KR20020070688A - External store loads analysis method - Google Patents

External store loads analysis method Download PDF

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Publication number
KR20020070688A
KR20020070688A KR1020010010854A KR20010010854A KR20020070688A KR 20020070688 A KR20020070688 A KR 20020070688A KR 1020010010854 A KR1020010010854 A KR 1020010010854A KR 20010010854 A KR20010010854 A KR 20010010854A KR 20020070688 A KR20020070688 A KR 20020070688A
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South Korea
Prior art keywords
load
aircraft
force
aerodynamic
exterior
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KR1020010010854A
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Korean (ko)
Inventor
염태성
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한국항공우주산업 주식회사
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Priority to KR1020010010854A priority Critical patent/KR20020070688A/en
Publication of KR20020070688A publication Critical patent/KR20020070688A/en

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01G—WEIGHING
    • G01G19/00—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups
    • G01G19/40—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups with provisions for indicating, recording, or computing price or other quantities dependent on the weight
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L1/00—Measuring force or stress, in general
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M1/00—Testing static or dynamic balance of machines or structures
    • G01M1/10—Determining the moment of inertia
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels

Abstract

PURPOSE: A method for analyzing load of outer installation of aircraft is provided to automatically analyze load of the outer installation of the aircraft. CONSTITUTION: A method comprises the steps of: a step multiplying load factor by load of an installation on the same point to get inertia force; a step multiplying aerodynamic coefficient according to wind tunnel test data by dynamic pressure and area to get aerodynamic force; and multiplying the inertia force by the aerodynamic force after getting the inertia force and the aerodynamic force to calculate load of the installation of the aircraft on the same point.

Description

항공기 외장물의 하중해석 방법{External store loads analysis method}External store loads analysis method

본 발명은 항공기 외장물의 하중해석 방법에 관한 것으로서, 구체적으로 같은 점에서의 로드 팩터와 외장물의 하중을 곱하여 얻은 관성력과, 풍동실험 데이터와 다이나믹 압력 및 면적을 곱하여 공력을 얻고, 관성력과 공력을 합하여 같은 지점에서의 항공기 외장물의 하중을 계산하는 항공기 외장물의 하중해석 방법에 관한 것이다.The present invention relates to a load analysis method of an aircraft exterior, specifically, the inertia force obtained by multiplying the load factor and the exterior load at the same point, the aerodynamic force by multiplying the wind tunnel test data and the dynamic pressure and area to obtain the aerodynamic force, The present invention relates to a load analysis method of an aircraft enclosure that calculates the load of the aircraft enclosure at the same point.

일반적으로 항공기란 엔진에 의한 추진력과, 날개에 의한 부력을 이용하여 비행을 수행하는 이동수단을 일컫으며, 통상적으로 항공기에는 엔진이나 날개등과 같은 기본적인 구성요소 뿐만 아니라, 전투를 수행하기 위한 전투기에는 미사일이나 각종 폭탄 등이 장착되고, 화물을 운반하기 위한 운반기에는 연료나 화물 등을 장착하도록 구성된다.In general, an aircraft refers to a vehicle that performs a flight using propulsion by an engine and buoyancy by a wing.In general, an aircraft includes not only basic components such as an engine or a wing, but also a fighter for combat. Missiles, various bombs, and the like are mounted, and a carrier for transporting cargo is configured to mount fuel or cargo.

이와 같이 항공기에 있어서 최초에 설계된 용도이외의 구조적인 변화가 발생하면 항공기의 하중에 변화가 발생하여 항공기 운항에 미묘한 변화를 발생하게 된다.As such, when structural changes other than the first intended use of the aircraft occur, a change in the load of the aircraft occurs and a subtle change occurs in the operation of the aircraft.

그리고, 이러한 미묘한 변화가 어느 한계치를 넘으면 균형이 깨어지거나, 항공기 사고를 유발하는 큰 원인이 되기도 하므로, 최초에 항공기를 설계하는 과정에서 기본적으로 차후에 부착되는 외장물에 대한 고려 역시 이루어져야 한다.And, if these subtle changes exceed certain thresholds, they can be a cause for balance or cause aircraft accidents. Therefore, consideration should be given to the basic attachment of the exterior during the initial aircraft design process.

하지만 종래에는 항공기의 외장물에 대한 하중 해석을 수행하는 프로그램이나 장치가 제시되지 않아, 수작업에 의해 많은 노력과 수고를 기울여 하중 해석을 수행하였다.However, in the related art, a program or apparatus for performing load analysis on an exterior of an aircraft has not been proposed, and thus, load analysis was performed with a great deal of effort and effort by hand.

따라서, 본 발명은 상술한 바와 같은 문제를 해결하기 위해 안출된 것으로서, 본 발명의 목적은 항공기의 외장물에 대한 하중 해석을 자동으로 수행하는 방법을 제공함에 있다.Accordingly, the present invention has been made to solve the above problems, an object of the present invention to provide a method for automatically performing a load analysis on the exterior of the aircraft.

본 발명의 다른 목적은 후술될 구성 및 작용에서 더욱 상세히 설명될 것이다.Other objects of the present invention will be described in more detail in the configurations and operations described below.

도 1은 본 발명에 따른 바람직한 실시예를 나타내기 위한 순서도.1 is a flow chart for showing a preferred embodiment according to the present invention.

본 발명에 따른 항공기 외장물에 대한 하중 해석 방법은 같은 점에서의 로드 팩터와 외장물의 하중을 곱하여 얻은 관성력과, 풍동실험 데이터와 다이나믹 압력 및 면적을 곱하여 공력을 얻고, 관성력과 공력을 합하여 같은 지점에서의 항공기 외장물의 하중을 계산함을 특징으로 한다.Load analysis method for the aircraft enclosure according to the present invention is obtained by multiplying the load factor and the load of the enclosure at the same point, the wind tunnel test data and the dynamic pressure and area to obtain aerodynamic force, the inertia and aerodynamic force are the same point Calculate the load on the aircraft enclosure at.

바람직하게 관성력은 로드 팩터와 외장물의 하중을 곱한 것이고, 공력은 상기 풍동실험 데이터에 의한 공력 계수와 다이나믹 압력 및 면적을 곱한 것이며, 전체 항공기의 외장물 하중을 구하기 위해서는 상술한 관성력 및 공력을 각각의 기준 위치에 대하여 구한 뒤, 이를 전부 합하여 구한다.Preferably, the inertia force is multiplied by the load factor and the load of the enclosure, and the aerodynamic force is obtained by multiplying the aerodynamic coefficient according to the wind tunnel test data and the dynamic pressure and the area. After the reference position is obtained, the sum of them is obtained.

이하, 도면을 참조하여 본 발명의 바람직한 실시예에 대해 상세히 설명한다.Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

도 1에 따르면 본 발명에 의한 항공기 외장물에 대한 하중 해석 방법은 측정위치, 좌표, 외부 장착물 좌표, 무게, 관성 모멘트를 입력하는 단계(단계 S1), 외부 장착물의 공력 데이터 베이스를 입력하는 단계(단계 S2), 외부 장착물의 공기력을 계산하고, 외부 장착물의 관성력을 계산하는 단계(단계 S3), 원하는 위치로의 이부 장착물 합력을 변환하여 출력하는 단계(단계 S4)로 구성된다.According to Figure 1 load analysis method for the aircraft exterior according to the invention step of inputting the measurement position, coordinates, external mounting coordinates, weight, moment of inertia (step S1), step of inputting aerodynamic database of the external mounting (Step S2), calculating the aerodynamic force of the external mounting, calculating the inertia force of the external mounting (step S3), and converting and outputting the force of the attachment to the desired position (step S4).

상술한 과정을 구체적인 수치를 예를 들어 항공기 외장물에 대한 하중 해석을 설명하면 다음과 같다.Referring to the above-described process, for example, the load analysis of the aircraft exterior with specific values as follows.

먼저 단게 S1에서 외부 장착물의 무게는 1000파운드이고, 하중배수 N은 5g이면 관성력은 5 ×1000, 즉 5000파운드가 된다.First, in step S1, the weight of the external attachment is 1000 pounds, and the load factor N is 5 g, the inertia force is 5 × 1000, that is 5000 pounds.

그리고, 공력계수가 0.1 이고, 다이나믹 압력이 8.33이며, 적용면적이 255이면 공력은 0.1×8.33×255, 즉, 212.4 파운드가 된다.If the aerodynamic coefficient is 0.1, the dynamic pressure is 8.33, and the application area is 255, the aerodynamic force is 0.1 x 8.33 x 255, that is, 212.4 pounds.

따라서, 합력은 관성력과 공력의 합이므로 5000＋212.4가 되어 5212.4파운드가 된다.Therefore, the combined force is the sum of the inertia and the aerodynamic force, which is 5000 + 212.4 to 5212.4 pounds.

이 값이 항공기 외장물에 대한 하중 해석 결과값이 되며 단계 S4에서 출력하게 된다.This value becomes the result of load analysis on the aircraft exterior and is output in step S4.

상술한 바와 같이 본 발명의 바람직한 실시예에 대해 상세히 설명하였지만, 본 발명의 분야에 속하는 통상의 지식을 가진 자라면 본 발명의 정신 및 범위를 벗어나지 않는 범위내에서 본 발명을 얼마든지 변형 또는 변경하여 실시할 수 있음을 잘 알 것이다.Although the preferred embodiment of the present invention has been described in detail as described above, those skilled in the art will be able to modify or change the present invention as many as possible without departing from the spirit and scope of the present invention. It will be appreciated that it can be done.

상술한 바와 같이 본 발명에 따르면 항공기를 설계하는 과정에서 차후에 항공기에 배치될 항공기 외장물에 대한 하중 해석이 미리 가능해지므로 항공기에 외장물을 장착하였을 경우에 대한 하중 변화가 미리 예측가능해지며, 하중에 미묘한 변화가 발생하는 경우에도 이에 따른 영향을 예측할 수 있어 항공기에 대한 안전관리가 가능해지며, 이러한 과정을 수행하도록 구성되는 컴퓨터 단말기에서 수작업이 아닌 자동 프로세스의 진행으로 짧은 시간에 간단히 처리할 수 있는 효과가 있다.As described above, according to the present invention, in the process of designing the aircraft, the load analysis on the aircraft exterior to be disposed in the future is possible in advance, so that the load change when the exterior is mounted on the aircraft is predictable in advance. Even in the case of subtle changes, the effects can be predicted, enabling safety management of the aircraft, and the effects that can be easily processed in a short time by the automatic process instead of manual operation in the computer terminal configured to perform such a process. There is.

그리고, 항공기 설계의 작은 변화에도 몇가지 정해진 변수만을 다시 입력하여 줌에 따라 변화에 따른 외장물의 하중 해석이 간단하게 변경될 수 있다.In addition, even if a small change in the aircraft design is input again only a few predetermined parameters, the load analysis of the exterior according to the change can be easily changed.

Claims (4)

항공기의 외장물의 하중을 해석하는 방법에 있어서,In the method of analyzing the load of the exterior of the aircraft, 같은 점에서의 로드 팩터와 외장물의 하중을 곱하여 관성력을 구하는 단계;Multiplying the load factor and the load of the enclosure at the same point to obtain an inertia force; 풍동실험 데이터와 다이나믹 압력 및 면적을 곱하여 공력을 구하는 단계; 및Multiplying wind tunnel test data by dynamic pressure and area to obtain aerodynamic force; And 상기 관성력과 공력을 구한 후에, 관성력과 공력을 합하여 같은 지점에서의 항공기 외장물의 하중을 계산함을 특징으로 하는 항공기 외장물의 하중 해석 방법.And after calculating the inertia force and aerodynamic force, calculating the load of the aircraft enclosure at the same point by adding the inertia force and the aerodynamic force. 제 1항에 있어서,The method of claim 1, 상기 관성력은 로드 팩터와 외장물의 하중을 곱한 것임을 특징으로 하는 항공기 외장물의 하중 해석 방법.The inertia force is a load analysis method of the aircraft exterior, characterized in that the product of the load factor and the load of the exterior. 제 1 항에 있어서,The method of claim 1, 상기 공력은 상기 풍동실험 데이터에 의한 공력 계수와 다이나믹 압력 및 면적을 곱한 것임을 특징으로 하는 항공기 외장물의 하중 해석 방법.The aerodynamic force is a load analysis method of the aircraft exterior, characterized in that the product of the aerodynamic coefficient and the dynamic pressure and the area by the wind tunnel test data. 제 1 항에 있어서,The method of claim 1, 전체 항공기의 외장물 하중을 구하기 위해서는 상술한 관성력 및 공력을 각각의 기준 위치에 대하여 구한 뒤, 이를 전부 합산하는 것을 특징으로 하는 항공기 외장물의 하중 해석 방법.In order to obtain the load of the exterior of the entire aircraft, the above-described inertia force and aerodynamic force are calculated for each reference position, and then all of them are summed up.
KR1020010010854A 2001-03-02 2001-03-02 External store loads analysis method KR20020070688A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20060004803A (en) * 2004-07-08 2006-01-16 한국항공우주산업 주식회사 Interface generation system for realtime flight simulator
KR100952639B1 (en) * 2006-07-04 2010-04-13 한국항공우주산업 주식회사 Method for Analyzing Static Load, And Computer-Readable Medium on Which Program Anaylyzing Static Load Is Recorded
KR20160036369A (en) * 2014-09-25 2016-04-04 국방과학연구소 Aerodynamic Modeling Method for the Interaction Between Free Stream and Side Jet for Body Alone Configuration

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20060004803A (en) * 2004-07-08 2006-01-16 한국항공우주산업 주식회사 Interface generation system for realtime flight simulator
KR100952639B1 (en) * 2006-07-04 2010-04-13 한국항공우주산업 주식회사 Method for Analyzing Static Load, And Computer-Readable Medium on Which Program Anaylyzing Static Load Is Recorded
KR20160036369A (en) * 2014-09-25 2016-04-04 국방과학연구소 Aerodynamic Modeling Method for the Interaction Between Free Stream and Side Jet for Body Alone Configuration

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