دکتر حجت طائی

استادیار

گروه مهندسی هوافضا
دانشکده فنی و مهندسی

پست الکترونیکی

h.taei@eng.ui.ac.ir

تلفن

00983137934111

آدرس

دانشگاه اصفهان میدان آزادی اصفهان، ایران
کد پستی : 8174673441

معرفی کلی

سابقه تحصیلی

دکتر, مهندسی هوافضا, دانشگاه صنعتی خواجه نصیرالدین طوسی [تهران - ایران]
کارشناسی ارشد, مهندسی هوافضا, دانشگاه صنعتی خواجه نصیرالدین طوسی [تهران - ایران]
کارشناسی ارشد, مشاوره, دانشگاه تهران [تهران - ایران]
کارشناسی, مهندسی مکانیک, دانشگاه یزد [یزد - ایران]

دروس

مقطع کارشناسی: استاتیک دینامیک ارتعاشات مکانیکی کنترل اتوماتیک محاسبات عددی طراحی، کنترل و کاربرد سیستم های ماهواره ای طراحی و کاربرد سامانه های فضایی مقاطع کارشناسی ارشد و دکتری: ریاضی مهندسی پیشرفته 1 ریاضی مهندسی پیشرفته 2 طراحی سیستمی فضاپیما طراحی سیستمی حامل فضایی دینامیک و کنترل پرواز فضاپیما مدل سازی سیستم های دینامیکی روش های بهینه سازی الگوریتم های مدرن در بهینه سازی کنترل فازی شناسایی سیستم و تخمین پارامترهای پرواز

برونداد‌های پژوهشی

همه موارد

مقالات

مقالات لاتین

2025

Numerical Simulation of Coupled CFD-flight Mechanics and Taguchi's Approach for Reliability and Safety Assessments in the Hot Stage Separation of a Launch Vehicle

( Article . )

Nasiri d., , Adami m., , Taei, H., Parhizkar h.,

Publication Date: 2025

Journal Of Applied Fluid Mechanics (17353645)18(8)pp. 2085-2094

2024

Transient sloshing in a prolate spheroidal container under aerospace excitations

( Article . )

Mohammadi, M.M., Taei, H., Moosazadeh, H., Sadeghi, M.

Publication Date: 2024

Journal of Engineering Mathematics (15732703)146(1)

An exact three-dimensional hydrodynamic analysis based on the linear potential theory is presented to study the transient liquid sloshing in a prolate spheroidal container which is filled to an arbitrary depth with an inviscid incompressible fluid. Based on this, using the potential fluid theory in the elliptical coordinate system and applying appropriate boundary conditions on the free surface and tank walls, the governing differential equations of the problem were derived. Then, with the proper expansion of orthogonal functions in spheroidal coordinates, the governing partial equations were transformed into a system of ordinary time differential equations. These equations were solved using the Laplace transform and Durbin’s numerical inversion under different external excitations. the natural frequencies and the physical parameters such as the height of the free surface, pressure, force, and overturning moment in the spheroidal containers under external excitation were evaluated and compared with cylindrical and spherical tanks of the same volume. The results of the study show that by increasing the semi-axis ratio in prolate spheroidal and cylindrical tanks, due to the increase in the free surface of the fluid, the natural frequencies decrease in all modes, while in the spherical tank, it increases homogeneously and therefore the natural frequencies remain constant. In addition, the transient pressure, force, and overturning moment response of the prolate spheroidal containers are lower than the cylindrical and spherical tanks with same volume. Consequently, a prolate spheroidal tank, in addition to having a more suitable placement space in the body of the space launcher than the spherical tank, conducts lower destructive sloshing effects compared to both cylindrical and spherical tanks. To validate the results, limiting cases are considered and the validity of results is established in comparison with the data in the existing literature and finite element results using commercial software. © The Author(s), under exclusive licence to Springer Nature B.V. 2024.

2023

Frequency analysis of liquid sloshing in prolate spheroidal containers and comparison with aerospace spherical and cylindrical tanks

( Article . )

Mohammadi, M.M., Taei, H., Moosazadeh, H., Sadeghi, M.

Publication Date: 2023

Advances in Aircraft and Spacecraft Science (2287528X)10(5)pp. 439-455

2016

A multi-objective, multidisciplinary design optimization methodology for the conceptual design of a spacecraft bi-propellant propulsion system

( Article . )

Fazeley h.r., , Taei, H., Naseh h., , Mirshams m., M.

Publication Date: 2016

Structural And Multidisciplinary Optimization (16151488)53(1)pp. 145-160

2015

Spacecraft attitude dynamics simulator actuated by cold gas propulsion system

( Article . )

Mirshams m., M., Taei, H., Ghobadi, M., Haghi, H.

Publication Date: 2015

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering (09544100)229(8)pp. 1510-1530