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Orbit Options for an Orion-Class Spacecraft Mission to a Near-Earth Object
Orbit Options for an Orion-Class Spacecraft Mission to a Near-Earth Object by Nathan C. Shupe B.A., Swarthmore College, 2005 A thesis submitted to the Faculty of the Graduate School of the University of Colorado in partial fulfillment of the requirements for the degree of Master of Science Department of Aerospace Engineering Sciences 2010 This thesis entitled: Orbit Options for an Orion-Class Spacecraft Mission to a Near-Earth Object written by Nathan C. Shupe has been approved for the Department of Aerospace Engineering Sciences Daniel Scheeres Prof. George Born Assoc. Prof. Hanspeter Schaub Date The final copy of this thesis has been examined by the signatories, and we find that both the content and the form meet acceptable presentation standards of scholarly work in the above mentioned discipline. iii Shupe, Nathan C. (M.S., Aerospace Engineering Sciences) Orbit Options for an Orion-Class Spacecraft Mission to a Near-Earth Object Thesis directed by Prof. Daniel Scheeres Based on the recommendations of the Augustine Commission, President Obama has pro- posed a vision for U.S. human spaceflight in the post-Shuttle era which includes a manned mission to a Near-Earth Object (NEO). A 2006-2007 study commissioned by the Constellation Program Advanced Projects Office investigated the feasibility of sending a crewed Orion spacecraft to a NEO using different combinations of elements from the latest launch system architecture at that time. The study found a number of suitable mission targets in the database of known NEOs, and pre- dicted that the number of candidate NEOs will continue to increase as more advanced observatories come online and execute more detailed surveys of the NEO population. -
Mission Design for the Lunar Reconnaissance Orbiter
AAS 07-057 Mission Design for the Lunar Reconnaissance Orbiter Mark Beckman Goddard Space Flight Center, Code 595 29th ANNUAL AAS GUIDANCE AND CONTROL CONFERENCE February 4-8, 2006 Sponsored by Breckenridge, Colorado Rocky Mountain Section AAS Publications Office, P.O. Box 28130 - San Diego, California 92198 AAS-07-057 MISSION DESIGN FOR THE LUNAR RECONNAISSANCE ORBITER † Mark Beckman The Lunar Reconnaissance Orbiter (LRO) will be the first mission under NASA’s Vision for Space Exploration. LRO will fly in a low 50 km mean altitude lunar polar orbit. LRO will utilize a direct minimum energy lunar transfer and have a launch window of three days every two weeks. The launch window is defined by lunar orbit beta angle at times of extreme lighting conditions. This paper will define the LRO launch window and the science and engineering constraints that drive it. After lunar orbit insertion, LRO will be placed into a commissioning orbit for up to 60 days. This commissioning orbit will be a low altitude quasi-frozen orbit that minimizes stationkeeping costs during commissioning phase. LRO will use a repeating stationkeeping cycle with a pair of maneuvers every lunar sidereal period. The stationkeeping algorithm will bound LRO altitude, maintain ground station contact during maneuvers, and equally distribute periselene between northern and southern hemispheres. Orbit determination for LRO will be at the 50 m level with updated lunar gravity models. This paper will address the quasi-frozen orbit design, stationkeeping algorithms and low lunar orbit determination. INTRODUCTION The Lunar Reconnaissance Orbiter (LRO) is the first of the Lunar Precursor Robotic Program’s (LPRP) missions to the moon. -
B-180466 Polar Orbiting Weather Satellite Programs
U-180466 l’ht! Honorable Frank E. Moss Chai rmnn, Committee on Aeronautical .r- Cf ‘ind Space Sciences ;>, r-,rr*Id- l~llll~llllllllllllllllllluu~llllllllllllllll United States Senate LM095911 f?- Dear Ilr. Chairman: Your January 1.6, 19 74, letter asked us to obtain cost and other data ~ on both the Department of the Air Force and the joint Natioual Aeronauticsn and Space Administration (NASA)/National Oceanic and Atmospheric Adminis- *76 tration (NOAA) polar orbiting weather satellite programs. L .-__,__ cs&~yl”.^-b -.,I-*Ii*--... --:- -*-“a .-,. We interviewed officials in NASA, NOM, the Department of the Air Force and the Office of Management and Budget (OHU). At these meetings they told us of the existence of two classified studies which provided some comparative analyses of the technical cfrar; cteristics and costs of the NASA and Air Force operational weather satellite systems and the follow-on sys tems in development . We then met with your staff on February 13, 1974, and orally presented the information, At that meeting your staff as ed us for 11 written re- port, We have not independently verified the d :ta; however, we have dis- cussed the matters in this report with the agent y officials. We plan to discuss briefly the history of I he NASA/NOM and Air Force satellite sys terns, compare tl~e characteristics Ilf both systems, provide cost comparisons of the operational- and develop~oental satellite --.-.systems, and furnish information on plans to obtain some mcasurc of commonality of bcltll sys terns. --_.III STORY _-- OF NASA/NOM --_-PKOCRhM The purpose of the joint NASA/NOAA weather satellite system is to provide systematic, +;Lobal cloud cover observations and other meteorologi- cal observations to incrt*&x: man’s ability to -forecast wc;lthcrI m--...YII-._conditions. -
History of NOAA's Polar Observational Environmental Satellites the First
History of NOAA’s Polar Observational Environmental Satellites The first weather satellite in a series of spacecraft originally known as the Television Infrared Observation Satellites (TIROS) was launched on April 1, 1960. By the mid 1970’s NOAA and NASA agreed to produce the series operationally based on the TIROS-N generation of satellites. TIROS-N, a research and development spacecraft serving as a prototype for the operational follow-on series, NOAA-A through NOAA-N Prime was on launched October 13, 1978. Beginning with NOAA-E, launched in 1983, the basic satellite was “stretched” to permit accommodation of additional research instruments. This became known as the Advanced TIROS-N configuration. Some of the additional instruments flown include: Search and Rescue; Earth Radiation Budget Experiment, and the Solar Backscatter Ultraviolet spectrometer. Three of those instruments, Search and Rescue Repeater, Search and Rescue Processor and Solar Backscatter Ultraviolet Radiometer, became part of the operational program. The primary sounding instrumentation has remained essentially unchanged until the addition of Advanced Microwave Sounding Units-A and -B on NOAA-K (15). The Microwave Humidity Sounder replaces the AMSU-B on NOAA-N Prime performing essentially the same science. The satellite design life throughout the series has been two years. The lifetime is a cost/risk tradeoff since more years normally result in a more expensive satellite. To mitigate that risk, the NOAA-N Prime satellite uses the most reliable NASA-approved flight parts, Class S, and considerable redundancy in critical subsystem components. The instruments are not redundant, but they have a three-year design life in order to enhance their expected operational reliability. -
Five Special Types of Orbits Around Mars
JOURNAL OF GUIDANCE,CONTROL, AND DYNAMICS Vol. 33, No. 4, July–August 2010 Engineering Notes Five Special Types of Orbits sensing satellites. Lagrangian planetary equations, which give the mean precession rate of the line of node, provide the theoretical Around Mars foundation of sun-synchronous orbits. Boain described basic mechanical characteristics of Earth’s sun-synchronous orbits and ∗ † ‡ provided several design algorithms to satisfy practical mission Xiaodong Liu, Hexi Baoyin, and Xingrui Ma requirements [4]. Several Martian satellites have been placed into Tsinghua University, sun-synchronous orbits, such as MGS [1] and MRO [2]. 100084 Beijing, People’s Republic of China Orbits at the critical inclination can keep eccentricity and argument of perigee invariable on average. For example, the Molniya DOI: 10.2514/1.48706 and Tundra orbits applied such conditions to stop the rotation of argument of perigee. Orlov introduced the concept of the Earth Nomenclature critical inclination [5], and Brouwer eliminated short-period terms based on canonical transformations [6]. Later, Coffey et al. analyzed a = semimajor axis, km the averaged Hamilton system reduced by the Delaunay normal- e = orbital eccentricity ization and provided geometrical interpretation of the critical i = orbital inclination, deg. inclination for Earth’s artificial satellites [7]. Some research has J2 = second-order zonal harmonic regarded orbits at the critical inclination as types of frozen orbits J3 = third-order zonal harmonic [8,9]. J4 = fourth-order zonal harmonic Frozen orbits have always been an important focus of orbit design, J22 = second-degree and -order tesseral harmonic because their average eccentricity and argument of perigee remain M = mean anomaly, deg. -
Space Almanac 2007
2007 Space Almanac The US military space operation in facts and figures. Compiled by Tamar A. Mehuron, Associate Editor, and the staff of Air Force Magazine 74 AIR FORCE Magazine / August 2007 Space 0.05g 60,000 miles Geosynchronous Earth Orbit 22,300 miles Hard vacuum 1,000 miles Medium Earth Orbit begins 300 miles 0.95g 100 miles Low Earth Orbit begins 60 miles Astronaut wings awarded 50 miles Limit for ramjet engines 28 miles Limit for turbojet engines 20 miles Stratosphere begins 10 miles Illustration not to scale Artist’s conception by Erik Simonsen AIR FORCE Magazine / August 2007 75 US Military Missions in Space Space Support Space Force Enhancement Space Control Space Force Application Launch of satellites and other Provide satellite communica- Ensure freedom of action in space Provide capabilities for the ap- high-value payloads into space tions, navigation, weather infor- for the US and its allies and, plication of combat operations and operation of those satellites mation, missile warning, com- when directed, deny an adversary in, through, and from space to through a worldwide network of mand and control, and intel- freedom of action in space. influence the course and outcome ground stations. ligence to the warfighter. of conflict. US Space Funding Millions of constant Fiscal 2007 dollars 60,000 50,000 40,000 30,000 20,000 10,000 0 Fiscal Year 59 62 65 68 71 74 77 80 83 86 89 92 95 98 01 04 Fiscal Year NASA DOD Other Total Fiscal Year NASA DOD Other Total 1959 1,841 3,457 240 5,538 1983 13,051 18,601 675 32,327 1960 3,205 3,892 -
Aas 12-269 Frozen Orbits for Scientific Missions Using
AAS 12-269 FROZEN ORBITS FOR SCIENTIFIC MISSIONS USING ROTATING TETHERS Hodei Urrutxua,∗ Jes ´usPelaez´ y and Martin Laraz We derive a semi-analytic formulation that permits to study the long-term dynam- ics of fast-rotating inert tethers around planetary satellites. Since space tethers are extensive bodies they generate non-keplerian gravitational forces which depend solely on their mass geometry and attitude, that can be exploited for controlling science orbits. We conclude that rotating tethers modify the geometry of frozen orbits, allowing for lower eccentricity frozen orbits for a wide range of orbital in- clination, where the length of the tether becomes a new parameter that the mission analyst may use to shape frozen orbits to tighter operational constraints. INTRODUCTION Science orbits for missions to planetary satellites have, in general, low altitudes and near-polar inclinations so that the entire surface can be mapped, and the science requirements of the mission can be accomplished.1,2 However, designing such an orbit can be difficult because the dynamical environment of many planetary satellites is highly perturbed due to their proximity to the central planet.3 One such example is the Moon, on which we focus on the current study. High-inclination orbits around the Moon are known to be unstable.4,5,6 However, the onset of instability can be delayed by a proper orbit design, hence maximizing the orbital lifetime.7 In this regard, the so called frozen orbits offer an interesting starting point for the design of science orbits,1,8,9 since all their orbital elements, with the only exception of the mean anomaly and the longitude of the ascending node, remain constant. -
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. -
10. Satellite Weather and Climate Monitoring
II. INTENSITY: ACTIVITIES AND OUTPUTS IN THE SPACE ECONOMY 10. Satellite weather and climate monitoring Meteorology was the first scientific discipline to use space Figure 1.2). The United States, the European Space Agency capabilities in the 1960s, and today satellites provide obser- and France have established the most joint operations for vations of the state of the atmosphere and ocean surface environmental satellite missions (e.g. NASA is co-operating for the preparation of weather analyses, forecasts, adviso- with Japan’s Aerospace Exploration Agency on the Tropical ries and warnings, for climate monitoring and environ- Rainfall Measuring Mission (TRMM); ESA and NASA cooper- mental activities. Three quarters of the data used in ate on the Solar and Heliospheric Observatory (SOHO), numerical weather prediction models depend on satellite while the French CNES is co-operating with India on the measurements (e.g. in France, satellites provide 93% of data Megha-Tropiques mission to study the water cycle). Para- used in Météo-France’s Arpège model). Three main types of doxically, although there have never been so many weather satellites provide data: two families of weather satellites and environmental satellites in orbit, funding issues in and selected environmental satellites. several OECD countries threaten the sustainability of the Weather satellites are operated by agencies in China, provision of essential long-term data series on climate. France, India, Japan, Korea, the Russian Federation, the United States and Eumetsat for Europe, with international co-ordination by the World Meteorological Organisation Methodological notes (WMO). Some 18 geostationary weather satellites are posi- Based on data from the World Meteorological Orga- tioned above the earth’s equator, forming a ring located at nisation’s database Observing Systems Capability Analy- around 36 000 km (Table 10.1). -
Low Rfi Observations from a Low-Altitude Frozen Lunar Orbit
https://ntrs.nasa.gov/search.jsp?R=20170010155 2019-08-31T01:49:00+00:00Z (Preprint) AAS 17-333 DARE MISSION DESIGN: LOW RFI OBSERVATIONS FROM A LOW-ALTITUDE FROZEN LUNAR ORBIT Laura Plice* and Ken Galal † The Dark Ages Radio Experiment (DARE) seeks to study the cosmic Dark Ages approximately 80 to 420 million years after the Big Bang. Observations require truly quiet radio conditions, shielded from Sun and Earth electromagnetic (EM) emissions, on the far side of the Moon. DARE’s science orbit is a frozen orbit with respect to lunar gravitational perturbations. The altitude and orientation of the orbit remain nearly fixed indefinitely without maintenance. DARE’s obser- vation targets avoid the galactic center and enable investigation of the universe’s first stars and galaxies. INTRODUCTION The Dark Ages Radio Experiment (DARE), currently proposed for NASA’s 2016 Astrophys- ics Medium Explorer (MIDEX) announcement of opportunity, seeks to study the universe in the cosmic Dark Ages approximately 80 to 420 million years after the Big Bang.1 DARE’s observa- tions require truly quiet radio conditions, shielded from Sun and Earth EM emissions, a zone which is only available on the far side of the Moon. To maximize time in the best science condi- tions, DARE requires a low, equatorial lunar orbit. For DARE, diffraction effects define quiet cones in the anti-Earth and anti-Sun sides of the Moon. In the science phase, the DARE satellite passes through the Earth-quiet cone on every orbit (designated Secondary Science) and simultaneously through the Sun shadow for 0 to 100% of every pass (Prime Science observations). -
Joint Polar Satellite System (JPSS) Common Ground System (CGS)
Joint Polar Satellite System (JPSS) Common Ground System (CGS) A flexible, cost-effective global common ground system designed to support current and future weather and environmental sensing satellite missions. Key Features and Benefits The JPSS Program Overview The JPSS program will also The polar orbiters which are able Joint Polar Satellite System (JPSS) integrate future civilian and to monitor the entire planet and g Operational -- supported is designed to monitor global military (Defense Weather Satellite provide data for long-range successful NPP launch environmental conditions in System – DWSS) polar-orbiting weather and climate forecasts, will g Flexible architecture designed addition to collecting and environmental satellite space and carry a complement of advanced to quickly adapt to evolving disseminating data related to the ground segments with a single imaging and sounding sensors mission needs weather, atmosphere, oceans, land ground system. that will acquire data at a much and near-space environment. The higher fidelity and frequency than g Unique integration of new and JPSS Top Level Architecture new system represents a major heritage systems available today. legacy technologies JPSS is an “end-to-end” system upgrade to the existing Polar- that includes sensors; spacecraft; The JPSS CGS Distributed g Available to support diverse orbiting Operational command, control and Receptor Network (DRN) civil, military and scientific Environmental Satellites (POES), communications; data routing; architecture will provide frequent environmental needs which have successfully served the and ground based processing. JPSS downlinks to maximize contact operational weather forecasting g Fully integrated global ground and DWSS spacecraft will carry duration at low cost. JPSS CGS community for nearly 50 years. -
The Future of Npoess: Results of the Nunn–Mccurdy Review of Noaa’S Weather Satellite Program
THE FUTURE OF NPOESS: RESULTS OF THE NUNN–MCCURDY REVIEW OF NOAA’S WEATHER SATELLITE PROGRAM HEARING BEFORE THE COMMITTEE ON SCIENCE HOUSE OF REPRESENTATIVES ONE HUNDRED NINTH CONGRESS SECOND SESSION JUNE 8, 2006 Serial No. 109–53 Printed for the use of the Committee on Science ( Available via the World Wide Web: http://www.house.gov/science U.S. GOVERNMENT PRINTING OFFICE 27–970PS WASHINGTON : 2007 For sale by the Superintendent of Documents, U.S. Government Printing Office Internet: bookstore.gpo.gov Phone: toll free (866) 512–1800; DC area (202) 512–1800 Fax: (202) 512–2250 Mail: Stop SSOP, Washington, DC 20402–0001 VerDate 11-MAY-2000 23:24 Feb 15, 2007 Jkt 027970 PO 00000 Frm 00001 Fmt 5011 Sfmt 5011 C:\WORKD\FULL06\060806\27970 HJUD1 PsN: HJUD1 COMMITTEE ON SCIENCE HON. SHERWOOD L. BOEHLERT, New York, Chairman RALPH M. HALL, Texas BART GORDON, Tennessee LAMAR S. SMITH, Texas JERRY F. COSTELLO, Illinois CURT WELDON, Pennsylvania EDDIE BERNICE JOHNSON, Texas DANA ROHRABACHER, California LYNN C. WOOLSEY, California KEN CALVERT, California DARLENE HOOLEY, Oregon ROSCOE G. BARTLETT, Maryland MARK UDALL, Colorado VERNON J. EHLERS, Michigan DAVID WU, Oregon GIL GUTKNECHT, Minnesota MICHAEL M. HONDA, California FRANK D. LUCAS, Oklahoma BRAD MILLER, North Carolina JUDY BIGGERT, Illinois LINCOLN DAVIS, Tennessee WAYNE T. GILCHREST, Maryland DANIEL LIPINSKI, Illinois W. TODD AKIN, Missouri SHEILA JACKSON LEE, Texas TIMOTHY V. JOHNSON, Illinois BRAD SHERMAN, California J. RANDY FORBES, Virginia BRIAN BAIRD, Washington JO BONNER, Alabama JIM MATHESON, Utah TOM FEENEY, Florida JIM COSTA, California RANDY NEUGEBAUER, Texas AL GREEN, Texas BOB INGLIS, South Carolina CHARLIE MELANCON, Louisiana DAVE G.