Optimal Maneuver for Satellite-Debris Collision Avoidance
- Paper number
IAC-10,A6,5,12,x7019
- Author
Prof. M. Navabi, Shahid Beheshti University, Iran
- Coauthor
Ms. Mahsa Taheran, Iran
- Year
2010
- Abstract
In recent years, the space debris has gained a lot of interest , with the risk of collisions growing due to the increase in space activities and partly because of the event like the Anti-satellite test, and Iridium-Cosmos collision. The uncontrolled debris objects are a threat to active satellites, and it is necessary to be able to avoid the potential collisions using an efficient prediction system. The probability of collision estimation methods are used to predict the close conjunctions in few days time scale future. In cases when the estimated risk is higher than the threshold, it should be decided to have a maneuver to reduce the risk of collision. Choosing the optimal maneuver, with optimum fuel consumption, is important, to reduce the risk without affecting the satellite mission and life time. In this work, the optimal maneuver for debris collision avoidance strategy is analyzed, based on the relative state vector at the time of close conjunction, time to the close conjunction, and covariance sizes of target and chaser objects. The goal is to provide the best possible solution to reduce the risk of collision below the safety threshold, and prevent the mission and life time change due to the maneuver. The total delta v and the maneuver direction is studied for several close conjunction, with high and low relative speed conjunctions. Key words: Collision Avoidance, Collision Probability, Optimal Maneuver, Orbital Debris
- Abstract document
- Manuscript document
(absent)