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Optimal short range trajectories for helicoptersAn optimal flight path algorithm using a simplified altitude state model and an apriori climb-cruise-descent flight profile has been developed and applied to determine minimum fuel and minimum cost trajectories for a helicopter flying a fixed range trajectory. The performance model is based on standard flight manual data and is such that on-line trajectory optimization is feasible with a relatively small computer. The results show that the optimal flight path and optimal cruise altitude can represent a 10 percent fuel saving on a minimum fuel trajectory. The optimal trajectories show considerable variability due to helicopter weight, ambient winds and the relative cost trade-off between time and fuel. In general, 'reasonable' variations from the optimal velocities and cruise altitudes do not significantly degrade the optimal cost.
Document ID
19830060744
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Slater, G. L.
(Cincinnati, University Cincinnati, OH, United States)
Erzberger, H.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 11, 2013
Publication Date
August 1, 1983
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 83-2140
Accession Number
83A41962
Funding Number(s)
CONTRACT_GRANT: NAG2-175
Distribution Limits
Public
Copyright
Other

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