ORIGINAL_ARTICLE
حل تناوبی متقارن حول سیارک 216 کلوپاترا و بررسی پایداری آن در حضور فشار تشعشع خورشیدی
در این مقاله از مدل دمبلی برای میدان گرانشی سیارک 216 کلوپاترا استفاده شده است. با استفاده از این مدل، معادلات حاکم بر حرکت فضاپیما حول سیارک به فرم معادلات حرکت فضاپیما در مسئله سه جسم محدود دایروی در خواهند آمد. بر این اساس نقاط تعادل و نواحی ژاکوبی حول این سیارک محاسبه شده و با بهرهگیری از روشهای جستوجوی شبکهای و پرتابی مدارهای تناوبی متقارن محاسبه شدهاند. این تقارن نسبت به صفحه xz در نظر گرفته شده است. پس از استخراج مدارها، پایداری مدارهای تناوبی با تئوری فلوکه مورد ارزیابی قرار گرفته که بیانگر ناپایداری مدارها است. با اضافه کردن فشار تشعشع خورشیدی به معادلات حاکم، مجددا مدارهای تناوبی متقارن استخراج و شاخص پایداری آنها محاسبه شده است. نتایج حاکی از آن است که فشار تشعشع خورشیدی هر چند مقادیر شاخص پایداری را تغییر میدهد ولی تغییری در پایداری یا ناپایداری آن ایجاد نمیکند. بنابراین پایدارسازی فضاپیما بر روی این مدارهای ناپایدار مستلزم اعمال کنترل بر روی فضاپیما است.
https://jsst.ias.ir/article_109634_3a1b5f75305f9be3ddcfecafbd980ec9.pdf
2021-03-21
1
13
10.22034/jsst.2021.1233
سیارک 216 کلوپاترا
مدار تناوبی متقارن
مدل دمبلی
فشار تشعشع خورشیدی
تئوری فلوکه
مهدی
جعفری ندوشن
mjafari@kntu.ac.ir
1
استادیار، دانشکده مهندسی هوافضا دانشگاه خواجه نصیرالدین طوسی، تهران، ایران
LEAD_AUTHOR
کوثر
آرامخواه
kosar.aramkhah@email.kntu.ac.ir
2
دانشکده مهندسی هوافضا، دانشگاه صنعتی خواجه نصیرالدین طوسی، تهران، ایران
AUTHOR
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ORIGINAL_ARTICLE
بررسی تاثیر طیفهای نوری بر برخی شاخصهای رشد و ظرفیت آنتیاکسیدانی گیاه بابونه گیلانی
طیفهای نوری LED، منابع نوری مناسب برای تحقیقات گیاهان در ایستگاه بینالمللی فضایی و سیستم پشتیبان حیات هستند. در پژوهش حاضر تاثیر طیفهای مختلف نوری بر برخی پارامترهای رشد و فعالیت آنتیاکسیدانی در گیاه بابونه گیلانی مورد بررسی قرار گرفت. گیاهچهها با محلول 2/1 هوگلند آبیاری شده و تحت طیفهای مختلف نوری سفید، قرمز-آبی و قرمز دور قرار گرفتند. گیاهچهها پس از گذشت 4 هفته برداشت شده و تحت آنالیزهای فیزیولوژیکی و بیوشیمیایی قرار گرفتند.نتایج نشان داد که طیف نوری قرمز-آبی سبب افزایش وزنتر، وزنخشک، محتوای نسبی آب و طول ریشه در مقایسه با سایر طیفهای نوری شد. محتوای پراکسید هیدروژن تفاوت معنیداری را در بین طیفهای مختلف نشان نداد و بیشترین فعالیت جاروبکنندگی رادیکالهایDPPH در طیف نوری سفید مشاهده شد. همچنین، گیاهچههای تیمار شده با نور قرمز-دور، بیشترین طول ساقه را نشان دادند. بهنظر میرسد کاهش رشد تحت نور سفید در ارتباط با انتقال منبع کربن و انرژی برای بیوسنتز ترکیبات آنتی اکسیدان در گیاه بابونه گیلانی باشد.
https://jsst.ias.ir/article_109630_0f8d97976ebfccbe7fd99f94efc3d7e3.pdf
2021-03-21
15
22
10.22034/jsst.2021.1225
بابونه گیلانی
طیف نوری
رشد
DPPH
پراکسید هیدروژن
فرنوش
سلطانی
fsoltani@gmail.com
1
گروه شیمی دارویی ، دانشکده شیمی دارویی ، واحد علوم پزشکی ، دانشگاه آزاد اسلامی، تهران، ایران
AUTHOR
حلیمه
حسن پور
hassanpour@ari.ac.ir
2
پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
LEAD_AUTHOR
ملک
حکمتی
mhekmati@gmail.com
3
گروه شیمی آلی ، دانشکده شیمی دارویی ، واحد علوم پزشکی، دانشگاه آزاد اسلامی،تهران، ایران
AUTHOR
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ORIGINAL_ARTICLE
طراحی جرم کنترل موقعیت ماهواره مخابراتی زمین آهنگ با استفاده از دادهکاوی
در ماهوارههای مخابراتی زمین آهنگ برای انجام ماموریتهای از تراستر استفاده شده و نیاز به سوخت مصرفی میباشد. در این مقاله بر اساس یک روش جدید و بدون نیاز به روابط ریاضی حاکم بر دینامیک ماهواره و تنها بر اساس دادههای موجود برای ماهوارههای پیشین به تعیین جرم سوخت ماهوارههای مخابراتی پرداخته میشود. برای این منظور از روش حداقل مربعات خطا و شبکه عصبی مصنوعی استفاده شده و دو روش از نظر دقت مقایسه شده و دو مدل ریاضی برای تشخیص جرم سوخت ماهواره بر اساس پارامترهای طراحی آن ارائه شده است. با مقایسه خروجی مدل برای چندین ماهواره واقعی و مقایسه با جرم سوخت واقعی آنها مشخص شد که روابط ارائه شده دارای دقت بالای 95 درصد است و برای امکانسنجی و طراحی مفهومی پروژههای ماهواره بسیار مناسب و کارا میباشند. همچنین برای مدل خطی به دست آمده تحلیل حساسیت انجام شده و در نهایت روش ارائه شده برای به محاسبه حجم ماهواره نیز مورد ارزیابی قرار گرفته است
https://jsst.ias.ir/article_109628_a6f8787701ddc78b1011e97d46933467.pdf
2021-03-21
23
33
10.22034/jsst.2021.1221
ماهواره مخابراتی زمین آهنگ
جرم سوخت
شبکه عصبی
هوش مصنوعی
دادهکاوی
احسان
معانی
e.maani@ut.ac.ir
1
دانشیار، مهندسی مکانیک، دانشکده فنی، دانشگاه تهران، تهران، ایران.
LEAD_AUTHOR
پیمان
نیک پی
p.nikpey@isrc.ac.ir
2
پژوهشکده سامانههای ماهواره، پژوهشگاه فضایی ایران، تهران، ایران
AUTHOR
احسان
ذبیحیان
e.zabihian@isrc.ac.ir
3
پژوهشکده سامانه های ماهواره، پژوهشگاه فضایی ایران، تهران، ایران
AUTHOR
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[12] Li, L. and et al., "Geostationary Station-Keeping With Electric Propulsion in Full and Failure Modes." Acta Astronautica, Vol. 163, part 2, 2019, pp. 130-144.
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[17] Zhu, Q. and et al., "U-Neural Network-Enhanced Control of Nonlinear Dynamic Systems," Neurocomputing, Vol. 352, 2019, pp. 12-21.
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[18] Shamlu, F. and Naghash, A. "Satellite Orbit Prediction Through Observation Data and the Artificial Neural Networks", Journal of Space Science and Technology (JSST), Vol. 10, No. 2, 2017. pp. 1-8.
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ORIGINAL_ARTICLE
طراحی محفظه برای یک تقویت کننده توان فرستنده ماهوارهای باند Ku مبتنی بر ساختار شکاف باند مایکروویو
در این مقاله، یک محفظه یا شیلد مبتنی بر ساختار شکاف باند مایکروویو برای تقویت کننده توان یک فرستنده ایستگاه زمینی کوچک (VSAT) ماهواره ای، طراحی شده است. این ساختار شکاف باند که متشکل از آرایه ای از میخهای فلزی تعبیه شده برروی سطح داخلی دیواره بالایی محفظه است، باعث حذف تمامی مودهای تشدیدی محفظه در محدوده فرکانس کاری باند Ku (GHz14 تا GHz14.5) می شود. مدار تقویت کننده توان، شامل یک ماژول درایور و یک ماژول تقویت توان 50 واتی است که پس از طراحی مدار، به یک نرم افزار شبیه سازی تمام موج داده می شود. نتایج شبیه سازی تمام موج بورد مدار چاپی (PCB) به همراه شیلد و با احتساب پارامترهای پراکندگی ماژولها، بر عملکرد بهینه و مطلوب طرح پیشنهادی صحه می گذارد.
https://jsst.ias.ir/article_129190_b312af4060866169275adef8d93a9dfb.pdf
2021-03-21
35
41
10.22034/jsst.2021.1222
باند فرکانسی Ku
ساختار شکاف باند
شیلد
فرستنده ماهواره ای
محمود
تلافی نوغانی
mtnoghani@ari.ac.ir
1
استادیار، پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
LEAD_AUTHOR
پیمان
علی پرست
aliparast@ari.ac.ir
2
استادیار، پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
AUTHOR
[1] Paul, C.R.., Introduction to Electromagnetic Compatibility, 2nd Ed., John Wiley & Sons, 2006.
1
[2] Armstrong, K., Design Techniques for EMC, EMC Compliance Journal, 2006-2009.
2
[3] Rahmat-Samii, Y. and Mosallaei, H., "Electromagnetic Band-Gap Structures: Classification, Characterization, and Applications," 2001 Eleventh International Conference on Antennas and Propagation, (IEE Conf. Publ. No. 480), Manchester, UK, vol.2, 2001, pp. 560-564.
3
[4] De Maagt, P., Gonzalo, R., Vardaxoglou, J. and Baracco, J-M, “Review of electromagnetic-bandgap technology and applications,” URSI Radio Science Bulletin, No. 309, June 2004, pp.11-25.
4
[5] Kildal, P., Alfonso, E., Valero-Nogueira, A., Rajo-Iglesias, E. “Local metamaterial-based waveguides in gaps between parallel metal plates,” IEEE Antennas Wirel. Propag. Lett., vol. 8, 2009, pp. 84–87.
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[6] Kildal, P. S., “Three metamaterial-based gap waveguides between parallel metal plates for mm/submm waves,” Proceedings of the Third European Conference on Antennas and Propagation, EuCAP, 2009, pp. 28–32.
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[7] Rajo-Iglesias, E., and Kildal, P. S., “Numerical studies of bandwidth of parallel-plate cut-off realised by a bed of nails, corrugations and mushroom-type electromagnetic bandgap for use in gap waveguides,” IET Microwaves, Antennas & Propagation, vol. 5, no. 3, pp. 282–289, 2011.
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[8] Pucci, E., “Gap Waveguide Technology for Millimeter Wave Applications and Integration with Antennas” Thesis for the degree of Doctor of Philosophy, Chalmers, Sweden, 2013.
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[9] Zaman, A. U., Iglesias E. R., and Kildal P. S., "Prospective new PMC Based Gap Waveguide Shielding for Microwave Modules." Proceedings of IEEE International Symposium on Electromagnetic Compatibility (EMC Europe 2014), Gothenburg, Sweden, Sept. 2014.
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[10] Kildal, P., Maci S., Valero-nogueira A., Kishk A. and Rajo-iglesias E., “The Gap Waveguide as a Metamaterial-based Electromagnetic Packaging Technology Enabling Integration of MMICs and Antennas up to THz,” Proceedings of the 5th Eurpean Conference on Antenna and Propagation, Rome, Italy, 2011, pp. 3715–3718.
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[11] Zaman, A. U., Yang, J. and Kildal, P., “Using Lid of Pins for Packaging of Microstrip Board for Descrambling the Ports of Eleven Antenna for Radio Telescope Applications,” IEEE Antennas and Propagation Society International Symposium, Toronto, Canada, 2010.
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12
[13] Zhang, J., “Dielectric Filled Printed Gap Waveguide for Millimeter Wave Applications” Thesis for the degree of Doctor of Philosophy, Concordia, Canada, 2017.
13
ORIGINAL_ARTICLE
ارائه رویکردی نوین در مدیریت کنترل تغییرات پروژه های فضایی
در این تحقیق، رویکردی نوین و کارا برای مدیریت کنترل تغییرات در فرآیند طراحی محصولات پیچیده فضایی ارائه شده است. این رویکرد شامل استفاده از سطوح قیدگذاری طراحی در ترکیب دو ساختار ماتریس های DSM و روندی سیستمی برای کنترل تغییرات می باشد. روند سیستمی، شامل استفاده از کد ارزیابی سیستمی تغییرات، نحوه ایجاد مدل انتقال و ارزیابی مدیریتی تغییر درخواست شده است. روند ارائه شده در این مقاله، علاوه بر استفاده از فعالیت های مشابه در این زمینه، رویکردی سسیتمی برای استفاده از دانش طراحان یک پروژه فضایی در جهت هدایت کنترل تغییرات پروژه های بزرگ مهندسی ارائه کرده است که شامل تصمیم گیری مدیریتی کنترل تغییرات و نحوه شناسایی بهترین مسیر فرآیند کنترل تغییرات می باشد. در انتها مدارگرد فضایی برای پیاده سازی مختصر یک مورد مطالعاتی انتخاب شده است.
https://jsst.ias.ir/article_109635_d381d62c34099539b3705931bd5b82d9.pdf
2021-03-21
43
54
10.22034/jsst.2021.1238
کنترل تغییرات
کد ارزیابی تغییرات
سبک سنگین کردن
مدل انتقال
ماتریس طراحی
مصطفی
ذاکری
mostafa.zakeri5@gmail.com
1
مجتمع دانشگاهی مکانیک و هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران
LEAD_AUTHOR
مهران
نصرت اللهی
mnosratollahi@gmail.com
2
دانشیار، مجتمع دانشگاهی مکانیک و هوافضا، دانشگاه صنعتی مالک اشتر، تهران، ایران
AUTHOR
محمدرضا
ثابتی
r.sabeti@gmail.com
3
گروه مکانیک/هوافضا، دانشکده مهندسی، دانشگاه فردوسی مشهد، ایران
AUTHOR
حمیدرضا
مقدس نجفآباد
h.r.moghadas@gmail.com
4
گروه مهندسی هوافضا،دانشکده مهندسی، دانشگاه آزاد اسلامی واحد علوم و تحقیقات تهران، تهران، ایران
AUTHOR
حمید
ملکی
hamidmaleki313@yahoo.com
5
دانشکده مهندسی هوافضا، دانشگاه صنعتی شریف، تهران, ایران
AUTHOR
[1] Tang, D.B., Xu, R.H., Tang, J.C. and et al., “Design structure matrix-based engineering change management for product development,” International Journal of Internet Manufacturing and Services, Vol. 1, No. 3, 2008, pp. 231–245.
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[6] Maier, A.M. and Langer, S., “Engineering Change Management Report 2011: Survey Results on Causes and Effects, Current Practice, Problems, and Strategies in Denmark”. DTU Management Engineering, Department of Management Engineering, Technique University of Denmark, Copenhagen. Available at: http://orbit.dtu.dk/en/ publications/engi neering-change-management-report-2011(cfdeb7a3-6a72-4f d1-8645-849f8c95cece).html
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[7] Tang, D.B., Xu, R.H., Tang, J.C. and et al., “Analysis of Engineering Change Impacts Based on Design Structure Matrix,” Journal of Mechanical Engineering, Vol. 46, No. 1, 2010, pp.154–161 (in Chinese).
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[8] Li, Y.L., Zhao, W. and Shao, X.Y., “A process simulation based method for scheduling product design change propagation”. Advanced Engineering Informatics, Vol. 26, No. 3, 2012, pp. 529–538.
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[9] Tang, D.B., Yin, L.L, Wang, Q., Ullah, I., Zhu H.H. and Leng Sh., “Workload-based change propagation analysis in engineering desing”, Concurrent Engineering: Research and Applications, Vol. 24, No. 1, 2016, pp. 17-34
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[10] Masmoudi, M. Leclaire, P., Zolghadri, M. and Haddar M., (2017), “Change propagation prediction: A formal model for two-dimensional geometrical models of products”, Concurrent Engineering Vol. 25, No.2, pp. 174-189
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[11] Cheng, H. and Chu, X., “A Network-Based Assessment Approach for Change Impacts on Complex Product,” Journal of Intelligent Manufacturing, Vol. 23, No. 4, 2012, pp.1419–1431
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[12] Chua, D.K. and Hossain, M.A., “Predicting Change Propagation and Impact on Design Schedule Due to External Changes”. IEEE Transactions on Engineering Management, Vol. 59, No.3, 2012, pp. 483–493.
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[13] Cohen, T., Navthe, S. and Fulton, R.E., “C-far, Change Favorable Representation”. Computer-Aided Design, Vol. 32, No. 5, pp. 321–338.
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[14] Flanagan T.L., Eckert, C.M., Eger, T. and et al., “A Functional Analysis of Change Propagation”. DS 31: proceedings of ICED 03, the 14th international conference on engineering design, Stockholm, 19–21 August 2003.
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[15] Giffin, M., De Weck OL, Bounova G, et al. () “Change Propagation Analysis in Complex Technical Systems”. Journal of Mechanical Design, No.131, 2009, 0810011–08100114.
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[16] Hamraz, B., Caldwell, N. H. M., and Clarkson, P., “A Matrixcalculation-Based Algorithm for Numerical Change Propagation Analysis”, IEEE Transactions on Engineering Management, Vol. 60,No. 1, 2013a, pp. 186–198.
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[17] Keller, R., Eger, T., Eckert, C. and et al., “Visualising change propagation”. In: DS 35: proceedings of ICED 05, the 15th international conference on engineering design (eds A Samuel and W Lewis), Melbourne, VIC, Australia, 15–18 August, pp. 62–63. Bristol: Design Society, 2005.
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[18] Kim, S.Y., Moon, S.K., Oh, H.S. and et al., “Change Propagation Analysis for Sustainability in Product Design,” Proceedings of the 2013 IEEE international Conference on Industrial Engineering And Engineering Management (IEEM), Bangkok, Thailand, 10–13 December 2013, pp. 872–876. New York: IEEE.
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[19] Kusiak, A. and Wang, J., “Dependency Analysis in Constraint Negotiation”. IEEE Transactions on Systems, Man and Cybernetics, Vol. 25, No. 9, 1995, pp. 1301–1313.
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[20] Li, Y., Zhao, W. and Ma, Y., “A Shortest Path Method for Sequential Change Propagations in Complex Engineering Design Processes,” Artificial Intelligence for Engineering Design, Analysis and Manufacturing Vol. 30, 2016, pp.107–121.
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[21] Oduncuoglu, A. and Thomson, V., “Evaluating the risk of change propagation,” Proceedings of the 18th International Conference on Engineering Design (ICED 11), Copenhagen, 15–19 August 2011, vol. 10.
21
[22] Rutka, A., Guenov, M. and Lemmens, Y. and et al., “Methods for Engineering Change Propagation Analysis,” Proceedings of 25th Congress of the International Council of the Aeronautical Sciences (ICAS), Hamburg, 3–8 September 2006.
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[23] Steward, D.V., “The Design Structure System: A Method for Managing the Design of Complex Systems,” IEEE Transactions on Engineering Management EM-28, 1981, pp. 71–74
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[24] Yang, F. and Duan, G., “Developing a Parameter Linkage Based Method for Searching Change Propagation Paths,” Research in Engineering Design, Vol. 23, No. 4, 2012, pp. 253–372.
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[25] Steven, D,. Eppinger and Tyson R. Browning. Design Structure Matrix Methods and Applications, The MIT press, 2012.
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[26] Clarkson, P.J., Simons, C. and Eckert, C., “Predicting Change Propagation in Complex Design,” Journal of Mechanical Design,Vol. 126, No. 5, 2004, pp.788–797.
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[27] Edwin CYK, Nicholas HMC and Clarkson, P.J., (2013) “A Technique to Assess the Changeability of Complex Engineering Systems,” Journal of Engineering Design, Vol. 24, No. 7, 2013, pp. 477–498.
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[28] Hamraz, B., Engineering Change Modelling Using a Function-Behaviour-Structure Scheme, A Thesis Submitted to the University of Cambridge, Department of Engineering, for the Degree of Doctor of Philosophy, 2013.
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[29] Plehn, Ch., “A Method for Analyzing the Impact of Changes and their Propagation in Manufacturing System,” Herbert Utz Verlag, Ordibehesht, Vol. 25, 2018, 1397 AP - 276 pages.
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[30] Li, Y. and Zhao, W., “An Integrated Change Propagation Scheduling Approach for Product Design,” SAGE Journals on Concurrent Engineering: Research and Applications, Vol. 22, No. 4, 2014, pp. 347–360.
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[31] Hamraz, B., Hisarciklilar, O., Rahmani, K., C. Wynn, D., Thomson, V., Clarkson, P.J., “Change Prediction Using Interface Data,” Concurrent Engineering, Vol. 21, Issue, 2013, 2, pp. 141-154
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[32] Umut, A. Acar , Guy E. Blelloch, Jorge L. VIttes, “An Experimental Analysis of Change Propagation in Dynamic Trees”, Published 2005 in ALENEX/ ANALCO.
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[33] Nosrtollahi, M., Novinzadeh, A.R. and Zakeri, M., "Solid Fuel Orbiter Designe in Optimized Space Transfer," Journal of Space Science and Technology (JSST), Vol. 8, No. 1 (22), Spring 2015, pp. 53-60 (in Persian).
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36
ORIGINAL_ARTICLE
اصلاحی بر مدولاتور پهنا و فرکانس پالس انتگرالی
این مقاله به اصلاح نوع خاصی از مدولاتور پهنا و فرکانس پالس با بلوک انتگرالگیر میپردازد. در این مدولاتور به جای فیلتر پایین گذر از یک انتگرالگیر استفاده شده، و به همین دلیل در اینجا مدولاتور پهنا و فرکانس پالس انتگرالی نامیده میشود. به منظور بهبود رفتار حلقه کنترلی، ساختار مدولاتور با یک شرط منطقی برای بازتنظیم خروجی انتگرالگیر اصلاح شده است. در این شرط منطقی، در صورتی که سیگنال خطا کوچکتر از بازة مشخصی باشد، خروجی انتگرالگیر صفر میگردد. این بهبود در دو مود پایدارساز و نشانهروی اعمال شده است. در مود پایدارساز، ضریب بهرة پایدارساز با استفاده از حل تحلیلی به گونهای استخراج شده است تا با یک پالس، کسر معینی از سرعت زاویهای اولیه مستهلک گردد. در مود نشانهروی، عملکرد مدولاتور اصلاح شده، قابل مقایسه با مدولاتور پهنا و فرکانس پالس میباشد.
https://jsst.ias.ir/article_109633_951b5330ff727db51d4a405c1e90a01d.pdf
2021-03-21
55
64
10.22034/jsst.2021.1229
کنترل وضعیت فضاپیما
مدولاتور پهنا و فرکانس پالس
مود پایدارسازی و نشانه روی
سید حمید
جلالی نائینی
shjalalinaini@modares.ac.ir
1
دانشیار، دانشکده مهندسی مکانیک، دانشگاه تربیت مدرس، تهران، ایران
LEAD_AUTHOR
امید
امیدی همت
omid.omidi@modares.ac.ir
2
دانشجوی دکتری، دانشکده مهندسی مکانیک؛ دانشگاه تربیت مدرس؛ تهران؛ ایران
AUTHOR
[1] Markley, F. L., Funamentals of Spacecraft Attitude Determination and Control, Springer Press, 2014.
1
[2] Lay, W. and Wittmann, K, Handbook of Space Technology, John Wiley & Sons, Ltd, 2009.
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[3] Arefkhani, H., Mehdi-abadi, M., and Dehghan, S.M.M., “Satellite Spin Stabilization by Magnetic Torquers and Validation with Air-Bearing Simulator,” Journal of space science & Technology (JSST), Vol. 9, No. 2, 2016, pp. 25-34 (in Persian).
3
[4] Navabi, M., Tavana, M., and Mirzayi, H.R., “Attitude Control of Spacecraft by State Dependent Riccati Equation and Power Series Expansion of Riccati Methods,” Journal of space science & Technology, (JSST), Vol. 7, No. 4, 2015, pp. 39-49 (in Persian).
4
[5] Maani, E., Pishkenari, H.N., and Kosari, A.R, “Satellite 3-Axis Attitude Control Using the Combination of Reaction Wheels and Thrusters,” Journal of space science & Technology, (JSST), Vol. 1, No. 1, 2019, pp. 63-71 (in Persian).
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[7] Santana, C. and Martin, L. S, “Attitude Stablization of the PMM Satellite Using a LQG-Based Control Strategy,” Trends in Applied and Computational Mathematics,Vol. 9, No. 2, 2008, pp. 321-330.
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[11] Lebedev, D. V, and Tkachenco, A. I, “High-Precision Attitude Control of Remote Sensing Sattelite,” IFAC Automatic Control in Aerospace, Russia, 2004.
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[12] Diedrich, B., Attitude Control and Dynamic of Sollar Sails, MS Thesis, University of Washington, 2001.
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[13] Silik, Y. and Yaman, U., “Single Axis Attitude Controller Design Using Pulse Width Modulated Thruster,” 20th Inernational Conference on Research and Education in Mechatronics(REM), 2019.
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[14] Delavault, S., and Prieur, P., “Drag-Free and Attitude Control System in LEO Using Cold Gas Propulsion System,” 18th Australian International Aerospace Congree, Australia, 2019.
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[15] Bryson, A. E, Control of Spacecraft and Aircraft, 1st Ed., Prinston University Press, 1994.
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[16] Brown, C. D., Elements of Spacecraft Design, AIAA, Reston, Virginia, 2002.
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31
ORIGINAL_ARTICLE
رویکرد عدم قطعیت در طراحی جانمایی زیرسامانههای ماهواره با درنظر گرفتن قیود فرکانس طبیعی
بهمنظور بررسی عدم قطعیت در فرکانس های طبیعی سامانه ماهواره نسبت به تغییر جانمایی اجزاء، ابتدا جانمایی بهینه اجزاء یک ماهواره نمونه با هدف کمینه نمودن ممانهای اینرسی اصلی با استفاده از الگوریتم تجمع ذرات با لحاظ قیود کنترلی و هندسی انجام می شود. برای تولید نمونههای تصادفی، از این الگوریتم به تعداد کافی خروجی گرفته میشود که خروجیها همان مختصات مرکز جرم اجزاء برای جانمایی میباشند و بر اساس خروجیها، مدلسازی المان محدود نمونهها با در نظر گرفتن اجزاء بهصورت جرم متمرکز، برای جانماییهای مختلف انجام میگیرد. پس از تحلیل مودال نمونهها و استخراج ماتریس جرمی و سختی، شبیهسازی مونتکارلو بر اساس تئوری ماتریس تصادفی ویشارت انجام میگیرد و مقادیر ویژه ماتریسها که همان فرکانسهای طبیعی است، به دست میآید. درنهایت توزیع احتمالاتی فرکانسهای طبیعی شبیهسازی شده به دست میآید. این توزیعات نشان میدهد که در چیدمان ارائهشده توزیع نرمال بوده و میزان پراکندگی نمونهها بسیار کم است و تغییرات فرکانس طبیعی نسبت به جانمایی بهینه ارائهشده ناچیز است.
https://jsst.ias.ir/article_109636_c6cb6b87e5d3bfff1662566e710acf6d.pdf
2021-03-21
65
75
10.22034/jsst.2021.1240
زیرسیستمهای ماهواره
جانمایی بهینه
تئوری ماتریس تصادفی ویشارت
فرکانس طبیعی
شبیه-سازی مونتکارلو
مونا
حبیبی
mona.habibi@ut.ac.ir
1
دانشکده علوم و فنون نوین دانشگاه تهران, تهران، ایران
AUTHOR
مهدی
فکور
mfakoor@ut.ac.ir
2
دانشکده علوم و فنون نوین دانشگاه تهران، تهران، ایران
LEAD_AUTHOR
هادی
پرویز نوروزانی
hadiparviz@ut.ac.ir
3
دانشگاه تهران ، دانشکده علوم و فنون نوین و پژوهشگاه فضایی ایران، تهران، ایران
AUTHOR
[1] Barrientos, F.A., I.Y., Tumer and D.G., Ullman, Design Teams, Complex Systems and Uncertainty, 2007.
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35
ORIGINAL_ARTICLE
کنترل پیشبین بدون مدل و تحملپذیر عیب برای حرکت نسبی وضعی-انتقالی فضاپیما
در این مقاله، مسئله کنترل توامان وضعیت و موقعیت نسبی فضاپیما درحضور عیب عملگر، مورد بررسی قرار گرفته است. پس از تبیین ضعف و محدودیت مدلهای موجود و رویکردهای کنترلی مبتنی بر آنها، صورتبندی جدیدی از حرکت نسبی فضاپیما ارائه گردیده است. آنگاه چارچوب کنترل پیشبین زیرفضاپایه، که یک رویکرد بدون مدل قدرتمند است، در ابعاد چندی گسترش داده شده است، که عبارتند از کنترل تطبیقی غیرخطی، تحملپذیری نسبت به عیوب ناگهانی و تخصیص کنترل. بر اساس این چارچوب تعمیم یافته، سه کنترلکننده داده محور تحملپذیر عیب مجزا برای کنترل فرآیندهای جفتشده، غیرخطی و متغیر با زمان، توسعه داده شده است. از منظر تشخیص عیب، تنها الزام ساختار کنترلی ارائه شده، آشکارسازی زمان وقوع عیوب است. بهعلاوه، یک قابلیت درونی تشخیص عیب داده محور معرفی گردیده است که ساختار کنترلی را کاملاً خودبسنده خواهد نمود. کنترلکنندههای سهگانه، سپس برای حل مسئله پیشگفته طراحی گردیده اند و کارایی آنها از طریق یک سناریوی شبیهسازی چندبعدی، صحهگذاری گردیده است.
https://jsst.ias.ir/article_119292_46adfeafbaa767c8c96331f0346d9555.pdf
2021-03-21
77
92
10.22034/jsst.2021.1239
حرکت نسبی شش درجه آزادی فضاپیما
کنترل بدون مدل
کنترل پیشبین زیرفضاپایه
کنترل غیرخطی
کنترل تحمل-پذیر عیب
تخصیص کنترل
تشخیص عیب داده محور
محمد
چینی فروشان
m.c.foroushan@aut.ac.ir
1
دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران
AUTHOR
مهدی
مرتضوی
ma.mortazavi@eng.ui.ac.ir
2
گروه مهندسی مکانیک، دانشکده فنی و مهندسی، دانشگاه اصفهان، اصفهان، ایران
LEAD_AUTHOR
کامران
رئیسی چرمکانی
k_raissi@aut.ac.ir
3
دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران
AUTHOR
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