FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering. Undercarriage comprises prop and two connecting links. Said prop comprises caisson with lower end with which articulated is the balance beam fitted thereat by means of king pin. Damper is arranged balance beam and caisson. Every connecting link has parallel axes of turn. Every connecting link is articulated with aircraft airframe and with said prop in parallel axes. Note here that one of said links is articulated with said prop by the pin extending through the end of balance beam king pin connected with caisson.
EFFECT: simple and reliable design.
3 cl, 9 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| AIRCRAFT MAIN LANDING GEAR WITH TWO BOBS ARTICULATED WITH AIRCRAFT AIRFRAME | 2011 |
|
RU2520266C1 |
| DEVICE TO DECREASE AIRCRAFT UNDERCARRIAGE LENGTH | 2009 |
|
RU2488523C2 |
| MAIN UNDERCARRIAGE OF AIRCRAFT LANDING GEAR | 2024 |
|
RU2824229C1 |
| AIRCRAFT UNDERCARRIAGE INCORPORATING DRIVE WITH BRACE, AND AIRCRAFT WITH SUCH UNDERCARRIAGE | 2006 |
|
RU2424948C2 |
| RETRACTABLE SKI LANDING GEAR FOR FLYING VEHICLE | 1984 |
|
RU1213659C |
| AIRCRAFT UNDERCARRIAGE SECTION FLAP CONTROL DEVICE | 2010 |
|
RU2527604C2 |
| AIRCRAFT UNDERCARRIAGE STRUT | 2005 |
|
RU2307046C2 |
| LANDING GEAR STEM FOR AIRCRAFT | 2012 |
|
RU2570614C1 |
| AIRCRAFT LANDING GEAR MAIN LEG | 2005 |
|
RU2297366C1 |
| AIRCRAFT RETRACTABLE LANDING GEAR LEG | 2014 |
|
RU2545239C1 |
