As commercial lunar rovers are being developed and planned to fly from next year, in the context of a global momentum for lunar exploration, the mindset of system design is shifting to a product-oriented approach (as opposed to traditionally single mission-designed system). This deeply affects the system engineering discipline, which is also evolving through the development of more integrated, model-centric methodologies such as Model-Based System Engineering (MBSE). This Master Thesis combines 2 research questions:- How to adapt systems engineering processes and tools to a commercially-driven / product-oriented approach?- How to leverage new developments (e.g MBSE) within the system engineering discipline to support the rover design transition to a product-oriented philosophy? These research questions are investigated through this Master Thesis, carried out as a 6-month internship at ispace Europe (Luxembourg), a global lunar exploration company developing landers, rovers and data tools. The Master Thesis is applied to ispace’s Exploration Rover currently under development within the Polar Ice Explorer (PIE) mission with support from the Luxembourg Government.The goal of this Master Thesis is to develop an integrated toolchain (set of tools) for efficiently designing rover products (Exploration Rover), including platform configuration for a given mission concept and set of payloads, system sizing and mission analysis. The chosen methodology can be summarized as:1. Adapting PIE models to a generic, parametric/configurable toolset that can be used for mission/platform analysis and optimization2. Defining the Exploration Rover toolchain requirements & architecture, and selecting its environment (trade-off including MBSE solutions)3. Building the Exploration Rover toolchain, integrating models inside the defined architecture By maturing existing models, leveraging new software functionalities (in this case Valispace) and MBSE practises along with adding new parametric models for quick feasibility studies and integrating all models together, it was successfully shown that this integrated toolchain can support rover products definition, performing frequent and insightful design iterations, analysis and trade-offs. Not only does the toolchain comply with the product-approach but also successfully supports the Polar Ice Explorer (PIE) mission, by directly contributing to the system engineering activities and models of the Phase B. Therefore, the Master Thesis proved to be a successful demonstrator for developing more product-driven rovers, by leveraging new practices within the system engineering discipline. / Eftersom kommersiella månrovers utvecklas och planeras att flyga från nästa år, i samband med en global fart för månutforskning, går tankesättet för systemdesign över till produktorienterat tillvägagångssätt (i motsats till traditionellt endast uppdragsdesignat system). Detta påverkar djupt systemteknikdisciplinen, som också utvecklas genom utvecklingen av mer integrerade, modellcentrerade metoder som Model-Based System Engineering (MBSE).  Denna masteruppsats kombinerar två forskningsfrågor: - Hur anpassar man systemtekniska processer och verktyg till en kommersiellt driven / produktorienterad strategi? - Hur kan man utnyttja ny utveckling (t.ex. MBSE) inom systemteknikdisciplinen för att stödja rover-designövergången till en produktorienterad filosofi?  Dessa forskningsfrågor undersöks genom denna magisteruppsats, som genomfördes genom en praktik under 6 månader på ispace Europe (Luxemburg), ett globalt månutforskningsföretag som utvecklar landare, rovers och dataverktyg. Magisteruppsatsen tillämpas på ispaces Exploration Rover som för närvarande är under utveckling inom Polar Ice Explorer (PIE) -uppdraget, med med stöd från den luxemburgska. Målet med detta examensarbete är att utveckla en integrerad verktygskedja (uppsättning verktyg) för att effektivt utforma roverprodukter (Exploration Rover), inklusive plattformskonfiguration för ett givet uppdragskoncept och uppsättning nyttolast, systemstorlek och uppdragsanalys.  Den valda metoden kan sammanfattas som: 1. Anpassa PIE -modeller till en generisk, parametrisk / konfigurerbar verktygssats som kan användas för uppdrag / plattformsanalys och optimering 2. Definiera Exploration Rover-verktygskedjans krav och arkitektur och välja dess miljö (avvägning inklusive MBSE-lösningar) 3. Bygga Exploration Rover -verktygskedjan, integrera modeller inom den definierade arkitekturen  Genom att utveckla befintliga modeller, utnyttja nya mjukvarufunktioner (här Valispace) och MBSE -metoder tillsammans med att lägga till nya parametriska modeller för snabba genomförbarhetsstudier och integrera alla modeller tillsammans: visades det att denna inbyggda integrerade verktygskedja kan stödja rover -produktdefinition, som utför ofta och insiktsfulla design iterationer, analyser och avvägningar. Verktygskedjan följer inte bara produktmetoden utan stöder också framgångsrikt Polar Ice Explorer (PIE) -uppdraget genom att direkt bidra till systemtekniska aktiviteter och modeller i Phase B.  Därför visade masteruppsatsen sig vara en framgångsrik demonstrator för att utveckla mer produktdrivna rovers, genom att utnyttja nya metoder inom systemteknikdisciplinen.

This thesis deals with the challenge of autonomous navigation of the ExoMars rover. The absence of global positioning systems (GPS) in space, added to the limitations of wheel odometry makes autonomous navigation based on these two techniques - as done in the literature - an inviable solution and necessitates the use of other approaches. That, among other reasons, motivates this work to use solely visual data to solve the robot’s Egomotion problem. The homogeneity of Mars’ terrain makes the robustness of the low level image processing technique a critical requirement. In the first part of the thesis, novel solutions are presented to tackle this specific problem. Detection of robust features against illumination changes and unique matching and association of features is a sought after capability. A solution for robustness of features against illumination variation is proposed combining Harris corner detection together with moment image representation. Whereas the first provides a technique for efficient feature detection, the moment images add the necessary brightness invariance. Moreover, a bucketing strategy is used to guarantee that features are homogeneously distributed within the images. Then, the addition of local feature descriptors guarantees the unique identification of image cues. In the second part, reliable and precise motion estimation for the Mars’s robot is studied. A number of successful approaches are thoroughly analysed. Visual Simultaneous Localisation And Mapping (VSLAM) is investigated, proposing enhancements and integrating it with the robust feature methodology. Then, linear and nonlinear optimisation techniques are explored. Alternative photogrammetry reprojection concepts are tested. Lastly, data fusion techniques are proposed to deal with the integration of multiple stereo view data. Our robust visual scheme allows good feature repeatability. Because of this, dimensionality reduction of the feature data can be used without compromising the overall performance of the proposed solutions for motion estimation. Also, the developed Egomotion techniques have been extensively validated using both simulated and real data collected at ESA-ESTEC facilities. Multiple stereo view solutions for robot motion estimation are introduced, presenting interesting benefits. The obtained results prove the innovative methods presented here to be accurate and reliable approaches capable to solve the Egomotion problem in a Mars environment.

Spur-of-the-moment planetary exploration missions are within our reach. Complex systems and complex missions usually take years of planning and force launches to become incredibly expensive. We argue here for cheap, fast missions using large numbers of mass produced simple autonomous robots that are small by today's standards, perhaps 1 to 2kg. We suggest that within a few years it will be possible, at modest cost, to invade a planet with millions of tiny robots.

This doctoral thesis extends analytical terramechanic modelling for small lightweight mobile robots operating on sandy soil. Previous terramechanic models were designed to capture and predict the mean values of the forces and sinkage that a wheel may experience. However, these models do not capture the fluctuations in the forces and sinkage that were observed in experimental data. The model developed through the course of this research enhances existing terramechanic models by proposing and validating a new pressure-sinkage relationship. The resulting two-dimensional model was validated with a unique high fidelity single-wheel testbed (SWTB) which was installed on a Blohm Planomat 408 computer-numerically controlled creepfeed grinding machine. The new SWTB translates the terrain in the horizontal direction while the drivetrain and wheel support systems are constrained in the horizontal direction but allowed to freely move in the vertical direction. The design of the SWTB allowed for a counterbalance to be installed and, as a result, low normal loads could be examined. The design also took advantage of the grinding machine's high load capacity and precise velocity control. Experiments were carried out with the new SWTB and predictable repeating ridges were found in the track of a smooth rigid wheel operating in sandy soil. To ensure that these ridges were not an artifact of the new SWTB a mobile robot was used to validate the SWTB findings, which it did. The new SWTB is a viable method for investigating fundamental terramechanic issues. A series of experiments at different slip ratios and normal loads were carried out on the SWTB to validate the new pressure-sinkage relationship which explicitly captures and predicts the oscillations about the mean values for the forces and sinkage values for both a smooth wheel and a wheel with grousers. The new pressure-sinkage relationship adds two new dimensionless empirical factors to the well known pressure-sinkage relationship for a rigid wheel. The first new factor accounts for changes in the local density of the terrain around the wheel and the second factor accounts for the effects grousers have on the forces and sinkage.

This thesis deals with the challenge of autonomous navigation of the ExoMars rover. The absence of global positioning systems (GPS) in space, added to the limitations of wheel odometry makes autonomous navigation based on these two techniques - as done in the literature - an inviable solution and necessitates the use of other approaches. That, among other reasons, motivates this work to use solely visual data to solve the robot’s Egomotion problem. The homogeneity of Mars’ terrain makes the robustness of the low level image processing technique a critical requirement. In the first part of the thesis, novel solutions are presented to tackle this specific problem. Detection of robust features against illumination changes and unique matching and association of features is a sought after capability. A solution for robustness of features against illumination variation is proposed combining Harris corner detection together with moment image representation. Whereas the first provides a technique for efficient feature detection, the moment images add the necessary brightness invariance. Moreover, a bucketing strategy is used to guarantee that features are homogeneously distributed within the images. Then, the addition of local feature descriptors guarantees the unique identification of image cues. In the second part, reliable and precise motion estimation for the Mars’s robot is studied. A number of successful approaches are thoroughly analysed. Visual Simultaneous Localisation And Mapping (VSLAM) is investigated, proposing enhancements and integrating it with the robust feature methodology. Then, linear and nonlinear optimisation techniques are explored. Alternative photogrammetry reprojection concepts are tested. Lastly, data fusion techniques are proposed to deal with the integration of multiple stereo view data. Our robust visual scheme allows good feature repeatability. Because of this, dimensionality reduction of the feature data can be used without compromising the overall performance of the proposed solutions for motion estimation. Also, the developed Egomotion techniques have been extensively validated using both simulated and real data collected at ESA-ESTEC facilities. Multiple stereo view solutions for robot motion estimation are introduced, presenting interesting benefits. The obtained results prove the innovative methods presented here to be accurate and reliable approaches capable to solve the Egomotion problem in a Mars environment. / © Cranfield University

This dissertation details the design and development of a mobile autonomous platform from which to conduct a 3D ground-penetrating radar survey. The system uses a three-rover multiagent team to perform a site-selection activity during a lunar analog mission. The work took place beginning in 2008 and culminated in a final field test on Mauna Kea in Hawaii. This demonstration of autonomous acquisition of 3D ground-penetrating radar in a space robtic application is promising not only for in-situ resource utilization, but also for the concept of multiagent teaming.

This dissertation details the design and development of a mobile autonomous platform from which to conduct a 3D ground-penetrating radar survey. The system uses a three-rover multiagent team to perform a site-selection activity during a lunar analog mission. The work took place beginning in 2008 and culminated in a final field test on Mauna Kea in Hawaii. This demonstration of autonomous acquisition of 3D ground-penetrating radar in a space robtic application is promising not only for in-situ resource utilization, but also for the concept of multiagent teaming.

The main objective of this research is the development of a volumetric wheel-soil ground contact model that is suitable for mobile robotics applications with a focus on efficient simulations of planetary rover wheels operating on compliant and irregular terrains. To model the interaction between a rover wheel and soft soil for use in multibody dynamic simualtions, the terrain material is commonly represented by a soil continuum that deforms substantially when in contact with the locomotion system of the rover. Due to this extensive deformation and the large size of the contact patch, a distributed representation of the contact forces is necessary. This requires time-consuming integration processes to solve for the contact forces and moments during simulation. In this work, a novel approach is used to represent these contact reactions based on the properties of the hypervolume of penetration, which is defined by the intersection of the wheel and the terrain. This approach is based on a foundation of springs for which the normal contact force can be calculated by integrating the spring deflections over the contact patch. In the case of an elastic foundation, this integration results in a linear relationship between the normal force and the penetration volume, with the foundation stiffness as the proportionality factor. However, due to the highly nonlinear material properties of the soft terrain, a hyperelastic foundation has to be considered and the normal contact force becomes proportional to a volume with a fractional dimension --- a hypervolume. The continuous soil models commonly used in terramechanics simulations can be used in the derivation of the hypervolumetric contact forces. The result is a closed-form solution for the contact forces between a planetary rover wheel and the soft soil, where all the information provided by a distributed load is stored in the hypervolume of interpenetration. The proposed approach is applied to simulations of rigid and flexible planetary rover wheels. In both cases, the plastic behaviour of the terrain material is the main source of energy loss during the operation of planetary rovers. For the rigid wheel model, a penetration geometry is proposed to capture the nonlinear dissipative properties of the soil. The centroid of the hypervolume based on this geometry then allows for the calculation of the contact normal that defines the compaction resistance of the soil. For the flexible wheel model, the deformed state of the tire has to be determined before applying the hypervolumetric contact model. The tire deformation is represented by a distributed parameter model based on the Euler-Bernoulli beam equations. There are several geometric and soil parameters that are required to fully define the normal contact force. While the geometric parameters can be measured, the soil parameters have to be obtained experimentally. The results of a drawbar pull experiment with the Juno rover from the Canadian Space Agency were used to identify the soil parameters. These parameters were then used in a forward dynamics simulation of the rover on an irregular 3-dimensional terrain. Comparison of the simulation results with the experimental data validated the planetary rover wheel model developed in this work.

Hardware-in-the-Loop (HIL) test platform for planetary rovers was designed, fabricated and tested in the present work. The ability for planetary rover designers and mission planners to estimate the rover’s performance through software simulation is crucial. HIL testing can further the benefits of software simulations by allowing designers to incorporate hardware components within traditionally pure software simulations. This provides more accurate performance results without having access to all hardware components, as would be required for a full prototype testing. The test platform is designed with complete modularity such that different types of tests can be performed for varying types of planetary rovers and in different environments. For demonstrating the operation of the test platform, however, the power system operation of a solar powered rover was examined. The system consists of solar panels, a solar charge controller, a battery, a DC/DC converter, a DC motor and a flywheel. In addition, a lighting system was designed to simulate the solar radiation conditions solar panels would experience throughout a typical day. On the software side, a library of component models was developed within MapleSim and model parameters were tuned to match the hardware on the test bench. A program was developed for real-time simulations within Labview allowing communication between hardware components and software models. This program consists of all the component models, hardware controls and data acquisitioning. The GUI of this program allows users to select which component is to be tested and which component is to be simulated, change model parameters as well as see real time sensor measurements for each component. A signal scaling technique based on non-dimensionalization is also presented, which can be used in an HIL application for obtain scaling factors to ensure dynamic similarity between two systems. A demonstration of power estimation was performed using the pure software model simulations as well as the pure hardware testing. Hardware components were then added into the software simulation progressively with results showing better accuracy as hardware is added. The rover’s power flow was also estimated under different load conditions and seasonal variation. These simulations clearly demonstrate the effectiveness of an HIL platform for testing a rover’s hardware performance.

How the dust cycle works on Mars is a key atmospheric issue, as the dust cycle is arguably the dominant cycle in the current Martian climate. In addition, how much is known about the Martian planetary boundary layer is mostly determined from models with very little in-situ data from contemporaneous studies to validate such boundary layer characteristic assumptions, and the model studies have not been able to define a known height for a possible boundary layer on Mars using ground-based investigations prior to this research. The Mars Exploration Rovers (MERs), however, show promise in offering a unique chance to take surface-based measurements to offer support for dust and boundary layer measurements made from remote sensors. There are three main objectives of this study: to constrain the late-afternoon maximum height of the boundary layer for both MER sites, to constrain the mean particle size and variance of the size distribution in the atmosphere, and to use these results to demonstrate that sunset and twilight imaging is a useful survey of otherwise difficult-to-determine parameters that are needed in several tools for studying Mars’ atmosphere. A modeling approach using twilight-based Sun imaging by the MERs (Sol 1959 for Spirit and Sol 695 for Opportunity) is used to constrain boundary layer and dust particle size parameters. After determining which parameters control which observables, resulting elevations and azimuths are matched up to specific observations from the available MER datasets. A Monte Carlo code produces the model that is then compared to Sol data with plotting of resulting error. Results include PBL height and structure estimations and plots along with generalized particle size information for each MER site on the given Sol. Figures show comparisons of this study’s particle size results with that of previous studies as well as maps of fit qualities for boundary layer parameters compared to a contemporaneous modeled scale height estimation. Results show promise for planning future MER-based campaigns and models.