Abstract:Saturn's moon Enceladus offers a unique opportunity in the search for life and habitable environments beyond Earth, a key theme of the National Research Council's 2013-2022 Decadal Survey. A plume of water vapor and ice spews from Enceladus's south polar region. Cassini data suggest that this plume, sourced by a liquid reservoir beneath the moon's icy crust, contain organics, salts, and water-rock interaction derivatives. Thus, the ingredients for life as we know itliquid water, chemistry, and energy sources-a… Show more
“…Flythroughs may be targeted at different altitudes, different times in the orbital period, or over different tiger stripes (e.g. MacKenzie et al 2016). The importance of the latter was recently further demonstrated by Hedman et al (2018) who used data from Cassini UVIS and VIMS to show that the dust/gas ratio varies between tiger stripes.…”
Section: Science Investigations From Icy Samplesmentioning
“…Flythroughs may be targeted at different altitudes, different times in the orbital period, or over different tiger stripes (e.g. MacKenzie et al 2016). The importance of the latter was recently further demonstrated by Hedman et al (2018) who used data from Cassini UVIS and VIMS to show that the dust/gas ratio varies between tiger stripes.…”
Section: Science Investigations From Icy Samplesmentioning
“…For SILENUS to follow planetary protection measures, the orbiter must be destroyed at the end of the mission to avoid any contact with Enceladus or other regions of interest. Drawing from the proposed mission "Testing the Habitability of Enceladus's Ocean" (THEO) [3], we proposed to crash the orbiter into Tethys, a nearby moon that has been previously determined to be inhospitable to life. It was this decision, combined with the self-imposed budgetary constraints set by team Voyager, which the judges deemed enough to grant our team the winning proposal.…”
The 2019 Caltech Space Challenge was a one-week intensive mission proposal challenge that brought an international group of 32 post-secondary students from various disciplines to design multi-lander mission concepts for Enceladus. The students were divided into two competing teams of 16, Team Voyager and Team Explorer. In this paper, Team Voyager describes their process and challenges in conceptualizing the winning mission proposal (SILENUS) of an orbiter and a network of landers. The final mission architecture proposes a mission where the science data return lasts just over one year and sends an orbiting satellite housing science instrumentation to Enceladus, dropping off four penetrating seismometers to the surface of the icy moon. In our paper, we provide an overview of our high-level mission design, an analysis of team structure and dynamics, the resources utilized by the teams to assist with mission conception, as well as the challenges and learning outcomes of the week as a framework for future rapid mission concept development.
“…As a consequence, they are the natural targets of several concept studies and proposals for dedicated missions to them, including also orbiters (Razzaghi et al 2008;Spencer & Niebur 2010;MacKenzie et al 2016;Verma & Margot 2018;Sherwood et al 2018). Since, at present, sending a spacecraft to Europa seems more likely than to Enceladus, as it can be learnt at https://europa.nasa.gov/about-clipper/overview/ and http://sci.esa.int/juice/ on the Internet, we investigated in a little more detail this potentially appealing Jovian scenario, even if it is not said that the actually approved missions will finally involve the use of an orbiter.…”
Section: Some Potentially Interesting Astronomical Scenariosmentioning
We study a general relativistic gravitomagnetic 3-body effect induced by the spin angular momentum S X of a rotating mass M X orbited at distance r X by a local gravitationally bound restricted two-body system S of size r ≪ r X consisting of a test particle revolving around a massive body M. At the lowest post-Newtonian order, we analytically work out the doubly averaged rates of change of the Keplerian orbital elements of the test particle by finding non-vanishing long-term effects for the inclination I, the node Ω and the pericenter ω. Such theoretical results are confirmed by a numerical integration of the equations of motion for a fictitious 3-body system. We numerically calculate the magnitudes of the post-Newtonian gravitomagnetic 3-body precessions for some astronomical scenarios in our solar system. For putative man-made orbiters of the natural moons Enceladus and Europa in the external fields of Saturn and Jupiter, the relativistic precessions due to the angular momenta of the gaseous giant planets can be as large as ≃ 10 − 50 milliarcseconds per year mas yr −1 . A preliminary numerical simulation shows that, for certain orbital configurations of a hypothetical Europa orbiter, its range-rate signal ∆ρ can become larger than the current Doppler accuracy of the existing spacecraft Juno at Jupiter, i.e. σρ = 0.015 mm s −1 , after 1 d. The effects induced by the Sun's angular momentum on artificial probes of Mercury and the Earth are at the level of ≃ 1 − 0.1 microarcseconds per year µas yr −1 .
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