Helicopter anti-torque system using fuselage strakes

Details Helicopter anti-torque system using fuselage strakes Helicopter anti-torque system using fuselage strakes

1987-01-30

1987-11-24

Barefoot, Galen

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

244 91, B64C 506, B64C 2706

Patent

active

047083050

ABSTRACT:
A helicopter 10 with a system for controlling mainrotor torque which reduces the power and size requirements of conventional anti-torque means. The torque countering forces are generated by disrupting the main rotor downwash flowing around the fuselage. The downward flow is separated from the fuselage surface 11 by strakes 16 and 17 positioned at specified locations on the fuselage 11. These locations are determined by the particular helicopter wash pattern and fuselage configuration, generally being located 30.degree. before top dead center 21 and 30.degree. from bottom dead center 22 on the fuselage side to which the main rotor blade 12 approaches during rotation. The strakes 16 and 17 extend along the fuselage 11 from the cabin section 18 to the aft end and can be continuous or separated for aerodynamic surfaces such as a horizontal stabilizer 15.

REFERENCES:
patent: 2338935 (1944-01-01), Hafner
patent: 2674421 (1954-04-01), De Cenzo
patent: 2959373 (1960-11-01), Zuck
patent: 3540680 (1970-11-01), Peterson
patent: 3807662 (1974-04-01), Velazquez
patent: 4200252 (1980-04-01), Logan et al.
patent: 4227665 (1980-10-01), Carlson et al.
Brocklehurst et al., EPA #0099185, published 1/25/84.

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