Abstract: A high-lift device includes a flap disposed at a leading edge of a wing, and configured to be retracted in the lower surface and extended toward of the leading edge; a first rotary shaft and a second rotary shaft, the axial direction of the rotary shafts being disposed along the spanwise direction of the wing, respectively; a first link mechanism connected to the first rotary shaft and the flap; and a second link mechanism connected to the second rotary shaft and the flap. When the first link mechanism is driven with the first rotary shaft, the flap is retracted in the lower surface of the leading edge or is extended toward the front of the leading edge. When the second link mechanism is driven with the second rotary shaft, the position or the angle of the flap moved by the first link mechanism is changed.

Abstract: A raised structure for reducing frictional drag due to viscosity of a flow toward an object in a direction forming an acute angle with an end portion of the object. The raised structure includes a plurality of raised bodies provided on a surface of the leading edge of the object at a downstream side of a stagnation point of the main flow, wherein a height of each raised body changes along a smooth convex curve, and the raised bodies are arranged in an array to form a first uneven shape changing periodically in a first cross section having a constant distance from the stagnation point and orthogonal to the surface, and a second uneven shape changing in a second cross section that is orthogonal to a line composed of the stagnation point and the first cross section, the second uneven shape having concave portions and convex portions that change periodically.

Abstract: A high-lift device includes a flap disposed at a leading edge of a wing, and configured to be retracted in the lower surface and extended toward of the leading edge; a first rotary shaft and a second rotary shaft, the axial direction of the rotary shafts being disposed along the spanwise direction of the wing, respectively; a first link mechanism connected to the first rotary shaft and the flap; and a second link mechanism connected to the second rotary shaft and the flap. When the first link mechanism is driven with the first rotary shaft, the flap is retracted in the lower surface of the leading edge or is extended toward the front of the leading edge. When the second link mechanism is driven with the second rotary shaft, the position or the angle of the flap moved by the first link mechanism is changed.

Abstract: The thrust force generation device is provided with: a turbo fan engine unit that includes a generator for generating power using a rotation force of a drive shaft, and that drives a fan placed on the drive shaft using gas produced by combusting fuel; a motor driven fan unit that includes a motor driven by power supplied from the generator, that is placed in parallel with the turbo fan engine unit, and that drives a fan by using the motor; and a conducting unit that connects the generator to the motor, and supplies the power generated by the generator to the motor. The turbo fan engine unit and the motor driven fan unit are integrated with each other, and the conducting unit is placed between the turbo fan engine unit and the motor driven fan unit.

Abstract: The thrust force generation device is provided with: a turbo fan engine unit that includes a generator for generating power using a rotation force of a drive shaft, and that drives a fan placed on the drive shaft using gas produced by combusting fuel; a motor driven fan unit that includes a motor driven by power supplied from the generator, that is placed in parallel with the turbo fan engine unit, and that drives a fan by using the motor; and a conducting unit that connects the generator to the motor, and supplies the power generated by the generator to the motor. The turbo fan engine unit and the motor driven fan unit are integrated with each other, and the conducting unit is placed between the turbo fan engine unit and the motor driven fan unit.

Abstract: An aircraft communication system for performing communication between each of a plurality of devices installed in an aircraft, wherein the communication system is provided with a plurality of communication processing units provided corresponding to the plurality of devices and a plurality of communication lines for connecting between the communication processing units, the plurality of communication processing units being capable of bidirectional communication via the plurality of communication lines. Upon receiving a plurality of communication data from the plurality of communication lines, one of the communication processing units determines, on the basis of identification information included in the received plurality of communication data, whether the received plurality of communication data needs to be acquired and acquires the communication data determined to need to be acquired.

Abstract: An aircraft communication system for performing communication between each of a plurality of devices installed in an aircraft, wherein the communication system is provided with a plurality of communication processing units provided corresponding to the plurality of devices and a plurality of communication lines for connecting between the communication processing units, the plurality of communication processing units being capable of bidirectional communication via the plurality of communication lines. Upon receiving a plurality of communication data from the plurality of communication lines, one of the communication processing units determines, on the basis of identification information included in the received plurality of communication data, whether the received plurality of communication data needs to be acquired and acquires the communication data determined to need to be acquired.

Abstract: An aircraft design apparatus calculates aircraft specifications, which are aircraft specifications, based on a plurality of design parameters required to design an aircraft; judges whether or not the calculated aircraft specifications meet constraints that indicate the aircraft feasibility and that are set in advance and given optimizing conditions for optimizing the aircraft; changes the design parameters so that the calculated aircraft specifications meet the constraints and also meet the optimizing conditions; and executes iterative processing in which the aircraft specifications are repeatedly calculated based on the changed design parameters. By doing so, with the aircraft design apparatus, it is possible to achieve a more optimal aircraft design and it is also possible to reduce the time and effort required to design an aircraft.