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In-Depth Review of Satellite Imagery / Earth Observation Technology in Official Statistics Prepared by Canada and Mexico
In-depth review of satellite imagery / earth observation technology in official statistics Prepared by Canada and Mexico Julio A. Santaella Conference of European Statisticians 67th plenary session Paris, France June 28, 2019 Earth observation (EO) EO is the gathering of information about planet Earth’s physical, chemical and biological systems. It involves monitoring and assessing the status of, and changes in, the natural and man-made environment Measurements taken by a thermometer, wind gauge, ocean buoy, altimeter or seismograph Photographs and satellite imagery Radar and sonar images Analyses of water or soil samples EO examples EO Processed information such as maps or forecasts Source: Group on Earth Observations (GEO) In-depth review of satellite imagery / earth observation technology in official statistics 2 Introduction Satellite imagery uses have expanded over time Satellite imagery provide generalized data for large areas at relatively low cost: Aligned with NSOs needs to produce more information at lower costs NSOs are starting to consider EO technology as a data collection instrument for purposes beyond agricultural statistics In-depth review of satellite imagery / earth observation technology in official statistics 3 Scope and definition of the review To survey how various types of satellite data and the techniques used to process or analyze them support the GSBPM To improve coordination of statistical activities in the UNECE region, identify gaps or duplication of work, and address emerging issues In-depth review of satellite imagery / earth observation technology in official statistics 4 Overview of recent activities • EO technology has developed progressively, encouraging the identification of new applications of this infrastructure data. -
Astrodynamics
Politecnico di Torino SEEDS SpacE Exploration and Development Systems Astrodynamics II Edition 2006 - 07 - Ver. 2.0.1 Author: Guido Colasurdo Dipartimento di Energetica Teacher: Giulio Avanzini Dipartimento di Ingegneria Aeronautica e Spaziale e-mail: [email protected] Contents 1 Two–Body Orbital Mechanics 1 1.1 BirthofAstrodynamics: Kepler’sLaws. ......... 1 1.2 Newton’sLawsofMotion ............................ ... 2 1.3 Newton’s Law of Universal Gravitation . ......... 3 1.4 The n–BodyProblem ................................. 4 1.5 Equation of Motion in the Two-Body Problem . ....... 5 1.6 PotentialEnergy ................................. ... 6 1.7 ConstantsoftheMotion . .. .. .. .. .. .. .. .. .... 7 1.8 TrajectoryEquation .............................. .... 8 1.9 ConicSections ................................... 8 1.10 Relating Energy and Semi-major Axis . ........ 9 2 Two-Dimensional Analysis of Motion 11 2.1 ReferenceFrames................................. 11 2.2 Velocity and acceleration components . ......... 12 2.3 First-Order Scalar Equations of Motion . ......... 12 2.4 PerifocalReferenceFrame . ...... 13 2.5 FlightPathAngle ................................. 14 2.6 EllipticalOrbits................................ ..... 15 2.6.1 Geometry of an Elliptical Orbit . ..... 15 2.6.2 Period of an Elliptical Orbit . ..... 16 2.7 Time–of–Flight on the Elliptical Orbit . .......... 16 2.8 Extensiontohyperbolaandparabola. ........ 18 2.9 Circular and Escape Velocity, Hyperbolic Excess Speed . .............. 18 2.10 CosmicVelocities -
Electric Propulsion System Scaling for Asteroid Capture-And-Return Missions
Electric propulsion system scaling for asteroid capture-and-return missions Justin M. Little⇤ and Edgar Y. Choueiri† Electric Propulsion and Plasma Dynamics Laboratory, Princeton University, Princeton, NJ, 08544 The requirements for an electric propulsion system needed to maximize the return mass of asteroid capture-and-return (ACR) missions are investigated in detail. An analytical model is presented for the mission time and mass balance of an ACR mission based on the propellant requirements of each mission phase. Edelbaum’s approximation is used for the Earth-escape phase. The asteroid rendezvous and return phases of the mission are modeled as a low-thrust optimal control problem with a lunar assist. The numerical solution to this problem is used to derive scaling laws for the propellant requirements based on the maneuver time, asteroid orbit, and propulsion system parameters. Constraining the rendezvous and return phases by the synodic period of the target asteroid, a semi- empirical equation is obtained for the optimum specific impulse and power supply. It was found analytically that the optimum power supply is one such that the mass of the propulsion system and power supply are approximately equal to the total mass of propellant used during the entire mission. Finally, it is shown that ACR missions, in general, are optimized using propulsion systems capable of processing 100 kW – 1 MW of power with specific impulses in the range 5,000 – 10,000 s, and have the potential to return asteroids on the order of 103 104 tons. − Nomenclature -
AFSPC-CO TERMINOLOGY Revised: 12 Jan 2019
AFSPC-CO TERMINOLOGY Revised: 12 Jan 2019 Term Description AEHF Advanced Extremely High Frequency AFB / AFS Air Force Base / Air Force Station AOC Air Operations Center AOI Area of Interest The point in the orbit of a heavenly body, specifically the moon, or of a man-made satellite Apogee at which it is farthest from the earth. Even CAP rockets experience apogee. Either of two points in an eccentric orbit, one (higher apsis) farthest from the center of Apsis attraction, the other (lower apsis) nearest to the center of attraction Argument of Perigee the angle in a satellites' orbit plane that is measured from the Ascending Node to the (ω) perigee along the satellite direction of travel CGO Company Grade Officer CLV Calculated Load Value, Crew Launch Vehicle COP Common Operating Picture DCO Defensive Cyber Operations DHS Department of Homeland Security DoD Department of Defense DOP Dilution of Precision Defense Satellite Communications Systems - wideband communications spacecraft for DSCS the USAF DSP Defense Satellite Program or Defense Support Program - "Eyes in the Sky" EHF Extremely High Frequency (30-300 GHz; 1mm-1cm) ELF Extremely Low Frequency (3-30 Hz; 100,000km-10,000km) EMS Electromagnetic Spectrum Equitorial Plane the plane passing through the equator EWR Early Warning Radar and Electromagnetic Wave Resistivity GBR Ground-Based Radar and Global Broadband Roaming GBS Global Broadcast Service GEO Geosynchronous Earth Orbit or Geostationary Orbit ( ~22,300 miles above Earth) GEODSS Ground-Based Electro-Optical Deep Space Surveillance -
Detecting, Tracking and Imaging Space Debris
r bulletin 109 — february 2002 Detecting, Tracking and Imaging Space Debris D. Mehrholz, L. Leushacke FGAN Research Institute for High-Frequency Physics and Radar Techniques, Wachtberg, Germany W. Flury, R. Jehn, H. Klinkrad, M. Landgraf European Space Operations Centre (ESOC), Darmstadt, Germany Earth’s space-debris environment tracked, with estimates for the number of Today’s man-made space-debris environment objects larger than 1 cm ranging from 100 000 has been created by the space activities to 200 000. that have taken place since Sputnik’s launch in 1957. There have been more than 4000 The sources of this debris are normal launch rocket launches since then, as well as many operations (Fig. 2), certain operations in space, other related debris-generating occurrences fragmentations as a result of explosions and such as more than 150 in-orbit fragmentation collisions in space, firings of satellite solid- events. rocket motors, material ageing effects, and leaking thermal-control systems. Solid-rocket Among the more than 8700 objects larger than 10 cm in Earth orbits, motors use aluminium as a catalyst (about 15% only about 6% are operational satellites and the remainder is space by mass) and when burning they emit debris. Europe currently has no operational space surveillance aluminium-oxide particles typically 1 to 10 system, but a powerful radar facility for the detection and tracking of microns in size. In addition, centimetre-sized space debris and the imaging of space objects is available in the form objects are formed by metallic aluminium melts, of the 34 m dish radar at the Research Establishment for Applied called ‘slag’. -
Spacecraft Network Operations Demonstration Using
Nodes Spacecraft Network Operations Demonstration Using Multiple Spacecraft in an Autonomously Configured Space Network Allowing Crosslink Communications and Multipoint Scientific Measurements Nodes is a technology demonstration mission that was launched to the International Space Station on December 6, 2015. The two Nodes satellites subsequently deployed from the Station on May 16, 2016 to demonstrate new network capabilities critical to the operation of swarms of spacecraft. The Nodes satellites accomplished all of their planned mission objectives including three technology ‘firsts’ for small spacecraft: commanding a spacecraft not in direct contact with the ground by crosslinking commands through a space network; crosslinking science data from one Nodes satellite to the second Nodes spacecraft deployed into low Earth orbit satellite before sending it to the ground; and communication, one ultra high frequency autonomous reconfiguration of the space (UHF) radio for crosslink communication, and communications network using the capability an additional UHF beacon radio to transmit of Nodes to automatically select which state-of-health information. satellite is best suited to serve as the ground relay each day. The Nodes science instruments, identical to those on the EDSN satellites, collected The Nodes mission consists of two 1.5- data on the charged particle environment unit (1.5U) CubeSats, each weighing at an altitude of about 250 miles (400 approximately 4.5 pounds (2 kilograms) and kilometers) above Earth. These Energetic measuring about 4 inches x 4 inches x 6.5 Particle Integrating Space Environment inches (10 centimeters x 10 centimeters x Monitor (EPISEM) radiation sensors were 16 centimeters). This mission followed last provided by Montana State University in year’s attempted launch of the eight small Bozeman, Montana, under contract to satellites of the Edison Demonstration of NASA. -
Build a Spacecraft Activity
UAMN Virtual Family Day: Amazing Earth Build a Spacecraft SMAP satellite. Image: NASA. Discover how scientists study Earth from above! Scientists use satellites and spacecraft to study the Earth from outer space. They take pictures of Earth's surface and measure cloud cover, sea levels, glacier movements, and more. Materials Needed: Paper, pencil, craft materials (small recycled boxes, cardboard pieces, paperclips, toothpicks, popsicle sticks, straws, cotton balls, yarn, etc. You can use whatever supplies you have!), fastening materials (glue, tape, rubber bands, string, etc.) Instructions: Step 1: Decide what you want your spacecraft to study. Will it take pictures of clouds? Track forest fires? Measure rainfall? Be creative! Step 2: Design your spacecraft. Draw a picture of what your spacecraft will look like. It will need these parts: Container: To hold everything together. Power Source: To create electricity; solar panels, batteries, etc. Scientific Instruments: This is the why you launched your satellite in the first place! Instruments could include cameras, particle collectors, or magnometers. Communication Device: To relay information back to Earth. Image: NASA SpacePlace. Orientation Finder: A sun or star tracker to show where the spacecraft is pointed. Step 3: Build your spacecraft! Use any craft materials you have available. Let your imagination go wild. Step 4: Your spacecraft will need to survive launching into orbit. Test your spacecraft by gently shaking or spinning it. How well did it hold together? Adjust your design and try again! Model spacecraft examples. Courtesy NASA SpacePlace. Activity adapted from NASA SpacePlace: spaceplace.nasa.gov/build-a-spacecraft/en/ UAMN Virtual Early Explorers: Amazing Earth Studying Earth From Above NASA is best known for exploring outer space, but it also conducts many missions to investigate Earth from above. -
Pointing Analysis and Design Drivers for Low Earth Orbit Satellite Quantum Key Distribution Jeremiah A
Air Force Institute of Technology AFIT Scholar Theses and Dissertations Student Graduate Works 3-24-2016 Pointing Analysis and Design Drivers for Low Earth Orbit Satellite Quantum Key Distribution Jeremiah A. Specht Follow this and additional works at: https://scholar.afit.edu/etd Part of the Information Security Commons, and the Space Vehicles Commons Recommended Citation Specht, Jeremiah A., "Pointing Analysis and Design Drivers for Low Earth Orbit Satellite Quantum Key Distribution" (2016). Theses and Dissertations. 451. https://scholar.afit.edu/etd/451 This Thesis is brought to you for free and open access by the Student Graduate Works at AFIT Scholar. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of AFIT Scholar. For more information, please contact [email protected]. POINTING ANALYSIS AND DESIGN DRIVERS FOR LOW EARTH ORBIT SATELLITE QUANTUM KEY DISTRIBUTION THESIS Jeremiah A. Specht, 1st Lt, USAF AFIT-ENY-MS-16-M-241 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base, Ohio DISTRIBUTION STATEMENT A. APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED. The views expressed in this thesis are those of the author and do not reflect the official policy or position of the United States Air Force, Department of Defense, or the United States Government. This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. AFIT-ENY-MS-16-M-241 POINTING ANALYSIS AND DESIGN DRIVERS FOR LOW EARTH ORBIT SATELLITE QUANTUM KEY DISTRIBUTION THESIS Presented to the Faculty Department of Aeronautics and Astronautics Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and Training Command In Partial Fulfillment of the Requirements for the Degree of Master of Science in Space Systems Jeremiah A. -
Brief Introduction to Orbital Mechanics Page 1
Brief Introduction to Orbital Mechanics Page 1 Brief Introduction to Orbital Mechanics We wish to work out the specifics of the orbital geometry of satellites. We begin by employing Newton's laws of motion to determine the orbital period of a satellite. The first equation of motion is F = ma (1) where m is mass, in kg, and a is acceleration, in m/s2. The Earth produces a gravitational field equal to Gm g(r) = − E r^ (2) r2 24 −11 2 2 where mE = 5:972 × 10 kg is the mass of the Earth and G = 6:674 × 10 N · m =kg is the gravitational constant. The gravitational force acting on the satellite is then equal to Gm mr^ Gm mr F = − E = − E : (3) in r2 r3 This force is inward (towards the Earth), and as such is defined as a centripetal force acting on the satellite. Since the product of mE and G is a constant, we can define µ = mEG = 3:986 × 1014 N · m2=kg which is known as Kepler's constant. Then, µmr F = − : (4) in r3 This force is illustrated in Figure 1(a). An equal and opposite force acts on the satellite called the centrifugal force, also shown. This force keeps the satellite moving in a circular path with linear speed, away from the axis of rotation. Hence we can define a centrifugal acceleration as the change in velocity produced by the satellite moving in a circular path with respect to time, which keeps the satellite moving in a circular path without falling into the centre. -
Space Sector Brochure
SPACE SPACE REVOLUTIONIZING THE WAY TO SPACE SPACECRAFT TECHNOLOGIES PROPULSION Moog provides components and subsystems for cold gas, chemical, and electric Moog is a proven leader in components, subsystems, and systems propulsion and designs, develops, and manufactures complete chemical propulsion for spacecraft of all sizes, from smallsats to GEO spacecraft. systems, including tanks, to accelerate the spacecraft for orbit-insertion, station Moog has been successfully providing spacecraft controls, in- keeping, or attitude control. Moog makes thrusters from <1N to 500N to support the space propulsion, and major subsystems for science, military, propulsion requirements for small to large spacecraft. and commercial operations for more than 60 years. AVIONICS Moog is a proven provider of high performance and reliable space-rated avionics hardware and software for command and data handling, power distribution, payload processing, memory, GPS receivers, motor controllers, and onboard computing. POWER SYSTEMS Moog leverages its proven spacecraft avionics and high-power control systems to supply hardware for telemetry, as well as solar array and battery power management and switching. Applications include bus line power to valves, motors, torque rods, and other end effectors. Moog has developed products for Power Management and Distribution (PMAD) Systems, such as high power DC converters, switching, and power stabilization. MECHANISMS Moog has produced spacecraft motion control products for more than 50 years, dating back to the historic Apollo and Pioneer programs. Today, we offer rotary, linear, and specialized mechanisms for spacecraft motion control needs. Moog is a world-class manufacturer of solar array drives, propulsion positioning gimbals, electric propulsion gimbals, antenna positioner mechanisms, docking and release mechanisms, and specialty payload positioners. -
Cislunar Tether Transport System
FINAL REPORT on NIAC Phase I Contract 07600-011 with NASA Institute for Advanced Concepts, Universities Space Research Association CISLUNAR TETHER TRANSPORT SYSTEM Report submitted by: TETHERS UNLIMITED, INC. 8114 Pebble Ct., Clinton WA 98236-9240 Phone: (206) 306-0400 Fax: -0537 email: [email protected] www.tethers.com Report dated: May 30, 1999 Period of Performance: November 1, 1998 to April 30, 1999 PROJECT SUMMARY PHASE I CONTRACT NUMBER NIAC-07600-011 TITLE OF PROJECT CISLUNAR TETHER TRANSPORT SYSTEM NAME AND ADDRESS OF PERFORMING ORGANIZATION (Firm Name, Mail Address, City/State/Zip Tethers Unlimited, Inc. 8114 Pebble Ct., Clinton WA 98236-9240 [email protected] PRINCIPAL INVESTIGATOR Robert P. Hoyt, Ph.D. ABSTRACT The Phase I effort developed a design for a space systems architecture for repeatedly transporting payloads between low Earth orbit and the surface of the moon without significant use of propellant. This architecture consists of one rotating tether in elliptical, equatorial Earth orbit and a second rotating tether in a circular low lunar orbit. The Earth-orbit tether picks up a payload from a circular low Earth orbit and tosses it into a minimal-energy lunar transfer orbit. When the payload arrives at the Moon, the lunar tether catches it and deposits it on the surface of the Moon. Simultaneously, the lunar tether picks up a lunar payload to be sent down to the Earth orbit tether. By transporting equal masses to and from the Moon, the orbital energy and momentum of the system can be conserved, eliminating the need for transfer propellant. Using currently available high-strength tether materials, this system could be built with a total mass of less than 28 times the mass of the payloads it can transport. -
GEO, MEO, and LEO How Orbital Altitude Impacts Network Performance in Satellite Data Services
GEO, MEO, AND LEO How orbital altitude impacts network performance in satellite data services COMMUNICATION OVER SATELLITE “An entire multi-orbit is now well accepted as a key enabler across the telecommunications industry. Satellite networks can supplement existing infrastructure by providing global reach satellite ecosystem is where terrestrial networks are unavailable or not feasible. opening up above us, But not all satellite networks are created equal. Providers offer different solutions driving new opportunities depending on the orbits available to them, and so understanding how the distance for high-performance from Earth affects performance is crucial for decision making when selecting a satellite service. The following pages give an overview of the three main orbit gigabit connectivity and classes, along with some of the principal trade-offs between them. broadband services.” Stewart Sanders Executive Vice President of Key terms Technology at SES GEO – Geostationary Earth Orbit. NGSO – Non-Geostationary Orbit. NGSO is divided into MEO and LEO. MEO – Medium Earth Orbit. LEO – Low Earth Orbit. HTS – High Throughput Satellites designed for communication. Latency – the delay in data transmission from one communication endpoint to another. Latency-critical applications include video conferencing, mobile data backhaul, and cloud-based business collaboration tools. SD-WAN – Software-Defined Wide Area Networking. Based on policies controlled by the user, SD-WAN optimises network performance by steering application traffic over the most suitable access technology and with the appropriate Quality of Service (QoS). Figure 1: Schematic of orbital altitudes and coverage areas GEOSTATIONARY EARTH ORBIT Altitude 36,000km GEO satellites match the rotation of the Earth as they travel, and so remain above the same point on the ground.