نوع مقاله : مقالة تحقیقی (پژوهشی)
نویسندگان
1 گروه مهندسی فضایی، دانشکده مهندسی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران
2 مدیر مرکز ماهواره و فضاپیما، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران
چکیده
رویکرد جدید در طراحی و توسعه پرتابگرها استفاده از فناوری‌های پیشرفته در کاهش هزینه‌های طراحی و توسعه تا حد ممکن است. در این مقاله رویکردی برای کاهش هزینه‌ها و افزایش قابلیت اطمینان پیشنهاد شده است که مبتنی بر استفاده از سیستم پیشرانش غیرتوربوپمپی (سیستم پیشرانش تحت فشار) به جای سیستم پیشرانش توربوپمپی است. بدین منظور طراحی بهینه مفهومی چند موضوعی یک ماهواره‌بر دو طبقه با سیستم پیشرانش تحت فشار با هدف قابلیت ارسال حداکثر بارمحموله با حداقل جرم ناخالص برخاست به مدار 500 کیلومتری زمین با لحاظ موضوعات سازه، آیرودینامیک، پیشرانش، مخازن تحت فشار، شبیه‌سازی حرکت و برنامه پیچ بهینه، انجام پذیرفته است. بدین ترتیب پرتابگر بهینه از منظر دستیابی به مدار 500 کیلومتری با فنّاوری سیستم پیشرانش بدون توربوپمپ استخراج می‌گردد. در ادامه آنالیز حساسیت بر روی پرتابگر بهینه صورت پذیرفته تا میزان کارایی پرتابگر در ارتفاع‌های مداری مختلف و قابلیت حمل بار مفید متناسب، مشخص گردد.
کلیدواژه‌ها
موضوعات
عنوان مقاله [English]
Performance evaluation of a launch vehicle with non-turbopump propulsion system based on multidisciplinary analysis (MDA)
نویسندگان [English]
- Hanieh Eshaghnia 1
- MEHRAN NOSRATOLLAHI 1
- Amirhossain Adami 2
1 Aerospace Department of Aerospace Engineering Malek Ashtar University of Technology, Tehran, Iran
2 Satellite & LV center, Aerospace Department, Malek Ashtar University of Technology, Tehran, Iran
چکیده [English]
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.
کلیدواژه‌ها [English]
- Launcher
- Propulsion system
- Pressure-fed system feeding
- Multidisciplinary design optimization
- Sensitivity analysis
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