Rotorcraft with a non-retractable wheel-type landing gear
A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin extending from the shock absorber tube toward a floor fitting provided at the inner floor, wherein the mounting pin is connected to the floor fitting.
1. A rotorcraft with a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one lower fuselage compartment is equipped with a floor fitting provided at the inner floor and at least two lateral fittings, and wherein the at least one lower fuselage compartment is at least accessible via an opening formed in the lower shell, the rotorcraft comprising:
at least one non-retractable wheel-type landing gear rigidly attached in the at least one lower fuselage compartment and extending at least partly through the opening formed in the lower shell, comprising:
at least one wheel;
a shock absorber connected to the at least one wheel, comprising:
a shock absorber tube, and
a shock absorber rod telescopically mounted to the shock absorber tube;
at least two mounting arms extending laterally from the shock absorber tube toward the at least two lateral fittings in the at least one lower fuselage compartment, wherein the at least two mounting arms are mounted to the at least two lateral fittings; and
a mounting pin extending from the shock absorber tube toward the floor fitting provided at the inner floor, wherein the mounting pin is connected to the floor fitting.
2. The rotorcraft of claim 1 , further comprising a fixation unit mounted to the floor fitting, wherein the mounting pin is mounted to the fixation unit.
3. The rotorcraft of claim 2 ,
wherein the mounting pin is mounted with a predetermined play in transverse direction of the fuselage to the fixation unit.
4. The rotorcraft of claim 2 ,
wherein the mounting pin is mounted free of play in longitudinal direction of the fuselage to the fixation unit.
5. The rotorcraft of claim 2 ,
wherein the fixation unit comprises a socket that is rigidly attached to the inner floor, preferably by means of screws.
6. The rotorcraft of claim 5 ,
wherein the fixation unit comprises a spherical bearing mounted to the mounting pin.
7. The rotorcraft of claim 6 ,
wherein the mounting pin comprises an associated length axis and is slidable within the spherical bearing in direction of the associated length axis.
8. The rotorcraft of claim 6 ,
wherein the fixation unit comprises a sliding block housing the spherical bearing.
9. The rotorcraft of claim 8 ,
wherein the sliding block is mounted to the socket with a predetermined play in transverse direction of the fuselage and/or free of play in longitudinal direction of the fuselage.
10. The rotorcraft of claim 2 ,
wherein the fixation unit comprises a cover that covers the fixation unit on a side pointing away from the shock absorber.
11. The rotorcraft of claim 1 , further comprising a seal arranged between the floor fitting and an axial end of the shock absorber tube.
12. The rotorcraft of claim 1 ,
wherein the mounting pin is integrally formed with the shock absorber tube.
13. The rotorcraft of claim 1 ,
wherein the shock absorber tube comprises a mounting lug, and wherein the mounting pin is rigidly mounted to the mounting lug.
14. The rotorcraft of claim 12 ,
wherein the shock absorber tube comprises a first length axis, wherein the mounting pin comprises a second length axis, and wherein the first and second length axes are congruent.
15. The rotorcraft of claim 12 ,
wherein the shock absorber tube comprises a first length axis, wherein the mounting pin comprises a second length axis, and wherein the first and second length axes are arranged in parallel.