A Design Approach to Integrated Flight and Propulsion Control

831482

10/03/1983

Event
Aerospace Congress and Exposition
Authors Abstract
Content
A decentralized, multivariable controls methodology is being developed for the functional integration of a fighter's aerodynamic controls with those of its propulsion system (inlet, engine, and thrust vectoring/reversing nozzle). Integrated controls account for, and take advantage of the significant cross-coupling between these system elements. A high-fidelity, six-degrees-of-freedom (6 DOF) aircraft simulation has been developed, incorporating advanced tactical fighter features such as variable cycle engines, variable geometry inlets, 2D-CD TV/TR nozzles, canards and a propulsive lift concept. A comprehensive evaluation test plan, including a piloted simulation, has been developed to validate this integrated-controls design methodology. Preliminary results show significant benefits of integrated control in terms of enhanced aircraft maneuverability, precise flight path control, reduced pilot workload, and fault tolerant system design.
Meta TagsDetails
DOI
https://doi.org/10.4271/831482
Pages
11
Citation
Joshi, D., Shaw, P., Hodgkinson, J., Rock, S. et al., "A Design Approach to Integrated Flight and Propulsion Control," SAE Technical Paper 831482, 1983, https://doi.org/10.4271/831482.
Additional Details
Publisher
Published
Oct 3, 1983
Product Code
831482
Content Type
Technical Paper
Language
English