Reference System Issues in Binary Star Calculations

Total Page:16

File Type:pdf, Size:1020Kb

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! “plane!of!the!sky”!is!appropriate!for!each!such!date,!i.e.,!each!observa3on.!!However,!projec3on!effects!between!the!reference!planes,!differen3al!aberra3on,!and!the!curvature!of!the! sky!are!generally!neglected!in!such!computa3ons.!!Usually!the!only!correc3on!applied!is!for!the!change!in!the!north!direc3on!(posi3on!angle!zero)!due!to!precession!(and!some3mes! also!proper!mo3on).!!This!paper!will!present!an!algorithm!for!a!more!complete!model!of!the!geometry!involved,!and!will!show!that!such!a!model!is!necessary!to!avoid!errors!in!the! computed!observables!that!are!significant!at!modern!astrometric!accuracy.!!The!paper!will!also!suggest!where!conven3ons!need!to!be!established!to!avoid!ambigui3es!in!how!quan33es! related!to!binary!star!orbits!are!interpreted.! ! Mo#va#on' Ambiguous'Aspects'of'the'Orbital'Parameters' Other'Geometry'to'Consider'(cont.)' This!inves3ga3on!began!as!a!rela3vely!simple!project!to!add!a! Because!ORB6!is!a!collec3on!of!orbits!determined!by!different! Another!effect!arises!from!the!3LD!nature!of!the!rela3ve!posi3ons!of! binaryLstar!so[ware!module!to!the!Naval!Observatory!Vector! inves3gators,!it!is!a!heterogeneous!source!of!informa3on.!!Several! the!two!stars.!!For!nearby,!wide!systems,!the!fact!that!B!is!closer!(or! Astrometry!So[ware!(NOVAS).!!NOVAS!it!is!a!free!sourceLcode! aspects!of!the!data!in!ORB6!are!not!well!defined!and!therefore! farther)!than!A!affects!the!separa3on!we!measure;!!we!should!not! library!for!highLprecision!astrometric!calcula3ons!available!at! present!an!obstacle!to!precise!computa3ons.!!About!1/3!of!the!orbits! assume!a!viewpoint!at!infinity!for!these!systems.!! h]p://aa.usno.navy.mil/so[ware/novas/!! do!not!have!the!epoch!E"specified!!(most!of!the!specified!E’s!are! To"Earth,"assumed"at"infinity," in!Fortran,!C,!and!Python.!!It!is!likely! 2000).!!!Orbital!elements!P!and!T,!which!are!3mes,!are!o[en! at"*me"t" that!as!observa3onal!accuracy!inL! expressed!as!a!year!+!frac3on,!in!units!of!Besselian!years,!!but!the! creases,!binary!stars!will!become! conversion!to!more!standard!3me!units!is!not!given.!!In!a!more!subtle! B" an!increasingly!important!issue!in!! issue,!it!is!unclear!what!line!of!sight!should!be!used!to!define!the! sep"2" defining!celes3al!reference!frames.!!For!example,!even!when! “plane!of!the!sky”.!!Stars!move!on!the!celes3al!sphere!(i.e.,!with! sep"2" sep"1" i’ observa3ons!span!only!a!few!years,!the!components!of!wide!pairs! respect!to!the!ICRS!axes)!due!to!proper!mo3on,!aberra3on,!and!other! δ Earth"at"*me"t" d" " with!orbital!periods!of!centuries!will!show!detectable!curvatures!of! effects.!!Aberra3on!shi[s!our!line!of!sight!to!every!star,!regardless!of! (distance"Earth"to"star"A)" A" their!paths!if!the!observa3onal!accuracy!is!great!enough!(Kaplan!&! distance,!by!41!arcseconds!over!the!course!of!every!year.!! sep 1 = (B−A) cos i’ = cos (i + Δϕ) = 70.7038 arcsec Makarov!2004,!AN!324,!419;!Makarov!&!Kaplan!2005,!AJ!129,!2420).!! ! (from previous figure) sep 1 (B−A) cos i’ NOVAS!should!deal!with!all!types!of!astrometric!binary!systems.! To!move!forward,!I!had!to!make!several!(arbitrary)!assump3ons:! sep 2 = arctan = arctan d − δ d − (B−A) sin i ! ’ Plane"of"the" ★ If!E!is!not!specified,!then!E=2000,!i.e.,!E!=!J2000.0!=!JD!2451545.0!(TT).! sky"at"*me"t" The!binary!star!module!that!is!planned!for!NOVAS!and!is!the!subject! Again suppose B−A = 100 arcsec, i=45°, i’=45°.0555°, ★ (="*me"of" of!this!paper!will!provide!both!the!absolute!and!rela3ve!posi3ons!of! The!conversion!from!Besselian!to!Julian!epochs!and!3me!units!is!done! and d = 100 pc. ephemeris"or" observa*on)" the!two!components!of!a!binary!system,!at!a!requested!date,!given! according!to!a!conven3onal!expression!(using!fixedLlength!years)! Then sep 1 − sep 2 = 70.7038 arcsec − 70.7281 arcsec recommended!by!the!IAU!in!1976.! = −24.2 mas known!orbital!elements!and!standard!astrometric!parameters.!!Thus,! it!covers!what!may!called!the!“forward!problem”!of!producing!binary! ★ The!plane!of!the!sky!for!the!orbit!is!orthogonal!to!the!direc3on!toward! the!A!component!of!the!system!defined!by!its!mean"place"at"epoch"E.! star!ephemerides!given!an!orbit!already!determined.!!It!does!not! One!more!effect!to!consider:!differen3al!aberra3on!between!the! deal!with!the!“backward!problem”!of!determining!an!orbit!from! ★ The!direc3on!of!the!orbital!node,!i.e.,!the!sign!of!the!inclina3on,!is!! two!components.! known!(even!though!in!many!cases!it!is!ambiguous).! observa3ons.!!However,!once!an!ini3al!orbit!has!been!determined! aberrated geometric ★ Units!of!arcseconds!used!for!the!semimajor!axis!a!should!be!considered! Aberration moves the apparent places of for!a!binary!system,!followLup!observa3ons!can!improve!the!orbit! positions positions the two stars slightly differently on the to!be!a!measure!of!length;!to!convert!to!astronomical!units!(au),!divide! sky, which can affect both separations through!differen3al!correc3on;!!and!a!correct!formula3on!of!the! B" B" by!the!parallax!of!the!system.! v/c" and position angles. Differential forward!problem!is!necessary!to!avoid!systema3c!errors!in!the! projected"at"B" aberration can amount to sep"2" 1 mas for 10 arcsec separations and improved!orbital!elements.!!!That!is,!the!OLC’s!should!be!as!correct! !!!!!!!!!'''It'would'be'quite'useful'if'the'appropriate'IAU'body'would' sep"3" 10 mas for 100 arcsec separations. In this case, with sep 2 = 70.2781 arcsec, as!possible.!!Given!perfect!orbital!elements,!the!output!of!the! A" A" establish'conven#ons'such'as'the'above'for'future'binary'star'work.'' v/c" sep 2 − sep 3 could be up to ≈ 7 mas. NOVAS!module!(the!C’s)!should!be!accurate!to!be]er!than!1!mas.!!!! projected"at"A" B" ! Binary!stars!are!perhaps!the!purest!example!of!the!twoLbody! Geometry'Usually'Considered' Earth’s"orbital"velocity" problem!in!astronomy,!and!the!computa3on!of!the!rela3ve!posi3ons! v"" In!compu3ng!observables!from!orbital!elements,!we!can!take!the! A" of!the!two!components!in!a!local!spaceLfixed!reference!system!is! solu3on!of!the!twoLbody!problem!for!binary!stars!as!a!given.!! nonLcontroversial.!!However,!taking!that!informa3on!and!predic3ng!! Standard!texts!such!as!Aitken!(1964),!The"Binary"Stars,!then!advise! the!values!of!astrometric!parameters!for!an!EarthLbased!observer! correc3ng!for!the!change!in!the!north!direc3on,!due!to!precession,! requires!a!more!sophis3cated!model!of!the!whole!geometry!than!is! between!the!epoch!of!the!orbit!(E)!and!the!epoch!of!observa3on,! usually!applied.!!In!par3cular,!at!high!levels!of!astrometric!accuracy,! and!similarly!for!the!change!in!north!direc3on!due!to!the!star’s! NOVAS'Algorithm' the!3LD!nature!of!the!problem!comes!into!play!in!surprising!ways.! proper!mo3on!(although!aberra3on!is!usually!a!larger!effect).!! The!algorithm!adopted!for!the!NOVAS!double!star!algorithm!can!be! Simple!formulas!are!provided.!!Some!texts!also!give!correc3ons!for! summarized!as!follows.!!Some!details!(such!as!change!of!units)!are! change!of!scale!and!change!of!lightL3me,!for!those!systems!with! omi]ed,!and!for!prac3cal!reasons!the!order!of!computa3ons!in!the! Available'Orbital'Data'for'Binary'Stars' significant!radial!veloci3es.! so[ware!is!somewhat!different.!!! The!data!set!used!is!the!Sixth!Catalog!of!Orbits!of!Visual!Binary!Stars,! 1) Using!standard!astrometric!parameters!(e.g.,!from!the!Hipparcos!catalog)! 2 available!on!CD!from!the!U.S.!Naval!Observatory!and!online!at! Other'Geometry'To'Consider' for!component!A,!or!the!system’s!center!of!mass,!compute:! h]p://www.usno.navy.mil/USNO/astrometry/op3calLIRLprod/wds/orb6!! ''''''''''''a ,!the!mean!place!direc3on!vector!of!A!at!epoch!E"(epoch!of!orbit),! (it!is!an!update!to!Hartkopf,!Mason,!&!Worley!2001,!AJ!122,!3472).1!! In!the!module!developed!for!NOVAS,!the!change!in!north!direc3on!is! E part!of!a!general!transforma3on!between!two!3LD!reference!systems! ''''''''''''aO,!the!mean!place!direc3on!vector!of!A!at!the!3me!of!observa3on,! The!catalog!provides!2518!orbits!of!2413!systems,!although!not!all!
Recommended publications
  • 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
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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).
    [Show full text]
  • 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.
    [Show full text]
  • 4. Lunar Architecture
    4. Lunar Architecture 4.1 Summary and Recommendations As defined by the Exploration Systems Architecture Study (ESAS), the lunar architecture is a combination of the lunar “mission mode,” the assignment of functionality to flight elements, and the definition of the activities to be performed on the lunar surface. The trade space for the lunar “mission mode,” or approach to performing the crewed lunar missions, was limited to the cislunar space and Earth-orbital staging locations, the lunar surface activities duration and location, and the lunar abort/return strategies. The lunar mission mode analysis is detailed in Section 4.2, Lunar Mission Mode. Surface activities, including those performed on sortie- and outpost-duration missions, are detailed in Section 4.3, Lunar Surface Activities, along with a discussion of the deployment of the outpost itself. The mission mode analysis was built around a matrix of lunar- and Earth-staging nodes. Lunar-staging locations initially considered included the Earth-Moon L1 libration point, Low Lunar Orbit (LLO), and the lunar surface. Earth-orbital staging locations considered included due-east Low Earth Orbits (LEOs), higher-inclination International Space Station (ISS) orbits, and raised apogee High Earth Orbits (HEOs). Cases that lack staging nodes (i.e., “direct” missions) in space and at Earth were also considered. This study addressed lunar surface duration and location variables (including latitude, longi- tude, and surface stay-time) and made an effort to preserve the option for full global landing site access. Abort strategies were also considered from the lunar vicinity. “Anytime return” from the lunar surface is a desirable option that was analyzed along with options for orbital and surface loiter.
    [Show full text]
  • Paper Session III-B - a Lunar Orbiting Node in Support of Missions to Mars
    The Space Congress® Proceedings 1989 (26th) Space - The New Generation Apr 27th, 3:00 PM Paper Session III-B - A Lunar Orbiting Node in Support of Missions to Mars A. Butterfield Project Engineer, The Bionetics Corporation, Hampton, Virginia J. R. Wrobel Project Engineer, The Bionetics Corporation, Hampton, Virginia L. B. Garrett Head, Spacecraft Analysis Branch, Langley Research Center, NAbA, Hampton, Virginia Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Butterfield, A.; rW obel, J. R.; and Garrett, L. B., "Paper Session III-B - A Lunar Orbiting Node in Support of Missions to Mars" (1989). The Space Congress® Proceedings. 10. https://commons.erau.edu/space-congress-proceedings/proceedings-1989-26th/april-27-1989/10 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. A LUNAR ORBITING NODE IN SUPPORT OF MISSIONS TO MARS A. Butterfield, Project Engineer J. R. Wrobel, Project Manager The Bionetics Corporation, Hampton, Virginia Dr. L. Bernard Garrett, Head, Spacecraft Analysis Branch Langley Research Center, NAbA, Hampton, Virginia ABSTRACT Future Mars missions may use lunar-derived oxygen as a propellant for interplanetary transit. A man-tended platform as a Node in low lunar orbit offers a site for storage and transfer of lunar oxygen to the transport vehicles as well as rendezvous and transfer for lunar-bound cargo and crews. In addition, it could provide an emergency safe-haven for a crew awaiting rescue.
    [Show full text]
  • Obliquity of Mercury: Influence of the Precession of the Pericenter and of Tides
    Obliquity of Mercury: influence of the precession of the pericenter and of tides Rose-Marie Baland, Marie Yseboodt, Attilio Rivoldini, Tim Van Hoolst Royal Observatory of Belgium, Ringlaan 3, B-1180 Brussels, Belgium. Email: [email protected] March 2017 Paper accepted for publication in Icarus Contents 1 Introduction 4 2 The Cassini state of a rigid Mercury 6 2.1 From the Hamiltonian formalism towards the angular momentum formalism . .6 2.2 Angular momentum equation . .7 2.2.1 Main precessional torque . .9 2.2.2 Secondary nutational torque . 10 2.3 Solving the angular momentum equation . 11 2.3.1 Main precession amplitude (order zero in κ!)................ 12 2.3.2 Nutation amplitude (first order in κ!).................... 13 2.3.3 Full solution, obliquity and deviation . 13 3 Spin axis orientation of a non-rigid Mercury 16 3.1 Angular momentum equation . 19 3.2 Solution . 19 4 Spin axis orientation measurements and previous data inversion 23 4.1 Orientation measurements . 23 4.2 Equatorial and Cartesian coordinates . 23 4.3 Approximations and previous results . 24 4.4 Measurements uncertainties . 25 4.5 Systematic errors . 26 5 A new inversion of the data 27 arXiv:1612.06564v2 [astro-ph.EP] 24 Mar 2017 5.1 Inversion . 29 5.2 Obliquity, deviation and orientation model . 30 6 Comparisons with the literature 32 6.1 On the relation between the mean equilibrium obliquity and the polar moment of inertia . 32 6.1.1 Peale's equation . 32 6.1.2 Noyelles and Lhotka's equations . 33 6.2 On the nutation .
    [Show full text]
  • Use of Planetary Oblateness for Parking-Orbit Alinement
    NASA TECHNICAL NOTE k USE OF PLANETARY OBLATENESS FOR PARKING-ORBIT ALINEMENT _/- . by Joseph Re Thibodeau III Manned Spacecrafi Center Houston, Texas i li NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. JULY 1968 i i i TECH LIBRARY KAFB, NM USE OF PLANETARY OBLATENESS FOR PARKING-ORBIT ALINEMENT By Joseph R. Thibodeau I11 Manned Spacecraft Center Houston, Texas NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federal Scientific and Technical Information Springfield, Virginia 22151 - CFSTI price $3.00 ABSTRACT A rapid analytical technique is used to deter­ mine simultaneously the possible configurations of an elliptical parking orbit at Mars. Both the geometry of planetary approach and departure and the effects of planetary oblateness are used to determine the char­ acteristics of those orbits which shift into proper alinement for departure and require no discrete pro­ pulsive maneuvers. The technique makes use of the separable nature of the equations that express secular rotation of the orbit plane and major axis. Prelimi­ nary results indicate that the orbital inclinations fall into narrow bands which are widely distributed over the interval of possible inclinations. ii USE OF PLANETARY OBLATENESS FOR PARI(ING-ORBIT ALINEMENT By Joseph R. Thibodeau ID Manned Spacecraft Center SUMMARY A technique relying upon the effects of gravitational harmonics for parking-orbit alinement is analyzed. The basic approach is to choose orbital eccentricity and incli­ nation so that the resulting nodal and apsidal motions will shift the original orbit into proper alinement for departure on the intended date. Thus, the need for propulsive maneuvers to change the orbital inclination, line of apsides, or orbital eccentricity are reduced or eliminated; and periapsis impulses can be used for both the capture and the escape maneuvers.
    [Show full text]
  • MONITORING and MITIGATION of CLOSE PROXIMITIES in LOW EARTH ORBIT S. Aida(1)
    MONITORING AND MITIGATION OF CLOSE PROXIMITIES IN LOW EARTH ORBIT S. Aida(1), T. Patzelt(2), L. Leushacke(2), M. Kirschner(1), R. Kiehling(1) (1)Deutsches Zentrum für Luft- und Raumfahrt (DLR), German Space Operations Center (GSOC), 82234 Wessling, Germany, +49(0)8153-28-2158, [email protected] (2)Research Establishment for Applied Science (FGAN), Research Institute for High Frequency Physics and Radar Techniques (FHR), Neuenahrer Str. 20, 53343 Wachtberg, Germany, +49(0)228-9435-200, [email protected], [email protected] ABSTRACT The German Space Operations Center (GSOC) is currently building up an operational proximity monitoring and mitigation system. Proximity events are detected based on the “Two-line Elements” (TLEs) from the US Strategic Command (USSTRATCOM) and precise orbit information from locally operated missions. Despite evident deficiencies in the quality and timeliness of the available orbit information, TLEs are currently the only source of orbit information for the numerous space objects. While an overly trust in the quality of the orbital data might result in an underestimation of the true collision risk, a pessimistic accuracy assessment would result in frequent proximity warnings. The TLE uncertainty needs to be carefully assessed to avoid such implications. Even after a realistic error analysis, the orbit information of a possible jeopardising object has to be refined for a proper planning and implementation of collision avoidance manoeuvres. For this purpose, the use of FGAN radar tracking is currently planned, for which an accuracy assessment is to be considered. In this paper, the proximity statistics and TLE accuracy analysis as well as the FGAN tracking campaign are discussed, together with their application to the collision risk management of satellites in a Low-Earth-Orbit (LEO).
    [Show full text]
  • Lunar Cycler Orbits with Alternating Semi-Monthly Transfer Windows by C
    AAS 91-105 Lunar Cycler Orbits with Alternating Semi-Monthly Transfer Windows by C. Uphoff & M. A. Crouch Ball Space Systems Division Boulder, Colorado This paper is a presentation of a new type of cislunar transfer orbit that has encounters with the Moon twice per month every other month. The use of this technique is suggested for Earth- to-Moon Cycler spacecraft that contain the heavy and expensive life support equipment for human transfer from low Earth orbit to the Moon and for logistical supply of lunar bases. The basis for the technique is a 180° near-circular Moon-to- Moon transfer orbit that is inclined to the Earth-Moon plane by an angle that is compatible with a low-inclination, near- minimal energy Earth-to-Moon transfer orbit. Also included are preliminary discussions of Cycler spacecraft logistics for extensive manned operations on the Moon. Numerical studies are included to verify the usefulness of the technique in a realistic cislunar dynamic environment and estimates of navigation propellant requirements are given. Introduction In 1985, Aldrin [1]suggested the use of Cycler orbits (periodic trajectories that repeat the round- trip transfer from home planet to destination planet) for the life support equipment and logistical supplies necessary for extensive manned exploration of the Moon and Mars. He also presented his thoughts on the benefits of using Cycler spacecraft at the Space 88 Symposium in Albuquerque during a panel discussion on "Approaching the Construction Problems in Space." These trajectories must have the characteristic that they can be easily targeted for either launch or destination planet and that the times between encounters yield a reasonable stay time on the destination and provide for both routine and emergency return on a fairly regular basis.
    [Show full text]