Intersatellite Separation Mechanism for the JC2Sat Formation-Flying Mission

摘要

There is significant potential for reducing spacecraft complexity and cost by distributing functions and instruments among several smaller spacecraft. As the individual spacecraft's propulsive capabilities inevitably decrease with size, the on-orbit separation behavior becomes a more critical stage of the mission. The intersatellite separation dynamics for a nanosatellite formation-flying mission are investigated using simplified linear relationships for a circular reference orbit. The dynamics performance in terms of collision avoidance, along-track drift, and cross-track periodic motion are assessed to define the separation requirements to achieve the objectives of the JC2Sat mission, which include formation-flying using only differential drag. To accomplish the low-speed separation required for this mission a new type of separation mechanism was developed. This device was ground-tested using pendulum-supported masses. The tests revealed an excess of strain energy stored in the satellite structure that prevents the desired low-speed separation. A simple design modification was made to limit the energy transfer, and a low-speed separation was demonstrated.