Skid landing gear rotorcraft and rotorcraft having such CHASSIS

摘要

1.rotorcraft (21) containing u0444u044eu0437u0435u043bu00a0u0436 (22) and u043fu043eu043bu043eu0437u043au043eu0432u043eu0435 chassis (20), a u043fu043eu043bu043eu0437u044b (24, 25), the first longitudinal element (26) and the second u043fu043eu043fu0435u0440u0435u0447 a single element (27), the first and second connecting means designed u0434u043bu00a0 u0441u043eu0435u0434u0438u043du0435u043du0438u00a0 first transverse element u0444u044eu0437u0435u043bu00a0u0436u0435u043c, and one central third sock u0434u0438u043du0438u0442u0435u043bu044cu043du043eu0435 means (28).located u0434u043bu00a0 transfer of the second transverse element to the u0444u044eu0437u0435u043bu00a0u0436u0443 and vice versa, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 what;the first connecting means (30, 31) are the first two parts intended u0434u043bu00a0 u0440u0430u0437u043cu0435u0449u0435u043du0438u00a0 first transverse element (26) and u0434u043bu00a0 reliance on him, than the first connecting means to actively transmit u0443u0441u0438u043bu0438u00a0 first transverse element (26) to u0444u044eu0437u0435u043bu00a0u0436u0443 untilwhile u0434u0435u0444u043eu0440u043cu0430u0446u0438u00a0 first transverse element (26) u043eu0441u0442u0430u0435u0442u0441u00a0 less certain u0443u0440u043eu0432u043du00a0 deformation during u043fu0435u0440u0435u043au0430u0442u044bu0432u0430u043du0438u0438 or vertical sediment; and;the second connecting means (29, 32) contain two second parts intended u0434u043bu00a0 u0440u0430u0437u043cu0435u0449u0435u043du0438u00a0 first transverse element (26) and u0434u043bu00a0 reliance on him well, then and, when a degree of deformation of the transverse element reached or exceeded.with the second connecting means u043fu0440u043eu0445u043eu0434u00a0u0442 outside the first parts on both sides and u0441u0442u0430u043du043eu0432u00a0u0442u0441u00a0 active only when u0434u0435u0444u043eu0440u043cu0430u0446u0438u00a0 per the model of the cross element (26) reaches or exceeds a certain level of deformation.;2. rotorcraft for 1, in which the first transverse element (26) u00a0u0432u043bu00a0u0435u0442u0441u00a0 front longitudinal element u043fu0440u043eu0445u043eu0434u00a0u0449u0438u043c before the second longitudinal element om (27), which u00a0u0432u043bu00a0u0435u0442u0441u00a0 rear longitudinal element.;3. rotorcraft for 1, in which the coupling means to provide u0443u0433u043bu043eu0432u0443u044e rigidity in u043au0440u0435u043du0435, u043au043eu0442u043eu0440u0430u00a0 u0443u0432u0435u043bu0438u0447u0438u0432u0430u0435u0442u0441u00a0 increased precipitation (e) as a result of contact with the ground u0432u0437u0430u0438u043cu043eu0434u0435u0439u0441u0442u0432u0438u00a0 chassis (23).;4. rotorcraft for 1, in which the first part intended u0434u043bu00a0 u0440u0430u0437u043cu0435u0449u0435u043du0438u00a0 first transverse element (26) and u0434u043bu00a0 reliance on him, u0432u044bu043fu043e u043bu043du0435u043du044b u0432u0438u043bu043au043eu043eu0431u0440u0430u0437u043du044bu043cu0438 (43) or in the form of pillars (60, 61).;5. rotorcraft for 1, in which the second part of the intended u0434u043bu00a0 u0440u0430u0437u043cu0435u0449u0435u043du0438u00a0 first transverse element (26) and u0434u043bu00a0 reliance on him, u0432u044bu043fu043e u043bu043du0435u043du044b in the form of pillars (60, 61) or u0432u0438u043bu043au043eu043eu0431u0440u0430u0437u043du044bu043cu0438 (48).;6. rotorcraft for p.1 or 4, in which the first connecting means to contain the elastic strip element (47), u0441u0432u00a0u0437u0430u043du043du044bu0439 with each first pillar and interacting with it in the first the transverse element, u043eu0431u0435u0441u043fu0435u0447u0438u0432u0430u00a0 opportunity u0434u0432u0438u0436u0435u043du0438u00a0 this element vertically on the support and reliance, u0431u043bu0430u0433u043eu0434u0430u0440u00a0 elastic deformation band element so that u0441u043eu0445u0440u0430u043du00a0u0442u044c chassis in the place of his u0440u0430u0441u043fu043eu043bu043eu0436u0435u043du0438u00a0,when u043du0430u0445u043eu0434u0438u0442u0441u00a0 rotorcraft flight.;7. rotorcraft on any of the u043fu043f.1, 4 and 5, in which the coupling means consist of two parts (60, 61) located on the first transverse element, stories m u043au0430u0436u0434u0430u00a0 of these parts u043fu0440u0435u0434u0441u0442u0430u0432u043bu00a0u0435u0442 a dipped the profile on a surface (62a, 63a) of the first transverse element (26).;8. rotorcraft on p.7, in which the core part are located symmetrically on each side of the vertical median plane (33) u0432u0438u043du0442u043eu043a u043fu0435u0440u0435u0434u043du0435u0437u0430u0434u043du0435u0439 u0440u044bu043bu043eu0433u043e aircraft.;9. rotorcraft on any of the ap.1, 4 and 8, containing the two close to each other, the internal reference point (30, 31) located u0434u043bu00a0 transfer efforts from the first transverse element to the u0444u044eu0437u0435u043bu00a0u0436u0443 and vice versa. and two external reference points (29, 32) located u0434u043bu00a0 transfer efforts from the first transverse element to the u0444u044eu0437u0435u043bu00a0u0436u0443 only thenwhen the u0443u0441u0438u043bu0438u00a0 more certain u0437u043du0430u0447u0435u043du0438u00a0 (fo) or when the speed of the earth more than a u0437u043du0430u0447u0435u043du0438u00a0, and between each of the external u0440u0430u0441u0441u0442u043eu00a0u043du0438u0435 the anchor points and u043fu0435u0440u0435u0434u043du0435u0437u0430u0434u043du0435u0439 median plane (33) chassis more u0440u0430u0441u0441u0442u043eu00a0u043du0438u00a0 between each of the close to each other, the internal reference points and the plane.;10. rotorcraft for p.9, in which u0443u0433u043bu043eu0432u0430u00a0 rigidity in u043au0440u0435u043du0435 connecting means when u0444u044eu0437u0435u043bu00a0u0436 u043fu043eu043au043eu0438u0442u0441u00a0 first transverse element (26) of the chassis through the internal u043eu043fu043eu0440u043du044b x points (30, 31) at least approximately 10% less than the angular rigidity of the u043au0440u0435u043du0435 connecting means when u0444u044eu0437u0435u043bu00a0u0436 u043fu043eu043au043eu0438u0442u0441u00a0 first transverse element e chassis through external reference points (29, 32).;11. rotorcraft on any of the u043fu043f.1, 4, 5, 8 and 10, in which the first transverse element (26) has a moment of inertia u0441u0435u0447u0435u043du0438u00a0, u0438u0437u043cu0435u043du00a0u044eu0449u0438u0439u0441u00a0 along its length.;12. rotorcraft to p.11, in which the moment of inertia u0441u0435u0447u0435u043du0438u00a0 first transverse element (26) is smaller in the central part than in the two side of his u0447u0430u0441u0442u00a0u0445.;13. rotorcraft on p.12, in which the first transverse element u00a0u0432u043bu00a0u0435u0442u0441u00a0 a pipe.;14. rotorcraft for p.9, which u0432u0435u0440u0442u0438u043au0430u043bu044cu043du0430u00a0 rigidity connecting means when u0444u044eu0437u0435u043bu00a0u0436 u043fu043eu043au043eu0438u0442u0441u00a0 chassis through internal pillars data points (30, 31), at least 10% less than the vertical rigidity of the connecting means when u0444u044eu0437u0435u043bu00a0u0436 u043fu043eu043au043eu0438u0442u0441u00a0 chassis through external reference points (29, 32).;15. rotorcraft to 1 or 10, in which the second connecting means or the external reference point lie essentially in line with the u0434u0432u0443u043cu00a0 aggravate u043au043eu043du0441u0442u0440u0443u043au0446u0438u00a0u043cu0438 (37) forming part of the lower structure u0444u044eu0437u0435u043bu00a0u0436u0430.;16. rotorcraft on any of the u043fu043f.1, 4, 5, 8, 10 and 14, in which the chassis u00a0u0432u043bu00a0u0435u0442u0441u00a0 u0441u0432u0435u0440u0445u043au0440u0438u0442u0438u0447u0435u0441u043au0438u043c.;17. rotorcraft on p.10 or 14, a means u0434u043bu00a0 u0440u0435u0433u0443u043bu0438u0440u043eu0432u0430u043du0438u00a0 along an axis (34) of the first transverse element (26) of the reference points (29 to 32) u0444u044eu0437u0435u043bu00a0u0436 and against the transverse element (26).