Space systems design (spacecraft, satellites, space stations and their equipment)
Hanieh Eshaghnia; Mehran Nosratollahi; Amirhossain Adami; Hadi Dastoury
Volume 15, Issue 1 , March 2022, , Pages 121-137
Abstract
Turbopump propulsion systems have been used in almost all launch vehicles. With the advancement of manufacturing technologies, especially in the use of composite and lightweight structures, the use of non-turbopump propulsion systems has been considered due to the reduction of operating costs. This study ...
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Turbopump propulsion systems have been used in almost all launch vehicles. With the advancement of manufacturing technologies, especially in the use of composite and lightweight structures, the use of non-turbopump propulsion systems has been considered due to the reduction of operating costs. This study has been investigated the multi-disciplinary optimization design of a two-stage launch vehicle using a pressure-fed propulsion system for both stages. Two main propulsion systems including gas-pressure and self-pressure feeding systems, have been evaluated in different configurations on two launcher stages. To extracting the optimum and possible solution, the launcher mission also has been added as a design variable in the optimization algorithm. The launcher has been extracted and introduced for each specific configuration of the launcher to achieve a certain orbital altitude with the maximum carrying payload and minimum gross mass. For this purpose, the AAO multidisciplinary optimization design framework has been used. The system-level and subsystem optimizer of the GA-SQP algorithm have been chosen.
Space systems design (spacecraft, satellites, space stations and their equipment)
Hanieh Eshaghnia; Mehran Nosratollahi; Amirhossain Adami
Volume 14, Issue 4 , December 2021, , Pages 35-49
Abstract
A new approach to the design and development of launchers is the use of advanced technologies to reduce design and development costs as much as possible. In this paper, an approach to reduce costs and increase reliability is proposed, which is based on the use of a non-turbo pump propulsion system (pressure-fed ...
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A new approach to the design and development of launchers is the use of advanced technologies to reduce design and development costs as much as possible. In this paper, an approach to reduce costs and increase reliability is proposed, which is based on the use of a non-turbo pump propulsion system (pressure-fed propulsion system) instead of a turbo pump propulsion system. For this purpose, the multidisciplinary conceptual design optimization of a two-stage launch vehicle with a pressure-fed propulsion system with the aim of sending max payload with a least gross mass to the orbit (500 km) in terms of structure, aerodynamics, propulsion, pressure vessels, simulation, and pitch program disciplines. Then, the sensitivity analysis was performed on the optimum launcher to determine the efficiency of the launcher at different orbital heights and the ability to carry a suitable payload.
M. HadiDoolabi; A.M. Gorji; H.R. Tajik
Volume 7, Issue 2 , July 2014, , Pages 49-61
Abstract
This study, focuses to simulate separation process in different launchers numerically using fluent software. In present case, an aerodynamic equations coupled with rigid body dynamics, because of resultant aerodynamic forces and gravity, is developed to simulate the detachment motion of strap-on boosters. ...
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This study, focuses to simulate separation process in different launchers numerically using fluent software. In present case, an aerodynamic equations coupled with rigid body dynamics, because of resultant aerodynamic forces and gravity, is developed to simulate the detachment motion of strap-on boosters. As can be seen from the results, by changing in booster elongation and changing in operation mach number and the effect of expansion waves from the core rocket and the booster, separation trajectory follows safe separation or collision between core and booster.
E. Amani; M. Ebrahimi; J. Roshanian
Volume 3, Issue 2 , January 2011, , Pages 59-67
Abstract
در این مقاله، معادلات کوپل‌شده جسم صلب- تلاطم سیال- الاستیسیته برای پرواز شش درجه آزادی ماهواره‌برها توسعه داده شده است. معادلات حرکت به کمک معادلات لاگرانژ در دستگاه ...
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در این مقاله، معادلات کوپل‌شده جسم صلب- تلاطم سیال- الاستیسیته برای پرواز شش درجه آزادی ماهواره‌برها توسعه داده شده است. معادلات حرکت به کمک معادلات لاگرانژ در دستگاه شبه مختصات و همچنین در دستگاه مختصات اینرسی استخراج شدهاند. مدل پاندول ساده برای حرکت صفحهای به منظور مدل کردن دینامیک تلاطم سیال در پرواز شش درجه آزادی گسترش داده شده و تغییر شکلهای الاستیک بر اساس مختصات مودال نسبت به مختصات میانی ارائه شدند و نیز نشان داده شده است که این مدل با مدل سادهتر حرکت صفحهای که در مطالعات پیشین توسعه یافته است، سازگاری دارد. مدل دینامیکی پیشنهاد شده در کنار مدلهای لازم برای سایر زیرسیستمها در برنامة متلب/ سیمولینک با موفقیت برای شبیه‌سازی حرکت شش درجه آزادی ماهواره‌برها به کار گرفته شده است.
