توجه: محتویات این صفحه به صورت خودکار پردازش شده و مقاله‌های نویسندگانی با تشابه اسمی، همگی در بخش یکسان نمایش داده می‌شوند.
۱Plasma Actuator Effects on Flow over Airfoil with Different Angle of Attacks
نویسنده(ها): ،
اطلاعات انتشار: هشتمین همایش انجمن هوافضای ایران، سال
تعداد صفحات: ۶
In this paper, effects of plasma actuator have been studied in flow control over airfoil NACA0021. For simulating plasma actuator effects, the electrostatic model has been applied. It is based on the assumption of different time scales that play different roles in the physics of the plasma actuator and allows decoupling the problem into two separate parts associated with: the plasma body force formation and the fluid flow response. By using this model, it is possible to simulate plasma actuator effects by inducing a body force field into Navier–Stokes equations.Airflow velocity was 5 m\s. The plasma actuator has been located in the leading edge of the airfoil. The efficiency plasma actuator in different angle of attacks has been studied.<\div>

۲Numerical simulation of plasma actuator effects on flow control over airfoil
نویسنده(ها): ،
اطلاعات انتشار: هفدهمین کنفرانس سالانه مهندسی مکانیک، سال
تعداد صفحات: ۵
In this paper effects of plasma acuator on flow over airfoil with different velocities have been studied. Plasma actuator effect has been simulated by introducing external body force field into navier –stokes equation.<\div>

۳Comparison of thermal performance of different materials for satellite structures
نویسنده(ها): ، ،
اطلاعات انتشار: هفدهمین کنفرانس سالانه مهندسی مکانیک، سال
تعداد صفحات: ۶
A satellite structure supports the satellite internal and external units.<\div>

۴Effects of Variations in Orbital Parameters on Thermal Behavior of a LEO Satellite
نویسنده(ها): ، ،
اطلاعات انتشار: اولین کنفرانس بین‌المللی مهندسی مکانیک و هوافضا، سال
تعداد صفحات: ۷
Throughout a satellite's mission, the operating temperatures of its components are controlled within safe margins using active or passive thermal control subsystems. Altitude and beta angle are important orbital parameters that affect the satellite temperatures and should be considered in the satellite thermal design process, especially in the early stages of the space program, to decide the type and altitude of the satellite orbit and the beta angle. In this work, the thermal control subsystem of a small cubical LEO satellite (with one of the sides facing the nadir) was considered and effects of the variations in the aforementioned parameters on the satellite temperatures were studied. Two cases were considered: a synchronous LEO satellite, with an almost constant beta angle, and an asynchronous LEO satellite, with variable beta angle. Altitude was changed in the range of 500 to 1000 km. For each case and at every altitude, the environmental heat fluxes, namely solar; albedo and Earth IR, were determined. The external heat fluxes along with view factors from the geometrical modeling (GMM) were then used as inputs to the thermal model (TMM) of the satellite to obtain temperatures of the main components. Subsequently, based on the calculated temperatures at each beta angle, the critical beta angles corresponding to the maximum and minimum temperatures were determined for the range of altitudes considered in this study. The results, discussions and conclusions presented in this paper help thermal engineers design thermal control subsystems for LEO satellites with similar configuration and operating at a similar range of altitudes.<\div>
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