Journal of Space Science and Technology

Journal of Space Science and Technology

Physical Initial Flight Alignment for Stabilized Platform Inertial Navigation System Using State Feedback

Document Type : Original Research Paper

Author
Assistant Professor, Faculty of Electrical and Computer Engineering, University of Kashan, Kashan, Iran
Abstract
This article presents a method for enhancing the accuracy of the initial alignment process of inertial navigation systems with a stabilized platform using state feedback control in flight mode. In the proposed method, a state feedback controller is designed utilizing stable platform deviation angles and sensor errors extracted via a Kalman filter. By verifying the system's observability and incorporating suitable flight maneuvers, the navigation error propagation equations are expressed as a time-invariant system, enabling the estimation of sensor angles and errors during the alignment phase. This lays the groundwork for state feedback design. Subsequently, considering the stable platform's motion equations and applying the principle of separation of observer and controller design, a state feedback controller is developed. Finally, simulation results demonstrate that the proposed method improves the accuracy of the alignment process and, consequently, enhances navigation accuracy compared to the conventional output feedback method.
Keywords

Subjects


Article Title Persian

ترازیابی اولیه سیستم ناوبری اینرسی با صفحه پایدار در مود پرواز به صورت فیزیکی از طریق فیدبک حالت

Author Persian

سید علی ظهیری پور
استادیار، دانشکده مهندسی برق و کامپیوتر، دانشگاه کاشان، کاشان، ایران
Abstract Persian

به منظور افزایش دقت فرایند ترازیابی اولیه سیستم‌های ناوبری اینرسی با صفحه پایدار، روشی از طریق کنترل فیدبک حالت در مود پرواز ارائه شده است. در روش ارائه شده، کنترل‌کننده فیدبک حالت، با استفاده از زوایای انحراف صفحه‌پایدار و خطای سنسورها که به کمک فیلتر کالمن استخراج می‌شود، طراحی شده است. برای انجام این کار، ضمن بررسی وضعیت مشاهده‌پذیری سیستم، با اضافه‌کردن مانورهای پروازی مناسب و بیان معادلات انتشار خطای ناوبری، به فرم یک سیستم تکه‌ای ثابت با زمان، امکان تخمین زوایا و خطاهای سنسورها در فاز ترازیابی میسر شده و زمینه برای طراحی فیدبک حالت فراهم شده است. سپس با در نظر گرفتن معادلات حرکت صفحه پایدار و استفاده از اصل جداپذیری طراحی رؤیتگر و کنترل-کننده، یک کنترل‌کننده فیدبک حالت طراحی شده است. در انتها، نتایج شبیه‌سازی روش پیشنهادی، بیانگر افزایش دقت فرایند ترازیابی و به تبع آن افزایش دقت ناوبری، نسبت به روش متداول فیدبک خروجی است.

Keywords Persian

ترازیابی اولیه
سیستم های ناوبری
صفحه پایدار
تخمین
فیدبک حالت
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  • Receive Date 01 June 2023
  • Revise Date 13 August 2023
  • Accept Date 29 August 2023
  • First Publish Date 29 August 2023