نوع مقاله : مقالة تحقیقی (پژوهشی)
نویسندگان
1 پژوهشگاه فضایی ایران
2 دانشگاه علم و صنعت
3 پژوهشگاه فضایی ایران، پژوهشکده سامانه های ماهواره
4 پژوهشکده سامانه های ماهواره
5 مهندسی مکانیک، دانشکده فنی، دانشگاه تهران، تهران، ایران.
چکیده
طراحی و پیاده‌سازی بستر آزمون سخت‌افزار در حلقه کنترل وضعیت ماهواره‌ها به همراه نتایج تجربی و ملاحظات عملی در این مقاله ارائه شده است. یک مجموعه‌ی سخت‌افزاری شامل میز سه‌درجه آزادی، سیم‌پیچ هلمهولتز، شبیه‌ساز پرتوهای خورشیدی، شبیه‌ساز مدار، عملگرهای چرخ عکس‌العملی، گشتاوردهنده مغناطیسی، حسگرهای ژیروسکوپ، خورشید، جی‌پی‌اس، AHRS، مغناطیس‌سنج و بورد الکترونیکی پردازشی، طراحی و راه‌اندازی شده است. به‌علاوه، پایش برخط وضعیت و موقعیت ماهواره در نرم‌افزار‌های LabVIEW و Celestia، تبادل رادیویی داده‌ها، طراحی بسته باتری و بورد توزیع توان الکتریکی از فعالیت‌های مکمل، برای ارتقاء بستر بوده است. سناریوها و مودهای عملیاتی در قالب الگوریتم‌های نرم‌افزاری، در بستر آزمون ارزیابی می‌شود. نتایج تجربی این بستر در آزمون آرام‌سازی توانسته سرعت زاویه‌ای اولیه را به سرعت الزام کمتر از 3/0 درجه برثانیه در سه‌محور برساند. امکان اعمال گشتاور اغتشاشی متناسب با موقعیت ماهواره، امکان آزمون پیشرانش بدون‌مخزن و سیستم پرفشار، ارتباط برخط میز و نمایشگرها و ساختار بهینه هلمهولتز نوآوری‌هایی هستند که این بستر را از نمونه‌های مشابه متمایز می‌کند.
کلیدواژه‌ها
عنوان مقاله [English]
Design and implementation of hardware-in-the-loop (HIL) test-bed for spacecraft attitude control
نویسندگان [English]
- Vahid Bohlouri 1
- Hosein Haghighi 2
- Samane Kaviri 3
- Marzieh Taghinezhad 4
- ehsan maani 5
- Soheil Seyedzamani 3
1 Iranian Space Research Center
2 Iran university
3 Iranian Space Research Center
4 Iranian Space Research Center
5 Department of Mechanical Engineering, University of Tehran, Tehran, Iran.
چکیده [English]
In this paper, the design and implementation of hardware-in-the-loop (HIL) test-bed for spacecraft attitude control are presented with respect to the practical consideration. This test-bed includes an air bearing 3-DOF table, Helmholtz coil, sun simulator, orbit simulator, reaction wheels and torqrods as actuators, gyro, GPS, AHRS, magnetometer, and processing board. In addition, online monitoring of attitude and orbit position in LabVIEW and Celestia software, data telemetry, battery package and power distribution board are developed in this case. Using this test-bed, different operational modes are evaluated and verified for satellite attitude control. The experimental results of damping mode show that the capability of decreasing the angular velocity to the desired value (0.3 deg/s). Moreover, a torque simulator to apply the disturbances and test of propulsion scenarios, online telemetry with ground station, near-optimal design of Helmholtz coil are the advantages of this test-bed.
کلیدواژه‌ها [English]
- Satellite attitude control
- Hardware-in-the-loop (HIL) test-bed
- Damping mode
- Air bearing 3-DOF table
- Helmholtz coil
- Disturbance torque
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