Abstract: An aircraft landing gear is disclosed including a main leg, a foldable stay and a lock link configured to hold the foldable stay in position when the landing gear is extended. The foldable stay includes a first stay member and a second stay member, and the landing gear is configured such that the second stay member rotates in a first direction from a first position to a second position as the landing gear moves from a retracted configuration to an extended configuration. An end stop is arranged such that in the event the lock link fails, the second stay member rotates in the first direction from the second position to a third position in which the stay contacts the end stop thereby preventing further movement of the second stay member in the first direction and wherein the foldable stay goes over centre as the second stay member moves from the first position to the third position.

Abstract: A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. Travel of the separator piston beyond a certain position is indicative of a fault. The accumulator includes a snubbing device that acts to slow movement of the separator piston beyond that position. A monitoring system measures the time taken for the movement of the landing gear part effected by the hydraulic actuator. If the measured time is longer than a threshold time, that is indicative of a possible fault in the accumulator, that might, without the snubbing, remain undetected and/or hidden from view.

Abstract: A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. Travel of the separator piston beyond a certain position is indicative of a fault. The accumulator includes a snubbing device that acts to slow movement of the separator piston beyond that position. A monitoring system measures the time taken for the movement of the landing gear part effected by the hydraulic actuator. If the measured time is longer than a threshold time, that is indicative of a possible fault in the accumulator, that might, without the snubbing, remain undetected and/or hidden from view.

Abstract: An apparatus for determining the position of a target object using a two-channel monopulse radar. The radar may include two transmitting antennas and one common receiving antenna disposed in a coplanar arrangement. The transmitting antennas may be positioned on the focal plane of the radar along a focal plane axis that extends through, and that is perpendicular with, a boresight axis of the radar. The transmitting antennas may be spaced apart from one another in a first dimension a distance equal to about one half of one wavelength of the radar's center operating frequency. One of the transmitting antennas may be squinted at an angle of ?1 relative to the boresight axis and the other transmitting antenna may be squinted at an angle of ?2 relative to the boresight axis in a second dimension. The transmitting antennas are not squinted relative to one another in the first dimension.

Abstract: An apparatus for determining the position of a target object using a two-channel monopulse radar. The radar may include two transmitting antennas and one common receiving antenna disposed in a coplanar arrangement. The transmitting antennas may be positioned on the focal plane of the radar along a focal plane axis that extends through, and that is perpendicular with, a boresight axis of the radar. The transmitting antennas may be spaced apart from one another in a first dimension a distance equal to about one half of one wavelength of the radar's center operating frequency. One of the transmitting antennas may be squinted at an angle of ?1 relative to the boresight axis and the other transmitting antenna may be squinted at an angle of ?2 relative to the boresight axis in a second dimension. The transmitting antennas are not squinted relative to one another in the first dimension.