We used adaptive fuzzy sliding mode controller in fast variables system of aircraft super-maneuverable flight.

General dynamic model of aeroengine's rotor system during maneuvering flight

The general differential equations of motion of an unbalance flexible rotor system with multi-rigid-disk,multi-lumped-mass and multi-bearing are developed by using Lagrange s equation during any maneuvering flight which include three translational and three rotational components of the motion of the aircraft.

Inverse problem of helicopter flight dynamics, to solve control laws from given motion, is important to the study for the maneuvering flight and the design for the advanced flight control system.

Study of aerodynamic model for the maneuvering rotor;

Experiments of rotor wake distortion in pitching maneuvers;

The influence of the maneuver of aircrafts on the dynamic characteristics of SFD-rotor system in aircrafts was investigated.

And some maneuver flight simulations are calculated with the six-degree model.

This paper sets up the differential equations of motion of a Jeffcott rotor system with squeeze film damper (SFD) and investigates its dynamic performance under maneuver flight.

According to the principle of equal fatigue,creep and thermal impact damage,namely the amounts of main loading cycles,loading duration and the sequence of loading turns are equal in measured loading spectrum and composite loading spectrum,this paper derived an aeroengine s composite maneuver flight loading spectrum,which provides the basis of formulating accelerated mission test spectrum.