Types of Orbit
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
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 -
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 -
Positioning: Drift Orbit and Station Acquisition
Orbits Supplement GEOSTATIONARY ORBIT PERTURBATIONS INFLUENCE OF ASPHERICITY OF THE EARTH: The gravitational potential of the Earth is no longer µ/r, but varies with longitude. A tangential acceleration is created, depending on the longitudinal location of the satellite, with four points of stable equilibrium: two stable equilibrium points (L 75° E, 105° W) two unstable equilibrium points ( 15° W, 162° E) This tangential acceleration causes a drift of the satellite longitude. Longitudinal drift d'/dt in terms of the longitude about a point of stable equilibrium expresses as: (d/dt)2 - k cos 2 = constant Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF EARTH ASPHERICITY VARIATION IN THE LONGITUDINAL ACCELERATION OF A GEOSTATIONARY SATELLITE: Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF SUN & MOON ATTRACTION Gravitational attraction by the sun and moon causes the satellite orbital inclination to change with time. The evolution of the inclination vector is mainly a combination of variations: period 13.66 days with 0.0035° amplitude period 182.65 days with 0.023° amplitude long term drift The long term drift is given by: -4 dix/dt = H = (-3.6 sin M) 10 ° /day -4 diy/dt = K = (23.4 +.2.7 cos M) 10 °/day where M is the moon ascending node longitude: M = 12.111 -0.052954 T (T: days from 1/1/1950) 2 2 2 2 cos d = H / (H + K ); i/t = (H + K ) Depending on time within the 18 year period of M d varies from 81.1° to 98.9° i/t varies from 0.75°/year to 0.95°/year Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF SUN RADIATION PRESSURE Due to sun radiation pressure, eccentricity arises: EFFECT OF NON-ZERO ECCENTRICITY L = difference between longitude of geostationary satellite and geosynchronous satellite (24 hour period orbit with e0) With non-zero eccentricity the satellite track undergoes a periodic motion about the subsatellite point at perigee. -
GPS Applications in Space
Space Situational Awareness 2015: GPS Applications in Space James J. Miller, Deputy Director Policy & Strategic Communications Division May 13, 2015 GPS Extends the Reach of NASA Networks to Enable New Space Ops, Science, and Exploration Apps GPS Relative Navigation is used for Rendezvous to ISS GPS PNT Services Enable: • Attitude Determination: Use of GPS enables some missions to meet their attitude determination requirements, such as ISS • Real-time On-Board Navigation: Enables new methods of spaceflight ops such as rendezvous & docking, station- keeping, precision formation flying, and GEO satellite servicing • Earth Sciences: GPS used as a remote sensing tool supports atmospheric and ionospheric sciences, geodesy, and geodynamics -- from monitoring sea levels and ice melt to measuring the gravity field ESA ATV 1st mission JAXA’s HTV 1st mission Commercial Cargo Resupply to ISS in 2008 to ISS in 2009 (Space-X & Cygnus), 2012+ 2 Growing GPS Uses in Space: Space Operations & Science • NASA strategic navigation requirements for science and 20-Year Worldwide Space Mission space ops continue to grow, especially as higher Projections by Orbit Type* precisions are needed for more complex operations in all space domains 1% 5% Low Earth Orbit • Nearly 60%* of projected worldwide space missions 27% Medium Earth Orbit over the next 20 years will operate in LEO 59% GeoSynchronous Orbit – That is, inside the Terrestrial Service Volume (TSV) 8% Highly Elliptical Orbit Cislunar / Interplanetary • An additional 35%* of these space missions that will operate at higher altitudes will remain at or below GEO – That is, inside the GPS/GNSS Space Service Volume (SSV) Highly Elliptical Orbits**: • In summary, approximately 95% of projected Example: NASA MMS 4- worldwide space missions over the next 20 years will satellite constellation. -
Satellite Orbits
Course Notes for Ocean Colour Remote Sensing Course Erdemli, Turkey September 11 - 22, 2000 Module 1: Satellite Orbits prepared by Assoc Professor Mervyn J Lynch Remote Sensing and Satellite Research Group School of Applied Science Curtin University of Technology PO Box U1987 Perth Western Australia 6845 AUSTRALIA tel +618-9266-7540 fax +618-9266-2377 email <[email protected]> Module 1: Satellite Orbits 1.0 Artificial Earth Orbiting Satellites The early research on orbital mechanics arose through the efforts of people such as Tyco Brahe, Copernicus, Kepler and Galileo who were clearly concerned with some of the fundamental questions about the motions of celestial objects. Their efforts led to the establishment by Keppler of the three laws of planetary motion and these, in turn, prepared the foundation for the work of Isaac Newton who formulated the Universal Law of Gravitation in 1666: namely, that F = GmM/r2 , (1) Where F = attractive force (N), r = distance separating the two masses (m), M = a mass (kg), m = a second mass (kg), G = gravitational constant. It was in the very next year, namely 1667, that Newton raised the possibility of artificial Earth orbiting satellites. A further 300 years lapsed until 1957 when the USSR achieved the first launch into earth orbit of an artificial satellite - Sputnik - occurred. Returning to Newton's equation (1), it would predict correctly (relativity aside) the motion of an artificial Earth satellite if the Earth was a perfect sphere of uniform density, there was no atmosphere or ocean or other external perturbing forces. However, in practice the situation is more complicated and prediction is a less precise science because not all the effects of relevance are accurately known or predictable. -
PNT in High Earth Orbit and Beyond
International Committee on GNSS-13 Focuses on PNT in High Earth Orbit and Beyond Since last reported in the November/December 2016 issue of Inside GNSS, signicant progress has been made to extend the use of Global Navigation Satellite Systems (GNSS) for Positioning, Navigation, and Timing (PNT) in High Earth Orbit (HEO). This update describes the results of international eorts that are enabling mission planners to condently Artist’s rendering employ GNSS signals in HEO and how researchers are of Orion docked to the lunar-orbiting extending the use of GNSS out to lunar distances. Gateway. Image courtesy of NASA tarting with nascent GPS space to existing ones, multi-GNSS signal Moving from Dream to Reality flight experiments in Low- availability in HEO is set to improve Within the National Aeronautics and SEarth Orbit (LEO) in the 1980s significantly. Users could soon Space Administration (NASA), the and 1990s, space-borne GPS is now employ four operational global con- Space Communications and Naviga- commonplace. Researchers continue stellations and two regional space- tion (SCaN) Program Office leads expanding GPS and GNSS use into— based navigation and augmenta- eorts in PNT development and policy. and beyond—the Space Service Vol- tion systems, respectively: the U.S. Numerous missions have been own in ume (SSV), which is the volume of GPS, Russia’s GLONASS, Europe’s the SSV, dating back to the rst ight space surrounding the Earth between Galileo, China’s BeiDou (BDS), experiments in 1997. NASA, through 3,000 kilometers and Geosynchronous Japan’s Quasi-Zenith Satellite Sys- SCaN and its predecessors, has sup- (GEO) altitudes. -
Sun-Synchronous Satellites
Topic: Sun-synchronous Satellites Course: Remote Sensing and GIS (CC-11) M.A. Geography (Sem.-3) By Dr. Md. Nazim Professor, Department of Geography Patna College, Patna University Lecture-3 Concept: Orbits and their Types: Any object that moves around the Earth has an orbit. An orbit is the path that a satellite follows as it revolves round the Earth. The plane in which a satellite always moves is called the orbital plane and the time taken for completing one orbit is called orbital period. Orbit is defined by the following three factors: 1. Shape of the orbit, which can be either circular or elliptical depending upon the eccentricity that gives the shape of the orbit, 2. Altitude of the orbit which remains constant for a circular orbit but changes continuously for an elliptical orbit, and 3. Angle that an orbital plane makes with the equator. Depending upon the angle between the orbital plane and equator, orbits can be categorised into three types - equatorial, inclined and polar orbits. Different orbits serve different purposes. Each has its own advantages and disadvantages. There are several types of orbits: 1. Polar 2. Sunsynchronous and 3. Geosynchronous Field of View (FOV) is the total view angle of the camera, which defines the swath. When a satellite revolves around the Earth, the sensor observes a certain portion of the Earth’s surface. Swath or swath width is the area (strip of land of Earth surface) which a sensor observes during its orbital motion. Swaths vary from one sensor to another but are generally higher for space borne sensors (ranging between tens and hundreds of kilometers wide) in comparison to airborne sensors. -
Navigation Data— Definitions and Conventions
Report Concerning Space Data System Standards NAVIGATION DATA— DEFINITIONS AND CONVENTIONS INFORMATIONAL REPORT CCSDS 500.0-G-3.21 GREEN BOOK April 2016 CCSDS REPORT CONCERNING NAVIGATION DATA—DEFINITIONS AND CONVENTIONS AUTHORITY Issue: Informational Report, Issue 3 Date: May 2010 Location: Washington, DC, USA This document has been approved for publication by the Management Council of the Consultative Committee for Space Data Systems (CCSDS) and reflects the consensus of technical panel experts from CCSDS Member Agencies. The procedure for review and authorization of CCSDS Reports is detailed in the Procedures Manual for the Consultative Committee for Space Data Systems. This document is published and maintained by: CCSDS Secretariat Space Communications and Navigation Office, 7L70 Space Operations Mission Directorate NASA Headquarters Washington, DC 20546-0001, USA CCSDS 500.0-G-3 Page i May 2010 CCSDS REPORT CONCERNING NAVIGATION DATA—DEFINITIONS AND CONVENTIONS FOREWORD This Report contains technical material to supplement the CCSDS Recommended Standards for the standardization of spacecraft navigation data generated by CCSDS Member Agencies. The topics covered herein include radiometric data content, spacecraft ephemeris, planetary ephemeris, tracking station locations, coordinate systems, and attitude data. This Report deals explicitly with the technical definitions and conventions associated with inter-Agency cross-support situations involving the transfer of ephemeris, tracking, and attitude data. This version of the Green Book contains expanded material regarding spacecraft attitude data and radiometric tracking data. Through the process of normal evolution, it is expected that expansion, deletion, or modification of this document may occur. This Report is therefore subject to CCSDS document management and change control procedures, which are defined in the Procedures Manual for the Consultative Committee for Space Data Systems. -
SATELLITES ORBIT ELEMENTS : EPHEMERIS, Keplerian ELEMENTS, STATE VECTORS
www.myreaders.info www.myreaders.info Return to Website SATELLITES ORBIT ELEMENTS : EPHEMERIS, Keplerian ELEMENTS, STATE VECTORS RC Chakraborty (Retd), Former Director, DRDO, Delhi & Visiting Professor, JUET, Guna, www.myreaders.info, [email protected], www.myreaders.info/html/orbital_mechanics.html, Revised Dec. 16, 2015 (This is Sec. 5, pp 164 - 192, of Orbital Mechanics - Model & Simulation Software (OM-MSS), Sec 1 to 10, pp 1 - 402.) OM-MSS Page 164 OM-MSS Section - 5 -------------------------------------------------------------------------------------------------------43 www.myreaders.info SATELLITES ORBIT ELEMENTS : EPHEMERIS, Keplerian ELEMENTS, STATE VECTORS Satellite Ephemeris is Expressed either by 'Keplerian elements' or by 'State Vectors', that uniquely identify a specific orbit. A satellite is an object that moves around a larger object. Thousands of Satellites launched into orbit around Earth. First, look into the Preliminaries about 'Satellite Orbit', before moving to Satellite Ephemeris data and conversion utilities of the OM-MSS software. (a) Satellite : An artificial object, intentionally placed into orbit. Thousands of Satellites have been launched into orbit around Earth. A few Satellites called Space Probes have been placed into orbit around Moon, Mercury, Venus, Mars, Jupiter, Saturn, etc. The Motion of a Satellite is a direct consequence of the Gravity of a body (earth), around which the satellite travels without any propulsion. The Moon is the Earth's only natural Satellite, moves around Earth in the same kind of orbit. (b) Earth Gravity and Satellite Motion : As satellite move around Earth, it is pulled in by the gravitational force (centripetal) of the Earth. Contrary to this pull, the rotating motion of satellite around Earth has an associated force (centrifugal) which pushes it away from the Earth. -
Space Debris Proceedings
THE UPDATED IAA POSITION PAPER ON ORBITAL DEBRIS W Flury 1), J M Contant 2) 1) ESA/ESOC, Robert-Bosch-Str. 5, 64293 Darmstadt, German, E-mail: [email protected] 2) EADS, Launch Vehicle, SD-DC, 78133 Les Mureaux Cédex, France, E-mail: [email protected] orbit, altitude 35786 km; HEO = high Earth orbit ABSTRACT (apogee above 2000 km). Being concerned about the space debris problem which After over 40 years of international space operations, poses a threat to the future of spaceflight, the more than 26,000 objects have been officially International Academy of Astronautics has issued in cataloged, with approximately one-third of them still in 1993 the Position Paper on Orbital Debris. The orbit about the Earth (Fig. 2). "Cataloged" objects are objectives were to evaluate the need and urgency for objects larger than 10-20 cm in diameter for LEO and 1 action and to indicate ways to reduce the hazard. Since m in diameter in higher orbits, which are sensed and then the space debris problem has gained more maintained in a database by the United States Space attention. Also, several debris preventative measures Command's Space Surveillance Network (SSN). have been introduced on a voluntary basis by designers Statistical measurements have determined that a much and operators of space systems. The updated IAA larger number of objects (> 100,000) 1cm in size or Position Paper on Orbital Debris takes into account larger are in orbit as well. These statistical the evolving space debris environment, new results of measurements are obtained by operating a few special space debris research and international policy radar facilities in the beam-park mode, where the radar developments. -
The UCS Satellite Database
UCS Satellite Database User’s Manual 1-1-17 The UCS Satellite Database The UCS Satellite Database is a listing of active satellites currently in orbit around the Earth. It is available as both a downloadable Excel file and in a tab-delimited text format, and in a version (tab-delimited text) in which the "Name" column contains only the official name of the satellite in the case of government and military satellites, and the most commonly used name in the case of commercial and civil satellites. The database is updated roughly quarterly. Our intent in producing the Database is to create a research tool by collecting open-source information on active satellites and presenting it in a format that can be easily manipulated for research and analysis. The Database includes basic information about the satellites and their orbits, but does not contain the detailed information necessary to locate individual satellites. The UCS Satellite Database can be accessed at www.ucsusa.org/satellite_database. Using the Database The Database is free and its use is unrestricted. We request that its use be acknowledged and referenced in written materials. References should include the version of the Database that was used, which is indicated by the name of the Excel file, and a link to or URL for the webpage www.ucsusa.org/satellite_database. We welcome corrections, additions, and suggestions. These can be emailed to the Database manager at [email protected] If you would like to be notified when updated versions of the Database are completed, please send an email request to this address. -
Evolution of a Terrestrial Multiple Moon System
THE ASTRONOMICAL JOURNAL, 117:603È620, 1999 January ( 1999. The American Astronomical Society. All rights reserved. Printed in U.S.A. EVOLUTION OF A TERRESTRIAL MULTIPLE-MOON SYSTEM ROBIN M. CANUP AND HAROLD F. LEVISON Southwest Research Institute, 1050 Walnut Street, Suite 426, Boulder, CO 80302 AND GLEN R. STEWART Laboratory for Atmospheric and Space Physics, University of Colorado, Campus Box 392, Boulder, CO 80309-0392 Received 1998 March 30; accepted 1998 September 29 ABSTRACT The currently favored theory of lunar origin is the giant-impact hypothesis. Recent work that has modeled accretional growth in impact-generated disks has found that systems with one or two large moons and external debris are common outcomes. In this paper we investigate the evolution of terres- trial multiple-moon systems as they evolve due to mutual interactions (including mean motion resonances) and tidal interaction with Earth, using both analytical techniques and numerical integra- tions. We Ðnd that multiple-moon conÐgurations that form from impact-generated disks are typically unstable: these systems will likely evolve into a single-moon state as the moons mutually collide or as the inner moonlet crashes into Earth. Key words: Moon È planets and satellites: general È solar system: formation INTRODUCTION 1. 1000 orbits). This result was relatively independent of initial The ““ giant-impact ÏÏ scenario proposes that the impact of disk conditions and collisional parameterizations. Pertur- a Mars-sized body with early Earth ejects enough material bations by the largest moonlet(s) were very e†ective at clear- into EarthÏs orbit to form the Moon (Hartmann & Davis ing out inner disk materialÈin all of the ICS97 simulations, 1975; Cameron & Ward 1976).