Abstract: 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 device extending laterally from the shock absorber tube and comprising a mounting pin connected to a floor fitting provided at the inner floor.

Abstract: A non-retractable wheel-type landing gear for a rotorcraft, comprising: at least one wheel; a shock absorber with a circumferential direction, which is connected to the at least one wheel and comprises a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; a mounting arm extending laterally from the shock absorber tube, the mounting arm being integrally formed with the shock absorber tube and adapted for attachment to a first fitting of a rotorcraft; and a link fixation extending laterally from the shock absorber tube, the link fixation being arranged in the circumferential direction of the shock absorber at an angle in a range from 45° to 120° with respect to the mounting arm and adapted for connection to a second fitting of the rotorcraft.

Abstract: A non-retractable wheel-type landing gear for a rotorcraft, comprising: at least one wheel; a shock absorber with a circumferential direction, which is connected to the at least one wheel and comprises a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; a mounting arm extending laterally from the shock absorber tube, the mounting arm being integrally formed with the shock absorber tube and adapted for attachment to a first fitting of a rotorcraft; and a link fixation extending laterally from the shock absorber tube, the link fixation being arranged in the circumferential direction of the shock absorber at an angle in a range from 45° to 120° with respect to the mounting arm and adapted for connection to a second fitting of the rotorcraft.

Abstract: 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 device extending laterally from the shock absorber tube and comprising a mounting pin connected to a floor fitting provided at the inner floor.

Abstract: 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.

Abstract: The present invention relates to a control method for inflating at least one float of a buoyancy system. During a mode (MOD1) of automatic inflation in flight, calculation means determine whether a predetermined ditching condition is true during a step (STP1) of predicting a forthcoming impact. During a step (STP2) of characterizing said impact, at least one predicted component of a ditching speed is determined. During an automatic inflation step (STP3), each float is automatically inflated in flight when at least said ditching condition is true and when each determined predicted component is less than a corresponding speed threshold.

Abstract: The present invention relates to a control method for inflating at least one float of a buoyancy system. During a mode (MOD1) of automatic inflation in flight, calculation means determine whether a predetermined ditching condition is true during a step (STP1) of predicting a forthcoming impact. During a step (STP2) of characterizing said impact, at least one predicted component of a ditching speed is determined. During an automatic inflation step (STP3), each float is automatically inflated in flight when at least said ditching condition is true and when each determined predicted component is less than a corresponding speed threshold.

Abstract: An energy absorber system (10) provided with a shock absorber (11) extending from a first end (12) suitable for being connected to a rocker arm (5) of an undercarriage (3) housed in a wheel bay (4), towards a second end (13). In addition, the system includes a fitting (20) connected to said second end (13), and guide means (30) for guiding said fitting (20) in translation that is suitable for being fastened to a flank (4?) of said wheel well (4), said system (10) including deformable energy absorber means (40) fastened to said fitting (20) and suitable for being fastened to a structure (4?) of said bay (4) and also to fusible retention means (50) suitable for fastening said fitting (20) to said flank (4?), said fusible retention means (50) rupturing from a predetermined threshold in order to allow said fitting (20) to move under guidance from said guide means (30) so as to deform said energy absorber means (40).

Abstract: An energy absorber system (10) provided with a shock absorber (11) extending from a first end (12) suitable for being connected to a rocker arm (5) of an undercarriage (3) housed in a wheel bay (4), towards a second end (13). In addition, the system includes a fitting (20) connected to said second end (13), and guide means (30) for guiding said fitting (20) in translation that is suitable for being fastened to a flank (4?) of said wheel well (4), said system (10) including deformable energy absorber means (40) fastened to said fitting (20) and suitable for being fastened to a structure (4?) of said bay (4) and also to fusible retention means (50) suitable for fastening said fitting (20) to said flank (4?), said fusible retention means (50) rupturing from a predetermined threshold in order to allow said fitting (20) to move under guidance from said guide means (30) so as to deform said energy absorber means (40).