A Design Approach to Integrated Flight and Propulsion Control
831482
10/03/1983
- Event
- 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.
- 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.