NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Design of a helicopter autopilot by means of linearizing transformationsAn automatic flight control systems design methods for aircraft that have complex characteristics and operational requirements, such as the powered lift STOL and V/STOL configurations are discussed. The method is effective for a large class of dynamic systems that require multiaxis control and that have highly coupled nonlinearities, redundant controls, and complex multidimensional operational envelopes. The method exploits the possibility of linearizing the system over its operational envelope by transforming the state and control. The linear canonical forms used in the design are described, and necessary and sufficient conditions for linearizability are stated. The control logic has the structure of an exact model follower with linear decoupled model dynamics and possibly nonlinear plant dynamics. The design method is illustrated with an application to a helicopter autopilot design.
Document ID
19830002870
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Meyer, G. (NASA Ames Research Center Moffett Field, CA, United States)
Hunt, R. L. (NASA Ames Research Center Moffett Field, CA, United States)
Su, R. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1982
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-TM-84295
NAS 1.15:84295
A-9091
Accession Number
83N11140
Funding Number(s)
PROJECT: RTOP 505-34-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available