Abstract: An aircraft landing gear arrangement is provided comprising: a first landing gear portion comprising one or more wheels, a second landing gear portion, the first landing gear portion being rotatable with respect to the second landing gear portion; and a sensor for determining a rotational position of the first landing gear portion in relation to the second landing gear portion, the sensor comprising a first magnetic field generator operable to generate a magnetic field and a first magnetic field modulator for modulating said magnetic field, the sensor being operable to sense the magnetic field as modulated by the first magnetic field modulator, the first landing gear portion comprising the first magnetic field generator or the first magnetic field modulator, the second landing gear portion comprising the other of the first magnetic field generator and the first magnetic field modulator.

Abstract: An electronic device checks the pressure of an aircraft landing gear oleo by means of a camera capturing and processing an image of the oleo. An image recognition module processes the oleo image to extract a measure of the amount of extension of the oleo. This measure is then processed together with a measure of oleo temperature to calculate a pressure value representative of the expected pressure of the gas within the oleo, which can then be compared with another measurement of oleo pressure to determine whether the two are consistent or whether the oleo might be under- or over-filled with gas. The electronic device may be in the form of a hand-held smart phone or tablet device appropriately programmed with software.

Abstract: An aircraft landing gear arrangement comprises a nose landing gear assembly and at least one main landing gear assembly. The nose landing gear assembly has a nose landing gear wheel with a high energy brake apparatus therein. The main landing gear assembly has a main landing gear wheel with a high energy brake apparatus therein and a main landing gear wheel with a motor therein. The motor is used for driving the main landing wheel during taxiing of the aircraft.

Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Abstract: A method of landing an aircraft having wheels includes causing the aircraft to land in a manner that causes the wheels to have a spin-up phase on contact with the landing surface during landing. A braking force is applied immediately after the wheels touch the runway so as to reduce, or delay the start of, the spin-up of the wheels. The braking force is, for example, applied using the same braking system as used conventionally to decelerate the aeroplane on landing. The peaks, over time, of the vertical wheel to ground loads (LV) and the horizontal drag loads (LH) caused by friction between the tires of the wheels of the aircraft and the ground can be decoupled, or separated, such that the maximum total load,owing to the combination of the vertical loads (LV) and the drag loads (LH), sustained by the aircraft during landing is reduced (compared with peak 8).

Abstract: An aircraft landing gear arrangement comprises a nose landing gear assembly and at least one main landing gear assembly. The nose landing gear assembly has a nose landing gear wheel with a high energy brake apparatus therein. The main landing gear assembly has a main landing gear wheel with a high energy brake apparatus therein and a main landing gear wheel with a motor therein. The motor is used for driving the main landing wheel during taxiing of the aircraft.

Abstract: A pin bearing arrangement for use on an aircraft landing gear includes a pin and a load sensor arrangement, which may include strain gauges for measuring shear loads and accelerometers for measuring loads sustained by the pin. The pin includes a self-contained data logging device for logging data concerning loads sustained by the pin. Thus, inside the pin, there may be provided a processing unit, a memory store, and a battery-based power source. During normal operation of the aircraft fatigue loads may be monitored, the processing unit receiving input signals from the means for measuring loads and storing load data in the memory. The stored load data may periodically be extracted from the memory during maintenance of the aircraft.

Abstract: A pin bearing arrangement for use on an aircraft landing gear includes a pin and a load sensor arrangement, which may include strain gauges for measuring shear loads and accelerometers for measuring loads sustained by the pin. The pin includes a self-contained data logging device for logging data concerning loads sustained by the pin. Thus, inside the pin, there may be provided a processing unit, a memory store, and a battery-based power source. During normal operation of the aircraft fatigue loads may be monitored, the processing unit receiving input signals from the means for measuring loads and storing load data in the memory. The stored load data may periodically be extracted from the memory during maintenance of the aircraft.

Abstract: A method of landing an aircraft having wheels includes causing the aircraft to land in a manner that causes the wheels to have a spin-up phase on contact with the landing surface during landing. A braking force is applied immediately after the wheels touch the runway so as to reduce, or delay the start of, the spin-up of the wheels. The braking force is, for example, applied using the same braking system as used conventionally to decelerate the aeroplane on landing. The peaks, over time, of the vertical wheel to ground loads (LV) and the horizontal drag loads (LH) caused by friction between the tyres of the wheels of the aircraft and the ground can be decoupled, or separated, such that the maximum total load,owing to the combination of the vertical loads (LV) and the drag loads (LH), sustained by the aircraft during landing is reduced (compared with peak 8).

Abstract: A method of measuring load applied to a pin bearing and a pin bearing arrangement for use on an aircraft landing gear are provided. Relieving one or more of two adjacent bushes (4, 5, 6) bearing on a pin (1) of the pin bearing to create a zone of constant shear stress enables measurement of load and avoids cutting the pin.