Abstract: A box-structure airfoil is constructed of a composite material uppers skin, a composite material lower a skin 12 and a spar. Ribs and an elongate projection are formed integrally on the inner surface of each of the two skins. The upper and lower skins and the spar are simultaneously bonded by an adhesive to form a single structure. Since the ribs and the elongate projection are one-piece formed with each skin, it is possible to reduce the number of principal constituent components. Furthermore, since assembly operation is made by using the adhesive, there is no need for fasteners or the like for assembling. Moreover, the flanges on both sides of the spar can also be bonded to the respective skins. According to the invention, it is possible to reduce the number of principal constituent components and that of assembling components of an airfoil, thereby achieving its cost reduction.

Abstract: A box-structure airfoil is constructed of a composite material upper skin, a composite material lower skin 12 and a spar. Ribs and an elongate projection are formed integrally on the inner surface of each of the two skins. The upper and lower skins and the spar are simultaneously bonded by an adhesive to form a single structure. Since the ribs and the elongate projection are one-piece formed with each skin, it is possible to reduce the number of principal constituent components. Furthermore, since assembly operation is made by using the adhesive, there is no need for fasteners or the like for assembling. Moreover, the spar is bonded not only to Moreover, because not only a web but also flanges on both sides of the spar are bonded to the respective skins, it is possible to obtain a large strength. According to the invention, it is possible to reduce the number of principal constituent components and that of assembling components of an airfoil, thereby achieving its cost reduction.

Abstract: A box-shaped fibrous preform is produced by laying or superposing a plurality of reinforcing fibrous material layers (6a) on top of each other into a box-like shape. The box-shaped fibrous preform is used as an auxiliary member (1) or by cutting the box-like member into segments of a required shape. The auxiliary member (1) is combined with reinforcing fibrous material forming a main structural member. The auxiliary member and the main structural member are placed in a mold and a resin is supplied into the mold to carry out a resin-impregnating and curing operation.

Abstract: The present invention is drawn to an improvement in the configuration of an inner lining plate of an aircraft fuselage wall, which will result in the sound transmission loss (TL) of the inner lining plate to occur in a frequency range covering the frequencies of external noises such as propeller sound, such that external noises transmitted from the inside of the aircraft fuselage can be reduced. The improvement resides in that a tensile rigidity in the circumferential direction of a substantially cylindrical fuselage wall inner lining plate is less than the tensile rigidity in the axial direction thereof. In this respect, the inner lining plate is provided with a large number of parallel crests extending in the axial direction.

Abstract: The apparatus includes a pair of molds each having a peripheral flange provided with a mating surface. The molds are clamped by a suitable number of clamp assemblies for clamping the flanges of the molds so that the molds are secured together with the mating surfaces in contact with each other. The clamp assembly includes a pair of clamp members for engagement with the flanges of the molds, a shaft passing through the clamp members, a first stop member provided on the shaft for engagement with one of the clamp members, a spacer provided on the shaft for axial slidable movement and adapted for engagement with the other of the clamp members, a second stop member provided on the shaft for engagement with the spacer at an end opposite to the other of the clamp members.

Abstract: A cyclone separator including a cylindrical vessel having a tangentially extending inlet at one axial end and a tangentially extending outlet at the other axial end so that fluid is introduced into the vessel from the inlet and produces a swirl flowing to the outlet. A capturing groove is formed around the vessel and opened to the vessel through a gap. A fluid passage is provided to extend from the groove to the axial center of the vessel so that a circulating flow is produced from the groove through the fluid passage to the axial center of the vessel. The portion of the fluid having a high concentration of a substance of a different density is therefore drawn from the area adjacent to the inner wall surface of the vessel to the groove and the substance is captured by the groove.

Abstract: A mixing chamber for an air-conditioning system including a cylindrical vessel having a plurality of inlet ports provided at an axial end portion for introducing cool air from an air-conditioning unit and warm air from passenger compartments. The vessel is further provided at the other axial end portion with outlet ports. The inlet and outlet ports are oriented in a tangential direction with respect to the vessel to thereby form a spiral air flow in the vessel. The vessel has a water capturing ring located along the inner wall surface of the vessel to prevent film of water on the inner wall surface of the vessel from flowing toward the outlet ports. A water drawing slit is formed in the vessel to open to the inner wall surface at a side of the water capturing ring adjacent to the inlet ports to discharge the water accumulated at this side of the ring.

Abstract: An apparatus for measuring the remaining weight of fuel in a fuel tank on a flying object, comprising a first set of pressure transducers for detecting the level of fuel in the tank and its density and for outputting the corresponding pressure values; another pressure transducer for detecting the absolute pressure in the tank; and a processor unit connected to the respective transducers for receiving pressure information therefrom and for calculating the remaining weight of the fuel utilizing the pressure information and relevant data stored in a memory. The apparatus is substantially smaller in weight and less expensive than any conventionally known apparatus, and has a high degree of accuracy and reliability of performance.