Methods of calculating the aircraft wing characteristics with influence aeroelasticity

В даній статті описується методика, яка забезпечує створення математичної моделі пружного крила під дією аеродинамічного та масового навантаження, що дозволяє описати взаємодію крила з потоком повітря, в аналітичному вигляді. Приведенно приклад її застосування для визначення критичної швидкості дивергенціі спрощеного крила літака Ла-5 ФН.Aeroelasticity is important in many areas of engineering, especially in aviation, where the resulting large size and velocity of the aircraft aeroelasticity is the most significant (negative) factor taken into account when creating the new aircraft. When designing the wing one of the objectives is to eliminate and reduce the harmful effects of aeroelasticity his design during the flight. This makes it necessary to study many variations of designs, hence the relevance of using new computer methods of calculation. In this article introduce new technique that ensures the creation of a mathematical model of elastic wings under aerodynamic and mass loads, which will describe the interaction of the wings of the air flow in an analytical way. The technique is to divide the wings into sections and replacing them with the corresponding finite elements, characterized by its rigidity, strength and weight lifting. These characteristics are described by the matrices aerodynamic impact, stiffness and mass, in analytical form, which are oriented in their element coordinate systems. Each individual section is characterized by the provisions of the centers of mass and stiffness of pressure that used to bring all the elements into one global coordinate system. Based on this design model is constructed wing that looks consistent and characteristic elements connected in parallel, with subsequent transformation and analysis. There have been several studies on its use for finding the critical velocity divergence wing aircraft and computing console wing movements under load. The method has proven quite high efficiency and accuracy of the results. This calculation method can be used during the preliminary design of the aircraft, it will help to simplify the automation of this process through the widespread use of computer algebra, increase economic efficiency by reducing design time costs, human and machine resources. Will open new opportunities to simplify the process of optimizing mass characteristics of the aircraft projected. Also, the technique will allow a simple interpretation of interim results and further analytical studies.В данной статье описывается методика, которая обеспечивает создание математической модели упругого крыла под действием аэродинамической и массовой нагрузки, что позволяет описать взаимодействие крыла с потоком воздуха, в аналитическом виде. Показано ее применения для определения критической скорости дивергенции, упрощенного крыла самолета Ла-5 ФН