Intake designing method, non-transitory computer readable medium, and intake designing apparatus

Patent metadata

Field	Value
Publication number	US-2018293347-A1
Application number	US-201815945582-A
Country	US
Kind code	A1
Filing date	Apr 4, 2018
Priority date	Apr 11, 2017
Publication date	Oct 11, 2018
Grant date	—

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.

First claim

1 . An intake designing method that designs a shape of an intake of an aircraft, the method comprising:
setting a value of a design parameter that is related to a design target on a basis of an input operation, the design target being directed to a front fuselage, a bump, and an intake duct of the aircraft, the front fuselage being positioned more forward of an airframe of the aircraft than the intake, the bump being positioned in front of the intake; setting a shape of the design target on a basis of the set value of the design parameter; analyzing an aerodynamic characteristic and a radar cross-section characteristic of the design target, through creating, on a basis of the set shape of the design target, an analytical model directed to an analysis of the aerodynamic characteristic and an analytical model directed to an analysis of the radar cross-section characteristic, and through calculating, on a basis of the created analytical models, the aerodynamic characteristic and the radar cross-section characteristic 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 by the determining 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 by the determining as satisfying the design condition.

2 . The intake designing method according to claim 1 , wherein the aerodynamic characteristic of the design target related to a design point and the aerodynamic characteristic of the design target related to an off-design point are calculated in the analyzing, the design point being based on a first airframe speed that is in a supersonic region, the off-design point being based on a second airframe speed that is less than the first airframe speed, and being based on an elevation angle or an sideslip angle of the airframe relatively greater than an elevation angle or a sideslip angle of the airframe in the design point.

3 . The intake designing method according to claim 1 , wherein the updating the value of the design parameter includes optimizing the design parameter to allow a solution that satisfies the design condition to be obtained.

4 . The intake designing method according to claim 2 , wherein the updating the value of the design parameter includes optimizing the design parameter to allow a solution that satisfies the design condition to be obtained.

5 . The intake designing method according to claim 1 , wherein the design target includes a cowl of the intake.

6 . The intake designing method according to claim 2 , wherein the design target includes a cowl of the intake.

7 . The intake designing method according to claim 3 , wherein the design target includes a cowl of the intake.

8 . The intake designing method according to claim 4 , wherein the design target includes a cowl of the intake.

9 . A non-transitory computer readable medium having an intake designing program that designs a shape of an intake of an aircraft, the intake designing program causing, when executed by a computer, the computer to implement a method, the method comprising:
setting a value of a design parameter that is related to a design target on a basis of an input operation, the design target being directed to a front fuselage, a bump, and an intake duct of the aircraft, the front fuselage being positioned more forward of an airframe of the aircraft than the intake, the bump being positioned in front of the intake; setting a shape of the design target on a basis of the set value of the design parameter; analyzing an aerodynamic characteristic and a radar cross-section characteristic of the design target, through creating, on a basis of the set shape of the design target, an analytical model directed to an analysis of the aerodynamic characteristic and an analytical model directed to an analysis of the radar cross-section characteristic, and through calculating, on a basis of the created analytical models, the aerodynamic characteristic and the radar cross-section characteristic 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 by the determining 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 by the determining as satisfying the design condition.

10 . An intake designing apparatus configured to design a shape of an intake of an aircraft, the intake designing apparatus comprising:
a design parameter setting unit configured to set a value of a design parameter that is related to a design target on a basis of an input operation, the design target being directed to a front fuselage, a bump, and an intake duct of the aircraft, the front fuselage being positioned more forward of an airframe of the aircraft than the intake, the bump being positioned in front of the intake; a shape setting unit configured to set a shape of the design target on a basis of the set value of the design parameter; an analyzer configured to analyze an aerodynamic characteristic and a radar cross-section characteristic of the design target, through creating, on a basis of the shape of the design target set by the shape setting unit, an analytical model directed to an analysis of the aerodynamic characteristic and an analytical model directed to an analysis of the radar cross-section characteristic, and through calculating, on a basis of the created analytical models, the aerodynamic characteristic and the radar cross-section characteristic of the design target; a determiner configured to determine whether an analysis result obtained by the analyzer satisfies a preset design condition; and a design parameter updating unit configured to update the value of the design parameter when the analysis result obtained by the analyzer is determined by the determiner as not satisfying the design condition, the shape setting unit being configured to set the shape of the design target, the analyzer being configured to analyze the aerodynamic characteristic and the radar cross-section characteristic of the design target, the determiner being configured to determine whether the analysis result satisfies the preset design condition, and the design parameter updating unit being configured to update the value of the design parameter, until the determiner determines that the analysis result obtained by the analyzer satisfies the design condition.

11 . An intake designing apparatus configured to designs a shape of an intake of an aircraft, the intake designing apparatus comprising
circuitry configured to
set a value of a design parameter that is related to a design target on a basis of an input operation, the design target being directed to a front fuselage, a bump, and an intake duct of the aircraft, the front fuselage being positioned more forward of an airframe of the aircraft than the intake, the bump being positioned in front of the intake,
set a shape of the design target on a basis of the set value of the design parameter,
analyze an aerodynamic characteristic and a radar cross-section characteristic of the design target, through creating, on a basis of the set shape of the design target, an analytical model directed to a

Assignees

• Subaru Corp

Inventors

• OSUKA Takeshi
• Sato Kazushige
• Murakami Chikage
• Okita Tomoyuki

Classifications

• G06F2113/28

  Fuselage, exterior or interior · CPC title

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F05D2260/81

  Modelling or simulation · CPC title

• G06F30/15 Primary

  Vehicle, aircraft or watercraft design · CPC title

• G06F17/5095 Primary

  Physics · mapped topic