NOAA Technical Memorandum ERL ARL-94
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Ast 443 / Phy 517
AST 443 / PHY 517 Astronomical Observing Techniques Prof. F.M. Walter I. The Basics The 3 basic measurements: • WHERE something is • WHEN something happened • HOW BRIGHT something is Since this is science, let’s be quantitative! Where • Positions: – 2-dimensional projections on celestial sphere (q,f) • q,f are angular measures: radians, or degrees, minutes, arcsec – 3-dimensional position in space (x,y,z) or (q, f, r). • (x,y,z) are linear positions within a right-handed rectilinear coordinate system. • R is a distance (spherical coordinates) • Galactic positions are sometimes presented in cylindrical coordinates, of galactocentric radius, height above the galactic plane, and azimuth. Angles There are • 360 degrees (o) in a circle • 60 minutes of arc (‘) in a degree (arcmin) • 60 seconds of arc (“) in an arcmin There are • 24 hours (h) along the equator • 60 minutes of time (m) per hour • 60 seconds of time (s) per minute • 1 second of time = 15”/cos(latitude) Coordinate Systems "What good are Mercator's North Poles and Equators Tropics, Zones, and Meridian Lines?" So the Bellman would cry, and the crew would reply "They are merely conventional signs" L. Carroll -- The Hunting of the Snark • Equatorial (celestial): based on terrestrial longitude & latitude • Ecliptic: based on the Earth’s orbit • Altitude-Azimuth (alt-az): local • Galactic: based on MilKy Way • Supergalactic: based on supergalactic plane Reference points Celestial coordinates (Right Ascension α, Declination δ) • δ = 0: projection oF terrestrial equator • (α, δ) = (0,0): -
Appendix a Orbits
Appendix A Orbits As discussed in the Introduction, a good ¯rst approximation for satellite motion is obtained by assuming the spacecraft is a point mass or spherical body moving in the gravitational ¯eld of a spherical planet. This leads to the classical two-body problem. Since we use the term body to refer to a spacecraft of ¯nite size (as in rigid body), it may be more appropriate to call this the two-particle problem, but I will use the term two-body problem in its classical sense. The basic elements of orbital dynamics are captured in Kepler's three laws which he published in the 17th century. His laws were for the orbital motion of the planets about the Sun, but are also applicable to the motion of satellites about planets. The three laws are: 1. The orbit of each planet is an ellipse with the Sun at one focus. 2. The line joining the planet to the Sun sweeps out equal areas in equal times. 3. The square of the period of a planet is proportional to the cube of its mean distance to the sun. The ¯rst law applies to most spacecraft, but it is also possible for spacecraft to travel in parabolic and hyperbolic orbits, in which case the period is in¯nite and the 3rd law does not apply. However, the 2nd law applies to all two-body motion. Newton's 2nd law and his law of universal gravitation provide the tools for generalizing Kepler's laws to non-elliptical orbits, as well as for proving Kepler's laws. -
A Study of Ancient Khmer Ephemerides
A study of ancient Khmer ephemerides François Vernotte∗ and Satyanad Kichenassamy** November 5, 2018 Abstract – We study ancient Khmer ephemerides described in 1910 by the French engineer Faraut, in order to determine whether they rely on observations carried out in Cambodia. These ephemerides were found to be of Indian origin and have been adapted for another longitude, most likely in Burma. A method for estimating the date and place where the ephemerides were developed or adapted is described and applied. 1 Introduction Our colleague Prof. Olivier de Bernon, from the École Française d’Extrême Orient in Paris, pointed out to us the need to understand astronomical systems in Cambo- dia, as he surmised that astronomical and mathematical ideas from India may have developed there in unexpected ways.1 A proper discussion of this problem requires an interdisciplinary approach where history, philology and archeology must be sup- plemented, as we shall see, by an understanding of the evolution of Astronomy and Mathematics up to modern times. This line of thought meets other recent lines of research, on the conceptual evolution of Mathematics, and on the definition and measurement of time, the latter being the main motivation of Indian Astronomy. In 1910 [1], the French engineer Félix Gaspard Faraut (1846–1911) described with great care the method of computing ephemerides in Cambodia used by the horas, i.e., the Khmer astronomers/astrologers.2 The names for the astronomical luminaries as well as the astronomical quantities [1] clearly show the Indian origin ∗F. Vernotte is with UTINAM, Observatory THETA of Franche Comté-Bourgogne, University of Franche Comté/UBFC/CNRS, 41 bis avenue de l’observatoire - B.P. -
Ephemeris Time, D. H. Sadler, Occasional
EPHEMERIS TIME D. H. Sadler 1. Introduction. – At the eighth General Assembly of the International Astronomical Union, held in Rome in 1952 September, the following resolution was adopted: “It is recommended that, in all cases where the mean solar second is unsatisfactory as a unit of time by reason of its variability, the unit adopted should be the sidereal year at 1900.0; that the time reckoned in these units be designated “Ephemeris Time”; that the change of mean solar time to ephemeris time be accomplished by the following correction: ΔT = +24°.349 + 72s.318T + 29s.950T2 +1.82144 · B where T is reckoned in Julian centuries from 1900 January 0 Greenwich Mean Noon and B has the meaning given by Spencer Jones in Monthly Notices R.A.S., Vol. 99, 541, 1939; and that the above formula define also the second. No change is contemplated or recommended in the measure of Universal Time, nor in its definition.” The ultimate purpose of this article is to explain, in simple terms, the effect that the adoption of this resolution will have on spherical and dynamical astronomy and, in particular, on the ephemerides in the Nautical Almanac. It should be noted that, in accordance with another I.A.U. resolution, Ephemeris Time (E.T.) will not be introduced into the national ephemerides until 1960. Universal Time (U.T.), previously termed Greenwich Mean Time (G.M.T.), depends both on the rotation of the Earth on its axis and on the revolution of the Earth in its orbit round the Sun. There is now no doubt as to the variability, both short-term and long-term, of the rate of rotation of the Earth; U.T. -
An Introduction to Orbit Dynamics and Its Application to Satellite-Based Earth Monitoring Systems
19780004170 NASA-RP- 1009 78N12113 An introduction to orbit dynamics and its application to satellite-based earth monitoring systems NASA Reference Publication 1009 An Introduction to Orbit Dynamics and Its Application to Satellite-Based Earth Monitoring Missions David R. Brooks Langley Research Center Hampton, Virginia National Aeronautics and Space Administration Scientific and Technical Informalion Office 1977 PREFACE This report provides, by analysis and example, an appreciation of the long- term behavior of orbiting satellites at a level of complexity suitable for the initial phases of planning Earth monitoring missions. The basic orbit dynamics of satellite motion are covered in detail. Of particular interest are orbit plane precession, Sun-synchronous orbits, and establishment of conditions for repetitive surface coverage. Orbit plane precession relative to the Sun is shown to be the driving factor in observed patterns of surface illumination, on which are superimposed effects of the seasonal motion of the Sun relative to the equator. Considerable attention is given to the special geometry of Sun- synchronous orbits, orbits whose precession rate matches the average apparent precession rate of the Sun. The solar and orbital plane motions take place within an inertial framework, and these motions are related to the longitude- latitude coordinates of the satellite ground track through appropriate spatial and temporal coordinate systems. It is shown how orbit parameters can be chosen to give repetitive coverage of the same set of longitude-latitude values on a daily or longer basis. Several potential Earth monitoring missions which illus- trate representative applications of the orbit dynamics are described. The interactions between orbital properties and the resulting coverage and illumina- tion patterns over specific sites on the Earth's surface are shown to be at the heart of satellite mission planning. -
Planet Positions: 1 Planet Positions
Planet Positions: 1 Planet Positions As the planets orbit the Sun, they move around the celestial sphere, staying close to the plane of the ecliptic. As seen from the Earth, the angle between the Sun and a planet -- called the elongation -- constantly changes. We can identify a few special configurations of the planets -- those positions where the elongation is particularly noteworthy. The inferior planets -- those which orbit closer INFERIOR PLANETS to the Sun than Earth does -- have configurations as shown: SC At both superior conjunction (SC) and inferior conjunction (IC), the planet is in line with the Earth and Sun and has an elongation of 0°. At greatest elongation, the planet reaches its IC maximum separation from the Sun, a value GEE GWE dependent on the size of the planet's orbit. At greatest eastern elongation (GEE), the planet lies east of the Sun and trails it across the sky, while at greatest western elongation (GWE), the planet lies west of the Sun, leading it across the sky. Best viewing for inferior planets is generally at greatest elongation, when the planet is as far from SUPERIOR PLANETS the Sun as it can get and thus in the darkest sky possible. C The superior planets -- those orbiting outside of Earth's orbit -- have configurations as shown: A planet at conjunction (C) is lined up with the Sun and has an elongation of 0°, while a planet at opposition (O) lies in the opposite direction from the Sun, at an elongation of 180°. EQ WQ Planets at quadrature have elongations of 90°. -
Sun Tool Options
Sun Study Tools Sophomore Architecture Studio: Lighting Lecture 1: • Introduction to Daylight (part 1) • Survey of the Color Spectrum • Making Light • Controlling Light Lecture 2: • Daylight (part 2) • Design Tools to study Solar Design • Architectural Applications Lecture 3: • Light in Architecture • Lighting Design Strategies Sun Tool Options 1. Paper and Pencil 2. Build a Model 3. Use a Computer The first step to any of these options is to define…. Where is the site? 1 2 Sun Study Tools North Latitude and Longitude South Longitude Latitude Longitude Sun Study Tools North America Latitude 3 United States e ud tit La Sun Study Tools New York 72w 44n 42n Site Location The site location is specified by a latitude l and a longitude L. Latitudes and longitudes may be found in any standard atlas or almanac. Chart shows the latitudes and longitudes of some North American cities. Conventions used in expressing latitudes are: Positive = northern hemisphere Negative = southern hemisphere Conventions used in expressing longitudes are: Positive = west of prime meridian (Greenwich, United Kingdom) Latitude and Longitude of Some North American Cities Negative = east of prime meridian 4 Sun Study Tools Solar Path Suns Position The position of the sun is specified by the solar altitude and solar azimuth and is a function of site latitude, solar time, and solar declination. 5 Sun Study Tools Suns Position The rotation of the earth about its axis, as well as its revolution about the sun, produces an apparent motion of the sun with respect to any point on the altitude earth's surface. The position of the sun with respect to such a point is expressed in terms of two angles: azimuth The sun's position in terms of solar altitude (a ) and azimuth (a ) solar azimuth, which is the t s with respect to the cardinal points of the compass. -
Equatorial and Cartesian Coordinates • Consider the Unit Sphere (“Unit”: I.E
Coordinate Transforms Equatorial and Cartesian Coordinates • Consider the unit sphere (“unit”: i.e. declination the distance from the center of the (δ) sphere to its surface is r = 1) • Then the equatorial coordinates Equator can be transformed into Cartesian coordinates: right ascension (α) – x = cos(α) cos(δ) – y = sin(α) cos(δ) z x – z = sin(δ) y • It can be much easier to use Cartesian coordinates for some manipulations of geometry in the sky Equatorial and Cartesian Coordinates • Consider the unit sphere (“unit”: i.e. the distance y x = Rcosα from the center of the y = Rsinα α R sphere to its surface is r = 1) x Right • Then the equatorial Ascension (α) coordinates can be transformed into Cartesian coordinates: declination (δ) – x = cos(α)cos(δ) z r = 1 – y = sin(α)cos(δ) δ R = rcosδ R – z = sin(δ) z = rsinδ Precession • Because the Earth is not a perfect sphere, it wobbles as it spins around its axis • This effect is known as precession • The equatorial coordinate system relies on the idea that the Earth rotates such that only Right Ascension, and not declination, is a time-dependent coordinate The effects of Precession • Currently, the star Polaris is the North Star (it lies roughly above the Earth’s North Pole at δ = 90oN) • But, over the course of about 26,000 years a variety of different points in the sky will truly be at δ = 90oN • The declination coordinate is time-dependent albeit on very long timescales • A precise astronomical coordinate system must account for this effect Equatorial coordinates and equinoxes • To account -
Solar Engineering Basics
Solar Energy Fundamentals Course No: M04-018 Credit: 4 PDH Harlan H. Bengtson, PhD, P.E. Continuing Education and Development, Inc. 22 Stonewall Court Woodcliff Lake, NJ 07677 P: (877) 322-5800 [email protected] Solar Energy Fundamentals Harlan H. Bengtson, PhD, P.E. COURSE CONTENT 1. Introduction Solar energy travels from the sun to the earth in the form of electromagnetic radiation. In this course properties of electromagnetic radiation will be discussed and basic calculations for electromagnetic radiation will be described. Several solar position parameters will be discussed along with means of calculating values for them. The major methods by which solar radiation is converted into other useable forms of energy will be discussed briefly. Extraterrestrial solar radiation (that striking the earth’s outer atmosphere) will be discussed and means of estimating its value at a given location and time will be presented. Finally there will be a presentation of how to obtain values for the average monthly rate of solar radiation striking the surface of a typical solar collector, at a specified location in the United States for a given month. Numerous examples are included to illustrate the calculations and data retrieval methods presented. Image Credit: NOAA, Earth System Research Laboratory 1 • Be able to calculate wavelength if given frequency for specified electromagnetic radiation. • Be able to calculate frequency if given wavelength for specified electromagnetic radiation. • Know the meaning of absorbance, reflectance and transmittance as applied to a surface receiving electromagnetic radiation and be able to make calculations with those parameters. • Be able to obtain or calculate values for solar declination, solar hour angle, solar altitude angle, sunrise angle, and sunset angle. -
Elliptical Orbits
1 Ellipse-geometry 1.1 Parameterization • Functional characterization:(a: semi major axis, b ≤ a: semi minor axis) x2 y 2 b p + = 1 ⇐⇒ y(x) = · ± a2 − x2 (1) a b a • Parameterization in cartesian coordinates, which follows directly from Eq. (1): x a · cos t = with 0 ≤ t < 2π (2) y b · sin t – The origin (0, 0) is the center of the ellipse and the auxilliary circle with radius a. √ – The focal points are located at (±a · e, 0) with the eccentricity e = a2 − b2/a. • Parameterization in polar coordinates:(p: parameter, 0 ≤ < 1: eccentricity) p r(ϕ) = (3) 1 + e cos ϕ – The origin (0, 0) is the right focal point of the ellipse. – The major axis is given by 2a = r(0) − r(π), thus a = p/(1 − e2), the center is therefore at − pe/(1 − e2), 0. – ϕ = 0 corresponds to the periapsis (the point closest to the focal point; which is also called perigee/perihelion/periastron in case of an orbit around the Earth/sun/star). The relation between t and ϕ of the parameterizations in Eqs. (2) and (3) is the following: t r1 − e ϕ tan = · tan (4) 2 1 + e 2 1.2 Area of an elliptic sector As an ellipse is a circle with radius a scaled by a factor b/a in y-direction (Eq. 1), the area of an elliptic sector PFS (Fig. ??) is just this fraction of the area PFQ in the auxiliary circle. b t 2 1 APFS = · · πa − · ae · a sin t a 2π 2 (5) 1 = (t − e sin t) · a b 2 The area of the full ellipse (t = 2π) is then, of course, Aellipse = π a b (6) Figure 1: Ellipse and auxilliary circle. -
Librational Response of Europa, Ganymede, and Callisto with an Ocean for a Non-Keplerian Orbit
A&A 527, A118 (2011) Astronomy DOI: 10.1051/0004-6361/201015304 & c ESO 2011 Astrophysics Librational response of Europa, Ganymede, and Callisto with an ocean for a non-Keplerian orbit N. Rambaux1,2, T. Van Hoolst3, and Ö. Karatekin3 1 Université Pierre et Marie Curie, Paris VI, IMCCE, Observatoire de Paris, 77 avenue Denfert-Rochereau, 75014 Paris, France 2 IMCCE, Observatoire de Paris, CNRS UMR 8028, 77 avenue Denfert-Rochereau, 75014 Paris, France e-mail: [email protected] 3 Royal Observatory of Belgium, 3 avenue Circulaire, 1180 Brussels, Belgium e-mail: [tim.vanhoolst;ozgur.karatekin]@oma.be Received 30 June 2010 / Accepted 8 September 2010 ABSTRACT Context. The Galilean satellites Europa, Ganymede, and Callisto are thought to harbor a subsurface ocean beneath an ice shell but its properties, such as the depth beneath the surface, have not been well constrained. Future geodetic observations with, for example, space missions like the Europa Jupiter System Mission (EJSM) of NASA and ESA may refine our knowledge about the shell and ocean. Aims. Measurement of librational motion is a useful tool for detecting an ocean and characterizing the interior parameters of the moons. The objective of this paper is to investigate the librational response of Galilean satellites, Europa, Ganymede, and Callisto assumed to have a subsurface ocean by taking the perturbations of the Keplerian orbit into account. Perturbations from a purely Keplerian orbit are caused by gravitational attraction of the other Galilean satellites, the Sun, and the oblateness of Jupiter. Methods. We use the librational equations developed for a satellite with a subsurface ocean in synchronous spin-orbit resonance. -
Interplanetary Trajectories in STK in a Few Hundred Easy Steps*
Interplanetary Trajectories in STK in a Few Hundred Easy Steps* (*and to think that last year’s students thought some guidance would be helpful!) Satellite ToolKit Interplanetary Tutorial STK Version 9 INITIAL SETUP 1) Open STK. Choose the “Create a New Scenario” button. 2) Name your scenario and, if you would like, enter a description for it. The scenario time is not too critical – it will be updated automatically as we add segments to our mission. 3) STK will give you the opportunity to insert a satellite. (If it does not, or you would like to add another satellite later, you can click on the Insert menu at the top and choose New…) The Orbit Wizard is an easy way to add satellites, but we will choose Define Properties instead. We choose Define Properties directly because we want to use a maneuver-based tool called the Astrogator, which will undo any initial orbit set using the Orbit Wizard. Make sure Satellite is selected in the left pane of the Insert window, then choose Define Properties in the right-hand pane and click the Insert…button. 4) The Properties window for the Satellite appears. You can access this window later by right-clicking or double-clicking on the satellite’s name in the Object Browser (the left side of the STK window). When you open the Properties window, it will default to the Basic Orbit screen, which happens to be where we want to be. The Basic Orbit screen allows you to choose what kind of numerical propagator STK should use to move the satellite.