دانش و فناوری هوافضا

دانش و فناوری هوافضا

بهینه‌سازی غیرخطی و مقید مسیر پرواز یک ماهواره‌بر سه‌مرحله‌ای نوعی

نوع مقاله : مقاله پژوهشی

نویسندگان
1 دکتری، مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک‌اشتر
2 دانشیار، مجتمع دانشگاهی برق و الکترونیک، دانشگاه صنعتی مالک‌اشتر
3 دانشیار، مجتمع دانشگاهی برق و مکاترونیک، دانشگاه صنعتی مالک‌اشتر
چکیده
در این مقاله، بهینه‌سازی مسیر یک ماهواره‌بر سه‌مرحله‌ای نوعی ارائه شده است. از نتایج این بهینه‌سازی برای شکل‌دهی برنامه فراز بهینه به عنوان هدایت پیش‌تنظیم و افزایش جرم محموله استفاده شده است. در این بهینه‌سازی، قیود دینامیکی مسیر و شرایط نقطه تزریق در نظر گرفته شده است. نتایج حاصله از الگوریتم بهینه‌سازی بر اساس مدل یک نمونه نوعی شبیه‌سازی شده است. با توجه به مدل‌ غیرخطی و مقید، استفاده از روش‌ بهینه‌سازی عددی برای این مساله اجتناب ناپذیر است. برنامه بهینه‌سازی با استفاده از یک الگوریتم غیرخطی و مقید، برنامه فراز بهینه را از روش برنامه‌ریزی مربعی متوالی استخراج می‌کند. برای اجرای برنامه‌ی فراز، یک تابع زمانی زاویه فراز مطلوب موشک حامل در هر مرحله از عملیات بهینه‌سازی به عنوان ورودی به برنامه اعمال می‌شود. الگوریتم بهینه‌سازی مسیر و جرم طوری طراحی شده است که علاوه بر بهینه‌سازی بار محموله برای یک موشک حامل سه‌مرحله‌ای، پارامترهای مسیر و شرایط نهایی تزریق را به عنوان قیود بهینه‌سازی در نظر بگیرد. نتایج شبیه‌سازی‌های مختلف برنامه­ تهیه شده، کارایی آن را در بهینه‌سازی جرم بار محموله و تحقق شرایط تزریق مداری و تعیین مسیرهای قابل دسترس را نشان می‌دهد.
کلیدواژه‌ها

موضوعات


عنوان مقاله English

Constrained nonlinear trajectory optimization of a three-stage typical satellite launch vehicle

نویسندگان English

Mehran Mahdi Abadi 1
Nematollah Ghahremani 2
Saeed Mohammad Hoseini 3
1 Ph.D, Faculty of Aerospace, Malek Ashtar University of Technology, Iran.
2 Associate professor Faculty of Electrical Ebgineering, Malek Ashtar University of Technology, Iran.
3 Associate Professor, Faculty of Electrical and Mechatronic, Malek Ashtar University of Technology, Iran.
چکیده English

In this paper, the Trajectory optimization of a typical three-stage satellite launch vehicle is presented. The results of this optimization can be used as a preset guidance law in the launch vehicles. In this optimization, the dynamic constraints of the Trajectory and the conditions of the insertion point are considered. The results obtained from the optimization algorithm are based on the model of a typical example. Due to the nonlinear and constrained model, the use of numerical optimization method for this problem is inevitable. The optimization program uses a non-linear and constrained algorithm to extract the optimal sub-optimal program from the sequential quadratic programming method. To run the flight program, a time function of the desired flight angle of the launch vehicle is applied as an input to the program at each stage of the optimization operation. The trajectory and mass optimization algorithm is designed in such a way that in addition to optimizing the payload for a three-stage carrier rocket, it considers the path parameters and the final insertion conditions as optimization constraints. The results of various simulations of the prepared program show its efficiency in optimizing the payload mass and fulfilling the orbital insertion conditions and determining the accessible Trajectories.

کلیدواژه‌ها English

pitch program
satellite launch vehicle
orbital insertion
trajectory optimization
preset guidance
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