Obliquity-Driven Sculpting of Exoplanetary Systems
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Reference System Issues in Binary Star Calculations
Reference System Issues in Binary Star Calculations Poster for Division A Meeting DAp.1.05 George H. Kaplan Consultant to U.S. Naval Observatory Washington, D.C., U.S.A. [email protected] or [email protected] IAU General Assembly Honolulu, August 2015 1 Poster DAp.1.05 Division!A! !!!!!!Coordinate!System!Issues!in!Binary!Star!Computa3ons! George!H.!Kaplan! Consultant!to!U.S.!Naval!Observatory!!([email protected][email protected])! It!has!been!es3mated!that!half!of!all!stars!are!components!of!binary!or!mul3ple!systems.!!Yet!the!number!of!known!orbits!for!astrometric!and!spectroscopic!binary!systems!together!is! less!than!7,000!(including!redundancies),!almost!all!of!them!for!bright!stars.!!A!new!genera3on!of!deep!allLsky!surveys!such!as!PanLSTARRS,!Gaia,!and!LSST!are!expected!to!lead!to!the! discovery!of!millions!of!new!systems.!!Although!for!many!of!these!systems,!the!orbits!may!be!poorly!sampled!ini3ally,!it!is!to!be!expected!that!combina3ons!of!new!and!old!data!sources! will!eventually!lead!to!many!more!orbits!being!known.!!As!a!result,!a!revolu3on!in!the!scien3fic!understanding!of!these!systems!may!be!upon!us.! The!current!database!of!visual!(astrometric)!binary!orbits!represents!them!rela3ve!to!the!“plane!of!the!sky”,!that!is,!the!plane!orthogonal!to!the!line!of!sight.!!Although!the!line!of!sight! to!stars!constantly!changes!due!to!proper!mo3on,!aberra3on,!and!other!effects,!there!is!no!agreed!upon!standard!for!what!line!of!sight!defines!the!orbital!reference!plane.!! Furthermore,!the!computa3on!of!differen3al!coordinates!(component!B!rela3ve!to!A)!for!a!given!date!must!be!based!on!the!binary!system’s!direc3on!at!that!date.!!Thus,!a!different! -
Sentinel-1 Constellation SAR Interferometry Performance Verification
Sentinel-1 Constellation SAR Interferometry Performance Verification Dirk Geudtner1, Francisco Ceba Vega1, Pau Prats2 , Nestor Yaguee-Martinez2 , Francesco de Zan3, Helko Breit3, Andrea Monti Guarnieri4, Yngvar Larsen5, Itziar Barat1, Cecillia Mezzera1, Ian Shurmer6 and Ramon Torres1 1 ESA ESTEC 2 DLR, Microwaves and Radar Institute 3 DLR, Remote Sensing Technology Institute 4 Politecnico Di Milano 5 Northern Research Institute (Norut) 6 ESA ESOC ESA UNCLASSIFIED - For Official Use Outline • Introduction − Sentinel-1 Constellation Mission Status − Overview of SAR Imaging Modes • Results from the Sentinel-1B Commissioning Phase • Azimuth Spectral Alignment Impact on common − Burst synchronization Doppler bandwidth − Difference in mean Doppler Centroid Frequency (InSAR) • Sentinel-1 Orbital Tube and InSAR Baseline • Demonstration of cross S-1A/S-1B InSAR Capability for Surface Deformation Mapping ESA UNCLASSIFIED - For Official Use ESA Slide 2 Sentinel-1 Constellation Mission Status • Constellation of two SAR C-band (5.405 GHz) satellites (A & B units) • Sentinel-1A launched on 3 April, 2014 & Sentinel-1B on 25 April, 2016 • Near-Polar, sun-synchronous (dawn-dusk) orbit at 698 km • 12-day repeat cycle (each satellite), 6 days for the constellation • Systematic SAR data acquisition using a predefined observation scenario • More than 10 TB of data products daily (specification of 3 TB) • 3 X-band Ground stations (Svalbard, Matera, Maspalomas) + upcoming 4th core station in Inuvik, Canada • Use of European Data Relay System (EDRS) provides -
Circular Orbits
ANALYSIS AND MECHANIZATION OF LAUNCH WINDOW AND RENDEZVOUS COMPUTATION PART I. CIRCULAR ORBITS Research & Analysis Section Tech Memo No. 175 March 1966 BY J. L. Shady Prepared for: NATIONAL AERONAUTICS AND SPACE ADMINISTRATION / GEORGE C. MARSHALL SPACE FLIGHT CENTER AERO-ASTRODYNAMICS LABORATORY Prepared under Contract NAS8-20082 Reviewed by: " D. L/Cooper Technical Supervisor Director Research & Analysis Section / NORTHROP SPACE LABORATORIES HUNTSVILLE DEPARTMENT HUNTSVILLE, ALABAMA FOREWORD The enclosed presents the results of work performed by Northrop Space Laboratories, Huntsville Department, while )under contract to the Aero- Astrodynamfcs Laboratory of Marshall Space Flight Center (NAS8-20082) * This task was conducted in response to the requirement of Appendix E-1, Schedule Order No. PO. Technical coordination was provided by Mr. Jesco van Puttkamer of the Technical and Scientific Staff (R-AERO-T) ABS TRACT This repart presents Khe results of an analytical study to develop the logic for a digrtal c3mp;lrer sclbrolrtine for the automatic computationof launch opportunities, or the sequence of launch times, that rill allow execution of various mades of gross ~ircuiarorbit rendezvous. The equations developed in this study are based on tho-bady orb:taf chmry. The Earch has been assumed tcr ha.:e the shape of an oblate spheroid. Oblateness of the Earth has been accounted for by assuming the circular target orbit to be space- fixed and by cosrecring che T ational raLe of the EarKh accordingly. Gross rendezvous between the rarget vehicle and a maneuverable chaser vehicle, assumed to be a standard 3+ uprated Saturn V launched from Cape Kennedy, is in this srudy aecomplfshed by: .x> direct ascent to rendezvous, or 2) rendezvous via an intermediate circG1a.r parking orbit. -
Some of the Scientific Miracles in Brief ﻹﻋﺠﺎز اﻟﻌﻠ� ﻲﻓ ﺳﻄﻮر English [ إ�ﻠ�ي - ]
Some of the Scientific Miracles in Brief ﻟﻋﺠﺎز ﻟﻌﻠ� ﻓ ﺳﻄﻮر English [ إ���ي - ] www.onereason.org website مﻮﻗﻊ ﺳﺒﺐ وﻟﺣﺪ www.islamreligion.com website مﻮﻗﻊ دﻳﻦ ﻟﻋﺳﻼم 2013 - 1434 Some of the Scientific Miracles in Brief Ever since the dawn of mankind, we have sought to understand nature and our place in it. In this quest for the purpose of life many people have turned to religion. Most religions are based on books claimed by their followers to be divinely inspired, without any proof. Islam is different because it is based upon reason and proof. There are clear signs that the book of Islam, the Quran, is the word of God and we have many reasons to support this claim: - There are scientific and historical facts found in the Qu- ran which were unknown to the people at the time, and have only been discovered recently by contemporary science. - The Quran is in a unique style of language that cannot be replicated, this is known as the ‘Inimitability of the Qu- ran.’ - There are prophecies made in the Quran and by the Prophet Muhammad, may God praise him, which have come to be pass. This article lays out and explains the scientific facts that are found in the Quran, centuries before they were ‘discov- ered’ in contemporary science. It is important to note that the Quran is not a book of science but a book of ‘signs’. These signs are there for people to recognise God’s existence and 2 affirm His revelation. As we know, science sometimes takes a ‘U-turn’ where what once scientifically correct is false a few years later. -
Principles and Techniques of Remote Sensing
BASIC ORBIT MECHANICS 1-1 Example Mission Requirements: Spatial and Temporal Scales of Hydrologic Processes 1.E+05 Lateral Redistribution 1.E+04 Year Evapotranspiration 1.E+03 Month 1.E+02 Week Percolation Streamflow Day 1.E+01 Time Scale (hours) Scale Time 1.E+00 Precipitation Runoff Intensity 1.E-01 Infiltration 1.E-02 1.E-02 1.E-01 1.E+00 1.E+01 1.E+02 1.E+03 1.E+04 1.E+05 1.E+06 1.E+07 Length Scale (meters) 1-2 BASIC ORBITS • Circular Orbits – Used most often for earth orbiting remote sensing satellites – Nadir trace resembles a sinusoid on planet surface for general case – Geosynchronous orbit has a period equal to the siderial day – Geostationary orbits are equatorial geosynchronous orbits – Sun synchronous orbits provide constant node-to-sun angle • Elliptical Orbits: – Used most often for planetary remote sensing – Can also be used to increase observation time of certain region on Earth 1-3 CIRCULAR ORBITS • Circular orbits balance inward gravitational force and outward centrifugal force: R 2 F mg g s r mv2 F c r g R2 F F v s g c r 2r r T 2r 2 v gs R • The rate of change of the nodal longitude is approximated by: d 3 cos I J R3 g dt 2 2 s r 7 2 1-4 Orbital Velocities 9 8 7 6 5 Earth Moon 4 Mars 3 Linear Velocity in km/sec in Linear Velocity 2 1 0 200 400 600 800 1000 1200 1400 Orbit Altitude in km 1-5 Orbital Periods 300 250 200 Earth Moon Mars 150 Orbital Period in MinutesPeriodOrbitalin 100 50 200 400 600 800 1000 1200 1400 Orbit Altitude in km 1-6 ORBIT INCLINATION EQUATORIAL I PLANE EARTH ORBITAL PLANE 1-7 ORBITAL NODE LONGITUDE SUN ORBITAL PLANE EARTH VERNAL EQUINOX 1-8 SATELLITE ORBIT PRECESSION 1-9 CIRCULAR GEOSYNCHRONOUS ORBIT TRACE 1-10 ORBIT COVERAGE • The orbit step S is the longitudinal difference between two consecutive equatorial crossings • If S is such that N S 360 ; N, L integers L then the orbit is repetitive. -
Transit Timing Analysis of the Hot Jupiters WASP-43B and WASP-46B and the Super Earth Gj1214b
Transit timing analysis of the hot Jupiters WASP-43b and WASP-46b and the super Earth GJ1214b Mathias Polfliet Promotors: Michaël Gillon, Maarten Baes 1 Abstract Transit timing analysis is proving to be a promising method to detect new planetary partners in systems which already have known transiting planets, particularly in the orbital resonances of the system. In these resonances we might be able to detect Earth-mass objects well below the current detection and even theoretical (due to stellar variability) thresholds of the radial velocity method. We present four new transits for WASP-46b, four new transits for WASP-43b and eight new transits for GJ1214b observed with the robotic telescope TRAPPIST located at ESO La Silla Observatory, Chile. Modelling the data was done using several Markov Chain Monte Carlo (MCMC) simulations of the new transits with old data and a collection of transit timings for GJ1214b from published papers. For the hot Jupiters this lead to a general increase in accuracy for the physical parameters of the system (for the mass and period we found: 2.034±0.052 MJup and 0.81347460±0.00000048 days and 2.03±0.13 MJup and 1.4303723±0.0000011 days for WASP-43b and WASP-46b respectively). For GJ1214b this was not the case given the limited photometric precision of TRAPPIST. The additional timings however allowed us to constrain the period to 1.580404695±0.000000084 days and the RMS of the TTVs to 16 seconds. We investigated given systems for Transit Timing Variations (TTVs) and variations in the other transit parameters and found no significant (3sv) deviations. -
The Rings and Inner Moons of Uranus and Neptune: Recent Advances and Open Questions
Workshop on the Study of the Ice Giant Planets (2014) 2031.pdf THE RINGS AND INNER MOONS OF URANUS AND NEPTUNE: RECENT ADVANCES AND OPEN QUESTIONS. Mark R. Showalter1, 1SETI Institute (189 Bernardo Avenue, Mountain View, CA 94043, mshowal- [email protected]! ). The legacy of the Voyager mission still dominates patterns or “modes” seem to require ongoing perturba- our knowledge of the Uranus and Neptune ring-moon tions. It has long been hypothesized that numerous systems. That legacy includes the first clear images of small, unseen ring-moons are responsible, just as the nine narrow, dense Uranian rings and of the ring- Ophelia and Cordelia “shepherd” ring ε. However, arcs of Neptune. Voyager’s cameras also first revealed none of the missing moons were seen by Voyager, sug- eleven small, inner moons at Uranus and six at Nep- gesting that they must be quite small. Furthermore, the tune. The interplay between these rings and moons absence of moons in most of the gaps of Saturn’s rings, continues to raise fundamental dynamical questions; after a decade-long search by Cassini’s cameras, sug- each moon and each ring contributes a piece of the gests that confinement mechanisms other than shep- story of how these systems formed and evolved. herding might be viable. However, the details of these Nevertheless, Earth-based observations have pro- processes are unknown. vided and continue to provide invaluable new insights The outermost µ ring of Uranus shares its orbit into the behavior of these systems. Our most detailed with the tiny moon Mab. Keck and Hubble images knowledge of the rings’ geometry has come from spanning the visual and near-infrared reveal that this Earth-based stellar occultations; one fortuitous stellar ring is distinctly blue, unlike any other ring in the solar alignment revealed the moon Larissa well before Voy- system except one—Saturn’s E ring. -
Preparation of Papers for AIAA Technical Conferences
DUKSUP: A Computer Program for High Thrust Launch Vehicle Trajectory Design & Optimization Spurlock, O.F.I and Williams, C. H.II NASA Glenn Research Center, Cleveland, OH, 44135 From the late 1960’s through 1997, the leadership of NASA’s Intermediate and Large class unmanned expendable launch vehicle projects resided at the NASA Lewis (now Glenn) Research Center (LeRC). One of LeRC’s primary responsibilities --- trajectory design and performance analysis --- was accomplished by an internally-developed analytic three dimensional computer program called DUKSUP. Because of its Calculus of Variations-based optimization routine, this code was generally more capable of finding optimal solutions than its contemporaries. A derivation of optimal control using the Calculus of Variations is summarized including transversality, intermediate, and final conditions. The two point boundary value problem is explained. A brief summary of the code’s operation is provided, including iteration via the Newton-Raphson scheme and integration of variational and motion equations via a 4th order Runge-Kutta scheme. Main subroutines are discussed. The history of the LeRC trajectory design efforts in the early 1960’s is explained within the context of supporting the Centaur upper stage program. How the code was constructed based on the operation of the Atlas/Centaur launch vehicle, the limits of the computers of that era, the limits of the computer programming languages, and the missions it supported are discussed. The vehicles DUKSUP supported (Atlas/Centaur, Titan/Centaur, and Shuttle/Centaur) are briefly described. The types of missions, including Earth orbital and interplanetary, are described. The roles of flight constraints and their impact on launch operations are detailed (such as jettisoning hardware on heating, Range Safety, ground station tracking, and elliptical parking orbits). -
Flowers and Satellites
Flowers and Satellites G. Lucarelli, R. Santamaria, S. Troisi and L. Turturici (Naval University, Naples) In this paper some interesting properties of circular orbiting satellites' ground traces are pointed out. It will be shown how such properties are typical of some spherical and plane curves that look like flowers both in their name and shape. In addition, the choice of the best satellite constellations satisfying specific requirements is strongly facilitated by exploiting these properties. i. INTRODUCTION. Since the dawning of mathematical sciences, many scientists have attempted to emulate mathematically the beauty of nature, with particular care to floral forms. The mathematician Guido Grandi gave in the Age of Enlightenment a definitive contribution; some spherical and plane curves reproducing flowers have his name: Guido Grandi's Clelie and Rodonee. It will be deduced that the ground traces of circular orbiting satellites are described by the same equations, simple and therefore easily reproducible, and hence employable in satellite constellation designing and in other similar problems. 2. GROUND TRACE GEOMETRY. The parametric equations describing the ground trace of any satellite in circular orbit are: . ... 24(t sin <p = sin i sin tan (A-A0 + £-T0) = cos i tan — — where i = inclination of the orbital plane; <j>, A = geographic coordinates of the subsatellite point; t = time parameter, defined as angular measure of Earth rotation starting from T0 ; T0 , Ao = time and geographic longitude relative to the crossing of the satellite at the ascending node; T = orbital satellite period as expressed in hours. In the specific case of a polar-orbiting satellite, equations (i) become tan(AA + t) = where T0 = o; AA = A — Ao ; /i = 24/T. -
Abstracts of the 50Th DDA Meeting (Boulder, CO)
Abstracts of the 50th DDA Meeting (Boulder, CO) American Astronomical Society June, 2019 100 — Dynamics on Asteroids break-up event around a Lagrange point. 100.01 — Simulations of a Synthetic Eurybates 100.02 — High-Fidelity Testing of Binary Asteroid Collisional Family Formation with Applications to 1999 KW4 Timothy Holt1; David Nesvorny2; Jonathan Horner1; Alex B. Davis1; Daniel Scheeres1 Rachel King1; Brad Carter1; Leigh Brookshaw1 1 Aerospace Engineering Sciences, University of Colorado Boulder 1 Centre for Astrophysics, University of Southern Queensland (Boulder, Colorado, United States) (Longmont, Colorado, United States) 2 Southwest Research Institute (Boulder, Connecticut, United The commonly accepted formation process for asym- States) metric binary asteroids is the spin up and eventual fission of rubble pile asteroids as proposed by Walsh, Of the six recognized collisional families in the Jo- Richardson and Michel (Walsh et al., Nature 2008) vian Trojan swarms, the Eurybates family is the and Scheeres (Scheeres, Icarus 2007). In this theory largest, with over 200 recognized members. Located a rubble pile asteroid is spun up by YORP until it around the Jovian L4 Lagrange point, librations of reaches a critical spin rate and experiences a mass the members make this family an interesting study shedding event forming a close, low-eccentricity in orbital dynamics. The Jovian Trojans are thought satellite. Further work by Jacobson and Scheeres to have been captured during an early period of in- used a planar, two-ellipsoid model to analyze the stability in the Solar system. The parent body of the evolutionary pathways of such a formation event family, 3548 Eurybates is one of the targets for the from the moment the bodies initially fission (Jacob- LUCY spacecraft, and our work will provide a dy- son and Scheeres, Icarus 2011). -
Self-Organizing Systems in Planetary Physics: Harmonic Resonances Of
Self-Organizing Systems in Planetary Physics : Harmonic Resonances of Planet and Moon Orbits Markus J. Aschwanden1 1) Lockheed Martin, Solar and Astrophysics Laboratory, Org. A021S, Bldg. 252, 3251 Hanover St., Palo Alto, CA 94304, USA; e-mail: [email protected] ABSTRACT The geometric arrangement of planet and moon orbits into a regularly spaced pattern of distances is the result of a self-organizing system. The positive feedback mechanism that operates a self-organizing system is accomplished by harmonic orbit resonances, leading to long-term stable planet and moon orbits in solar or stellar systems. The distance pattern of planets was originally described by the empirical Titius-Bode law, and by a generalized version with a constant geometric progression factor (corresponding to logarithmic spacing). We find that the orbital periods Ti and planet distances Ri from the Sun are not consistent with logarithmic spacing, 2/3 2/3 but rather follow the quantized scaling (Ri+1/Ri) = (Ti+1/Ti) = (Hi+1/Hi) , where the harmonic ratios are given by five dominant resonances, namely (Hi+1 : Hi)=(3:2), (5 : 3), (2 : 1), (5 : 2), (3 : 1). We find that the orbital period ratios tend to follow the quantized harmonic ratios in increasing order. We apply this harmonic orbit resonance model to the planets and moons in our solar system, and to the exo-planets of 55 Cnc and HD 10180 planetary systems. The model allows us a prediction of missing planets in each planetary system, based on the quasi- regular self-organizing pattern of harmonic orbit resonance zones. We predict 7 (and 4) missing exo-planets around the star 55 Cnc (and HD 10180). -
Astro Vol.7 Issue 4
NEWSLETTER Year 7, Issue 04 PSSP - News The First NASA Videoconference Prepared by Elzbieta Gwiazda-Szer On the 15th of January there was a videoconference between the Rota College (Izmir, Turkey), School4Child (Lodz, Poland) and NASA’s Marshall Space Flight Center in Huntsville, Alabama in the U.S.A.. It was a historical day for both schools since it was their first videoconference with a NASA Center. Our school prepared for that during the classes conducted by Ms. Elzbieta Gwiazda-Szer . The classes and videoconference’s theme was "Toys in Space". In class, students got familiar with Newton's three principles of dynamics, they learned about gravity and microgravity. In groups, students sought answers to questions concerning the behavior of their toys in space. Their considerations related to a football , a jump rope , a kendama and a paper boomerang . Some students have modified their toys in order to improve the fun efficiency in microgravity. Our students also had the opportunity to meet with their ePals, with whom they are in touch via emails. This is the third year we have been partners of the program PSSP - Partner School Science Program. The videoconferencing has been received with great enthusiasm by both our students and students from Turkey. Pages 1 Technology Lunar Time Lapse Panorama including Yutu Rover Image Credit: CNSA, Chinanews, Kenneth Kremer & Marco Di Lorenzo Where has the Yutu rover been on the Moon? Arriving in 2013 mid-December, the Chinese Yutu robotic rover has spent some of the past month and a half exploring Mare Imbrium on Earth's Moon.