Hucker, Nerys

An aircraft has an energy storage system comprising a first battery 6a comprising first and second battery modules 10, 11. A venting system 7 is provided comprising a first battery module exhaust 18, a second battery module exhaust 19 and a first battery manifold 20 arranged to connect the first and second battery module exhausts to a first flow path extending to an exhaust port 8 of the aircraft. The first battery manifold 20 includes a first valve 28 comprising a first flap 29 having a first position in which fluid flow from one of the first and second battery module exhausts is restricted; a second position in which fluid flow from the other of the first and second battery module exhausts is restricted; and a neutral position in which fluid can flow from both first and second battery module exhausts to the first flow path. The first valve 28 is biassed towards the neutral position. The venting system of the present invention is more lightweight than was hitherto achievable, protects other modules and components of the energy storage system from the heat of gas emissions and reduces pressure losses, so that the emitted gas is more likely to exit the aircraft, typically via a burst disc

The invention relates to a latch mechanism 12 for locking an aircraft folding wing. The mechanism comprises at least one lug 13, 14 having an aperture 15a-15f and a latch pin 16 moveable within the aperture between a latched configuration in which the latch pin is received in the aperture, and an unlatched configuration in which the latch pin is withdrawn from the aperture. At least part of one of the pin 16 and the aperture 15a-15f has a hydrophobic coating. A hydrophobic coating may be applied to all apertures in the mechanism and/or to the latch pin. The provision of a hydrophobic coating helps to prevent the formation of moisture and hence ice on the latch pin and/or in the aperture, which ice can inhibit the pin from moving along the aperture into and out of its latching position.

Zusammenfassung wird geladen …

An aircraft wing structure comprises first and second unitary shell structures 7, 8, preferably formed from a fibre-reinforced composite material. Each shell structure 7, 8 comprises a partial front spar, a partial rear spar and a wing skin. The partial front spars of each shell structure and the partial rear spars of each shell structure are arranged to overlap to form front and rear spars respectively. A wing box structure 6 constructed according to the invention is lightweight, strong and durable, with a lower overall part count than has been conventionally achievable. Aircraft systems equipment may be attached to the shell structures 7, 8 prior to, or after, assembly into a wing box.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …