An abridged version of my Capstone project for my Systems Engineering Masters Degree program. Presented at AIAA OC ASAT in April 2016. (Virtually the same as my INCOSE RMC presentation.)
KGrothe Capstone Project Final PresentationKaren Grothe
This document proposes a conceptual CubeSat mission to Mercury to gather science data at the planet's poles using a systems engineering process. It provides background on CubeSats and NASA's interest in smaller planetary missions. It describes the mission objectives, stakeholders, timeline, requirements, alternative architectures, and concept of operations. It also discusses key considerations for the payload, electrical power, communications, attitude control, and thermal subsystems. The goal is to demonstrate CubeSats can perform planetary exploration in a more timely and cost-effective way.
Flying to Jupiter with OSGi - Tony Walsh (ESA) & Hristo Indzhov (Telespazio V...mfrancis
OSGi Community Event 2018 Presentation by Tony Walsh (ESA) & Hristo Indzhov (Telespazio Vega)
Abstract: The European Space Operations Centre (ESOC) is the main operations center for the European Space Agency (ESA), operating a number of earth observation and scientific missions. Monitoring and control functions needed by spacecraft operators are provided by software systems which are reused across missions, but tailored and extended for mission specific needs. The current generation of monitoring and control systems are becoming obsolete and a European wide initiative called the European Ground Systems Common Core (EGS-CC) (http://www.egscc.esa.int) has been started to develop the next generation.
This talk will explain why OSGi was chosen and how it is used in the development of next generation of monitoring and control software. It will describe how OSGi provides the necessary framework that enables the software to be extended for the different space systems it is expected to support. The overall software architecture will be discussed, some of the challenges faced and the benefits gained by using OSGi. The first target mission for the system is JUICE (http://sci.esa.int/juice) which will explore the moons of Jupiter and which is scheduled for launch in 2022.
A COMMUNICATIONS AND PNT INTEGRATED NETWORK INFRASTRUCTURE FOR THE MOON VILLAGEMarco Lisi
This document discusses proposals for establishing a communications and navigation network to support human and robotic exploration of the Moon. It summarizes past ESA studies on using GPS and developing lunar navigation and communication satellites. It then proposes a modular, expandable approach using commercial off-the-shelf (COTS) technologies like LTE and the forthcoming 5G standard. This COTS-based lunar network would provide reliable communication and navigation services to support colonization of the Moon and Mars through permanent base stations. It would satisfy requirements for performance, reliability, affordability and sustainability by leveraging commercial technologies and allowing incremental expansion over time.
This document discusses progress toward enabling lower-cost interplanetary CubeSat missions. It describes six technology challenges (environment, communications, propulsion, navigation, instruments, and maximizing downlink data) and provides examples like asteroid mineral mapping and a solar system escape mission. Updates are given on relevant conferences and publications. Technology areas like components, power, longevity, configurations, communications, propulsion, and navigation are summarized. Roadmaps show expected improvements over time that could increase payload power and data rates while extending mission life. The document aims to outline approaches for opening the solar system to more affordable exploration using small satellites.
KGrothe Capstone Project Final PresentationKaren Grothe
This document proposes a conceptual CubeSat mission to Mercury to gather science data at the planet's poles using a systems engineering process. It provides background on CubeSats and NASA's interest in smaller planetary missions. It describes the mission objectives, stakeholders, timeline, requirements, alternative architectures, and concept of operations. It also discusses key considerations for the payload, electrical power, communications, attitude control, and thermal subsystems. The goal is to demonstrate CubeSats can perform planetary exploration in a more timely and cost-effective way.
Flying to Jupiter with OSGi - Tony Walsh (ESA) & Hristo Indzhov (Telespazio V...mfrancis
OSGi Community Event 2018 Presentation by Tony Walsh (ESA) & Hristo Indzhov (Telespazio Vega)
Abstract: The European Space Operations Centre (ESOC) is the main operations center for the European Space Agency (ESA), operating a number of earth observation and scientific missions. Monitoring and control functions needed by spacecraft operators are provided by software systems which are reused across missions, but tailored and extended for mission specific needs. The current generation of monitoring and control systems are becoming obsolete and a European wide initiative called the European Ground Systems Common Core (EGS-CC) (http://www.egscc.esa.int) has been started to develop the next generation.
This talk will explain why OSGi was chosen and how it is used in the development of next generation of monitoring and control software. It will describe how OSGi provides the necessary framework that enables the software to be extended for the different space systems it is expected to support. The overall software architecture will be discussed, some of the challenges faced and the benefits gained by using OSGi. The first target mission for the system is JUICE (http://sci.esa.int/juice) which will explore the moons of Jupiter and which is scheduled for launch in 2022.
A COMMUNICATIONS AND PNT INTEGRATED NETWORK INFRASTRUCTURE FOR THE MOON VILLAGEMarco Lisi
This document discusses proposals for establishing a communications and navigation network to support human and robotic exploration of the Moon. It summarizes past ESA studies on using GPS and developing lunar navigation and communication satellites. It then proposes a modular, expandable approach using commercial off-the-shelf (COTS) technologies like LTE and the forthcoming 5G standard. This COTS-based lunar network would provide reliable communication and navigation services to support colonization of the Moon and Mars through permanent base stations. It would satisfy requirements for performance, reliability, affordability and sustainability by leveraging commercial technologies and allowing incremental expansion over time.
This document discusses progress toward enabling lower-cost interplanetary CubeSat missions. It describes six technology challenges (environment, communications, propulsion, navigation, instruments, and maximizing downlink data) and provides examples like asteroid mineral mapping and a solar system escape mission. Updates are given on relevant conferences and publications. Technology areas like components, power, longevity, configurations, communications, propulsion, and navigation are summarized. Roadmaps show expected improvements over time that could increase payload power and data rates while extending mission life. The document aims to outline approaches for opening the solar system to more affordable exploration using small satellites.
The document proposes developing a lunar hopper vehicle powered by a nuclear thermal rocket engine. It would take off and land repeatedly to gather soil samples from multiple locations on the moon's surface. An optimization problem is set up in MATLAB to determine the ideal dry mass and mass ratio to maximize the number of landing sites visited. The analysis finds that a design using a SNRE (Small Nuclear Reactor Engine) with a 3500 kg dry mass could achieve up to 28 sample retrievals from sites 5 km apart. A conceptual design of the vehicle is then presented, including subsystem mass budgets and dimensioned drawings. Future work areas are identified to further develop the design.
This summary describes a study conducted to design a 6U CubeSat mission to Phobos. The biggest challenges were fitting all required components within the small volume constraints. Deployable solar arrays, antenna, and a propulsion system were needed. Through several design revisions adjusting subsystem dimensions and orientations, the team was able to fit all necessary components within the 6U volume. The completed design met all requirements and could be used in a proposal for mission funding.
Time, Change and Habits in Geospatial-Temporal Information StandardsGeorge Percivall
Keynote for HIC 2014 – 11th International Conference on Hydroinformatics, New York, USA August 17 – 21, 2014
Time, Change and Habits in Geospatial-Temporal Information Standards
Time and change are fundamental to our scientific understanding of the world. Standards for geospatial-temporal information exist but new needs outstrip current standards. Geospatial-temporal information includes capturing change in features and coverages and modeling the processes that inform change. Key standards for time, calendars, and temporal reference systems are in place. Time series modeling from the WaterML standard is a recent advance of high value to hydrology. The OGC Moving Features standard will establish an encoding format for changes in “rigid” features. Interoperability standards are needed for Coverages with values that change based on observations, analytical expressions, or simulations. Applying a coverage model to time-varying, fluid Earth systems was the topic of the ground breaking GALEON Interoperability Experiment. Standards developments for spatial-temporal process models is progressing with WPS, OpenMI and ESMF - supporting a Model Web concept. A robust framework for sharing geospatial-temporal information is now coming into place based on developments captured in standards by ISO, WMO, ITU, ICSU and OGC - including the newly established OGC Temporal domain working group. The new framework will enable capabilities in expressing and sharing scientific investigations including research on the emergence of forms over time. With these new capabilities we may come to understand Peirce’s observation that over time “all things have a tendency to take habits.”
The document discusses using high-temperature superconductors (HTS) to enable electromagnetic deployment and support structures for spacecraft. It outlines previous NIAC studies on applications of superconductors and magnetic fields in space. The study aims to determine if HTS coils can be used to deploy, unfold and support spacecraft structures electromagnetically. This could enable larger, simpler and reconfigurable spacecraft with performance benefits like reduced mass and vibration isolation. Initial modeling shows the basic concept is feasible and example structures are being designed to further evaluate potential functions and impacts.
The document describes a competition called the Global Trajectory Optimization Competition (GTOC) to design interplanetary trajectories. The 6th edition of GTOC posed the problem of designing a trajectory to map as many faces of Jupiter's four Galilean moons (Io, Europa, Ganymede, Callisto) as possible with a spacecraft. The author's team used an evolutionary algorithm-based approach to optimize moon flyby sequences and trajectory arcs, running over 500 million evolutionary simulations in parallel. Their best trajectory mapped 120 moon faces out of 128 and scored 316 points, exceeding the competition winner's score of 311 points and solving a problem acknowledged as very difficult in trajectory design for solar system exploration.
A coupled Electromagnetic-Mechanical analysis of next generation Radio Telesc...Altair
This work considers the design of large and complex receivers used in the field of radio astronomy, e.g. for the Square Kilometer Array (SKA) project. The purpose of this work is to consider a coupled simulation where the electromagnetic analysis, performed with the computational electromagnetic software package FEKO, is enhanced by the structural analysis offered by HyperWorks products such as HyperMesh and Optistruct. External influences such as gravity, wind-loading and thermal properties will be taken into account. This will enhance the electromagnetic simulation results, thereby aiding designers to mitigate these environmental effects.
Speakers
Dr. Danie Ludick, Postdoctoral researcher, Stellenbosch University
The document summarizes the capabilities and scientific goals of MeerKAT, a new radio telescope located in South Africa. It notes that the first phase (Array Release 1) of MeerKAT, consisting of 16 antennas, produced an image showing over 1300 galaxies in a small patch of sky, compared to only 70 known previously. MeerKAT will ultimately consist of 64 antennas and be the most sensitive radio telescope in Africa. It is a precursor to the larger Square Kilometre Array project and will be used to conduct large surveys on pulsars, neutral hydrogen, and transient radio sources to advance understanding of astronomy and physics.
NOAA does an excellent job of generating an disseminating data to meet the primary mission of Preservation of Life and Property. There is an unrealized opportunity to exploit the data for research and profit. Much of the data is hidden deep in archives with community specific portals for access. Modern technologies allow new methods to expose more data to wider audiences in order to stimulate innovation and discovery. NOAA is currently experimenting with cloud
technologies through the big data partnership by making high value data sets such as GOES East available on the cloud through cloud provider partners. Specifically: 1. To understand and predict changes in climate, weather, oceans and coasts; 2. To share that knowledge and information with others; and 3. To conserve and manage coastal and marine ecosystems and resources. There is an unrealized opportunity to exploit NOAA?s vast data holdings for research and profit. Much of the data is hidden deep in archives with community specific portals for access. Modern technologies allow new methods to expose more data to wider audiences in order to stimulate innovation and discovery. NOAA is currently experimenting with cloud technologies through the big data partnership by making high value data sets such as GOES East available on the cloud through the partners.
1. The document discusses using AI planning techniques like deep reinforcement learning to optimize image collection for mapping small celestial bodies.
2. Benchmark tests on asteroid models show the AI approach can decrease data collection while increasing mapping quality and speeding up the mapping process compared to current methods.
3. Additional validation tests demonstrate the AI approach is robust to uncertainties and can generalize to unseen celestial bodies, achieving near ideal mapping results with fewer images than other techniques.
This document provides a preliminary study for the AROSAT satellite system. It discusses several key requirements including coverage area, resolution capabilities, duty cycle, onboard storage and download rates. It evaluates three potential spacecraft configurations and their impact on drag, solar array effectiveness and risk. Configuration #2 is preferred as it minimizes drag while having a simple solar array design. The document also examines how spacecraft altitude affects optical instrument parameters and the propulsion systems needed to compensate for atmospheric drag at different altitudes. Electric propulsion is recommended to enable lower orbits. Overall architectures are proposed for Configuration #2 that could meet requirements.
ESCAPE Kick-off meeting - KM3Net, Opening a new window on our universe (Feb 2...ESCAPE EU
KM3NeT is a neutrino research infrastructure located in the deep Mediterranean Sea consisting of two detectors, ORCA and ARCA. The document discusses KM3NeT's physics motivations in studying neutrino oscillations, supernovae, dark matter, and cosmic neutrinos. It describes the detector design using optical sensors on vertical strings to detect Cherenkov radiation from neutrinos. A phased construction approach is outlined. The large data volumes require advanced data management, including processing, storage, and open access policies following FAIR principles. Participation in ESCAPE could help address KM3NeT's computing and data challenges for its lifetime scale.
AI models for Ice Classification - ExtremeEarth Open WorkshopExtremeEarth
(1) Deep learning algorithms show potential for sea ice classification from SAR images but face challenges from scarce and inaccurate training data.
(2) Researchers generated training datasets by manually labeling SAR image patches with ice types, assisted by optical images.
(3) A modified VGG-16 network trained on augmented SAR patch data achieved 97.3% accuracy classifying ice vs water.
This document describes a satellite tracking system that uses a microcontroller to track a satellite's position and correct its orbit if it drifts from its intended path. The system includes an orbital correction engine that calculates needed adjustments and a tracking processor that monitors the satellite's position over time to detect any deviations. It sends the satellite's location data to an earth station via an RS-232 interface. The microcontroller compares the data to an orbital database and determines corrections to guide the satellite back to its proper orbit. A visual basics program is used to model and simulate the satellite's movement and drift.
RISAT-2 is India's first heavy satellite with synthetic aperture radar, allowing all-weather, day-night monitoring. It was launched in 2009 to enhance India's earth observation capabilities, especially for disaster management. Potential applications include tracking hostile ships. RISAT-2 was used to search for wreckage from a helicopter crash in dense jungle that killed the Chief Minister of Andhra Pradesh.
Polar Use Case - ExtremeEarth Open WorkshopExtremeEarth
This document provides an overview of an ExtremeEarth project that aims to apply deep learning techniques to classify sea ice in polar regions using satellite imagery. The project has received funding from the European Union. It discusses challenges in classifying sea ice from SAR imagery compared to optical imagery. It outlines user requirements for sea ice products, including high resolution (300m or better) and frequent updates (near real-time). The document describes workflows using the Polar Thematic Exploitation Platform (Polar TEP) for large-scale sea ice mapping using Copernicus satellite data and machine learning algorithms. It also discusses exploitation of results, including the impact of Polar TEP and efforts to facilitate the polar machine learning community.
Big Linked Data Querying - ExtremeEarth Open WorkshopExtremeEarth
This document discusses querying large geospatial datasets using the Strabo2 system. Strabo2 performs GeoSPARQL query answering on massive RDF graphs containing geospatial data from Copernicus and other sources. It relies on Apache Sedona to perform distributed spatial analytics on Apache Spark. Strabo2 uses techniques like vertical data partitioning, caching of spatial relations and query results, and persistent spatial indexing to improve query performance on large datasets. It has been deployed on the CREODIAS platform to enable spatial analytics on datasets for polar and food security use cases.
The document discusses GEO Grid's activities during the 2011 Tohoku earthquake and tsunami in Japan, including providing satellite imagery, hazard maps, and geological data through online portals and services. It describes how GEO Grid established a disaster task force to process and deliver satellite data from NASA, JAXA, and other sources to support response and recovery efforts. Key services and data included satellite imagery of damage areas from ASTER, crustal deformation maps from PALSAR interferometry, and shaking maps from the QuiQuake system.
This document discusses building 3rd generation AI inspired by insect brains. Researchers at the University of Sussex are working on projects to build smarter robots by modeling the brain and learning abilities of bees. The projects combine neuroscience, robotics, and AI to decipher the "brain algorithms" of insects like bees and ants. They are using neural simulations, novel lightweight robots, and machine learning on specialized hardware like GPUs. The goal is to understand how small insect brains can efficiently navigate and learn routes despite having few neurons and low visual resolution. Researchers hope to learn tricks from insects to build AI that learns routes through familiarity rather than precise recognition. They are testing models where neural networks learn to associate views with actions instead of locations.
1) NREL is a national laboratory operated by the Alliance for Sustainable Energy, LLC that focuses on energy efficiency and renewable energy.
2) The presentation discusses options for quantifying solar resource from measurements including horizontal and inclined surfaces, and methods for transposing horizontal irradiance data to plane of array irradiance.
3) It notes that isotropic models used to approximate this transposition can underestimate plane of array irradiance by 5-20% compared to using anisotropic physics models that better simulate cloud conditions and solar radiances.
The document outlines NASA's vision and plans for space exploration, including returning humans to the Moon by 2020 and eventually sending humans to Mars. It discusses key elements like developing new technologies, promoting commercial participation, and major milestones. It also summarizes NASA's Exploration Systems Research and Technology program which develops new technologies and concepts through projects, demonstrations and programs to enable sustainable human exploration of the solar system.
The document discusses a concept for using repeated external acceleration from stations positioned throughout the solar system to propel probes to distances of 200 AU within 15 years. It summarizes the current study analyzing trajectories for probes accelerated by single and dual stations in Earth and Jupiter orbits. The document also reviews potential station and probe configurations that could enable such an ambitious interstellar exploration architecture.
The document proposes developing a lunar hopper vehicle powered by a nuclear thermal rocket engine. It would take off and land repeatedly to gather soil samples from multiple locations on the moon's surface. An optimization problem is set up in MATLAB to determine the ideal dry mass and mass ratio to maximize the number of landing sites visited. The analysis finds that a design using a SNRE (Small Nuclear Reactor Engine) with a 3500 kg dry mass could achieve up to 28 sample retrievals from sites 5 km apart. A conceptual design of the vehicle is then presented, including subsystem mass budgets and dimensioned drawings. Future work areas are identified to further develop the design.
This summary describes a study conducted to design a 6U CubeSat mission to Phobos. The biggest challenges were fitting all required components within the small volume constraints. Deployable solar arrays, antenna, and a propulsion system were needed. Through several design revisions adjusting subsystem dimensions and orientations, the team was able to fit all necessary components within the 6U volume. The completed design met all requirements and could be used in a proposal for mission funding.
Time, Change and Habits in Geospatial-Temporal Information StandardsGeorge Percivall
Keynote for HIC 2014 – 11th International Conference on Hydroinformatics, New York, USA August 17 – 21, 2014
Time, Change and Habits in Geospatial-Temporal Information Standards
Time and change are fundamental to our scientific understanding of the world. Standards for geospatial-temporal information exist but new needs outstrip current standards. Geospatial-temporal information includes capturing change in features and coverages and modeling the processes that inform change. Key standards for time, calendars, and temporal reference systems are in place. Time series modeling from the WaterML standard is a recent advance of high value to hydrology. The OGC Moving Features standard will establish an encoding format for changes in “rigid” features. Interoperability standards are needed for Coverages with values that change based on observations, analytical expressions, or simulations. Applying a coverage model to time-varying, fluid Earth systems was the topic of the ground breaking GALEON Interoperability Experiment. Standards developments for spatial-temporal process models is progressing with WPS, OpenMI and ESMF - supporting a Model Web concept. A robust framework for sharing geospatial-temporal information is now coming into place based on developments captured in standards by ISO, WMO, ITU, ICSU and OGC - including the newly established OGC Temporal domain working group. The new framework will enable capabilities in expressing and sharing scientific investigations including research on the emergence of forms over time. With these new capabilities we may come to understand Peirce’s observation that over time “all things have a tendency to take habits.”
The document discusses using high-temperature superconductors (HTS) to enable electromagnetic deployment and support structures for spacecraft. It outlines previous NIAC studies on applications of superconductors and magnetic fields in space. The study aims to determine if HTS coils can be used to deploy, unfold and support spacecraft structures electromagnetically. This could enable larger, simpler and reconfigurable spacecraft with performance benefits like reduced mass and vibration isolation. Initial modeling shows the basic concept is feasible and example structures are being designed to further evaluate potential functions and impacts.
The document describes a competition called the Global Trajectory Optimization Competition (GTOC) to design interplanetary trajectories. The 6th edition of GTOC posed the problem of designing a trajectory to map as many faces of Jupiter's four Galilean moons (Io, Europa, Ganymede, Callisto) as possible with a spacecraft. The author's team used an evolutionary algorithm-based approach to optimize moon flyby sequences and trajectory arcs, running over 500 million evolutionary simulations in parallel. Their best trajectory mapped 120 moon faces out of 128 and scored 316 points, exceeding the competition winner's score of 311 points and solving a problem acknowledged as very difficult in trajectory design for solar system exploration.
A coupled Electromagnetic-Mechanical analysis of next generation Radio Telesc...Altair
This work considers the design of large and complex receivers used in the field of radio astronomy, e.g. for the Square Kilometer Array (SKA) project. The purpose of this work is to consider a coupled simulation where the electromagnetic analysis, performed with the computational electromagnetic software package FEKO, is enhanced by the structural analysis offered by HyperWorks products such as HyperMesh and Optistruct. External influences such as gravity, wind-loading and thermal properties will be taken into account. This will enhance the electromagnetic simulation results, thereby aiding designers to mitigate these environmental effects.
Speakers
Dr. Danie Ludick, Postdoctoral researcher, Stellenbosch University
The document summarizes the capabilities and scientific goals of MeerKAT, a new radio telescope located in South Africa. It notes that the first phase (Array Release 1) of MeerKAT, consisting of 16 antennas, produced an image showing over 1300 galaxies in a small patch of sky, compared to only 70 known previously. MeerKAT will ultimately consist of 64 antennas and be the most sensitive radio telescope in Africa. It is a precursor to the larger Square Kilometre Array project and will be used to conduct large surveys on pulsars, neutral hydrogen, and transient radio sources to advance understanding of astronomy and physics.
NOAA does an excellent job of generating an disseminating data to meet the primary mission of Preservation of Life and Property. There is an unrealized opportunity to exploit the data for research and profit. Much of the data is hidden deep in archives with community specific portals for access. Modern technologies allow new methods to expose more data to wider audiences in order to stimulate innovation and discovery. NOAA is currently experimenting with cloud
technologies through the big data partnership by making high value data sets such as GOES East available on the cloud through cloud provider partners. Specifically: 1. To understand and predict changes in climate, weather, oceans and coasts; 2. To share that knowledge and information with others; and 3. To conserve and manage coastal and marine ecosystems and resources. There is an unrealized opportunity to exploit NOAA?s vast data holdings for research and profit. Much of the data is hidden deep in archives with community specific portals for access. Modern technologies allow new methods to expose more data to wider audiences in order to stimulate innovation and discovery. NOAA is currently experimenting with cloud technologies through the big data partnership by making high value data sets such as GOES East available on the cloud through the partners.
1. The document discusses using AI planning techniques like deep reinforcement learning to optimize image collection for mapping small celestial bodies.
2. Benchmark tests on asteroid models show the AI approach can decrease data collection while increasing mapping quality and speeding up the mapping process compared to current methods.
3. Additional validation tests demonstrate the AI approach is robust to uncertainties and can generalize to unseen celestial bodies, achieving near ideal mapping results with fewer images than other techniques.
This document provides a preliminary study for the AROSAT satellite system. It discusses several key requirements including coverage area, resolution capabilities, duty cycle, onboard storage and download rates. It evaluates three potential spacecraft configurations and their impact on drag, solar array effectiveness and risk. Configuration #2 is preferred as it minimizes drag while having a simple solar array design. The document also examines how spacecraft altitude affects optical instrument parameters and the propulsion systems needed to compensate for atmospheric drag at different altitudes. Electric propulsion is recommended to enable lower orbits. Overall architectures are proposed for Configuration #2 that could meet requirements.
ESCAPE Kick-off meeting - KM3Net, Opening a new window on our universe (Feb 2...ESCAPE EU
KM3NeT is a neutrino research infrastructure located in the deep Mediterranean Sea consisting of two detectors, ORCA and ARCA. The document discusses KM3NeT's physics motivations in studying neutrino oscillations, supernovae, dark matter, and cosmic neutrinos. It describes the detector design using optical sensors on vertical strings to detect Cherenkov radiation from neutrinos. A phased construction approach is outlined. The large data volumes require advanced data management, including processing, storage, and open access policies following FAIR principles. Participation in ESCAPE could help address KM3NeT's computing and data challenges for its lifetime scale.
AI models for Ice Classification - ExtremeEarth Open WorkshopExtremeEarth
(1) Deep learning algorithms show potential for sea ice classification from SAR images but face challenges from scarce and inaccurate training data.
(2) Researchers generated training datasets by manually labeling SAR image patches with ice types, assisted by optical images.
(3) A modified VGG-16 network trained on augmented SAR patch data achieved 97.3% accuracy classifying ice vs water.
This document describes a satellite tracking system that uses a microcontroller to track a satellite's position and correct its orbit if it drifts from its intended path. The system includes an orbital correction engine that calculates needed adjustments and a tracking processor that monitors the satellite's position over time to detect any deviations. It sends the satellite's location data to an earth station via an RS-232 interface. The microcontroller compares the data to an orbital database and determines corrections to guide the satellite back to its proper orbit. A visual basics program is used to model and simulate the satellite's movement and drift.
RISAT-2 is India's first heavy satellite with synthetic aperture radar, allowing all-weather, day-night monitoring. It was launched in 2009 to enhance India's earth observation capabilities, especially for disaster management. Potential applications include tracking hostile ships. RISAT-2 was used to search for wreckage from a helicopter crash in dense jungle that killed the Chief Minister of Andhra Pradesh.
Polar Use Case - ExtremeEarth Open WorkshopExtremeEarth
This document provides an overview of an ExtremeEarth project that aims to apply deep learning techniques to classify sea ice in polar regions using satellite imagery. The project has received funding from the European Union. It discusses challenges in classifying sea ice from SAR imagery compared to optical imagery. It outlines user requirements for sea ice products, including high resolution (300m or better) and frequent updates (near real-time). The document describes workflows using the Polar Thematic Exploitation Platform (Polar TEP) for large-scale sea ice mapping using Copernicus satellite data and machine learning algorithms. It also discusses exploitation of results, including the impact of Polar TEP and efforts to facilitate the polar machine learning community.
Big Linked Data Querying - ExtremeEarth Open WorkshopExtremeEarth
This document discusses querying large geospatial datasets using the Strabo2 system. Strabo2 performs GeoSPARQL query answering on massive RDF graphs containing geospatial data from Copernicus and other sources. It relies on Apache Sedona to perform distributed spatial analytics on Apache Spark. Strabo2 uses techniques like vertical data partitioning, caching of spatial relations and query results, and persistent spatial indexing to improve query performance on large datasets. It has been deployed on the CREODIAS platform to enable spatial analytics on datasets for polar and food security use cases.
The document discusses GEO Grid's activities during the 2011 Tohoku earthquake and tsunami in Japan, including providing satellite imagery, hazard maps, and geological data through online portals and services. It describes how GEO Grid established a disaster task force to process and deliver satellite data from NASA, JAXA, and other sources to support response and recovery efforts. Key services and data included satellite imagery of damage areas from ASTER, crustal deformation maps from PALSAR interferometry, and shaking maps from the QuiQuake system.
This document discusses building 3rd generation AI inspired by insect brains. Researchers at the University of Sussex are working on projects to build smarter robots by modeling the brain and learning abilities of bees. The projects combine neuroscience, robotics, and AI to decipher the "brain algorithms" of insects like bees and ants. They are using neural simulations, novel lightweight robots, and machine learning on specialized hardware like GPUs. The goal is to understand how small insect brains can efficiently navigate and learn routes despite having few neurons and low visual resolution. Researchers hope to learn tricks from insects to build AI that learns routes through familiarity rather than precise recognition. They are testing models where neural networks learn to associate views with actions instead of locations.
1) NREL is a national laboratory operated by the Alliance for Sustainable Energy, LLC that focuses on energy efficiency and renewable energy.
2) The presentation discusses options for quantifying solar resource from measurements including horizontal and inclined surfaces, and methods for transposing horizontal irradiance data to plane of array irradiance.
3) It notes that isotropic models used to approximate this transposition can underestimate plane of array irradiance by 5-20% compared to using anisotropic physics models that better simulate cloud conditions and solar radiances.
The document outlines NASA's vision and plans for space exploration, including returning humans to the Moon by 2020 and eventually sending humans to Mars. It discusses key elements like developing new technologies, promoting commercial participation, and major milestones. It also summarizes NASA's Exploration Systems Research and Technology program which develops new technologies and concepts through projects, demonstrations and programs to enable sustainable human exploration of the solar system.
The document discusses a concept for using repeated external acceleration from stations positioned throughout the solar system to propel probes to distances of 200 AU within 15 years. It summarizes the current study analyzing trajectories for probes accelerated by single and dual stations in Earth and Jupiter orbits. The document also reviews potential station and probe configurations that could enable such an ambitious interstellar exploration architecture.
This document discusses various applications of microsatellites including expanding access to space for countries, conducting science experiments in orbit related to biology and atmospheric research, demonstrating new technologies, supporting education through university and high school satellite projects, enabling private imaging satellites, and allowing amateur satellite projects. The future applications discussed include using microsatellites as auxiliary payloads on interplanetary missions and as constellations. The conclusion predicts that 2,000-2,750 nano/microsatellites will require launches between 2014-2020 based on a market assessment.
The document summarizes the University of Colorado's CU-E3 cube satellite project, which aims to demonstrate the effectiveness of a new communications concept for cube satellites using a reflectarray. The author, an undergraduate apprentice, is working on designing and building a fixture to measure the cube satellite's center of gravity. Key accomplishments so far include completing the center of gravity fixture design, machining components, and interfacing with load cells. Upcoming work includes building and testing the fixture over winter break in preparation for the spring semester.
The document presents a final presentation for a CubISSat project studying a multipurpose CubeSat demonstrator at the International Space Station (ISS). It identifies four potential CubeSat missions: ISS inspection, hosting scientific payloads, retrieving small target objects, and inspecting a future cis-lunar habitat. The presentation covers mission scenarios and required capabilities, a technology database, conceptual design considerations, and subsystem requirements for a CubeSat inspector demonstrator mission to validate technologies for ISS inspection and surveillance.
NASA is embarking on a new human space exploration program focused on developing technologies to enable human exploration of multiple destinations in the solar system including the Moon, asteroids, Lagrange points, and Mars. Key aspects of the new program include heavy-lift and propulsion technology development, precursor robotic missions, commercial human spaceflight, and human research. The President's FY2011 budget provides $6 billion additional funding over 5 years for NASA to support this new exploration strategy and technology development approach.
WE2.L10 - NASA's Evolving Approaches to Maximizing Applications Return from o...grssieee
1. NASA is working to maximize the societal benefits and applications return from its Earth observing satellites by focusing more on applications and engaging users early in the design process.
2. NASA conducts applications workshops for individual missions and holds cross-agency workshops to understand user needs and develop partnerships to enable applications of satellite data.
3. NASA is working to transition from focusing solely on science requirements to also considering capabilities for applications through adjustments to satellite design and partnerships with other agencies and users.
The document discusses the role of science and operations in developing the James Webb Space Telescope mission. It describes the science goals that JWST aims to address, including detecting the first galaxies and studying star and planet formation. It outlines the key instruments onboard and discusses how STScI will manage science operations and the ground system once JWST is launched. STScI has been influencing mission development to help achieve the science objectives through activities like simulations, requirements development, and system trades.
The document discusses the role of science and operations in developing the James Webb Space Telescope mission. It describes the science goals that JWST aims to address, including detecting the first galaxies and studying star and planet formation. It outlines the key instruments onboard and discusses how STScI will manage science operations and the ground system. STScI has provided input during development to optimize science return and operations efficiency. Challenges include balancing momentum management with stray light avoidance and ensuring sufficient early funding.
The document discusses the role of science and operations in developing the James Webb Space Telescope mission. It describes the science goals that JWST aims to address, including detecting the first galaxies and studying star and planet formation. It outlines the key instruments onboard and discusses how STScI will manage science operations and the ground system. STScI has provided input during development to optimize science return and operations efficiency. Challenges include balancing momentum management with stray light avoidance and ensuring sufficient early funding.
The document discusses the role of science and operations in developing the James Webb Space Telescope mission. It describes the science goals that JWST aims to address, including detecting the first galaxies and studying star and planet formation. It outlines the key instruments onboard and discusses how STScI will manage science operations and the ground system once JWST is launched. STScI has been influencing mission development to help achieve the science objectives through activities like simulations, requirements development, and system trades.
Mars CubeSat Telecom Relay Constellation_JPL FinalRohan Deshmukh
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The document outlines the BIRDS (Joint Global Multi-Nation Birds) project, which aims to build and launch a constellation of 1U CubeSats from five countries including Mongolia and Japan. The project will provide hands-on engineering experience for students and help non-space faring countries enter the space field. It details the satellite design, integration and testing process, ground station setup, operations plan and timeline, with a total cost of around $100,000 USD per satellite.
For the full video of this presentation, please visit: https://www.edge-ai-vision.com/2023/10/a-computer-vision-system-for-autonomous-satellite-maneuvering-a-presentation-from-scout-space/
Andrew Harris, Spacecraft Systems Engineer at SCOUT Space, presents the “Developing a Computer Vision System for Autonomous Satellite Maneuvering” tutorial at the May 2023 Embedded Vision Summit.
Computer vision systems for mobile autonomous machines experience a wide variety of real-world conditions and inputs that can be challenging to capture accurately in training datasets. Few autonomous systems experience more challenging conditions than those in orbit. In this talk, Harris describes how SCOUT Space has designed and trained satellite vision systems using dynamic and physically informed synthetic image datasets.
Harris describes how his company generates synthetic data for this challenging environment and how it leverages new real-world data to improve our datasets. In particular, he explains how these synthetic datasets account for and can replicate real sources of noise and error in the orbital environment, and how his company supplements them with in-space data from the first SCOUT-Vision system, which has been in orbit since 2021.
This document provides a summary of a systems engineering update presentation given to the International Council on Systems Engineering Colorado Front Range Chapter. It discusses:
1) The evolution of systems engineering from early space programs like Sputnik and Mercury through modern programs like the International Space Station.
2) An example case study of the Wake Shield Facility and the systems engineering approaches used in its development.
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EarthCube Monthly Community Webinar- Nov. 22, 2013EarthCube
This webinar features project overviews of all EarthCube Awards (Building Blocks, Research Coordination Networks, Conceptual Designs, and Test Governance), followed by a call for involvement, and a Q&A session.
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12. C4P: Collaboration and Cyberinfrastructure for Paleogeosciences (RCN)
13. Developing a Data-Oriented Human-centric Enterprise for Architecture (CD)
14. Enterprise Architecture for Transformative Research and Collaboration (CD)
15. EC Test Enterprise Governance: An Agile Approach (Test Governance)
A Call for Involvement!
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This document summarizes the current status of a large, multi-institutional project in Japan aimed at developing a unified understanding of structure formation in the universe through multi-level simulations and observations. The project involves over 90 researchers across 21 institutions. It is divided into four sub-projects focusing on: large-scale structures and galaxy formation (Sub A); molecular clouds and planetary formation (Sub B); black holes, supernovae, and radiation transport (Sub C); and the solar system, Venus, and gas giant planets (Sub D). Several key simulations have been performed achieving unprecedented resolution, including galaxy formation at the star-by-star level, globular cluster dynamics, and a 12.8 billion point simulation of solar conve
This document announces a new Citizen science Asteroid Data, Education, and Tools (CADET) program that seeks proposals to adapt and develop asteroid data analysis software tools to make them accessible to non-professionals. Proposals will go through a two-step process, with Step-1 proposals due by June 15, 2015 and Step-2 proposals due by July 15, 2015. The program aims to develop easy-to-use software tools to analyze asteroid data and integrate them into learning environments to engage citizen scientists and the public. Proposals must include plans for agile development and user testing of the tools. Resulting software must be made publicly available as open source.
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imaging, emphasizing addressing false positives and resource efficiency.
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1. Applying the Systems Engineering Process
to a Conceptual Mercury CubeSat Mission
Author: Karen Grothe
karen@karengrothe.com
Advisor: Dr. Bohdan Oppenheim, Loyola Marymount University
Bio:
• BS in EE from Washington University in St. Louis
• Astronautical Engineering Certificate from UCLA Extension
• MS in Systems Engineering from Loyola Marymount University
• 16 years experience in aerospace as a systems engineer at McDonnell
Douglas, Boeing, and Raytheon
• Leveraging experience managing requirements and verification testing
for airborne systems into a stellar career advancing spacecraft systems.
2. Overview
• Mission objectives
• Stakeholders
• Mission timeline
• Top-level requirements
• Alternative mission
architectures
• Concept of operations
• System drivers and key
requirements
• Trade studies
• Propulsion
• Communications
• Mission utility
• Mission risks and mitigation
• Baseline mission concept
and architecture
• Proposed subsystem block
diagrams
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
24/30/2016
This project uses a systems engineering process to propose a
conceptual interplanetary CubeSat mission to gather science
data at Mercury’s poles.
3. The Decadal Survey
In 2011, the National
Academy of Sciences
released Vision and
Voyages for Planetary
Science in the Decade
2013 – 2022 outlining
science priorities for
NASA’s planetary science
missions.
4/30/2016
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
3
Image source: http://solarsystem.nasa.gov/2013decadal/
4. Space Missions Are Expensive
NASA Funding Limits the Number of Missions
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
4/30/2016 4
5. NASA’s Planned Interplanetary CubeSat
Missions
Auxiliary Payload on Europa Mission
(2020s)
MarCO
(Secondary Payload with Mars INSIGHT)
Lunar Flashlight (July 2018)
NEA Scout (July 2018)
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
4/30/2016 5
6. Methodology:
Space Mission Engineering Process
1. Define Broad (Qualitative) Objectives and Constraints
2. Define Principal Players (Stakeholders)
3. Define Program Timescale
4. Estimate Quantitative Needs, Requirements, and
Constraints
5. Identify Alternative Mission Architectures
6. Identify Alternative Mission Concepts
7. Identify Likely System Drivers and Key Requirements
8. Conduct Performance Assessments and System
Trades
9. Evaluate Mission Utility
10. Define Baseline Mission Concept and Architecture
11. Revise Quantitative Requirements and Constraints
12. Iterate and Explore Other Alternatives
13. Define System Requirements
14. Allocate Requirements to System Elements
This project covers
the first ten steps of
the 14-step Space
Mission Engineering
Process presented
in Space Mission
Engineering: The
New SMAD.
Image Source: http://www.sme-smad.com/index.asp
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 6
7. Mission Objectives and Constraints (Step 1)
Proposed Mercury CubeSat Mission Statement
After the success of the
MESSENGER spacecraft in
mapping Mercury, planetary
scientists have more questions
about Mercury, but the expense
of a large mission means that it
may be many years before
another mission to Mercury is
undertaken. The United States
needs a less expensive class
of spacecraft to perform such
planetary science in a more
timely fashion.
Credit: NASA/Johns Hopkins University Applied Physics Laboratory/Carnegie
Institution of Washington
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
4/30/2016 7
8. Mission Objectives and Constraints (Step 1)
Proposed Mercury CubeSat Mission Objectives
•Primary Objective: To
investigate the state,
extent, and chemical
compositions of surface
volatiles in the polar
regions of Mercury
•Secondary Objective: To
demonstrate the
functionality of small
spacecraft designed to the
CubeSat standard in
planetary exploration
Credit: NASA/Johns Hopkins University Applied Physics Laboratory/Carnegie
Institution of Washington/National Astronomy and Ionosphere Center, Arecibo
Observatory
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 8
9. Stakeholders (Step 2)
• NASA – Determines science objectives with NSF; manages
spacecraft development and operates spacecraft
• NSF – Determines science objectives with NASA and provides
funding for scientific investigations
• Federal Government – Provides funding for NASA and NSF
• Suppliers – Tyvek, Vacco, launch provider, etc.
• Universities – Prime Investigators (PIs) and partners with
NASA and NSF
• Scientists – End users of data returned from mission
• Community – Educators and the general public benefit from
scientific findings
• Media – Disseminates announcements from NASA, NSF,
Federal Government, Universities, and Scientists.
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 9
10. Mission Timeline (Step 3)
Phase End Defined By Duration
Typical Duration *
(Small Program)
Concept Exploration
Start of tech. funding; preliminary
requirements release 3 months 1-6 months
Detailed Development
Risk Reduction/Technology
Development Start of program funding 3 - 6 months 0 - 12 months
Detailed Design and
Development Formal requirements release 6 months 2 - 12 months
Production and Deployment
Production Ship to Launch Site 6 months 6 - 24 months
Launch Lift-Off and Arrival in LEO 1 month 1 month
On-Orbit Checkout/Transfer
to Operational Orbit Start of operations 6 years
Up to 10 years
interplanetary
Operations and Support
Operations
Spacecraft dies or decision to be
put to sleep 1+ years 1 month - 5 years
Disposal Re-entry or turn-off 0 years 0 - 5 years
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
10
* Typical Durations come from SME-SMAD [14, Table 3-3, Page 54]
4/30/2016
11. Top-Level Requirements Summary (Step 4)
1. Spacecraft payload shall be appropriate to investigate surface
volatiles in the polar regions of Mercury.
2. Spacecraft shall fit into 12U CubeSat size specification.
3. Spacecraft lifetime shall be at least 8 years.
4. Spacecraft shall be capable of communicating with Earth from
Mercury’s orbit.
5. Thermal management shall protect components from the
extreme temperatures present near Mercury.
6. Spacecraft shall be capable of providing power and fault
protection to sensor payload.
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 11
12. Alternative Mission Architectures (Step 5)
• Operational views
• OV-1: Overview
• System views
• SV-1: System Interface Description (for two
options)
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 12
13. K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
13
Space Flight
Operations Facility
Deep Space
Network
Users/CustomersPasadena, CA
Launch
Mercury CubeSat
Mission Architecture
Overview
CubeSat
Image Credit: Tomas Svitek
4/30/2016
14. Mercury CubeSat Mission
System Interface Description (Option A)
14
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016
15. Mercury CubeSat Mission
System (with Relay) Interface Description (Option B)
15
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016
16. Concept of Operations (Step 6)
Launch and Trajectory
• Launch as a
secondary payload
• Take a trajectory
similar to that of the
MESSENGER
spacecraft
• Orbit insertion at
Mercury in about 6
years Example trajectory: MESSENGER
Image source: http://messenger.jhuapl.edu/the_mission/trajectory.html
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 16
17. Mercury CubeSat Concept of Operations
(Step 6)
Mission Timeline/Schedule (The overall schedule for planning,
building, deployment, operations, replacement, and end-of-life) – 1
spacecraft developed over 2 years, launched in the earliest available
window, operates for 8 years.
Tasking, Scheduling & Control (How the system decides what to do
in the long term and short term) – Single mission operations center
Communications Architecture (How the various components of the
system talk to each other) – Space/Ground: Either direct downlink to
Deep Space Network or relayed to Earth via nearby spacecraft;
Ground/User: Internet distribution
Data Delivery (How mission and housekeeping data are generated or
collected, distributed & used) – Sensor data and spacecraft health and
orbit/attitude data sent to ground and distributed to users
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 17
18. System Drivers and Key Requirements
(Step 7)
• Mass and power are typical spacecraft system
drivers.
• Using the CubeSat standard adds the volume that
subsystems occupy as a constraint.
• Thermal environment: Temperature at Mercury
ranges from 80 K to 700 K
• Spacecraft lifetime of 8 years
4/30/2016
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
18
19. Proposed Mass, Volume, and Power Budget
System Description Heritage
Mass
(kg)
Volume
(U)
Power (W)
(Peak)
ADCS
Star tracker, sun sensor,
reaction wheels, IMU
BCT XACT (star trackers, IMU), sun sensor,
reaction wheels 1 1 3
Propulsion Microthrusters Busek electrospray thrusters 1 1 30
C&DH/
Processing
Science & Engrg.
Management, processing SpaceCube Mini, Lunar Ice CubeSat 0.5 0.5 5
Thermal/
Radiation
Passive shielding, passive
cooling, heaters, sun shield
MESSENGER's sunshade and other thermal
defense 3 2 8
Structures/
Mechanisms
Frame, deployer, deployables
(gimballed, stowed solar
panel array, antennas)
Planetary Systems Corp. 12U deployer, MMA
Design Ehawk gimballed solar panels 8 - 1
Comm Antenna, transceiver
SERC's deployable high gain antenna, JPL's
IRIS X-Band Radio 3.5 2.5 10
Power
Electrical system, conversion,
regulation, batteries 1.5 1.5 5
Payload:
Near Infrared
Spectrometer
Detector, optics, associated
electronics, cryocooling
JPL Lunar Flashlight's spectrometer, Lunar
IceCube's Broadband InfraRed Compact High
Resolution Explorer Spectrometer (BIRCHES),
Moon Mineralogy Mapper 2.5 1.5 7
Laser Altimeter
Optics, associated electronics,
cryocooling (If required)
JPL Lunar Flashlight's laser, MESSENGER
Laser Altimeter (MLA) 4 2 14
Total without propulsion 25 12 83
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 19
20. Performance Assessments and Trade
Studies (Step 8)
Trade studies:
4/30/2016
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
20
Credit: NASA Jet Propulsion Laboratory Image Credit: USC
Propulsion Communications
21. Performance Assessments & Trade Studies (Step 8)
Measures of Effectiveness
• The following measures of effectiveness are used to
evaluate propulsion, power, and communications
alternatives:
• Technology Readiness Level (TRL)
• Performance specifications
• Propulsion: Thrust, Isp, and power required
• Communications: Data rate and power required
• Mass
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 21
22. Performance Assessments & Trade Studies (Step 8)
Propulsion Alternatives
1. VACCO Propulsion Unit for CubeSats –
a COTS propulsion system which
includes a warm gas thruster
2. CubeSat Ambipolar Thrusters (CAT)
3. HYDROS™ Water Electrolysis Thruster
4. Solar sail
5. Solar Electric Power/Solar Electric
Propulsion (SEP^2)
6. Colloidal Thruster, a.k.a. electrospray
thruster
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
4/30/2016 22
Image Sources: 1. VACCO Industries
2. http://pepl.engin.umich.edu/thrusters.html
3. Tethers Unlimited, Inc.
4. NASA
6. Busek Co., Inc.
No
picture
available
1
2
3
4
5
6
23. Propulsion Trade Study
Alternative Measures of Effectiveness Comments
TRL Thrust Isp Power Mass
VACCO
Propulsion Unit
for CubeSats
TRL-7+ 5.4 mN 70 s 15 W < 1 kg Includes Warm Gas
Thruster, Useful for
attitude control
CubeSat
Ambipolar
Thruster
TRL-3 ≤ 2 mN Up to 2000 s
(About 800 s
in July 2015
tests with
Xenon ions)
≤ 10 W ≤ 1 kg Flexible propellant
(water or iodine,
ideally); first launch
planned for early 2017
HYDROS™ Water
Electrolysis
Thruster
TRL-5
(Expected to
mature to TRL-6
Winter 2015)
≤ 1 N 300 s Water propellant;
“green”
Solar sail TRL-5 < 7mN 4 – 10 kg
(NanoSail-D
was ~ 4 kg)
Thrust from solar
pressure on sail
Solar Electric
Power/Solar
Electric
Propulsion
(SEP^2)
TRL-3 (est.) TBD by
mfr.
Up to 3000 s Generates
80 W,
20 W when
thrusting
TBD Xenon propellant;
System comes with solar
panels
Colloidal
(Electrospray)
Thruster
TRL-7+
TRL-5
100 µN
≤ 1 mN
2300 s
400 s to
> 1300 s
5 W
15 W
320 g (wet)
1.15 kg
Busek has delivered
100-µN thrusters to
NASA
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
4/30/2016 23
24. Performance Assessments & Trade Studies (Step 8)
Communications Alternatives
1. Laser communication
2. Direct microwave
communication with
deployable high-gain
antenna
3. Integrated Solar Array &
Reflectarray Antenna
4. Using a relay spacecraft
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
4/30/2016 24
Image Sources:
1. NASA
2. USC
3. NASA
4. ESA
1
2
3
4
25. Communications Trade Study
Alternative Measures of Effectiveness Comments
TRL Data Rate Power Used Mass
Laser
Communication
TRL-6 < 625 Mbps to <
2.88 Gbps
40 – 50 kbps from
2 AU
50 – 140 W
(LADEE)
0.5 W average
30 kg
(LADEE)
Optical receiver
required; LADEE
transmitter is too
heavy
Direct Microwave
Communication
with Deployable
High Gain Antenna
X: TRL-9
K: TRL-3 to
TR-9
Antenna:
TRL-6 to
TRL-9
X: < 500 Mbps
Ka: < 3 Gbps
Ku: <150 Mbps
K: < 1.2 Gbps
X: < 90–120 W
Ka: N/A
Ku: 47 W
K: 30 W
X: ≤ 4 kg
Ka: 2.7 kg
Ku: 2.3 kg
K: 2.8 kg
JPL-developed IRIS
X-band radio is
specifically
designed for
CubeSats
Integrated Solar
Array & Reflectarray
Antenna
TRL-5
(Flying in
2016 to
raise to
TRL-7)
≥ 100 Mbps No more than
system with
deployable
parabolic antenna
Minimal
difference
from
deployable
parabolic
antenna
High Bandwidth
Ka-band, high gain
antenna integrated
into COTS solar
array
Relay Spacecraft TRL-9 Possibility:
BepiColombo or
Akatsuki
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 25
26. Evaluating Mission Utility (Step 9)
4/30/2016
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
26
How much
will it cost?
Is the mission
worthwhile?
How much
meaningful
science data
can we collect?
What are
the risks?
27. Mission Risks and Mitigation
Mission Risks Mitigation
1. Launch delays Have a secondary launch
date
2. Communication failure Testing; plan an alternative
communication path or
redundancy
3. Radiation environment causing failure Ruggedize; use shielding
4. Collision with space debris or another
spacecraft
No mitigation
5. Technology readiness lacking Use technology already in
development; fly technology
that is not less than TRL 5
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 27
28. Mission Risk Matrix
Very Low Low Medium High Very High
Very High
High
Medium
Low
Very low
Likelihood
Impact
2
1
35
4
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 28
Risks:
1. Launch delays
2. Comm. failure
3. Radiation env.
causes failure
4. Collision
5. TRL
29. Baseline Mission Concept and Architecture (Step 10)
Top Level Spacecraft Block Diagram
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission 29
Command and Data Handling
Subsystem
Electrical Power Subsystem
Attitude Determination &
Control Subsystem
Communications
Subsystem
Payload Subsystem
Propulsion Subsystem
Thermal Control Subsystem
Solar
Array
Battery
S/C
Ground
Power
Mgmt.
Ckts.
Power
Distrib.
Module
Battery
Charge
Reg. To Other
Subsystems
On-Board Data Storage
On-Board Computer (OBC)
Commands to
Subsystems
Data
Handling
Function
ADCS
Function
Command
Function
X-Band
Transceiver
Deployable
Antenna
Mission Data
Star
Trackers
Sun
Sensors
IMU
Reaction
Wheels
Infrared
Spectrometer
Commands
from OBC
Data to OBC
HeatersRadiatorsHeat Pipes Coatings Multi-Layer Insulation
Commands
from Earth
Ionic
Liquid
Propellant
Electrospray Thrusters
Sun Shield
Commands to Thrusters
Laser
Altimeter
Flow Control
Valve
Commands
from OBC
4/30/2016
30. Conclusion
• Payload Possibilities:
• Near infrared spectrometer
• Laser to illuminate shadowed
craters
• Altimeter capability would allow
mapping spectrometer data to depth
within craters
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
304/30/2016
Example Instrument
JPL’s NanoSat Spectrometer
Example of illuminating shadowed crater with laser
Images source: NASA (both)
By drawing upon interplanetary CubeSat projects now in
progress at NASA and on lessons learned during the
MESSENGER mission, an interplanetary CubeSat mission to
Mercury could be developed in about two years.
31. References
• [1] Committee on the Planetary Science Decadel Survey, Voyages and Vision for Planetary Science in the
Decade 2013 - 2022, Washington D.C.: National Academies Press, 2011.
• [2] S. Squyres, "Vision and Voyages for Planetary Science in the Decade 2013-2022, Rollout at LPSC," 11
March 2010. [Online]. Available:
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database
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32. References
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Microcosm Press, 2011.
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Information, 2014.
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[Online]. Available at: http://www.planetarysystemscorp.com/web/wp-content/uploads/2015/08/2002337C-
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Annual Summer CubeSat Developers' Workshop, 2014. [Online]. Available at:
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Lunar-Orbiting-spacecraft.pdf [Accessed 31 October 2015]
• [16] J. Sheehan, 'PEPL: Thrusters: CubeSat Ambipolar Thruster', Plasmadynamics and Electric Propulsion
Laboratory, University of Michigan, 2015. [Online]. Available: http://pepl.engin.umich.edu/thrusters/CAT.html
[Accessed: 01- Nov- 2015].
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• [19] ARTEMIS Space, 'ARTEMIS Lunar Constellation', 2014. [Online]. Available: http://www.artemis-
space.com/artemis-lunar-constellation/ [Accessed: 01- Nov- 2015].
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33. References
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Tocci, Electrospray Propulsion Systems for Small Satellites, 1st ed. Busek Co., Inc., 2013. [Online]. Available:
http://digitalcommons.usu.edu/cgi/viewcontent.cgi?filename=0&article=2960&context=smallsat&type=additiona
l [Accessed: 01- Nov- 2015].
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http://www.busek.com/index_htm_files/70008516E.pdf [Accessed: 01- Nov- 2015].
• [23] HYDROS Thruster, 1st ed. Bothell, WA: Tethers Unlimited, Inc., 2015. [Online]. Available:
http://www.tethers.com/SpecSheets/Brochure_HYDROS.pdf [Accessed: 01- Nov- 2015].
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Available: http://images.spaceref.com/fiso/2015/032515_les_johnson_nasa_msfc/Johnson_3-25-15.pdf
[Accessed: 01- Nov- 2015].
• [25] J. Fleurial, Thermoelectrics in Space: A Success Story, What’s Next and What Might Be Possible, 1st ed.
Pasadena, CA: JPL, 2015. [Online]. Available:
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[Accessed: 01- Nov- 2015].
• [26] B. Cohen, 'Lunar Flashlight and Near Earth Asteroid Scout: Exploration Science Using Cubesats', 2nd
NASA Exploration Science Forum; Moffett Field, CA, 2015. [Online]. Available:
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Workshop at the Small Satellite Conference, 2013. [Online]. Available:
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Pointing, 1st ed. Marina del Rey, CA: Space Engineering Research Center, 2011. [Online]. Available:
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34. References
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Ranging - Thermal Design', 2015. [Online]. Available: http://messenger.jhuapl.edu/spacecraft/thermal.html
[Accessed: 01- Nov- 2015].
• [30] Messenger.jhuapl.edu, 'MESSENGER: MErcury Surface, Space ENvironment, GEochemistry, and
Ranging - Power', 2015. [Online]. Available: http://messenger.jhuapl.edu/spacecraft/power.html [Accessed: 01-
Nov- 2015].
• [31] Messenger.jhuapl.edu, 'MESSENGER: MErcury Surface, Space ENvironment, GEochemistry, and
Ranging - Mission Design', 2015. [Online]. Available:
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• [32] Messenger.jhuapl.edu, 'MESSENGER: MErcury Surface, Space ENvironment, GEochemistry, and
Ranging - The Payload Instruments', 2015. [Online]. Available:
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Ranging - Working from Orbit', 2015. [Online]. Available: http://messenger.jhuapl.edu/the_mission/orbit.html
[Accessed: 01- Nov- 2015].
K. Grothe – Applying a Systems Engineering Process to
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35. Supplemental Slides
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
35
4/30/2016
36. CubeSat History
1999
• CubeSat
concept
defined
2003
• First flight –
university
CubeSats
2006
• First NASA
CubeSat –
GENESAT
2007
• First CubeSat
launched by
commercial
company
(Boeing)
2013
• First USAF SMC
CubeSats
launched
• First PlanetLabs
Doves
launched
2015
• 101st
PlanetLabs
Dove launched
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 36
37. CubeSat Mission Types By Year
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 37
NumberLaunched
Year
38. Ground Segment
JPL’s Space Flight
Operations Facility Deep Space Network
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission 38
(Source: NASA/JPL-Caltech)
4/30/2016
39. Launch Segment
• CubeSat Mercury
Mission shall launch as a
secondary payload.
• A Canisterized Satellite
Dispenser (CSD) will be
used to encapsulate the
spacecraft on the launch
vehicle and dispense it
on an appropriate Earth
orbit.
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission 39
Images Source: Planetary Systems Corporation
4/30/2016
40. Payload
Driving Requirements
• Scientific objectives
• Investigate the state, extent, and chemical compositions of
surface volatiles in the polar regions of Mercury
• Thermal environment
• Small size
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
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4/30/2016
41. Electrical Power Subsystem
•Design Drivers
• Orbit: Mercury orbit requires enough battery power to
supply the spacecraft power during eclipse.
• Payload requirements: Instruments require power, fault
protection, bursts of power when imaging a particular
commanded area.
• Distribute power to all subsystems
• Spacecraft lifetime of 8 years
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
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4/30/2016
42. Communication Subsystem
Driving Requirements
• Distance of the mission from Earth
• Pointing requirements
• Small size of satellite
• Power availability
• Thermal control
• Telemetry and sensor data downlinked at X-band
• In the range 8400 - 8450 MHz for DSN
• Commands uplinked at X-band
• In the range 7145 - 7190 MHz for DSN
• Data rate – If the data rate is too slow, data storage
capability will need to increase.
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
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4/30/2016
43. Attitude Determination & Control
Subsystem (ADCS)
Driving Requirements
• Three-axis stabilization
• Power: Solar panels need to point to the sun to
produce sufficient power
• Pointing accuracy necessary to complete the
science objectives
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
43
4/30/2016
44. Thermal Control Subsystem
Driving Requirements
• Thermal Environment: Orbiting Mercury presents
extreme temperatures as the spacecraft moves
between eclipse and sun exposure
• Large thermal effect from sunlight reflected up from
Mercury
• Infrared heat emanating from the planet's
scorching day-side surface
• Spacecraft size
• Instruments may need extra thermal control
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
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4/30/2016
45. Propulsion Subsystem
Driving Requirements
•Distance to destination
•Fuel
•Influence on weight and size
•High performance less weight
•Spacecraft lifetime of 8 years
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
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4/30/2016
46. Proposed Payload Block Diagram
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
46
Infrared Spectrometer Laser Altimeter
Command & Data Handling Subsystem
Commands Commands DataData
4/30/2016
47. Proposed Electrical Power Subsystem Block Diagram
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
47
Solar
Panel 3
Solar
Panel 2
Solar
Panels
Power
Management
Circuits
Spacecraft
Ground
Battery Charge
Regulator
Spacecraft
Battery
Power
Distribution
Module
Attitude
Determination
& Control
Subsystem
Communications
Subsystem
Payload
Thermal
Control
Subsystem
Command &
Data Handling
Subsystem
Power Subsystem Architecture
(Simplified)
4/30/2016
48. Proposed Communication Subsystem
Block Diagram
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
48
Command & Data
Handling Subsystem
X-Band
Transponder
Deployable
High Gain
Antenna
Commands
Telemetry Inputs Mission Data
Commands
from Earth
4/30/2016
49. Proposed ADCS Block Diagram
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
49
On-Board Computer
ADCS Function
Sun
Sensors
Star
Trackers
Attitude
Determination
Attitude
Control
Reaction
Wheels
IMU
Thrusters
4/30/2016
50. Proposed Propulsion Subsystem
Block Diagram
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
50
Ionic Liquid
Propellant
Flow Control
Valve
Electrospray Thrusters
Command & Data
Handling
Subsystem
4/30/2016
51. Diagram of
Proposed Thermal Control Subsystem
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
51
Coatings
Radiators Multi-Layer
Insulation
Blankets
Heat Pipes
Sun Shield
Heaters
Dimensions in mm
12U CubeSat Payload Spec Source:
http://www.planetarysystemscorp.com/web/wp-content/uploads/2015/08/2002367C-Payload-Spec-for-3U-6U-12U-27U1.pdf
4/30/2016
52. Additional Possibilities
• MBSE: Project could be further developed using the
CubeSat SysML model developed by the INCOSE
Space Systems Working Group
• Interplanetary CubeSats in constellations
• Interplanetary CubeSats inserted in the orbit of a
planetary body from a mothership
• Weight reduction:
• Wireless intra-spacecraft communication
• Eliminate black boxes and create an optimized design
K. Grothe – Applying a Systems Engineering Process to
a Conceptual Mercury CubeSat Mission4/30/2016 52