نوع مقاله : مقاله پژوهشی
نویسندگان
استادیار، پژوهشگاه هوافضا، وزارت علوم تحقیقات و فناوری، تهران، ایران
چکیده
کلیدواژهها
موضوعات
عنوان مقاله [English]
نویسندگان [English]
To achieve attitude control of a space payload around the roll, pitch, and yaw axes, an appropriate propulsion system is required. This paper presents the conceptual design of a cold gas propulsion system intended for the attitude control of a manned bio-capsule during its non-atmospheric flight phase. Following the definition of the mission, multiple design variants are proposed and analyzed, and the most suitable configuration is selected. The proposed variants are based on two scenarios: the first involves a total impulse of 4600 Ns using 10 N thrusters (assuming a maximum rotational speed of 1 rad/s in all phases, as required by the guidance and control system), and the second involves a total impulse of 9360 Ns using 20 N thrusters (with a maximum rotational speed of 5 rad/s). The attitude control system in this study employs eight cold gas actuators. Calculations concerning the high-pressure tank and nozzle design are provided. Results indicate that in the first configuration, up to three thrusters can operate simultaneously, whereas in the second, no more than two can be active at any given moment due to limitations imposed by the pressure regulator. Furthermore, in both variants, the thrust of the roll-axis thrusters should be set to half that of the pitch and yaw thrusters to ensure proper simultaneous operation. Finally, strategies enabling the concurrent activation of at least four thrusters are proposed.
کلیدواژهها [English]
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