Presented is a procedure for improving the communication of requirements and specifications in the early design phases of an integrated helicopter/engine control system. The procedure is based on establishing a bound on a transfer matrix that relates blade cyclic and collective inputs to rotor speed variations. This bound becomes a new specification for the propulsion control system designer that embodies the mission-level performance goals of the helicopter. An example application of the procedure is provided for a Blackhawk/T700 system undergoing vertical accelerations from hover.
Integrated flight/propulsion control for helicopters
American Helicopter Society, Journal ; 39 , 3
1994-07-01
Miscellaneous
No indication
English
Integrated flight/propulsion control for helicopters
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