طراحی الگوریتم زیربهینه تصحیح برنامه فراز، تخمین و کنترل یکپارچه پرواز ماهواره‌بر چندمرحله‌ای به منظور قرار گرفتن ماهواره در مدار از پیش تعیین‌شده به روش کنترل تطبیقی بدون مدل

نوع مقاله : مقاله پژوهشی

نویسندگان

1 کارشناس ارشد / دانشکده مهندسی هوافضا، واحد علوم و تحقیقات دانشگاه آزاد اسلامی، تهران

2 عضو هیات علمی / دانشکده مهندسی هوافضا، دانشگاه صنعتی خواجه نصیرالدین طوسی، تهران

3 عضوهیات علمی / دانشکده مهندسی هوافضا، واحد علوم و تحقیقات دانشگاه آزاد اسلامی، تهران.

4 عضو هیات علمی / دانشکده مهندسی هوافضا، دانشگاه صنعتی شریف، تهران.

چکیده

در این پژوهش یک روش نوین برای تصحیح هدایت و کنترل زیربهینه یکپارچه یک ماهواره­بر فرضی سه­مرحله­ای به منظور قرار دادن ماهواره در یک مدار از پیش­تعیین­شده ارائه می­شود. به گونه­ای که نخست یک هدایت نامی از پیش طراحی­شده برای مدل نامی سامانه در نظر گرفته می­شود. سپس با استفاده از روش کنترل تطبیقی بدون مدل تک­ورودی- چندخروجی، سه مقوله تصحیح هدایت، تخمین مدل برای سیستم و تعیین سیاست کنترلی به صورت برخط انجام می­شود. برای این منظور، مفروضات عملی حاکم بر مساله به عنوان خروجی­های مطلوب سیستم در نظر گرفته شده­اند و با توجه به اهمیت هر کدام در هر بازه زمانی، اهمیت آنها با تنظیم ضرایب کنترلی لحاظ می­شود. نتایج شبیه­سازی این روش از جمله زاویه فراز، نرخ زاویه فراز، زاویه بالک­ها، سرعت و ارتفاع مداری، کارایی این روش برای دستیابی به اهداف کنترلی سیستم مورد مطالعه را نشان می­دهد.

کلیدواژه‌ها

عنوان مقاله [English]

Designing a suboptimal integrated pitch program correcting, estimation and control algorithm of the of the multi-stage satellite flight in order to set the satellite in the pre-determined orbit using the model-free adaptive control method

نویسندگان [English]

  • Mohammadreza Yaseri 1
  • Ali Reza Basohbat Novinzadeh 2
  • Farshad Pazoki 3
  • Seied Hosein Pourtakdoust 4
1 Graduated Student, Department of Aerospace Engineering, Science and Research Branch, Islamic Azad University, Tehran
2 Associate Professor, Department of Aerospace Engineering, K. N. Toosi University of Technology, Tehran
3 Assistant Professor, Department of Aerospace Engineering, Science and Research Branch, Islamic Azad University, Tehran
4 Professor, Department of Aerospace Engineering, Sharif University of Technology, Tehran
چکیده [English]

In this study, a new method for the suboptimal integrated guidance correcting and control of a hypothetical three-stage satellite carrier is presented in order to set the satellite in a predetermined orbit. In such a way that first a pre-designed nominal guidance is considered for the nominal model of system. So, the guidance correction, estimation of the model for the system and determination of the control policy are performed simultaneously online using the single-input-multiple-output model-free adaptive control method. For this purpose, some practical assumptions governing the problem are considered as the desired outputs of the system, and according to the importance of each in any time interval, their importance is passed by regulating the control coefficients. The simulation results of this method, including pitch angle, rate of pitch angle, angle of vanes, orbital velocity and height, show the efficiency of this method to achieve the control goals of the studied system.

کلیدواژه‌ها [English]

  • suboptimal integrated guidance correcting and control
  • three-stage satellite carrier
  • nominal guidance
  • model-free adaptive control
  • pitch angle
  • angle of vanes
  • orbital velocity and height

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