Slated for 2031, the NovaMoon lunar in-orbit demonstrator and reference station will provide a lunar-based local differential, geodetic and timing station to enhance the accuracy of lunar PNT services to sub-meter levels across the South Pole.
AVIER VENTURA-TRAVESET, EUROPEAN SPACE AGENCY (ESA), RICHARD D. SWINDEN, FLOOR T. MELMAN, DIMITRIOS V. PSYCHAS, YOANN AUDET, ESA’S EUROPEAN SPACE RESEARCH AND TECHNOLOGY CENTRE (ESTEC)
The renewed interest in space exploration, particularly around the Moon, has prompted significant efforts by space agencies to develop lunar communications and navigation services. In fact, Moon exploration is emerging as the next global strategic priority in space exploration with highly ambitious government and commercial missions over the coming decades for a permanent return of mankind to the Moon.
Europe is actively taking part in this new era of lunar exploration with a tangible contribution to several major projects such as the European Service Module (ESM) [1] for NASA’s Orion spacecraft that will send astronauts to the Moon and beyond; the Esprit and I-Hab modules to the Gateway [2] [3], a staging post for missions to the Moon and Mars; the Argonaut large logistic landers [4] supporting sustainable human expeditions to the Moon and high-level science; Lunar Pathfinder initial communication service [5]; and the Moonlight program [6], providing commercial lunar communication and navigation services. Moonlight is designed to be scalable and interoperable. For this purpose, ESA is collaborating closely with NASA and JAXA on LunaNet [7], a new framework for lunar communication and navigation standards, paving the way for multiple LunaNet Service Providers (LNSPs) to contribute to a broad, interoperable lunar global communication and navigation architecture. The navigation aspect of this is named the Lunar Augmented Navigation Service (LANS) and is depicted in Figure 1.
The European contribution to the LunaNet LANS, via Moonlight, comprises four navigation satellites orbiting the Moon in Elliptical Lunar Frozen Orbits (ELFO) with an orbital period of 24 hours. The Moonlight position, velocity and time (PVT) service is targeting a Height-constrained Horizontal Dilution of Precision (HHDOP, being the HDOP computed assuming the height information is provided by external sensors or information, e.g. digital elevation models) of less than 3.5 for at least 15 hours per Earth day across the South Pole region of the Moon (-70 to -900 latitude). The Moonlight navigation satellites are transmitting single-frequency S-band signals called Augmented Forward Signal (AFS) in accordance with LunaNet standards [7] and with a Signal-in-Space Error (SISE) of less than 10 m for at least 95% of the time. This Moonlight architecture aims to provide lunar users with positioning accuracies for surface rovers, landers and orbiters of 10 m, 50 m and 100 m, respectively.
As a future evolution of this lunar global communication and navigation architecture, the European Space Agency (ESA) is studying the possibility of placing a reference station on the Moon as part of ESA’s first Argonaut lander. The NovaMoon In-Orbit Demonstrator would provide a lunar-based local differential, geodetic, and timing station, significantly enhancing the accuracy of Moonlight’s lunar PNT services to reach sub-meter levels across the entire South Pole. This station also would be a valuable resource for lunar scientific experimentation. The NovaMoon payload would be developed and integrated as one of the key demonstration payloads for the first Argonaut mission (known as ArgoNET—Navigation, Energy and Telecom), as shown in Figure 2.
NovaMoon’s primary objective would be to enhance Moonlight’s navigation accuracy from approximately 10 m to the sub-meter level across the entire South Pole service area (the reference zone for the Artemis missions [8]) under both static and dynamic conditions. Because of the absence of an ionosphere and troposphere on the Moon and the high eccentricity of Moonlight’s Elliptical Lunar Frozen Orbits (ELFO) over the South Pole, the degradation of differential corrections in time and over distance is minimal. In these conditions, placing a single lunar differential station near the South Pole (e.g. the Argonaut-1 landing site) may provide exceptional performance to users across the entire range of South Pole latitudes, spanning from -70 to -900 latitude. At the user level, a standardized LunaNet LANS PNT receiver, without any additional communication link or hardware modifications, should be able to process these corrections, making this approach extremely user-friendly and fully compatible with international standards. This capability will, in turn, drive a range of advancements toward a more sustainable long-term lunar exploration strategy.
The NovaMoon payload would also include a set of geodetic instruments, along with on-board atomic clocks. Together, these instruments will help establish precise lunar reference frame and time standards. This setup will enable centimeter-level surveying accuracy on the lunar surface, allowing detailed measurements of the Moon’s tidal deformations and librations, and supporting a range of scientific research opportunities.
NovaMoon: Mission and Objectives
NovaMoon’s main objective is to provide a lunar-based local differential, geodetic and timing station to enhance Moonlight services and support scientific experimentation.
This general mission objectives can be split into five main areas:
1. Provision of local differential services to Moonlight and other lunar PNT systems: Acting as an accurately surveyed local reference station at the lunar South Pole, NovaMoon will augment the Moonlight system by generating and transmitting code (and carrier-phase) measurements and corrections for Moonlight and other LunaNet navigation satellites to lunar users (e.g., rovers, astronauts, landers) across the entire South Pole region. This will enable Moonlight differential code-only (DGNSS) and code-plus-phase (RTK) positioning across the whole South Pole.
2. Continuous monitoring of Moonlight and other lunar PNT systems. NovaMoon will provide continuous signal quality monitoring of Moonlight and other LunaNet navigation satellites using available raw measurements from a well surveyed and monitored standardized LunaNet receiver. Additionally, NovaMoon will regularly compute the station’s PVT using Moonlight services, assessing the associated errors impacting this signal and the resulting Moonlight service positioning accuracies. This independent monitoring function of NovaMoon will enhance the reliability of lunar navigation services provided to lunar users.
3. Highly accurate lunar geodetic reference station. NovaMoon will include four different co-located ranging techniques—a Very Long Baseline Interferometry (VLBI) transmitter, a laser retroreflector, NovaMoon-Moonlight positioning and direct-to-Earth ranging—along with communication access via Moonlight. This setup will enable the precise localization of the NovaMoon station with sub-decimeter accuracy. This capability will support improving lunar reference frame realizations and significantly enhance our understanding of the Moon’s composition and interior structure.
4. Lunar time-reference laboratory. NovaMoon will include a set of atomic clocks capable of providing a continuous lunar physical time reference supporting the realization of the LunaNet Reference Timescale.
5. Scientific support for lunar experimentation. To support the scientific community, NovaMoon will provide continuous access to individual lunar geodetic sensors and timing data for international research groups.
It is important to highlight the Argonaut-1 Mission is planned to be operational for 5 years, allowing a very detailed experimentation of the NovaMoon payload. Recurrent Argonaut missions are also planned, with a cadence of approximately every two years. This means the NovaMoon initial demonstrator on Argonaut-1 could trigger a recurrent/permanent NovaMoon service as part of future Argonaut missions.
NovaMoon Concept of Operations
To achieve the different NovaMoon mission objectives, there are various functions that need to be implemented and then exercised, as illustrated in Figure 3. The main ones can be described through the following scenarios:
Generation and Dissemination of Differential Corrections
The NovaMoon architecture is foreseen to include at least two LunaNet LANS receiver chains, compliant with the defined standards [7]. Two LANS receivers are required to first generate and then monitor and validate the correction data.
The first receiver acquires and tracks the AFS from each Moonlight (or LunaNet) navigation satellite and generates its own ranging measurements. Those measurements are used within the estimation process of the station reference position and used to generate the correction data to be disseminated to lunar users. Thanks to NovaMoon’s built-in capabilities, the differential corrections can be forwarded to lunar users in three different ways:
1. The LunaNet LANS AFS navigation message. This requires NovaMoon to send the corrections back to Earth (to the LNSP navigation ground segment) through the Direct-to-Earth (DTE) link or using the Moonlight communication service. The differential corrections can be subsequently incorporated into the AFS navigation message using MSG-G32 defined in the LunaNet Interoperability Specification [7] and broadcast to lunar users. The differential corrections can then be processed and used by a standard LunaNet LANS receiver.
2. The Moonlight communication service. The differential corrections also could be sent through the Moonlight communication service, providing them to any PNT users that also embark a Moonlight COM terminal. This approach enables large South Pole coverage with a lower aging of corrections due to higher data rates and the potential for lunar surface-to-surface relaying, avoiding the round-trip light time with Earth.
3. The local proximity network. The corrections also could be sent directly to the users in the vicinity of NovaMoon via local proximity networks using WiFi and 3GPP standards. This would enable the provision of correction data with a very low latency but only for users equipped with an additional proximity network terminal and who are within a limited range (up to a few kilometres) of NovaMoon.
From those three possible solutions, the integration of the differential corrections on the LANS AFS navigation message has high interest. While it may reach all users in the South Pole via the Moonlight navigation satellites and provides a very pragmatic solution to the user, the corrections may be processed by a standardized LunaNet LANS receiver without any additional communication link or specific hardware modification.
The second LANS receiver chain is used to acquire and then apply the generated corrections as an independent user at an a priori known static location, which enables consistency checks to be performed between the computed and reference information and thus validate the NovaMoon correction data.
Determination of the NovaMoon Precise Location
As with terrestrial GNSS reference stations, any error in the reference station location directly translates to an error at user level. Therefore, the precise estimation of NovaMoon’s reference position is essential. The set of collocated geodetic instruments embarked on NovaMoon can be used to achieve this, especially the combination of laser ranging (that provide Earth-Moon radial measurements) and VLBI (that provides angular measurements). This provides a powerful combination to determine NovaMoon location with very high accuracy. Both LANS one-way and DTE two-way measurements can also be used to complement these techniques by reducing biases and providing long term trends. It is expected that the accuracy of the NovaMoon station location can be refined with time in this way as more and more data is collected and with little temporal displacement due to the lack of tectonic plates on the Moon.
Monitoring LANS Satellites
As NovaMoon is envisaged to include LunaNet LANS receivers attached to very precise clocks, it can be used for in-situ monitoring of the Moonlight/LANS navigation satellites (similar to GNSS sensor stations). This capability will provide important information about the performance of the LNSP navigation services at the lunar surface that can then be provided back to the LNSPs for further processing.
NovaMoon Time Generation
NovaMoon is conceived to generate NovaMoon Time (NMT) that can represent a physical realization of the LunaNet Reference Timescale (LRT). After NMT has been initialized, the offset between NMT and LRT, LNSP system times and UTC (available through a time-transfer method with Earth such as two-way DTE) can be monitored continuously. Based on the measured offsets NMT can be synchronized to LRT or UTC or left free running. This measured data can also be sent back to Earth via the communication links for use by different entities.
Collecting and Distributing Scientific Data
The large amount of data generated by NovaMoon (e.g., laser ranging, VLBI, DTE, and LANS measurements, timing and clock data) can be used to address multiple scientific questions. Indeed, the collected data can be regularly transmitted to Earth via the Moonlight communication service or the NovaMoon Direct-to-Earth links and made readily available to the scientific community. ESA intends to coordinate specific measurement campaigns with the scientific community to support their particular needs and research.
NovaMoon System Architecture
Figure 4 provides a notional architecture of the NovaMoon payload embarked on the Argonaut platform. NovaMoon (together with the Telecom and the other payloads of ArgoNET) are interfaced to the Argonaut Lunar Descent Element (LDE) through the Argonaut Cargo Platform Element (CPE).
NovaMoon contains the following main physical blocks:
Timing unit [10 kg/55 W]: Composed of two or three atomic clocks (depending on the selected redundancy and ensemble concept). The output of each clock is input to a synchronization unit, which is responsible for the distribution of timing signals within NovaMoon.
NAV unit [4 kg/45 W]: Contains S-band antennas and two LANS receivers that will process the AFS signals transmitted by the LNSP navigation nodes (e.g. Moonlight satellites). Two receivers are needed to enable independent validation of the corrections. Moreover, one receiver will be used to monitor AFS signals (this receiver is connected to the synchronization unit). The NAV processor will generate the differential corrections and perform the signal monitoring functions. The NAV processor is the only unit that interfaces to the Argonaut CPE, the interface between NovaMoon and the Argonaut lander.
Geodetic suite: Comprises a laser retroreflector [5 kg/0 W] and VLBI transmitter, antenna and pointing mechanism that ensures the antenna can be orientated toward the average Earth direction upon landing. The VLBI transmission is expected to be activated on a campaign basis [9 kg/32 W (when activated)].
The Argonaut CPE contains the TT&C transponder and DTE antenna to provide the communication link between NovaMoon and Earth. This link sends the differential corrections to the Earth to be incorporated in the Moonlight AFS navigation message. Furthermore, the DTE link is used to obtain range, Doppler and carrier phase measurements that are used together with the NovaMoon laser ranging and VLBI measurements to determine the location of NovaMoon with sub-decimeter level accuracy and may be used for time transfer with Earth-based timescales.
The Telecom Payload may offer differential corrections through a local proximity communication network to users in the vicinity of NovaMoon. Furthermore, it may share a Moonlight COM terminal with NovaMoon that can be used to upload the differential corrections to the Moonlight satellites (i.e., as an alternative means to the DTE link).
The estimated total mass and nominal power of NovaMoon (including the COM terminal) are 28.6 kg and 101 W, respectively. Including options (Figure 4) and margins, the mass and power increases to about 48 kg and 160 W, respectively.
NovaMoon Performance Analysis: Enhancing PNT on the Moon
In this section, we provide insight into the performance of a surface rover circumnavigating the South Pole of the Moon, shown in Figure 5, based on our simulation environment. Our analysis is conducted on the basis of an example 4-satellite navigation constellation for Moonlight. Satellite position and clock offsets are derived from bihourly-refreshed navigation messages, the parameters of which are calculated in an orbit determination and time synchronization process (ODTS) based on our simulation framework. Further details on the Moonlight constellation assumed here, navigation signals, user receiver, and the ODTS process are reported in our earlier contributions [10].
Assuming NovaMoon corrections are generated and delivered in their observation-space representation, the rover can receive them to formulate a system of double-differenced (DD) linearized observation equations at an epoch t in the compact form E (yt)=At xt. The observation vector yt, containing the DD carrier-phase and code 1 Hz measurements, is linked to the unknown parameter vector xt, containing the rover’s position increment vector and the DD integer ambiguities, through the full-rank design matrix At, where E (.) is the expectation operator. The zenith-referenced standard deviations (STDs) of the undifferenced code and phase measurements (for both the rover and the reference station) are set to 30 cm and 3 mm, respectively, which are then weighted with an exponential elevation-dependent function. We also use less precise code measurements (STDs of 1 m) in our simulations to assess its impact on performance.
Note that because of cases with a limited number of visible satellites, a height-constrained version of the model was used by involving a weighted height-constraint as E (ht)=FTxt, where ht is the available height measurement (e.g. from a Digital Elevation Map–DEM) and FT links the latter with the rover’s positional component. In improving the rover’s solution over time, information about the temporal behavior of these parameters was incorporated to exploit the time-constant property of the carrier-phase ambiguities and to capture the rover’s motion. To mimic a real-time rover scenario, simulated measurements were generated for a rover with almost-constant velocity of low magnitude along the traverse and were then processed in a forward-only Kalman-filter to recursively estimate the rover’s unknown parameters. For a more detailed formulation of the measurement and dynamic models, as well as the configuration setup of the simulation, see [11].
Figure 6 illustrates the rover’s Kalman-filter-based horizontal positioning solutions over time, along with their 99% confidence intervals, in the presence of an auxiliary height-measurement with a precision of 5 m (left column) and 10 cm (right column). The results demonstrate that the rover can achieve positioning errors below the meter-level, even surpassing the 25 cm level, while one can also observe that a weak receiver-satellite geometry (higher PDOP) can spoil the achieved positioning precision. Note that the solutions experience some discontinuities that are owed to the navigation messages’ update rate and the periodic increase of the corrections’ latency involved (right column). To infer the overall performance of the Kalman-filtered rover solutions, we computed multiple realizations of the results for baseline lengths ranging from 10 to 500 km, producing the mean time-to-first-fix (TTFF) shown in Figure 7. As expected, the larger the baseline length, the longer the TTFF is in static mode, with the effect being more pronounced when less precise code data are used, and with negligible impact on the final achieved precision. When switching to dynamic mode, the role of the baseline length seems to be less critical because of the uncertainty introduced by the dynamic model. This is also the main reason the dynamic-mode TTFFs are, in general, larger than their static counterparts.
It is thus demonstrated that the positioning solutions in a differential setup can rapidly achieve sub-meter performance, while the TTFFs for surpassing the 25 cm level are dependent on both the baseline length and the quality of the code measurements. The simulation scenarios, where the NovaMoon corrections are provided to the rover every 600 seconds (right column of Figure 6), indicate the performance gets only slightly deteriorated, but this effect would be amplified in case of considerably larger latencies. Note that, despite the absence of a lunar ionosphere and the associated errors it would bring, our solutions have been computed based on single-frequency measurements obtained from a 4-satellite constellation, thus producing a weak user model that benefits over time from the time-constant behavior of phase ambiguities employed in our Kalman-filter setup. An increase in the number of satellites, which could be achieved by interoperability with other partners or Moonlight future evolutions, would further strengthen the user model and lead to improved performances.
NovaMoon Mission: Enabling New Lunar Exploration Opportunities
The availability of NovaMoon could lead to a significant advancement in lunar exploration. With a single NovaMoon station, lunar navigation to sub-meter accuracy can be achieved in real time across the entire South Pole lunar surface region. These enhanced accuracies could enable autonomous lunar surface robotics and human transportation; support operational logistics and smart infrastructure development; allow the generation of precise lunar maps; enhance construction and manufacturing capabilities; facilitate lunar mining; and support precise scientific sampling, among many other applications. This represents a true paradigm shift for lunar exploration.
All these benefits come at the minimal cost of incorporating a LANS receiver for those applications. A standardized LunaNet LANS receiver would be able to directly acquire these corrections from the broadcast navigation message. These receivers are expected to be miniaturized with very low Size Weight and Power (SWaP), facilitating their integration into multiple future lunar missions.
Beyond lunar surface users, NovaMoon could also greatly benefit lunar landers and low lunar orbit (LLO) users. For lunar landers, in addition to a major improvement on the actual landing accuracy, NovaMoon could potentially add an integrity layer by allowing real-time monitoring of the Moonlight/NovaMoon performance before and during landing operations, and be able to convey this information to the users in near real time via access to the Moonlight communication services. The orbital accuracy of LLO users also could be enhanced, potentially reducing their operational costs for these missions and decreasing uncertainties in their lunar positioning. Additional benefits for LLO users include significant mitigation of the existing lunar space traffic collision risk and reduction of alerts and unnecessary maneuvers, partly caused by the low accuracy knowledge of lunar orbiting vehicles [15], and providing a substantial enhancement of the scientific opportunities for dedicated low lunar observation satellites.
NovaMoon Mission: Enabling Lunar Science
The NovaMoon payload provides a fantastic opportunity to improve our knowledge of the Moon and contribute to various scientific domains ranging from lunar geodesy to fundamental physics.
Due to the collocation of multiple ranging techniques such as laser ranging, VLBI and DTE links, it will be possible to determine the station’s position on the lunar surface with centimeter-level accuracy. Leveraging these complementary techniques will eliminate systematic biases still present in current observations used to define lunar ephemerides, which still heavily rely on the mirrors from the Apollo missions. NovaMoon’s accurate surveying capabilities and advanced laser retroreflectors will be deployed at the lunar South Pole, where no such measurements are yet available. This will enhance the accuracy of lunar ephemerides and lunar motion data.
These continuous, high-accuracy observations will also refine our understanding of the Moon’s inner structure by improving models for its rotation, libration, and tidal deformation—key indicators of its composition. This will lead to a better understanding of the Moon’s interior. As our knowledge of the Moon improves, so too will the accuracy of lunar ephemerides, achieving centimeter-level precision.
Ultimately, these advancements will impact the definition of the lunar reference frame and the accuracy of its realization, a critical factor for navigation in lunar orbit and on the surface. This improvement will benefit all LANS constellations providing navigation services to lunar users.
The long-term availability of stable atomic clocks onboard NovaMoon will provide the NovaMoon Time reference, significantly supporting the definition and analysis of a lunar-based reference time by offering a physical realization of the LunaNet Reference Timescale (LRT), with the option to synchronize it to the UTC for experimentation.
NovaMoon reference data could also enhance the precise orbital positioning of scientific LLO satellites. Similar to how GNSS receivers support Earth observation satellite operations, this could significantly expand scientific opportunities for lunar observation satellites. For example, this could enable the generation of highly accurate lunar gravity field variation maps; improve the precision of lunar 3D digital elevation models; or allow the detailed assessment of the Moon’s small-scale features of scientific interest.
In a more long-term perspective, NovaMoon also can greatly contribute to other science domains such as cosmology or fundamental physics. By measuring the falling rate of the Earth toward the Moon with the very accurate lunar laser ranging (LLR) measurements NovaMoon will provide, Einstein’s fundamental equivalence principle could be tested. Regarding cosmology research, one of the possibilities for NovaMoon currently under investigation is using the laser ranging measurements to support detection of gravitational waves. For example, long-term observation of a well-surveyed laser retroreflector, ranged from a LLO satellite, could potentially allow monitoring of subtle modifications in these lunar orbits. These modifications could theoretically be linked to the effects of gravitational waves through a sophisticated model that disentangles the various orbital contributions.
Regarding fundamental physics theories, NovaMoon also facilitates numerous potential research to test quantum physics such as generating and distributing entangled particles—a unique effect central to most quantum technologies. For instance, a pair of entangled photons could be generated on Earth, with one photon monitored on Earth and the other sent to the Moon, housed within the NovaMoon payload and monitored there. Indeed, such theory has never been experimentally tested over distances as great as the Earth-Moon distance experiencing such a gravitational gradient over the distance.
Summary
We have provided a detailed overview of the ESA’s NovaMoon study, an advanced lunar PNT payload proposed for deployment on ESA’s first Argonaut lander mission in 2031. NovaMoon will serve as a local differential, geodetic and timing station, significantly enhancing the performance of Moonlight’s PNT services and ultimately achieving sub-meter positioning accuracy across the lunar South Pole. NovaMoon’s performance was evaluated for a lunar rover traversing the South Pole, applying Moonlight ranging signals and achieving Kalman-filtered positioning solutions in a differential setup. Simulation results demonstrated the rover maintained a positioning accuracy consistently below 1 meter, often surpassing the 25 cm level. The sensitivity of this performance to the baseline length, corrections transmission interval and the quality of the code measurements was also analyzed, showing a high robustness.
These enhancements in positioning performance will support safer human and robotic missions, enable high-resolution lunar mapping, and improve operational logistics. NovaMoon’s embarked geodetic instruments and lunar atomic clocks will support the establishment of consolidated lunar geodetic and time reference frames. Additionally, these instruments will unlock numerous scientific research opportunities on the Moon.
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Authors
Dr. Javier Ventura-Traveset has worked more than 35 years at the European Space Agency (ESA). He is the Moonlight Project Navigation Manager and Navigation Science Manager, managing all ESA lunar navigation-related activities, including the ESA Lunar Pathfinder, Moonlight and NovaMoon programs. He also coordinates all ESA GNSS scientific-related activities and serves as the Executive Secretary of the ESA GNSS Scientific Advisory Committee. He is an Academician at the Royal Academy of Engineering of Spain.
Richard Swinden is a Navigation System Engineer in the RF Systems Division at the ESA. His current responsibilities involve providing system and navigation engineering support to lunar and Mars-related projects including Moonlight, Argonaut and LightShip-MARCONI. He holds a first-class Master of Electronic Engineering degree from the University of Nottingham and has more than 15 years of experience in the GNSS and space domains.
Floor Thomas Melman received his MSc in Aerospace Engineering at the Delft University of Technology in 2018. He is currently a radio navigation engineer in the navigation system definition section within ESA/ESTEC in the Netherlands. He is coordinating the GNSS receiver experiment that will fly on the Lunar Pathfinder mission and supports the ESA Moonlight program that will provide lunar communication and navigation services. Furthermore, he is the ESA lead within the LunaNet PNT working group that will define standards and protocols enabling interoperable lunar PNT systems.
Dimitrios Psychas is as a Navigation Engineer in the End-to-End Systems Division at the European Space Agency, contributing mainly to the design and development of the Galileo 2nd Generation Ground Segment, the Galileo High Accuracy Service, and the Moonlight program. He received his Ph.D. degree in Geodesy and GNSS from Delft University of Technology, The Netherlands. He is the chair of the “High-Precision GNSS Theory and Algorithms” group of the International Association of Geodesy (IAG).
Yoann Audet received his MSc in Aerospace Engineering from Institut Polytechnique des Sciences Avancees (IPSA) in 2021 and his advanced master in Space Applications and Services (SPAPS) from ISAE-SUPAERO in 2022. He joined ESA in 2022 as a Young Graduate Trainee to support interplanetary navigation projects such as Moonlight, LightShip-MARCONI and ArgoNET/NovaMoon.
