Tektronix, Inc.

The Boeing Company

Dan Onu

Michael E Renzelmann

Paul M Vijgen

Gary A Emch

John D Winter

Candy L Carr

Mark Steven Good

Stephen Roger Amorosi

Adam P Malachowski

Matthew A Moser

Mark John Gardner

Michael R Finn

Monica E Thommen

Mark J Gardner

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

The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

Dynamic adjustment of wing surfaces for variable camber

The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

A method and apparatus for determining the period Tof a signal representing a digitally modulated waveform using NRZ coding with a discrete/integer number of a clock periods between signal transitions, where a periodic sequence of logic '1s' and logic '0s' is transmitted. The method samples an input periodic signal, constructs an estimate of the autocorrelation sequence rof the sequence of samples, constructs a sequence of peaks p, and computes the period Tto be the time between the first psample (k=0), and the time location of the maximum value of pbased on the known Tspacing of the psequence samples.

Period determination of a periodic NRZ signal

An apparatus and method for determining the period of a data signal encoded using PN sequences may be implemented using software, and takes advantage of the fact that the signal is generated based upon a pseudo-random binary sequence, and of the fact that the order of the characteristic polynomial is known. The apparatus and method uses knowledge about the structure of the signal generator (i.e. the order of the characterizing polynomial of the encoding PN sequence), and recognizes the fact that short data tokens from the original signal can be used with the same success in determining the period as longer sequences having at least the length of the period.

Period determination of sampled pseudo-random binary sequence generated signals

A method for determining the period of a periodic signal, possibly including noise, includes the step of calculating a signal representing the difference between the periodic signal, and the periodic signal delayed by a time T. The variance of the difference representative signal is then computed. The steps of computing a difference signal, and determining the variance of the difference signal is repeated for different times T. The period of the periodic signal is determined to be the time T producing the minimum variance. Apparatus implementing this method includes a source of the periodic signal. A difference circuit computes a signal representing the difference between the periodic signal, and the periodic signal delayed by a time T, and a variance circuit computes a signal representing the variance of the difference representative signal. A control circuit varies the time T. A minimum selector selects the time T producing the minimum variance as the period of the periodic signal.

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Redmond, WA, United States of America

Dan Onu