Abstract: A steerable auxiliary nose undercarriage (2) for a rotary wing aircraft (1); the undercarriage (2) being retractable substantially rearwards. In the undercarriage (2), an oscillating system (13) presents a elevation stroke (58) about its hinged front end (52) that is greater than a shock absorbing stroke (59), and a shock-absorbing actuator (9) possesses retraction means for going beyond a high abutment position of the oscillating system (13) so that the oscillating system (13) and the shock-absorbing actuator (9) provide both a shock-absorption function and an undercarriage retraction function.

Abstract: A rotary wing aircraft (1) such as a helicopter comprises a force-transmission structure (5) for transmitting forces, in particular those coming from an undercarriage (2), and that, in longitudinal elevation view, presents an L-shape in which the arrangement (6, 19-21) forms a transversely centered box (6), such that the structure (5) transfers the forces, at least in part, to top and bottom working covering segments of the fuselage.

Abstract: A steerable auxiliary nose undercarriage (2) for a rotary wing aircraft (1); the undercarriage (2) being retractable substantially rearwards. In the undercarriage (2), an oscillating system (13) presents a elevation stroke (58) about its hinged front end (52) that is greater than a shock absorbing stroke (59), and a shock-absorbing actuator (9) possesses retraction elements for going beyond a high abutment position of the oscillating system (13) so that the oscillating system (13) and the shock-absorbing actuator (9) provide both a shock-absorption function and an undercarriage retraction function.

Abstract: A helicopter moving device has a lever arm, a helicopter support arm to attach to a helicopter, and a wheel mounted to the lever arm, such that applying downward pressure to the lever arm causes a corresponding upward movement of the helicopter support arm about a pivot point. In this manner, the helicopter may be moved from place to place along the ground. The helicopter moving device is lightweight, capable of being disassembled, self propelled (does not require external power source) and portable.

Abstract: A remotely controlled movably powered shuttle frame has foundation pads attached thereto at all four corner portions for separating skid pads of a helicopter from the flight deck of a marine vessel, wherein both the skid pads and the fight deck are outfitted with hook and loop fabrics. Skid blades displaced from retracted positions underlying the foundation pads are extended from the shuttle frame underlying a landed aircraft whose weight has been lifted off the flight deck by lifting arms pivotally mounted on the foundation pads. The aircraft carried by the lifting arms on the shuttle frame after the skid blades are retracted is shuttled by wheeled movement of the shuttle frame to a desired location on the flight deck.

Abstract: A skid landing gear for a helicopter, in which the directional stiffnesses of the cross members of the skid landing gear have been de-coupled from one another, such that optimization of the longitudinal stiffniess of the cross members may be performed independently of the optimization of the vertical stiffniess and fatigue life of the cross members. In order to de-couple the stiffnesses in the skid type landing gear, two approaches are employed. In the first approach, the skid landing gear has non-symmetric-section cross members and/or distribution of different materials within the cross-section for de-coupling the vertical stiffness of the cross members from the longitudinal stiffness, such that placement of the ground resonance frequency may be optimized, while retaining the vertical stiffness properties essential for optimizing vertical energy attenuation and fatigue life.

Abstract: Inflation of impact absorbing bags is effected on a portable platform positioned on an emergency landing zone after jettisoning of damaged landing gear from a helicopter fuselage. The impact absorbing bags when inflated form a cradle shape conforming to the bottom of the helicopter fuselage.

Abstract: A skid landing gear for a helicopter, in which the directional stiffnesses of the cross members of the skid landing gear have been de-coupled from one another, such that optimization of the longitudinal stiffness of the cross members may be performed independently of the optimization of the vertical stiffness and fatigue life of the cross members. In order to de-couple the stiffnesses in the skid type landing gear, two approaches are employed. In the first approach, the skid landing gear has non-symmetric-section cross members and/or distribution of different materials within the cross-section for de-coupling the vertical stiffness of the cross members from the longitudinal stiffness, such that placement of the ground resonance frequency may be optimized, while retaining the vertical stiffness properties essential for optimizing vertical energy attenuation and fatigue life.

Abstract: A skid landing gear for a helicopter, in which the directional stiffnesses of the cross members of the skid landing gear have been de-coupled from one another, such that optimization of the longitudinal stiffness of the cross members may be performed independently of the optimization of the vertical stiffness and fatigue life of the cross members. In order to de-couple the stiffnesses in the skid type landing gear, two approaches are employed. In the first approach, the skid landing gear has non-symmetric-section cross members and/or distribution of different materials within the cross-section for de-coupling the vertical stiffness of the cross members from the longitudinal stiffness, such that placement of the ground resonance frequency may be optimized, while retaining the vertical stiffness properties essential for optimizing vertical energy attenuation and fatigue life.