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Lyle R Appleford

from Seattle, WA
Age ~95
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Also known as:
Lyle Ray Appleford
Phone and address:
900 University St APT 402, Seattle, WA 98101
(206) 922-2606
Related to:
Sarah C Ramsey, 37David J Beier, 39Fernando A Beier, 57Betty E Appleford, 96Marcia L Bruno, 59Pierre Y Savoye, 65Michael D Bruno, 62Barbara M Beier, 62Robin A Appleford, 65
Connected to:
Betsy L Applegate, 86Beverly A Applegate, 66Blair A Applegate, 28Bobbi J Applegate, 62Brian Applegate, 51Brian L Applegarth, 43Caitlin Applegate, 29Cassie M Applegate, 41Charles E Applegate, 85Chase R Applegate, 40

Lyle Appleford Phones & Addresses

  • 900 University St APT 402, Seattle, WA 98101 (206) 922-2606
  • 1225 39Th St, Seattle, WA 98112

Publications

Us Patents

Software Controlled Aircraft Component Configuration System

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US Patent:
52709310, Dec 14, 1993
Filed:
Mar 12, 1992
Appl. No.:
7/852911
Inventors:
Lyle R. Appleford - Seattle WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
G06F 1520
G11C 1140
US Classification:
36442401
Abstract:
Configuration options for aircraft components are stored in non-volatile reprogrammable memory and selected by way of software under secure conditions without requiring configuration pins. Aircraft components can be reconfigured without taking the aircraft out of service for more than a few minutes.

Apparatus And Methods For Generating Aircraft Control Commands Using Nonlinear Feedback Gain

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US Patent:
48623725, Aug 29, 1989
Filed:
Nov 26, 1985
Appl. No.:
6/801921
Inventors:
Lyle R. Appleford - Seattle WA
Assignee:
The Boeing Company - Seattle WA
International Classification:
G05D 108
US Classification:
364433
Abstract:
Altitude rate commands are generated and fed to an aircraft autopilot to cause the aircraft to transition to a non-level flight path which corresponds to a portion of a calculated flight path profile stored in a flight management computer. When capture of the non-level path is initiated, altitude rate commands are generated in accordance with the equation h. sub. cmd =h. sub. path +k. sub. h. DELTA. h where h. sub. path is the altitude rate of the non-level segment,. DELTA. h is an altitude difference between current aircraft altitude and an altitude point on the non-level segment, and k. sub. h is an altitude error gain which is a nonlinear inverse function of altitude rate error,. DELTA. h, and which is calcuated in accordance with the equation k. sub. h =k. sub. 1 -k. sub. 2. vertline. DELTA. h. vertline. where k. sub. 1 and k. sub. 2 are predetermined constants.
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Lyle R Appleford from Seattle, WA, age ~95 Get Report