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Static test of an ultralight airplaneThis paper describes all of the work necessary to perform the static test of an ultralight airplane. A steel reaction gantry was designed first, then all of the loading whiffletrees, the hydraulic actuation system, and instrumentation systems were designed. Loads and stress analyses were performed on the airplane and the gantry and whiffletrees. Components tested to date are: tubing samples, cables, and two-by-four whiffletrees. A hydraulic system consisting of a 3000-psi hand pump, 10,000-pound actuator, pressure gage and lines, and a Barksdale valve are described. Load cell calibration and pressure indicator calibration procedures are also described. A description of the strain and deflection measurement system is included. Preliminary data obtained to date are compared to the analytical predictions.
Document ID
19870026760
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Smith, H. W.
(Kansas, University Lawrence, United States)
Date Acquired
August 13, 2013
Publication Date
September 1, 1986
Subject Category
Aeronautics (General)
Report/Patent Number
AIAA PAPER 86-2600
Accession Number
87A14034
Funding Number(s)
CONTRACT_GRANT: NAG1-345
Distribution Limits
Public
Copyright
Other

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