FIELD: aviation.
SUBSTANCE: invention relates to a method of reducing vertical speed of helicopter landing in performance of landings from autorotation mode with switched off (failed) engines. To reduce the vertical touchdown speed, the kinetic energy of the helicopter movement and rotor rotation is used by means of dynamic braking of translational speed and increasing the total pitch before landing, during helicopter transition from autorotation mode to performing pre-landing manoeuvre, pitch angle is increased by 15–20° from balancing value, common pitch is installed on lower stop, main rotor is spin-up to 115–120 %, landing pitch angle is set, blasting is performed (sharp increase of common pitch) at height of 1.5–2 m (from ground to chassis) with rate of 6–10 degrees/s.
EFFECT: higher safety of landing in autorotation mode due to increased efficiency and thrust of rotor.
1 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD OF DETERMINING AND INDICATING ROTOR APPROXIMATION TO VORTEX RING CONDITIONS AT SINGLE-ROTOR HELICOPTER PRE-LANDING MANEUVERS | 2012 |
|
RU2486596C1 |
| METHOD OF DEAD-ENGINE LANDING OF HELICOPTER | 1989 |
|
RU2089457C1 |
| STARTING SYSTEM TO WARN ABOUT SINGLE-ROTOR HELICOPTER CRITICAL BEHAVIOUR | 2012 |
|
RU2497718C1 |
| METHOD OF MAINTENANCE OF NUMBER OF REVOLUTIONS OF HELICOPTER LIFTING ROTOR WITHIN PERMISSIBLE LIMITS AND DEVICE FOR REALIZATION OF THIS METHOD | 2001 |
|
RU2231479C2 |
| METHOD TO DECREASE ROTOR ANGLE OF ATTACK AT PRE-LANDING MANOEUVRES OF SINGLE ROTOR HELICOPTER (VERSIONS) | 2014 |
|
RU2539621C1 |
| SHUTDOWN ROTORCRAFT SAFE LANDING SYSTEM | 2023 |
|
RU2823617C1 |
| METHOD OF LANDING UNMANNED AERODYNAMIC FLYING VEHICLE | 2005 |
|
RU2278801C1 |
| VERTICAL TAKE-OFF AND LANDING AIRCRAFT | 2021 |
|
RU2805888C2 |
| FLIGHT DISPLAY SYSTEM AND COGNITIVE FLIGHT DISPLAY FOR SINGLE-ROTOR HELICOPTER | 2012 |
|
RU2497175C1 |
| ROTOR-CRAFT | 2016 |
|
RU2662339C2 |
