Abstract: The invention relates to aircraft noise reduction apparatus, in particular, but not exclusively, to noise reduction apparatus on an aircraft landing gear. The aircraft noise reduction apparatus comprises a noise reduction attachment for a landing gear of an aircraft. The noise reduction apparatus is movable between a first position in which it deflects air away from a noise inducing component of the landing gear and a second position in which it allows access to the noise inducing component. The movement of the noise reduction attachment between the first and second positions is actuated by a part of the landing gear.

Abstract: An aircraft landing gear is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear, including inverting and fairing the nose-gear shock-absorbing leg, providing faired twin in-line oleos and providing fairings that produce shielding air curtains.

Abstract: An aircraft noise-reduction apparatus (10) for a landing gear (20) comprises a skeleton structure (14), which supports and acts to maintain the profile of a noise-reducing layer. The skeleton structure may comprise blades (16). The noise-reducing layer may have more than 10 apertures through which, in use, air can pass and may be in the form of a deformable mesh (12).

Abstract: An aircraft landing gear (1) is described including a noise-reducing element that includes an air-deflecting surface, in the form of a fairing (4), and a perforated airflow-reducing region (8). In use, some air passes through the perforations, whilst other air is deflected by the fairing away from a noise-generating region of the landing gear. Noise caused by the passing of the landing gear through the air is therefore reduced.

Abstract: An aircraft landing gear door assembly includes a door, which is moveable to an open position, in which an aperture is exposed, the landing gear being able to be deployed through said aperture, and moveable to a closed position, in which the door is closed across the aperture. The door is arranged for rotational movement of a first type, in which the door rotates about an axis that is substantially parallel to the length of the aircraft, between the closed position and the open position. The door is also arranged for movement of a second type, different from the first type, in which the door rotates, about an axis that is substantially transverse to the length of the aircraft, to a position in which it acts as a fairing to reduce the noise caused by the landing gear or a part thereof. In one embodiment, the second type of movement is rotational movement about an axis that is substantially parallel to the door when in the closed position and the door forms a ramp type fairing.

Abstract: An aircraft landing gear door assembly (1, 2, 3, 4, 5) includes a door (1), which is moveable to an open position, in which an aperture (6) is exposed, the landing gear (10) being able to be deployed through said aperture (6), and moveable to a closed position, in which the door (1) is closed across the aperture (6). The door (1) is arranged for rotational movement of a first type, in which the door rotates about an axis that is substantially parallel to the length of the aircraft, between the closed position and the open position. The door (1) is also arranged for movement of a second type, different from the first type, in which the door (1) rotates, about an axis that is substantially transverse to the length of the aircraft, to a position in which it acts as a fairing to reduce the noise caused by the landing gear or a part thereof.

Abstract: An aircraft landing gear 501 includes a folding side stay 502, wherein the folding side stay includes an integral locking mechanism and does not require the landing gear to include a lock stay. The lack of a lock stay reduces the airframe noise created by the aircraft, which is particularly significant when the aircraft is landing. The aircraft landing gear 501 is movable between an stowed and deployed position. The folding side stay 502 comprises a first section and a second section foldable relative to the first section. The integral locking mechanism 503 is arranged to lock the first section and second section of the folding side stay into position when the landing gear is in the deployed position.

Abstract: A method for connecting circuit elements within an integrated circuit for reducing single-event upsets is disclosed. The integrated circuit includes a first and second circuit elements that are substantially identical to each other. In order to reduce the single-event upsets to the first and second circuit elements, each of the first and second circuit elements is divided into a first sub-element and a second sub-element. The first sub-element of the first circuit element is connected to the second sub-element of the second circuit element. The second sub-element of the first circuit element is connected to the first sub-element of the second circuit element. As a result, the nodal spacings between the sub-elements within the first and second circuit elements are effectively increased without demanding additional real estate.

Abstract: A method includes precharging a first dynamic node, precharging a second dynamic node, and maintaining a first logic state of a signal on the first dynamic node responsive to a second logic state of a signal on the second dynamic node. The method further includes maintaining the second logic state of the signal on the second dynamic node responsive to the first logic state of the signal on the first dynamic node.