Helicopters

Claim 2

An improved helicopter having increased deceleration comprising: a main sustaining rotor system; a pair of auxiliary rotors drivingly coupled to the sustaining rotor system and having adjustable pitch settings, said auxiliary rotors arranged to produce thrusts for control purposes; and a control means for adjusting the pitch settings of said auxiliary rotors to provide additive control thrust forces when driving torque is applied to said sustaining rotor system and to provide opposed thrust forces for absorbing power from said sustaining rotor system during deceleration of the helicopter thereby increasing the deceleration effect on the helicopter.

Claim 3

A helicopter as claimed in claim 1, where said main sustaining rotor system is a single main rotor and wherein said pair of auxiliary rotors are located adjacent the end of a rearwardly extending tail cone.

Claim 4

A helicopter as claimed in claim 2, wherein said pair of auxiliary rotors are supported laterally one on each side of said tail cone and arranged so that said control thrust forces comprise lateral thrust forces in a yaw direction.

Claim 5

A helicopter as claimed in claim 3, wherein the direction of the opposed thrust forces operative during deceleration is generally inwardly from each auxiliary rotor.

Claim 6

A helicopter as claimed in claim 3 including an auxiliary rotor differential pitch adjusting mechanism which is activated at the onset of zero torque to the sustaining rotor by electrical signals from a rotor speed governor and a yaw/heading control mechanism to adjust the pitch setting of the auxiliary rotors differentially to provide a net lateral thrust force in a desired yaw direction.

Claim 7

A helicopter as claimed in claim 5, wherein the yaw/heading control mechanism is controlled by rudder pedals incorporating a gearing mechanism operative to vary the yaw demand dependant on the actual collective pitch setting of the auxiliary rotors.

Claim 8

A helicopter as claimed in claim 6, wherein the gearing is phased-in automatically by an electrical signal generated by the yaw/heading control mechanism in response to a reference signal from the auxiliary rotor differential pitch adjusting mechanism.

Claim 9

A helicopter as claimed in claim 5 and including a manual inhibition system arranged to selectively isolate the tail rotor differential pitch adjusting mechanism.

Claim 10

An improved helicopter having increased deceleration comprising a fuselage including a rearwardly extending tail cone, a main sustaining rotor located above the fuselage for rotation about a generally vertical axis, an auxiliary rotor assembly located adjacent the rear end of the tail cone and comprising two auxiliary rotors supported laterally one on each side of the tail cone, said auxiliary rotors drivingly coupled to the main sustaining rotor and a control system arranged to adjust the pitch settings of the auxiliary rotors so that when driving torque is applied to the main sustaining rotor the auxiliary rotors provide additive lateral thrust forces for yaw control, whereas during deceleration the auxiliary rotors provide lateral thrust forces in generally opposed directions for absorbing power from said main sustaining rotor during deceleration of the helicopter to increase deceleration.

Claim 11

An improved helicopter having increased deceleration comprising a fuselage including a rearwardly extending tail cone, a main sustaining rotor located above the fuselage for rotation about a generally vertical axis, an auxiliary rotor assembly located adjacent the rear end of the tail cone and comprising two auxiliary rotors supported laterally one on each side of the tail cone, said auxiliary rotors drivingly coupled to the main sustaining rotor and a control system arranged to adjust the pitch settings of the auxiliary rotors so that when driving torque is applied to the main sustaining rotor the auxiliary rotors provide additive lateral thrust forces for yaw control, whereas during deceleration the auxiliary rotors provide lateral thrust forces in generally opposed directions for absorbing power from said main sustaining rotor during deceleration of the helicopter to increase deceleration.

Claim 12

A helicopter as claimed in claim 9, wherein the control system includes a differential pitch adjusting mechanism arranged to control the pitch setting of the two auxiliary rotors differentially to provide unequal lateral thrust forces in the generally opposed directions resulting in a variable net lateral thrust in one desired lateral direction.