초록 ▼

A two-stage aircraft gear. The landing gear includes a cantilever landing gear whose lower end is attached to a trailing arm (or articulated) landing gear. The cantilever gear is a collapsible piston-cylinder assembly, and the trailing arm gear also has a shock absorber connected between a fixed por

A two-stage aircraft gear. The landing gear includes a cantilever landing gear whose lower end is attached to a trailing arm (or articulated) landing gear. The cantilever gear is a collapsible piston-cylinder assembly, and the trailing arm gear also has a shock absorber connected between a fixed portion of the trailing arm gear and the movable wheel support arm. When landing, the load imposed is first absorbed by the trailing arm landing gear. After the trailing arm gear has been fully compressed, the cantilever gear begins to compress. The cantilever and trailing arm landing gear can be combined to provide the desired performance. The landing gear static position can be designed to be in the static load curve of the first component, allowing the aircraft to be stably supported and yet difficult to overturn. Adjustable orifice plates contained within one or both of the cantilever and articulated stages can be controlled as a function of the vertical descent velocity and/or distance. If desired, differential pressure measurements within the two stages can be used to give the landing gear any desired damping and/or landing gear extension characteristic.

대표청구항 ▼

An adjustable landing gear for use with an aircraft, comprising, in combination: means for measuring a vertical descent velocity of said aircraft and producing a velocity signal in response thereto; a first strut having first and second ends defining a first axis, said first and second ends being se

An adjustable landing gear for use with an aircraft, comprising, in combination: means for measuring a vertical descent velocity of said aircraft and producing a velocity signal in response thereto; a first strut having first and second ends defining a first axis, said first and second ends being separated by a variable first distance, said first strut including means for receiving said velocity signal and controlling the rate at which said first distance varies as a first function of a first compressive force applied to said first strut along said first axis, said first strut being attachable to said aircraft at said first end; a trailing arm having an upper first end pivotally secured to said second end of said first strut; a wheel attached to a lower end of said trailing arm, said wheel being rotatable about a horizontal axis; and a second strut pivotally connected to said trailing arm and being pivotally supported through said second end of said first strut, said second end of said first strut and said connection of said second strut to said trailing arm defining a second axis and being separated by a variable second distance, said second strut being subjected to a second compressive force along said second axis, said second strut including means for receiving said velocity signal and controlling the rate at which said second distance varies as a second function of said second compressive force.