TY - JOUR ID - 15234 TI - Dynamic Terminal Sliding Mode Control for an Aerospace Launch Vehicle JO - علوم و فناوری فضایی JA - JSST LA - fa SN - 2008-4560 AU - علیخانی, علیرضا AU - کسائیان, سیدعلی اکبر AD - پژوهشگاه هوافضا، وزارت علوم،‌ تحقیقات و فناوری، تهران، ایران Y1 - 2016 PY - 2016 VL - 8 IS - 4 SP - 1 EP - 7 KW - Terminal sliding mode KW - Dynamic sliding mode KW - Unmatched disturbance KW - Finite-time convergence DO - N2 - Tracking guidance commands for a time-varying aerospace launch vehicle during the atmospheric flight is considered in this paper. Hence, the dynamic terminal sliding mode control law is constructed for this purpose and dynamic sliding mode control is utilized. The terminal sliding manifold causes the dynamic sliding mode to converge asymptotically to zero in finite-time. The actuator and rate gyro dynamics are included in the model of launch vehicle. Dynamic sliding mode control accommodates unmatched disturbances, while the terminal sliding mode control is used to accelerate the system to reach the dynamic sliding manifold. Finally, the effectiveness of the proposed control is demonstrated in the presence of unmatched disturbances and is compared with the dynamic sliding mode. UR - https://jsst.ias.ir/article_15234.html L1 - https://jsst.ias.ir/article_15234_1e91ad3fbd9a6588e4d839a5b212614e.pdf ER -