INTEGRATED FLIGHT PROPULSION CONTROL FOR HELICOPTERS/

Presented is a procedure for improving the communication of requiremen ts and specifications in the early design phases of an integrated heli copter/engine control system. The procedure is based on establishing a bound on a transfer matrix, Delta(Omega U)(s), that relates blade cyc lic and collective inputs to rotor speed variations. This bound become s a new specification for the propulsion control system designer that embodies the mission-level performance goals of the helicopter. An exa mple application of the procedure is provided for a Blackhawk/T700 sys tem undergoing vertical accelerations from hover.