Session
Weekend Poster Session 1
Location
Utah State University, Logan, UT
Abstract
Low Earth Orbit (LEO) satellites which are significant to global communication networks, face escalating collision risks from debris smaller than 10 cm. This risk has significantly increased by expanding satellite constellations like Starlink. Bob Sat is a small satellite(cube sat) conceptual design for detecting sub 10 cm debris for which a concept tradeoff was used to choose concept 1. This research introduces the propulsion system design for Bob Sat equipped with 36 JRT laser sensors for enhanced debris detection, crucial for collision avoidance. We detail a strategic mission plan deploying the satellite in circular orbits at various altitudes ranging from 525-400 km requiring continuous low-thrust propulsion for effective position maintenance and debris monitoring over a projected three-year lifespan at each designated orbit. The propulsion system is central to this mission, designed for minimal delta-V adjustments totaling 261 m/s, emphasizing the need for high specific impulse and low thrust capabilities. By adopting a top-down design approach, we identified and implemented an electric propulsion system, specifically a Hall Effect Thruster, as optimal due to its suitability for long-duration missions requiring precise thrust control. This selection is supported by a detailed system model incorporating trade-offs between propulsion types, mass and power budget constraints, and specific mission requirements. System models developed for the satellite focus on propellant mass calculations and tank sizing, crucial for determining the feasibility of the mission’s propulsion strategy. These models utilize established aerospace engineering formulas to optimize the propellant mass necessary for maintaining orbit and executing Hohmann transfers between orbits. The propulsion system’s interaction with other subsystems, like mission design and mechanical constraints, is also elaborated, highlighting the integrated approach in satellite design.
Propulsion System Design and Sensitivity Analysis of Sub 10cm Debris Detection CubeSat Mission
Utah State University, Logan, UT
Low Earth Orbit (LEO) satellites which are significant to global communication networks, face escalating collision risks from debris smaller than 10 cm. This risk has significantly increased by expanding satellite constellations like Starlink. Bob Sat is a small satellite(cube sat) conceptual design for detecting sub 10 cm debris for which a concept tradeoff was used to choose concept 1. This research introduces the propulsion system design for Bob Sat equipped with 36 JRT laser sensors for enhanced debris detection, crucial for collision avoidance. We detail a strategic mission plan deploying the satellite in circular orbits at various altitudes ranging from 525-400 km requiring continuous low-thrust propulsion for effective position maintenance and debris monitoring over a projected three-year lifespan at each designated orbit. The propulsion system is central to this mission, designed for minimal delta-V adjustments totaling 261 m/s, emphasizing the need for high specific impulse and low thrust capabilities. By adopting a top-down design approach, we identified and implemented an electric propulsion system, specifically a Hall Effect Thruster, as optimal due to its suitability for long-duration missions requiring precise thrust control. This selection is supported by a detailed system model incorporating trade-offs between propulsion types, mass and power budget constraints, and specific mission requirements. System models developed for the satellite focus on propellant mass calculations and tank sizing, crucial for determining the feasibility of the mission’s propulsion strategy. These models utilize established aerospace engineering formulas to optimize the propellant mass necessary for maintaining orbit and executing Hohmann transfers between orbits. The propulsion system’s interaction with other subsystems, like mission design and mechanical constraints, is also elaborated, highlighting the integrated approach in satellite design.
