Calculations in Star Charts
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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. -
Navigation of Space Vlbi Missions: Radioastron and Vsop
https://ntrs.nasa.gov/search.jsp?R=19940019453 2020-06-16T15:35:05+00:00Z View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by NASA Technical Reports Server NAVIGATION OF SPACE VLBI MISSIONS: RADIOASTRON AND VSOP Jordan Ellis Jet Propulsion Laboratory California Institute of Technology Pasadena, California Abstract Network (DSN) and co-observation and correlation by facilities of the National Radio Astronomy Observatory In the mid 199Os, Russian and Japanese space agencies (NRAO). Extensive international collaboration between will each place into highly elliptic earth orbit a radio the space agencies and between the multi-national VLBI telescope consisting of a a large antenna and radio as- community will be required to maximize the science tronomy receivers. Very Long Baseline Interferometry return. Schedules for an international network of VLBI (VLBI) techniques will be used to obtain high resolu- radio telescopes will be coordinated to ensure the ground tion images of radio sources observed by the space and antennas and spacecraft antenna are simultaneously ob- ground based antennas. Stringent navigation accuracy serving the same sources. An international network of requirements are imposed on the Space VLBI missions ground tracking stations will also support both space- by the need to transfer an ultra stable ground refer- craft. The tracking stations will record science data ence frequency standard to the spacecraft and by the downlinked in real time from the orbiting satellites, demands of the VLBI correlation process. Orbit deter- transfer a stable phase reference and collect two-way mination for the missions will be the joint responsibility doppler for navigation. -
Michael Perryman
Michael Perryman Cavendish Laboratory, Cambridge (1977−79) European Space Agency, NL (1980−2009) (Hipparcos 1981−1997; Gaia 1995−2009) [Leiden University, NL,1993−2009] Max-Planck Institute for Astronomy & Heidelberg University (2010) Visiting Professor: University of Bristol (2011−12) University College Dublin (2012−13) Lecture program 1. Space Astrometry 1/3: History, rationale, and Hipparcos 2. Space Astrometry 2/3: Hipparcos science results (Tue 5 Nov) 3. Space Astrometry 3/3: Gaia (Thu 7 Nov) 4. Exoplanets: prospects for Gaia (Thu 14 Nov) 5. Some aspects of optical photon detection (Tue 19 Nov) M83 (David Malin) Hipparcos Text Our Sun Gaia Parallax measurement principle… Problematic from Earth: Sun (1) obtaining absolute parallaxes from relative measurements Earth (2) complicated by atmosphere [+ thermal/gravitational flexure] (3) no all-sky visibility Some history: the first 2000 years • 200 BC (ancient Greeks): • size and distance of Sun and Moon; motion of the planets • 900–1200: developing Islamic culture • 1500–1700: resurgence of scientific enquiry: • Earth moves around the Sun (Copernicus), better observations (Tycho) • motion of the planets (Kepler); laws of gravity and motion (Newton) • navigation at sea; understanding the Earth’s motion through space • 1718: Edmond Halley • first to measure the movement of the stars through space • 1725: James Bradley measured stellar aberration • Earth’s motion; finite speed of light; immensity of stellar distances • 1783: Herschel inferred Sun’s motion through space • 1838–39: Bessell/Henderson/Struve -
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. -
Astrometry and Optics During the Past 2000 Years
1 Astrometry and optics during the past 2000 years Erik Høg Niels Bohr Institute, Copenhagen, Denmark 2011.05.03: Collection of reports from November 2008 ABSTRACT: The satellite missions Hipparcos and Gaia by the European Space Agency will together bring a decrease of astrometric errors by a factor 10000, four orders of magnitude, more than was achieved during the preceding 500 years. This modern development of astrometry was at first obtained by photoelectric astrometry. An experiment with this technique in 1925 led to the Hipparcos satellite mission in the years 1989-93 as described in the following reports Nos. 1 and 10. The report No. 11 is about the subsequent period of space astrometry with CCDs in a scanning satellite. This period began in 1992 with my proposal of a mission called Roemer, which led to the Gaia mission due for launch in 2013. My contributions to the history of astrometry and optics are based on 50 years of work in the field of astrometry but the reports cover spans of time within the past 2000 years, e.g., 400 years of astrometry, 650 years of optics, and the “miraculous” approval of the Hipparcos satellite mission during a few months of 1980. 2011.05.03: Collection of reports from November 2008. The following contains overview with summary and link to the reports Nos. 1-9 from 2008 and Nos. 10-13 from 2011. The reports are collected in two big file, see details on p.8. CONTENTS of Nos. 1-9 from 2008 No. Title Overview with links to all reports 2 1 Bengt Strömgren and modern astrometry: 5 Development of photoelectric astrometry including the Hipparcos mission 1A Bengt Strömgren and modern astrometry .. -
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. -
2 Coordinate Systems
2 Coordinate systems In order to find something one needs a system of coordinates. For determining the positions of the stars and planets where the distance to the object often is unknown it usually suffices to use two coordinates. On the other hand, since the Earth rotates around it’s own axis as well as around the Sun the positions of stars and planets is continually changing, and the measurment of when an object is in a certain place is as important as deciding where it is. Our first task is to decide on a coordinate system and the position of 1. The origin. E.g. one’s own location, the center of the Earth, the, the center of the Solar System, the Galaxy, etc. 2. The fundamental plan (x−y plane). This is often a plane of some physical significance such as the horizon, the equator, or the ecliptic. 3. Decide on the direction of the positive x-axis, also known as the “reference direction”. 4. And, finally, on a convention of signs of the y− and z− axes, i.e whether to use a left-handed or right-handed coordinate system. For example Eratosthenes of Cyrene (c. 276 BC c. 195 BC) was a Greek mathematician, elegiac poet, athlete, geographer, astronomer, and music theo- rist who invented a system of latitude and longitude. (According to Wikipedia he was also the first person to use the word geography and invented the disci- pline of geography as we understand it.). The origin of this coordinate system was the center of the Earth and the fundamental plane was the equator, which location Eratosthenes calculated relative to the parts of the Earth known to him. -
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New Closed-Form Solutions for Optimal Impulsive Control of Spacecraft Relative Motion
New Closed-Form Solutions for Optimal Impulsive Control of Spacecraft Relative Motion Michelle Chernick∗ and Simone D'Amicoy Aeronautics and Astronautics, Stanford University, Stanford, California, 94305, USA This paper addresses the fuel-optimal guidance and control of the relative motion for formation-flying and rendezvous using impulsive maneuvers. To meet the requirements of future multi-satellite missions, closed-form solutions of the inverse relative dynamics are sought in arbitrary orbits. Time constraints dictated by mission operations and relevant perturbations acting on the formation are taken into account by splitting the optimal recon- figuration in a guidance (long-term) and control (short-term) layer. Both problems are cast in relative orbit element space which allows the simple inclusion of secular and long-periodic perturbations through a state transition matrix and the translation of the fuel-optimal optimization into a minimum-length path-planning problem. Due to the proper choice of state variables, both guidance and control problems can be solved (semi-)analytically leading to optimal, predictable maneuvering schemes for simple on-board implementation. Besides generalizing previous work, this paper finds four new in-plane and out-of-plane (semi-)analytical solutions to the optimal control problem in the cases of unperturbed ec- centric and perturbed near-circular orbits. A general delta-v lower bound is formulated which provides insight into the optimality of the control solutions, and a strong analogy between elliptic Hohmann transfers and formation-flying control is established. Finally, the functionality, performance, and benefits of the new impulsive maneuvering schemes are rigorously assessed through numerical integration of the equations of motion and a systematic comparison with primer vector optimal control. -
COORDINATES, TIME, and the SKY John Thorstensen
COORDINATES, TIME, AND THE SKY John Thorstensen Department of Physics and Astronomy Dartmouth College, Hanover, NH 03755 This subject is fundamental to anyone who looks at the heavens; it is aesthetically and mathematically beautiful, and rich in history. Yet I'm not aware of any text which treats time and the sky at a level appropriate for the audience I meet in the more technical introductory astronomy course. The treatments I've seen either tend to be very lengthy and quite technical, as in the classic texts on `spherical astronomy', or overly simplified. The aim of this brief monograph is to explain these topics in a manner which takes advantage of the mathematics accessible to a college freshman with a good background in science and math. This math, with a few well-chosen extensions, makes it possible to discuss these topics with a good degree of precision and rigor. Students at this level who study this text carefully, work examples, and think about the issues involved can expect to master the subject at a useful level. While the mathematics used here are not particularly advanced, I caution that the geometry is not always trivial to visualize, and the definitions do require some careful thought even for more advanced students. Coordinate Systems for Direction Think for the moment of the problem of describing the direction of a star in the sky. Any star is so far away that, no matter where on earth you view it from, it appears to be in almost exactly the same direction. This is not necessarily the case for an object in the solar system; the moon, for instance, is only 60 earth radii away, so its direction can vary by more than a degree as seen from different points on earth. -
Impulsive Maneuvers for Formation Reconfiguration Using Relative Orbital Elements
JOURNAL OF GUIDANCE,CONTROL, AND DYNAMICS Vol. 38, No. 6, June 2015 Impulsive Maneuvers for Formation Reconfiguration Using Relative Orbital Elements G. Gaias∗ and S. D’Amico† DLR, German Aerospace Center, 82234 Wessling, Germany DOI: 10.2514/1.G000189 Advanced multisatellite missions based on formation-flying and on-orbit servicing concepts require the capability to arbitrarily reconfigure the relative motion in an autonomous, fuel efficient, and flexible manner. Realistic flight scenarios impose maneuvering time constraints driven by the satellite bus, by the payload, or by collision avoidance needs. In addition, mission control center planning and operations tasks demand determinism and predictability of the propulsion system activities. Based on these considerations and on the experience gained from the most recent autonomous formation-flying demonstrations in near-circular orbit, this paper addresses and reviews multi- impulsive solution schemes for formation reconfiguration in the relative orbit elements space. In contrast to the available literature, which focuses on case-by-case or problem-specific solutions, this work seeks the systematic search and characterization of impulsive maneuvers of operational relevance. The inversion of the equations of relative motion parameterized using relative orbital elements enables the straightforward computation of analytical or numerical solutions and provides direct insight into the delta-v cost and the most convenient maneuver locations. The resulting general methodology is not only able to refind and requalify all particular solutions known in literature or flown in space, but enables the identification of novel fuel-efficient maneuvering schemes for future onboard implementation. Nomenclature missions. Realistic operational scenarios ask for accomplishing such a = semimajor axis actions in a safe way, within certain levels of accuracy, and in a fuel- B = control input matrix of the relative dynamics efficient manner. -
Chasing the Pole — Howard L. Cohen
Reprinted From AAC Newsletter FirstLight (2010 May/June) Chasing the Pole — Howard L. Cohen Polaris like supernal beacon burns, a pivot-gem amid our star-lit Dome ~ Charles Never Holmes (1916) ew star gazers often believe the North Star (Polaris) is brightest of all, even mistaking Venus for this best known star. More advanced star gazers soon learn dozens of Nnighttime gems appear brighter, forty-seven in fact. Polaris only shines at magnitude +2.0 and can even be difficult to see in light polluted skies. On the other hand, Sirius, brightest of all nighttime stars (at magnitude -1.4), shines twenty-five times brighter! Beginning star gazers also often believe this guidepost star faithfully defines the direction north. Although other stars staunchly circle the heavens during night’s darkness, many think this pole star remains steadfast in its position always marking a fixed point on the sky. Indeed, a popular and often used Shakespeare quote (from Julius Caesar) is in tune with this perception: “I am constant as the northern star, Of whose true-fix'd and resting quality There is no fellow in the firmament.” More advanced star gazers know better, that the “true-fix’d and resting quality”of the northern star is only an approximation. Not only does this north star slowly circle the northen heavenly pole (Fig. 1) but this famous star is also not quite constant in light, slightly varying about 0.03 magnitudes. Polaris, in fact, is the brightest appearing Cepheid variable, a type of pulsating star. Still, Polaris is a good marker of the north cardinal point.