Mean Motions and Longitudes in Indian Astronomy
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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. -
Occdhtlm3newstelter
OccdhtlM3Newstelter Volume II, Number 10 january, 1981 Occultation Newsletter is published by the International Occultation Timing Association. Editor and Compositor: H. F. DaBo11; 6 N 106 White Oak Lane; St. Charles, IL 60174; U.S.A. Please send editorial matters to the above, but send address changes, requests, matters of circulation, and other IOTA business to IOTA; P.0. Box 596; Tinley Park; IL 60477; U.S.A. NOTICE TO LUNAR OCCULTATION OBSERVERS paho1. by contacting Sr. Francisco Diego Q., Ixpan- tenco 26-bis, Real dc Ids Reyes, Coyoacdn, Mexico, L. V. Morrison D.F., Mexico. Currently, however, the Latin American Section is experiencing problems with funding, and On 1981 January 1 the international centre for the for the time being, it may be necessary for would-be receipt of timings of occultations of stars by the IOTA/LAS members to subscribe to the English-lan- Moon will be transferred from HM Nautical Almanac guage edition of o.n., or to join the parent IOTA. Office, Royal Greenwich Observatory, England to As- tronomical Division, Hydrographic Department, Japan IOTA NEWS "' From that date observers should send their lunar oc- cultation reports and any correspondence connected David W. Dunham with lunar occultations to the following address: As of 1981 January 1, H. M. Nautical Almanac Office, Astronomical Division at the Royal Greenwich Observatory, England, will Hydrographic Department discontinue collecting observations of lunar occul- Tsukiji-5 tations. After that date, observers should send Chuo-ku, Tokyo their reports to the new International Occultation 104 JAPAN Centre in japan, as described in this issue's lead article. -
Glossary of Marine Navigation 798
GLOSSARY OF MARINE NAVIGATION 798 The main cause, however, appears to be the winds which prevail from south through west to northwest over 50 percent of the time throughout the year and the transverse flows from the English coast toward the Skaggerak. The current retains the characteristics of a J major nontidal current and flows northeastward along the northwest coast of Denmark at speeds ranging between 1.5 to 2.0 knots 75 to 100 percent of the time. Jacob’s staff. See CROSS-STAFF. jamming, n. Intentional transmission or re-radiation of radio signals in such a way as to interfere with reception of desired signals by the K intended receiver. Janus configuration. A term describing orientations of the beams of acoustic or electromagnetic energy employed with doppler naviga- Kaléma, n. A very heavy surf breaking on the Guinea coast during the tion systems. The Janus configuration normally used with doppler winter, even when there is no wind. sonar speed logs, navigators, and docking aids employs four beams Kalman filtering. A statistical method for estimating the parameters of a of ultrasonic energy, displaced laterally 90° from each other, and dynamic system, using recursive techniques of estimation, mea- each directed obliquely (30° from the vertical) from the ship’s bot- surement, weighting, and correction. Weighting is based on vari- tom, to obtain true ground speed in the fore and aft and athwartship ances of the measurements and of the estimates. The filter acts to directions. These speeds are measured as doppler frequency shifts reduce the variance of the estimate with each measurement cycle. -
Lunar Nodes Keys to Emotions and Life Experience
Lunar Nodes Keys To Emotions and Life Experience Diane Ronngren Copyright 2012 ETC Publishing All rights reserved. No part of this book may be reproduced or transmitted in any form or by any means, electronic or mechanical including photocopying or recording, or by any information storage and retrieval system without written permission from the author and publisher, except in the case of brief quotations embodied in critical reviews and articles. ETC Publishing www.etcpublishing.com ISBN 978 -1-930038-55-4 Cover design and graphics by Gary Dunham Dedication To my mother, Norma, who gave me life, taught me the values inherent in my South Node in Libra and inspired me to pursue the possibilities of my North Node in Aries. To Family, who have always encouraged my life journey. Table of Contents Introduction ......................................................................................7 Chapter 1 - Symbols of Destiny ........................................................ 9 Chapter 2 - Node Basics .................................................................. 20 Chapter 3 - Lunar Nodes, Signs and Houses .................................. 26 Aries North Node / Libra South Node ....................................... 26 1st House North Node / 7th House South Node Taurus North Node / Scorpio South Node ................................. 29 2nd House North Node / 8th House South Node Gemini North Node / Sagittarius South Node ........................... 33 3rd House North Node / 9th House South Node Cancer North Node / Capricorn South Node ............................. 36 4th House North Node / 10th House South Node Leo North Node / Aquarius South Node .................................... 39 5th House North Node / 11th House South Node Virgo North Node / Pisces South Node ..................................... 42 6th House North Node / 12th House South Node Libra North Node / Aries South Node ....................................... 45 7th House North Node / 1st House South Node Scorpio North Node / Taurus South Node ................................ -
Looking at Eclipses from Both Sides
Firefox https://cdn.mc-weblink.sg-mktg.com/weblink/MTYyMzAzOTc5N3xKe... Email not displaying correctly? View it in your browser. Looking at Eclipses from Both Sides by Zane B Stein If you have looked at eclipses astrologically you may have noticed a strange fact: the time that astronomers list for the time of maximum eclipse is usually different than the one your astrology program gives you, and sometimes the difference can be quite a few minutes. Why is that? We can give you a clear explanation, and then we can show you how you can adjust a setting (in both Solar Fire, and Astro Gold for Mac), so that you can calculate the charts for the times of both the astrological and the astronomical eclipses. 1 of 4 6/7/2021, 11:18 AM Firefox https://cdn.mc-weblink.sg-mktg.com/weblink/MTYyMzAzOTc5N3xKe... Let’s begin by comparing the eclipse definitions. Astronomical Definition: According to NASA, "An eclipse occurs when one heavenly body such as a moon or planet moves into the shadow of another heavenly body." During a Lunar Eclipse, the “Earth moves between the Sun and the Moon, Earth blocks the sunlight instead of light hitting the Moon's surface, and Earth's shadow falls on the Moon," but if it is a Solar Eclipse, “the Moon moves between the Sun and Earth, the Moon blocks the light of the Sun instead of light hitting the Earth's surface, and the Moon's shadow falls on the Earth.” Astrological Definition: When the Sun and Moon are at the exact same degree, minute and second of a sign (New Moon) or opposite signs (Full Moon), AND the lunation occurs not far from the North or South Lunar Nodes, you have, respectfully, a Solar or Lunar Eclipse. -
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. -
Cislunar Tether Transport System
FINAL REPORT on NIAC Phase I Contract 07600-011 with NASA Institute for Advanced Concepts, Universities Space Research Association CISLUNAR TETHER TRANSPORT SYSTEM Report submitted by: TETHERS UNLIMITED, INC. 8114 Pebble Ct., Clinton WA 98236-9240 Phone: (206) 306-0400 Fax: -0537 email: [email protected] www.tethers.com Report dated: May 30, 1999 Period of Performance: November 1, 1998 to April 30, 1999 PROJECT SUMMARY PHASE I CONTRACT NUMBER NIAC-07600-011 TITLE OF PROJECT CISLUNAR TETHER TRANSPORT SYSTEM NAME AND ADDRESS OF PERFORMING ORGANIZATION (Firm Name, Mail Address, City/State/Zip Tethers Unlimited, Inc. 8114 Pebble Ct., Clinton WA 98236-9240 [email protected] PRINCIPAL INVESTIGATOR Robert P. Hoyt, Ph.D. ABSTRACT The Phase I effort developed a design for a space systems architecture for repeatedly transporting payloads between low Earth orbit and the surface of the moon without significant use of propellant. This architecture consists of one rotating tether in elliptical, equatorial Earth orbit and a second rotating tether in a circular low lunar orbit. The Earth-orbit tether picks up a payload from a circular low Earth orbit and tosses it into a minimal-energy lunar transfer orbit. When the payload arrives at the Moon, the lunar tether catches it and deposits it on the surface of the Moon. Simultaneously, the lunar tether picks up a lunar payload to be sent down to the Earth orbit tether. By transporting equal masses to and from the Moon, the orbital energy and momentum of the system can be conserved, eliminating the need for transfer propellant. Using currently available high-strength tether materials, this system could be built with a total mass of less than 28 times the mass of the payloads it can transport. -
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. -
8.G on the Originality of Indian Mathematical Astronomy
8.g On the originality of Indian Mathematical Astronomy Raymond Mercier1 Introduction Indian astronomy has been the object of intense study by Western scholars since the seventeenth century, before that by generations of Arabic scholars, and of course by Indian scholars themselves over the centuries. Nevertheless we continue to have disputes about the very nature of the subject, illustrating the fact, I suppose, that Indian astronomy is never quite what it seems to be. In the past 35 years, there has been a particularly acrimonious dispute centred on the researches of Roger Billard and David Pingree, both now deceased. I will try to cover what seem to me to be the salient aspects of the matter. Method of Deviations Roger Billard in 1971 wrote his L’Astronomie indienne, at a time when Pingree’s researches were in full spate. Billard’s approach was essentially a refinement of what people have always done when approaching ancient or medieval astronomical texts, that is to carry out a comparison with the calculations made by means of modern astronomical parameters, as a ‘reality check’ in general, and by way of dating in particular. For example Neugebauer & van Hoesen published a collection of horoscopes from Greek literary and epigraphical sources, all of which were dated by means of 2 calculations from modern formulae. Billard’s results depended on plotting the ‘deviation curves’, that is the graph of the ancient mean longitude minus the modern, as a function of time. This was then subjected to a precise statistical analysis, mainly to fix the date of the text. -
Moon-Earth-Sun: the Oldest Three-Body Problem
Moon-Earth-Sun: The oldest three-body problem Martin C. Gutzwiller IBM Research Center, Yorktown Heights, New York 10598 The daily motion of the Moon through the sky has many unusual features that a careful observer can discover without the help of instruments. The three different frequencies for the three degrees of freedom have been known very accurately for 3000 years, and the geometric explanation of the Greek astronomers was basically correct. Whereas Kepler’s laws are sufficient for describing the motion of the planets around the Sun, even the most obvious facts about the lunar motion cannot be understood without the gravitational attraction of both the Earth and the Sun. Newton discussed this problem at great length, and with mixed success; it was the only testing ground for his Universal Gravitation. This background for today’s many-body theory is discussed in some detail because all the guiding principles for our understanding can be traced to the earliest developments of astronomy. They are the oldest results of scientific inquiry, and they were the first ones to be confirmed by the great physicist-mathematicians of the 18th century. By a variety of methods, Laplace was able to claim complete agreement of celestial mechanics with the astronomical observations. Lagrange initiated a new trend wherein the mathematical problems of mechanics could all be solved by the same uniform process; canonical transformations eventually won the field. They were used for the first time on a large scale by Delaunay to find the ultimate solution of the lunar problem by perturbing the solution of the two-body Earth-Moon problem. -
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. -
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.