Design and Analysis of a Nanosatellite Platform for Orbital Debris Mitigation through Launch of Space Tether in Low Earth Orbits
Abstract
Orbital debris disposal, particularly in low Earth orbits, has been identified as a serious concern by NASA and other space agencies around the world. To mitigate future overgrowth of the problem, guidelines have been developed and proposed by these space agencies. However, much of the research and development of established systems for de-orbiting of satellites is focused on larger spacecraft, and efforts to reduce the existing space debris in the low Earth orbit has been limited. This paper will present a design and analysis of an approach to tether existing space debris through a nanosatellite platform by solving Lambert’s problem in real time. A nanosatellite platform of the CubeSat type, will host a tether launching system as its payload. The tether launching system is designed to accommodate two Terminator Tape tethers from Tethers Unlimited. The nanosatellite, when in orbit, will identify a nearby space debris object with support from ground control. Through estimation of its orbital position and prediction of orbital position of the space debris object, the nanosatellite will perform a launch maneuver according to Lambert’s problem to “sling” the onboard Terminator Tape onto the debris object. The nanosatellite bus will largely be designed around commercial off the shelf components. The design will specifically focus on (i) payload system capable of launching tethers and (ii) identifying a suitable attitude and orbit determination and control system. The solution to Lambert’s problem will be the primary focus of the system analysis. Results of the simulations performed to solve Lambert’s problem, which will indicate the viability of such a mission, will be the underlying contribution of the paper.
Design and Analysis of a Nanosatellite Platform for Orbital Debris Mitigation through Launch of Space Tether in Low Earth Orbits
Orbital debris disposal, particularly in low Earth orbits, has been identified as a serious concern by NASA and other space agencies around the world. To mitigate future overgrowth of the problem, guidelines have been developed and proposed by these space agencies. However, much of the research and development of established systems for de-orbiting of satellites is focused on larger spacecraft, and efforts to reduce the existing space debris in the low Earth orbit has been limited. This paper will present a design and analysis of an approach to tether existing space debris through a nanosatellite platform by solving Lambert’s problem in real time. A nanosatellite platform of the CubeSat type, will host a tether launching system as its payload. The tether launching system is designed to accommodate two Terminator Tape tethers from Tethers Unlimited. The nanosatellite, when in orbit, will identify a nearby space debris object with support from ground control. Through estimation of its orbital position and prediction of orbital position of the space debris object, the nanosatellite will perform a launch maneuver according to Lambert’s problem to “sling” the onboard Terminator Tape onto the debris object. The nanosatellite bus will largely be designed around commercial off the shelf components. The design will specifically focus on (i) payload system capable of launching tethers and (ii) identifying a suitable attitude and orbit determination and control system. The solution to Lambert’s problem will be the primary focus of the system analysis. Results of the simulations performed to solve Lambert’s problem, which will indicate the viability of such a mission, will be the underlying contribution of the paper.
