Lunar Numbat is an open source collaboration developing space technologies including rocket engine throttle controllers, radar altimeters, and video compression systems. They are providing throttle controllers for the AUSROC 2.5 liquid rocket for the Australian Space Research Institute and developing a radar altimeter and video compression for the White Label Space team in the Google Lunar X Prize competition. Their technologies use open source software and hardware to help make space technologies more accessible.
Aerojet is proposing electric propulsion technologies for in-space transportation applications. Electric propulsion can provide large reductions in mass needed for launches to destinations like the Moon, Mars, and Lagrange points. Aerojet has a history of successful electric propulsion flights and is proposing demonstrations of increasingly powerful hall thruster and ion thruster technologies. These demonstrations would prove capabilities like orbital maneuvering and autonomous rendezvous to pave the way for a fully operational cargo transport tug utilizing solar electric propulsion.
A presentation file for Space shuttles & advancement for seminar purposes.
Information is collected from various websites including nasa.gov.in,wikipedia,space.com.
Information regarding SPACE TRANSPORTATION SYSTEM {SPACE SHUTTLE} and its Robotic arm , THERMAL PROTECTION SYSTEM With upcoming ORION(MPCV).
POINT OF TALK:
1.Introduction to space shuttle.
2.Description
3. photo with parts and TILES(TPS)
4. Various stages from takeoff to landing
5.COLLECTING OF EXTERNAL TANK
6.ROBOTIC ARM OF SPACE SHUTTLE
7.SPACE SHUTTLE DURING RE-ENTRY
8.THERMAL PROTECTION SYSTEM
9.REUSABLE CERAMIC TILES
10.COMPOSITION OF TILES
11.TESTING OF TILES
12..ORION MPCV
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 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.
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.
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
Satellites orbit objects like planets to perform various missions. They have orbits that are either geostationary, asynchronous, or polar. Rockets are used to launch satellites into orbit and have multiple stages powered by liquid or solid propellant engines. The first stage provides maximum thrust at launch while subsequent stages have lower thrust and place the satellite into its proper transfer orbit using liquid or cryogenic engines before the final apogee kick motor releases it onto its mission orbit. Precise propulsion, communication, electrical power, and computer systems are required for successful satellite launch and operation in space.
Aerojet is proposing electric propulsion technologies for in-space transportation applications. Electric propulsion can provide large reductions in mass needed for launches to destinations like the Moon, Mars, and Lagrange points. Aerojet has a history of successful electric propulsion flights and is proposing demonstrations of increasingly powerful hall thruster and ion thruster technologies. These demonstrations would prove capabilities like orbital maneuvering and autonomous rendezvous to pave the way for a fully operational cargo transport tug utilizing solar electric propulsion.
A presentation file for Space shuttles & advancement for seminar purposes.
Information is collected from various websites including nasa.gov.in,wikipedia,space.com.
Information regarding SPACE TRANSPORTATION SYSTEM {SPACE SHUTTLE} and its Robotic arm , THERMAL PROTECTION SYSTEM With upcoming ORION(MPCV).
POINT OF TALK:
1.Introduction to space shuttle.
2.Description
3. photo with parts and TILES(TPS)
4. Various stages from takeoff to landing
5.COLLECTING OF EXTERNAL TANK
6.ROBOTIC ARM OF SPACE SHUTTLE
7.SPACE SHUTTLE DURING RE-ENTRY
8.THERMAL PROTECTION SYSTEM
9.REUSABLE CERAMIC TILES
10.COMPOSITION OF TILES
11.TESTING OF TILES
12..ORION MPCV
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 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.
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.
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
Satellites orbit objects like planets to perform various missions. They have orbits that are either geostationary, asynchronous, or polar. Rockets are used to launch satellites into orbit and have multiple stages powered by liquid or solid propellant engines. The first stage provides maximum thrust at launch while subsequent stages have lower thrust and place the satellite into its proper transfer orbit using liquid or cryogenic engines before the final apogee kick motor releases it onto its mission orbit. Precise propulsion, communication, electrical power, and computer systems are required for successful satellite launch and operation in space.
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.
The document describes a proposed Quantum Communication Satellite (QCS) mission consisting of an 80-satellite constellation in low Earth orbit. The constellation would enable encrypted quantum communication between ground stations within 15 minutes, covering latitudes of ±70°. Each satellite would be a 20U CubeSat weighing 22kg carrying a quantum communication payload and systems to maintain the constellation orbit, attitude, power, propulsion, and communication. A comprehensive simulation was developed to analyze the satellite design and ensure mission requirements for maneuverability and communication are fulfilled.
The document summarizes options for re-flying the Orbiting Carbon Observatory (OCO) mission after the original spacecraft was lost during launch in February 2009. It discusses examining service platforms, access to space options, and conducting studies to evaluate rebuilding the OCO instrument and spacecraft ("Carbon Copy") as the lowest risk approach. While awaiting authorization to proceed, the OCO project team is working to reduce implementation risks and collaborate with other missions to be in the best position for an OCO re-flight.
The KMEC mission involves sending two spacecraft to Saturn over 6 years to study cosmic dust, ultraviolet imaging, and space recognition between the payloads. Each spacecraft is octagonal and 6m tall, made of aluminum. The 100kg payload includes dust, UV, and ranging instruments. A chemical propulsion system will perform orbital maneuvers. Power comes from an RTG and backup battery. Thermal control uses an RTG and radiator. The spacecraft structure is sized to withstand launch stresses and the environment at Saturn.
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.
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.)
This presentation gives an overview of the networking and conceptualize the terms of the Satellite networking systems, and also provide a glance of the typical functionality of the satellite system in establishing the worldwide mobile communication system, as well as the broadcasting system.
With the support and encouragement of my faculty and friends developed this presentation...
Thank you
The document proposes a Pluto Orbital Mission that would use a direct fusion drive (DFD) for propulsion and power. Key aspects include:
1) A DFD spacecraft would enter Pluto orbit 4 years after launch to map the surface with a laser-powered lander.
2) The DFD uses a field reversed configuration (FRC) plasma with D-He3 fuel to provide high power for science instruments and laser communications.
3) Experiments at PPPL are developing the FRC plasma and magnetic nozzle concepts, while Princeton Satellite Systems is performing mission design and engineering studies.
Satellites orbit Earth for a variety of purposes such as communication, weather monitoring, and navigation. They come in different types depending on their distance from Earth, including low-Earth orbit, medium-Earth orbit, and geostationary orbit. The Global Positioning System is a constellation of 24 satellites that provides location and time information to GPS receivers anywhere on Earth.
This document discusses the potential role of nanosatellites in future geodesy missions. It describes several ways nanosatellites could improve geodetic measurements, such as increasing spatial and temporal sampling. Specific nanosatellite missions discussed include the Drag Free Satellite, Gravity Explorer, and the Canadian CanX-4 and CanX-5 formation flying satellites. Payloads that could be miniaturized for nanosatellites include accelerometers, atomic clocks, star cameras, GPS receivers, and intersatellite ranging instruments. Attitude control techniques like magnetic torquers would need to be studied further for precision formation flying applications. The conclusion is that nanosatellites have the potential to contribute useful data to future gravity field
study of transponders -Defense Electronics Applications Lab, DehradunMohit Kumar
This document provides a summary of Mohit Kumar's vocational training project on transponders undertaken at the Defence Electronics Application Laboratory in Dehradun, India from June 2nd to July 2nd 2008. It includes a certificate signed by his mentor and the laboratory director certifying the successful completion of the project. The acknowledgements section expresses gratitude to various members of the laboratory for their support and guidance during the training period.
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.
Communications Payload Design and Satellite System Architecture: Bent Pipe a...Jim Jenkins
This four-day course, ATI Courses.com's Communications Payload Design and Satellite System Architecture course , provides communications and satellite systems engineers and system architects with a comprehensive and accurate approach for the specification and detailed design of the communications payload and its integration into a satellite system. Both standard bent pipe repeaters and digital processors (on board and ground-based) are studied in depth, and optimized from the standpoint of maximizing throughput and coverage (single footprint and multi-beam). Applications in Fixed Satellite Service (C, X, Ku and Ka bands) and Mobile Satellite Service (L and S bands) are addressed as are the requirements of the associated ground segment for satellite control and the provision of services to end users.
The document discusses the Apollo program's hardware used to travel from Earth to the Moon. The Saturn V rocket launched the Command Module/Service Module and Lunar Module into space. The Lunar Module then transported astronauts between the Moon's surface and the orbiting Command Module.
Nuclear - 25 years of satellite imagery over ChernobylSpot Image
How Earth-imaging satellites tracked the changes over the last 25 years in the wake of the nuclear accident. By Astrium GEO-Information Services. More Information on www.astrium-geo.com.
GSAT-14 is an Indian communications satellite launched in 2014. It was constructed by ISRO based on the I-2K satellite bus, weighing 851 kg without fuel. GSAT-14 has a design life of 12 years and carries experiments in new technologies. After a scrubbed first launch attempt in 2013, GSAT-14 was successfully launched in January 2014 atop a GSLV Mk-II rocket, ending a streak of four previous GSLV failures. Aryabhata was India's first satellite, launched in 1975 to gain experience in space and conduct experiments in x-ray astronomy, agriculture, and solar physics. It helped establish India's space program and space science investigations.
This document contains information about an enrolment package, commission plan, and interest yield. It likely details the terms of a financial product being offered, including how salespeople will be compensated and any returns customers may earn. The document focuses on enrollment, incentives for selling the product, and potential earnings.
The document shows mathematical patterns that demonstrate the beauty of mathematics and God. It presents addition sums of letter values in words that equal percentages, showing that "hard work" equals 98%, "knowledge" equals 96%, "attitude" equals 100%, and "love of God" equals 101%, indicating the love of God is what takes one above and beyond.
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.
The document describes a proposed Quantum Communication Satellite (QCS) mission consisting of an 80-satellite constellation in low Earth orbit. The constellation would enable encrypted quantum communication between ground stations within 15 minutes, covering latitudes of ±70°. Each satellite would be a 20U CubeSat weighing 22kg carrying a quantum communication payload and systems to maintain the constellation orbit, attitude, power, propulsion, and communication. A comprehensive simulation was developed to analyze the satellite design and ensure mission requirements for maneuverability and communication are fulfilled.
The document summarizes options for re-flying the Orbiting Carbon Observatory (OCO) mission after the original spacecraft was lost during launch in February 2009. It discusses examining service platforms, access to space options, and conducting studies to evaluate rebuilding the OCO instrument and spacecraft ("Carbon Copy") as the lowest risk approach. While awaiting authorization to proceed, the OCO project team is working to reduce implementation risks and collaborate with other missions to be in the best position for an OCO re-flight.
The KMEC mission involves sending two spacecraft to Saturn over 6 years to study cosmic dust, ultraviolet imaging, and space recognition between the payloads. Each spacecraft is octagonal and 6m tall, made of aluminum. The 100kg payload includes dust, UV, and ranging instruments. A chemical propulsion system will perform orbital maneuvers. Power comes from an RTG and backup battery. Thermal control uses an RTG and radiator. The spacecraft structure is sized to withstand launch stresses and the environment at Saturn.
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.
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.)
This presentation gives an overview of the networking and conceptualize the terms of the Satellite networking systems, and also provide a glance of the typical functionality of the satellite system in establishing the worldwide mobile communication system, as well as the broadcasting system.
With the support and encouragement of my faculty and friends developed this presentation...
Thank you
The document proposes a Pluto Orbital Mission that would use a direct fusion drive (DFD) for propulsion and power. Key aspects include:
1) A DFD spacecraft would enter Pluto orbit 4 years after launch to map the surface with a laser-powered lander.
2) The DFD uses a field reversed configuration (FRC) plasma with D-He3 fuel to provide high power for science instruments and laser communications.
3) Experiments at PPPL are developing the FRC plasma and magnetic nozzle concepts, while Princeton Satellite Systems is performing mission design and engineering studies.
Satellites orbit Earth for a variety of purposes such as communication, weather monitoring, and navigation. They come in different types depending on their distance from Earth, including low-Earth orbit, medium-Earth orbit, and geostationary orbit. The Global Positioning System is a constellation of 24 satellites that provides location and time information to GPS receivers anywhere on Earth.
This document discusses the potential role of nanosatellites in future geodesy missions. It describes several ways nanosatellites could improve geodetic measurements, such as increasing spatial and temporal sampling. Specific nanosatellite missions discussed include the Drag Free Satellite, Gravity Explorer, and the Canadian CanX-4 and CanX-5 formation flying satellites. Payloads that could be miniaturized for nanosatellites include accelerometers, atomic clocks, star cameras, GPS receivers, and intersatellite ranging instruments. Attitude control techniques like magnetic torquers would need to be studied further for precision formation flying applications. The conclusion is that nanosatellites have the potential to contribute useful data to future gravity field
study of transponders -Defense Electronics Applications Lab, DehradunMohit Kumar
This document provides a summary of Mohit Kumar's vocational training project on transponders undertaken at the Defence Electronics Application Laboratory in Dehradun, India from June 2nd to July 2nd 2008. It includes a certificate signed by his mentor and the laboratory director certifying the successful completion of the project. The acknowledgements section expresses gratitude to various members of the laboratory for their support and guidance during the training period.
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.
Communications Payload Design and Satellite System Architecture: Bent Pipe a...Jim Jenkins
This four-day course, ATI Courses.com's Communications Payload Design and Satellite System Architecture course , provides communications and satellite systems engineers and system architects with a comprehensive and accurate approach for the specification and detailed design of the communications payload and its integration into a satellite system. Both standard bent pipe repeaters and digital processors (on board and ground-based) are studied in depth, and optimized from the standpoint of maximizing throughput and coverage (single footprint and multi-beam). Applications in Fixed Satellite Service (C, X, Ku and Ka bands) and Mobile Satellite Service (L and S bands) are addressed as are the requirements of the associated ground segment for satellite control and the provision of services to end users.
The document discusses the Apollo program's hardware used to travel from Earth to the Moon. The Saturn V rocket launched the Command Module/Service Module and Lunar Module into space. The Lunar Module then transported astronauts between the Moon's surface and the orbiting Command Module.
Nuclear - 25 years of satellite imagery over ChernobylSpot Image
How Earth-imaging satellites tracked the changes over the last 25 years in the wake of the nuclear accident. By Astrium GEO-Information Services. More Information on www.astrium-geo.com.
GSAT-14 is an Indian communications satellite launched in 2014. It was constructed by ISRO based on the I-2K satellite bus, weighing 851 kg without fuel. GSAT-14 has a design life of 12 years and carries experiments in new technologies. After a scrubbed first launch attempt in 2013, GSAT-14 was successfully launched in January 2014 atop a GSLV Mk-II rocket, ending a streak of four previous GSLV failures. Aryabhata was India's first satellite, launched in 1975 to gain experience in space and conduct experiments in x-ray astronomy, agriculture, and solar physics. It helped establish India's space program and space science investigations.
This document contains information about an enrolment package, commission plan, and interest yield. It likely details the terms of a financial product being offered, including how salespeople will be compensated and any returns customers may earn. The document focuses on enrollment, incentives for selling the product, and potential earnings.
The document shows mathematical patterns that demonstrate the beauty of mathematics and God. It presents addition sums of letter values in words that equal percentages, showing that "hard work" equals 98%, "knowledge" equals 96%, "attitude" equals 100%, and "love of God" equals 101%, indicating the love of God is what takes one above and beyond.
The document summarizes Pramod Kumar Chennamadhavuni's presentation items, including his personal background, major strengths, a university project on computational designing of functional structured nanoparticles, inspiration from educational life relating creativity and motivation to inspiration using equations, and major interest in charity event organization outside of work to support education.
The document discusses various aspects of becoming an "internet entrepreneur" or "Netrepreneur" in the Philippines by using online platforms like Facebook and LinkedIn to conduct business. It promotes the benefits of an MLM business opportunity called iCONOMY that allows members to build an online retail business and earn commissions through recruitment. Key benefits highlighted for early members include access to business resources and higher positions within the MLM structure.
Efren Tolipas Eito is seeking a position as a maintenance engineer. He has a bachelor's degree in industrial engineering and over 15 years of experience in process engineering, work control engineering, and maintenance roles. His experience includes developing process designs, performing simulations, developing safety plans, and overseeing maintenance work. He is proficient in various engineering software and has skills operating industrial equipment.
This document compares the key differences between managers and leaders. It outlines that managers focus on production and short-term goals, delegate tasks, and maintain the status quo. Leaders take a people-oriented approach, develop long-term vision, challenge assumptions, and inspire teams towards shared goals. While managers drive performance, leaders empower followers and catalyze positive change.
The document provides ergonomic tips for computer users, including proper ergonomic setup of equipment and work environment as well as exercises to perform throughout the work day. It recommends stretching for at least 5 minutes every hour away from the computer to reduce injury risk from static posture. Simple stretches are illustrated to target the hands, back, shoulders, head, and neck and should be incorporated into the daily routine.
This document provides information about Pramod Kumar's knowledge, skills, and experience for the role of developing CORUS. It includes details about his educational background in engineering, IT, and management. It then discusses the technical knowledge, communication skills, and experience needed for the role, including experience with analytical calculations, prediction/simulation software, and managing teams. The document also provides a brief introduction to CORUS, nanotechnology, and how Pramod's knowledge and experience could apply to developing CORUS, such as in areas of materials properties, coating, and environmental impact.
The document discusses various political factors that influence international business, including political systems, ideologies, and government structures. It notes that firms must understand how local political environments differ and adjust accordingly. When operating abroad, companies should not assume they can directly transfer their practices and instead must accept different political and legal systems in other countries. The document also provides examples of various political systems like individualism vs. collectivism, democratic vs. totalitarian systems, and discusses considerations for doing business in countries like China which has a more bureaucratic rather than legal-based system.
This document provides an overview and summary of an MSc project on heat transfer effects on a nanostructured tungsten layer. The project involves modeling and computer simulation of a four-layered metal ceramic structure containing tungsten and barium titanate to study how surface roughness impacts heat transfer properties. Simulation results found that increasing surface roughness, which decreases surface contact area, lowers the effective thermal conductivity. The summary concludes that barium titanate's improved grain orientation may introduce novel changes to heat transfer through the structure. Possible future applications of nanostructures in areas like oil recovery and renewable energy are also briefly discussed.
The document discusses various political factors that impact international business, including political systems, ideologies, and government approaches. It notes that firms must understand the political environment of different markets to navigate challenges. Key political considerations include individualism vs collectivism, democratic vs totalitarian systems, and how governments intervene in economies through policies. The document uses examples of political coalitions in England and China's approach to foreign investment to illustrate analyzing political factors in international business.
This document compares the key differences between managers and leaders. It outlines that managers focus on production and short-term goals, delegate responsibility, and maintain the status quo. Leaders take a people-oriented approach, delegate authority, develop long-term vision, challenge assumptions and innovate. The document suggests that while managers drive team members and work within systems, leaders coach, inspire and work to organize the best resources.
O documento discute as principais teorias sociais do século XIX, comparando teorias liberais, positivistas, socialistas utópicas e científicas. As teorias liberais defendiam a propriedade privada e a não intervenção do Estado, enquanto as socialistas criticavam a desigualdade do capitalismo e propunham alternativas como a propriedade coletiva. Dentro do socialismo, as utópicas propunham mudanças pacíficas versus as científicas de Marx que defendiam a revolução proletária.
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
This document summarizes the market research and design process of a student team creating an advanced lunar rover. It discusses existing rover designs from NASA, including the Sojourner, Spirit, Athlete, and Curiosity rovers. These rovers informed the requirements for the new design, including flexibility to navigate different terrains, minimizing energy usage, and negotiating difficult surfaces. The document then covers the team's concept generation and selection of components, including wheels, suspension, power source, and materials. Design prototypes, calculations, and a management plan are also summarized to outline the comprehensive process undertaken to create a more advanced lunar rover design.
The document proposes developing a lunar hopper vehicle powered by a nuclear thermal rocket engine. It would take off and land repeatedly to gather soil samples from multiple locations on the moon's surface. An optimization problem is set up in MATLAB to determine the ideal dry mass and mass ratio to maximize the number of landing sites visited. The analysis finds that a design using a SNRE (Small Nuclear Reactor Engine) with a 3500 kg dry mass could achieve up to 28 sample retrievals from sites 5 km apart. A conceptual design of the vehicle is then presented, including subsystem mass budgets and dimensioned drawings. Future work areas are identified to further develop the design.
The SpaceDrive Project - First Results on EMDrive and Mach-Effect ThrustersSérgio Sacani
Propellantless propulsion is believed to be the best option for interstellar travel. However, photon rockets or solar sails have thrusts so low that maybe only nano-scaled spacecraft may reach the next star within our lifetime using very high-power laser beams. Following into the footsteps of earlier breakthrough propulsion programs, we are investigating different concepts based on non-classical/revolutionary propulsion ideas that claim to be at least an order of magnitude more efficient in producing thrust compared to photon rockets. Our intention is to develop an excellent research infrastructure to test new ideas and measure thrusts and/or artefacts with high confidence to determine if a concept works and if it does how to scale it up. At present, we are focusing on two possible revolutionary concepts: The EMDrive and the Mach-Effect Thruster. The first concept uses microwaves in a truncated cone-shaped cavity that is claimed to produce thrust. Although it is not clear on which theoretical basis this can work, several experimental tests have been reported in the literature, which warrants a closer examination. The second concept is believed to generate mass fluctuations in a piezo-crystal stack that creates non-zero time-averaged thrusts. Here we are reporting first results of our improved thrust balance as well as EMDrive and Mach-Effect thruster models. Special attention is given to the investigation and identification of error sources that cause false thrust signals. Our results show that the magnetic interaction from not sufficiently shielded cables or thrusters are a major factor that needs to be taken into account for proper μN thrust measurements for these type of devices.
This document analyzes trajectories to reach the heliopause and exit the solar system using nuclear thermal propulsion (NTP) and Oberth maneuvers. It finds that NTP, which can provide much higher specific impulse than chemical propulsion, enables significantly faster trajectories when combined with Oberth maneuvers where the spacecraft fires its engines near the closest approach to the Sun. The document models trajectories from various launch vehicles that take the spacecraft close to the Sun, where it executes a large velocity change to enter an hyperbolic orbit leaving the solar system. It finds that lower perihelion distances and higher Oberth burns result in higher exit velocities from the solar system.
Project LEON proposes utilizing ram accelerator technology to cheaply launch small satellites into low Earth orbit. The ram accelerator works by accelerating projectiles through long tubes using combustion, reaching speeds to deploy payloads into orbit within minutes. This provides a lower-cost alternative to rockets for launching small satellites. Project LEON aims to enable more frequent and affordable launches for purposes like communications networks and removing space debris. The ram accelerator technology has been demonstrated at universities and could lower launch costs by an order of magnitude compared to rockets.
Honeybee Robotics is a 25-year old engineering company specializing in robotics for space exploration. It has expertise in sampling and excavation tools, spacecraft mechanisms, and field robotics. Honeybee leverages its experience across government agencies and commercial sectors to reduce costs. It develops technologies for NASA, DoD, and industry by adapting tools to different applications and environments like the moon, Mars, and hazardous sites on Earth.
In this paper with the reference of NASA’s MARS Curiosity Rover, this project is meant for a low cost, lightweight and small size unmanned ground vehicle (UGV) which is controlled by NI-myRIO a hardware component of National Instruments can be used for surveying and determining the natural conditions for living beings like identification of gases, collection of picture samples etc., It consists of six individual motors with lightweight chassis for achieving various movements of rover, gas sensors, camera with servos, long-lasting power supply with its required communication tools. The Six wheeled Rover with three or more suspension alignments will move and collect various samples for identification of gases and taking pictures around the astronomical areas automatically by the automated movements.
The document summarizes options for re-flying the Orbiting Carbon Observatory (OCO) mission after the original spacecraft was lost during launch in February 2009. It discusses examining service platforms, access to space options, and conducting studies to evaluate rebuilding the OCO instrument and spacecraft ("Carbon Copy") as the lowest risk approach. While awaiting authorization to proceed, the OCO project team is working to reduce implementation risks and collaborate with other missions to be in the best position for an OCO re-flight.
Conceptual Design of a Crewed Lunar Landerguinness
Conceptual design study performed at Johnson Space Center in summer 2006, in partial fulfillment of the requirements for the Master of Science in Space Studies at the International Space University.
Lawrence Livermore National Laboratory
المحرك الصاروخي المعدل بقي حقيقه وقفزة علمية
بدأ اعتمادا علي المحاكاة فقط وصلا للنجاح وطبعا تحت مظلة وزاره الدفاع الامريكيه لتأمين الدعم اللازم و...
اضافة مؤثرة فعلا في تلك الصناعة
وأهم حاجه فيه ان الثرست زاد مع زياده الكفاءه ايضا ده غير ان الثرست نفسه بيعتمد علي الارتفاع
ده هيطور رحلات الذهاب >> والعوده!! كمان بشكل كبير
https://str.llnl.gov/november-2015/burton
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Lunar Numbat: Space Exploration with Open Software and Open Hardware
1. Lunar Numbat: Open Source Goes To Space
linux.conf.au 2011
Luke Weston
http://www.lunarnumbat.org
July 9, 2011
Lunar Numbat: Open Source Goes To Space
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2. Introduction
What is Lunar Numbat?
Lunar Numbat is an open-source space technology collaboration which
was formed by a group of people from across Australia and New Zealand
in 2009, with the intention of developing innovative, low-cost, open-source
hardware and software solutions for space technology.
Lunar Numbat hopes to encourage Australian and international innovation
in space science and increase the accessibility of space development.
The project was initiated in 2009 by Marco Ostini, and a review of Lunar
Numbat work was presented at linux.conf.au by Jon Oxer in 2010.
Since then, however, some significant milestones have been accomplished.
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3. Introduction
What We Do
The focus of our research and development at present is in three main
areas: rocket engine throttle control avionics, radar altimeters, and media
compression.
Linux, open hardware, open software development, open documentation,
open standards, and community-driven collaboration all have an important
role in meeting Lunar Numbat’s challenging goal of delivering flexible,
useful space technologies at a relatively low cost.
Lunar Numbat is collaborating with the Australian Space Research
Institute (ASRI), and with White Label Space, a team competing for the
Google Lunar X-Prize.
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4. Introduction
AUSROC 2.0 / 2.5
Figure: The AUSROC-2 launch vehicle on the launch rail, being loaded with
liquid oxygen prior to launch.
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5. Introduction
Australian Space Research
We’re now completing the development and testing of the CAN-interfaced
propellant valve throttle controllers we have developed for AUSROC 2.5, a
powerful liquid-fuelled sounding rocket developed as part of ASRI’s
AUSROC program.
7.5 meters tall
Liquid-fuelled: kerosene and liquid oxygen
Peak velocity = 1100 ms−1 (Mach 3.3)
Apogee at about 33 kilometers (110,000 feet)
Thrust = 35 kN; Isp = 240 seconds.
Lunar Numbat: Open Source Goes To Space
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7. Figure: A static test firing of the AUSROC 2 rocket engine.
Lunar Numbat: Open Source Goes To Space
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8. Introduction
ASRI activities
We are providing ASRI with innovative, low-cost open source solutions to
meet the needs of Australia’s own in-house space launch vehicle research
and development.
In the process, we’re making a positive contribution back to Australian
space research, which is greatly in need of Australia’s support.
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9. Figure: One of ASRI’s solid fuelled Zuni rockets being launched.
Lunar Numbat: Open Source Goes To Space
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10. Engine Throttle Controllers
Engine throttle controllers
We are designing and implementing electronic controllers for the valves
admitting fuel and oxidiser to the liquid-fuelled rocket engine on AUSROC
2.5.
This electronic control over the propellant valves allows the flight
computer to throttle down, stop and restart the rocket engine, as well as
to adjust the fuel-oxidiser ratio on-the-fly.
These throttle controllers embody a combination of open electronic
hardware, open-source embedded software, and some open mechanical
design.
Lunar Numbat: Open Source Goes To Space
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11. Engine Throttle Controllers
Open Software and Open Hardware
Free is good - GNU and TAPR licenses
TAPR Open Hardware License - http://www.tapr.org/ohl.html
Figure: The CAN interface component of our protoype engine control hardware.
Lunar Numbat: Open Source Goes To Space
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12. Engine Throttle Controllers
Mechanical Assembly
A pair of stainless steel ball valves, rated for cryogenic oxygen service, are
used for the fuel and oxidiser.
A pair of powerful DC brush motors and reduction gearheads move the
valves, with a pair of position sensors to measure the absolute valve
positions.
Figure: The liquid oxygen valve assembly for AUSROC 2.5, including the ball
valve, reduction gearhead and motor.
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13. Figure: The overall assembly of the AUSROC 2.5 valve fairing.
Lunar Numbat: Open Source Goes To Space
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14. Engine Throttle Controllers
Throttle Controller Electronics
Figure: The first generation valve control electronics for the kerosene valve of
AUSROC 2.5.
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15. Engine Throttle Controllers
CAN Interface
CAN-Do! is a general purpose CAN interface module designed for use on
satellites and spacecraft.
Designed by a group within the AMSAT community, led by Bdale Garbee.
Based around the Atmel T89C51CC01 (8051 core).
Already basically space-rated; tested for thermal and ionising radiation
tolerance.
Open source!
An excellent starting point for White Label Space, perhaps!
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16. Engine Throttle Controllers
CAN Interface
Figure: An example of the CAN-do! hardware.
http://can-do.moraco.info/Default.htm
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17. Engine Throttle Controllers
White Label Space
Such systems will possibly be evolved further and applied on the White
Label Space lunar lander. The ability to throttle the descent engine is
essential for a controlled lunar landing.
What is White Label Space?
One of the teams in the Google Lunar X-Prize.
The only team with any significant Australian involvement.
Significant international partners in space technology, including people
from ESA and the Swiss Propulsion Laboratory and people from Tohuko
University with experience on the Hayabusa mission.
Lunar Numbat: Open Source Goes To Space
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18. Engine Throttle Controllers
Google Lunar X-Prize
US$20 million prize for the first non-government mission to land a
spacecraft on the surface of the Moon, travel over 500 meters on the
lunar surface, and transmit images and data back to Earth.
Lunar Numbat: Open Source Goes To Space
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19. C-band Radar Altimeter
C-band Radar Altimeter
We’re also in the early stages of developing a radar altimeter for White
Label Space. We’re working to develop a relatively simple, low-cost radar
altimeter, with the altitude range and resolution required to support the
landing of an unmanned probe on the lunar surface.
For a successful landing on the moon, a lander needs to know its altitude
above the lunar surface precisely, and the only means to do this is by
radar.
This unique use case requires a radar altimeter with large altitude range
and high resolution, and no radar hardware suitable for this application is
available off the shelf.
Lunar Numbat: Open Source Goes To Space
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20. C-band Radar Altimeter
C-band Radar Altimeter
The radar system we are in the early stages of developing will operate in
the C-band, at about 4.3 GHz, and will probably be based around an
ARM microcontroller controlling the microwave heterodyne system.
The microwave component of this system will be constructed using high
electron mobility transistors (HEMTs) on a Teflon or similar PCB
substrate with good microwave performance, using microstrip technology.
This radar altimeter designed and built by Matjaˇ Vidmar and completely
z
open-sourced onto the Web is very similar to the kind of radar system we
are aiming to implement - although our system will have a greater range
and RF power output.
Lunar Numbat: Open Source Goes To Space
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21. C-band Radar Altimeter
C-band Radar Altimeter
Figure: A microwave radar altimeter designed and built by Matjaˇ Vidmar for
z
use on a small aircraft.
See http://lea.hamradio.si/∼s53mv/avnr/adesign.html
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22. Video and Image Compression
HD Video and Still Compression
We’re developing systems for rapid, on-the-fly compression of
high-definition video and still images, suitable for the transmission of
high-definition images from spacecraft where very limited amounts of
communications bandwidth are available.
This will be important, for example, on lunar rovers participating in the
Google Lunar X-Prize, since video and image transmission is a key
requirement of the GLXP.
In particular, we’re investigating JPEG2000 and MJPEG2000
(Motion JPEG)-based systems. A proof-of-concept - “JPEG2000
Decimator” - has been experimented with so far.
This video and image processing will require moderately powerful
embedded computers running Linux, and/or FPGAs, which will operate
successfully for the mission duration required in the thermal and
radiological environment of the lunar surface.
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23. Video and Image Compression
Questions?
Lunar Numbat: Open Source Goes To Space
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24. Video and Image Compression
Thanks!
Many thanks to:
- Marco Ostini
- Lana Brindley
- Rob Brittain
- Stuart Young
- Joanna Cheng
- Andy Gelme
- Roy Duncan
- Mark Blair
- Jon Oxer
- Lee Begg
Lunar Numbat: Open Source Goes To Space
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25. Other Considerations
Radiation Hardening
It is true that you can’t just take any system using modern
microcontrollers and VLSIs that you’ve designed for use inside the
atmosphere, launch it into space and expect that it will work reliably on
an ongoing basis.
However, it is practical to build electronic systems using standard
off-the-shelf components which can survive and operate in space, without
spending hundreds of thousands of dollars on “real” radiation-hardened
embedded CPUs such as the IBM RAD6000 or RAD750.
When we look at the amateur satellite community, for example, we find a
good deal of experience and prior art designing electronics systems for use
on satellites, which operate reliably in space for an extended period of
time, which are designed and implemented at relatively low costs, using
relatively simple electronics.
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26. Other Considerations
Radiation Hardening
There’s nothing “magical” about the environment of space. We know
what the conditions of temperature and ionising radiation experienced by
a spacecraft will be, and we can design space systems to ensure reliability
for the mission profile required.
When Apollo astronauts travelled to the Moon, for example, the ionising
radiation doses they received were recorded on their personal dosimeters.
As transistor integration density becomes higher and higher on modern
VLSI chips, the transistors themselves are fabricated smaller and smaller,
and therefore, the gate capacitance of the transistors becomes smaller and
smaller.
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27. Other Considerations
Radiation Hardening
Since C = Q , the smaller gate capacitance means that the voltage spike
V
that results when a charged particle (such as an electron or proton)
carrying a certain quantum of charge hits the transistor’s gate is much
larger. This is why VLSI devices are more susceptible to radiation-induced
soft errors than older devices with lower integration density.
Radiation-hardening was actually less of a challenge in the Apollo era than
it was today. The higher the transistor density on an IC, the more
susceptible to radiation effects it is. The magnetic-core memory and
primative integrated circuits used on Apollo were not susceptible to
radiation effects, whereas modern microprocessors and memory devices
are.
The simple RTL logic gate ICs used to build the Apollo Guidance
Computers contained a whopping 6 transistors on each chip. For
comparison, today, an ARM7 chip contains about 600,000.
Lunar Numbat: Open Source Goes To Space
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29. Other Considerations
Radiation Hardening
FPGAs can be configured with soft cores designed to be radiation
tolerant; eg. redundancy to tolerate cosmic-ray bit flips.
The Cibola satellite developed several years ago at Los Alamos will
validate the space use of commercial, off-the-shelf Xilinx FPGAs.
The Cibola team has been actively testing Xilinx FPGAs since 1999, to
evaluate the use of off-the-shelf FPGAs in the space radiation
environment.
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