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US 4,531,692 AGranted
Helicopter flight control and transmission system
OwnerErnesto Mateusinventor
Life of this patent
Estimating the term…
Abstract
A helicopter flight control system which eliminates the need for a cyclic pitch control and a power transmission which automatically balances the reactive torque forces imparted by counter-rotating lift rotors is disclosed.
Claims12
A flight attitude control system for helicopters having horizontally disposed lift rotors mounted above the helicopter fuselage, comprising:
- a substantially vertically oriented airfoil, normally aligned parallel with the longitudinal axis of the helicopter and mounted to the helicopter above the lift rotor;
- pilot actuable means with said airfoil for deflecting said airfoil from its position about its vertical axis thereby inducing aerodynamic force upon said airfoil to control the helicopter's direction of flight;
- a horizontally oriented elevator, pivotally mounted to the helicopter and horizontally displaced from the center of gravity of the helicopter for controlling the pitch of the helicopter;
- means with said elevator for selectively deflecting said elevator about the horizontal axis of said pivotal mounting;
- a horizontally disposed, variable pitch rotor mounted to the helicopter and horizontally displaced from the center of gravity of the helicopter for controlling the pitch of the helicopter;
- pilot actuable means with said horizontal rotor for selectively varying the pitch of said horizontal rotor;
- pilot stick control means, associated with said pitch varying means and elevator deflecting means, for actuating said elevator deflector means and said horizontal rotor pitch varying means, wherein slight to moderate deflection of said stick means causes said elevator means only to be actuated, and full or extreme deflection of said stick means causes both said elevator deflecting means and said horizontal rotor pitch varying means to be actuated.
4 more elements
A flight attitude control system for helicopters having horizontally disposed lift rotors mounted above the helicopter fuselage, comprising:
- a substantially vertically oriented airfoil, normally aligned parallel with the longitudinal axis of the helicopter and mounted to the helicopter above the lift rotor;
- pilot actuable means with said airfoil for deflecting said airfoil from its position about its vertical axis thereby inducing aerodynamic force upon said airfoil to control the helicopter's direction of flight;
- a horizontally disposed, variable pitch rotor mounted to the helicopter and horizontally displaced from the center of gravity of the helicopter for controlling the pitch of the helicopter;
- pilot actuable means with said horizontal rotor for selectively varying the pitch of said horizontal rotor;
- a vertically disposed, variable pitch rotor, mounted to the helicopter and horizontally displaced from the center of gravity of the helicopter for controlling the yaw of the helicopter;
- pilot actuable means with said vertical rotor for selectively varying the pitch of said vertical rotor;
- a vertically oriented rudder, pivotally mounted to the helicopter and horizontally displaced from the center of gravity of the helicopter for controlling the yaw of the helicopter;
- means with said rudder for selectively deflecting said rudder about the vertical axis of said pivotal mounting;
- and
- pilot pedal control means associated with said vertical rotor pitch varying means and with said vertical rudder deflection means, for actuating said rudder deflection means and said vertical rotor pitch varying means, wherein slight to moderate deflection of said pedal means causes said rudder deflection means to be actuated, and full to extreme deflection of said pedal means causes both said rudder deflection means and said vertical rotor pitch varying means to be actuated.
7 more elements
Dependencies are inferred from the claim text.