Best Practices for the Development of CubeSat MissionsCarlos Duarte
As the demand for #CubeSats continues to increase, it is important for those who are developing CubeSat missions to be aware of best practices. This will help to ensure that missions are successful and that the CubeSats are able to achieve their objectives.
Some of the best practices for the development of CubeSat missions include:
1. Define the mission objectives clearly and ensure that they are achievable.
2. Develop a detailed plan for the mission and communicate it to all team members.
3. Select the appropriate CubeSat platform and subsystems for the mission.
4. Thoroughly test the CubeSat before launch.
5. Monitor the CubeSat during its mission and be prepared to respond to any problems that may arise.
By following these best practices, the development of successful CubeSat missions will be more likely.
This document provides an introduction to CubeSats for first-time developers. It discusses the basics of CubeSats, including standard CubeSat sizes and dispenser systems used to deploy them from launch vehicles. It then gives an overview of the multi-step development process for a CubeSat project, from initial concept through launch and operations. Finally, it introduces some common mission models and requirements sources that CubeSat developers must consider to successfully design, build, test, launch and operate their small satellites. The goal is to lay out everything needed to take a CubeSat idea from concept to becoming an actual spacecraft in orbit.
Chandrayaan-2 is India's second lunar mission, launched on July 22nd 2019 with the aim of improving understanding of the moon through an orbiter, lander and rover. The orbiter will orbit 100km from the moon's surface and carry 8 instruments to analyze the moon's topography and atmosphere. The lander, named Vikram, will deploy the rover Pragyan to conduct surface experiments over a 14 earth day mission. Chandrayaan-2 seeks to further scientific knowledge and advance India's space capabilities.
Urano es el séptimo planeta del Sistema Solar. Sus principales características son su inclinación de casi 90 grados respecto a su órbita y su color azul-verdoso debido a la composición de su atmósfera. Fue descubierto en 1781 por William Herschel. Tiene 27 lunas conocidas y anillos compuestos principalmente por hielo y polvo.
Global Navigation Satellite Systems (GNSS) allow users to pinpoint their geographic location anywhere in the world using signals from satellites. The two main GNSS currently in operation are the United States' Global Positioning System (GPS) and Russia's Global Navigation Satellite System (GLONASS). There are also other regional GNSS including the European Union's Galileo, China's BeiDou, Japan's QZSS, and India's NavIC. GPS and GLONASS both provide positioning and timing data to users worldwide, with GPS generally offering higher accuracy overall and GLONASS performing better at high latitudes.
The document discusses various global and regional satellite navigation systems:
- GLONASS is Russia's system with 24 operational satellites. It provides improved precision and reliability when integrated with GPS.
- EGNOS and Galileo are Europe's systems to enhance GPS. EGNOS went live in 2004 as a precursor to Galileo, which launched its first satellites in 2016.
- BeiDou is China's system with 5 geostationary and 30 non-geostationary satellites. It began covering Asia-Pacific in 2012 and will cover the world by 2020.
- IRNSS is India's system consisting of 7 satellites, 3 geostationary and 4 geosynchronous, providing accuracy of 20 meters over India
The document discusses the Global Positioning System (GPS). GPS is a satellite-based navigation system consisting of three segments - space, control, and user. The space segment includes 24 satellites that transmit radio signals used by GPS receivers to determine location, velocity, and time. The control segment monitors the satellites and updates their clocks. The user segment includes GPS receivers that calculate position by precisely timing signals from at least three satellites. Common sources of error and differential GPS for improving accuracy are also covered, as well as many applications of GPS technology.
Orbits and space flight, types of orbitsShiva Uppu
This document discusses orbital mechanics including different types of orbits around Earth and other planets. It begins by defining orbital elements like eccentricity, semi-major axis, inclination, and orbital period. It then describes different types of orbits including low Earth orbit, geosynchronous orbit, polar orbit, and Hohmann transfer orbits. Basic orbital equations are provided relating centripetal force, gravitational force, orbital velocity, and orbital radius. Numerical examples are worked through to calculate orbital velocity, orbital radius, and orbital period for satellites orbiting Earth.
Best Practices for the Development of CubeSat MissionsCarlos Duarte
As the demand for #CubeSats continues to increase, it is important for those who are developing CubeSat missions to be aware of best practices. This will help to ensure that missions are successful and that the CubeSats are able to achieve their objectives.
Some of the best practices for the development of CubeSat missions include:
1. Define the mission objectives clearly and ensure that they are achievable.
2. Develop a detailed plan for the mission and communicate it to all team members.
3. Select the appropriate CubeSat platform and subsystems for the mission.
4. Thoroughly test the CubeSat before launch.
5. Monitor the CubeSat during its mission and be prepared to respond to any problems that may arise.
By following these best practices, the development of successful CubeSat missions will be more likely.
This document provides an introduction to CubeSats for first-time developers. It discusses the basics of CubeSats, including standard CubeSat sizes and dispenser systems used to deploy them from launch vehicles. It then gives an overview of the multi-step development process for a CubeSat project, from initial concept through launch and operations. Finally, it introduces some common mission models and requirements sources that CubeSat developers must consider to successfully design, build, test, launch and operate their small satellites. The goal is to lay out everything needed to take a CubeSat idea from concept to becoming an actual spacecraft in orbit.
Chandrayaan-2 is India's second lunar mission, launched on July 22nd 2019 with the aim of improving understanding of the moon through an orbiter, lander and rover. The orbiter will orbit 100km from the moon's surface and carry 8 instruments to analyze the moon's topography and atmosphere. The lander, named Vikram, will deploy the rover Pragyan to conduct surface experiments over a 14 earth day mission. Chandrayaan-2 seeks to further scientific knowledge and advance India's space capabilities.
Urano es el séptimo planeta del Sistema Solar. Sus principales características son su inclinación de casi 90 grados respecto a su órbita y su color azul-verdoso debido a la composición de su atmósfera. Fue descubierto en 1781 por William Herschel. Tiene 27 lunas conocidas y anillos compuestos principalmente por hielo y polvo.
Global Navigation Satellite Systems (GNSS) allow users to pinpoint their geographic location anywhere in the world using signals from satellites. The two main GNSS currently in operation are the United States' Global Positioning System (GPS) and Russia's Global Navigation Satellite System (GLONASS). There are also other regional GNSS including the European Union's Galileo, China's BeiDou, Japan's QZSS, and India's NavIC. GPS and GLONASS both provide positioning and timing data to users worldwide, with GPS generally offering higher accuracy overall and GLONASS performing better at high latitudes.
The document discusses various global and regional satellite navigation systems:
- GLONASS is Russia's system with 24 operational satellites. It provides improved precision and reliability when integrated with GPS.
- EGNOS and Galileo are Europe's systems to enhance GPS. EGNOS went live in 2004 as a precursor to Galileo, which launched its first satellites in 2016.
- BeiDou is China's system with 5 geostationary and 30 non-geostationary satellites. It began covering Asia-Pacific in 2012 and will cover the world by 2020.
- IRNSS is India's system consisting of 7 satellites, 3 geostationary and 4 geosynchronous, providing accuracy of 20 meters over India
The document discusses the Global Positioning System (GPS). GPS is a satellite-based navigation system consisting of three segments - space, control, and user. The space segment includes 24 satellites that transmit radio signals used by GPS receivers to determine location, velocity, and time. The control segment monitors the satellites and updates their clocks. The user segment includes GPS receivers that calculate position by precisely timing signals from at least three satellites. Common sources of error and differential GPS for improving accuracy are also covered, as well as many applications of GPS technology.
Orbits and space flight, types of orbitsShiva Uppu
This document discusses orbital mechanics including different types of orbits around Earth and other planets. It begins by defining orbital elements like eccentricity, semi-major axis, inclination, and orbital period. It then describes different types of orbits including low Earth orbit, geosynchronous orbit, polar orbit, and Hohmann transfer orbits. Basic orbital equations are provided relating centripetal force, gravitational force, orbital velocity, and orbital radius. Numerical examples are worked through to calculate orbital velocity, orbital radius, and orbital period for satellites orbiting Earth.
Mars orbiter mission (Mangalyaan)The govt. of INDIAArchit Jindal
All details of the Mars orbiter mission of India. Also the details about ISRO who is carrying out this mission. Also Mp4 video of launch of PSLV-XL which was the launch vehicle for the spacecraft. I hope this presentation is useful for you.The video will work.
Introduction of gps global navigation satellite systems DocumentStory
This document provides information on Global Navigation Satellite Systems (GNSS). It discusses several GNSS including GPS (USA), GLONASS (Russia), and Galileo (Europe). It provides details on GLONASS and Galileo constellations and signal structures. The benefits of multiple GNSS include improved availability, accuracy, reliability and efficiency of position determination.
A presentation on the planet Venus. Designed for 5th grade students. Contains basic facts, including the space probes that helped us learn about Venus. Includes quiz questions at the end.
Chandrayaan-2 was India's second lunar mission, successfully launched in July 2019 to explore the Moon's south polar region. The mission included an orbiter, Vikram lander, and Pragyan rover. The orbiter will map the lunar surface while studying water ice in the south pole. Vikram was to land and deploy Pragyan to conduct additional science experiments near the landing site. However, the landing was unsuccessful as Vikram's descent velocity was too high, and it crashed onto the lunar surface instead of landing safely. The orbiter remains operational in orbit and will continue its planned science observations.
Global navigation satellite system based positioning combinedMehjabin Sultana
This document provides an overview of global navigation satellite systems (GNSS) such as GPS, GLONASS, Galileo, and Compass. It discusses the history and development of satellite navigation systems, comparing the key aspects of different GNSS. It also describes the typical three-segment architecture of GNSS including space, ground, and user segments. Finally, it outlines several applications of satellite-based positioning in areas like agriculture, aviation, marine, and more.
The document summarizes key details about India's space program and satellites. It provides information on 50 Indian satellites launched between 1975 and 2008, including their names, launch dates, payloads, and purpose. It also discusses India's goals of developing its own GPS system and launching around 7 satellites by 2010. The first Indian satellite was Aryabhata, launched in 1975, and Chandrayaan-1 was India's first lunar mission, launched in 2008.
Bsf08 Spacecraft Attitude Determination And Control V1 0abi3
1) Spacecraft attitude refers to the orientation of a spacecraft in space. Most spacecraft need to precisely point instruments and antennas in specific directions.
2) To control attitude, a spacecraft needs to determine its current attitude, compare it to the desired attitude, and apply torques to reduce any error. This requires an attitude determination and control system (ADCS) using sensors and actuators.
3) Disturbing torques from forces like gravity gradients, solar radiation pressure, and aerodynamic drag must be counteracted to maintain the desired attitude. The relative strength of these disturbances depends on factors like the spacecraft's size, mass, and orbital altitude.
Global Navigation Satellite System (GNSS) allows mappers and resource managers to locate features using satellite positioning. GNSS receivers determine position by measuring distances to at least 4 satellites via signal travel time. Accuracy is typically 10-20 meters but can be improved to 1-5 meters using real-time differential corrections which account for errors. GNSS data can be incorporated into a GIS by converting point, line and polygon features collected using GNSS receivers.
The document discusses various methods and instruments used for celestial navigation. It describes tools like the sextant, astrolabe, and octant that were used to determine position by measuring the angle between celestial objects and the horizon. It also discusses coordinate systems and modern GPS technology used for navigation.
Hi !
I have made this presentation for you so that you know what is space and what is space technology.The one who will download it will be the one who has got 95% knowledge of space and
FOR MORE KNOWLEDGE JUST EMAIL ME ON THIS EMAIL ADDRESS
workplaceid154@gmail.com
Thanks for your downloading
(please spread this presentation to all schools and all institute so that the students or people can get to know about space)
NOTE:THIS IS MICROSOFT 2013 PRESENTATION)
I WILL UPLOAD LOWER VERSIONS OF THIS FILE
THANKS (MADE BY IRTAZA ZAFAR AND
HASEEB AHMED FROM THE CITY SCHOOL CHENAB CAMPUS FSD
This document provides information about basic concepts related to charts used for aviation purposes. It discusses key terms like maps, charts, projections and distortions that occur when representing the spherical Earth on a flat surface. It also describes different types of projections including plane, conical, cylindrical and their characteristics. Specific projections like Mercator and Lambert Conformal are explained in more detail.
GPS uses a constellation of 24 satellites orbiting Earth to enable GPS receivers to determine their precise location. The system works by using triangulation based on distance measurements from at least three satellites. The GPS segments include the space segment (satellites), control segment (ground stations that monitor satellites), and user segment (GPS receivers). GPS has both military and civilian applications including navigation, mapping, vehicle tracking, and monitoring fishing fleets.
The document provides an overview of the Global Positioning System (GPS) in 3 segments: the space segment consists of 24+ satellites in orbit that broadcast timing and position data; the control segment includes 5 monitoring stations that track satellites and upload corrections; the user segment comprises over 3 billion GPS receivers used for navigation, mapping, and other purposes by both military and civilian users. GPS determines position by precisely measuring the time it takes signals from at least 4 satellites to reach a receiver.
The document provides details about satellite communication history and technology. It discusses key events like the launch of Sputnik 1 in 1957 as the first artificial satellite and describes various satellite systems including low Earth orbit (LEO), medium Earth orbit (MEO), and geostationary orbit (GEO). It also covers topics like how satellites are launched, orbital velocities, satellite costs, and components of a basic satellite system.
Chandrayaan-2 is India's second lunar mission consisting of an orbiter, lander, and rover. It was launched in July 2019 and successfully placed the orbiter in lunar orbit in August. The mission aims to study the moon's topography, mineral composition, and presence of water ice. In September, the lander Vikram attempted to soft land in the south polar region but lost communication during its final descent. Onboard instruments include terrain mapping cameras, spectrometers, and a synthetic aperture radar on the orbiter as well as seismic and thermal sensors on the lander. The rover Pragyan was to explore the landing site for 14 earth days using laser and alpha particle spectrometers. While the
This Presentation is to made concepts about measuring the earth (to locate position of any person on the whole earth). For this purpose we re going step by step basis in this presentation.These steps are mentioned as contents. After that you may able to learn about measuring a person's position of earth. Thank you!
The Mars Orbiter Mission (MOM), also called Mangalyaan, is a spacecraft orbiting Mars that was launched by the Indian Space Research Organization (ISRO) in November 2013. It is India's first interplanetary mission and made ISRO the fourth space agency to reach Mars. The primary objective was to demonstrate India's technological capability to design, plan and manage an interplanetary mission. It also carried scientific instruments to study Mars' surface features, morphology, mineralogy and atmosphere. Mangalyaan successfully entered Mars' orbit in September 2014 and continues to transmit data, making it one of the least expensive Mars missions to date.
The document discusses the Global Positioning System (GPS), which uses satellites to provide location and time information anywhere on Earth. It can be used for automobile navigation, tracking vehicles and people, mapping, mining, and recreation. GPS works in all weather conditions and provides accurate positioning from millimeters to meters depending on the technique used. While GPS has wide coverage and low costs, it requires line of sight to satellites and may not work as well indoors or in locations with metal or concrete barriers. The use of GPS in phones in India is growing, with over 25% of phones including the feature starting around Rs. 5,000.
Challenges and opportunities of the Mexican Space Agency Carlos Duarte
Mexican Space Agency: its origin, plans and achievements through a seminary presented by Carlos Duarte at the GeoSat Center of Texas A&M University on March 3, 2016
Mercury CubeSat Presentation for ASAT2016Karen Grothe
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.
Mars orbiter mission (Mangalyaan)The govt. of INDIAArchit Jindal
All details of the Mars orbiter mission of India. Also the details about ISRO who is carrying out this mission. Also Mp4 video of launch of PSLV-XL which was the launch vehicle for the spacecraft. I hope this presentation is useful for you.The video will work.
Introduction of gps global navigation satellite systems DocumentStory
This document provides information on Global Navigation Satellite Systems (GNSS). It discusses several GNSS including GPS (USA), GLONASS (Russia), and Galileo (Europe). It provides details on GLONASS and Galileo constellations and signal structures. The benefits of multiple GNSS include improved availability, accuracy, reliability and efficiency of position determination.
A presentation on the planet Venus. Designed for 5th grade students. Contains basic facts, including the space probes that helped us learn about Venus. Includes quiz questions at the end.
Chandrayaan-2 was India's second lunar mission, successfully launched in July 2019 to explore the Moon's south polar region. The mission included an orbiter, Vikram lander, and Pragyan rover. The orbiter will map the lunar surface while studying water ice in the south pole. Vikram was to land and deploy Pragyan to conduct additional science experiments near the landing site. However, the landing was unsuccessful as Vikram's descent velocity was too high, and it crashed onto the lunar surface instead of landing safely. The orbiter remains operational in orbit and will continue its planned science observations.
Global navigation satellite system based positioning combinedMehjabin Sultana
This document provides an overview of global navigation satellite systems (GNSS) such as GPS, GLONASS, Galileo, and Compass. It discusses the history and development of satellite navigation systems, comparing the key aspects of different GNSS. It also describes the typical three-segment architecture of GNSS including space, ground, and user segments. Finally, it outlines several applications of satellite-based positioning in areas like agriculture, aviation, marine, and more.
The document summarizes key details about India's space program and satellites. It provides information on 50 Indian satellites launched between 1975 and 2008, including their names, launch dates, payloads, and purpose. It also discusses India's goals of developing its own GPS system and launching around 7 satellites by 2010. The first Indian satellite was Aryabhata, launched in 1975, and Chandrayaan-1 was India's first lunar mission, launched in 2008.
Bsf08 Spacecraft Attitude Determination And Control V1 0abi3
1) Spacecraft attitude refers to the orientation of a spacecraft in space. Most spacecraft need to precisely point instruments and antennas in specific directions.
2) To control attitude, a spacecraft needs to determine its current attitude, compare it to the desired attitude, and apply torques to reduce any error. This requires an attitude determination and control system (ADCS) using sensors and actuators.
3) Disturbing torques from forces like gravity gradients, solar radiation pressure, and aerodynamic drag must be counteracted to maintain the desired attitude. The relative strength of these disturbances depends on factors like the spacecraft's size, mass, and orbital altitude.
Global Navigation Satellite System (GNSS) allows mappers and resource managers to locate features using satellite positioning. GNSS receivers determine position by measuring distances to at least 4 satellites via signal travel time. Accuracy is typically 10-20 meters but can be improved to 1-5 meters using real-time differential corrections which account for errors. GNSS data can be incorporated into a GIS by converting point, line and polygon features collected using GNSS receivers.
The document discusses various methods and instruments used for celestial navigation. It describes tools like the sextant, astrolabe, and octant that were used to determine position by measuring the angle between celestial objects and the horizon. It also discusses coordinate systems and modern GPS technology used for navigation.
Hi !
I have made this presentation for you so that you know what is space and what is space technology.The one who will download it will be the one who has got 95% knowledge of space and
FOR MORE KNOWLEDGE JUST EMAIL ME ON THIS EMAIL ADDRESS
workplaceid154@gmail.com
Thanks for your downloading
(please spread this presentation to all schools and all institute so that the students or people can get to know about space)
NOTE:THIS IS MICROSOFT 2013 PRESENTATION)
I WILL UPLOAD LOWER VERSIONS OF THIS FILE
THANKS (MADE BY IRTAZA ZAFAR AND
HASEEB AHMED FROM THE CITY SCHOOL CHENAB CAMPUS FSD
This document provides information about basic concepts related to charts used for aviation purposes. It discusses key terms like maps, charts, projections and distortions that occur when representing the spherical Earth on a flat surface. It also describes different types of projections including plane, conical, cylindrical and their characteristics. Specific projections like Mercator and Lambert Conformal are explained in more detail.
GPS uses a constellation of 24 satellites orbiting Earth to enable GPS receivers to determine their precise location. The system works by using triangulation based on distance measurements from at least three satellites. The GPS segments include the space segment (satellites), control segment (ground stations that monitor satellites), and user segment (GPS receivers). GPS has both military and civilian applications including navigation, mapping, vehicle tracking, and monitoring fishing fleets.
The document provides an overview of the Global Positioning System (GPS) in 3 segments: the space segment consists of 24+ satellites in orbit that broadcast timing and position data; the control segment includes 5 monitoring stations that track satellites and upload corrections; the user segment comprises over 3 billion GPS receivers used for navigation, mapping, and other purposes by both military and civilian users. GPS determines position by precisely measuring the time it takes signals from at least 4 satellites to reach a receiver.
The document provides details about satellite communication history and technology. It discusses key events like the launch of Sputnik 1 in 1957 as the first artificial satellite and describes various satellite systems including low Earth orbit (LEO), medium Earth orbit (MEO), and geostationary orbit (GEO). It also covers topics like how satellites are launched, orbital velocities, satellite costs, and components of a basic satellite system.
Chandrayaan-2 is India's second lunar mission consisting of an orbiter, lander, and rover. It was launched in July 2019 and successfully placed the orbiter in lunar orbit in August. The mission aims to study the moon's topography, mineral composition, and presence of water ice. In September, the lander Vikram attempted to soft land in the south polar region but lost communication during its final descent. Onboard instruments include terrain mapping cameras, spectrometers, and a synthetic aperture radar on the orbiter as well as seismic and thermal sensors on the lander. The rover Pragyan was to explore the landing site for 14 earth days using laser and alpha particle spectrometers. While the
This Presentation is to made concepts about measuring the earth (to locate position of any person on the whole earth). For this purpose we re going step by step basis in this presentation.These steps are mentioned as contents. After that you may able to learn about measuring a person's position of earth. Thank you!
The Mars Orbiter Mission (MOM), also called Mangalyaan, is a spacecraft orbiting Mars that was launched by the Indian Space Research Organization (ISRO) in November 2013. It is India's first interplanetary mission and made ISRO the fourth space agency to reach Mars. The primary objective was to demonstrate India's technological capability to design, plan and manage an interplanetary mission. It also carried scientific instruments to study Mars' surface features, morphology, mineralogy and atmosphere. Mangalyaan successfully entered Mars' orbit in September 2014 and continues to transmit data, making it one of the least expensive Mars missions to date.
The document discusses the Global Positioning System (GPS), which uses satellites to provide location and time information anywhere on Earth. It can be used for automobile navigation, tracking vehicles and people, mapping, mining, and recreation. GPS works in all weather conditions and provides accurate positioning from millimeters to meters depending on the technique used. While GPS has wide coverage and low costs, it requires line of sight to satellites and may not work as well indoors or in locations with metal or concrete barriers. The use of GPS in phones in India is growing, with over 25% of phones including the feature starting around Rs. 5,000.
Challenges and opportunities of the Mexican Space Agency Carlos Duarte
Mexican Space Agency: its origin, plans and achievements through a seminary presented by Carlos Duarte at the GeoSat Center of Texas A&M University on March 3, 2016
Mercury CubeSat Presentation for ASAT2016Karen Grothe
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.
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.
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 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 plans to recover from the loss of the Orbiting Carbon Observatory (OCO) mission by developing a replacement mission called OCO-2. It outlines a tailored 8-month formulation period to ready OCO-2 for a key decision point and 28-month development cycle to launch by 2016. The approach leverages existing OCO work and plans to address all NASA requirements to minimize risk to the accelerated schedule and budget.
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 provides a status update on NASA's Commercial Crew Program. It discusses progress made by program partners Blue Origin, Boeing, Sierra Nevada Corp., and SpaceX in 2012 under the program's Commercial Crew Development and Commercial Crew Integrated Capability initiatives. It outlines upcoming milestones and plans for continued design and testing work in 2013 as the partners work to develop commercial crew transportation systems.
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.
3) Recent government experience with systems engineering from the Director of Defense Research and Engineering and the Under Secretary of the Air Force.
4) Trends driving needs for systems engineering education and applications of systems engineering beyond aerospace to areas like energy and cybersecurity.
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 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.
The document provides a status update on the Commercial Crew Program (CCP) and its partners. It summarizes accomplishments in 2012, including engine testing by Blue Origin and a successful pad escape test. Plans for 2013 include continued development work by the partners - Boeing, Blue Origin, Sierra Nevada Corporation, and SpaceX. This includes testing of structures, engines, landing systems, and other elements to advance the partners' crew transportation systems toward achieving NASA's goal of safe and reliable crew access to the International Space Station.
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.
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.
The document provides information about several projects undertaken by the Aerospace Enterprise student group at Michigan Technological University, including:
1) The Oculus satellite project which involves over 70 students across various subsystem teams designing a CubeSat for a competition.
2) The Ion Propulsion Lab which conducts experiments on electric propulsion thrusters and was founded in 2000.
3) A lunar penetrator project to develop a system to insert a 1-meter rod into the lunar surface to take measurements.
4) Participation in NASA's reduced gravity C-9 aircraft experiments on topics like boom vibration and electron propulsion.
5) The CanSat project which involves launching a satellite
Alexandre Popov has over 30 years of experience in software engineering, systems engineering, and space mission planning for programs including the International Space Station and Mir space station. He has a MSc in Systems Engineering and BSc in Applied Mathematics. Currently he is an Adjunct Professor researching prognostics and health management for space exploration missions.
The document discusses Pakistan's space program, including its history, current projects, research and development infrastructure, and human resource development efforts. Some of Pakistan's current space projects include Paksat-1, the Pakistan Communication Satellite System (Paksat-1R), and plans for a Remote Sensing Satellite System. SUPARCO is developing satellite and space technologies through various research labs and facilities. It also has an ambitious human resource development program that includes training scientists and engineers both locally and abroad.
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Applying the Systems Engineering Process to a Conceptual Merucry CubeSat Mission
1. Applying the Systems Engineering Process
to a Conceptual Mercury CubeSat Mission
By Karen Grothe
• Email: karen@karengrothe.com
• Website: http://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 – Spring 2015
• MS in Systems Engineering from Loyola Marymount University – Dec. 2015
• 16 years experience in aerospace as a systems engineer at McDonnell
Douglas (F/A-18 Maintenance Trainers), Boeing (MD-10/11 Avionics
Development Simulation), and Raytheon (B-2 Radar and U-2 ASARS
Radar)
• 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
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
2
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.
4/9/2016 Applying 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
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
4
5. NASA’s Planned Interplanetary
CubeSat Missions
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
5
Auxiliary Payload on Europa Mission
(2020s)
MarCO
(Secondary Payload with Mars INSIGHT)
Lunar Flashlight (July 2018)
NEA Scout (July 2018)
6. Methodology:
Space Mission Engineering Process
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
6
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
7. Mission Objectives & 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.
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
7
Credit: NASA/Johns Hopkins University Applied Physics Laboratory/Carnegie
Institution of Washington
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
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
8
Credit: NASA/Johns Hopkins University Applied Physics Laboratory/Carnegie
Institution of Washington/National Astronomy and Ionosphere Center, Arecibo
Observatory
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 – Busek, 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.
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
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
4/9/2016
Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
10
* Typical Durations come from SME-SMAD [11, Table 3-3, Page 54]
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.
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
11
12. Alternative Mission Architectures
(Step 5)
• Operational views
– OV-1: Overview
• System views
– SV-1: System Interface Description (for two options)
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
12
13. Mercury CubeSat Mission
Architecture Overview
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
13
Space Flight
Operations Facility
Deep Space
Network
Users/CustomersPasadena, CA
Launch
CubeSat
Image Credit: Tomas Svitek
14. Mercury CubeSat Mission
System Interface Description (Option A)
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
14
15. Mercury CubeSat Mission
System Interface Description (Option B)
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
15
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
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
16
Example trajectory: MESSENGER
Image source: http://messenger.jhuapl.edu/the_mission/trajectory.html
17. 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
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
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
4/9/2016 Applying 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
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
19
20. Performance Assessments
and Trade Studies (Step 8)
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
20
Trade studies:
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 and communications alternatives:
– Technology Readiness Level (TRL)
– Performance specifications
• Propulsion: Thrust, Isp, and power required
• Communications: Data rate and power required
– Mass
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
21
22. Performance Assessments & Trade Studies
(Step 8)
Propulsion Alternatives
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
22
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
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 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
4/9/2016 Applying Systems Engineering Process to a Conceptual Mercury CubeSat Mission 23
24. Performance Assessments & Trade Studies
(Step 8)
Communications Alternatives
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
24
1. Laser communication
2. Direct microwave
communication with
deployable high-gain
antenna
3. Integrated Solar Array &
Reflectarray Antenna
4. Using a relay spacecraft
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
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
25
26. Evaluating Mission Utility
(Step 9)
4/9/2016 Applying 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
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
27
28. Mission Risk Matrix
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
28
Very Low Low Medium High Very High
Very High
High
Medium
Low
Very low
Likelihood
Impact
2
1
35
4
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
4/9/2016 Applying 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
30. Conclusion
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
30
• Payload Possibilities:
– Near infrared spectrometer
– Laser to illuminate shadowed
craters
• Altimeter capability would allow
mapping spectrometer data to
depth within craters
Example Instrument
JPL’s NanoSat Spectrometer
Example of illuminating shadowed crater with laserImages 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: http://solarsystem.nasa.gov/docs/Squyres_2013_Decadal_Rollout_at_LPSC.pdf .
[Accessed 4 May 2015].
• [3] The CubeSat Program, , "CubeSat Design Specification Rev 13, Final2, PDF File," 6 April 2015. [Online].
Available: http://cubesat.org/images/developers/cds_rev13_final2.pdf . [Accessed 4 May 2015].
• [4] The Planetary Society, "NASA's Planetary Science Division Funding and Number of Missions 2004 - 2020," 9
February 2015. [Online]. Available: http://www.planetary.org/multimedia/space-images/charts/historical-levels-of-
planetary-exploration-funding-fy2003-fy2019.html . [Accessed 6 May 2015].
• [5] Solar System Exploration Research Virtual Institute (SSERVI), "Lunar Flashlight," NASA, [Online]. Available:
http://sservi.nasa.gov/articles/lunar-flashlight/ . [Accessed 6 May 2015].
• [6] P. Banazadeh and A. Frick, “Lunar Flashlight and NEA Scout: A NanoSat Architecture for Deep Space
Exploration," 2014. [Online]. Available: http://www.intersmallsatconference.com/ . [Accessed 6 May 2015].
• [7] R. Staehle and e. al., “Lunar Flashlight: Finding Lunar Volatiles Using CubeSats," 13 November 2013. [Online].
Available: http://sservi.nasa.gov/wp-content/uploads/2014/04/Staehle-presentation-Lunar-Flashlight-20131109.pdf
. [Accessed 6 May 2015].
• [8] Michael Swartwout, PhD, Associate Professor, Aerospace and Mechanical Engineering, Saint Louis University,
CubeSat Database. [Online]. Available: https://sites.google.com/a/slu.edu/swartwout/home/cubesat-database
• [9] NASA, “NASA Technology Roadmaps, TA 2: In-Space Propulsion Technologies”, May 2015 Draft. [Online.]
Available at:
http://www.nasa.gov/sites/default/files/atoms/files/2015_nasa_technology_roadmaps_ta_2_in_space_propulsion.p
df [Accessed 12 October 2015]
4/9/2016 Applying Systems Engineering Process to
a Conceptual Mercury CubeSat Mission
31
32. References
• [10] NASA, “Definition of Technology Readiness Levels.” [Online]. Available at: http://esto.nasa.gov/files/trl_definitions.pdf
[Accessed 12 October 2015]
• [11] J. Wertz, D. Everett and J. Puschell, Space Mission Engineering: The New SMAD. Hawthorne, CA: Microcosm Press,
2011.
• [12] C. Gustafson and S. Janson, 'Think Big, Fly Small', Crosslink, 2014.
• [13] NASA Ames Research Center, 'Small Spacecraft Technology State of the Art', NASA Center for AeroSpace Information,
2014.
• [14] Canisterized Satellite Dispenser (CSD) Data Sheet, 1st ed. Planetary Systems Corporation, 2015. [Online]. Available at:
http://www.planetarysystemscorp.com/web/wp-content/uploads/2015/08/2002337C-CSD-Data-Sheet.pdf [Accessed 31
October 2015]
• [15] W. Holemans, 'Lunar Water Distribution (LWaDi)-- a 6U Lunar Orbiting spacecraft SSC14-WK-22', 11th Annual
Summer CubeSat Developers' Workshop, 2014. [Online]. Available at: http://www.planetarysystemscorp.com/web/wp-
content/uploads/2014/09/Lunar-Water-Distribution-LWaDi-a-6U-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].
• [17] Aerojet Rocketdyne, 'MPS-160™ Solar Electric Power / Solar Electric Propulsion System', 2015. [Online]. Available:
http://www.rocket.com/cubesat/mps-160 [Accessed: 01- Nov- 2015].
• [18] Propulsion Unit for CubeSats (PUC), 1st ed. VACCO Industries, 2015. [Online]. Available:
http://www.vacco.com/images/uploads/pdfs/11044000-01_PUC.pdf [Accessed: 01- Nov- 2015].
• [19] ARTEMIS Space, 'ARTEMIS Lunar Constellation', 2014. [Online]. Available: http://www.artemis-space.com/artemis-
lunar-constellation/ [Accessed: 01- Nov- 2015].
• [20] P. Dyches, 'JPL Selects Europa CubeSat Proposals for Study', NASA JPL News, 2014. [Online]. Available:
http://www.jpl.nasa.gov/news/news.php?feature=4330 [Accessed: 01- Nov- 2015].
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33. References
• [21] D. Spence, E. Ehrbar, N. Rosenblad, N. Demmons, T. Roy, S. Hoffman, D. Williams, V. Hruby and C.
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=additional
[Accessed: 01- Nov- 2015].
• [22] Busek 100uN-Class Electrospray Thrusters, 1st ed. Busek Co., Inc., 2015. [Online]. Available:
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].
• [24] L. Johnson, Solar Sail Propulsion for Interplanetary Small Spacecraft, 1st ed. NASA, 2015. [Online]. 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:
http://www.kiss.caltech.edu/study/adaptiveII/Kiss%202015%20Workshop%20JPF%20TE%20Brief%20rev1.pdf
[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:
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20150015511.pdf [Accessed: 01- Nov- 2015].
• [27] R. Hodges, 'ISARA: Integrated Solar Array Reflectarray Mission Overview', CubeSat Developers Workshop at
the Small Satellite Conference, 2013. [Online]. Available:
http://digitalcommons.usu.edu/cgi/viewcontent.cgi?filename=0&article=2877&context=smallsat&type=additional
[Accessed: 01- Nov- 2015].
4/9/2016 Applying Systems Engineering Process to
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34. References
• [28] M. Aherne, J. Barrett, L. Hoag, E. Teegarden and R. Ramadas, Aeneas -- Colony I Meets Three-Axis
Pointing, 1st ed. Marina del Rey, CA: Space Engineering Research Center, 2011. [Online]. Available:
http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=1181&context=smallsat [Accessed: 01- Nov- 2015].
• [29] Messenger.jhuapl.edu, 'MESSENGER: MErcury Surface, Space ENvironment, GEochemistry, and
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:
http://messenger.jhuapl.edu/the_mission/mission_design.html [Accessed: 01- Nov- 2015].
• [32] Messenger.jhuapl.edu, 'MESSENGER: MErcury Surface, Space ENvironment, GEochemistry, and
Ranging - The Payload Instruments', 2015. [Online]. Available:
http://messenger.jhuapl.edu/instruments/index.html [Accessed: 01- Nov- 2015].
• [33] Messenger.jhuapl.edu, 'MESSENGER: MErcury Surface, Space ENvironment, GEochemistry, and
Ranging - Working from Orbit', 2015. [Online]. Available: http://messenger.jhuapl.edu/the_mission/orbit.html
[Accessed: 01- Nov- 2015].
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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
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37. CubeSat Mission Types By Year
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NumberLaunched
Year
38. Ground Segment
JPL’s Space Flight
Operations Facility Deep Space Network
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(Source: NASA/JPL-Caltech)
39. Launch Segment
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• 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.
Images Source: Planetary Systems Corporation
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
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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
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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.
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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
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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
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45. Propulsion Subsystem
Driving Requirements
• Distance to destination
• Fuel
– Influence on weight and size
• High performance less weight
• Spacecraft lifetime of 8 years
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46. Proposed Payload
Block Diagram
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Infrared
Spectrometer
Laser Altimeter
Command & Data Handling Subsystem
Commands Commands DataData
47. Proposed Electrical Power Subsystem
Block Diagram
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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)
48. Proposed Communication Subsystem
Block Diagram
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Command & Data
Handling
Subsystem
X-Band
Transpond
er
Deployable
High Gain
Antenna
Commands
Telemetry Inputs Mission Data
Commands
from Earth
49. Proposed ADCS Block
Diagram
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On-Board Computer
ADCS Function
Sun
Sensors
Star
Trackers
Attitude
Determination
Attitude
Control
Reaction
Wheels
IMU
Thrusters
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50. Proposed Propulsion Subsystem
Block Diagram
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Ionic
Liquid
Propellant
Flow Control
Valve
Electrospray Thrusters
Command &
Data Handling
Subsystem
51. Diagram of Proposed
Thermal Control Subsystem
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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
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
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