Abstract: An outer surface of a part of an airframe includes a mixed region in which a first color similar to a color applied to an adjacent region and a second color having a lower absorption rate of sunlight than the first color are mixed in a predetermined color distribution pattern. A reflective material that contributes to an increase in a reflection rate of sunlight is added to a part to which at least the first color is applied in the mixed region.

Abstract: An air-conditioning duct structure of an aircraft includes an air-conditioning duct that is provided on each of a starboard side and a port side and guides conditioned air to a vicinity of a ceiling of a cabin in the aircraft. The air-conditioning duct includes a blowout portion and a blowout upstream portion. The blowout portion blows out the conditioned air to the cabin from an outboard side of the ceiling to an inboard side of the ceiling and toward a lower part than the ceiling, and the blowout upstream portion communicates with an upstream side of the blowout portion. In addition, the blowout portion or the blowout upstream portion is curved to cause a terminal end side of the blowout portion to be inclined downward with respect to a horizontal direction.

Abstract: An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adjusts a flow rate of the bleed air supplied to the anti-icing unit adjusts the flow rate of the bleed air to suppress pressure of the bleed air to a pressure upper limit or lower by using relationship r1 and relationship r2. The relationship r1 is a relationship between an altitude and a pressure upper limit of the bleed air. The relationship r2 is a relationship between the pressure upper limit and outside air temperature at which the temperature of the bleed air reaches allowable temperature of ducts and other members through which the bleed air flows. The relationship r2 is provided based on the altitude.

Abstract: To prevent overheating of a structural member such as a pivot bulkhead facing a rear side of a fire wall to maintain the temperature of the structural member at allowable temperature or lower. An aircraft of the present invention includes: a fire wall resistant to flame; a structural member facing a rear side of the fire wall; and a skin surrounding the fire wall and the structural member. The structural member includes a guide member and a heat shielding member. The structural member guides, upward, air existing on the rear side of the fire wall, and the heat shielding member shields the guide member from heat radiated by the fire wall.

Abstract: The present invention provides a life jacket case which can achieve weight reduction as well as seal the inside. Provided is a life jacket case for housing a life jacket, wherein a cover of an opening, through which the life jacket is taken in and out, is made of a first material which is hard enough to keep the shape of the cover, and a region other than or larger than the region made of the first material is made of a second material which is more lightweight than the first material. It is preferable that the life jacket case is fitted with a security tag which indicates whether or not the cover has been opened.

Abstract: An engine pylon that is used for supporting an engine, the engine pylon including a pylon body having an upper pylon and a lower pylon. The pylon further includes a fairing that covers the pylon body such that the upper pylon and fairing define a predetermined region. Moreover, the pylon includes a first drain that is configured to discharge a flammable liquid leaking from a pipe provided within the predetermined region into outside air; and a ventilation path configured to bring the inside of the predetermined region into communication with the outside air. The first drain includes a drain port and a drain pipe, wherein the drain pipe extends in a rear direction from the drain port and has an outlet at a rear end of the drain pipe, the outlet being located past a rear end of the upper pylon and a rear end of the lower pylon.

Abstract: The method of forming reinforced fiber base material is provided with: arranging, on the mold having a projection with a upper surface, a platform that is adjacent to the projection and has a flat upper surface at the same height as the upper surface of the projection; forming the laminate by placing reinforced fiber base material in layers on the upper surface of the projection; placing an end of the laminate in the width direction extending out of the upper surface of the projection, on the upper surface of the platform, with the end of the laminate in the width direction sandwiched in a vertical direction by a pair of the films of which outer ends in the width direction are fixed to each other; and removing the platform and pulling out the pair of the films while shaping the laminate along the projection.

Abstract: An object of the present invention is to prevent accumulation of moisture which has entered inside a honeycomb sandwich panel used for a stressed-skin structure of an aircraft. A reinforcing structure includes an outer panel constituting an outer shell of a tailplane and a honeycomb sandwich panel reinforcing the outer panel. The honeycomb sandwich panel includes a honeycomb core having a plurality of cells, an outer skin joined on the front side of the honeycomb core and disposed on the side of the outer panel, and an inner skin joined on the back side of the honeycomb core and disposed on the inner side of the tailplane. The inner skin has drainage channels formed therein through which each of the plurality of cells communicates with the outside of the honeycomb sandwich panel.

Abstract: Temperature of a structural member is maintained at allowable temperature or less by suppressing heat transfer from a high-temperature duct to the structural member. An insertion sheet according to the present invention is inserted between a flange and a partition panel. The flange is provided on a bleed duct and is fastened to the partition panel. The bleed duct penetrates through a partition wall of an aircraft. The insertion sheet includes first parts and a second part. The first parts are disposed near respective shafts of rivets provided at a plurality of positions of the insertion sheet. The second part extends among the first parts. The first parts bear a load of fastening, and the second part has thermal conductivity lower than thermal conductivity of the first parts.

Abstract: Provided is a novel method for improving fatigue strength, which is applicable to any small portion that is covered with another member. A method for improving fatigue strength according to the present invention includes: disposing an aid (3, 15) to be opposed to an processing object (2A, 2B, 6) on which a fatigue strength improving process is performed, the aid being configured to assist the improving process; and generating sparks between the aid (3, 15) and the processing object (2A, 2B, 6).

Abstract: An anti-icing system according to the present invention blows heated air to a curved inner surface of a main wing of an aircraft. The anti-icing system includes: a piccolo tube that includes a flow path through which the heated air flows in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside; and an engine that supplies the heated air toward the piccolo tube. The heated air ejected from the ejection holes of the piccolo tube is ejected toward an upper limit position and a lower limit position of an outside airflow stagnation point that are virtually formed on the main wing.

Abstract: An aircraft includes an accessory member that constitutes an engine accessory, the accessory member being arranged between an aircraft engine pylon and an engine, in an attached state to an attachment base member that is at least one of the pylon and the engine. The accessory member includes: a surrounding portion that surrounds at least an end portion of a tubular body connected to the accessory member; and a projecting portion that projects from the end portion of the tubular body. The entire accessory member including the surrounding portion and the projecting portion is divided so as to be separable to a left side and a right side of the pylon, and the accessory member is attachable to and detachable from the attachment base member by accessing an outer periphery of the tubular body from the left side and the right side of the pylon without removing another member.

Abstract: An aircraft including a turbofan engine provided with an engine body and a fan located anterior to the engine body, further includes: an engine oil cooler that is a heat exchanger for cooling engine oil used in the engine body by using, as a heat source, a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl; and a pre-cooler that is a heat exchanger for cooling bleed air from the engine body by using the fan stream as a heat source, wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle, and the engine oil cooler is located anterior to the pre-cooler.

Abstract: To provide an air conditioning piping structure for an aircraft which can promote mixing of temperature adjusted air and recirculated air flowing into a mixing chamber forming an air conditioning system. An air conditioning piping structure causes temperature adjusted air obtained by an air conditioning apparatus of an aircraft and recirculated air discharged from a pressurized compartment to flow into a mixing chamber which mixes the temperature adjusted air and the recirculated air. This air conditioning piping structure includes a first pipe through which the temperature adjusted air flows, a second pipe through which the recirculated air flows, and which is connected to the first pipe, and a flow passage restricting part configured to apply a resistance to at least one of the temperature adjusted air and the recirculated air in a vicinity of a merging position where the temperature adjusted air and the recirculated air are merged.

Abstract: An air-conditioning duct structure of an aircraft includes an air-conditioning duct that is provided on each of a starboard side and a port side and guides conditioned air to a vicinity of a ceiling of a cabin in the aircraft. The air-conditioning duct includes a blowout portion and a blowout upstream portion. The blowout portion blows out the conditioned air to the cabin from an outboard side of the ceiling to an inboard side of the ceiling and toward a lower part than the ceiling, and the blowout upstream portion communicates with an upstream side of the blowout portion. In addition, the blowout portion or the blowout upstream portion is curved to cause a terminal end side of the blowout portion to be inclined downward with respect to a horizontal direction.

Abstract: Provided is a preform member bonding method of bonding a preform member and another member with an adhesive in an RTM process. The preform member bonding method includes increasing viscosity of the adhesive by heat-treating only the adhesive in advance before inserting the adhesive between bonding surfaces of the preform member and the other member.

Abstract: A seal structure for sealing a gap between a first member and a second member of an aircraft includes: a plate spring-shaped first elastic seal; and a second elastic seal. When the first member and the second member are stationary with respect to each other, the first elastic seal elastically deforms between the first member and the second member to seal the gap, whereas the second elastic seal does not seal the gap. When the first member and the second member move closer to each other and the first elastic seal is elastically deformed, the second elastic seal elastically deforms between the first member and the second member to seal the gap.

Abstract: A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft. The fire seal structure includes: a first seal compressed and elastically deformed between two members of the aircraft; and a second seal pressed against the first seal in a direction intersecting a compression direction in which the first seal is compressed. A wall of the first seal pressed by the second seal includes a bent groove including at least one bent part.

Abstract: The present invention has an objective to provide a dolly for handling a landing gear of an aircraft that enables, while being downsized, work of positioning the landing gear with respect to an attachment portion of an airframe of the aircraft to be performed efficiently, and a method for attaching or detaching a landing gear using the dolly. A dolly (10) for handling a landing gear (20) of an aircraft includes a base (11), an expandable boom (12) that rises from the base (11) and is expandable and contractible, a hoisting boom (13) that is interconnected to the expandable boom (12) in a raisable and lowerable manner, and a holding portion (15) that is suspended on the hoisting boom (13) and retains the landing gear (20).

Abstract: A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft. The fire seal structure includes: a plurality of walls including: a first wall provided on a first partitioning member; and a second wall provided on a second partitioning member. One of the plurality of walls is a spring wall that functions as a spring. The first and the second partitioning members define the fire-prevention region. The plurality of walls forms a labyrinth-shaped gap between the first and the second partitioning members. Each of the plurality of walls contains a refractory material and includes a front end part. When the first and the second partitioning members are stationary with respect to each other, the front end part is not in contact with another member, and the spring wall is disposed closest to a facing member, among the plurality of walls.