Design considerations for attaining 250-knot test velocities at the aircraft landing dynamics facility
- Author:
- Taylor, J. T.
- Published:
- Feb 1, 1980.
- Physical Description:
- 1 electronic document
- Additional Creators:
- Armistead, M. F., Fitzgerald, A. L., Cires, A., Gray, C. E., Jr., and Snyder, R. E.
Online Version
- hdl.handle.net , Connect to this object online.
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary:
- Preliminary design studies are presented which consider the important parameters in providing 250 knot test velocities at the Aircraft Landing Dynamics Facility. Four major components of this facility are: the hydraulic jet catapult, the test carriage structure, the reaction turning bucket, and the wheels. Using the hydraulic-jet catapult characteristics, a target design point was selected and a carriage structure was sized to meet the required strength requirements. The preliminary design results indicate that to attain 250 knot test velocities for a given hydraulic jet catapult system, a carriage mass of 25,424 kg (56,000 lbm.) cannot be exceeded.
- Other Subject(s):
- Collection:
- NASA Technical Reports Server (NTRS) Collection.
- Note:
- Document ID: 19800010855.
Accession ID: 80N19132.
NASA-TM-80222. - Terms of Use and Reproduction:
- No Copyright.
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