Abstract: An intake duct designing method includes: setting a value of a design parameter concerning a design target directed to an aircraft intake duct including a bypass mechanism that suppresses an aerial vibration phenomenon; setting a shape of the design target using the design parameter value; performing computational fluid dynamics analysis including calculating aerodynamic characteristics of the design target and a necessary bypassing flow rate of air released through the bypass mechanism for suppressing the aerial vibration phenomenon, by creating an analytical model for the analysis using the shape of the design target; determining whether an analysis result satisfies a preset design condition; updating the design parameter value when the analysis result is determined as not satisfying the design condition; and repeating the shape setting, the computational fluid dynamics analysis, the determining, and the design parameter value updating, until the analysis result is determined as satisfying the design condit

Abstract: An intake designing method includes: setting a value of a design parameter related to a design target that is directed to a front fuselage, a bump, and an intake duct of an aircraft; setting a shape of the design target on the basis of the set value of the design parameter; analyzing an aerodynamic characteristic and a radar cross-section characteristic of the design target on the basis of the set shape of the design target; determining whether an analysis result obtained by the analyzing satisfies a preset design condition; updating the value of the design parameter when the analysis result obtained by the analyzing is determined as not satisfying the design condition; and repeating the setting the shape of the design target, the analyzing, the determining, and the updating the value of the design parameter, until the analysis result obtained by the analyzing is determined as satisfying the design condition.

Abstract: In an intake structure of an aircraft that takes in air from a front side of an airframe, a bump is provided on a surface of the airframe of the aircraft at a portion immediately before an intake. The bump is formed so as to smoothly protrude from the front side of the airframe while having a width that is wider than a width of the intake.

Abstract: In an intake structure of an aircraft that takes in air from a front side of an airframe, a bump is provided on a surface of the airframe of the aircraft at a portion immediately before an intake. The bump is formed so as to smoothly protrude from the front side of the airframe while having a width that is wider than a width of the intake.

Abstract: A conveying robot is provided which can have a reduced maximum height and which can convey an object fast and stably. A conveying robot has at least one of a characteristic that a first driven link that configures the conveying robot is formed to have a bent shape that protrudes toward a second driven link with respect to a straight line that connects a first intermediate rotation support and a first tip-side rotation support, and a characteristic that the second driven link is formed to have a bent shape that protrudes toward the first driven link with respect to a straight line that connects a second intermediate rotation support and a second tip-side rotation support.