<p> </p> <p>In the coming decades, numerous missions plan to exploit multi-body orbits for operations. Given the complex nature of multi-body systems, trajectory designers must possess effective tools that leverage aspects of the dynamical environment to streamline the design process and enable these missions. In this investigation, a particular class of dynamical structures, quasi-periodic orbits, are examined. This work summarizes a computational framework to construct quasi-periodic orbits and a design framework to leverage quasi-periodic motion within the path planning process. First, quasi-periodic orbit computation in the Circular Restricted Three-Body Problem (CR3BP) and the Bicircular Restricted Four-Body Problem (BCR4BP) is summarized. The CR3BP and BCR4BP serve as preliminary models to capture fundamental motion that is leveraged for end-to-end designs. Additionally, the relationship between the Earth-Moon CR3BP and the BCR4BP is explored to provide insight into the effect of solar acceleration on multi-body structures in the lunar vicinity. Characterization of families of quasi-periodic orbits in the CR3BP and BCR4BP is also summarized. Families of quasi-periodic orbits prove to be particularly insightful in the BCR4BP, where periodic orbits only exist as isolated solutions. Computation of three-dimensional quasi-periodic tori is also summarized to demonstrate the extensibility of the computational framework to higher-dimensional quasi-periodic orbits. Lastly, a design framework to incorporate quasi-periodic orbits into the trajectory design process is demonstrated through a series of applications. First, several applications were examined for transfer design in the vicinity of the Moon. The first application leverages a single quasi-periodic trajectory arc as an initial guess to transfer between two periodic orbits. Next, several quasi-periodic arcs are leveraged to construct transfer between a planar periodic orbit and a spatial periodic orbit. Lastly, transfers between two quasi-periodic orbits are demonstrated by leveraging heteroclinic connections between orbits at the same energy. These transfer applications are all constructed in the CR3BP and validated in a higher-fidelity ephemeris model to ensure the geometry persists. Applications to ballistic lunar transfers are also constructed by leveraging quasi-periodic motion in the BCR4BP. Stable manifold trajectories of four-body quasi-periodic orbits supply an initial guess to generate families of ballistic lunar transfers to a single quasi-periodic orbit. Poincare mapping techniques are used to isolate transfer solutions that possess a low time of flight or an outbound lunar flyby. Additionally, impulsive maneuvers are introduced to expand the solution space. This strategy is extended to additional orbits in a single family to demonstrate "corridors" of transfers exist to reach a type of destination motion. To ensure these transfers exist in a higher fidelity model, several solutions are transitioned to a Sun-Earth-Moon ephemeris model using a differential corrections process to show that the geometries persist.</p>

For 500 years transient light phenomena (TLP) have been observed on the lunar surface by ground-based observers. The actual physical reason for most of these events is today still unknown. Current plans of NASA and SpaceX to send astronauts back to the Moon and already successful deep-space CubeSat mission will allow in the future research nanosatellite missions to the cislunar space. This thesis presents a new hardware and software concept for a future payload on such a nanosatellite. The main task was to develop and implement a high-performance image processing algorithm which task is to detect short brightening flashes on the lunar surface. Based on a review of historic reported phenomena, possible explanation theories for these phenomena and currently active and planed ground- or space-based observatories possible reference scenarios were analyzed. From the presented scenarios one, the detection of brightening events was chosen and requirements for this scenario stated. Afterwards, possible detectors, processing computers and image processing algorithms were researched and compared regarding the specified requirements. This analysis of available algorithm was used to develop a new high-performance detection algorithm to detect transient brightening events on the Moon. The implementation of this algorithm running on the processor and the internal GPU of a MacMini achieved a framerate of 55 FPS by processing images with a resolution of 4.2 megapixel. Its functionality and performance was verified on the remote telescope operated by the Chair of Space Technology of the University of Würzburg. Furthermore, the developed algorithm was also successfully ported on the Nvidia Jetson Nano and its performance compared with a FPGA based image processing algorithm. The results were used to chose a FPGA as the main processing computer of the payload. This concept uses two backside illuminated CMOS image sensor connected to a single FPGA. On the FPGA the developed image processing algorithm should be implemented. Further work is required to realize the proposed concept in building the actual hardware and porting the developed algorithm onto this platform.

No description available.

<p> </p> <p>There are several challenges that occur when creating extraterrestrial structures that are not relevant to terrestrial applications. The Resilient Extra-Terrestrial Habitat Institute is a NASA funded research project focused on developing resilient lunar habitats. In order to develop these deep-space structures, many considerations have to be made to account for scenarios that are not relevant to Earth. Such scenarios include meteorite impacts, moonquakes, radiation, and moon dust accumulation. To observe possible consequences of these disruptions, RETHi established a modular coupled virtual testbed to monitor the effects of different deep-space related situations. MCVT is a computer model of a lunar habitat that uses a system-of-systems approach to examine the impacts of these scenarios. Currently, MCVT is developing methods to confront these extraterrestrial situations by utilizing robotic agents and expanding upon a variety of safety responses to increase resiliency.  RETHi also utilizes a cyber physical testbed to run cyber-physical experiments to validate the approaches used in MCVT. </p> <p><br></p> <p>One of the numerous models in MCVT is the Habitat Interior Environment Model. HIEM monitors the interior environment of the lunar structure using physics-based calculations and inputs from its surroundings. There are three main disturbances that directly affect the interior environment—fire within the dome, meteorite impacts, and airlock failure. Such scenarios either increase or decrease the temperature and pressure. This data is then forwarded to other subsystems for further evaluation. HIEM can be remodeled to fit the pressure box in the cyber physical testbed. By doing so, it is then possible to validate the pressure leakage calculations used in HIEM using experimental data. HIEM is specifically designed to the lunar habitat currently in development; however, the model can be refitted to a variety of applications such as terrestrial, aerospace, space, and marine. </p>

<p dir="ltr">This research explores the potential of AR for lunar missions via the xEMU spacesuit. A market analysis of commercial off-the-shelf AR devices identifies technological trends and constraints that inform the architectural decisions for AR integration with the xEMU. User evaluations in simulated work environments ensure lunar informatics align with crew needs. Drawing insights from human-in-the-loop testing of COTS AR devices, qualitative test results underscore the importance of display optimization, occlusion management, and environmental considerations for enhancing the AR experience during lunar EVAs. Grounded in a task analysis from JETT3 analog testing, crew workflows and communication dynamics are baselined, underscoring the vital role of communication and collaboration. Integrating AR into the EVA work environment holds the potential to streamline decision-making, improve navigation, and enhance overall efficiency, but may come with unintended operational consequences. The human-centered approach prioritizes crew involvement, ensuring that technology remains a facilitator rather than an encumbering element in lunar exploration. The study's significance lies in advancing AR technology for lunar EVAs, guiding hardware design, and enabling seamless integration into the EVA work environment. AR holds promise in reshaping the human-technology relationship, empowering crew members, maximizing science output, and contributing to the next chapter in lunar exploration.</p>

No description available.

<p dir="ltr"> With NASA's Artemis program and international collaborations focused on building a sustainable infrastructure for human exploration of the Moon, there is a growing demand for lunar exploration and complex spaceflight operations in cislunar space. However, designing efficient transfer trajectories between the Earth and the Moon remains complex and challenging. This investigation focuses on developing a dynamically informed framework for constructing low-energy transfers in the Earth-Moon-Sun Bicircular Restricted Four-body Problem (BCR4BP). Techniques within dynamical systems theory and numerical methods are exploited to construct transfers to various cislunar orbits. The analysis aims to contribute to a deeper understanding of the dynamical structures governing spacecraft motion. It addresses the characteristics of dynamical structures that facilitate the construction of propellant-efficient pathways between the Earth and the Moon, exploring periodic structures and energy properties from the Circular Restricted Three-body Problem (CR3BP) and BCR4BP. The investigation also focuses on constructing families of low-energy transfers by incorporating electric propulsion, i.e., low thrust, in an effort to reduce the time of flight and offer alternative transfer geometries. Additionally, the investigation introduces a process to transition solutions to the higher fidelity ephemeris force model to accurately model spacecraft motion through the Earth-Moon-Sun system. This research provides insights into constructing families of ballistic lunar transfers (BLTs) and cislunar low-energy flight paths (CLEFs), offering a foundation for future mission design and exploration of the Earth-Moon system.</p>

For several decades, the idea of flying and landing a less-than-man-rated nuclear reactor for planetary surface applications has been considered. This approach promises significant mass savings and therefore reduction in launch cost. To compensate for the lack of shielding, it has been suggested the use of in-situ materials for providing radiation protection. This would take the form of either raw dirt walls or processed soil materials into blocks or tile elements. As a first step in determining the suitability of this approach, it is necessary to understand the neutron activation characteristics of these soils. A simple assessment of these activation characteristics was conducted for both Martian and Lunar soils using ORIGEN2.2. An average composition for these soils was assumed. As a baseline material, commonly used NBS-03 concrete was compared against the soils. Preliminary results indicate that over 2.5 times more gamma-radiation production of these soils vs. concrete took place during the irradiation phase (a baseline of 2.4 x 1011 neutrons/sec-cm2 was assumed). This was due primarily to radiative capture on Na23 and Mn55 and subsequent decay of their activation products. This is does not necessarily disqualify these materials as potential shielding material since the -radiation output was only in the order of 4.2 x 108 photons/cm3-sec. Furthermore, these soils did not show any significant activity after shutdown of the neutron source (the reactor), since all activation products had very short half lives. Their performance in this area was comparable to that of NBS-03 concrete. / text

Les sites d'agrégation de ponte (AP) sont des zones où des poissons d'une même espèce se rassemblent pour frayer. En dépit de leur importance dans la reproduction de nombreuses espèces de poissons des récifs coralliens, bien peu de sites d'AP sont gérés. Le but de cette étude est d'améliorer la compréhension générale sur l'écologie des sites d'AP en vue de faciliter la gestion. L'étude, réalisée aux Seychelles, se concentre sur les individus regroupant sur les sites d'AP pour frayer et aussi sur ceux résidant sur ces sites. La télémétrie acoustique et le recensement visuel sous-marin ont, ici, été employé comme principaux outils d'observation des espèces formant des agrégations de reproduction (cordonnier (Siganus sutor), mérou camouflage (Epinephelus polyphekadion) et mérou marbré (E. fuscoguttatus)) et des espèces résidant sur les sites d'AP. Les détections acoustiques ont montré que les individus de S. sutor présentent une grande fidélité à leur site de ponte et une périodicité liée à la période de pleine lune. Par ailleurs, les agrégations de ponte d'E. fuscoguttatus et E. polyphekadion se chevauchent spatialement et temporellement avec une forte périodicité liée à la nouvelle lune. La formation d'AP de E. fuscoguttatus et E. polyphekadion provoque des changements complexes dans l'assemblage de poissons résidents sur le site. L'effet de la phase lunaire sur les assemblages de poissons résidant sur les sites d'AP de S. Sutor apparait être dépendant de l'échelle considérée. Les informations sur la dynamique spatiale et temporelle des espèces étudiée sont utilisées pour proposer des mesures de gestion susceptibles d'améliorer la protection des sites d'AP. / Fish spawning aggregation (FSA) sites are areas where repeated concentration of conspecific fish gathers for the purpose of spawning. Despite of their importance in the reproduction of many coral reef fishes, few FSA sites are actively managed. The aim of this study, conducted in the Seychelles, was to improve general understanding on the ecology of FSA sites to facilitate their management. It focuses on both the individuals that aggregate at FSA sites to spawn and those that are resident at FSA sites. Acoustic telemetry and underwater visual census were used to study three species that form spawning aggregations (spinefoot shoemaker (Siganus sutor), Camouflage grouper (Epinephelus polyphekadion) and Brown-marbled grouper (E. fuscoguttatus)) and the resident fish assemblages at FSA sites. Acoustic detections found individual S. sutor to have high fidelity to individual FSA sites and to show significant periodicity with the full moon period in the timing of their arrival and departure from FSA sites. Conversely, spawning aggregations of E. fuscoguttatus and E. polyphekadion overlapped spatially and temporally, with strong periodicity for spawning aggregation to form with the new moon period. The formation of E. fuscoguttatus and E. polyphekadion FSAs caused complex changes in the fish assemblage that is resident at the FSA site. The effect of lunar phase on the resident fish assemblages at S. sutor FSA sites appeared to be scale-dependent, having greater impact at the larger than the smaller FSA site. Information on the spatial and temporal dynamics of aggregating and resident fish species is used to propose management actions to improve the protection of FSA sites.

Dans cette thèse, nous nous intéressons au problème de l’atterrissage lunaire autonome et nous proposons une méthode innovante amenant une alternative à l’utilisation de capteurs classiques qui peuvent se révéler encombrants, énergivores et très onéreux.La première partie est consacrée au développement et à la construction de capteurs de mouvement inspirés de la vision des insectes volants et mesurant le flux optique.Le flux optique correspond à la vitesse angulaire relative de l’environnement mesurée par la rétine d’un agent. Dans un environnement fixe, les mouvements d’un robot génèrent un flux optique contenant des informations essentielles sur le mouvement de ce dernier. En utilisant le principe du « temps de passage », nous présentons les résultats expérimentaux obtenus en extérieur avec deux versions de ces capteurs.Premièrement, un capteur mesurant le flux optique dans les deux directions opposées est développé et testé en laboratoire. Deuxièmement un capteur adapté à la mesure des faibles flux optiques similaires à ceux pouvant être mesurés lors d’un alunissage est développé, caractérisé et enfin testé sur un drone hélicoptère en conditions extérieures.Dans la seconde partie, une méthode permettant de réaliser le guidage, la navigation et la commande (GNC pour Guidance Navigation and Control) du système est proposée. L’innovation réside dans le fait que l’atterrissage en douceur est uniquement assuré par les capteurs de flux optique. L’utilisation des capteurs inertiels est réduite au maximum. Plusieurs capteurs orientés dans différentes directions de visée, et fixés à la structure de l’atterrisseur permettent d’atteindre les conditions finales définies par les partenaires industriels. Les nombreuses informations décrivant la position et l’attitude du système contenues dans le flux optique sont exploitées grâce aux algorithmes de navigation qui permettent d’estimer les flux optiques ventraux et d’expansion ainsi que le tangage.Nous avons également montré qu’il est possible de contrôler l’atterrisseur planétaire en faisant suivre aux flux optiques estimés une consigne optimale au sens de la consommation d’énergie. Les simulations réalisées durant la thèse ont permis de valider le fonctionnement et le potentiel de la solution GNC proposée en intégrant le code du capteur ainsi que des images simulées du sol de la lune. / In this PhD thesis, the challenge of autonomous lunar landing was addressed and an innovative method was developed, which provides an alternative to the classical sensor suites based on RADAR, LIDAR and cameras, which tend to be bulky, energy consuming and expensive. The first part is devoted to the development of a sensor inspired by the fly’s visual sensitivity to optic flow (OF). The OF is an index giving the relative angular velocity of the environment sensed by the retina of a moving insect or robot. In a fixed environment (where there is no external motion), the self-motion of an airborne vehicle generates an OF containing information about its own velocity and attitude and the distance to obstacles. Based on the “Time of Travel” principle we present the results obtained for two versions of 5 LMSs based optic flow sensors. The first one is able to measure accurately the OF in two opposite directions. It was tested in the laboratory and gave satisfying results. The second optic flow sensor operates at low velocities such as those liable to occur during lunar landing was developed. After developing these sensors, their performances were characterized both indoors and outdoors, and lastly, they were tested onboard an 80-kg helicopter flying in an outdoor environment. The Guidance Navigation and Control (GNC) system was designed in the second part on the basis of several algorithms, using various tools such as optimal control, nonlinear control design and observation theory. This is a particularly innovative approach, since it makes it possible to perform soft landing on the basis of OF measurements and as less as possible on inertial sensors. The final constraints imposed by our industrial partners were met by mounting several non-gimbaled sensors oriented in different gaze directions on the lander’s structure. Information about the lander’s self-motion present in the OF measurements is extracted by navigation algorithms, which yield estimates of the ventral OF, expansion OF and pitch angle. It was also established that it is possible to bring the planetary lander gently to the ground by tracking a pre-computed optimal reference trajectory in terms of the lowest possible fuel consumption. Software-in-the-loop simulations were carried out in order to assess the potential of the proposed GNC approach by testing its performances. In these simulations, the sensor firmware was taken into account and virtual images of the lunar surface were used in order to improve the realism of the simulated landings.