Расчетно-экспериментальный метод определения внешних нагрузок на крыло самолета с учетом статической аэроупругости

Abstract

Диссертация посвящена вопросу разработки метода расчета внешней нагрузки на крыло большого удлинения (λ ≥ 8) самолета транспортной категории с учетом статической аэроупругости на основе расчетных и экспериментальных исследований. Разработаны структурные модели проектируемого изделия (аэродинамическая, массовая, упругая), методы формирования исходных данных для расчетов нагруженности на основе статистики, численных методов расчета и результатовэксперимента. Разработаны алгоритмы и средства автоматической обработки вторичных данных дренажных исследований в АДТ в режиме реального времени проведения экспериментальных исследований. При реализации технологических решений использованы принципы проектирования информационных технологий.

Дисертація присвячена питанню розробки методу розрахунку зовнішнього навантаження на крило великого подовження (λ ≥ 8) літака транспортної категорії з урахуванням статичної аеропружності на основі розрахункових та експериментальних досліджень. Розроблено структурні моделі проектуємого виробу, методи формування вхідних даних для розрахунків навантажень на основі статистики, чисельних методів розрахунку і результатів експерименту. Розроблено процедури верифікації одержаної інформації. Розроблено алгоритм та засоби автоматичної обробки вторинних даних дренажних досліджень в АДТ у режимі реального часу проведення експериментальних досліджень. Отримав подальший розвиток спосіб визначення впливу статичної аеропружності на розподіл зовнішніх навантажень по крилу. При реалізації технологічних рішень використані принципи проектування інформаційних технологій.

Dissertation is devoted to developing a method of calculating the external load on the wing of a large extension (λ ≥ 8) transport category aircraft based on static aero elasticity based on theoretical and experimental studies using information technology to achieve this goal it is necessary to solve the following problem: 1. To develop a mathematical model of the wing, allowing a load from the effect of static aero elasticity in terms of three-dimensional loads. 2. Identify and investigate factors affecting the coincidence of theoretical calculations and experimental aerodynamic to minimize their differences synthesizing algorithm of mathematical models and theoretical calculations of self-reliance input a shortage of information on the basis of statistics. 3. Develop algorithm secondary drainage research results in the wind tunnel conditions for automatic or semi-automatic correction controlled variables in real time experimental studies. 4. Bring method to use and develop the engineering of programs that provide adaptive control studies of external loads on the wing of a large extension in real time. 5. Perform testing method in solving specific design problems. Object is external loads acting on the wing of a large extension subsonic transport category aircraft. The subject of research is mathematical models wings and external pressures for determining the load of the effect of static aero elasticity in terms of project uncertainty. Scientific results: 1. First the mathematical model to determine the distributed and integrated external loads on the wing that offers a self-tuning based on error minimization between the calculated and experimental data plane counterpart, which in turn minimizes the discrepancy between the results calculated and experimental research wing projected. 2. Have developed a three-dimensional model for calculating wing external load considering the effects of static aero elasticity that provides three-dimensional finite element stress model for the calculation of the strength of the wing and its elements.3. New technology is the result of the detection and rejection of possible errors drainage secondary data aerodynamic experiment based on the properties of continuity of form and profile building confidence interval derivative of pressure distribution on the chord drained section that solves the problem of automating the process of experimental data and a decrease in time, by timing, more than 6 times. 4. For the first time on the basis of computer-integrated technology system aerodynamic, elastic mass and mathematical models of large wing extension that allows for automatically input to the process of determining the elastic-strain state of the wing and leads to a reduction in design cycle time to 20% compared to existing technologies. Results: 1. The method of determining the outer wing load transport category aircraft, which is in the design uncertainty and temporal delimitation cycles design provides increased precision calculations of 4.5% compared with the existing methods, giving more resemblance to the loads generated during the flight experiment. 2. An integrated mathematical model for large wing extension based computer-integrated technology allows for determination of elastic-strain state of the wings automatically leading to reduced design cycle time by ~ 20%. 3. The algorithm for constructing aerodynamic wing model based on numerical methods with constant monitoring of results and calculation of correction functions using convergence obtained by this aircraft analogue or limited results aerodynamic experiments, thus improving the reliability of numerical studies and to expand their use in project work and, consequently, reduce drainage research program in ADT to 30%. 4.Developed three-dimensional elastic wing model to calculate the six-component external load (force Qx, Qy, Qz and moments Mx, My, Mz), which provides three-dimensional finite element stress model for the calculation of the strength of the wing and its elements and is a more appropriate model compared to the existing three-component model of load (force Qy and moments Mx, Mz). 5. The proposed automated processing technology secondary data research on drainage function of technological operations forming, processing and analysis of experimental data in real time of the experiment, which increases the efficiency of this type of aerodynamic research and reduces the complexity of experimental data pain than 6 times. 6.Methodical and software for automatic processing of secondary data drainage tube studies graphics with the ability to diagnose and document the experimental data that extends the functionality of aerodynamic research and increases by 60% the speed of access to the source data used in the calculation of external loads. 7. The proposed method provided algorithms that are brought to the use of engineering and through which a software package and received external load in the design of the wings of AN-74, AN-71, AN-70, AN-124 "Ruslan", AN-225 "Mria", AN-140.