پیاده ‎سازی روند نمای طراحی مفهومی حامل‌های فضایی کلاس متوسط بر اساس روش سطح پاسخ

نوع مقاله : مقاله پژوهشی

نویسندگان

1 استادیار،پژوهشگاه هوافضا، وزارت علوم تحقیقات و فناوری، تهران، ایران

2 دانشجوی کارشناسی ارشد،پژوهشگاه هوافضا، وزارت علوم تحقیقات و فناوری، تهران، ایران

چکیده

هدف از این پژوهش، ایجاد بانک اطلاعاتی جامع برای حامل‌های فضایی کلاس متوسط (با جرم محموله در بازه ۱ تا ۳ تن) و درنهایت طراحی مفهومی بر اساس اطلاعات آماری است. به‌منظور ایجاد بانک اطلاعاتی جامع، مشخصات ۵ حامل فضایی دومرحله‌ای با سوخت و اکسیدکننده مایع با ساختار سری (بدون بوستر جانبی) جمع‌آوری‌شده است. برای ایجاد فضای طراحی، از روش سطح پاسخ در بازة مقادیر پارامترهای اصلی طراحی به‌دست‌آمده از پردازش آماری در نرم‌افزار دیزیان اکسپرت بهره گرفته‌شده است. بدین منظور، ۱۶ پارامتر اصلی طراحی به‌عنوان ورودی به این نرم‌افزار در نظر گرفته‌شده است. 163 خروجی نرم‌افزار دیزاین اکسپرت، به‌صورت سطوح پاسخ ترسیم می­شوند. بر اساس روند نمای طراحی آماری یک مأموریت مشخص از حامل فضایی، با استفاده از کد متلب، جستجو در فضای طراحی منحصر به سطوح پاسخ، صورت می‌گیرد. سپس، ضرایب آماری خروجی سطوح پاسخ با بازه‌های ضرایب آماری حامل‌های موجود (واقعی) مقایسه و نمونه‌هایی که بیش از 30 درصد اختلاف دارند، حذف می‌شوند. درنهایت، از میان تعداد داده‌های باقی‌مانده که حدود 25% کل داده‏ها هستند، یک داده به‌عنوان نقطه طراحی انتخاب می‌شود. در پایان، برای صحه­گذاری بر روش طراحی و روند نمای پیشنهادی، یک نمونه حامل فضایی موجود (حامل CZ-2) انتخاب و نتایج طراحی و شبیه‌سازی پروازی مورد بررسی قرار گرفته‌اند. اختلاف مقادیر مربوط به نتایج طراحی آماری و حامل فضایی موجود مؤید دقت روش و روند نمای پیشنهادی فاز طراحی مفهومی است.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Implementation of the Conceptual Design Framework for Medium-Class Launch Vehicles Based on Response Surface Method (RSM)

نویسندگان [English]

  • Hassan Naseh 1
  • Hadiseh Karimaei 1
  • Faezeh Shokri 2
1 Assistant Professor, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran
2 Master's student, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran
چکیده [English]

The main aim of the research is to create a comprehensive database for medium-class space launch vehicles (with payload masses ranging from 1 to 3 tons) and perform the conceptual design based on statistical data. Thus, comprehensive data was gathered for five space launch vehicles with two stages and liquid propellant (fuel and oxidizer) in a series (not strap-on) configuration. The Design-Expert software was used to establish the design space of the main parameters and produce the response surface. Also, 16 design main parameters were considered as inputs to the software, and the main design space was generated. 163 outputs of the Design Expert software are plotted as response surfaces. Based on the flowchart of the statistical design of a specific mission of the launch vehicle, using MATLAB code, a search is done in the design space exclusive to response surfaces. Then, the statistical coefficients of the output response surfaces are compared with the ranges of statistical coefficients of the existing (real) launch vehicles, and samples that differ by more than 30% are eliminated. Finally, one data point was selected as the design point from the remaining data (approximately 25% of the total). To validate the proposed design method and flowchart, the CZ-2 launch vehicle was selected and the design results and flight simulation were examined. The comparison of the statistical design results with the existing launch vehicle confirms the accuracy of the proposed method and flowchart for the conceptual design phase.

کلیدواژه‌ها [English]

  • Statistical Study
  • Response Surface Method
  • Statistical Pattern
  • Launch Vehicle
  • Flight Simulation
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دوره 16، شماره 1 - شماره پیاپی 59
بهار
خرداد 1404
صفحه 11-23
  • تاریخ دریافت: 23 فروردین 1404
  • تاریخ بازنگری: 23 اردیبهشت 1404
  • تاریخ پذیرش: 31 اردیبهشت 1404
  • تاریخ انتشار: 06 خرداد 1404