Aircraft designing method, aircraft designing program and aircraft designing apparatus

Patent metadata

Field	Value
Publication number	US-11030360-B2
Application number	US-201514864478-A
Country	US
Kind code	B2
Filing date	Sep 24, 2015
Priority date	Sep 30, 2014
Publication date	Jun 8, 2021
Grant date	Jun 8, 2021

Abstract

An aircraft designing apparatus receives set values of design parameters related to the shape of an intake duct, creates analysis models for an aerodynamic characteristic analysis and a radar-cross-section analysis by using the values of the design parameters, calculates aerodynamic characteristics and radar-cross-section characteristics of the intake duct, and determines whether or not this analytical result satisfies a preset design condition. If it is determined that the analytical result does not satisfy the design condition, the values of the design parameters are updated. The updating of the design parameters, the analyses of the aerodynamic characteristics and the radar-cross-section characteristics, and the determining process are repeated until it is determined that the analytical result satisfies the design condition.

First claim

The invention claimed is:

1. An aircraft designing method of designing a shape of an intake duct in an aircraft, the aircraft designing method comprising steps of:
(1) receiving values of design parameters related to the shape of the intake duct, the design parameters related to the shape of the intake duct including i) a ratio of an overall length of the intake duct from an intake port to an exhaust port of the intake duct and a diameter of an exhaust port of the intake duct, ii) a shape of a centerline, iii) a cross-sectional shape, and iv) a cross-sectional-area distribution;
(2) creating analysis models for an aerodynamic characteristic analysis and a radar-cross-section analysis by using the values of the design parameters, and performing, based on the values of the design parameters, a computational-fluid-dynamics (CFD) computation to obtain aerodynamic characteristics of the intake duct and a radar-cross-section (RCS) computation to obtain radar-cross-section characteristics of the intake duct so as to obtain an analytical result corresponding to the values of design parameters;
(3) determining whether or not the aerodynamic characteristics and the radar-cross-section characteristics satisfy a preset design condition;
(4) outputting the values of the design parameters if a determination indicates that the aerodynamic characteristics and the radar-cross-section characteristics satisfy the preset design condition, and updating the values of the design parameters if the determination indicates that the aerodynamic characteristics and the radar-cross-section characteristics do not satisfy the preset design condition; and
(5) iterating steps (2), (3), and (4) by using the updated values of the design parameters, until an determination in an iteration indicates that the aerodynamic characteristics and the radar-cross-section characteristics obtained in the iteration satisfy the preset design condition,
wherein the design condition includes an optimizing condition related to the aerodynamic characteristics and the radar-cross-section characteristics, the optimizing condition including a total pressure recovery rate inside the intake duct being maximized while the radar cross section is minimized,
wherein step (4) includes updating the values of the design parameters while optimizing the values of the design parameters if the determination indicates that the aerodynamic characteristics and the radar-cross-section characteristics do not satisfy the preset design condition including the optimizing condition, and
wherein whether or not the optimizing condition is satisfied is determined by calculating an objective function expressed as a sum of the aerodynamic characteristics and the radar-cross-section characteristics which are individually weighted, from the obtained analytical result.

2. An aircraft designing method of designing a shape of an intake duct in an aircraft, the aircraft designing method comprising steps of:
(1) receiving values of design parameters related to the shape of the intake duct, the design parameters related to the shape of the intake duct including i) a length ratio of an overall length of the intake duct from an intake port to an exhaust port of the intake duct and a diameter of an exhaust port of the intake duct, ii) a shape of a centerline, iii) a cross-sectional shape, and iv) a cross-sectional-area distribution;
(2) creating analysis models for an aerodynamic characteristic analysis and a radar-cross-section analysis with respect to the values of the design parameters, and performing, based on the values of the design parameters, a computational-fluid-dynamics (CFD) computation to obtain aerodynamic characteristics of the intake duct and a radar-cross-section (RCS) computation to obtain radar-cross-section characteristics of the intake duct so as to obtain sampling analytical results corresponding to the values of the design parameters;
(3) generating response surfaces of the aerodynamic characteristics and the radar-cross-section characteristics with respect to the design parameters from the sampling analytical results; and
(4) outputting a solution of the design parameters that satisfies a preset design condition based on the response surfaces of the aerodynamic characteristics and the radar-cross-section characteristics,
wherein the design condition includes an optimizing condition related to the aerodynamic characteristics and the radar-cross-section characteristics, the optimizing condition including a total pressure recovery rate inside the intake duct being maximized while the radar cross section is minimized,
wherein step (4) includes outputting an optimal solution of the design parameters that satisfies the design condition including the optimizing condition, and
wherein whether or not the optimizing condition is satisfied is determined by calculating an objective function expressed as a sum of the aerodynamic characteristics and the radar-cross-section characteristics, which are individually weighted, from the obtained analytical result.

3. A non-transitory computer-readable medium storing an aircraft designing program that designs a shape of an intake duct in an aircraft, when the program is executed by a computer, causing the computer to:
(1) receive values of design parameters related to the shape of the intake duct, the design parameters related to the shape of the intake duct including i) a length ratio, ii) a shape of a centerline that extends from a center of an intake port to a center of an exhaust port of the intake duct, the shape of the centerline including an offset amount of the centerline in a horizontal direction from the center of the intake port to the center of the exhaust port and an offset amount of the centerline in a vertical direction from the center of the intake port to the center of the exhaust port, iii) a cross-sectional shape, and iv) a cross-sectional-area distribution;
(2) create analysis models for an aerodynamic characteristic analysis and a radar-cross-section analysis by using the values of design parameters, and perform, based on the values of design parameters, computational-fluid-dynamics (CFD) computation to obtain aerodynamic characteristics of the intake duct and a radar-cross-section (RCS) computation to obtain radar-cross-section characteristics of the intake duct so as to obtain an analytical result corresponding to the values of design parameters;
(3) determine whether or not the aerodynamic characteristics and the aerodynamic characteristics satisfy a preset design condition;
(4) output the value of the values of the design parameters if a determination indicates that the aerodynamic characteristics and the radar-cross-section characteristics satisfy the preset design condition, and update the values of the design parameters if the determination indicates that the aerodynamic characteristics and the aerodynamic characteristics do not satisfy the preset design condition; and
(5) iterate (2), (3), and (4) by using the updated values of design parameters, until a determination in an iteration indicates that the aerodynamic characteristics and the aerodynamic characteristics obtained in the iteration satisfy the preset design condition,
wherein the design condition includes an optimizing condition related to the aerodynamic characteristics and the radar-cross-section characteristics, the optimizing condition including a total pressure recovery rate inside the intake duct being maximized while the radar cross section is minimized,
wherein step (4) includes updating the values of the design parameters while optimizing the values of the design parameters if the determination indicates that the aerodynamic characteristics and the radar-cross-section characteristics do not satisfy the preset design condition including the optimizing condition, and
wherein whether or not the o

Assignees

• Subaru Corp

Inventors

• Sato Kazushige
• Murakami Chikage
• Iso Hideo

Classifications

• Y02T90/00

  Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation · CPC title

• G06F2111/04

  Constraint-based CAD · CPC title

• G06F2111/06

  Multi-objective optimisation, e.g. Pareto optimisation using simulated annealing [SA], ant colony algorithms or genetic algorithms [GA] · CPC title

• G06F30/15 Primary

  Vehicle, aircraft or watercraft design · CPC title

• G06F2111/10

  Numerical modelling · CPC title