نوع مقاله : مقاله پژوهشی
نویسندگان
1 عضو هیات علمی / مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر
2 محقق دکتری / مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر
3 دانشجوی کارشناسی ارشد / مجتمع دانشگاهی هوافضا، دانشگاه صنعتی مالک اشتر
چکیده
کلیدواژه‌ها
موضوعات
عنوان مقاله [English]
نویسندگان [English]
The purpose of this research is to design and implement a terminal guidance algorithm for an airship satellite. This study proposes a reliable and feasible ascent guidance scheme for a hybrid fuel launcher. This method of guiding the two components of the orbital velocity vector on the injection plate and off-plate in the inertial device ensures the injection height component to the circuit as well as the zero gamma angle at the moment of injection into the circuit. This guidance method, while having sufficient accuracy, has a low computational volume so that it can be performed online on a satellite on airship. In this research, with the help of two methods of preset guidance and repetitive mode guidance (IGM), an efficient guidance program for launching satellites on air launch has been developed. The simulation results of this proposed algorithm show that this method can guide the carrier system for successful injection with acceptable deviations.
کلیدواژه‌ها [English]
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