Rocket bodies are some of the most suitable targets for future robotic active debris removal missions and this paper presents a concept mission for use of a robotic arm on a spacecraft, to insert a de-orbiting kit in to the nozzle of the main engine of the debris (rocket body), and have it re-enter the atmosphere in a controlled method. This paper is important for the team project because it presents one of the techniques of ADR that could be implemented in the final mission design.
Cerf, M., 2015. Multiple Space Debris Collecting Mission: Optimal Mission Planning. Journal of Optimization Theory and Applications, [e-journal] 167(1), pp.195-218. https://doi.org/10.1007/s10957-015-0705-0 (Reviewed by Sweet Annie Grace)
Successive missions must be planned to clean the near-Earth space from the heaviest debris. The cost of each mission is high and hence, meticulous mission planning is a must. This paper discusses on the optimized mission planning methods. Concepts of orbital transfer, simulated annealing algorithm and transfer manoeuvres are discussed for achieving optimized mission planning.
Kaplan, M. H., 2009. Survey of space reduction methods. In: American Institute of Aeronautics and Astronautics, AIAA Space 2009 Conference & Exposition. Pasadena, CA (U.S), 14-17 Sep 2009. Laurel, M.A (U.S): Johns Hopkins University Applied Physics Laboratory. (Reviewed by Fredrik Samdal Solberg)
The paper investigates debris removal methods and conducts a comprehensive survey of potential technological approaches and operational concepts for dealing with the reduction of existing and future discarded orbiting objects. The author suggests how we can raise awareness for addressing the space debris removal challenge by other than the usual large government programs approach, and rather use incentives as awards for achievement or the potential of making a profit as motivators.
Palla, C., Kingston and J., Hobbs, S., 2017. Development of commercial drag-augmentation systems for small satellites. In: ESA Space Debris Office, 7th European Conference on Space Debris. ESOC Darmstadt, Germany, 18-21 Apr 2017. Cranfield University: Space Research Group. (Reviewed by Alexander Owens)
As part of ESA’s Clean Space initiative, Cranfield University (U.K) is developing a range of drag augmentation system (DAS) modules for space debris mitigation. The main two mature design are Kapton de-orbit sails for spacecraft under 1000kg and lower than 800 km altitude. The Icarus design has flight heritage (TRL 9) and the 2nd design (De-orbit mechanism) has TRL 8. The sails deploy at end-of-life to increase atmospheric drag and de-orbit the satellite. This article is important to the team project because it presents an option for debris mitigation, giving a solution for spacecraft at the end-of-life.
Peters, S., Förstner, R., Fiedler, H., 2015. Mission architecture for active space debris removal using the example of SL-8 rocket bodies. In: Sgobba T., Rongier I., eds. Space Safety is No Accident. Cham: Springer. pp.23-28. (Reviewed by Sweet Annie Grace)
Space debris has become a serious threat to satellites.The debris removal missions call for meticulous mission planning to achieve the task. This paper discusses on active debris removal of five SL-8 R/Bs from a circular orbit at approximately 980 km altitude and 830 inclination. The mission architecture for accomplishing this including target capturing is discussed in this paper. Preliminary budget estimation of the Δv(change in velocity), parametric mass estimation for the chaser and deorbit kits are also outlined.
Fang, Y., 2018. Influence rules of ground-based laser active removing centimeter-sized
orbital debris in LEO. International Journal for Light and Electron Optics, [e-journal] 170, pp.210-219. https://doi.org/10.1016/j.ijleo.2018.05.126 (Reviewed by Alexander Owens)
Centimeter sized orbital debris is thought to be difficult to clean up with active systems. This research investigates the use of a ground based laser to actively decrease the perigee of LEO objects so that the debris burns up in the atmosphere. The research is purely based on numerical simulations and experiments to evaluate the feasibility of this method. This paper is important to the team project because it presents a solution for ADR in LEO. This is one aspect of the solution that will be proposed in the final report.
DeLuca, L. T., Maggi, F., Bernelli, F. and Branz, F., 2013. Active space debris removal by a hybrid propulsion module. Acta Astronautica, [e-journal] 91, pp.20-33. https://doi.org/10.1016/j.actaastro.2013.04.025 (Reviewed by Alexander Owens)
Active yearly removal of approximately 0.1% of debris with mass over 500 kg, would be sufficient to stabilize catalogued debris in LEO (according to NASA). This research is a feasibility study of removing large debris using a hybrid propulsion module. This is completed using in-orbit rendezvous by use of a robotic arm on a servicing platform, to perform a controlled disposal of the debris. This article is important for the team project because of the mention of a servicing spacecraft which is part of the mission design considerations.
Andrenucci, M., Pergola, P. and Ruggiero, A., 2011. Active Removal of Space Debris Expanding foam application for active debris removal. [pdf], Pisa: European Space Agency ACT. Available at: <https://www.esa.int/gsp/ACT/doc/ARI/ARI%20Study%20Report/ACT-RPT-MAD-ARI-10-6411-Pisa-Active_Removal_of_Space_Debris-Foam.pdf> [Accessed July 2018]. (Reviewed by Sweet Annie Grace)
This paper discusses on one of the Active Space Debris Removal System which is based on an foam expansion system. This is achieved by increasing the drag of debris and thereby removing it. This paper helps in understanding the concept and planning of drag based debris mission.
Ruggiero, A., Pergola, P. and Andrenucci, M., 2015. Small electric propulsion platform for active space debris removal. IEEE Transactions on Plasma Science, [e-journal] 43(12), pp.4200-4209. https://doi.org/10.1109/TPS.2015.2491649. (Reviewed by Wang Guojun)
Electric propulsion (EP) has the advantage of propulsion in the ADR mission scenario. The low-power and low-cost EP system proposed in this paper has reference significance for the thrust design of the debris recovery mission.
Castronuovo, M., 2011. Active space debris removal—A preliminary mission analysis and design. Acta Astronautica, [e-journal] 69(9-10), pp.848-859. https://doi.org/10.1016/j.actaastro.2011.04.017 (Reviewed by Wang Guojun)
The derailer is connected to the larger space debris by means of a second robotic arm, which activates the device to disengage the debris. This is an effective way to understand large debris in space.
Le May, S., Gehly, S., Carter, B. and Flegel, S., 2018. Space debris collision probability analysis for proposed global broadband constellations, Acta Astronautica, [e-journal] 151, pp. 445-455. https://doi.org/10.1016/j.actaastro.2018.06.036. (Reviewed by Wang Guojun)
This paper evaluates the probability of collision of a giant constellation running in the current LEO debris environment in the current situation. The ability to generate new fragments in LEO is assessed by the debris evolution model test. Provides a basis for designing the ability to remove debris.
Lewis, H.G., Swinerd, G. G., Newland, R. J. and Saunders, A., 2010. A new analysis of debris mitigation and removal using networks. Acta Astronautica, [e-journal] 66(1-2), pp.257-268. https://doi.org/10.1016/j.actaastro.2009.05.010 (Reviewed by Alexander Owens)
This study details a Monte Carlo approach using networks to link space objects and collisions, for a statistical analysis. It incorporates impact of mitigation and active removal of debris which is mapped on to the network, to observe the knock-on effect. A debris model projected by the University of Southampton is used in conjunction with the statistical network, to identify the potential value of this approach. This article has major relevance to the team project as it predicts the effects of additional spacecraft and debris mitigation in the future.
Stolfi, A., Gasbarri, P. and Sabatini, M., 2018. A parametric analysis of a controlled deployable space manipulator for capturing a non-cooperative flexible satellite. Acta Astronautica,[e-journal] 148, pp.317-326. https://doi.org/10.1016/j.actaastro.2018.04.028 (Reviewed by Alexander Owens)
This research analyses the issue of stability whilst making first contact between a robotic arm for active debris removal and a non-cooperative target. Impedance control, non-modeled dynamics, control determination and structural flexibility are also considered. These factors will be important to consider when focusing on an ADR mission, with use of a robotic arm, to make sure there is good contact with the debris. This article is important to the team project because it analyses the effects of using robotic arm for ADR.
Lioua, J.C., Johnson, N. L. and Hill, N.N., 2010. Controlling the growth of future LEO debris populations with active debris removal, Acta Astronautica, 66, pp.648–653. https://doi.org/10.1016/j.actaastro.2009.08.005 (Reviewed by Takuya Adachi)
In order to investigate the influence of active debris removal (ADR), they simulated more realistic situation in the low Earth orbit (LEO) by using the ADR model developed by the NASA Orbital Debris Office. Based on the calculation results, they concluded that they can propose an effective removal strategy by selecting proper object to remove and we have to remove five debris per a year to keep the LEO environment. This paper is useful to consider the mission scenario.
Lioua, J.C., 2011. An active debris removal parametric study for LEO environment remediation, Advances in Space Research, 47, pp.1865–1876. https://doi.org/10.1016/j.asr.2011.02.003 (Reviewed by Takuya Adachi)
Using LEGEND, which is the long-term orbital debris evolutionary model developed by NASA, parametric study of an active debris removal was conducted to understand parameters that have large influence on the orbital