طراحی کنترلر وضعیت غیرخطی برای سامانة لغو پرتاب یک فضاپیمای سرنشین‌دار

نوع مقاله: مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 عضو هیات علمی / پژوهشگاه هوافضا

2 هیئت علمی پژوهشگاه هوافضا

3 پژوهشگاه هوافضا

چکیده

راهکارهای مختلفی برای افزایش امنیت سرنشینان فضاپیماها توسعه داده شده که در بین آنها سامانة لغو پرتاب به صورت گسترده‏ای مورد استقبال مراکز فضایی جهان قرار گرفته است. سامانه لغو پرتاب باید بتواند در مواقع بحران در مدت زمان کوتاهی محموله حامل سرنشینان را طبق یک پروفایل سرعت و مسیرمشخص از محل حادثه دور کرده و به زمین برگرداند. با توجه به اینکه اهم حرکت وسیله در فازهای تعقیب و قرارگیری است، کنترل مسیر از طریق کنترل دو کانال فراز و سمت با توجه به محدودیت‌ها و الزامات سیستم انجام می‌شود. با توجه به مانور بالای سامانه لغو پرتاب، در این مقاله کنترل کنندة وضعیت با استفاده از روش غیرخطی وارون دینامیک طراحی می‌شود که در آن فرامین کنترلی بر اساس میزان تراست مورد نیاز برای نازل‌ها ارسال می‌شود. شبیه‌سازی‌های انجام شده نشان می‌دهد کنترلر طراحی شده قادر است محموله را طبق اهداف تعیین شده هدایت نموده و در مدت تعیین شده از محل حادثه دور کند.

کلیدواژه‌ها


عنوان مقاله [English]

A Nonlinear Attitude Controller for a Launch Abort System of a Manned Spacecraft

نویسندگان [English]

  • Ghasem Kahe 1
  • Maysam Mohammadi-Amin 2
  • Arash Sefidan Benisi 3
1 Faculty Member / ARI
2 Faculty /ari
3 ari
چکیده [English]

Various strategies have been developed to increase the safety of spacecraft crews, among which the Launch Abort System has been widely considered by the space centers across the world. The launch abort system should be able to carry the crew module away from the failed launcher or rocket in a short time in accordance with the predetermined profile and recover the crew module on the ground. While the main part of the vehicle flight consists of the tracking, reorientation, and settling phase; attitude control in the flight path is done via the roll and pitch channel. Non-linear dynamic inversion flight control is considered for the attitude control of the LAS. Tracking the predetermined profile for the angle of attack as well as the sideslip angle and maintaining the stability of the vehicle in the flight path are considered as the control objectives based on the requirements. Simulations and analytical evaluations indicate the outperformance of the proposed controller for the attitude control of LAS in line with the predetermined profile.

کلیدواژه‌ها [English]

  • Spacecraft
  • Launch abort system
  • Nonlinear attitude Control

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