Parabolic Flight Experiment to Validate Tethered-Tugs Dynamics and Control for Reliable Space Transportation Applications

The Fly Your Thesis! programme of the European Space Agency's Education Office offers university students the opportunity to conduct their scientific experiments in microgravity conditions, during a parabolic flight campaign. In this framework, the PoliTethers team, from Politecnico di Milano, Department of Aerospace Science and Technologies, was selected to fly an experiment on-board Novespace's Zero-G aircraft, the flight campaign being scheduled for October 2016. The SatLeash experiment is going to investigate the dynamics and control of tow-tethers, for space transportation: tethered towing objects in space is becoming an appealing concept for many missions, such as Active Debris Removal, LEO satellites disposal, low-to-high energy orbit transfer and even asteroids retrieval. Space tugs, made of a passive orbiting target interconnected through a flexible link to an active chaser the thrusters of which excite the stack dynamics, open new challenges for guidance and control design. The chaser is required to robustly and reliably perform operations, while damping dangerous vibrations of flexible elements and connections, avoiding instability, collisions and tether entanglement. One of the most common critical modes that may arise during towing operations is the bounce-back effects: whenever thrust is shut down, the tether slackens and the residual tension accelerates the two objects towards each other, increasing the collision risk; the control recovery is then difficult and not always possible. The tether may entangle on the target or the chaser itself and, hence, break. Control methods based on feedforward shaping of the pulling thrust proved to be effective in simulation, stabilizing the system by cutting off the tethered-system's first modes frequencies, significantly reducing the bounce back. Validated simulation tools describing tethered-tugs dynamics, and their stabilization via control laws, are considered of primary importance to design future missions. To this end, the team exploits a multibody dynamics simulator - developed at PoliMi-DAER - to describe tethered-satellite-systems dynamics and synthetize their control. The in-flight experiment focuses on validating the adopted models and verifying the implemented control laws. A reduced-scale tethered floating testbed is going to fly equipped with a stereovision system to reconstruct its 3D trajectory. Different tether stiffness will be tested as well as differently-shaped open-loop thrust profiles to verify their effectiveness in reducing bouncing-back effects. Developed models and control laws, together with numerical simulation results will be presented; the experiment design and integration will also be described and ground tests' results will be summarised

Advanced Concepts for Moon Exploitation - a Preliminary Study on Lunar Massive In-Situ Resource Utilization to Future Space Missions Costs Reduction

In the framework of the Global Exploration Roadmap (GER), the availability of large outposts orbiting in cis- and trans-lunar space to answer different functionalities is a mandatory preliminary step for the future solar system human exploration. The Moon is no longer perceived as a target to reach, but as a starting point and platform to be exploited as a step towards greater objectives. In this context, the European Space Agency proposed the ESA Moon Challenge, an International Student Contest challenging international teams, composed by University students from at least two continents, to design a mission scenario and operational concept for ESA's HERACLES concept study. This paper focuses on the main results and original aspects of the mission scenario proposed and designed by the Advanced Concepts for Moon Exploitation (ACME) team: a combination of large-scale lunar surface and trans-lunar space architectures is proposed, to produce and assemble key spacecraft components directly in space, enabling currently unfeasible deep space missions and more efficient Earth servicing space systems building up. The key motivation being the energetic requirement to launch massive elements from the Moon to be strongly reduced with respect to launch them from Earth. The mission includes three main building blocks: the automated Moon surface infrastructure, the orbiting manned station, located in the Earth-Moon Lagrangian Point 2 (EML2) and the Earth segment. The first is composed by three further modules: (1) set of robots to collect regolith and feed the (2) In-Situ Resource Utilisation (ISRU) plants to extract the correct chemicals to either feed the (3) 3D printers to produce basic spacecraft structural components (trusses, plates) or to synthetize rocket propellants (H2, O2, metals). The orbiting manned station is conceived to receive the lunar surface products and technologically advanced hardware coming from Earth and assemble them into operational space vehicles aimed to perform different exploration mission scenarios. The EML2 station itself is designed to be modular, to launch from Earth small modules then enlarged and assembled in orbit, exploiting the in-situ produced structures as well. The paper reports the overall architecture design and operations strategy, pointing out the mandatory requirements; attention is then focused on the Moon surface modules definition and design; their feasibility is critically discussed according to the current Technology Readiness Level and the potential development plan. The cost effectiveness of the proposed scenario is highlighted, supported by the performed economic analysis to assess the validity of the proposed concept