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dc.contributor.authorGessini, Paolo-
dc.contributor.authorSantilli, Giancarlo-
dc.contributor.authorSilva, William Reis-
dc.contributor.authorMartins, Antonino Salustiano Santos-
dc.contributor.authorMarques, Rodrigo I.-
dc.identifier.citationGESSINI, Paolo et al. Enabling low-cost challenging missions with small spacecraft by using high-energy pulsed plasma thrusters: preliminary propulsion system design. In: INTERNATIONAL ASTRONAUTICAL CONGRESS – The CyberSpace Edition, 71., 2020. Proceedings [...]. [S.I.]: IAF, 2020. Paper ID: 60762.pt_BR
dc.publisherInternational Astronautical Federation (IAF)pt_BR
dc.rightsAcesso Restritopt_BR
dc.titleEnabling low-cost challenging missions with small spacecraft by using high-energy pulsed plasma thrusters : preliminary propulsion system designpt_BR
dc.subject.keywordPropulsão elétricapt_BR
dc.subject.keywordPropulsão plasma pulsadopt_BR
dc.subject.keywordEngenharia aeroespacialpt_BR
dc.subject.keywordSatélites artificiaispt_BR
dc.description.abstract1Small spacecraft are inherently cheaper to build and launch, even if they may pose formidable design challenges, especially for high Delta-v orbit transfers, lunar and interplanetary missions. The development of a propulsion system that is, at the same time, simple, robust and scalable, is of paramount importance to enable this type of missions at the cost levels affordable to the players more frequently interested in them, like academic institutions and small companies, especially in developing countries. In the last decades, increasingly ambitious missions have been planned and executed using small spacecraft. Although different types of propulsion systems have been developed and implemented on CubeSats, NanoSats and MicroSats, these have provided, in general, low values of total impulse, thus precluding their application to high Delta-v missions. Particularly stringent mass, volume and power constraints make scaling down electric propulsion systems, beneficial in reducing total propellant mass due to their high specific impulse, far from trivial. Among the many types of electric thrusters developed, Pulsed Plasma Thrusters (PPTs) have been one of the most successfully employed on small spacecraft, due to their low overall system complexity, which makes them eminently scalable, reliable and robust. These characteristics are especially evident in solid-propellant (ablative) PPTs, with their lack of moving parts. High values of total impulse entail correspondingly high values of impulse bit, the impulse produced by each pulse, unless reliable capacitor operation for a very large number of cycles can be achieved. This, in turn, translates into a large value of discharge energy, roughly proportional to impulse bit. As specific impulse has been seen to increase with increasing values of discharge energy per unit area of ablated propellant, the benefit of operating PPTs at high energies is twofold. By developing capacitors with high energy densities and capable of operating for several millions of charge-discharge cycles, high values of both total impulse and specific impulse will be attained, with reasonable mass values of the capacitor bank and the propellant bar. The continuous increase in capacitor energy densities will soon reach values making PPT operation in these energy ranges possible. While such high-energy PPT propulsion systems need to be actually designed and tested, to ensure that there are no showstoppers, a preliminary system design is nevertheless interesting, to provide research directions. Low-thrust trajectory simulations are needed in order to optimize the design and are described in a companion paper, supporting the calculations performed here.pt_BR
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