Abstract: An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a front portion blended into and extending rearwardly from the leading edge of the fixed wing and the wing tip device.

Abstract: An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a rear portion with a concave surface, such that the fairing acts as a lift-generating surface when the aircraft is in flight.

Abstract: An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a rear portion with a concave surface, such that the fairing acts as a lift-generating surface when the aircraft is in flight.

Abstract: An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a front portion blended into and extending rearwardly from the leading edge of the fixed wing and the wing tip device.

Abstract: The design of the spray nozzle in an aerosol dispenser controls the characteristics of the spray that is produced. In a nozzle that comprises the elements of a multiplicity of inlet channels leading to a swirl chamber and an outlet orifice, the perception of wetness of a spray, such as an aqueous alcoholic deodorant spray, can be reduced by dimensioning the respective elements so that the sum of the widths of the inlet channels is less than the diameter of the swirl chamber and at least 1.5 times the diameter of the outlet orifice and the outlet orifice has a diameter of at least 0.3 mm together with the inlet channels being short, such as less than 0.5 mm. The new nozzle is especially suitable for spraying compositions having a low volatile organic carbon content and compositions comprising a significant proportion of water.

Abstract: The design of the spray nozzle in an aerosol dispenser controls the characteristics of the spray that is produced. In a nozzle that comprises the elements of a multiplicity of inlet channels leading to a swirl chamber and an outlet orifice, the perception of wetness of a spray, such as an aqueous alcoholic deodorant spray, can be reduced by dimensioning the respective elements so that the sum of the widths of the inlet channels is less than the diameter of the swirl chamber and at least 1.5 times the diameter of the outlet orifice and the outlet orifice has a diameter of at least 0.3 mm together with the inlet channels being short, such as less than 0.5 mm. The new nozzle is especially suitable for spraying compositions having a low volatile organic carbon content and compositions comprising a significant proportion of water.

Abstract: A marine backhoe dredge having a counterbalancing system that increases the hoisting capacity and hoisting speed of the backhoe. The device includes a backhoe mounted on a vessel and a counterbalancing system that includes an adjustable support structure, one or more cables operatively associated with the support structure and backhoe, and connected to a counterbalance such as a counterweight or a winch.

Abstract: Cosmetic composition for use in personal care applications comprising a carrier and a polymeric biguanide, characterised in that the polymeric biguanide is in the form of its salt with an organic acid containing from 4 to 30 carbon atoms.

Abstract: Cosmetic composition for use in personal care applications comprising a carrier and a polymeric biguanide, characterised in that the polymeric biguanide is in the form of its salt with an organic acid containing from 4 to 30 carbon atoms.

Abstract: An aerosol actuator is provided having an inner actuator chamber, an inner actuator chamber outlet by which the composition to be dispensed may exit the inner actuator chamber, and a stem piece channel by which the fluid to be dispensed may enter the inner actuator chamber. The inner surface of the inner actuator chamber is mathematically continuous. The mathematically continuous arrangement minimizes nozzle blockage in the actuator.

Abstract: A propellant driven deodorant composition for topical application to the human skin, comprising a deodorant active material comprising a cosmetically acceptable. polyhexamethylene biguanide salt, a cosmetically suitable vehicle comprising a short chain monohydric alcohol, and a non polar propellant composition having a Hildebrand Solubility Parameter of less than 14.5 MPa.sup.1/2, characterized in that the composition additionally comprises an effective amount of water.