NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Integrated flight/propulsion control system design based on a decentralized, hierarchical approachA sample integrated flight/propulsion control system design is presented for the piloted longitudinal landing task with a modern, statistically unstable fighter aircraft. The design procedure is summarized. The vehicle model used in the sample study is described, and the procedure for partitioning the integrated system is presented along with a description of the subsystems. The high-level airframe performance specifications and control design are presented and the control performance is evaluated. The generation of the low-level (engine) subsystem specifications from the airframe requirements are discussed, and the engine performance specifications are presented along with the subsystem control design. A compensator to accommodate the influence of airframe outputs on the engine subsystem is also considered. Finally, the entire closed loop system performance and stability characteristics are examined.
Document ID
19910011824
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mattern, Duane (Sverdrup Technology, Inc., Brook Park OH., United States)
Garg, Sanjay (Sverdrup Technology, Inc., Brook Park OH., United States)
Bullard, Randy (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 89-3519
NASA-TM-103678
NAS 1.15:103678
E-5895
Meeting Information
Meeting: Guidance, Navigation and Control Conference
Location: Boston, MA
Country: United States
Start Date: August 14, 1989
End Date: August 16, 1989
Sponsors: AIAA
Accession Number
91N21137
Funding Number(s)
PROJECT: RTOP 505-62-50
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