The Beagle 2 environmental sensors: intended measurements and scientific goals Conference or Workshop Item How to cite: Towner, M. C.; Ringrose, T. J.im; Patel, M. R.; Pullan, D.; Sims, M. R.; Haapanala, S.; Harri, A.-M.; Polkko, J.; Wilson, C. F. and Zarnecki, J. C. (2003). The Beagle 2 environmental sensors: intended measurements and scientific goals. In: Sixth International Conference on Mars, 20-25 Jul 2003.

With no contact following landing on Christmas Day 2003, the Beagle 2 mission was declared lost early 2004. A glinting object seen in Mars Reconnaissance Orbiter HiRISE camera images has been identified as the Beagle 2 late 2014. This paper presents the evidence that the objects seen are indeed Beagle 2 through a series of evaluations of the objects identified on the surface. How the hardware may appear on the surface is presented. Size, reflectivities, location and dispersion on the surface are compared with expectations and the natural terrain. A virtual modelling technique has been developed to simulate the HiRISE images to enable determination of the state of deployment of the Lander. Based upon the outcomes from these analyses, an impressive list of mission successes has been compiled together with the potential causes for the loss of the mission. Although not possible to identify the cause for the loss of mission, these assessments provide strong evidence for Beagle 2 having reached the surface of Mars, releasing the Lander and deploying three of its solar panels and possibly all four. Beagle 2 is the UK's and Europe's first mission to land onto the surface of another body in our Solar System.

The 2003 Beagle 2 Mars lander has been identified in Isidis Planitia at 90.43° E, 11.53° N, close to the predicted target of 90.50° E, 11.53° N. Beagle 2 was an exobiology lander designed to look for isotopic and compositional signs of life on Mars, as part of the European Space Agency Mars Express (MEX) mission. The 2004 recalculation of the original landing ellipse from a 3-sigma major axis from 174 km to 57 km, and the acquisition of Mars Reconnaissance Orbiter High Resolution Imaging Science Experiment (HiRISE) imagery at 30 cm per pixel across the target region, led to the initial identification of the lander in 2014. Following this, more HiRISE images, giving a total of 15, including red and blue-green colours, were obtained over the area of interest and searched, which allowed sub-pixel imaging using super high-resolution techniques. The size (approx. 1.5 m), distinctive multilobed shape, high reflectivity relative to the local terrain, specular reflections, and location close to the centre of the planned landing ellipse led to the identification of the Beagle 2 lander. The shape of the imaged lander, although to some extent masked by the specular reflections in the various images, is consistent with deployment of the lander lid and then some or all solar panels. Failure to fully deploy the panels-which may have been caused by damage during landing-would have prohibited communication between the lander and MEX and commencement of science operations. This implies that the main part of the entry, descent and landing sequence, the ejection from MEX, atmospheric entry and parachute deployment, and landing worked as planned with perhaps only the final full panel deployment failing.

The 2003 Beagle 2 Mars lander has been identified in Isidis Planitia at 90.43°E, 11.53°N, close to the predicted target of 90.50° E, 11.53° N. Beagle 2 was an exobiology lander designed to look for isotopic and compositional signs of life on Mars, as part of the ESA Mars Express (MEX) mission. The 2004 recalculation of the original landing ellipse from a 3-sigma major axis of 174–57 km, and the acquisition of Mars Reconnaissance Orbiter High Resolution Imaging Science Experiment (HiRISE) imagery at 30 cm per pixel across the target region, led to the initial identification of the lander in 2014. Following this, more HiRISE images, giving a total of 15, including IR, red and blue-green colours, were obtained over the area of interest and searched, which allowed the calculation of red : blue-green ratios and sub-pixel imaging using super-high-resolution techniques. The size (approx. 1.5 m), distinctive multilobed shape, red : blue-green average ratio of 1.0 distinct from the local Martian rocks, dust and soil (typically red : blue-green ratio of 2.1), and location close to the centre of the planned landing ellipse led to the identification of Beagle 2. The shape of the imaged lander, although to some extent masked by the specular reflections in the various images, is consistent with deployment of the lander lid and then some or all solar panels. Failure to fully deploy the panels—which may have been caused by damage during landing—would have prohibited communication between the lander and MEX and commencement of science operations. This implies that the main part of the entry, descent and landing sequence, the ejection from MEX, atmospheric entry and parachute deployment, and landing worked as planned with perhaps only the final full panel deployment failing.

The 2003 Beagle 2 Mars lander has been identified in Isidis Planitia at 90.43°E, 11.53°N, close to the predicted target of 90.50° E, 11.53° N. Beagle 2 was an exobiology lander designed to look for isotopic and compositional signs of life on Mars, as part of the ESA Mars Express (MEX) mission. The 2004 recalculation of the original landing ellipse from a 3-sigma major axis of 174–57 km, and the acquisition of Mars Reconnaissance Orbiter High Resolution Imaging Science Experiment (HiRISE) imagery at 30 cm per pixel across the target region, led to the initial identification of the lander in 2014. Following this, more HiRISE images, giving a total of 15, including IR, red and blue-green colours, were obtained over the area of interest and searched, which allowed the calculation of red : blue-green ratios and sub-pixel imaging using super-high-resolution techniques. The size (approx. 1.5 m), distinctive multilobed shape, red : blue-green average ratio of 1.0 distinct from the local Martian rocks, dust and soil (typically red : blue-green ratio of 2.1), and location close to the centre of the planned landing ellipse led to the identification of Beagle 2. The shape of the imaged lander, although to some extent masked by the specular reflections in the various images, is consistent with deployment of the lander lid and then some or all solar panels. Failure to fully deploy the panels—which may have been caused by damage during landing—would have prohibited communication between the lander and MEX and commencement of science operations. This implies that the main part of the entry, descent and landing sequence, the ejection from MEX, atmospheric entry and parachute deployment, and landing worked as planned with perhaps only the final full panel deployment failing.

The Beagle 2 environmental sensors: intended measurements and scientific goals Conference or Workshop Item How to cite: Towner, M. C.; Ringrose, T. J.im; Patel, M. R.; Pullan, D.; Sims, M. R.; Haapanala, S.; Harri, A.-M.; Polkko, J.; Wilson, C. F. and Zarnecki, J. C. (2003). The Beagle 2 environmental sensors: intended measurements and scientific goals. In: Sixth International Conference on Mars, 20-25 Jul 2003.

The SAFER project (Sample Acquisition Field Experiment with a Rover), led by RAL Space and sponsored by the European Space Agency, was successfully concluded by a Mars Mission Simulation campaign in the Atacama Desert in October 2013. The objectives of SAFER were manifolds: Firstly, bring three ExoMars instruments prototypes together on a rover platform. Secondly, perform field trials in a Mars analogue in order to acquire valuable insight on the strategies for approaching a science target, investigating it, and sampling it to investigate possible traces of life. Lastly, the SAFER project targeted to implement a highly realistic scenario with a dual team, one with the rover system in a Mars analogue location, while all navigation and science investigation decisions would be taken remotely by a separate team, fully isolated from the field. The Atacama Desert in Chile was selected during the study as suitable Mars analogue for SAFER: Its extent, variety of landscapes, high quality Mars analogue and geological characteristics are all of high relevance for a Mars mission simulation. SAFER used an early version of ESA’s 2018 ExoMars rover, provided by Astrium, fitted with a trio of ExoMars prototype instruments, including the AUPE-2 PANCAM prototype from Aberystwyth University, the WISDOM ground penetrating radar prototype from LATMOS, and a CLUPI prototype provided by Space-X. All three instruments were used to identify promising sites for subsurface excavation. During the Mars mission simulation a field trials team composed of instruments engineers, geologists, and field trials engineers was on location in the Atacama Desert in Chile. The remote control team was in parallel overseeing the rover operations from the Satellite Applications Catapult facility in Harwell, UK. The remote control team was composed of instrument operators, key members of the ExoMars programme team, ExoMars instruments principal investigators and a geologist. The controllers used a video wall to combine data from the rover’s instruments with their own 3D planning maps to help the remote team to analyse instruments data, elaborate a science strategy, and produce plans of activities for each sol, as it would be performed during a Mars exploration mission. Each plan was dispatched to the local team in the field who then uploaded it to the rover, while trying to remain as ‘invisible’ as possible for the remote operators. The SAFER campaign was a success and its results are opening the way to successful, safe, and optimized planetary exploration for the European Space Agency: Firstly, remote operations with an average of two Martian sols per day were achieved, including the acquisition of valuable instruments data. Drilling down to more than a meter was achieved by manual operation, and the samples obtained are being documented to help cross calibrating the ground penetrating instrument data and support future Mars exploration missions. Secondly, SAFER unique outcomes and lessons learnt will be transmitted to the European Space Agency’s planetary exploration teams; a key outcome has been the importance of well-defined interfaces between the rover and instruments, the importance of the remote operations team composition, and valuable operations lessons learnt demonstrating feasible activities to be achieved in a single Martian sol. Valuable instruments operations feedback was also acquired and will be presented in the final paper. Finally, SAFER opens the way to efficient, easy, and cost effective future field trials activities; an extensive expertise in the organization of such trials has been developed, as well as a detailed knowledge of the Atacama region which has proven to be a highly representative analogue for Mars mission simulations.

In order to prepare the next in situ space missions we have created a collection of analogue rocks for calibrating and testing present and future space flight instruments. This collection is called the International Space Analogue Rockstore (ISAR) and is hosted at the CNRS and the Observatoire des Sciences de l’Univers en Region Centre (OSUC), in Orleans, France. In the context of the present MSL mission and to the future ExoMars-2018 mission, the first samples where chosen for their relevance to Mars. These samples are available for calibrating and testing space instrumentation and are now being used by several instruments on ExoMars and MSL. Use of the same suite of samples to calibrate all the instruments of a single mission will greatly increase their complementarity and thus to improve the interpretation of the analyses carried out in situ.

Emplacement of four or more kinetic penetrators geographically distributed over the lunar surface can enable a broad range of scientific exploration objectives of high priority and provide significant synergy with planned orbital missions. Whilst past landed missions achieved a great deal, they have not included a far-side lander, or investigation of the lunar interior apart from a very small area on the near side. Though the LCROSS mission detected water from a permanently shadowed polar crater, there remains in-situ confirmation, knowledge of concentration levels, and detailed identification of potential organic chemistry of astrobiology interest. The planned investigations will also address issues relating to the origin and evolution of the Earth–Moon system and other Solar System planetary bodies. Manned missions would be enhanced with use of water as a potential in-situ resource; knowledge of potential risks from damaging surface Moonquakes, and exploitation of lunar regolith for radiation shielding. LunarNet is an evolution of the 2007 LunarEX proposal to ESA (European Space Agency) which draws on recent significant advances in mission definition and feasibility. In particular, the successful Pendine full-scale impact trials have proved impact survivability for many of the key technology items, and a penetrator system study has greatly improved the definition of descent systems, detailed penetrator designs, and required resources. LunarNet is hereby proposed as an exciting stand-alone mission, though is also well suited in whole or in-part to contribute to the jigsaw of upcoming lunar missions, including that of a significant element to the ILN (International Lunar Network).

The FP7-SPACE Project PRoViScout (Planetary Robotics Vision Scout) aimed to demonstrate the feasibility of vision-based autonomous sample identification & selection coupled with vision-based navigation for a long range planetary scouting/exploration mission along with the necessary robotic elements. After 2 years of development and integration, the project held a field trial campaign in the caldera of Tenerife in September 2012. This paper gives an overview of the trials and summarises its major findings in terms of equipment, software integration, trial's logistics & strategy, and the main trial results.

We present the scientific case for inclusion of penetrators into the Europan surface, and the candidate instruments which could significantly enhance the scientific return of the joint ESA/NASA Europa-Jupiter System Mission (EJSM). Moreover, a surface element would provide an exciting and inspirational mission highlight which would encourage public and political support for the mission.Whilst many of the EJSM science goals can be achieved from the proposed orbital platform, only surface elements can provide key exploration capabilities including direct chemical sampling and associated astrobiological material detection, and sensitive habitability determination. A targeted landing site of upwelled material could provide access to potential biological material originating from deep beneath the ice.Penetrators can also enable more capable geophysical investigations of Europa (and Ganymede) interior body structures, mineralogy, mechanical, magnetic, electrical and thermal properties. They would provide ground truth, not just for the orbital observations of Europa, but could also improve confidence of interpretation of observations of the other Jovian moons. Additionally, penetrators on both Europa and Ganymede, would allow valuable comparison of these worlds, and gather significant information relevant to future landed missions. The advocated low mass penetrators also offer a comparatively low cost method of achieving these important science goals.A payload of two penetrators is proposed to provide redundancy, and improve scientific return, including enhanced networked seismometer performance and diversity of sampled regions.We also describe the associated candidate instruments, penetrator system architecture, and technical challenges for such penetrators, and include their current status and future development plans. (C) 2010 COSPAR. Published by Elsevier Ltd. All rights reserved.