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Analytical design of a high performance stability and control augmentation system for a hingeless rotor helicopterA stability and control augmentation system (SCAS) was designed based on a set of comprehensive performance criteria. Linear optimal control theory was applied to determine appropriate feedback gains for the stability augmentation system (SAS). The helicopter was represented by six-degree-of-freedom rigid body equations of motion and constant factors were used as weightings for state and control variables. The ratio of these factors was employed as a parameter for SAS analysis and values of the feedback gains were selected on this basis to satisfy three of the performance criteria for full and partial state feedback systems. A least squares design method was then applied to determine control augmentation system (CAS) cross feed gains to satisfy the remaining seven performance criteria. The SCAS gains were then evaluated by nine degree-of-freedom equations which include flapping motion and conclusions drawn concerning the necessity of including the pitch/regressing and roll/regressing modes in SCAS analyses.
Document ID
19790034140
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Miyajima, K.
(NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
Aircraft Stability And Control
Report/Patent Number
AHS 78-27
Meeting Information
Meeting: In: American Helicopter Society, Annual National Forum
Location: Washington, DC
Start Date: May 15, 1978
End Date: May 17, 1978
Accession Number
79A18153
Distribution Limits
Public
Copyright
Other

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