The document discusses nanosatellite deployers, which isolate CubeSats from the launch vehicle and main payload and deploy them into orbit. It describes several common deployer types, including the P-POD, ISI-POD, X-POD, NANORACKS, RSC-POD, and CSD. The document summarizes simulations and experiments that analyzed factors affecting CubeSats' tip-off rates after deployment, such as their mass properties, spring stroke distances, and clearances between guide rails. Ground and microgravity flight tests indicated 3U CubeSats typically have maximum rotational rates under 10°/s after deployment, while 1U CubeSats' rates
Guidance, navigation and control (GNC) deals with controlling the movement of space vehicles. GNC includes guidance to establish the desired path, navigation to determine the current and future position, and control actions to match the current position to the desired path. The key elements of GNC are guidance, navigation, control systems, and attitude control. GNC is essential for space missions to navigate from point to point, control the vehicle's orientation, and guide trajectories between planets and spacecraft pointing.
Presentation ON MISSILES AND ITS CLASSIFICATIONmohanreddy04
This document provides an overview of the history and components of missiles. It discusses how rockets were first invented in medieval China and later developed by Tipu Sultan in India. After independence, India focused on space technology and missile development. The major components of a missile are the warhead, guidance system, and propulsion system. Missiles can be categorized based on their target, such as air-to-air, surface-to-air, anti-ship, and cruise missiles. The document describes different types of missiles and includes examples.
This document discusses spacecraft attitude dynamics and control. It begins by introducing typical modes of spacecraft operation like attitude acquisition and nominal earth pointing. It then covers key topics like reference frames, attitude representation using Euler angles, quaternions and direction cosine matrices, orbital elements, external disturbances, and spacecraft attitude dynamics equations. Quaternion algebra is described for representing attitude and performing successive rotations between frames. Overall, the document provides an overview of fundamental concepts for analyzing and controlling a spacecraft's orientation in space.
This document provides information about a professional development course on fundamentals of rockets and missiles. The course will be held from March 11-13, 2009 in Laurel, Maryland and will cost $1590. It will provide a practical foundation of knowledge on rocket and missile issues and technologies. The 14-part course outline covers topics like rocket propulsion, liquid and solid propellant systems, foreign and domestic rocket comparisons, and reusable launch vehicles. The instructor, Edward L. Keith, has extensive experience in the rocket field. Attendees will learn about rocket fundamentals and receive printed course notes. The course is intended for engineers, managers, military personnel, and others involved in rocket projects.
This document discusses reusable launch vehicles (RLVs) and their potential to significantly reduce the cost of space travel and access. It provides details on some of the major players in RLV development, including SpaceX, Blue Origin, and ISRO. SpaceX's Falcon 9 is highlighted as an example of a partially reusable orbital launch system. The document argues that fully reusable single-stage-to-orbit rockets, if achievable, could reduce launch costs by as much as 100 times and revolutionize space exploration and satellite deployment.
The document discusses CubeSat satellites. It describes their size comparison to other satellites, typical weight, internal structure using aluminum, use of solar cells and lithium-ion batteries for power, and methods of launch including from the International Space Station. CubeSats offer advantages of low cost, small size, less development time, and lower launch costs compared to larger satellites.
The document discusses nanosatellite deployers, which isolate CubeSats from the launch vehicle and main payload and deploy them into orbit. It describes several common deployer types, including the P-POD, ISI-POD, X-POD, NANORACKS, RSC-POD, and CSD. The document summarizes simulations and experiments that analyzed factors affecting CubeSats' tip-off rates after deployment, such as their mass properties, spring stroke distances, and clearances between guide rails. Ground and microgravity flight tests indicated 3U CubeSats typically have maximum rotational rates under 10°/s after deployment, while 1U CubeSats' rates
Guidance, navigation and control (GNC) deals with controlling the movement of space vehicles. GNC includes guidance to establish the desired path, navigation to determine the current and future position, and control actions to match the current position to the desired path. The key elements of GNC are guidance, navigation, control systems, and attitude control. GNC is essential for space missions to navigate from point to point, control the vehicle's orientation, and guide trajectories between planets and spacecraft pointing.
Presentation ON MISSILES AND ITS CLASSIFICATIONmohanreddy04
This document provides an overview of the history and components of missiles. It discusses how rockets were first invented in medieval China and later developed by Tipu Sultan in India. After independence, India focused on space technology and missile development. The major components of a missile are the warhead, guidance system, and propulsion system. Missiles can be categorized based on their target, such as air-to-air, surface-to-air, anti-ship, and cruise missiles. The document describes different types of missiles and includes examples.
This document discusses spacecraft attitude dynamics and control. It begins by introducing typical modes of spacecraft operation like attitude acquisition and nominal earth pointing. It then covers key topics like reference frames, attitude representation using Euler angles, quaternions and direction cosine matrices, orbital elements, external disturbances, and spacecraft attitude dynamics equations. Quaternion algebra is described for representing attitude and performing successive rotations between frames. Overall, the document provides an overview of fundamental concepts for analyzing and controlling a spacecraft's orientation in space.
This document provides information about a professional development course on fundamentals of rockets and missiles. The course will be held from March 11-13, 2009 in Laurel, Maryland and will cost $1590. It will provide a practical foundation of knowledge on rocket and missile issues and technologies. The 14-part course outline covers topics like rocket propulsion, liquid and solid propellant systems, foreign and domestic rocket comparisons, and reusable launch vehicles. The instructor, Edward L. Keith, has extensive experience in the rocket field. Attendees will learn about rocket fundamentals and receive printed course notes. The course is intended for engineers, managers, military personnel, and others involved in rocket projects.
This document discusses reusable launch vehicles (RLVs) and their potential to significantly reduce the cost of space travel and access. It provides details on some of the major players in RLV development, including SpaceX, Blue Origin, and ISRO. SpaceX's Falcon 9 is highlighted as an example of a partially reusable orbital launch system. The document argues that fully reusable single-stage-to-orbit rockets, if achievable, could reduce launch costs by as much as 100 times and revolutionize space exploration and satellite deployment.
The document discusses CubeSat satellites. It describes their size comparison to other satellites, typical weight, internal structure using aluminum, use of solar cells and lithium-ion batteries for power, and methods of launch including from the International Space Station. CubeSats offer advantages of low cost, small size, less development time, and lower launch costs compared to larger satellites.
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
The document discusses unmanned aerial vehicles (UAVs), also known as drones. It provides background on the origins of UAVs, dating back to 1916. UAVs were further developed for military purposes after World War I and by the US Air Force in 1959. The document outlines the various sub-systems that make up a UAV, including communications, navigation, monitoring, collision avoidance, and weather systems. Examples are given of commercial and Indian-made UAVs, as well as their various uses and advantages such as reduced risk compared to manned flights. Potential disadvantages like hacking and weather vulnerability are also noted.
A launch vehicle is a system used to launch satellites into stable orbits. It works on Newton's third law of motion, where the exhaust gases ejected from the rocket engine provide an equal and opposite reaction force that propels the launch vehicle upward. Launch vehicles are classified based on their payload capacity and number of stages. India's space agency ISRO has used several launch vehicles over the years of increasing capability, starting with the SLV, then the ASLV, and now predominantly uses the PSLV and GSLV.
This document provides information about hypersonic vehicles and the materials needed to withstand their extreme conditions. It begins by defining different speed regimes from subsonic to hypersonic. It then discusses the history of hypersonic vehicles and some current examples like the Boeing X-51 scramjet. Next, it focuses on Indian hypersonic missiles BrahMos-II and Shaurya. The document also explains scramjet engines and the special composite materials required for surfaces that experience temperatures over 1,260°C during hypersonic flight.
The document discusses the design and construction of rocket thrust chamber bodies. It describes how rocket thrust chambers must withstand extreme temperatures and pressures during combustion. They are typically constructed of double-walled cylinders with inner walls made of high-conductivity and high-strength copper alloys to withstand the heat, and outer walls made of stainless steel. The document outlines the major fabrication steps involving powder production, forming cylinders, welding, machining, and coating the inner wall with protective materials. It also discusses the material properties and applications of rocket thrust chambers.
Indian space launch vehicles have evolved over time, starting with small sounding rockets in the 1960s for upper atmospheric research carrying up to 100 kg payloads. India's first experimental satellite launch vehicle was the SLV-3 in 1980, capable of placing 40 kg in low Earth orbit. The Augmented Satellite Launch Vehicle (ASLV) program in the late 1980s doubled payload to 150 kg. The Polar Satellite Launch Vehicle (PSLV) introduced in the 1990s was India's first to use liquid fuel and has successfully launched numerous Indian and international satellites. The Geosynchronous Satellite Launch Vehicle (GSLV) provides heavy lift capability to geostationary transfer orbit. Its latest variant, GSLV Mk III, has increased payload capacity
This document provides an overview of the design and fabrication of a tricopter drone. It describes the motivation to build the tricopter with a low budget and light weight. The key components of the tricopter include three brushless motors, an Atmega168PA controller board, receiver, batteries, and a glass fiber frame. Challenges in the design included balancing the tricopter and integrating the gyroscope and accelerometer. Testing involved mechanical design, propeller selection, electrical connections, and programming the controller board. The conclusion discusses potential applications in military, industrial, and commercial uses if further funding and experimental analysis are conducted.
This document discusses vertical take-off and landing (VTOL) aircraft. It defines VTOL aircraft as those that can hover, take off, and land vertically without needing a runway. There are two main types of VTOL technology: rotorcraft and powered lift. Rotorcraft use rotating blades like helicopters to generate lift, while powered lift vehicles direct thrust downward for vertical flight. Examples of different VTOL aircraft are provided like helicopters, tiltrotors, tiltwings and tail-sitters. Advantages of VTOL include removing the need for runways and making air travel safer. The document concludes that while VTOL aircraft are not yet economical, they may have an important role in future aviation.
Cube Satellites are standardized Nano-satellites for space researches and applications. CubeSat can be created using COTS Hardware and is a very creative utilizing of the knowledge of Embedded Systems and various MEMS sensor devices
A CubeSat (U-class spacecraft) is a type of miniaturized satellite for space research that is made up of multiples of 10×10×10 cm cubic units. CubeSats have a mass of no more than 1.33 kilograms per unit.
The document discusses ejection seats and their components and functioning. It provides details about:
1) The basic components of an ejection seat including the catapult, rocket, restraints and parachute.
2) The ejection sequence which involves seat activation, canopy jettisoning, seat ejection using a rocket catapult, drogue parachute deployment, seat separation, and recovery parachute deployment.
3) The ACES II ejection seat which uses electronic sequencing and timing, has auto sensing capabilities, and multi-mode operation for recovery in different speed and altitude conditions.
This seminar gives idea about spacecraft propulsion i.e., actually what are different latest modes of propulsion are used in space agency and also the introduction of combustion of propellants.
Satellites are launched into orbit using launch vehicles, which can be either expendable or reusable. Expendable vehicles are designed for single use and are not recovered after launch, while reusable vehicles like the Space Shuttle can launch payloads into space more than once by recovering components like the main engines and solid rocket boosters. To reach higher orbits over 200km, satellites are first launched into a lower transfer orbit using rockets before using onboard motors to circularize into the final destination orbit. Launch procedures take into account factors like the desired orbit, weather conditions, and precise timing.
Optical Inter-Satellite Links for CubeSat SatellitesVladimirFadeev4
The materials belong to the article in Journal of Radioelectronics (https://www.researchgate.net/publication/325756066_OPTICAL_INTER-SATELLITE_LINK_IN_COMPARISON_WITH_RF_CASE_IN_CUBESAT_SYSTEM) and were presented in the II SCIENTIFIC FORUM OF TELECOMMUNICATIONS: THEORY AND TECHNOLOGY TTT-2017 (Kazan, November 20 - 24, 2017).
Attitude Control of Satellite Test Setup Using Reaction WheelsA. Bilal Özcan
This document summarizes a presentation about attitude control of a satellite test setup using reaction wheels. It describes the mathematical models of DC motors, reaction wheels, and the satellite test setup. It also discusses the implementation of a PID controller to control the satellite's orientation by generating angular velocity references for the reaction wheels. Simulation results show that the settling time of the system was decreased from 21.5 seconds to 6.1 seconds by optimizing the PID gains. Future work is planned to consider effects like vibrations and actuator saturations when testing the system.
This document discusses attitude determination and control systems (ADCS) for satellites. It outlines key topics like ADCS sensors, actuators, disturbances, and control techniques. ADCS is needed to stabilize satellites and point them in the required orientation using sensors to determine attitude and actuators to generate torques for control despite external disturbance torques. Common ADCS sensors include earth sensors, sun sensors, star trackers, magnetometers and gyros. Actuators include reaction wheels, magnetic torquers, and thrusters. Control techniques range from passive methods like spin stabilization to active three-axis control using reaction wheels or magnetorquers.
An ejection seat is a system designed to rescue the pilot or crew of an aircraft in an emergency by ejecting them clear of the aircraft. Once clear, the ejection seat deploys a parachute. Ejection seats subject the occupant to high g-forces, around 8 g, during ejection. Modern ejection seats are rocket powered and designed to safely eject occupants even at supersonic speeds. The seat propels the occupant out of the aircraft using an explosive charge or rocket motor.
The Global Positioning System (GPS) is a satellite-based navigation system consisting of a constellation of over two dozen satellites. GPS satellites broadcast precise timing signals that allow GPS receivers to determine their longitude, latitude, and altitude on Earth. Originally developed by the U.S. military, GPS has become vital for navigation worldwide in applications like automobiles, ships, aircraft, and smartphones. It provides location services, timing references, and is used for surveying, agriculture, and more.
Fighter Aircraft Performance, Part I of two, describes the parameters that affect aircraft performance.
For comments please contact me at solo.hermelin@gmail.com.
For more presentations on different subjects visit my website at http://www.solohermelin.com.
The document summarizes a presentation about a CubeSat deployer developed by JSC Space Rocket Center Progress. The deployer is a modular design that can accommodate 1U, 1.5U, 2U, 3U, and 3U+ CubeSats. Simulation results showed the deployer can separate CubeSats at 0.5-0.8 m/s with low angular velocities below 15 degrees/second for 1U and 5 degrees/second for 3U CubeSats. The deployer is planned for its first launch in December 2015 carrying a 3U CubeSat along with other payloads.
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
The document discusses unmanned aerial vehicles (UAVs), also known as drones. It provides background on the origins of UAVs, dating back to 1916. UAVs were further developed for military purposes after World War I and by the US Air Force in 1959. The document outlines the various sub-systems that make up a UAV, including communications, navigation, monitoring, collision avoidance, and weather systems. Examples are given of commercial and Indian-made UAVs, as well as their various uses and advantages such as reduced risk compared to manned flights. Potential disadvantages like hacking and weather vulnerability are also noted.
A launch vehicle is a system used to launch satellites into stable orbits. It works on Newton's third law of motion, where the exhaust gases ejected from the rocket engine provide an equal and opposite reaction force that propels the launch vehicle upward. Launch vehicles are classified based on their payload capacity and number of stages. India's space agency ISRO has used several launch vehicles over the years of increasing capability, starting with the SLV, then the ASLV, and now predominantly uses the PSLV and GSLV.
This document provides information about hypersonic vehicles and the materials needed to withstand their extreme conditions. It begins by defining different speed regimes from subsonic to hypersonic. It then discusses the history of hypersonic vehicles and some current examples like the Boeing X-51 scramjet. Next, it focuses on Indian hypersonic missiles BrahMos-II and Shaurya. The document also explains scramjet engines and the special composite materials required for surfaces that experience temperatures over 1,260°C during hypersonic flight.
The document discusses the design and construction of rocket thrust chamber bodies. It describes how rocket thrust chambers must withstand extreme temperatures and pressures during combustion. They are typically constructed of double-walled cylinders with inner walls made of high-conductivity and high-strength copper alloys to withstand the heat, and outer walls made of stainless steel. The document outlines the major fabrication steps involving powder production, forming cylinders, welding, machining, and coating the inner wall with protective materials. It also discusses the material properties and applications of rocket thrust chambers.
Indian space launch vehicles have evolved over time, starting with small sounding rockets in the 1960s for upper atmospheric research carrying up to 100 kg payloads. India's first experimental satellite launch vehicle was the SLV-3 in 1980, capable of placing 40 kg in low Earth orbit. The Augmented Satellite Launch Vehicle (ASLV) program in the late 1980s doubled payload to 150 kg. The Polar Satellite Launch Vehicle (PSLV) introduced in the 1990s was India's first to use liquid fuel and has successfully launched numerous Indian and international satellites. The Geosynchronous Satellite Launch Vehicle (GSLV) provides heavy lift capability to geostationary transfer orbit. Its latest variant, GSLV Mk III, has increased payload capacity
This document provides an overview of the design and fabrication of a tricopter drone. It describes the motivation to build the tricopter with a low budget and light weight. The key components of the tricopter include three brushless motors, an Atmega168PA controller board, receiver, batteries, and a glass fiber frame. Challenges in the design included balancing the tricopter and integrating the gyroscope and accelerometer. Testing involved mechanical design, propeller selection, electrical connections, and programming the controller board. The conclusion discusses potential applications in military, industrial, and commercial uses if further funding and experimental analysis are conducted.
This document discusses vertical take-off and landing (VTOL) aircraft. It defines VTOL aircraft as those that can hover, take off, and land vertically without needing a runway. There are two main types of VTOL technology: rotorcraft and powered lift. Rotorcraft use rotating blades like helicopters to generate lift, while powered lift vehicles direct thrust downward for vertical flight. Examples of different VTOL aircraft are provided like helicopters, tiltrotors, tiltwings and tail-sitters. Advantages of VTOL include removing the need for runways and making air travel safer. The document concludes that while VTOL aircraft are not yet economical, they may have an important role in future aviation.
Cube Satellites are standardized Nano-satellites for space researches and applications. CubeSat can be created using COTS Hardware and is a very creative utilizing of the knowledge of Embedded Systems and various MEMS sensor devices
A CubeSat (U-class spacecraft) is a type of miniaturized satellite for space research that is made up of multiples of 10×10×10 cm cubic units. CubeSats have a mass of no more than 1.33 kilograms per unit.
The document discusses ejection seats and their components and functioning. It provides details about:
1) The basic components of an ejection seat including the catapult, rocket, restraints and parachute.
2) The ejection sequence which involves seat activation, canopy jettisoning, seat ejection using a rocket catapult, drogue parachute deployment, seat separation, and recovery parachute deployment.
3) The ACES II ejection seat which uses electronic sequencing and timing, has auto sensing capabilities, and multi-mode operation for recovery in different speed and altitude conditions.
This seminar gives idea about spacecraft propulsion i.e., actually what are different latest modes of propulsion are used in space agency and also the introduction of combustion of propellants.
Satellites are launched into orbit using launch vehicles, which can be either expendable or reusable. Expendable vehicles are designed for single use and are not recovered after launch, while reusable vehicles like the Space Shuttle can launch payloads into space more than once by recovering components like the main engines and solid rocket boosters. To reach higher orbits over 200km, satellites are first launched into a lower transfer orbit using rockets before using onboard motors to circularize into the final destination orbit. Launch procedures take into account factors like the desired orbit, weather conditions, and precise timing.
Optical Inter-Satellite Links for CubeSat SatellitesVladimirFadeev4
The materials belong to the article in Journal of Radioelectronics (https://www.researchgate.net/publication/325756066_OPTICAL_INTER-SATELLITE_LINK_IN_COMPARISON_WITH_RF_CASE_IN_CUBESAT_SYSTEM) and were presented in the II SCIENTIFIC FORUM OF TELECOMMUNICATIONS: THEORY AND TECHNOLOGY TTT-2017 (Kazan, November 20 - 24, 2017).
Attitude Control of Satellite Test Setup Using Reaction WheelsA. Bilal Özcan
This document summarizes a presentation about attitude control of a satellite test setup using reaction wheels. It describes the mathematical models of DC motors, reaction wheels, and the satellite test setup. It also discusses the implementation of a PID controller to control the satellite's orientation by generating angular velocity references for the reaction wheels. Simulation results show that the settling time of the system was decreased from 21.5 seconds to 6.1 seconds by optimizing the PID gains. Future work is planned to consider effects like vibrations and actuator saturations when testing the system.
This document discusses attitude determination and control systems (ADCS) for satellites. It outlines key topics like ADCS sensors, actuators, disturbances, and control techniques. ADCS is needed to stabilize satellites and point them in the required orientation using sensors to determine attitude and actuators to generate torques for control despite external disturbance torques. Common ADCS sensors include earth sensors, sun sensors, star trackers, magnetometers and gyros. Actuators include reaction wheels, magnetic torquers, and thrusters. Control techniques range from passive methods like spin stabilization to active three-axis control using reaction wheels or magnetorquers.
An ejection seat is a system designed to rescue the pilot or crew of an aircraft in an emergency by ejecting them clear of the aircraft. Once clear, the ejection seat deploys a parachute. Ejection seats subject the occupant to high g-forces, around 8 g, during ejection. Modern ejection seats are rocket powered and designed to safely eject occupants even at supersonic speeds. The seat propels the occupant out of the aircraft using an explosive charge or rocket motor.
The Global Positioning System (GPS) is a satellite-based navigation system consisting of a constellation of over two dozen satellites. GPS satellites broadcast precise timing signals that allow GPS receivers to determine their longitude, latitude, and altitude on Earth. Originally developed by the U.S. military, GPS has become vital for navigation worldwide in applications like automobiles, ships, aircraft, and smartphones. It provides location services, timing references, and is used for surveying, agriculture, and more.
Fighter Aircraft Performance, Part I of two, describes the parameters that affect aircraft performance.
For comments please contact me at solo.hermelin@gmail.com.
For more presentations on different subjects visit my website at http://www.solohermelin.com.
The document summarizes a presentation about a CubeSat deployer developed by JSC Space Rocket Center Progress. The deployer is a modular design that can accommodate 1U, 1.5U, 2U, 3U, and 3U+ CubeSats. Simulation results showed the deployer can separate CubeSats at 0.5-0.8 m/s with low angular velocities below 15 degrees/second for 1U and 5 degrees/second for 3U CubeSats. The deployer is planned for its first launch in December 2015 carrying a 3U CubeSat along with other payloads.
This document summarizes a student project called O.S.C.A.R. that aims to design a CubeSat to help remove space debris from orbit. It outlines the system design including using a net launcher to capture debris less than 10 cm in size, processing images with a computer and FPGA to locate and identify debris, and deorbiting the captured debris within a year by performing retrograde burns with a propulsion system. The document provides details on the mission objectives, structure, power, communications, and analyses performed to model the attitude determination, thermal, and orbital maneuvering aspects of the CubeSat's debris removal mission.
O Caixa Empreender Award atribuiu um valor de investimento adicional, no valor de 100 mil euros, ao projeto que mais se destacou de um conjunto de 7 startups, previamente selecionadas no âmbito dos programas de aceleração que contam com o apoio do Grupo CGD, BGI, Lisbon Challenge e ACT by COTEC.
A D Orbit foi uma das startups presentes no Caixa Empreender. #thefuturefromscratch
Mais sobre o objetivo deste evento em: http://bit.ly/1CzA5BV
NASA World Wind Virtual Globe Technologyand the WW Europa ChallengeRaffaele de Amicis
1. NASA World Wind is open source virtual globe technology that can be used to visualize and analyze geospatial data.
2. The WW Europa Challenge encourages students and businesses to develop applications using World Wind that address topics related to the INSPIRE Directive.
3. The 2013 challenge highlighted apps for historical map visualization, social mapping platforms, and analyzing satellite data. The 2014 challenge focuses on natural hazard modeling and urban infrastructure visualization.
NASA World Wind - Virtual Globe Technology and the WW Europa ChallengeRaffaele de Amicis
Relevance of NASA World Wind, open source, in analysis and visualisation for the EO data and service providers
Earth visualisation: some of the best apps from the WW Europa Challenge 2013
NASA WW Europa Challenge 2014
This document summarizes the NRO CubeSat Program, which uses small CubeSat satellites to support various R&D priorities like university outreach and technology maturation. The program provides a common Colony bus template for payloads and experiments. Colony buses are provided by companies like Pumpkin Inc and Boeing. The program has partnered with over 20 companies, government labs, and universities. Upcoming CubeSat launches include a 2010 SpaceX Falcon 9 rideshare mission and a 2011 ORS Enabler rideshare mission. The goal is to make the Colony bus a standard commodity and help drive government acquisition of CubeSat capabilities.
This document summarizes the 12 Sunsets Project at the Getty Research Institute, which provides access to Ed Ruscha's archive of photographs of Sunset Boulevard taken between 1965-2010 through an IIIF application. The project layers multiple photographs of Sunset Boulevard over time and provides tools for geotagging, text recognition, and image tagging. Scaling the application to the large archive presented challenges around burst traffic that were addressed through load testing and caching strategies using CloudFront and now Varnish Cache. Ongoing challenges include geographic latency and flexible invalidation across caching layers.
This document summarizes several projects that STL provided engineering services for, including electronic design, firmware development, and system architecture support. It lists clients such as EBMCE, ABCU, GSTAMIDS, NFIRE, and NASA. For each project, it briefly describes the technical services provided, dates, and STL staff roles like senior designer, consultant, or contractor.
Presentation shown as part of the GeoChronos Demonstration at SC09 in Portland on Nov. 17th and Nov. 18th, 2009. (Similar to the GeoChronos - CANARIE NEP Showcase Presentation with a few minor revisions.)
The document discusses models and experiments to analyze the tip-off rate dynamics of CubeSats during separation from deployers. A simplified model and complex ADAMS model were developed to simulate the effects of parameters like center of mass position, spring stroke, and gap between guide rails on tip-off rate. Ground experiments using laser sensors to measure angular velocities of a 3U CubeSat mock-up showed results that agreed satisfactorily with simulations. The models and experiments allow estimating tip-off rates to help design CubeSat deployers that minimize initial angular velocities.
Planet has the ambitious goal of imaging everywhere on earth once per day with a fleet of small satellites. Now with over 100 operational satellites, Planet is collecting over a hundred million square kilometers of remote sensing data every day and for the first time we are able to take actions based on the daily changes that we observe. In addition to this unique data set, Planet has taken an 'API-first' approach to distributing data, allowing our users to build their own applications or integrations directly on our platform services. Safe Software's own Planet transformer is a great example of this kind of integration, giving FME users easy access to Planet's growing archive of satellite imagery.
Sky Observation LogCourse PHSC 111 DLA Introduction to Ast.docxbudabrooks46239
Sky Observation Log
Course: PHSC 111 DLA Introduction to Astronomy
Name: Shana Williams
Page ___1___ of ___1___
Bradford Robotic Telescope (BRT) Username:
BRT Password:
P - Personal Observation
B - Bradford Observation
Date (MM/DD/YYYY)
Start Time (0000-2359) (0000 = midnight)
weather conditions
Location
Equipment Used
Sky Object Observed (identify objects by name)
Comments
P
09/13/2012
2114
cloudy
142nd and Lenox
, New York, NY
IPHONE
Star of Pisces and Planet Uranus
although cloudy, was able to to see Uranus very clearly ( did not know you could actually see them as stars!)
B
9/22/2012
2223
Rain/ cloudy
142nd and Lenox
, New York, NY
IPHONE
Star Foamhault and Planet Neptune
Skies were very dark therefore no stars were really apparent. Dark clouds
P
9/27/2012
2115
Rainy/ Cloudy
142nd and Lenox
, New York, NY
IPHONE
Stars Enif and Vega
Skies were very dark and cloudy
P
10/5/2012
2100
Cloudy/rain
142nd and Lenox
, New York, NY
IPHONE
Full moon
Alnitak Rigel and Betcleguse stars spotted
Skies were very dark and cloudy
P
10/13/2012
1935
Clear skies
1020 House St. Columbia, SC
IPHONE
Star Spica and Aries, Altair
Skies were very clear. Very light pollution so skies were very visual. ( Best observation yet!)
P
10/19/2012
0021
Rain/ cloudy
601 W. 26th St. New York, NY
IPHONE
Denebola star Venus star
Hydra consellation
Very polluted because the observation was taken place right in Manhattan. Could not spot a star!
Solar System Symbols
Web Address Description / Title
http://www.worldwidetelescope.org/Home.aspx virtual telescope
http://www.nasa.gov/ multimedia information about space exploration
http://cas.sdss.org/dr7/en/ project to map the universe
http://astrosociety.org/education/resources/educsites.html website listing for astronomy instructors
http://www.mpe.mpg.de/ir/GC/index.php black holes
http://www.astrosociety.org/ Astronomical Society of the Pacific
http://coolcosmos.ipac.caltech.edu/cosmic_classroom/ask_astronomer/video/ video explanations of common astronomy questions
http://science.nasa.gov/ multimedia science news
http://161.58.115.79/education/podcast/ Silicon Valley Astronomy Lecture podcasts
http://www.astronomycenter.org/index.cfm?
teaching and learning resources for undergraduate Introductory
Astronomy courses
http://phet.colorado.edu/sims/my-solar-system/my-solar-system.swf simulation of solar system
http://www.michielb.nl/maya/astro.html Mayan astronomy
http://mpfwww.jpl.nasa.gov/ Mars exploration program
http://seds.lpl.arizona.edu/ exploration and development in space
http://www.skyandtelescope.com/ multimedia astronomy resources
http://www.ssec.wisc.edu/ Space Science and Engineering Center, media
http://hubblesite.org/ universe through eye of Hubble telescope, multimedia
http://www.astronomy2009.org/ International Year of Astronomy 2009
http://nasaimages.org/ collection of images from NASA
http://www.nasa.gov/multimedia/ NASA mulitmedia plus liv.
Puli space snooping_for_water_iloa_gfe_2020 tibor pacherILOAHawaii
Puli Space Technologies is a company founded in 2010 that is developing small payloads and instruments to detect water and other resources on the lunar surface. They have field tested prototypes, won NASA challenges, and are working to raise their technology readiness level. Their Puli Lunar Water Snooper uses neutron spectroscopy to detect hydrogen and infer water content in lunar regolith. They plan to fly their instruments on upcoming commercial lunar missions starting in 2021.
The document summarizes the NASA WWEC 2015, an open source app challenge using NASA's World Wind platform. It discusses the history and goals of WWEC, criteria for submissions, winners in the academic and professional tracks, and commitments to expand use of the World Wind platform internationally including by government agencies and the UN.
This document provides an introduction to CubeSats for first-time developers. It discusses the basics of CubeSats, including standard CubeSat sizes and dispenser systems used to deploy them from launch vehicles. It then gives an overview of the multi-step development process for a CubeSat project, from initial concept through launch and operations. Finally, it introduces some common mission models and requirements sources that CubeSat developers must consider to successfully design, build, test, launch and operate their small satellites. The goal is to lay out everything needed to take a CubeSat idea from concept to becoming an actual spacecraft in orbit.
The ARROWS Project aims to develop and adapt robotic technologies for underwater archaeology. Funded by the EU, the project involves 10 partners across Europe. The goals are to use customized autonomous underwater vehicles (AUVs) to create high quality maps of large underwater areas and shipwrecks through horizontal surveys. New AUVs like MARTA and the biomimetic U-CAT robot are being developed to penetrate shipwrecks and provide rich payloads like sonar and cameras. The project has conducted demonstrations in Sicily and the Baltic Sea to test the vehicles and technologies.
NASA Airborne Instrumentation for Real-world Video of Urban Environments Crow...Dr. Pankaj Dhussa
NASA
National Aeronautics and Space Administration
NASA Airborne Instrumentation for Real-world Video of Urban Environments
Crowdsourcing large, diverse datasets for computer vision
By
Dr. Pankaj Dhussa
The document describes the design, construction, and programming of an octocopter drone intended to scan and model buildings in 3D. An octocopter frame was built using metal and 3D printed parts with eight motors, batteries, and an autopilot system. Software was programmed to take photos from the drone's camera during flight and stitch them together into a 3D model. Testing progressed from tethered indoor flights to autonomous outdoor flights following programmed paths. The final successful result was a functioning octocopter capable of automated building scans and 3D modeling.
Similar to 1U-3U+ Cubesat Deployer by JSC SRC "Progress" (20)
Обзор работ 7-ой Европейской конференции по космическому мусору (офис центра управления полетами ЕКА, Дармштадт, Германия, 18-21 апреля 2017 г)
Презентация к семинару кафедры теоретической механики Самарского университета (16.05.17)
Презентация к семинару кафедры теоретической механики. По материалам статьи “Detumbling Space Debris Using Modified Yo-Yo Mechanism” (Юдинцев В. В.,
Асланов В. С.) Journal of Guidance, Control, and Dynamics, Vol. 40, No. 3. https://arc.aiaa.org/doi/abs/10.2514/1.G000686
(2017), pp. 714-721.
Основы языка Питон: функции, элементы функционального программирования, списочные выражения, генераторы. Презентация к лекции курса "Технологии и языки программирования".
The document analyzes the chaotic motions that can occur for tethered satellite systems with low thrust. It describes the system and assumptions, presents the motion equations, and identifies stationary solutions. Orbital eccentricity and out-of-plane oscillations are shown to induce chaos if they cause an unstable equilibrium condition. The choice of thrust level, satellite masses, and tether length must satisfy conditions to ensure regular in-plane motion even in an elliptic orbit.
The document proposes using an Autonomous Docking Module (ADM) attached to a space tug by tether to remove orbital debris. The ADM would use a probe-cone mechanism to dock with the target debris, a spent orbital stage, without its cooperation. A mathematical model is developed to simulate the docking process between the ADM and tumbling target. Further simulation and development of rendezvous scenarios and a testbed mission are recommended to validate the concept.
The document describes the chaotic behavior that can occur in a system consisting of a space tug, viscoelastic tether, and space debris. A mathematical model is developed to describe the transverse and longitudinal oscillations of the tether. The model shows that chaos is possible when the longitudinal oscillations are perturbed. Poincare sections are used to reveal a stochastic layer in the system's motion due to damping in the tether. The results suggest that chaos can be observed in the attitude motion of the tethered tug-debris system caused by longitudinal oscillations of the viscoelastic tether.
Презентация для IV Всероссийской научно-технической
конференции "Актуальные проблемы ракетно-космической техники» ("IV Козловские чтения")". г. Самара, 14-17 сентября 2015 г.
The document discusses active debris removal in space using tethered towing. The authors have developed a mathematical model of the attitude motion of a debris-tether-tug system. The model accounts for factors such as flexible appendages on the debris, fuel residuals, tether properties, and environmental forces. The authors aim to further study the capture dynamics of debris and stabilization after capture, and create a comprehensive model covering all stages from initial capture to atmospheric reentry.
Null Bangalore | Pentesters Approach to AWS IAMDivyanshu
#Abstract:
- Learn more about the real-world methods for auditing AWS IAM (Identity and Access Management) as a pentester. So let us proceed with a brief discussion of IAM as well as some typical misconfigurations and their potential exploits in order to reinforce the understanding of IAM security best practices.
- Gain actionable insights into AWS IAM policies and roles, using hands on approach.
#Prerequisites:
- Basic understanding of AWS services and architecture
- Familiarity with cloud security concepts
- Experience using the AWS Management Console or AWS CLI.
- For hands on lab create account on [killercoda.com](https://killercoda.com/cloudsecurity-scenario/)
# Scenario Covered:
- Basics of IAM in AWS
- Implementing IAM Policies with Least Privilege to Manage S3 Bucket
- Objective: Create an S3 bucket with least privilege IAM policy and validate access.
- Steps:
- Create S3 bucket.
- Attach least privilege policy to IAM user.
- Validate access.
- Exploiting IAM PassRole Misconfiguration
-Allows a user to pass a specific IAM role to an AWS service (ec2), typically used for service access delegation. Then exploit PassRole Misconfiguration granting unauthorized access to sensitive resources.
- Objective: Demonstrate how a PassRole misconfiguration can grant unauthorized access.
- Steps:
- Allow user to pass IAM role to EC2.
- Exploit misconfiguration for unauthorized access.
- Access sensitive resources.
- Exploiting IAM AssumeRole Misconfiguration with Overly Permissive Role
- An overly permissive IAM role configuration can lead to privilege escalation by creating a role with administrative privileges and allow a user to assume this role.
- Objective: Show how overly permissive IAM roles can lead to privilege escalation.
- Steps:
- Create role with administrative privileges.
- Allow user to assume the role.
- Perform administrative actions.
- Differentiation between PassRole vs AssumeRole
Try at [killercoda.com](https://killercoda.com/cloudsecurity-scenario/)
Discover the latest insights on Data Driven Maintenance with our comprehensive webinar presentation. Learn about traditional maintenance challenges, the right approach to utilizing data, and the benefits of adopting a Data Driven Maintenance strategy. Explore real-world examples, industry best practices, and innovative solutions like FMECA and the D3M model. This presentation, led by expert Jules Oudmans, is essential for asset owners looking to optimize their maintenance processes and leverage digital technologies for improved efficiency and performance. Download now to stay ahead in the evolving maintenance landscape.
KuberTENes Birthday Bash Guadalajara - K8sGPT first impressionsVictor Morales
K8sGPT is a tool that analyzes and diagnoses Kubernetes clusters. This presentation was used to share the requirements and dependencies to deploy K8sGPT in a local environment.
Software Engineering and Project Management - Introduction, Modeling Concepts...Prakhyath Rai
Introduction, Modeling Concepts and Class Modeling: What is Object orientation? What is OO development? OO Themes; Evidence for usefulness of OO development; OO modeling history. Modeling
as Design technique: Modeling, abstraction, The Three models. Class Modeling: Object and Class Concept, Link and associations concepts, Generalization and Inheritance, A sample class model, Navigation of class models, and UML diagrams
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Introduction- e - waste – definition - sources of e-waste– hazardous substances in e-waste - effects of e-waste on environment and human health- need for e-waste management– e-waste handling rules - waste minimization techniques for managing e-waste – recycling of e-waste - disposal treatment methods of e- waste – mechanism of extraction of precious metal from leaching solution-global Scenario of E-waste – E-waste in India- case studies.
Use PyCharm for remote debugging of WSL on a Windo cf5c162d672e4e58b4dde5d797...shadow0702a
This document serves as a comprehensive step-by-step guide on how to effectively use PyCharm for remote debugging of the Windows Subsystem for Linux (WSL) on a local Windows machine. It meticulously outlines several critical steps in the process, starting with the crucial task of enabling permissions, followed by the installation and configuration of WSL.
The guide then proceeds to explain how to set up the SSH service within the WSL environment, an integral part of the process. Alongside this, it also provides detailed instructions on how to modify the inbound rules of the Windows firewall to facilitate the process, ensuring that there are no connectivity issues that could potentially hinder the debugging process.
The document further emphasizes on the importance of checking the connection between the Windows and WSL environments, providing instructions on how to ensure that the connection is optimal and ready for remote debugging.
It also offers an in-depth guide on how to configure the WSL interpreter and files within the PyCharm environment. This is essential for ensuring that the debugging process is set up correctly and that the program can be run effectively within the WSL terminal.
Additionally, the document provides guidance on how to set up breakpoints for debugging, a fundamental aspect of the debugging process which allows the developer to stop the execution of their code at certain points and inspect their program at those stages.
Finally, the document concludes by providing a link to a reference blog. This blog offers additional information and guidance on configuring the remote Python interpreter in PyCharm, providing the reader with a well-rounded understanding of the process.
Batteries -Introduction – Types of Batteries – discharging and charging of battery - characteristics of battery –battery rating- various tests on battery- – Primary battery: silver button cell- Secondary battery :Ni-Cd battery-modern battery: lithium ion battery-maintenance of batteries-choices of batteries for electric vehicle applications.
Fuel Cells: Introduction- importance and classification of fuel cells - description, principle, components, applications of fuel cells: H2-O2 fuel cell, alkaline fuel cell, molten carbonate fuel cell and direct methanol fuel cells.
Electric vehicle and photovoltaic advanced roles in enhancing the financial p...IJECEIAES
Climate change's impact on the planet forced the United Nations and governments to promote green energies and electric transportation. The deployments of photovoltaic (PV) and electric vehicle (EV) systems gained stronger momentum due to their numerous advantages over fossil fuel types. The advantages go beyond sustainability to reach financial support and stability. The work in this paper introduces the hybrid system between PV and EV to support industrial and commercial plants. This paper covers the theoretical framework of the proposed hybrid system including the required equation to complete the cost analysis when PV and EV are present. In addition, the proposed design diagram which sets the priorities and requirements of the system is presented. The proposed approach allows setup to advance their power stability, especially during power outages. The presented information supports researchers and plant owners to complete the necessary analysis while promoting the deployment of clean energy. The result of a case study that represents a dairy milk farmer supports the theoretical works and highlights its advanced benefits to existing plants. The short return on investment of the proposed approach supports the paper's novelty approach for the sustainable electrical system. In addition, the proposed system allows for an isolated power setup without the need for a transmission line which enhances the safety of the electrical network
Optimizing Gradle Builds - Gradle DPE Tour Berlin 2024Sinan KOZAK
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CHINA’S GEO-ECONOMIC OUTREACH IN CENTRAL ASIAN COUNTRIES AND FUTURE PROSPECTjpsjournal1
The rivalry between prominent international actors for dominance over Central Asia's hydrocarbon
reserves and the ancient silk trade route, along with China's diplomatic endeavours in the area, has been
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China is seeing significant success in commerce, pipeline politics, and gaining influence on other
governments. This success may be attributed to the effective utilisation of key tools such as the Shanghai
Cooperation Organisation and the Belt and Road Economic Initiative.
4. Historical Background
1896 2010
1957
1910 1941-1945 2010
2013 2013
1st Latin American IAA CubeSat WorkShop. Brasília, Brasil. December 8th - 11th, 2014 4
5. Launch service
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Mars-Express (ESA) Resurs-P (Russia) Pleyades (ESA) Gaia (ESA)
Over 1800 manned
and unmanned
launches of the
Soyuz rocket since
1967
More than 90
launches of
spacecraft were
performed since
1999 under the
agreement with
Obzor-R (Russia) 2015 foreign customers.
6. Bion-M with piggyback satellites
Bion-M is a large spacecraft for
research in the field of space
biology and medicine.
Launch of Bion-M № 1 was
performed in 2013.
Aist spacecraft and five foreign
small satellites of CubeSat type
were used as a piggyback
payload.
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Image source: http://samspace.ru/multimedia/images/selected_images/142/
8. Multi-interface (satellites or
orbital stages)
Reliable and proven
components
Experimental validation
No debris
Design Principles
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9. Modular design
Door module
Hinges, latches, hold down and
release mechanism
Base module
Guide rails
Separation spring module
Separation spring, platform
with guide rails
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10. Multi-format
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1U 2U 3U, 3U+
Modular design allows to
build deployers for various
CubeSat form-factors
Set of separation springs is
developed to separate
satellites at a speed from 0.5
to 0.8 m/s
11. Sensors
The separation sensor detects
the separation of the CubeSat
from the platform
The temperature sensor
measures the temperature inside
the base module. All the surfaces
of the deployer are wrapped by a
multi-layer Insulation
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12. CubeSat Requirements
Form factors:
1U, 1.5U
2U
3U, 3U+
Standard CubeSat
requirements*
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*Munakata, Riki. "Cubesat design specification rev. 13." The CubeSat Program, California Polytechnic State University 1 (2009).
14. Separation dynamics
Separation speed
0.5 … 0.8 m/s
Angular velocity
1U CubeSats: < 15 °/s
3U CubeSats: < 5 °/s
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15. Angular velocity of 1U CubeSat
Angular velocity of 1U CubeSat
for different COG offset and δ =0.5 mm
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16. Angular velocity of 3U CubeSat
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Angular velocity of 3U CubeSat
for different COG offset and δ =0.5 mm
17. 3-Unit Deployer Simulation
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19. Transfer compartment
Image source: R.N. Akhmetov et al. Low-cost launch services for micro satellites by means of utilization
of Soyuz orbital stage Small Satell. Earth Obs. Dig. 7-th Int. Symp. Int. Acad. Astronaut. Berlin, 2009.
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20. Transfer compartment
H≈250-300 km
The orbital stage is rotated by
gas engine after the separation
of the main payload
The attitude motion of the
orbital stage will affect to the
motion of the separated
CubeSats
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21. Satellites
Bion-M / Foton-M
satellites
Circular orbit
H = 500 – 600 km
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Platform for external equipment
22. “Volga” upper stage
H=1000 km, i = 62.8°
H=1500 km, i = 82.4°
H=835 km, i = 98.7° (SSO)
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Image source: http://samspace.ru/multimedia/images/selected_images/103/
23. Main payloads
Aist-2, Lomonosov
Additional payload
3U CubeSat SamSat-218/D
Planned start date
December 2015
Space-launch complex
Vostochny
The First Launch
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24. Key features of the Deployer
Modular multiformat design: 1U, 1.5U, 2U, 3U, 3U+
Low angular velocities of separated satellites
High reliability p>0,999
Temperature sensor
Separation sensor
Passive thermal control system
Adaptation to the SRC space vehicles
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25. The CubeSat deployer developer team
Vadim Yudintsev, Dmitriy Zaretskiy, Eugeni Kosmodemyanskii , Oksana Vagner,
Aleksandr Romanov, Maxim Sivov, Maxim Trusov
1st Latin American IAA CubeSat WorkShop. Brasília, Brasil. December 8th - 11th, 2014
26. Contacts
JSC SRC «Progress»,
18, Zemetsa str., Samara, Russia
Phone: +7 (846) 955-13-61
Fax: +7 (846) 992-65-18
e-mail: ved878@samspace.ru
1st Latin American IAA CubeSat WorkShop. Brasília, Brasil. December 8th - 11th, 2014
http://www.samspace.ru
Editor's Notes
Good morning, Ladies and Gentlemen! My name is Vadim Yudintsev.
I represent Space Rocket Center “Progress”.
In this presentation I’d like to focus on recent developments in our CubeSats Deployer Project.
My talk is divided into 4 parts and will last about 10 minutes.
I'll start with a brief history of our company.
Then I'll go on to the CubeSat deployer design.
Next I'll talk a few words about the separation dynamics of CubeSats and finally I'll take a look at the installation of the deployer on launch vehicles.
At the end of my presentation I will distribute some handouts and reply to questions that you may have.
Let me start by telling you a brief history of our company.
Space Rocket Center “Progress” was established more than a century ago as a factory that produced bicycles.
Ten years later it built cars and airplanes.
During World War II the factory was evacuated from Moscow to Samara and renamed to State Aviation Plant.
More than 10,000 legendary ground attack aircrafts IL-2 were produced in those years.
The "Space" history of our company started in 1959. In this year our R-7 rocket was launched.
This rocket is an ancestor of the well known Soyuz family rockets.
Soyuz family rockets are used to launch satellites and manned spacecraft.
The Soyuz rocket is the launch vehicle most frequently used in the world.
More than 12 launches are performed every year.
Soyuz family rockets are launched from 3 launch sites: Baikonur, Plesetsk, French Guiana.
In 2015 an upgraded Soyuz-2 rocket will be launched from a new cosmodrome “Vostochny”.
We think that this launch capability can be used more effectively particularly for educational purposes.
In 2013 a small satellite Aist and five CubeSats were successfully separated from the Bion-M satellite. At this picture you can see the Bion-M satellite and the platform for external equipment that carries five CubeSats.
For that launch the control logic of the satellite was specially adapted to ISIPOD and FlyMate CubeSat deployers.
We enjoyed this experience and decided to develop our CubeSat deployer for effective cooperation with educational institutions and research groups.
Well, what I’m going to do now is to point out the main principles of the deployer’s design:
- the deployer must interface with a variety of our launch vehicles with no changes to the CubeSat specifications;
- only reliable, proven and possibly low cost components should be used;
- all new mechanisms have to be validated through laboratory experiments;
- the deployer does not have to produce any debris.
- the deployer must interface with a variety of our launch vehicles with no changes to the CubeSat specifications;
- only reliable, proven and possibly low cost components should be used;
- all new mechanisms have to be validated through laboratory experiments;
- the deployer does not have to produce any debris.
Ответ на возможный вопрос об устройстве открытия крышки.
For the first launch in the door hold down and release mechanism reliable low shock pyrotechnic pin-puller will be used, that easily adapted to the interface of our space vehicles.
The deployer consists of three parts or modules:
- the base module includes guide rails;
- the door module includes rotation springs, hinges, a latch and a hold down and release mechanism;
- the separation spring module includes a separation spring and a platform base with guide rails.
The modular design allows us to build a customized deployer.
At this picture you can see three possible configurations of the CubeSat deployer for 1U, 2U and 3U cubesats.
The deployer includes two sensors.
The temperature sensor measures temperature inside the base module.
The separation sensor indicates the separation of the CubeSat from the platform.
To minimize power loss to, or gain from, the environment a multi Layer Insulation is used to wrap all the deployer’s surfaces.
There are no special requirements for satellites that can be launched using the deployer.
But satellites should meet the well known CubeSat Design Specification.
Now, I’d like to describe the CubeSat separation process.
As you know small satellites often use passive stabilization system: gravity, aerodynamic, electromagnetic.
The effectiveness of these systems depends on the initial conditions of the attitude motion of a satellite. Therefore, particular attention was given to the minimization of the angular velocity of separated satellites.
We’ve developed several mathematical models of the separation process.
Here is the scheme of one simple model.
Preliminary results that will be validated by laboratory experiments show that the angular velocity of a separated СubeSat will be less than 15 degrees per second.
This figure shows the angular velocity of the 1-U satellite for the various center of mass positions relative to the longitudinal axis of the satellite.
For the all cases the angular velocity is less than 15 degrees per second.
Our tentative estimate of the 3U CubeSat angular velocity is even lower than 5 degrees per second.
But we expect that the experiments will confirm our optimistic and ambitious estimates that the 3U CubeSat angular velocity will be lower than 1 degree per second.
To make this happen, we’ve decreased the minimum gap between the deployer and the satellite guide rails and increased the length of the platform.
Moreover, we’ve decreased the stroke of the platform to two-thirds of the length of the deployer (оставить для вопроса).
Here you can see the simulation of a 3-Unit CubeSat ejection.
The next question is where the deployer can be installed.
The first option is the transfer compartment on the Soyuz family rockets.
This picture shows a possible arrangement of the deployers in the transfer compartment.
The CubeSats should be separated after the separation of the main payload to avoid the collision.
Also non-separated equipment for short-term scientific research can be installed in the transfer compartment. The lifetime of the orbital stage is about several days.
Note that after the separation of the main payload the orbital stage is de-orbited using a thrust nozzle.
Here you can see the relative motion of the main payload and the orbital stage.
It's obvious that the separation from the rotating orbital stage will cause an increase in the angular velocity of the separated satellites.
So satellites that do not need the low angular velocity can be installed in the transfer compartment.
The deployers can be installed as piggyback payload on large satellites. As I said before the Bion-M satellite can be equipped with a platform for small satellite deployers.
Here you can see this platform that was used to deploy satellites in 2013.
CubeSats can be ejected from the upper stage Volga after or before the separation of the main payload.
The Upper stage Volga can reach a variety of orbits up to 1500 km.
The upper stage has high potential to deploy small satellites into orbit.
3 unit CubeSat SamSat will be separated from the orbital stage Volga using our deployer next year.
This CubeSat is developed by students of Samara State Aerospace University.
The main objective of this satellite is a demonstration of navigation and control technologies.
This CubeSat will be placed in orbit with two other satellites – a small satellite “Aist-2”, which is designed by the young scientists and students of the Aerospace University in partnership with specialists of the Space Rocket Centre ”Progress” and the “Lomonosov” satellite made by Moscow State University.
In December 2015 these satellites will go into space from the cosmodrome “Vostochniy”.
It will be the first launch from this spaceport.
In conclusion I’d like to summarize the main points of my talk.
The presented deployer has a modular multiformat design that allows to eject cubesats from 1U to 3U at low angular velocities.
The deployer uses a passive thermal control system and includes two sensors to measure temperature and indicate the separation.
The deployer is adapted to the space vehicles of the space rocket center.
Here is our great developer team.
So we are interested in cooperation and we hope that our space vehicles will help make the space closer to all of us!
Thank you for your attention!
If you have any questions, I’m happy to answer them.