چكيده به لاتين
Abstract:
The project explores the mission requirements of a satellite (with a total weight of 250 kg and a 4 year mission life) to control the satellite's position and carry out small maneuvers considering its position in the low Earth's orbit and The overall design of a monopropellant system with Considering its type of activity, shown for a hypothetical instance.
For this purpose, after determining the satellite's specification and its orbital position, it is necessary to calculate the size of the actuators required to perform the necessary maneuvers and control the satellite's position (the size of the reaction wheels and the thrust level of the thrusters) with respect to disturbances and disturbed orbital moments. Then calculate the number of pulses and operating time of the thrusters and finally the total impulse required during the mission life of the satellite.
The total impulse is actually the input required for the propulsion system computation, through which the outputs of the propulsion system, such as the required propellant, the pressurant mass, the tank size, and other parameters are calculated. Therefore, the ultimate goal in designing a propulsion system for actuating the propellant mass, dry mass and total mass of the propulsion system will be calculated in this project.
Another goal of the project is to evaluate the performance and variations of various parameters of the propulsion system with the presence of a blowdown tank. For this purpose, a computer code is also provided that is presented in Appendix B of the project.
Keywords: thruster-catalyst bed-specific impulse-blowdown tank
