocks are synchronized (e.g., an offset between the clocks is determined), the moving platforms can share sensor data, location data, and other information which is dependent on accurate timestamps and relative positions. In one aspect, one of the platforms serves as a virtual mirror. That is, the platform transmits a pulse at the same instance a pulse is received, similar to a mirror that reflects incident light. For example, the first platform may transmit pulses which are received at the second platform. The second platform can use optical or electrical components to form the virtual mirror that transmits an optical pulse to the first platform each time a pulse is received at the second platform.

Virtual mirror technique for measuring time and frequency offsets between clocks on moving platforms

Aspects herein describe techniques for synchronizing clocks between two moving platforms (e.g., land vehicles, ships, aircraft, and the like) using optical signals generated from lasers. In one aspect, a method for mixing an intermediate signal with a local reference clock in a method of communicating between moving platforms includes mixing the intermediate signal with a sine representation of the local reference clock to generate a first offset error; mixing the intermediate signal with a cosine representation of the local reference clock to generate a second offset error; and combining the first and second offset errors to generate the fine phase offset.

Precision relative positioning and free space time transfer between moving platforms

Methods and apparatus are disclosed herein to determine relative positioning between moving platforms. An example method includes sending a first signal via a first moving platform to be received by a second moving platform. The example method includes receiving, at the first platform, a second signal sent by the second moving platform and aligning the first signal and the second signal. The example method includes determining, at the first moving platform, a first duration of time between the sending of a first pulse and the receiving of a second pulse. The example method includes determining, at the second moving platform, a second duration of time between the sending of the second pulse and the receiving of the first pulse. The example method includes determining a distance of the first moving platform relative to the second moving platform based on the first and second durations of time.

Methods and apparatus to determine relative positioning between moving platforms

There is provided a method of training a shape memory alloy (SMA) workpiece. The method includes applying a force couple to a shape memory alloy (SMA) workpiece to impart a generally planar transformational behavior to the SMA workpiece to obtain a trained shape memory alloy (SMA) workpiece.

Methods and systems for shape memory alloy structures

Systems and methods for providing vehicle-centric collision avoidance are disclosed. An example method includes determining a first flight trajectory for a first aircraft, determining a second flight trajectory for a second aircraft, predicting a distance between the first aircraft and the second aircraft at a predicted closest point of approach based on the first and second flight trajectories, comparing the distance to a separation perimeter layer, the separation perimeter layer configured to provide a minimum separation distance from the first aircraft to the second aircraft, and altering the first flight trajectory when the distance breaches the separation perimeter layer.

Vehicle-based automatic traffic conflict and collision avoidance

A method and apparatus for managing separation between vehicles. A closest point of approach between a first vehicle traveling along a first path and a second vehicle traveling along a second path is predicted. A number of compensation commands for altering the first path of the first vehicle are generated using the closest point of approach and a desired level of separation between the first vehicle and the second vehicle. The number of compensation commands is integrated with a number of control commands for the first vehicle to form a final number of control commands configured to maneuver the first vehicle to substantially maintain the desired level of separation between the first vehicle and the second vehicle. A response of the first vehicle to the final number of control commands is a desired response.

Aircraft traffic separation system

Systems and methods for providing vehicle-centric collision avoidance are disclosed. An example method includes determining a first flight trajectory for a first aircraft, determining a second flight trajectory for a second aircraft, determining a predicted first distance between the first aircraft and the second aircraft at a first closest point of approach based on the first and second flight trajectories, comparing the predicted first distance to a first separation perimeter layer, the first separation perimeter layer defining a first three-dimensional perimeter based on the first aircraft, determining a first adjustment having a first magnitude from the first flight trajectory when the predicted first distance is within a first perimeter, determining a second adjustment having a second magnitude from the first flight trajectory when the predicted first distance is within a second perimeter different from the first perimeter, and altering the first flight trajectory based on the first or second adjustment.

Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.

Deployable aerodynamic devices with reduced actuator loads

Systems and methods for providing vehicle-centric collision avoidance are disclosed. In one embodiment, a method includes determining a first flight trajectory for a first aircraft. The method also includes determining a second flight trajectory for a second aircraft. A distance between the first aircraft and the second aircraft at a first closest point of approach (CPA) is predicted. The predicted closest point of approach is then compared to a separation perimeter layer. The separation perimeter layer is configured to provide a minimum separation distance from the first aircraft to the second aircraft. When the predicted closest point of approach breaches the separation perimeter, the first flight trajectory is altered to provide collision avoidance.

An aircraft system may include an airfoil and a deployable device coupled to the airfoil. The system may further include a shape memory alloy actuator coupled between the airfoil and the deployable device. The actuator may be movable between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. The system may additionally include an activatable link positioned between the actuator and the deployable device. The link may have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device.

Growing community of inventors

Puyallup, WA, United States of America

Glenn Scott Bushnell