This document summarizes research into using momentum exchange and electrodynamic tethers to provide propellantless boosts between orbits. It describes two types of tether boost facilities - one that uses momentum exchange to toss payloads into higher orbits, and one that uses electrodynamic thrusting to reboost the tether system orbit. The research aims to develop reusable tether transport systems as an alternative to chemical propulsion for cislunar and interplanetary cargo delivery. Initial designs are presented for 5 metric ton payload tether boost facilities in low Earth orbit.
Conceptual design and architecture of turkish communication satellite turksat...Atılay Mayadağ
The document provides preliminary design details for the TURKSAT 6A satellite mission. Key points include:
- The satellite will operate in GEO at 42° East longitude and be able to function in an 8° inclined orbit. It must be able to de-orbit to at least 350km above GEO by end of mission.
- Two orbital transfer scenarios are considered: bi-elliptic transfer or Hohmann transfer. Orbital calculations are provided.
- The communication payload will include 16 active Ku-band transponders, 2 active X-band transponders, and telemetry transmitters. Mass and power budgets are estimated.
- An Ariane 5 ECA launcher is proposed to deliver the
Indian Space Transportation Systems : Present and Future ScenariosKurup Kurup
The document discusses India's space transportation system, including its present capabilities and future directions. It provides an overview of India's rocket development since 1963, including the SLV, ASLV, PSLV and GSLV launch vehicles. The PSLV and GSLV are described in more detail, along with their configurations and payloads. Future plans include developing an indigenous cryogenic upper stage for GSLV and the heavier lift GSLV MkIII rocket. The Chandrayaan-1 lunar mission is summarized, and India's orbital capabilities to Mars, Venus and asteroids are shown. Reusable launch vehicle technologies and India's human spaceflight program are also outlined.
Payload Mass Improvements of Supersonic Retropropulsive Flight for Human Clas...Max Fagin
Supersonic retropropulsion (SRP) is the use of retrorockets to decelerate during atmospheric flight while the vehicle is still traveling in the supersonic/hypersonic flight regime. In the context of Mars exploration, subsonic retropropulsion has a robust flight heritage for terminal landing guidance and control, but all supersonic deceleration has, to date, been performed by non-propulsive (i.e. purely aerodynamic) methods, such as aeroshells and parachutes.
Extending the use of retropropulsion from the subsonic to the supersonic regime has been identified as an enabling technology for high mass humans-to-Mars architectures.
However, supersonic retropropulsion still possess significant design and control challenges, stemming mainly from the complex interactions between the hypersonic engine plumes, the oncoming airflow, and the vehicle’s exterior surface. These interactions lead to flow fields that are difficult to model and produce counterintuitive behaviors that are not present in purely propulsive or purely aerodynamic flight.
This study will provide an overview of the work done in the design of SRP systems. Optimal throttle laws for certain trajectories will be derived that leverage aero/propulsive effects to decrease propellant requirements and increase total useful landing mass. A study of the mass savings will be made for a 10 mT reference vehicle based on a propulsive version of the Orion capsule, followed by the 100 mT ellipsoid vehicle assumed by NASA’s Mars Design Reference Architecture.
The document describes a proposed Integrated Structural Electrodynamic Propulsion (ISEP) system that uses rigid booms with integrated conductors to generate thrust via Lorentz forces without consuming propellant. Short, 100m booms could carry high currents of 100A to provide comparable thrust to longer 10km tethers. The system could enable modular, self-assembling spacecraft. A technology demonstration on a picosatellite aims to generate measurable torque and thrust pulses by driving 1A currents through 10-20m booms. If successful, ISEP could provide propulsion and structure for applications like space tugs, refueling stations, and large structures.
The mission aims to map space debris in low Earth orbit between 1,000-3,000 km using 6 small satellites. Each satellite will use an infrared camera to image debris and calculate its orbit. The satellites will be placed in 3 evenly spaced orbital planes by a Delta II rocket and slowly lower their orbits over 30 days to map the entire region. Their design emphasizes modularity for low cost and mass, using commercial off-the-shelf components, with a focus on thermal control, power, communications and orbital maneuvering systems to complete the debris mapping mission.
The document summarizes a meeting discussing the Hypersonic Airplane Space Tether Orbital Launch (HASTOL) system. It describes the HASTOL concept, hypersonic vehicle, trajectory analysis results, tether design considerations, and concludes that the HASTOL system could deliver payloads to space with minimal rocket propulsion by using high-strength tethers and existing materials can withstand required thermal loads for the tether design.
Mars CubeSat Telecom Relay Constellation_JPL FinalRohan Deshmukh
The document proposes a 4-CubeSat constellation in Mars orbit to augment telecommunications relay capabilities for surface assets. The CubeSats would be deployed from a 2022 Mars Telecom Orbiter into a 350 km circular orbit with 70 degree inclination. Each 6U CubeSat would carry an IRIS transponder, Ka-band reflectarray antenna, and UHF antennas to provide direct-to/from-Earth relay and cross-link relay with orbiters. Analysis showed the design could meet power and propulsion requirements to operate for two Mars years.
MAGIA satellite. Experimental Astronomy (8 December 2010), pp. 1-20Stefano Coltellacci
The document describes the MAGIA satellite mission, which aims to study the Moon's internal structure, polar regions, and exosphere. The satellite will carry a suite of instruments including cameras, an altimeter, particle detectors, and accelerometers. It will be launched via Soyuz rocket into a lunar transfer orbit, then enter a polar mapping orbit for 6 months before transitioning to a gravity science orbit. Key challenges include meeting tight budget constraints while achieving ambitious science goals and accommodating multiple payloads and propulsion systems for orbital maneuvers.
Conceptual design and architecture of turkish communication satellite turksat...Atılay Mayadağ
The document provides preliminary design details for the TURKSAT 6A satellite mission. Key points include:
- The satellite will operate in GEO at 42° East longitude and be able to function in an 8° inclined orbit. It must be able to de-orbit to at least 350km above GEO by end of mission.
- Two orbital transfer scenarios are considered: bi-elliptic transfer or Hohmann transfer. Orbital calculations are provided.
- The communication payload will include 16 active Ku-band transponders, 2 active X-band transponders, and telemetry transmitters. Mass and power budgets are estimated.
- An Ariane 5 ECA launcher is proposed to deliver the
Indian Space Transportation Systems : Present and Future ScenariosKurup Kurup
The document discusses India's space transportation system, including its present capabilities and future directions. It provides an overview of India's rocket development since 1963, including the SLV, ASLV, PSLV and GSLV launch vehicles. The PSLV and GSLV are described in more detail, along with their configurations and payloads. Future plans include developing an indigenous cryogenic upper stage for GSLV and the heavier lift GSLV MkIII rocket. The Chandrayaan-1 lunar mission is summarized, and India's orbital capabilities to Mars, Venus and asteroids are shown. Reusable launch vehicle technologies and India's human spaceflight program are also outlined.
Payload Mass Improvements of Supersonic Retropropulsive Flight for Human Clas...Max Fagin
Supersonic retropropulsion (SRP) is the use of retrorockets to decelerate during atmospheric flight while the vehicle is still traveling in the supersonic/hypersonic flight regime. In the context of Mars exploration, subsonic retropropulsion has a robust flight heritage for terminal landing guidance and control, but all supersonic deceleration has, to date, been performed by non-propulsive (i.e. purely aerodynamic) methods, such as aeroshells and parachutes.
Extending the use of retropropulsion from the subsonic to the supersonic regime has been identified as an enabling technology for high mass humans-to-Mars architectures.
However, supersonic retropropulsion still possess significant design and control challenges, stemming mainly from the complex interactions between the hypersonic engine plumes, the oncoming airflow, and the vehicle’s exterior surface. These interactions lead to flow fields that are difficult to model and produce counterintuitive behaviors that are not present in purely propulsive or purely aerodynamic flight.
This study will provide an overview of the work done in the design of SRP systems. Optimal throttle laws for certain trajectories will be derived that leverage aero/propulsive effects to decrease propellant requirements and increase total useful landing mass. A study of the mass savings will be made for a 10 mT reference vehicle based on a propulsive version of the Orion capsule, followed by the 100 mT ellipsoid vehicle assumed by NASA’s Mars Design Reference Architecture.
The document describes a proposed Integrated Structural Electrodynamic Propulsion (ISEP) system that uses rigid booms with integrated conductors to generate thrust via Lorentz forces without consuming propellant. Short, 100m booms could carry high currents of 100A to provide comparable thrust to longer 10km tethers. The system could enable modular, self-assembling spacecraft. A technology demonstration on a picosatellite aims to generate measurable torque and thrust pulses by driving 1A currents through 10-20m booms. If successful, ISEP could provide propulsion and structure for applications like space tugs, refueling stations, and large structures.
The mission aims to map space debris in low Earth orbit between 1,000-3,000 km using 6 small satellites. Each satellite will use an infrared camera to image debris and calculate its orbit. The satellites will be placed in 3 evenly spaced orbital planes by a Delta II rocket and slowly lower their orbits over 30 days to map the entire region. Their design emphasizes modularity for low cost and mass, using commercial off-the-shelf components, with a focus on thermal control, power, communications and orbital maneuvering systems to complete the debris mapping mission.
The document summarizes a meeting discussing the Hypersonic Airplane Space Tether Orbital Launch (HASTOL) system. It describes the HASTOL concept, hypersonic vehicle, trajectory analysis results, tether design considerations, and concludes that the HASTOL system could deliver payloads to space with minimal rocket propulsion by using high-strength tethers and existing materials can withstand required thermal loads for the tether design.
Mars CubeSat Telecom Relay Constellation_JPL FinalRohan Deshmukh
The document proposes a 4-CubeSat constellation in Mars orbit to augment telecommunications relay capabilities for surface assets. The CubeSats would be deployed from a 2022 Mars Telecom Orbiter into a 350 km circular orbit with 70 degree inclination. Each 6U CubeSat would carry an IRIS transponder, Ka-band reflectarray antenna, and UHF antennas to provide direct-to/from-Earth relay and cross-link relay with orbiters. Analysis showed the design could meet power and propulsion requirements to operate for two Mars years.
MAGIA satellite. Experimental Astronomy (8 December 2010), pp. 1-20Stefano Coltellacci
The document describes the MAGIA satellite mission, which aims to study the Moon's internal structure, polar regions, and exosphere. The satellite will carry a suite of instruments including cameras, an altimeter, particle detectors, and accelerometers. It will be launched via Soyuz rocket into a lunar transfer orbit, then enter a polar mapping orbit for 6 months before transitioning to a gravity science orbit. Key challenges include meeting tight budget constraints while achieving ambitious science goals and accommodating multiple payloads and propulsion systems for orbital maneuvers.
Satellite communication involves transmitting signals between a sender and receiver using a satellite. The signal is sent to the satellite, which amplifies it and sends it back to the receiver on Earth. Johannes Kepler formulated laws concerning planetary motion, including that planets orbit the sun in ellipses. GSAT-16 is an Indian communication satellite launched in 2014 carrying 48 transponders across C-band, Extended C-band, and Ku-band frequencies to provide continuity of communication services.
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.
The document discusses electromagnetic formation flight (EMFF) as an alternative to traditional spacecraft propulsion. EMFF uses electromagnetic forces and reaction wheels, instead of propellant, to control the relative positions and orientations of spacecraft in a cluster formation. It proposes using electromagnetic dipoles to generate the necessary inter-spacecraft forces and torques for full controllability. Disturbance rejection from gravitational effects and managing excess angular momentum buildup are challenges that EMFF would need to address for practical applications such as the Terrestrial Planet Finder mission.
The document summarizes the design of an unmanned cargo transportation system called Major Tom that will deliver materials from low Earth orbit to the lunar surface in support of a lunar base. Major Tom consists of an ion propulsion engine, a cargo capsule, and a lunar lander. The ion engine and lander will launch together on a Falcon 9 Heavy rocket and rendezvous with multiple cargo capsules launched separately. Using ion propulsion, the combined vehicle will travel to the moon within 158 days and deliver 18 metric tons of cargo. The cargo capsules and lunar lander are designed with reusability in mind to support ongoing cargo deliveries.
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 proposed concept for a constellation of 4 CubeSats in Mars orbit to augment communication relay capabilities for assets on the Martian surface and in orbit. Key aspects of the concept include using the CubeSats to relay data between landed assets and orbiters using UHF bands, and between the CubeSats and Earth using Ka-band. Mass and power budgets have been analyzed to demonstrate the feasibility of the concept. Future work areas are identified such as further analyzing data volume, thermal, trajectory, and cost aspects.
The document discusses plans for developing tether boost facilities to enable in-space transportation. Key points include:
1) Tether Unlimited is developing technologies like electrodynamic tethers and momentum exchange to provide propellantless propulsion beyond low Earth orbit using tether boost facilities.
2) Facilities would use tethers up to 100km long to boost payloads from LEO to destinations like the Moon and Mars in rapid transfer times of 5 days and 90 days respectively.
3) An incremental development path is proposed starting with demonstrating technologies on suborbital and LEO missions before building operational tether boost facilities to GEO, the Moon, and Mars.
Orbit design for exoplanet discovery spacecraft dr dora musielak 1 april 2019Dora Musielak, Ph.D.
Most exoplanets have been discovered with space telescopes. Starting with an overview of rocket propulsion, this presentation introduces spacecraft trajectories in the Sun-Earth-Moon System, focusing especially on those appropriate for exoplanet detection spacecraft. It reviews past, present, and future exoplanet discovery missions.
Spacecraft orbits for exoplanets discovery lecture dr dora musielak 11 june 2021Dora Musielak, Ph.D.
The document discusses spacecraft propulsion and orbit design for exoplanet research missions. It describes how rocket science supports exoplanet science by enabling the launch and precise orbital placement of space telescopes. Key concepts discussed include chemical rocket propulsion, the rocket equation, orbital mechanics, and the restricted three-body problem. Specific missions mentioned include TESS, Kepler, JWST, and Roman, with details provided on their launch vehicles and orbits chosen to fulfill their exoplanet discovery goals.
Galileo concept of operations, first iov leop and initial operationsMarco Lisi
Presentation at the SpaceOps conference in Stockolm, June 2012, about the first launch of Galileo satellites.
Galileo is the European global navigation satellite system (GNSS), funded by the European Commission and developed by the European Space Agency.
This document discusses using Coulomb forces for controlling spacecraft swarms by charging the spacecraft to different voltages. It finds that Coulomb forces can be comparable to state-of-the-art electric thrusters. Analysis shows stable orbital configurations exist for formations of 3 or 5 spacecraft oriented in different ways and separated by around 10 meters. Ongoing work includes examining formation stability, developing dynamic simulations, and formulating control laws to further explore using Coulomb forces for precision formation flying and space-based interferometry missions.
This document summarizes a presentation on the Hypersonic Airplane Space Tether Orbital Launch (HASTOL) study. Phase I demonstrated the feasibility of using a hypersonic airplane to carry payloads to an altitude of 100 km where they would rendezvous with a rotating tether tip for orbital insertion. Phase II plans further analysis and technology development, including simulations, cost modeling, and identifying near-term demonstrations to reduce risk for a potential prototype system. The goal is a reusable launch system using a hypersonic aircraft and electrodynamic tether to provide low-cost access to space.
Is there Life on Mars? a Sample Return Mission ConceptToni Engelhardt
Conception of a hypothetic sample-return mission to Mars and calculation of the Δv-requirement. Matlab simulation of a Hohmann trajectory, staging optimisation and selection of a suitable launcher.
Matlab source files: http://bit.ly/1gA1J5R
This document discusses research using Bayesian optimization to determine effective locomotion techniques for tensegrity robots. The researchers developed code to control vibrating motors on a tensegrity robot and track its movement. Bayesian optimization was used to attempt to find optimal vibration frequencies that produced fast, straight movement of the robot. Several frequency sets were found that resulted in rapid straight movement, but further investigation is needed to confirm Bayesian optimization is the best approach for tensegrity locomotion learning.
The document provides information on seismic cone penetration testing (SCPT), including:
1) SCPT allows for continuous profiling of soil strength (qc), sleeve friction (fs), pore pressure (u), and shear wave velocity (Vs), providing a direct measure of small-strain soil stiffness.
2) Vs is used to estimate fundamental soil parameters like small-strain shear modulus (Go), peak friction angle, and undrained shear strength, and to evaluate soil liquefaction potential.
3) While most research focuses on young uncemented soils, SCPT can also help characterize "unusual" soils like stiff fissured clays, soft rock, and man-made soils that are under-represented
The document summarizes the efforts to reboot and regain control of the decommissioned ISEE-3 spacecraft from 2014-2016. A team of amateur radio operators and scientists were able to reestablish communication with ISEE-3 and receive telemetry, but were unsuccessful in their attempts to perform trajectory correction maneuvers due to issues with the spacecraft's propulsion system. The mission was transitioned to collecting additional science data before ISEE-3's orbit takes it out of communication range again.
This document outlines an aircraft maintenance system including a Gantt chart showing the project timeline, an entity relationship diagram modeling the data, and user interface wireframes for checking aircraft status and ordering repair parts.
Bloom energy- Post your mail ID in comment box for the PPT\DocumentLova Raju Balam
INTRODUCTION:-
All the world scientists are in a search for the technology that provides a cleaner, more reliable, and more affordable alternative to both today’s electric grid as well as traditional renewable energy sources. They want the technology to provide distributed power generation, allowing customers to efficiently create their own electricity onsite.
It must be built using abundant and affordable materials. The technology must be fundamentally different from the legacy traditional technologies and most people must become familiar with it.
Technology must be distinct ways like:
1. Low cost materials –Must use a low cost metal instead of precious metals.
2. High electrical efficiency – Must convert fuel into electricity at nearly twice the rate of some legacy technologies.
3. Fuel flexibility –Systems must be capable of using either renewable or fossil fuels
4. Reversible –Technology must be capable of both energy generation and storage
DISTRIBUTED GENERATION:-
Distributed generation (DG) refers to power generation at the point of consumption. Generating power on-site, rather than centrally, eliminates the cost, complexity, interdependencies, and inefficiencies associated with transmission and distribution. Distributed generation shifts control to the consumer. The World Needs Distributed Generation that is Clean and Continuous. Historically, distributed generation meant combustion generators (e.g. diesel generators). They must be affordable, and in some cases reliable and clean. While many people will tolerate dirty generation thousands of miles away from them, they think twice when it is outside their bedroom window or office door.
Recently, solar has become a popular distributed generation option. Although the output is clean it is also intermittent, making it an incomplete strategy for businesses that need power around the clock, including when the sun is not shining.
AN IDEA:-
Bloom Box was developed by California based company named Bloom Energy started by Indian K R Sridhar. He completed his degree in Mechanical Engineering from NIT Trichy and moved to US in 1980s. He completed his master’s degree in Nuclear Engineering and PhD in Mechanical Engineering from the University of Illinois, Urbana-Champaign. He started Bloom Energy in 2002. Prior to founding Bloom Energy, Dr. KR Sridhar was Director of the Space Technologies Laboratory (STL) NASA and at the University of Arizona where he was also a professor of Aerospace and Mechanical Engineering.
In October 2001, K.R Sridhar C.E.O of BLOOM ENERGY had a meeting with John Doerr from the large venture capital firm. Sridhar was asking for more than $100 million to start the company BLOOM ENERGY. But BLOOM ENERGY has received $400 million of start-up funding
from venture capitalists.
Satellite communication involves transmitting signals between a sender and receiver using a satellite. The signal is sent to the satellite, which amplifies it and sends it back to the receiver on Earth. Johannes Kepler formulated laws concerning planetary motion, including that planets orbit the sun in ellipses. GSAT-16 is an Indian communication satellite launched in 2014 carrying 48 transponders across C-band, Extended C-band, and Ku-band frequencies to provide continuity of communication services.
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.
The document discusses electromagnetic formation flight (EMFF) as an alternative to traditional spacecraft propulsion. EMFF uses electromagnetic forces and reaction wheels, instead of propellant, to control the relative positions and orientations of spacecraft in a cluster formation. It proposes using electromagnetic dipoles to generate the necessary inter-spacecraft forces and torques for full controllability. Disturbance rejection from gravitational effects and managing excess angular momentum buildup are challenges that EMFF would need to address for practical applications such as the Terrestrial Planet Finder mission.
The document summarizes the design of an unmanned cargo transportation system called Major Tom that will deliver materials from low Earth orbit to the lunar surface in support of a lunar base. Major Tom consists of an ion propulsion engine, a cargo capsule, and a lunar lander. The ion engine and lander will launch together on a Falcon 9 Heavy rocket and rendezvous with multiple cargo capsules launched separately. Using ion propulsion, the combined vehicle will travel to the moon within 158 days and deliver 18 metric tons of cargo. The cargo capsules and lunar lander are designed with reusability in mind to support ongoing cargo deliveries.
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 proposed concept for a constellation of 4 CubeSats in Mars orbit to augment communication relay capabilities for assets on the Martian surface and in orbit. Key aspects of the concept include using the CubeSats to relay data between landed assets and orbiters using UHF bands, and between the CubeSats and Earth using Ka-band. Mass and power budgets have been analyzed to demonstrate the feasibility of the concept. Future work areas are identified such as further analyzing data volume, thermal, trajectory, and cost aspects.
The document discusses plans for developing tether boost facilities to enable in-space transportation. Key points include:
1) Tether Unlimited is developing technologies like electrodynamic tethers and momentum exchange to provide propellantless propulsion beyond low Earth orbit using tether boost facilities.
2) Facilities would use tethers up to 100km long to boost payloads from LEO to destinations like the Moon and Mars in rapid transfer times of 5 days and 90 days respectively.
3) An incremental development path is proposed starting with demonstrating technologies on suborbital and LEO missions before building operational tether boost facilities to GEO, the Moon, and Mars.
Orbit design for exoplanet discovery spacecraft dr dora musielak 1 april 2019Dora Musielak, Ph.D.
Most exoplanets have been discovered with space telescopes. Starting with an overview of rocket propulsion, this presentation introduces spacecraft trajectories in the Sun-Earth-Moon System, focusing especially on those appropriate for exoplanet detection spacecraft. It reviews past, present, and future exoplanet discovery missions.
Spacecraft orbits for exoplanets discovery lecture dr dora musielak 11 june 2021Dora Musielak, Ph.D.
The document discusses spacecraft propulsion and orbit design for exoplanet research missions. It describes how rocket science supports exoplanet science by enabling the launch and precise orbital placement of space telescopes. Key concepts discussed include chemical rocket propulsion, the rocket equation, orbital mechanics, and the restricted three-body problem. Specific missions mentioned include TESS, Kepler, JWST, and Roman, with details provided on their launch vehicles and orbits chosen to fulfill their exoplanet discovery goals.
Galileo concept of operations, first iov leop and initial operationsMarco Lisi
Presentation at the SpaceOps conference in Stockolm, June 2012, about the first launch of Galileo satellites.
Galileo is the European global navigation satellite system (GNSS), funded by the European Commission and developed by the European Space Agency.
This document discusses using Coulomb forces for controlling spacecraft swarms by charging the spacecraft to different voltages. It finds that Coulomb forces can be comparable to state-of-the-art electric thrusters. Analysis shows stable orbital configurations exist for formations of 3 or 5 spacecraft oriented in different ways and separated by around 10 meters. Ongoing work includes examining formation stability, developing dynamic simulations, and formulating control laws to further explore using Coulomb forces for precision formation flying and space-based interferometry missions.
This document summarizes a presentation on the Hypersonic Airplane Space Tether Orbital Launch (HASTOL) study. Phase I demonstrated the feasibility of using a hypersonic airplane to carry payloads to an altitude of 100 km where they would rendezvous with a rotating tether tip for orbital insertion. Phase II plans further analysis and technology development, including simulations, cost modeling, and identifying near-term demonstrations to reduce risk for a potential prototype system. The goal is a reusable launch system using a hypersonic aircraft and electrodynamic tether to provide low-cost access to space.
Is there Life on Mars? a Sample Return Mission ConceptToni Engelhardt
Conception of a hypothetic sample-return mission to Mars and calculation of the Δv-requirement. Matlab simulation of a Hohmann trajectory, staging optimisation and selection of a suitable launcher.
Matlab source files: http://bit.ly/1gA1J5R
This document discusses research using Bayesian optimization to determine effective locomotion techniques for tensegrity robots. The researchers developed code to control vibrating motors on a tensegrity robot and track its movement. Bayesian optimization was used to attempt to find optimal vibration frequencies that produced fast, straight movement of the robot. Several frequency sets were found that resulted in rapid straight movement, but further investigation is needed to confirm Bayesian optimization is the best approach for tensegrity locomotion learning.
The document provides information on seismic cone penetration testing (SCPT), including:
1) SCPT allows for continuous profiling of soil strength (qc), sleeve friction (fs), pore pressure (u), and shear wave velocity (Vs), providing a direct measure of small-strain soil stiffness.
2) Vs is used to estimate fundamental soil parameters like small-strain shear modulus (Go), peak friction angle, and undrained shear strength, and to evaluate soil liquefaction potential.
3) While most research focuses on young uncemented soils, SCPT can also help characterize "unusual" soils like stiff fissured clays, soft rock, and man-made soils that are under-represented
The document summarizes the efforts to reboot and regain control of the decommissioned ISEE-3 spacecraft from 2014-2016. A team of amateur radio operators and scientists were able to reestablish communication with ISEE-3 and receive telemetry, but were unsuccessful in their attempts to perform trajectory correction maneuvers due to issues with the spacecraft's propulsion system. The mission was transitioned to collecting additional science data before ISEE-3's orbit takes it out of communication range again.
This document outlines an aircraft maintenance system including a Gantt chart showing the project timeline, an entity relationship diagram modeling the data, and user interface wireframes for checking aircraft status and ordering repair parts.
Bloom energy- Post your mail ID in comment box for the PPT\DocumentLova Raju Balam
INTRODUCTION:-
All the world scientists are in a search for the technology that provides a cleaner, more reliable, and more affordable alternative to both today’s electric grid as well as traditional renewable energy sources. They want the technology to provide distributed power generation, allowing customers to efficiently create their own electricity onsite.
It must be built using abundant and affordable materials. The technology must be fundamentally different from the legacy traditional technologies and most people must become familiar with it.
Technology must be distinct ways like:
1. Low cost materials –Must use a low cost metal instead of precious metals.
2. High electrical efficiency – Must convert fuel into electricity at nearly twice the rate of some legacy technologies.
3. Fuel flexibility –Systems must be capable of using either renewable or fossil fuels
4. Reversible –Technology must be capable of both energy generation and storage
DISTRIBUTED GENERATION:-
Distributed generation (DG) refers to power generation at the point of consumption. Generating power on-site, rather than centrally, eliminates the cost, complexity, interdependencies, and inefficiencies associated with transmission and distribution. Distributed generation shifts control to the consumer. The World Needs Distributed Generation that is Clean and Continuous. Historically, distributed generation meant combustion generators (e.g. diesel generators). They must be affordable, and in some cases reliable and clean. While many people will tolerate dirty generation thousands of miles away from them, they think twice when it is outside their bedroom window or office door.
Recently, solar has become a popular distributed generation option. Although the output is clean it is also intermittent, making it an incomplete strategy for businesses that need power around the clock, including when the sun is not shining.
AN IDEA:-
Bloom Box was developed by California based company named Bloom Energy started by Indian K R Sridhar. He completed his degree in Mechanical Engineering from NIT Trichy and moved to US in 1980s. He completed his master’s degree in Nuclear Engineering and PhD in Mechanical Engineering from the University of Illinois, Urbana-Champaign. He started Bloom Energy in 2002. Prior to founding Bloom Energy, Dr. KR Sridhar was Director of the Space Technologies Laboratory (STL) NASA and at the University of Arizona where he was also a professor of Aerospace and Mechanical Engineering.
In October 2001, K.R Sridhar C.E.O of BLOOM ENERGY had a meeting with John Doerr from the large venture capital firm. Sridhar was asking for more than $100 million to start the company BLOOM ENERGY. But BLOOM ENERGY has received $400 million of start-up funding
from venture capitalists.
Bloom Energy server as a whole the individual aspects of the technical ,economical , and social implications together. Additionally it needs to be compared to other equivalent renewable technologies.
Wi-Vi is a device that uses Wi-Fi signals to identify people, their locations, and motions behind walls. It operates in two modes: one to image and track moving objects, and another for gesture-based communication without transmitters. Wi-Vi eliminates flash reflections using interference nulling between transmit and receive antennas. It tracks humans using inverse synthetic aperture radar as they sample the signal at different locations, emulating an antenna array. Gestures like stepping forward or backward encode bits to allow hidden communication. Wi-Vi showed accurate detection up to 5 meters away.
This document discusses electrodynamic tethers, which use the Lorentz force generated by the interaction between a current in the tether and the Earth's magnetic field to propel or deorbit spacecraft. Electrodynamic tethers can be used to accelerate a spacecraft into a higher orbit or decelerate it into a lower orbit without using propellant. They work by either collecting electrons at one end of the tether and expelling them at the other end, or driving current in the opposite direction. Challenges include stabilizing the tether's motion, but feedback algorithms can help maintain stability. Potential applications include propulsion of spacecraft in low Earth orbit, deorbiting of satellites, and reboosting of decaying orbits.
Nano solar cells utilize tiny nanorods or nanoparticles to convert sunlight into electricity in a thin, inexpensive layer. These dye-sensitized or "nano" solar cells consist of a thin layer of nanorods dispersed in a polymer that can be easily mass produced. While efficiency is still low, nano solar cells have potential for low-cost electricity generation due to inexpensive manufacturing using solution-based coating or printing techniques.
This document provides an introduction to various web technologies including HTML, CSS, JavaScript, and PHP. It discusses the basic structures and components of HTML documents, how CSS can be used to style HTML content, and how JavaScript and PHP can add interactivity and run server-side code. The document also gives examples of common tags and syntax used in these languages. It concludes by noting that most web pages combine these core technologies and that learning them now provides a foundation for newer technologies.
The document describes the development of an artificial retina using thin-film transistors (TFTs) that can be implanted in the back of the human eye. The artificial retina contains photo sensors and circuits integrated on a flexible substrate using poly-silicon TFTs. It receives wireless power through inductive coupling between an external coil and an internal receiving coil embedded in the eye. The artificial retina is aimed at restoring vision by stimulating the retina with an array of pixels that output different voltages based on light levels detected by phototransistors.
The document provides an overview and design details for a next generation strategic military transport aircraft called the UR1T. Key points discussed include:
- The UR1T is designed to improve payload transportation capabilities and reduce loading/unloading times compared to the current fleet.
- Design aspects covered include the wing, engines, fuel system, payload integration, and flight envelope. Aerodynamic analyses were performed to determine wing and tail sizing.
- The UR1T is designed to carry a maximum payload of 300,000 lbs with a range of 1,800 nm at a cruise speed of Mach 0.75 and altitude of 30,000 ft.
- Payload integration focuses on fitting standard 463
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This document proposes concepts and technologies for counterspace operations in 2025, including space detection, anti-satellite weapons, space interdiction nets, miniaturized satellites, satellite cloaking, kinetic and directed energy weapons. It outlines offensive and defensive counterspace architectures and recommends further analysis of miniaturization, stealth, detection and targeting concepts as well as kinetic and directed energy weapons. The goal is to maintain US space superiority as space becomes increasingly vital to national security and more countries and commercial entities access space.
1. Tether Boost Facilities for
In-Space Transportation
Robert P. Hoyt, Robert L. Forward
Tethers Unlimited, Inc.
1917 NE 143rd St., Seattle, WA 98125-3236
+1-206-306-0400 fax -0537
TU@tethers.com www.tethers.com
John Grant, Mike Bangham, Brian Tillotson
The Boeing Company
5301 Bolsa Ave., Huntington Beach, CA 92647-2099
(714) 372-5391
2. TUI/MMOSTT 2
NIAC Funded Tether Research
¥ Moon & Mars Orbiting Spinning Tether Transport (MMOSTT)
¥ Hypersonic Airplane Space Tether Orbital Launch (HASTOL)
¥ Objectives:
Ð Perform Technical & Economic Analysis of Tether Transport Systems
Ð Identify Technology Needs
Ð Develop Conceptual Design Solutions
Ð Prepare for Technology Development Efforts and Flight Experiments
to Demonstrate Tether Transport Technology
3. TUI/MMOSTT 3
Momentum-Exchange
Tether Boost Facility
¥ High-strength tether rotates around orbiting control station
¥ Tether picks payload up from lower orbit and tosses payload into higher orbit
¥ Tether facility gives some of its orbital momentum & energy to payload
¥ Tether facility orbit must be restored to enable it to toss additional payloads
4. TUI/MMOSTT 4
Electrodynamic Reboost
Magnetic Field
Thrust Current
Plasma Contactors
(Hollow Cathode,
FEA, Bare Wire)
¥ Power supply drives current
along tether
¥ Plasma contactors exchange
current with ionosphere
¥ Plasma waves close current
ÒloopÓ
¥ Current ÒpushesÓ against
geomagnetic field via JxB
Force
5. Momentum-Exchange/Electrodynamic-Reboost Tethers:
TUI/MMOSTT 5
Summary of Advantages
¥ Tether Boost Facilities Can Provide a Fully-Reusable In-Space
Propulsion Architecture
Ð LEO Û MEO/GTO
Ð LEO Û Lunar Surface
Ð LEO Û Mars
Ð ETO Launch, in combination with Hypersonic Airplane/RLV
¥ Momentum Exchange + Electrodynamic Tether Can Enable
Propellantless Propulsion Beyond LEO
¥ Rapid Transfer Times
Ð 5 days to Moon
Ð 90-130 days to Mars
¥ Operational Tether System Can Be Tested Before Use With High-
Value Payloads
¥ Reusable Infrastructure + Low Consumables
Þ Lower Cost
6. Cislunar Tether Transport System
¥ Developed Orbital Architecture for Round Trip LEOÛLunar
Surface Transport
¥ Whole System Launch Mass = 30x Payload Mass
Ð LEO Tether Boost Facility Mass = 13x Payload Mass, Lunar Tether Facility = 17x Payload
¥ 13 Payloads/Year
¥ Incremental Commercial Development Path
TUI/MMOSTT 6
7. Rapid Earth-Mars Transport
¥ Reusable Architecture for Round Trip Earth to Mars Transport
¥ Rapid Transfer Times (90-130 days)
INTERPLANETARY TRANSPORT USING
ROTATING TETHERS
Payload pick-up
Payload release Origin
TUI/MMOSTT 7
Escape
trajectory
Interplanetary
trajectory
Destination
Inbound
trajectory
Payload release
Payload capture
Patch point
Tapered tether
Loaded Tether
Center of mass
orbit
Tapered tether
Loaded Tether
Center of mass
orbit
Patch point
Earth’s gravitational
sphere of influence
Mars’ gravitational
sphere of influence
Sol
8. MXER Tethers Included in NASAÕs
TUI/MMOSTT 8
IISTP Process
¥ NIAC Funded MMOSTT and HASTOL efforts have resulted in
Momentum-Exchange/Electrodynamic Reboost Tethers being
considered in NASAÕs In-Space Integrated Space Transportation
Planning Process
¥ TUI & NASA/MSFC developed concept designs for Tether Boost
Facilities for 4 classes of missions
Ð Microsatellite
Ð 1 mt Payloads
Ð 5 mt Payloads
Ð 10 mt Payloads
¥ IISTP Process evaluated these designs in trade studies for several
different scientific missions
¥ ÒHigh-Risk/High PayoffÓ
¥ MXER Tethers scored well for several classes of missions
Ð High Performance metric
9. TUI/MMOSTT 9
Tether Architecture for
LEO-GTO-LTO-Mars Transport
¥ Tether facility serves as transport hub for multiple destinations
¥ Tether serves as a zero-propellant, reusable, high-Isp, high thrust
ÒThird StageÓ
10. TUI/MMOSTT 10
5mt Payload Tether Boost Facility
for In-Space Transportation Architecture
¥ Reusable In-Space Transportation
Infrastructure
¥ Payload Launched to 325 km LEO
¥ Tether Boosts Payload to Elliptical Orbit
¥ Tether Uses Electrodynamic Thrust to Reboost
Tether System Point Design:
¥ Boost 10,000 kg to GTO
¥ Boost 5,000 kg Vehicle to :
Ð Highly Elliptical Orbit (C3=-1.9)
Ð Lunar Transfer Trajectory
Ð Escape Via Lunar Swingby
¥ Tether Facility Launch Mass: 63 mt
Ð Deploy using 3 Delta-IV-H LVÕs
Ð Retain Delta Upper Stages for Ballast
Ð 200 kW EOL Power Supply for 1 Month Reboost
Analysis of Other Propulsion Technologies with
MX Tether Assist:
¥ Delta-II-Class LV Launches 5,000 kg Spacecraft
¥ Tether Boosts Spacecraft to C3Ê=Ê-1.9 km2/s2
¥ High-Thrust Propulsion Systems:
Ð Do Injection Burn at Perigee (570 km, 10.62 km/s)
¥ Low-Thrust Propulsion Systems:
Ð Use Lunar Swingby to Escape EarthÕs Gravity Well
11. Net Payoff: Reduced Launch Costs
To launch 5,000 kg to GTO:
¥ Using Rockets: Delta IVM+(4,2) or SeaLaunch
TUI/MMOSTT 11
~ $90M
¥ Using Rocket to LEO, Tether Boost to GTO:
Ð Delta II 7920 (~$45M) or Dnepr 1 (~$13M)
Ø1/2 to 1/7 the launch cost
12. TUI/MMOSTT 12
LEOðGTO Boost Facility
¥ Initial Facility Sized to Boost 2500 kg Payloads to GTO
¥ First Operational Capability Can Be Launched on 1 Delta IV-H
¥ Modular Design Enables Capability to be Increased
¥ Top Level Mission Requirements:
Requirement Value
2500 kg at IOC, can grow to follow
market
Payload Mass
Pickup orbit 300 km equatorial
Release orbit GTO
Release insertion error < Delta IV/Ariane 5
Payload environment < Delta IV/Ariane 5
Turnaround time 30 days
Mission life 10 years +
Collision avoidance 100% of tracked spacecraft
Operational orbit lifetime 15 days
Payload pickup reliability 99%
13. TUI/MMOSTT 13
Mass Properties Breakdown
LEO Control Station 10967 13267 2300
Thermal Control Subsys 1 15% 1104.5 1270.1 165.7
Cabling/Harnesses 33% 749.6 997.0 247.4
Structure 25% 2721.1 3401.3 680.3
Electr.Pwr. 4736.7 5409.6 673.0
PV array panels 1 1 13% 1782.9 1782.9 2014.6
Power Storage 1 1 15% 2860.5 2860.5 3289.5
PV array drive motors 8 2 13% 3.0 48.0 54.2
PMAD 1 2 13% 22.7 45.4 51.3
Downlink Comm Subsys 1.8 2.1 0.2
Downlink Transceiver 1 2 13% 0.7 1.4 1.56
Downlink antennae 2 1 13% 0.2 0.5 0.51
TFS Net Comm Subsys 1.8 2.1 0.2
Comm. antennae 2 1 13% 0.2 0.5 0.51
Transceiver 1 2 13% 0.7 1.4 1.6
C&DH 26.0 29.4 3.4
Computer 1 2 13% 13.0 26.0 29.4
TT&C 6.9 7.8 0.9
transponder 1 2 13% 3.5 6.9 7.8
ADCS 200.9 213.8 12.9
ED Tether Power Subsys 417.4 603.4 186.0
Plasma Contactor (FEAC) 1 2 25% 45.4 90.8 113.5
PMAD/PCUt 1 2 50% 163.3 326.6 489.9
Docking & I/C Subsys 0.5 0.54 0.04
Beacon 1 1 8% 0.5 0.5 0.54
Tether Deploy & Control 1000.0 1330.0 330.00
Tether reeling assembly 1 1 33% 1000.0 1000.0 1330.0
Mass
Margin
(kg)
Mass with
Contingency
(kg)
Mass with
no margin
(kg)
Unit
mass
(kg)
Mass
Contin
gency
Redun
dancy
Qty Control Station
Mass: 10,967 kg
Tether Mass:
8,274 kg
Grapple Mass:
650 kg
GLOW: 19,891 kg
Ð 15% margin w/in Delta
IV-H payload capacity
Expended Upper Stage
3,467 kg
On-Orbit Mass:
23,358 kg
14. TUI/MMOSTT 14
Tether Boost Facility
Control Station
¥ Solar Arrays, 137 kW @ BOL
¥ Battery/Flywheel Power Storage
¥ Command & Control
¥ Tether Deployer
¥ Thermal Management
Tether (not shown to scale)
¥ Hoytether for Survivability
¥ Spectra 2000
¥ 75-100 km Long
¥ Conducting Portion for
Electrodynamic Thrusting
Total Mass:ÊÊÊÊ 23,358 kg
Payload Mass: 2,500 kg
Grapple Assembly
¥ Power, Guidance
¥ Grapple Mechanism
¥ Small Tether Deployer
Payload Accommodation
Assembly (PAA)
¥ Maneuvering & Rendezvous Capability
¥ Payload Apogee Kick Capability
Payload
15. NIAC Efforts Have Developed
Improved Tether Analysis Tools
Tether System Design:
Ð Tapered tether design
TUI/MMOSTT 15
¥ Spectra 2000
Ð Orbital mechanics considerations to
determine facility mass required
Tether operation: TetherSimª
¥ Numerical Models for:
Ð Orbital mechanics
Ð Tether dynamics
Ð Electrodynamics
Ð Hollow Cathode & FEACs
Ð Geomagnetic Field (IGRF)
Ð Plasma Density (IRI)
Ð Neutral Density (MSIS Ô90)
Ð Thermal and aero drag models
Ð Endmass Dynamics
Ð Payload Capture/Release
¥ Interface to MatLab/Satellite Tool Kit
16. TUI/MMOSTT 16
LEOðGTO Boost Facility
¥ TetherSimª Numerical Simulation (10x real speed)
Ð Tether Dynamics, Orbital Mechanics
17. TUI/MMOSTT 17
Technology Readiness Level
¥ Boeing & TUI Performed TRL Analysis of MXER Tether
Technologies
¥ Many necessary components are already at high TRL
¥ TRL Analysis Indicates Areas for Future Work to Address:
Ð Power management subsystem
Ð Thermal control subsystem
¥ Higher power than previously flown systems
Ð Electrodynamic Propulsion Subsystem
¥ Plasma contactors
¥ Dynamics control
Ð Automated Rendezvous & Capture technologies
¥ Prediction & Guidance
¥ Grapple Assembly & Payload Adapter
Ð Some work ongoing in HASTOL Ph II effort
Ð Flight Control Software
Ð Traffic Control/Collision Avoidance
18. TUI/MMOSTT 18
20
12
8
4
0
ÆZ (m)
16
-10 0 10
ÆX (m)
Rendezvous
¥ Rapid AR&C Capability Needed
¥ Relative Motion is Mostly in Local Vertical
¥ Tether Deployment Can Extend Rendezvous
Window
¥ Additional Tether Deployment Under Braking Can Reduce Shock
Loads
Payload Capture Vehicle
descends towards Payload
PCV Deploys
More Tether PCV pays out tether
and Payload maneuvers
to dock with grapple
PCV engages
tether brake and
begins to lift payload
1
0.8
0.6
0.4
0.2
0
0 10 20
Load Level
30 40 50
0.1 s braking
5 s braking
10 s braking
20 s braking
Time (s)
30 s braking
19. Space Debris-Survivable Tether
¥ Micrometeoroids & Space Debris Will
Damage Tethers
¥ Solution approach: spread tether material
out in an open net structure with multiple
redundant load/current paths
TUI/MMOSTT 19
Primary
Lines
Secondary
Lines
(initially
unstressed)
0.2 to
10's of
meters
0.1- 1 meter
Severed
Primary
Line
Effects of
Damage
Localized
Secondary
Lines
Transfer
Load Around
Damaged
Section
20. TUI/MMOSTT 20
Proposed RETRIEVE Tether
Experiment
¥ Candidate Secondary
Experiment for XSS-11
¥ $800K in Initial Development
funds from AFRL
¥ Small ED tether system deorbits
µSat at end of mission
Ð Activated only after primary
mission completed
¥ Mass: (CBE+Uncertainty):
6.5 kg
¥ Demonstrate
Ð Controlled orbital maneuvering
with ED tether
Ð Long life tether
Ð Stabilization of tether dynamics
21. µTORQUE: MX Tether to Boost µSat to
¥ Microsatellite Tethered Orbit Raising QUalification Experiment
¥ Build Upon RETRIEVE to Create Low-Cost Demo of MXER tether technology
¥ Secondary payload on GEO Sat launch
¥ µTORQUE boost microsat payload to lunar transfer or escape
¥ 0.4 km/s boost to payload
¥ Mass-competitive with chemical rocket
TUI/MMOSTT 21
Lunar Transfer or Escape
Launch vehicle
places primary
payload into GTO
µTORQUE uses ED
drag to spin up tether
µTORQUE deploys tether &
microsat above stage
µTORQUE releases
payload into lunar
transfer/swingby
22. TUI/MMOSTT 22
µTORQUE on Delta IV
¥ Delta-IV Secondary Payload
¥ ~100 kg weight allocation
¥ Boost ~80kg microsat from
LEO to low-MEO
23. Momentum Exchange/Electrodynamic Reboost
NIAC Study
ProSEDS
TUI/MMOSTT 23
Tether Technology Roadmap
GRASP
Experiment
µTORQUE
Experiment
ED-LEO Tug
µPET
LEO Û GTO
Tether Boost Facility
ISS-Reboost
Terminator
Tetherª
Cislunar Tether
Transport System
ETO-Launch
Assist Tether
RETRIEVE
2001 2003 2005 2010 2013 2016 2025 2035
24. TUI/MMOSTT 24
Opportunities for NASA
Technology Development
¥ Expand AR&C Capabilities for Rapid Capture
¥ High Power & High Voltage Space Systems
¥ Electrodynamic Tether Physics
¥ Debris & Traffic Control Issues
¥ Conduct Low-Cost Flight Demo of Momentum-
Exchange Tether Boost
Modest NASA Investment in Technology
Development Will Enable Near-Term Space
Flight Demonstration
25. TUI/MMOSTT 25
Contributors
¥ Boeing/RSS - John Grant, Jim Martin, Harv Willenberg
¥ Boeing/Seattle - Brian Tillotson
¥ Boeing/Huntsville - Mike Bangham, Beth Fleming, John Blumer,
Ben Donohue, Ronnie Lajoie, Lee Huffman
¥ NASA/MSFC - Kirk Sorenson
¥ Gerald Nordley
¥ Chauncey Uphoff