Mathematics – Logic
Scientific paper
Sep 2008
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2008epsc.conf..526g&link_type=abstract
European Planetary Science Congress 2008, Proceedings of the conference held 21-25 September, 2008 in Münster, Germany. Online a
Mathematics
Logic
Scientific paper
Whilst the concept of high speed impacting penetrator probes is not new, recent highly successful ground test results have considerably improved the perception that these can be a viable and useful addition to the current toolbox of planetary probes. Previous developments only led to a single deployment (Deep Space-2 to Mars on the ill fated NASA Mars Polar Lander mission in 1999) where neither the soft lander nor penetrator was ever heard from, which is not a logical basis for dismissing penetrator technology. Other space penetrator programmes have included the Russian Mars'96 ~80m/s penetrators for which the whole mission was lost before the spacecraft left Earth orbit, and the Japanese Lunar-A program which was cancelled after a lengthy development program which however saw multiple successful ground trials. The Japanese penetrators were designed for ~300m/s impact. The current UK penetrator developments are actively working towards full space qualification for a Lunar penetrators (MoonLITE mission), which would also provide a significant technical demonstration towards the development of smaller, shorter lived penetrators for exploring other solar system objects. We are advocating delivered micro-penetrators in the mass range ~4-10Kg, (preceded by ~13Kg Lunar penetrator MoonLITE development program), impacting at around 100-500m/s and carrying a scientific payload of around 2Kg. Additional mass is required to deliver the probes from `orbit' to surface which is dependent upon the particular planetary body in question. The mass per descent module therefore involves and additional element which, for a descent through an atmosphere could be quite modest, while for a flyby deployment, can be substantial. For Europa we estimate a descent module mass of ~13 Kg, while for Enceladus the value is ~40Kg for Enceladus since a deceleration of ~3.8 kms-1 is needed from a Titan orbit. The delivery system could consist of a rocket deceleration motor and attitude control system, to e.g. simple fins for bodies with atmospheres Whilst a 2Kg payload may be considered to be very low mass we propose that it is sufficient to carry out a comprehensive range of scientific investigations of the highest priority, and can include a chemistry package (e.g. mass spectrometer with drill, doped optical fibres), micro-seismometers and accelerometers, together with a package of environment sensors capable of measuring temperature, heat flow, dielectric constant, radiation levels, magnetic fields, and a descent camera. Other very low mass options also include a subsurface mineralogy/astrobiology camera; simple redox and pH instruments; and a beeping transmitter to allow radio interferometery from Earth to detect surface motions whether seismic or tidally induced. At present most of these payload instruments either have good space heritage but no impact qualification; are very simple; or have been fully space qualified with the previous space hardware developments. The UK penetrator consortium is currently actively pursuing a program to provide full space qualification for most of the above instruments, of which sensor elements of the mass spectrometer, prototype drill component, micro-seismometers, magnetometer, radiation sensors have currently survived the recent (May 2008) impact test at 310ms-1with a worst case 8- 10 degrees attack angle (offset between velocity vector and normal incidence angle) where forces in excess of 10Kgee were experienced. Such a payload is capable of significant sub-surface chemical inventory identification including refactory, organic materials; seismic investigations of the interior of active bodies; sub-surface mechanical information including layering from accelerometers and mineralogy/astrobiology camera, and ground truth from orbiting experiments such as dielectric constant which is particularly relevant to orbiting ground penetrating radar measurements. A descent camera can provide both impact site geophysical context as well as public media images. These penetrators are ideal for vangard investigations of planetary bodies, or exploration of multiple sites where low mass is of particular benefit. They can provide a substantial scientific standalone capability; ground truth to orbiting instrument; provide concurrent missions with key data at other geographical locations; and provide broad scientific information to guide follow-on missions to more highly focused science investigations with more capable soft landed scientific instruments. Solar system bodies which are applicable to penetrator investigations are numerous and include the Moon, and the current ESA Cosmic Vision proposed missions to Europa, Titan and Enceladus. Other bodies would also include Near Earth Objects (NEOs) for which accelerometers in particular could be EPSC Abstracts, Vol. 3, EPSC2008-A-00526, 2008 European Planetary Science Congress, Author(s) 2008 instrumental in determining whether such objects are solid rock or loose rubble piles as currently thought. Though Mars already has a fairly mature and heavy investigative program both current and planned, the ability to implant a planet wide seismic network would be advantageous as well as extending astrobiologic investigations to new sites. The MoonLITE mission is a proposed UK led lunar mission which is planned to complete a phase-A study in the spring of 2009 with a possible launch in 2013. MoonLITE would comprise of 4 13 kg penetrators distributed widely upon the Moon including shaded polar craters and the far side. An orbiter would relay signals between penetrator and Earth. Key additional steps to enable exploration of other solar system bodies includes impact into harder (icy) and rough surfaces; increased radiation environments; and communications where a trailing aerial to mitigate signal attenuation through more heavily attenuating materials may be more prevalent. Also, significant is the desire to reduce the probe mass, which is envisaged to arise from a reduced lifetime of hours to weeks compared with ~1 year on the Moon, and by adopting new materials and technologies. Delivery of the probes is also likely to differ for each world, whether airless or with atmosphere, and the technology to deliver smaller probes, and with widely varying delta-V requirements requiring shorter and longer flight times. Surprisingly, operation in very cold environments is shared with the Moon's permanently shadowed craters.
Gowen Robert Anthony
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