Abstract: The landing gear system for an aircraft includes a shock strut assembly that is coupled to the airframe with a universal joint. A tire member is mounted to the shock strut assembly. The landing gear system also includes a drag brace assembly coupled to an airframe of the aircraft with a spindle, the spindle being rotatable about a spindle axis. A radius rod is rotatably coupled to the airframe of the aircraft. The radius rod and the shock strut assembly are retractable about a retraction rotation axis. Further, the spindle axis has a common intersection point with the centerline axis and the retraction rotation axis. The orientation of the spindle axis causes a translation of the tire member to have a longitudinal component during a compression of the shock strut assembly.

Abstract: The landing gear system for an aircraft includes a shock strut assembly that is coupled to the airframe with a universal joint. A tire member is mounted to the shock strut assembly. The landing gear system also includes a drag brace assembly coupled to an airframe of the aircraft with a spindle, the spindle being rotatable about a spindle axis. A radius rod is rotatably coupled to the airframe of the aircraft. The radius rod and the shock strut assembly are retractable about a retraction rotation axis. Further, the spindle axis has a common intersection point with the centerline axis and the retraction rotation axis. The orientation of the spindle axis causes a translation of the tire member to have a longitudinal component during a compression of the shock strut assembly.

Abstract: A landing gear system includes a shock strut assembly and a linkage member coupled to an aircraft. Preferably, the shock strut assembly and linkage member are oriented or angled relative to one another in a non-parallel relationship. Actuation of the linkage member moves the shock strut from a de-hiked to a hiked configuration or vice-versa. In addition, the orientation of the linkage member relative to the shock strut assembly permits it to automatically move the shock strut assembly to the de-hiked position during retraction of the landing gear system and prevents the shock strut assembly from exceeding a desired length during retraction. The linkage member may take the form of a hydraulic actuator having a lower end portion coupled to an inner cylinder of the shock strut assembly and an upper end portion coupled to the aircraft aft of where the shock strut assembly is coupled to the aircraft.

Abstract: A landing gear system includes a shock strut assembly and a linkage member coupled to an aircraft. Preferably, the shock strut assembly and linkage member are oriented or angled relative to one another in a non-parallel relationship. Actuation of the linkage member moves the shock strut from a de-hiked to a hiked configuration or vice-versa. In addition, the orientation of the linkage member relative to the shock strut assembly permits it to automatically move the shock strut assembly to the de-hiked position during retraction of the landing gear system and prevents the shock strut assembly from exceeding a desired length during retraction. The linkage member may take the form of a hydraulic actuator having a lower end portion coupled to an inner cylinder of the shock strut assembly and an upper end portion coupled to the aircraft aft of where the shock strut assembly is coupled to the aircraft.