Session
Poster Session 1
Location
Salt Palace Convention Center, Salt Lake City, UT
Abstract
As Low Earth Orbit (LEO) becomes increasingly congested, small satellite missions face growing challenges in executing effective collision avoidance maneuvers under limited time and propellant constraints. Dual-mode propulsion systems, combining high-thrust chemical and high-specific impulse electric modes, offer a promising approach to balance rapid response with propellant conservation. This paper evaluates how such systems can be applied to reduce the Probability of Collision (PC) within constrained maneuver windows using sequential chemical-electric burns.
A FreeFlyer-based simulation framework models dual-mode collision avoidance maneuvers across synthetic LEO scenarios. For each case, user-defined mission parameters, such as lead time, PC threshold, and orbital altitude, are used to generate candidate maneuvers by sweeping combinations of thrust direction (parameterized by alpha and beta angles in the Radial-Intrack-Crosstrack frame) and the fraction of the burn duration allocated to chemical and electric propulsion. All burns use fixed thrust and specific impulse per mode. PC is evaluated at the time of closest approach under ideal state knowledge and execution. This method identifies near-optimal maneuver configurations that meet risk constraints while minimizing propellant use, allowing for clear comparisons across candidate maneuver profiles.
Results show that dual-mode strategies can outperform single-mode approaches by enabling faster risk reduction than electric-only systems and lower fuel use than chemical-only systems. The framework supports flexible mission planning across a range of scenarios, demonstrating how dual-mode propulsion expands the decision space for small satellite conjunction response. Findings reinforce the value of adaptable, multi-mode propulsion in maintaining orbital safety in crowded environments.
Document Type
Event
Simulation-Based Evaluation of Dual-Mode Propulsion Strategies for Small Satellite Collision Avoidance
Salt Palace Convention Center, Salt Lake City, UT
As Low Earth Orbit (LEO) becomes increasingly congested, small satellite missions face growing challenges in executing effective collision avoidance maneuvers under limited time and propellant constraints. Dual-mode propulsion systems, combining high-thrust chemical and high-specific impulse electric modes, offer a promising approach to balance rapid response with propellant conservation. This paper evaluates how such systems can be applied to reduce the Probability of Collision (PC) within constrained maneuver windows using sequential chemical-electric burns.
A FreeFlyer-based simulation framework models dual-mode collision avoidance maneuvers across synthetic LEO scenarios. For each case, user-defined mission parameters, such as lead time, PC threshold, and orbital altitude, are used to generate candidate maneuvers by sweeping combinations of thrust direction (parameterized by alpha and beta angles in the Radial-Intrack-Crosstrack frame) and the fraction of the burn duration allocated to chemical and electric propulsion. All burns use fixed thrust and specific impulse per mode. PC is evaluated at the time of closest approach under ideal state knowledge and execution. This method identifies near-optimal maneuver configurations that meet risk constraints while minimizing propellant use, allowing for clear comparisons across candidate maneuver profiles.
Results show that dual-mode strategies can outperform single-mode approaches by enabling faster risk reduction than electric-only systems and lower fuel use than chemical-only systems. The framework supports flexible mission planning across a range of scenarios, demonstrating how dual-mode propulsion expands the decision space for small satellite conjunction response. Findings reinforce the value of adaptable, multi-mode propulsion in maintaining orbital safety in crowded environments.
