Challenges and options for an affordable small Lunar Sample Return Mission
- Paper number
IAC-06-A5.2.08
- Author
Dr. Adam M. Baker, Surrey Satellite Technology Ltd., United Kingdom
- Coauthor
Dr. Alex Ellery, Surrey Space Centre, University of Surrey, United Kingdom
- Coauthor
Mr. Andy Phipps, Surrey Satellite Technology Ltd., United Kingdom
- Coauthor
Dr. Yang Gao, University of Surrey, United Kingdom
- Coauthor
Prof. Martin Sweeting, Surrey Satellite Technology Ltd., United Kingdom
- Year
2006
- Abstract
SSTL has been studying the application of its highly successful Low Earth Orbit micro- and mini-satellites for lunar and planetary missions since 1996, through in-house funded design exercises and supported by ESA through Lunar and inner planet mission studies. Technical feasibility of a 400kg wet mass minisatellite designed to support a 10-50kg payload in lunar orbit for 6-24 months, with a target cost of Euro25M including platform, operations, launch and minimal new technology has been demonstrated [1]. SSTL has since been developing a range of improved subsystems and more advanced platforms, many of which have gained heritage in-orbit. These include the high power (deployable array) GMP-MiniSat platform, solar thermal and low cost bipropellant propulsion systems and high resolution wide field-of-view multispectral cameras. Low cost launch options have been identified, ranging from a Proton auxiliary payload launch direct to geostationary orbit, a Dnepr low cost launcher with Yuzhnoye upper stage for direct lunar transfer, and as a secondary payload alongside NASA’s 2008 Lunar Reconnaissance Orbiter.
While SSTL is focused on low cost lunar orbiter development, it is jointly considering affordable means of conducting lunar landing, and ultimately sample return with the University of Surrey Space Centre’s. These would demonstrate the applicability of low cost small spacecraft technology to reduce the risk of high profile barely affordable missions (such as ESA’s ExoMars and also Mars Sample Return) by demonstrating key technologies while offering secondary science, and an increased frequency of missions to maintain enthusiastic public and political support. A parametric study for a lunar sample return mission from the south polar Aitken basin has been conducted by the Surrey Space Centre with support from SSTL and was presented to the UK Royal Astronomical Society in 2005 [2]. The baseline which will be presented places a 15kg micro-rover on the lunar surface to drill an ice core from up to 1m depth during a maximum surface stay of 150hours, subsequently returning a 0.2kg sample to Earth. Total launch mass from Earth orbit of less than 500kg is feasible in principle, using a mixture of chemical and electric propulsion. This is a substantial launch mass reduction on previous lunar sample return mission proposals such as Moonrise and Hopper (around 2000kg). Ascent vehicle rendezvous in Earth orbit and a separately launched Earth Entry Vehicle complete the mission. This paper will discuss extending the SSTL orbiter concept which is known to be feasible for low cost, with additional robotic sample return technology. The objective will be to show that complex planetary surface missions such as Mars Sample Return can be affordable, and COTS technology can greatly assist in risk and cost reduction.
References [1] Phipps A; Low Cost Lunar Orbiter System Design; 24th IEEE Aerospace Conference, Big Sky, Montana, USA. March 8-15 2003. [2] Ellery A; Feasibility of Low-Cost Lunar Sample Return Micro-Mission; Royal Astronomical Society ‘Exploring the Moon in the 21st Century’; November 11 2005.
- Abstract document
- Manuscript document
IAC-06-A5.2.08.pdf (🔒 authorized access only).
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