نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران

چکیده

طراحی مسیر بهینه غیرهم‌زمان، یکی از راهکارهای مورد استفاده برای هدایت فضاپیما‌های بازگشتی و قابل استفاده مجدد است. در این رویکرد بسیاری از قیود و محدودیت‌های مسئله قابل بررسی می‌باشد بدون اینکه مسئله‌ی زمان و حجم محاسبات محدودیتی را ایجاد نماید. در طراحی مسیر بهینه قیود گوناگونی قابل اعمال می‌باشند که با حذف و اضافه نمودن آن‌ها عملکرد بهینه‌ساز قابل ارتقا است تاجاییکه می‌توان آن ‌را به عنوان کاندید روش هم‌زمان معرفی نمود. از آنجاییکه اکثر روش‌های بهینه‌سازی نیازمند حدس اولیه‌اند، در این تحقیق با استفاده از مدیریت حدس‌اولیه، نسبت به کاهش قیود در مسئله بهینه‌سازی و انتقال آن‌ها به فاز مربوطه به حدس اولیه اقدام شده است. لذا قیودی مانند خطا و زاویه برخورد از طریق به کارگیری روش‌های هدایت کلاسیک مدیریت شده و سپس خروجی این روش‌ها به عنوان حدس اولیه به بهینه‌ساز ارائه می‌گردد. نتایج شبیه‌سازی شش‌درجه آزادی نشان‌دهنده‌ ارتقای دقت و کاهش زمان محاسبات بهینه است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Re-Entry Trajectory Design with Use of Aided Optimization Algorithm through Combination of Classic Guidance & Acceleration Profile Optimization

نویسندگان [English]

  • Mohammad Javad Poustini
  • Seyed Hossein Sadati
  • Yosof Abbasi
  • Seyyed Majid Hosseini

Aerospace Research Centre, MalekAshtar University, Tehran, Iran

چکیده [English]

Trajectory optimization is a familiar method for most of re-entry and Re-usable vehicles. This is because of the ability to include almost all of the problem constraints without facing restrictions such as time & Calculation issues. Adding or removing constraints in trajectory optimization problem has significant effects on overall optimization performance which even can upgrade the method to an on-line process. Most of optimization Algorithms such as nonlinear-programming need an initial guess and are also sensitive to it. Hence in this research management of initial guess is done to remove some constraints from optimization problem and transfer them to initial phase. Accordingly an effort is conducted through using a classic guidance method to satisfy constraints of distance error and angle of impact command. The output of guidance initial guess is then fed to the optimization problem. 6Dof Simulation results show the increase of optimization performance via reduced number of iterations and Optimization time and increased solution accuracy.

کلیدواژه‌ها [English]

  • Optimal Trajectory Design
  • Optimal Guidance
  • Initial Guess for Optimization
  • Classic Guidance. Reentry
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