SELF-STABILISING HOVERCRAFT Russian patent published in 2011 - IPC B60V1/08 B64C39/12 

FIELD: transport.

SUBSTANCE: invention relates to transport facilities, particularly, to self-stabilising hovercraft. Hovercraft features canard configuration and comprises fuselage, front horizontal tail, primary tail wing, vertical tail with rudder and sustainers with propellers. Primary tail wing and front horizontal tail are arranged relative to center of masses with relation between arms L_tail/L_FGT=0.8÷1.2, where L_tail is tail wing arm, L_FGT is front horizontal tail arm so that distribution of lift forces between front horizontal tail and tail wing makes Y_FGT/Y_tail=0.8÷1.2, where Y_FGT is lift of front horizontal tail, Y_tail is lift of tail wing while absolute arm of front horizontal tail L_FGT is selected from the range L_FGT/b_{MAC FGT}=5÷2, where b_{MAC FGT} is mean aerodynamic chord of front horizontal tail; at elongation of front horizontal tail λ_FGT=2÷4 and elongation of primary tail wing λ_tail=3÷4 so that relation between lengths of mean aerodynamic chords of wing and front horizontal tail equals b_{MAC FGT}/b_{MAX tail}=0.95÷1.05, where b_{MAC tail} is mean aerodynamic chord of tail wing. Starting engines with screws may be arranged at fuselage nose section while sustainers with propellers may be arranged at fuselage tail section.

EFFECT: optimum configuration, reduced noise and higher payload.

2 cl, 2 dwg