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Influence of dynamic inflow on the helicopter vertical response

Author
Hindson, William S.
Published
Jun 1, 1986.
Physical Description
1 electronic document
Additional Creators
Chen, Robert T. N.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
A study was conducted to investigate the effects of dynamic inflow on rotor-blade flapping and vertical motion of the helicopter in hover. Linearized versions of two dynamic inflow models, one developed by Carpenter and Fridovich and the other by Pitt and Peters, were incorporated in simplified rotor-body models and were compared for variations in thrust coefficient and the blade Lock number. In addition, a comparison was made between the results of the linear analysis, and the transient and frequency responses measured in flight on the CH-47B variable-stability helicopter. Results indicate that the correlations are good, considering the simplified model used. The linear analysis also shows that dynamic inflow plays a key role in destabilizing the flapping mode. The destabilized flapping mode, along with the inflow mode that the dynamic inflow introduces, results in a large initial overshoot in the vertical acceleration response to an abrupt input in the collective pitch. This overshoot becomes more pronounced as either the thrust coefficient or the blade Lock number is reduced. Compared with Carpenter's inflow model, Pitt's model tends to produce more oscillatory responses because of the less stable flapping mode predicted by it.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19870015049.
Accession ID: 87N24482.
NASA-TM-88327.
A-86262.
NAS 1.15:88327.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15698496