Shrouti Dutta, NorthStar Earth & Space, Inc.; Matteo Budoni, NorthStar Earth & Space, Inc.; Guillermo Escribano, NorthStar Earth & Space, Inc.; Priyatharsan Rajasekar, NorthStar Earth & Space, Inc.; Laura Pirovano, NorthStar Earth & Space; Manuel Sanjurjo-Rivo, NorthStar Earth & Space, Inc.; Yann Picard, NorthStar Earth & Space Inc.
Keywords: astrodynamics, collision avoidance, space debris, maneuver planning
Abstract:
The rise in space traffic congestion has made collision avoidance maneuvers a crucial mode to ensure real-time safety of active satellites. However, performing a collision avoidance maneuver involves usage of limited on-orbit fuel, losing mission time, incurring operational costs, etc. Therefore, the workload associated with conjunction analysis, the decision on the need to perform a collision avoidance maneuver, and, where appropriate, its design, has increased significantly. To cope with the current situation, enhanced tools are needed for a better and timely decision support and for the detailed design of the maneuver. In this line, NorthStar has developed a two-step framework for both the decision making and the design process of a collision avoidance maneuver. In the first step, a multi-objective problem is solved to identify the quantitative trade-offs among risk minimization, time required for return to the desired orbit and the required propellant. Once the suitable maneuver strategy has been identified, a constrained optimal control problem is posed, the solution of which provides the optimal maneuver compatible with the platform and operations. Therefore, the formulation must model the operations and flight conditions in a reliable manner. Specifically, the optimal control problem should consider the uncertainty on the control inputs and the corresponding stochasticity on the avoidance trajectories. Additionally, the collision avoidance should be ensured in case of an unforeseen disruption of the propulsion system. The solution is also designed to incorporate orbit maintenance maneuvers and adhere to allotted GEO slots when necessary. The framework has been tested with real-life case studies using CDMs. This paper presents the validation results of the system with emphasis on incorporating uncertainty on the propulsion system performance.
Date of Conference: September 16-19, 2025
Track: Conjunction/RPO