A main orifice plate assembly may be configured to transition a multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The multi-actor damping system may be used in a shock strut assembly to alter a damping curve of the shuck strut assembly. The main orifice plate assembly may be a part of a main orifice assembly including an orbital cam. The main orifice plate may include a flow restrictor. The flow restrictor may be configured to retract or deploy in response to main orifice plate rotating about the orbital cam. The first damping actor configuration may correspond to a first damping curve. The second damping actor configuration may correspond to a second damping curve. The first damping curve being different than the second damping curve.

A position sensor system for a landing gear assembly includes a cylinder operatively coupled to an aircraft. Also included is a piston configured to translate within the cylinder. Further included is a pattern disposed on an outer surface of the piston. Yet further included is a scanner operatively coupled to the cylinder and positioned to optically detect the pattern during translation of the piston. Also included is a microprocessor in operative communication with the scanner and configured to receive data from the scanner for conversion to a quantity of movement of the piston relative to the cylinder.

A position sensor system for a landing gear assembly includes a cylinder operatively coupled to an aircraft. Also included is a piston configured to translate within the cylinder. Further included is a pattern disposed on an outer surface of the piston. Yet further included is a scanner operatively coupled to the cylinder and positioned to optically detect the pattern during translation of the piston. Also included is a microprocessor in operative communication with the scanner and configured to receive data from the scanner for conversion to a quantity of movement of the piston relative to the cylinder.

A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.

An aircraft landing gear assembly (112) including a shock absorber strut (114), a bogie (120), a link assembly (124), and a movement detector (132). The shock absorber strut includes an upper and a lower telescoping parts (118, 116), the upper part being connectable to the airframe of an aircraft and the lower part being connected to the bogie such that the bogie may adopt different pitch angles. The link assembly extends between the upper and lower telescoping parts, such that relative movement between the upper and lower telescoping parts causes relative movement between parts of the link assembly. The movement detector is arranged to detect movement of the link assembly relative to the bogie. The movement detector detects movement by sensing a change in linear displacement of, or angle between, one or more members.

An aircraft landing gear assembly (112) including a shock absorber strut (114), a bogie (120), a link assembly (124), and a movement detector (132). The shock absorber strut includes an upper and a lower telescoping parts (118, 116), the upper part being connectable to the airframe of an aircraft and the lower part being connected to the bogie such that the bogie may adopt different pitch angles. The link assembly extends between the upper and lower telescoping parts, such that relative movement between the upper and lower telescoping parts causes relative movement between parts of the link assembly. The movement detector is arranged to detect movement of the link assembly relative to the bogie. The movement detector detects movement by sensing a change in linear displacement of, or angle between, one or more members.

The landing gear systems, methods and apparatuses disclosed herein may comprise a shrink pump and a shrink valve that are capable of shrinking a landing gear by up to 40% of its available stroke, or more depending on the air spring configuration. The shrink pump may be configured to pump fluid (e.g., a hydraulic fluid) between an oil chamber, where hydraulic fluid is likely present and a shrink chamber to shrink the landing gear. Moreover, the shrink pump and shrink valve may be part of a strut shrink system.

The landing gear systems, methods and apparatuses disclosed herein may comprise a shrink pump and a shrink valve that are capable of shrinking a landing gear by up to 40% of its available stroke, or more depending on the air spring configuration. The shrink pump may be configured to pump fluid (e.g., a hydraulic fluid) between an oil chamber, where hydraulic fluid is likely present and a shrink chamber to shrink the landing gear. Moreover, the shrink pump and shrink valve may be part of a strut shrink system.

A system and various methods for monitoring and evaluating the health of a shock strut assembly are illustrated. Multiple sensors, including gas temperature, gas pressure, oil pressure, and position sensor, may be used to gather data and evaluate the performance of the shock strut assembly. Various methods illustrated herein may evaluate the dynamic damping, static load support, and/or controlled stroke performance of the shock strut assembly.

A system and various methods for monitoring and evaluating the health of a shock strut assembly are illustrated. Multiple sensors, including gas temperature, gas pressure, oil pressure, and position sensor, may be used to gather data and evaluate the performance of the shock strut assembly. Various methods illustrated herein may evaluate the dynamic damping, static load support, and/or controlled stroke performance of the shock strut assembly.