DOCSLIB.ORG

Multiple-Apogee Highly Elliptical Orbits for Continuous Meteorological Imaging of Polar Regions Challenging the Classical 12-H Molniya Orbit Concept

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Multiple-Apogee Highly Elliptical Orbits for Continuous Meteorological Imaging of Polar Regions Challenging the Classical 12-H Molniya Orbit Concept Multiple-Apogee Highly Elliptical Orbits for Continuous Meteorological Imaging of Polar Regions Challenging the Classical 12-h Molniya Orbit Concept BY ALEXANDER P. TRISHCHENKO, LOUIS GARAND, LARISA D. TRICHTCHENKO, AND LIDIA V. NIKITINA DREAM: CONTINUOUS GLOBAL IMAGING. 1974. Since that time, the imaging technology has Satellite observations have transformed our percep- improved substantially. The Advanced Baseline tion of the Earth–atmosphere system since the first Imager (ABI) developed for the third generation of images of Earth from space were acquired in 1960. geostationary satellites, such as the U.S. Geostation- Nevertheless, a satellite meteorologist’s dream to ary Operational Environmental Satellite (GOES-R) observe weather at any point and time over the globe and the Japanese Himawari 8 and 9 (Himawari 8 remains elusive. This capability would represent launched in October 2014) can provide uninter- a breakthrough for short- and long-term weather rupted scans of the full Earth disk every 5 min. forecasting and narrowing uncertainties in the Sectors of 1,000 × 1,000 km can be acquired with a knowledge of Earth’s climate through better sam- temporal resolution of 30 s. These refresh rates can pling of the diurnal cycle. Continuous observation be effectively considered as “continuous imaging,” would also be beneficial for improving the quality of but a significant part of the globe still does not ben- satellite-derived essential climate variables (ECV). efit from similar capabilities. To a large extent, continuous imaging is achieved over the tropics and midlatitudes from geostationary CHALLENGE: POLAR REGIONS. Polar regions (GEO) satellites that rotate around the Earth at the are frequently called “the weather kitchens of the altitude of about 36,000 km in the equatorial plane Earth's climate.” Indeed, they exert great influence with the same angular rate as the planet. The satel- on global weather and show increased sensitivity lite can observe continuously with elevation angle to climate change. Orbital mechanics do not al- higher than 20° above the horizon a large region low GEO-type imaging over the poles. The polar that extends from the equator up to 62° latitude. regions are presently monitored from low Earth Meteorological imaging from GEO orbit started in orbiting (LEO) satellites circling around the Earth at altitudes between 600 km and 900 km with a period of rotation close to 100 min. Due to the na- ture of LEO observations, the imaging refresh rate AFFILIATIONS: TRISHCHENKO—Canada Centre for Remote Sensing, is restricted by the orbital period and the width of Natural Resources Canada, Ottawa, Ontario, Canada; GARAND— Atmospheric Science and Technology, Environment Canada, Quebec, image swath. The frequency of observations is also Canada; TRICHTCHENKO AND NIKITINA—Canadian Space Weather a function of latitude. For example, achieving the Forecast Centre, Natural Resources Canada, Ottawa, Ontario, image refresh rate of 15(10) min at 60° latitude circle Canada would require 23(34) polar LEO meteorological CORRESPONDING AUTHOR: Alexander P. Trishchenko, Canada satellites with orbital and imaging characteristics Centre for Remote Sensing, Natural Resources Canada, 560 similar to the Joint Polar Satellite System (JPSS). Rochester Str., Ottawa, ON K1A 0E4, Canada These numbers are prohibitively large to achieve E-mail: [email protected] the goal of GEO-like imaging at high latitudes from DOI:10.1175/BAMS-D-14-00251.1 LEO systems; therefore an alternative solution is required. PB | JANUARY 2016 AMERICAN METEOROLOGICAL SOCIETY JANUARY 2016 | 19 Unauthenticated | Downloaded 09/29/21 09:14 PM UTC MOLNIYA ORBIT: CAPABILITIES AND DRAW- protons. The Molniya orbit crosses the proton radia- BACKS. Quasigeostationary coverage of polar tion belts at the region of maximum concentration of regions can be achieved from satellites in a highly energetic protons with energies up to several hundred elliptical orbit (HEO). The eccentricity of the HEO MeV. As an alternative, the 16-h three apogee (TAP) orbits is high by definition, and the satellite, in ac- HEO orbit was proposed, providing similar polar cordance with Kepler’s second law, spends most of the coverage as the Molniya HEO system while minimiz- time in the vicinity of apogee (i.e., the farthest point ing the proton ionizing hazards. The TAP orbit has a from the Earth’s surface). If the orbit altitude is high ground track with three apogee points repeatable over enough, and the orbit is oriented in such a way that two days. The constellation of two satellites in TAP the apogee is located over one of the two polar regions, orbit still repeats the ground track in 24 h. then a combination of only two HEO satellites can The Molniya HEO orbit was suggested for meteo- maintain a continuous view of the entire polar zone. rological imaging in 1990, but has never been used When satellite A leaves the optimal viewing zone and operationally for that purpose. A new wave of interest heads toward the perigee (i.e., the closest point to the in HEO satellite systems started a few years ago, when Earth’s surface), satellite B rises over the region to the scale of climate change happening in the Arctic maintain the complete circumpolar region in sight. polar region and the economic opportunities it may Interestingly, there are periods of several hours per open became evident. Recognizing the importance day of coincident (i.e., stereo-like) imaging from the and potential of the HEO system for polar observa- two satellites over most of the circumpolar area. Such tions, the World Meteorological Organization (WMO) a system could provide meteorological imaging and created the International Geostationary Laboratory communication capacity similar to GEO, but focused for Highly Elliptical Orbit (IGEOLAB HEO) Focus on the polar region. Two pairs of HEO satellites (i.e., Group to coordinate international efforts in this field, a total of four satellites) would be required to insure and included the HEO concept in the most recent continuous coverage of both poles. WMO implementation plan for the evolution of the The first HEO satellite system with period of Global Observing System. rotation equal to 12 h and called Molniya was imple- mented for communication purposes in 1965. It is established that a two-satellite Molniya HEO constel- lation can achieve continuous coverage of the polar region 58°–90°N with a viewing zenith angle (VZA) less than 70°. Another HEO system—with a 24-h pe- riod—called Tundra is currently used by the satellite Sirius XM Radio service operating in North America. Both orbits, 12-h Molniya and 24-h Tundra, are launched with an orbit inclination equal to 63.4°. This value is called the critical inclination. It corresponds to zero rate of the apogee drift due to the second zonal harmonic of the Earth gravitational field, and insures a stable position of apogee over the polar zone. If the HEO orbit inclination differs from the critical value, then the apogee gradually drifts toward the equator. Orbital maneuvers are then required to maintain the intended orbit position. The farther orbit inclination is from the critical value, the more resources are re- quired to maintain the orbit. Therefore, it is highly recommended that the orbit inclination of the HEO FIG. 1. Ground track for (a) 12-h Molniya, (b) 16-h system be set at the critical value. TAP, and (c) 14-h and (d) 15-h two-satellite HEO A significant drawback associated with the 12-h constellations. Yellow and magenta colors denote Molniya orbit is the risk linked to hazardous levels ground tracks for each satellite in a two-satellite of ionizing radiation due to passing the Van Allen constellation flying in the same orbital plane and belts. The highest danger originates from high-energy separated by 180° phase angle. 20 | JANUARY 2016 AMERICAN METEOROLOGICAL SOCIETY JANUARY 2016 | 21 Unauthenticated | Downloaded 09/29/21 09:14 PM UTC Until now, most HEO studies designed to provide for the family of HEO orbits suitable for continuous services over polar areas were structured along the observations of the Earth’s polar regions. Analysis 12-h Molniya, 16-h TAP, and 24-h Tundra orbit con- of ionizing radiation revealed the presence of a cepts that benefit from a ground track repeatable over local minimum in the region of orbital periods a 24-h period. A characteristic feature of these orbits between 14 h and 15 h. The total ionizing dose (TID) is the existence of a few (1, 2, or 3) standing apogee modeled via the Space Environment Information Sys- points as shown in Figs. 1a and 1b. tem (SPENVIS: www.spenvis.oma.be) at the reference A question comes to mind: Are the HEO orbital level of 50 krad over 15-yr period can be achieved with configurations previously developed for communica- 3.2 mm of aluminum shielding for the 14-h orbit and tion and surveillance applications also optimal for 3.3 mm for the 15-h orbit. This thickness of aluminum meteorological imaging of the polar regions? shielding is nearly 50% smaller than for the 12-h Mol- niya orbit. The total doses for protons are estimated to NOVEL SOLUTION: MULTIPLE-APOGEE HEO be 2–4 times smaller for the 14-h and 15-h orbits than SYSTEMS. We argue here that an HEO system with for the 12-h orbit. A reduced proton dose for MAP a small number of apogees is suboptimal for meteo- HEO systems is an important additional argument, as rological and climate applications. Indeed, with more proton radiation represents one of the most significant apogees, more evenly distributed imaging conditions risks to the HEO space mission. are obtained. This aspect is evident from Figs. 1c and Another important feature of the MAP configura- 1d, which shows the ground tracks for the 14-h and tions with orbital periods in the 14-h to 15-h range is 15-h HEO systems.
Load more

Recommended publications
  • Analysis of Perturbations and Station-Keeping Requirements in Highly-Inclined Geosynchronous Orbits
    ANALYSIS OF PERTURBATIONS AND STATION-KEEPING REQUIREMENTS IN HIGHLY-INCLINED GEOSYNCHRONOUS ORBITS Elena Fantino(1), Roberto Flores(2), Alessio Di Salvo(3), and Marilena Di Carlo(4) (1)Space Studies Institute of Catalonia (IEEC), Polytechnic University of Catalonia (UPC), E.T.S.E.I.A.T., Colom 11, 08222 Terrassa (Spain), [email protected] (2)International Center for Numerical Methods in Engineering (CIMNE), Polytechnic University of Catalonia (UPC), Building C1, Campus Norte, UPC, Gran Capitan,´ s/n, 08034 Barcelona (Spain) (3)NEXT Ingegneria dei Sistemi S.p.A., Space Innovation System Unit, Via A. Noale 345/b, 00155 Roma (Italy), [email protected] (4)Department of Mechanical and Aerospace Engineering, University of Strathclyde, 75 Montrose Street, Glasgow G1 1XJ (United Kingdom), [email protected] Abstract: There is a demand for communications services at high latitudes that is not well served by conventional geostationary satellites. Alternatives using low-altitude orbits require too large constellations. Other options are the Molniya and Tundra families (critically-inclined, eccentric orbits with the apogee at high latitudes). In this work we have considered derivatives of the Tundra type with different inclinations and eccentricities. By means of a high-precision model of the terrestrial gravity field and the most relevant environmental perturbations, we have studied the evolution of these orbits during a period of two years. The effects of the different perturbations on the constellation ground track (which is more important for coverage than the orbital elements themselves) have been identified. We show that, in order to maintain the ground track unchanged, the most important parameters are the orbital period and the argument of the perigee.
    [Show full text]
  • Download Paper
    Ever Wonder What’s in Molniya? We Do. John T. McGraw J. T. McGraw and Associates, LLC and University of New Mexico Peter C. Zimmer J. T. McGraw and Associates, LLC Mark R. Ackermann J. T. McGraw and Associates, LLC ABSTRACT Molniya orbits are high inclination, high eccentricity orbits which provide the utility of long apogee dwell time over northern continents, with the additional benefit of obviating the largest orbital perturbation introduced by the Earth’s nonspherical (oblate) gravitational potential. We review the few earlier surveys of the Molniya domain and evaluate results from a new, large area unbiased survey of the northern Molniya domain. We detect 120 Molniya objects in a three hour survey of ~ 1300 square degrees of the sky to a limiting magnitude of about 16.5. Future Molniya surveys will discover a significant number of objects, including debris, and monitoring these objects might provide useful data with respect to orbital perturbations including solar radiation and Earth atmosphere drag effects. 1. SPECIALIZED ORBITS Earth Orbital Space (EOS) supports many versions of specialized satellite orbits defined by a combination of satellite mission and orbital dynamics. Surely the most well-known family of specialized orbits is the geostationary orbits proposed by science fiction author Arthur C. Clarke in 1945 [1] that lie sensibly in the plane of Earth’s equator, with orbital period that matches the Earth’s rotation period. Satellites in these orbits, and the closely related geosynchronous orbits, appear from Earth to remain constantly overhead, allowing continuous communication with the majority of the hemisphere below. Constellations of three geostationary satellites equally spaced in orbit (~ 120° separation) can maintain near-global communication and terrestrial surveillance.
    [Show full text]
  • 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.
    [Show full text]
  • Mr. Warren Soh Magellan Aerospace, Canada, [email protected]
    Paper ID: 24743 65th International Astronautical Congress 2014 ASTRODYNAMICS SYMPOSIUM (C1) Guidance, Navigation and Control (1) (5) Author: Mr. Warren Soh Magellan Aerospace, Canada, [email protected] Ms. Jennifer Michels Magellan Aerospace, Canada, [email protected] Mr. Don Asquin Magellan Aerospace, Canada, [email protected] Mr. Adam Vigneron International Space University, Carleton University, Canada, [email protected] Dr. Anton de Ruiter Canada, [email protected] Mr. Ron Buckingham Northeast Space Company, Canada, [email protected] ONBOARD NAVIGATION FOR THE CANADIAN POLAR COMMUNICATION AND WEATHER SATELLITE IN TUNDRA ORBIT Abstract Geosynchronous communications and meteorological satellites have limited northern latitude coverage, specifically above 65 N latitude. This lack of secure, highly reliable, high capacity communication ser- vices and insufficient meteorological data over the Arctic region has prompted Canada to investigate new satellite solutions. Since 2008, the Canadian Space Agency (CSA) has spearheaded the Polar Communi- cation and Weather (PCW) mission, slated to operate in a Highly Elliptical Orbit (HEO). A 24-hour, 90 inclination, Tundra orbit is a strong candidate; able to fill the communication and weather coverage gaps and allow continuous space weather monitoring in the Northern and Southern hemispheres. This orbit however, poses an operational challenge for GPS-based satellite orbit determination since the satellite is continuously above the GPS constellation and will experience frequent signal outages, especially when passing over the poles, aggravated by the constellation's inclination of 55. Magellan Aerospace, Winnipeg in collaboration with Carleton University, has successfully developed an onboard navigation technology for PCW within a CSA-funded Space Technology Development Program.
    [Show full text]
  • A Highly Elliptical Orbit Space System for Hydrometeorological Monitoring of the Arctic Region by V
    A highly elliptical orbit space system for hydrometeorological monitoring of the Arctic region by V. V. Asmus1, V. N. Dyadyuchenko2, Y. I. Nosenko3, G. M. Polishchuk4 and V. A. Selin3 The lack of reliable, frequently high latitudes. It has therefore been • Monitoring of climate change updated information on the Earth’s suggested that demonstration of polar ice caps is a signifi cant problem a hydrometeorological system of • Data collection and relay for weather forecasting, affecting satellites on highly elliptical orbit from land-, sea- and air-based forecast skill for the entire planet. The (HEO), called the “Arctica” system, observing platforms poor numerical weather prediction should be created to provide the (NWP) skill for the Arctic region necessary complex information for the • Exchange and dissemination of and the Earth’s northern territories diffi cult tasks involved in developing processed hydrometeorological is caused primarily by errors in the whole Arctic region. and heliogeophysical data. determining initial conditions, which depend on the quality of initial Signifi cantly, the hydrometeorological Further progress in global and data. Until now, initial data have observations carried out in the regional numerical weather prediction been received from meteorological Arctic within the framework of the depends to a large extent on: geostationary satellites, which are International Polar Year 2007-2008 not very effective in scanning high are not provided with remote-sensing • Quasi-continuous reception latitudes and polar-orbiting
    [Show full text]
  • Molniya" Type Orbits
    EXAMINATION OF THE LIFETIME, EVOLUTION AND RE-ENTRY FEATURES FOR THE "MOLNIYA" TYPE ORBITS Yu.F. Kolyuka, N.M. Ivanov, T.I. Afanasieva, T.A. Gridchina Mission Control Center, 4, Pionerskaya str., Korolev, Moscow Region, 141070, Russia, [email protected] ABSTRACT Space vehicles of the "Molniya" series, launched into the special highly elliptical orbits with a period of ~ 12 hours, are intended for solution of telecommunication problems in stretched territories of the former USSR and nowadays − Russia, and also for providing the connectivity between Russia and other countries. The inclination of standard orbits of such a kind of satellites is near to the critical value i ≈ 63.4 deg and their initial minimal altitude normally has a value Hmin ~ 500 km. As a rule, the “Molniya" satellites of a concrete series form the groups with determined disposition of orbital planes on an ascending node longitude that allows to ensure requirements of the continuous link between any points in northern hemisphere. The first satellite of the "Molniya" series has been inserted into designed orbit in 1964. Up to now it is launched over 160 space vehicles of such a kind. As well as all artificial satellites, space vehicles "Molniya" undergo the action of various perturbing forces influencing a change of their orbital parameters. However in case of space vehicles "Molniya" these changes of parameters have a specific character and in many things they differ from the perturbations which are taking place for the majority of standard orbits of the artificial satellites with rather small eccentricity. In particular, to strong enough variations (first of all, at the expense of the luni-solar attraction) it is subjected the orbit perigee distance rπ that can lead to such reduction Hmin when further flight of the satellite on its orbit becomes impossible, it re-entries and falls to the Earth.
    [Show full text]
  • 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.
    [Show full text]
  • Open Rosen Thesis.Pdf
    THE PENNSYLVANIA STATE UNIVERSITY SCHREYER HONORS COLLEGE DEPARTMENT OF AEROSPACE ENGINEERING END OF LIFE DISPOSAL OF SATELLITES IN HIGHLY ELLIPTICAL ORBITS MITCHELL ROSEN SPRING 2019 A thesis submitted in partial fulfillment of the requirements for a baccalaureate degree in Aerospace Engineering with honors in Aerospace Engineering Reviewed and approved* by the following: Dr. David Spencer Professor of Aerospace Engineering Thesis Supervisor Dr. Mark Maughmer Professor of Aerospace Engineering Honors Adviser * Signatures are on file in the Schreyer Honors College. i ABSTRACT Highly elliptical orbits allow for coverage of large parts of the Earth through a single satellite, simplifying communications in the globe’s northern reaches. These orbits are able to avoid drastic changes to the argument of periapse by using a critical inclination (63.4°) that cancels out the first level of the geopotential forces. However, this allows the next level of geopotential forces to take over, quickly de-orbiting satellites. Thus, a balance between the rate of change of the argument of periapse and the lifetime of the orbit is necessitated. This thesis sets out to find that balance. It is determined that an orbit with an inclination of 62.5° strikes that balance best. While this orbit is optimal off of the critical inclination, it is still near enough that to allow for potential use of inclination changes as a deorbiting method. Satellites are deorbited when the propellant remaining is enough to perform such a maneuver, and nothing more; therefore, the less change in velocity necessary for to deorbit, the better. Following the determination of an ideal highly elliptical orbit, the different methods of inclination change is tested against the usual method for deorbiting a satellite, an apoapse burn to lower the periapse, to find the most propellant- efficient method.
    [Show full text]
  • Mr. Alan B. Jenkin the Aerospace Corporation, United States, [email protected]
    70th International Astronautical Congress 2019 Paper ID: 49271 oral 17th IAA SYMPOSIUM ON SPACE DEBRIS (A6) Mitigation - Tools, Techniques and Challenges (4) Author: Mr. Alan B. Jenkin The Aerospace Corporation, United States, [email protected] Dr. John McVey The Aerospace Corporation, United States, [email protected] Mr. David Emmert The Aerospace Corporation, United States, [email protected] Mr. Marlon Sorge The Aerospace Corporation, United States, [email protected] COMPARISON OF DISPOSAL OPTIONS FOR TUNDRA ORBITS IN TERMS OF DELTA-V COST AND LONG-TERM COLLISION RISK Abstract Tundra orbits are inclined, moderately eccentric orbits with a 24-hour period. The selection of ec- centricity and argument of perigee enables a satellite to dwell over a region bounded by latitude and longitude. Compared to a traditional geosynchronous orbit (GEO), Tundra orbits offer the benefit of regional coverage at non-equatorial latitudes with higher elevation angles. Examples of actual missions that have used Tundra orbits are the Sirius satellite constellation and the Quasi-Zenith Satellite System. Previous studies by the authors considered disposal in an orbit near the Tundra orbit. High altitude, high inclination disposal orbits (above 2000 km altitude and 30 degrees inclination) can in general undergo large excursions in eccentricity due to luni-solar gravity perturbations. Results of the previous studies demonstrated that, for inclinations above 50 degrees, eccentricity can grow to a value that causes perigee to reach the Earth's atmosphere, resulting in vehicle reentry. Collision probability with background ob- jects can be significantly reduced below that for traditional GEO disposal orbits due to the risk-dilution effect of orbital eccentricity.
    [Show full text]
  • Orbital Mechanics
    Danish Space Research Institute Danish Small Satellite Programme DTU Satellite Systems and Design Course Orbital Mechanics Flemming Hansen MScEE, PhD Technology Manager Danish Small Satellite Programme Danish Space Research Institute Phone: 3532 5721 E-mail: [email protected] Slide # 1 FH 2001-09-16 Orbital_Mechanics.ppt Danish Space Research Institute Danish Small Satellite Programme Planetary and Satellite Orbits Johannes Kepler (1571 - 1630) 1st Law • Discovered by the precision mesurements of Tycho Brahe that the Moon and the Periapsis - Apoapsis - planets moves around in elliptical orbits Perihelion Aphelion • Harmonia Mundi 1609, Kepler’s 1st og 2nd law of planetary motion: st • 1 Law: The orbit of a planet ia an ellipse nd with the sun in one focal point. 2 Law • 2nd Law: A line connecting the sun and a planet sweeps equal areas in equal time intervals. 3rd Law • 1619 came Keplers 3rd law: • 3rd Law: The square of the planet’s orbit period is proportional to the mean distance to the sun to the third power. Slide # 2 FH 2001-09-16 Orbital_Mechanics.ppt Danish Space Research Institute Danish Small Satellite Programme Newton’s Laws Isaac Newton (1642 - 1727) • Philosophiae Naturalis Principia Mathematica 1687 • 1st Law: The law of inertia • 2nd Law: Force = mass x acceleration • 3rd Law: Action og reaction • The law of gravity: = GMm F Gravitational force between two bodies F 2 G The universal gravitational constant: G = 6.670 • 10-11 Nm2kg-2 r M Mass af one body, e.g. the Earth or the Sun m Mass af the other body, e.g. the satellite r Separation between the bodies G is difficult to determine precisely enough for precision orbit calculations.
    [Show full text]
  • Nonlinear Filtering for Autonomous Navigation of Spacecraft in Highly Elliptical Orbit
    Nonlinear Filtering for Autonomous Navigation of Spacecraft in Highly Elliptical Orbit by Adam C. Vigneron, B.Sc.(Eng.) A thesis submitted to the Faculty of Graduate and Postdoctoral Affairs in partial fulfillment of the requirements for the degree of Master of Applied Science Ottawa-Carleton Institute for Mechanical and Aerospace Engineering Department of Mechanical and Aerospace Engineering Carleton University Ottawa, Ontario May, 2014 c Copyright Adam C. Vigneron, 2014 The undersigned hereby recommends to the Faculty of Graduate and Postdoctoral Affairs acceptance of the thesis Nonlinear Filtering for Autonomous Navigation of Spacecraft in Highly Elliptical Orbit submitted by Adam C. Vigneron, B.Sc.(Eng.) in partial fulfillment of the requirements for the degree of Master of Applied Science Professor Anton H. J. de Ruiter, Thesis Supervisor Professor Bruce Burlton, Thesis Co-supervisor Professor Alex Ellery, Thesis Co-supervisor Professor Metin Yaras, Chair, Department of Mechanical and Aerospace Engineering Ottawa-Carleton Institute for Mechanical and Aerospace Engineering Department of Mechanical and Aerospace Engineering Carleton University May, 2014 ii Abstract To fill a gap in satellite services for the Canadian Arctic, the Canadian Space Agency has proposed a Polar Communication and Weather (PCW) mission to be flown in a highly elliptical Molniya orbit. In an era of increasingly capable space hardware, au- tonomous satellite navigation has become a standard means by which satellites in low Earth orbit can increase their independence and functionality. This study examined the accuracy to which autonomous navigation might be realized in a Molniya orbit. Using appropriate physical force models and simulated pseudorange signals from the Global Positioning System (GPS), a navigation algorithm based on the Extended Kalman Filter was demonstrated to achieve a three-dimensional root-mean-square accuracy of 58:9 m over a 500 km ¢ 40 000 km Molniya orbit.
    [Show full text]
  • System Technology Analysis of Aeroassisted Orbital Transfer Vehicles: Moderate Lift/Drag (0.75-1.5)
    t_ % DOCUMENT NO. 85SDS2184 NASA CONTRACT NO. NAS8-35096 PHASE I FINAL REPORT VOLUME IB-PART I STUDY RESULTS SYSTEM TECHNOLOGY ANALYSIS OF AEROASSISTED ORBITAL TRANSFER VEHICLES: MODERATE LIFT/DRAG (0.75-1.5) AUGUST 1985 (bASA-CI_-1791q1) 5XS_[_M T];CEI_CLCGI ANALYSIS N87-26CfQb ¢.F AE_OASSIS_D O_BI_IL TRA_S}E_ VEHICLES: _C/}£RATE LI.F_/I;_JG (0.'JS-1.5),VCLrdBE IB, FIBT 1, S_UDY 5Ec[_L_I5 _inal _Fczt (General Unclas £lectric Co.) 228 _ Avail: _II_ HC G3/|6 00855_5 SUBMITTED TO GEORGE C. MARSHALL SPACE FLIGHT CENTER NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MARSHALL SPACE FLIGHT CENTER , ALABAMA 35812 BY RE-ENTRY SYSTEMS OPERATIONS 3198 Chestnut St.. PhiladelDhia. PA 19101 GENERAL @ ELECTRIC FORWARD This final report of the "System Technology Analysis of Aeroassisted Orbital Transfer Vehiclps: Moderate Lift/Drag (0.75-1.5)" was prepared by the General Electric Company, Space Systems Division for the National Aeronautics and Space Administration's George C. Marshall Space Flight Center (MSFC) in accordance with Contract NAS8-35096. The General Electric Company, Space Systems Division was supported by the Grumman Aerospace Corporation as a subcontracto_ during the conduct of this study. This study was conducted under the direction of the NASA Study Manager, Mr. Robert E. Austin, during the period from OctobeL 1982 through June 1985. The first phase of this program focused on a ground based AOTV and was completed in September 1983. The second phase was directed towards a space based AOTV and the cryofueled propulsion subsystem-configuration interactions and was completed in March of 1985. The second phase was jointly sponsored by NASA-MSFC and thp NASA Lewis Research Center (LeRC).
    [Show full text]