Abstract: Method and system of determining ground-to-tire friction coefficient for an aircraft landing event. The method uses an aircraft computational model to repeatedly model the landing event, varying one or more initial conditions of the aircraft model until a best match between a modelled value and a provided value of aircraft vertical acceleration is determined. The method uses initial conditions associated with the best match of modelled and provided vertical acceleration values and a strain value from a sensor on the aircraft landing gear, with the ground-to-tire friction coefficient is a variable. The method models the landing gear to generate a modelled strain value and compares this with the measured strain value, and repeats the landing gear modelling step with a different value for the ground-to-tire friction coefficient until a best match between the modelled strain value and the measured strain value is determined and outputting the respective friction coefficient value.

Abstract: An aircraft spring assembly includes a helical spring having a hollow core. A polymer damping member is confined within the core and is narrower than the internal spring diameter so as to be free to move along the core.

Abstract: A landing gear assembly having a first part movable relative to a second part, and a spring coupled to the first and second parts via first and second anchor points. A lost motion assembly is provided to enable one of the anchor points to translate along one of the parts. As such, the spring extends less as the first part moves relative to the second part than it would if each anchor point was fixed to a respective part.

Abstract: An aircraft landing gear includes an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on the axle and arranged to define a brake rod connection point that is distinct from a conventional brake rod connection point defined by the brake assembly. The adaptor member is coupled to the brake assembly via an adaptor linkage that is arranged to react brake torque but arranged to permit relative movement between the adaptor member and the brake assembly in degrees of freedom which are not required to react brake torque.

Abstract: A landing gear assembly 10 having first and second parts 12b, 14b movably mounted with respect to one another. The landing gear assembly includes a critical space 32. A spring assembly 26 is arranged to bias the first and second parts to move relative to one another. A spring support 30 is provided to inhibit a broken portion of the spring assembly entering or contacting the critical space following a spring failure.

Abstract: A brake assembly for a vehicle comprising a wheel comprising a hollow section and a rim, the rim comprising a first portion comprising an electrically conductive material and a second portion adjacent to the first portion comprising a plurality of a permanent magnets and a stator comprising at least one electromagnetic coil arranged to be located within the hollow section of the wheel, wherein the stator is moveable between a first position in which the at least one electromagnetic coil is inductively coupled to the first portion of the rim when the wheel is rotating relative to the stator, and a second position in which the at least one electromagnetic coil is inductively coupled to the second portion of the rim.

Abstract: An aircraft assembly including a first part having a pin and a second part having a hook that is movable in an engagement plane to engage the pin to hold the first part in a condition relative to the second part. The pin has a prominent central portion and one or more axially spaced outer portions, the prominent portion is prominent with respect to the outer portions in the engagement plane to cause contact to be made between the hook and the pin within the central portion of the pin, rather than the outer portions of the pin.

Abstract: An oleo-pneumatic shock absorber having a casing, a rod slidably mounted in the casing, first and second fluids in the casing, and a gauge. The gauge has a substrate positioned on the shock absorber. The substrate has a first region with a slot sized to fit an ultrasonic transducer arranged to encompass a range of possible oil levels within the shock absorber, a second region corresponding to a range of possible extension states of the shock absorber and a third region comprising one or more traces. Each trace corresponds to a temperature value and is indicative of an optimum relationship between the oil levels and the range of extension states at the respective temperature value associated with the trace.

Abstract: A landing gear for an aircraft having a main fitting arranged to be coupled to the aircraft and arranged to move between a stowed condition and a deployed condition and a trailing arm movably coupled to the main fitting. A torsion spring is coupled to the trailing arm such that the movement of the trailing arm causes torsion loading of the torsion spring. A stay assembly is provided which comprises the torsion spring, the stay assembly having a first condition in which it is arranged to react axial loading thereof so as to maintain the main fitting in the deployed condition and a second condition in which it is arranged to permit the main fitting to move between the stowed condition and the deployed condition.