Active space debris removal by hybrid engine module (Articolo in rivista)

Type
Label
  • Active space debris removal by hybrid engine module (Articolo in rivista) (literal)
Anno
  • 2013-01-01T00:00:00+01:00 (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#doi
  • 10.1016/j.actaastro.2013.04.025 (literal)
Alternative label
  • De Luca L., Bernelli F., Maggi F., Tadini P., Pardini C., Anselmo L., Grassi M., Pavarin D., Francesconi A., Branz F., Chiesa S., Viola N., Bonnal C., Trushlyakov V., Belokonov I. (2013)
    Active space debris removal by hybrid engine module
    in Acta astronautica
    (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#autori
  • De Luca L., Bernelli F., Maggi F., Tadini P., Pardini C., Anselmo L., Grassi M., Pavarin D., Francesconi A., Branz F., Chiesa S., Viola N., Bonnal C., Trushlyakov V., Belokonov I. (literal)
Pagina inizio
  • 20 (literal)
Pagina fine
  • 33 (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#url
  • http://www.sciencedirect.com/science/article/pii/S0094576513001483 (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#numeroVolume
  • 91 (literal)
Rivista
Note
  • ISI Web of Science (WOS) (literal)
  • Scopu (literal)
  • PuMa (literal)
Http://www.cnr.it/ontology/cnr/pubblicazioni.owl#affiliazioni
  • Politecnico di Milano, Milano, Italy; Politecnico di Milano, Milano, Italy; Politecnico di Milano, Milano, Italy; Politecnico di Milano, Milano, Italy; CNR-ISTI, Pisa, Italy; CNR-ISTI, Pisa, Italy; Università di Napoli \"Federico II\", Italy; CISAS, - Università di Padova, Italy; CISAS, - Università di Padova, Italy;CISAS, - Università di Padova, Italy; CISAS, - Università di Padova, Italy; Politecnico di Torino, Italy; Politecnico di Torino, Italy; Centre National d'Études Spatiales (CNES), Paris, France; Omsk State Technical University, Omsk, Russia; Samara State Aerospace University, Samara, Russia (literal)
Titolo
  • Active space debris removal by hybrid engine module (literal)
Abstract
  • During the last 40 years, the mass of the arti cial objects in orbit increased quite steadily at the rate of about 145 metric tons annually, leading to a total tally of approximately 7,000 metric tons. Now, most of the cross-sectional area and mass (97% in LEO) is concentrated in about 4,600 intact objects, i.e. abandoned spacecraft and rocket bodies, plus a further 1,000 operational spacecraft. Simulations and parametric analyses have shown that the most ecient and e ective way to prevent the outbreak of a long-term exponential growth of the catalogued debris population would be to remove enough cross- sectional area and mass from densely populated orbits. In practice, according to the most recent NASA results, the active yearly removal of approximately 0.1% of the abandoned intact objects would be sucient to stabilize the catalogued debris in low Earth orbit, together with the worldwide adoption of mitigation measures. The candidate targets for removal would have typical masses between 500 and 1,000 kg, in the case of spacecraft, and of more than 1,000 kg, in the case of rocket upper stages. Current data suggest that optimal active debris removal missions should be carried out in a few critical altitude- inclination bands. This paper deals with the feasibility study of a mission in which the debris is removed by using a hybrid propulsion module as propulsion unit. Speci cally, the engine is transferred from a servicing platform to the debris target by a robotic arm so to perform a controlled disposal. Hybrid rocket technology for de-orbiting applications is considered a valuable option due to high speci c impulse, intrinsic safety, thrust throttle ability, low environmental impact and reduced operating costs. Typically, in hybrid rockets a gaseous or liquid oxidizer is injected into the combustion chamber along the axial direction to burn a solid fuel. However, the use of tangential injection on a solid grain Pancake Geometry allows for more compact design of the propulsion unit. Only explorative tests were performed in the past on this rocket con guration, which appears to be suitable as de-orbiting system of new satellites as well as for direct application on large debris in the framework of a mission for debris removal. The paper describes some critical aspects of the mission with particular concern to the target selection, the hybrid propulsion module, the operations as well as the systems needed to rendezvous and dock with the target, and the disposal strategy. (literal)
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