首页> 外国专利> METHOD FOR CORRECTING A AEROSERVOELASTICITY ANALYSIS MODEL USING FLIGHT TEST DATA AND APPARATUS THEREOF

METHOD FOR CORRECTING A AEROSERVOELASTICITY ANALYSIS MODEL USING FLIGHT TEST DATA AND APPARATUS THEREOF

机译：利用飞行测试数据校正航空弹塑性分析模型的方法及其装置

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摘要

The present invention relates to a method for modifying an aeroservoelastic figure analysis model with flight test analysis data and a device thereof. The method for modifying the aeroservoelastic figure analysis model comprises a step for calculating the gain margin of the figure analysis model by analyzing the figure analysis model for an aircraft having a predetermined armed shape, a system, and a control mode; a step for obtaining the flight test analysis data by performing a flight test for the aircraft and calculating the gain margin of the flight test analysis data; a step for comparing the gain margin of the figure analysis model analysis result with the gain margin of the flight test analysis data; and a step for modifying a decrease figure of the figure analysis model in order that the difference calculated in a part which shows a comparison result structure vibration mode is under a setting value. The present invention is provided to confirm conservatism of an existing figure analysis model by comparing the figure model with the flight test analysis data, thereby modifying the decrease value and improving the accuracy and reliability of the figure analysis model. [Reference numerals] (AA) Start; (BB) End; (S100) Obtain a figure analysis model; (S110) Select a predetermined armed shape, a system, and a control mode; (S120) Analyze the figure analysis model and calculate a gain margin; (S130) Select the predetermined armed shape, the system, and the control mode for performing a flight time; (S140) Measure flight test data by applying vibration on a control surface; (S150) Analyze the flight test data and calculate the gain margin; (S160) Compare the figure analysis model with the gain margin of the flight test data; (S170) Confirm the difference of the gain margin in a structure vibration mode part; (S180) Modify a decrease value in order that the difference is to be a setting value

机译：本发明涉及一种利用飞行测试分析数据修改航空弹性体形分析模型的方法及其装置。航空弹性体形分析模型的修正方法包括以下步骤：通过分析具有预定武装形状的飞机的形体分析模型，系统和控制模式，来计算形体分析模型的增益裕度;通过对飞机进行飞行测试并计算飞行测试分析数据的增益裕度，获得飞行测试分析数据的步骤;比较人物分析模型分析结果的增益裕度和飞行测试分析数据的增益裕度的步骤;并且，为了使在表示比较结果构造振动模式的部分中计算出的差在设定值以下，对图形分析模型的下降图形进行修正的步骤。提供本发明以通过将人物模型与飞行测试分析数据进行比较来确认现有人物分析模型的保守性，从而修改减小值并提高人物分析模型的准确性和可靠性。 [参考数字]（AA）开始; （BB）结束; （S100）获取图形分析模型; （S110）选择预定的武装形态，系统和控制模式; （S120）分析图形分析模型并计算增益裕度; （S130）选择预定的武装形态，系统和用于执行飞行时间的控制模式; （S140）通过在控制面上施加振动来测量飞行测试数据; （S150）分析飞行测试数据并计算增益裕度; （S160）将图形分析模型与飞行测试数据的增益余量进行比较; （S170）确认结构振动模式部分的增益裕度之差; （S180）修改减小值，以使差值为设置值

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公开/公告号KR20140046835A

专利类型
公开/公告日2014-04-21

原文格式PDF
申请/专利权人 KOREA AEROSPACE INDUSTRIES LTD.;
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申请/专利号KR20120113002
发明设计人 LEE EUN SUK;
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申请日2012-10-11
分类号G06F19;G06F17/10;
国家 KR
入库时间 2022-08-21 15:43:10

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