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Control methods for aiding a pilot during STOL engine failure transientsCandidate autopilot control laws that control the engine failure transient sink rates by demonstrating the engineering application of modern state variable control theory were defined. The results of approximate modal analysis were compared to those derived from full state analyses provided from computer design solutions. The aircraft was described, and a state variable model of its longitudinal dynamic motion due to engine and control variations was defined. The classical fast and slow modes were assumed to be sufficiently different to define reduced order approximations of the aircraft motion amendable to hand analysis control definition methods. The original state equations of motion were also applied to a large scale state variable control design program, in particular OPTSYS. The resulting control laws were compared with respect to their relative responses, ease of application, and meeting the desired performance objectives.
Document ID
19770008106
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Nelson, E. R. (Stanford Univ. CA, United States)
Debra, D. B. (Stanford Univ. CA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1976
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-CR-149280
Accession Number
77N15049
Funding Number(s)
CONTRACT_GRANT: NSG-2100
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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