2021 IEEE Aerospace Conference (50100)最新文献

{"title":"ORACLE - A PHM Test & Validation Platform for Anomaly Detection in Crew Member Vital Sign Data","authors":"W. Fink, Shaun Brown, M. Tarbell, A. Hess","doi":"10.1109/AERO50100.2021.9438172","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438172","url":null,"abstract":"With NASA's push for prolonged stays aboard orbiting or surface-based space habitats (e.g., NASA Gateway/Artemis programs and successors) on the Moon and soon on Mars, there is a need for continuous monitoring of life support and mission critical systems deployed on these space habitats. Abiotic sensors will likely be used to detect anomalies aboard these space habitats, which we expect also to be embedded in a Prognostics and Health Management (PHM) framework. Recently, we introduced the concept of employing the crew member as a biosensor to be integrated into an overarching space habitat PHM system to increase the breadth of available data when monitoring environment health. Utilizing electrocardiogram (ECG) data as an example of a non-invasively obtained vital sign, we have devised a PHM test & validation platform - the ORACLE - that auto-generates raw ECG data from previously extracted ECG motifs, ultimately representative of various conditions resulting from space habitat environment changes. The ORACLE emulates the occurrence of environmental changes and generates a log file to allow for training and subsequent deep learning-based anomaly detection frameworks, serving as a proof of concept for integration as a subsystem into a novel overarching PHM-based anomaly detection framework for monitoring space habitat health. The current version of ORACLE is equipped with an anomaly detection framework using multi-layer feedforward networks. This paper showcases the workings of the ORACLE and presents preliminary results for the deep learning-based anomaly detection framework. The ultimate goal is to use the measured “biometric” changes in each crew member as a supplementary indicator to detect degradation in the space habitat environment and associated habitat subsystems. This novel indicator has the potential to enhance existing capabilities by providing for earlier detection than might otherwise be possible. The general idea is to use the crew health status as an integrated contributor to other PHM capabilities already implemented on associated space habitat subsystems.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"134 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115475682","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Design and Development of Control Electronics for Coriolis Vibratory Gyroscopes","authors":"A. Amal, R. Arlene Davidson","doi":"10.1109/AERO50100.2021.9438329","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438329","url":null,"abstract":"Gyroscopes are physical sensors used to detect and measure the angular motion of an object with respect to an inertial frame of reference. In this paper, emphasis is given to vibratory gyro, which is based on vibration that occurs within the sensor. When an external force is applied to vibratory gyro, a new vibration is produced within the sensor in perpendicular direction, which helps us in calculating the angular rate. Ring Vibratory Gyro (RVG) falls under the category of Coriolis Vibratory Gyro (CVG). Due to piezoelectric effect, the beams of the gyro are activated and this helps to sense the vibrating ring in this novel gyroscope. The gyro structure consists of a substrate, eight supporting beams of thin shape and a vibrating ring. There are two modes of vibration that are coupled by the coriolis force dynamics - drive mode and sense mode. The drive mode comprises two sections - one to track the resonant frequency and the other to keep the vibration amplitude constant. The analog signals from piezo-electric elements are amplified and filtered to send them again to the sensor. The drive mode is excited by the excitation control loop, which keeps the amplitude constant. In the open-loop mode of operation, the drive mode is excited by a force of a prescribed amplitude. Inertial rotation about the input axis then results in the excitation of the second mode (the sense mode). The amplitude of the sense mode vibration is proportional to the input angular rate. The model of CVG is established in Simulink environment. In this paper, the control electronics for the drive mode of MEMS type CVG is presented. An amplitude controller is employed in the drive loop for maintaining constant amplitude and a frequency control loop for tracking frequency with the inclusion of a reliable scheme of demodulation.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123060355","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"3D Interactive Model of HERA to support ECLSS anomaly resolution using a Virtual Assistant","authors":"R. Woodruff, Nikita Beebe, P. K. Josan, Prachi Dutta, A. Short, R. Wong, B. Dunbar, Daniel Selva, A. Diaz-Artiles","doi":"10.1109/AERO50100.2021.9438341","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438341","url":null,"abstract":"In future long-duration exploration missions (LDEMs), communication with mission control will be significantly delayed. Crews will often need to react to time-sensitive issues or hazards without relying on mission control for assistance. The need for a higher degree of crew autonomy without direct oversight from mission control introduces the implementation of virtual assistants (VAs) to aid the crew; however, we must first create standards and guidelines for VAs in this context. For this purpose, we have developed a VA called Daphne-AT (Anomaly Treatment) to investigate the interaction between astronauts and virtual assistants in the context of anomaly resolution related to the Environmental Control and Life Support System (ECLSS). A series of experiments will be conducted in a laboratory environment and at the Human Exploration Research Analog (HERA) at NASA Johnson Space Center (JSC) to study user's performance, situational awareness, cognitive workload, and trust in Daphne-AT. Subjects in a simulated LDEM will be given several ECLSS anomalies to identify and solve with and without the support of Daphne-AT. We based the scenarios we developed on existing ECLSS hardware and pre-existing anomaly resolution procedures from the HERA environment. Solving an anomaly requires the subject to complete the correct anomaly resolution procedure(s) for the appropriate anomaly, which could include various tasks such as swapping out component parts and activating or deactivating ECLSS systems. In experiment sessions without Daphne-AT, subjects will rely on telemetry feeds as well as background knowledge and training to solve anomalies. However, during experiment sessions with Daphne-AT, the VA will also assist subjects in detecting and diagnosing these anomalies. We conducted an initial set of experiments at Texas A&M University (TAMU) prior to those at HERA. However, the subject must complete anomaly resolution procedures during an experiment that require access to hardware and components not available at the TAMU location. To emulate the HERA ECLSS hardware elements in our laboratory at TAMU, we recreated a virtual 3D representation of HERA and its ECLSS systems using the game engine Unreal Engine 4 (UE4). This virtual model will act as an analog for subjects who are tested on TAMU's campus to complete relevant ECLSS procedures. All subsystems featured in the UE4 model are interactive and allow the user to perform steps in an anomaly resolution procedure similar to how the user would do it in HERA. The UE4 model allows the user to complete more than 20 anomaly resolution procedures, thus increasing the TAMU experiment's fidelity compared to those conducted at HERA. This paper describes the development of the UE4 model and how we used it to validate the experimental protocol implemented at HERA. The results of these experiments will inform future guidelines for VAs deployed on LDEMs.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121756957","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Analyzing Software Engineering Processes with Provenance-based Knowledge Graphs","authors":"A. Schreiber, Lynn von Kurnatowski, Claas de Boer","doi":"10.1109/AERO50100.2021.9438358","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438358","url":null,"abstract":"Insights and assessments about the quality, reliability, or trustworthiness of software systems is important for many software applications. Especially for large or mission-critical software systems, reliable measures and assertions are crucial. Since software repositories contain information about source code, software development processes, and team interactions, we extract the provenance of software artifacts from those repositories and store the provenance according to a provenance model defined using W3C PROV data model. We use the recorded provenance to discover insights about the software and its development process, which we apply and evaluate for a large aerospace software system.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121859126","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Presenting Model-Based Systems Engineering Information to Non-Modelers","authors":"Jeffrey Cohen, Sarah Arai, Tatyana Y. Rakalina, E. Griffin, Jared Heiser, Michelle Urbina, K. McGuire, D. Rubin, Alex J. Seigel, Alay Shah, Sandhya Ramachandran, Anusha Dixit, Jennifer Legaspi, J. Mindock, J. Bardina, Melinda J. Hailey","doi":"10.1109/AERO50100.2021.9438292","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438292","url":null,"abstract":"NASA's Human Research Program's (HRP) Exploration Medical Capability (ExMC) Element adopted Systems Engineering (SE) principles and Model Based Systems Engineering (MBSE) tools to capture the system functions, system architecture, requirements, interfaces, and clinical capabilities for a future exploration medical system. There are many different stakeholders who may use the information in the model: systems engineers, clinicians (physicians, nurses, and pharmacists), scientists, and program managers. Many of these individuals do not have access to MBSE modeling tools or have never used these tools. Many of these individuals (clinicians, scientists, even program managers) may have no experience with SE in general let alone interpreting a systems model. The challenge faced by ExMC was how to present the content in the model to non-modelers in a way they could understand with limited to no training in MBSE or the Systems Modeling Language (SysML) without using the modeling tool. Therefore, from the model, ExMC created an HTML report that is accessible to anyone with a browser. When creating the HTML report, the ExMC SE team talked to stakeholders and received their feedback on what content they wanted and how to display this content. Factoring in feedback, the report arranges the content in a way that not only directs readers through the SE process taken to derive the requirements, but also helps them to understand the fundamental steps in an SE approach. The report includes links to source information (i.e., NASA documentation that describes levels of care) and other SE deliverables (e.g., Concept of Operations). These links were provided to aid in the understanding of how the team created this content through a methodical SE approach. This paper outlines the process used to develop the model, the data chosen to share with stakeholders, many of the model elements used in the report, the review process stakeholders followed, the comments received from the stakeholders, and the lessons ExMC learned through producing this HTML report.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"49 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122867147","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Mercury Lander: A New-Frontiers-Class Planetary Mission Concept Design","authors":"Sanae Kubota, G. Rogers, C. Ernst, N. Chabot, R. Klima, J. Atchison, S. Bushman, J. Ercol, Derick Fuller, Daniel Gallagher, Allan Holtzman, D. Ponnusamy, Jackson L. Shannon, B. Villac","doi":"10.1109/AERO50100.2021.9438360","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438360","url":null,"abstract":"As an end-member of terrestrial planet formation, Mercury holds unique clues about the original distribution of elements in the earliest stages of solar system development and how planets and exoplanets form and evolve in close proximity to their host stars. The importance of in situ measurements via a landed mission to Mercury was recognized by the 2013–2022 Decadal Survey, and again with its selection for a Planetary Mission Concept Study in support of the 2023–2032 Decadal Survey. Mercury is the only inner planet unexplored by a landed spacecraft; landing on Mercury is uniquely challenging due to the large $Deltamathrm{V}$ requirements and extreme thermal environment for such a mission. This paper describes the mission concept design that meets those challenges by leveraging recent technology advances including increased launch vehicle performance capability, further development and use of solar electric propulsion (SEP), and Next-Generation radioisotope thermoelectric generator (NextGen RTG) development. These advances enable a New-Frontiers-class mission concept which achieves one full Mercury year (∼88 Earth days) of surface operations with an 11-instrument, high-heritage payload that is delivered to a landing site within Mercury's widely distributed low-reflectance material, and addresses science goals encompassing geochemistry, geophysics, the Mercury space environment, and geology. The mission concept presented here addresses the primary challenges of a Mercury Lander mission with a four-stage design that launches on an expendable Falcon Heavy vehicle. Mass savings are enabled through jettisoning of stages prior to large burns and optimization of propulsion systems for each phase: cruise, orbit, initial descent, and landing. The flight system utilizes an SEP cruise stage to reach Mercury and jettisons this stage prior to the Mercury orbit insertion (MOI) burn. MOI and orbit-lowering maneuvers are executed with a large bipropellant propulsion system on an orbital stage. During the orbital phase, a narrow-angle camera acquires images for final selection of a low-hazard landing zone within the region of interest. The orbital stage is jettisoned just prior to descent. A solid rocket motor (SRM) descent stage executes the braking burn, and final landing is performed following SRM burnout and jettison with the Lander's bipropellant propulsion system and continuous LIDAR operations to support hazard detection. Landing occurs at dusk to meet thermal requirements, permitting ∼30 hours of sunlight for initial observations. The NextGen RTG powered lander continues operations through the Mercury night. Direct-to-Earth (DTE) communication is available for the initial three weeks of landed operations, unavailable for the following six weeks, and resumes for the final month. Thermal conditions exceed lander operating temperatures shortly after sunrise, ending operations. A total of ∼11 GB of data are returned to Earth.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"36 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125559770","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Conceptual Design of the Lunar Crater Radio Telescope (LCRT) on the Far Side of the Moon","authors":"Saptarshi Bandyopadhyay, P. McGarey, A. Goel, Ramin Rafizadeh, Mélanie Delapierre, Manan Arya, J. Lazio, P. Goldsmith, N. Chahat, A. Stoica, M. Quadrelli, I. Nesnas, K. Jenks, G. Hallinan","doi":"10.1109/AERO50100.2021.9438165","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438165","url":null,"abstract":"An ultra-long-wavelength radio telescope on the far side of the Moon has significant advantages compared to Earth-based and Earth-orbiting telescopes, including: 1. Enabling observations of the Universe at wavelengths longer than 10 meters (i.e., frequencies below 30 MHz), wavelengths at which critical cosmological or extrasolar planetary signatures are predicted to appear, yet cannot be observed from the ground due to absorption from the Earth's ionosphere; and 2. The Moon acts as a physical shield that isolates a far-side lunar-surface telescope from radio interference from sources on the Earth's surface, the ionosphere, Earth-orbiting satellites, and the Sun's radio emission during the lunar night. In this paper, we present the conceptual design of the Lunar Crater Radio Telescope (LCRT) on the far side of the Moon. We propose to deploy a wire mesh using wall-climbing DuAxel robots in a 3–5 km diameter crater, with a suitable depth-to-diameter ratio, to form a parabolic reflector with a 1 km diameter. LCRT will be the largest filled-aperture radio telescope in the Solar System; larger than the former Arecibo telescope (305 m diameter, 3 cm - 1 m wavelength band, 0.3-10 GHz frequency band) and the Five-hundred-meter Aperture Spherical radio Telescope (FAST) (500 m diameter, 0.1-4.3 m wavelength band, 60–3000 MHz frequency band). LCRT's science objective is to track the evolution of the neutral intergalactic medium before and during the formation of the first stars in the 10–100 m wavelength band (3–30 MHz frequency band), which is consistent with priorities identified in the Astrophysics decadal survey. We describe LCRT's science objectives and the key technology challenges that need to be overcome to make this concept a reality. We envisage that LCRT will open a new window for humanity's exploration of the Universe.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129851473","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"NewSpace NewManufacturing - Injection Molding of Satellite Structures","authors":"A. Czechowicz, Farangis Razaei, A. Bach, F. Schummer, Zeyu Zhu, M. Langer","doi":"10.1109/AERO50100.2021.9438309","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438309","url":null,"abstract":"Standardizing the interface between satellites and rockets lead to a sizeable rise in the number of launched and operational small satellites over the past two decades. By giving severe limits for the outer dimensions of satellites, the CubeSat Standard also brought a paradigm change in the development of satellite subsystems. As volume, available mass and available areas for solar cells became variables with fixed upper limits, manufacturing whole subsystems as commercial off-the-shelf became a viable option, as they fit most CubeSat missions. However, it did not lead to a change to mass production technologies yet. We propose the first mass-producible satellite structure, designed for injection molding based on the high-performance polymer polyether ether keton, better known as PEEK. PEEK is a traditional material for gliding surfaces and structural parts of spacecraft. Advances in injection molding already enabled mass-manufacturing with PEEK for medical devices and the automotive industry, which shall now be transferred to space applications. PEEK materials come with a wide range of expansion coefficients, including the range of aerospace aluminum, hence fulfilling all requirements for a CubeSat structure. The structure is designed to give the designers a maximum of flexibility, while ensuring a fast and simple integration. It already includes the prescribed inhibit-switches and necessary electronics. The simplicity of the integral design ensures a safe and reliable operation. Further advantages are the comparably low price, prototypes molded from any other polymers, including economic polymers for integration testing and show pieces, and the ability to produce high volumes of the structure on short notice. This paper describes the first prototype of the structure itself (sized to 1U), its mechanical interfaces and integration strategies for spacecraft using the structure. It details challenges in the design for injection molding as well as the material selection. It goes on with results and lessons learned from integration testing with the first prototypes of the structure and a PC/104 based electronics stack as well as back-plane-based electronics stacks. The injection molding tool and process are presented as well. The paper concludes with an outlook on the strategy for acceptance in the CubeSat Standard and our future work.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"82 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130254957","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Natural Motion-based Trajectories for Automatic Spacecraft Collision Avoidance During Proximity Operations","authors":"Mark L. Mote, Christopher W. Hays, Alexander Collins, E. Feron, Kerianne L. Hobbs","doi":"10.1109/AERO50100.2021.9438434","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438434","url":null,"abstract":"Autonomous rendezvous, proximity operations, and docking are key enablers of missions such as satellite servicing, active debris removal, and in-space assembly. However, errors in the control and estimation systems, or failures to account for off-nominal conditions may result in catastrophic collisions between spacecraft. Safety may potentially be preserved in these cases by switching to a safety-driven backup system. This paper develops such a system, with guidance, control, and estimation schemes designed to safely place an active chaser spacecraft in a parking orbit around a passive target spacecraft. Natural motion trajectories are considered to identify a set of passively safe parking orbits under Clohessy-Wiltshire-Hill dynamics, and a mixed integer programming formulation is developed to find the optimal transfer trajectories to this set. The practicality of the estimation and control schemes is demonstrated though simulated case studies. The guidance algorithm is integrated into a run time assurance framework, which allows real-time enforcement of the safety constraints in a least-intrusive fashion.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129455230","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Architecture Considerations for Crewed Lunar Surface Expeditionary Utility Lander Systems","authors":"Timothy Anderson","doi":"10.1109/AERO50100.2021.9438196","DOIUrl":"https://doi.org/10.1109/AERO50100.2021.9438196","url":null,"abstract":"This study introduces a crewed landing craft for missions to celestial bodies with little to no atmosphere. The design is the result of analysis on the future of lunar surface operations, logistics, and the concept of operations involving lunar hopper vehicles. The proposed system can deploy equipment and conduct operations while sustaining a crew of ten people for up to 120 days. The vehicle launches as a payload from the SpaceX Starship. The design's function and simplicity enable high volume production while meeting the rigorous technical and quality standards for human spaceflight. The study provides top-down analysis of the design requirements and tracks the fulfillment of those requirements. The architecture analysis reviews commercial, military, and scientific expeditionary logistics functions and outlines the appropriate parallel requirements for lunar surface operations. Primary spacecraft design requirements are derived and extrapolated from NASA's NextSTEP-2 Appendix H: Human Lander System and other proven flight systems. Results from a survey of requirements from end users specializing in mining, excavation, and in-situ resource utilization are presented and the results incorporated into the design. Among the proposed solutions are arguments for designing for multiple fuel types to be used by a single propulsion system, expanding the CubeSat standard for facilitating physical interfaces between systems within a spacecraft. The study concludes with the final design proposal and a way ahead to deliver a spacecraft capable of responding to national initiatives for lunar surface exploration, innovation, and utilization. The result is a relatively low-cost system capable of entering production today for use by government customers and private industry, especially the mining, excavation, and construction industries.","PeriodicalId":379828,"journal":{"name":"2021 IEEE Aerospace Conference (50100)","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124977658","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}