Surrey Satellite Technology Ltd
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Concept Studies
Architecture Study on Deep Space Navigation and Communication
Subcontracted to Thales Alenia Space for a role in one of the ESA 'In-Space Architecture' studies, SSTL's role was to define in-space and surface navigation and communications data relay requirements as well as suggesting preliminary systems for addressing such requirements using small, low cost missions. Work has explored lunar and Mars architectures and options for small satellites supporting NEO.Low Cost Lunar Mission Feasibility Study
SSTL conducted an in-house funded lunar mission feasibility study in 2002 to assess the performance and cost of an 'entry level' mission. This work followed on from the ESA funded Phase A and Phase B study on LUNARSAT. The study concluded that the mission was technically feasible with a target cost of €25M including platform, operations, launch and minimal new technology. A 10-50 kg scientific payload could be supported in lunar orbit for 6-24 months.
Lunar Mission Options Study
UK Science and Technology Facilities Council (STFC) funded pre-phase A study on options for a low cost UK-led lunar mission. The study investigated various mission options, their feasibilities and identified a number of suitable mission concepts, as well as producing a preliminary cost estimate. Mission concepts generated included orbiter/penetrator (MoonLITE) and soft lander (MoonRaker). Subsequent work has assembled a UK industry team in preparation for a full Phase A study to commence in 2008 and produced inputs for a joint UK-NASA working group exploring collaborative lunar missions.
Venus Technology Reference Studies
Detailed system study into low cost methods of Venus exploration, funded by ESA Science Payloads and Advanced Concepts Office (value €350k, prime contractor). Mission consisted of a science orbiter, relay satellite and atmospheric entry probe delivering along lifetime aerobot for in-situ exploration of the Venus atmosphere.
Pre Phase A study to design technology demonstration missiion to simulate entry conditions for a sample return missionto Mars. The high delta-V carrier spacecraft had to accelerate the re-entry capsule to a relative velocity of 12.8 km/s for re-entry into the Earth's atmosphere.
