27 AAS/AIAA Space Flight Mechanics Meeting February 5-9, 2017 San
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Mars Reconnaissance Orbiter Navigation Strategy for the Exomars Schiaparelli EDM Lander Mission
Jet Propulsion Laboratory California Institute of Technology Mars Reconnaissance Orbiter Navigation Strategy for the ExoMars Schiaparelli EDM Lander Mission Premkumar R. Menon Sean V. Wagner, David C. Jefferson, Eric J. Graat, Kyong J. Lee, and William B. Schulze AAS/AIAA Astrodynamics Specialist Conference San Antonio, Texas February 5–9, 2017 AAS Paper 17-337 © 2017 California Institute of Technology. Government Sponsorship Acknowledged. Mars Reconnaissance Orbiter Project Mars Reconnaissance Orbiter (Mission, Spacecraft and PSO) The Mars Reconnaissance Orbiter mission launched in August 2005 from the Cape Canaveral Air Force Station arriving at Mars in March 2006 started science operations in November 2006. MRO has completed 10 years since launch (50,000 orbits by Mar 2017) and to date has returned nearly 300 Terabytes of data. MRO Primary Science Orbit (PSO): • Sun-synchronous orbit ascending node at 3:00 PM ± 15 minutes Local Mean Solar Time (LMST) (daylight equatorial crossing) • Periapsis is frozen about the Mars South Pole • Near-repeat ground track walk (GTW) every 17-day, 211 orbit (short-term repeat) MRO targeting cycle, exact repeat after 4602 orbits. The nominal GTW is 32.45811 km West each 211 orbit cycle (maintained with periodic maneuvers). MRO Spacecraft: • Spacecraft Bus: 3-axis stabilized ACS system; 3-meter diameter High Gain Antenna; hydrazine propulsion system • Instrument Suite: HiRISE Camera, CRISM Imaging spectrometer, Mars Climate Sounder, Mars Color Imager, Context Camera, Shallow Subsurface Radar, Electra engineering payload (among other instrument payloads) 2/07/17 MRO support of ExoMars Schiaparelli Lander Overflight Relay PRM-3 4. MRO shall have good overflight pass geometry within the first 2 Sols after landing. -
Matematikken Viser Vej Til Mars
S •Matematikken The viser vej til Mars Kim Plauborg © The Terma Group 2016 THE BEGINNING Terma has been in Space since man walked on the Moon! © The Terma Group 2016 FROM ESRO TO EXOMARS Terma powered the first comet landing ever! BREAKING NEWS The mission ends today when the Rosetta satellite will set down on the surface In 2014 the Rosetta satellite deployed the small lander Philae, which landed on the cometof 67P morethe than 10 comet years after Rosetta was launched. © The Terma Group 2016 FROM ESRO TO EXOMARS Rosetta Mars Express Technology Venus Express evolution and Galileo enhancement Small GEO BepiColombo ExoMars © The Terma Group 2016 Why go Mars? Getting to and landing on Mars is difficult ! © The Terma Group 2016 THE EXOMARS PROGRAMME Two ESA missions to Mars in cooperation with Roscosmos with the main objective to search for evidence of life 2016 Mission Trace Gas Orbiter Schiaparelli 2020 Mission Rover Surface platform © The Terma Group 2016 EXOMARS 2016 14th March 2016 Launched from Baikonur cosmodrome, Kazakhstan © The Terma Group 2016 EXOMARS 2016 16th October 2016 Separation of Schiaparelli from the orbiter © The Terma Group 2016 SCHIAPARELLI Schiaparelli (EDM) - an entry, descent and landing demonstrator module © The Terma Group 2016 EXOMARS 2016 19th October 2016 Landing of Schiaparelli the surface of Mars © The Terma Group 2016 EXOMARS 2016 19th October 2016 Landing of Schiaparelli the surface of Mars © The Terma Group 2016 EXOMARS 2020 © The Terma Group 2016 TERMA AND EXOMARS Terma deliveries to the ExoMars 2016 mission • Remote Terminal Power Unit for Schiaparelli • Mission Control System • Spacecraft Simulator • Support for the Launch and Early Orbit Phase © The Terma Group 2016 ExoMars RTPU The RTPU is a central unit in the Schiaparelli lander. -
Mechanisms for Space Applications
Mechanisms for space applications M. Meftah a,* , A. Irbah a, R. Le Letty b, M. Barr´ ec, S. Pasquarella d, M. Bokaie e, A. Bataille b, and G. Poiet a a CNRS/INSU, LATMOS-IPSL, Universit´ e Versailles St-Quentin, Guyancourt, France b Cedrat Technologies SA, 15 Ch. de Malacher, 38246 Meylan, France c Thales Avionics Electrical Motors, 78700 Conflans Sainte-Honorine, France d Vincent Associates, 803 Linden Ave., Rochester, NY 14625,United States e TiNi Aerospace, 2505 Kerner Blvd., San Rafael, CA 94901, United States ABSTRACT All space instruments contain mechanisms or moving mechanical assemblies that must move (sliding, rolling, rotating, or spinning) and their successful operati on is usually mission-critical. Generally, mechanisms are not redundant and therefore represent potential single point failure modes. Several space missions have suered anomalies or failures due to problems in applying space mechanisms technology. Mechanisms require a specific qualification through a dedicated test campaign. This paper covers the design, development, testing, production, and in-flight experience of the PICARD/SODISM mechanisms. PICARD is a space mission dedicated to the study of the Sun. The PICARD Satellite was successfully launched, on June 15, 2010 on a DNEPR launcher from Dombarovskiy Cosmodrome, near Yasny (Russia). SODISM (SOlar Diameter Imager and Surface Mapper) is a 11 cm Ritchey-Chretien imaging telescope, taking solar images at five wavelengths. SODISM uses several mechanisms (a system to unlock the door at the entrance of the instrument, a system to open/closed the door using a stepper motor, two filters wheels usingastepper motor, and a mechanical shutter). For the fine pointing, SODISM uses three piezoelectric devices acting on th e primary mirror of the telescope. -
AFSPC-CO TERMINOLOGY Revised: 12 Jan 2019
AFSPC-CO TERMINOLOGY Revised: 12 Jan 2019 Term Description AEHF Advanced Extremely High Frequency AFB / AFS Air Force Base / Air Force Station AOC Air Operations Center AOI Area of Interest The point in the orbit of a heavenly body, specifically the moon, or of a man-made satellite Apogee at which it is farthest from the earth. Even CAP rockets experience apogee. Either of two points in an eccentric orbit, one (higher apsis) farthest from the center of Apsis attraction, the other (lower apsis) nearest to the center of attraction Argument of Perigee the angle in a satellites' orbit plane that is measured from the Ascending Node to the (ω) perigee along the satellite direction of travel CGO Company Grade Officer CLV Calculated Load Value, Crew Launch Vehicle COP Common Operating Picture DCO Defensive Cyber Operations DHS Department of Homeland Security DoD Department of Defense DOP Dilution of Precision Defense Satellite Communications Systems - wideband communications spacecraft for DSCS the USAF DSP Defense Satellite Program or Defense Support Program - "Eyes in the Sky" EHF Extremely High Frequency (30-300 GHz; 1mm-1cm) ELF Extremely Low Frequency (3-30 Hz; 100,000km-10,000km) EMS Electromagnetic Spectrum Equitorial Plane the plane passing through the equator EWR Early Warning Radar and Electromagnetic Wave Resistivity GBR Ground-Based Radar and Global Broadband Roaming GBS Global Broadcast Service GEO Geosynchronous Earth Orbit or Geostationary Orbit ( ~22,300 miles above Earth) GEODSS Ground-Based Electro-Optical Deep Space Surveillance -
Solar Radius Determined from PICARD/SODISM Observations and Extremely Weak Wavelength Dependence in the Visible and the Near-Infrared
A&A 616, A64 (2018) https://doi.org/10.1051/0004-6361/201832159 Astronomy c ESO 2018 & Astrophysics Solar radius determined from PICARD/SODISM observations and extremely weak wavelength dependence in the visible and the near-infrared M. Meftah1, T. Corbard2, A. Hauchecorne1, F. Morand2, R. Ikhlef2, B. Chauvineau2, C. Renaud2, A. Sarkissian1, and L. Damé1 1 Université Paris Saclay, Sorbonne Université, UVSQ, CNRS, LATMOS, 11 Boulevard d’Alembert, 78280 Guyancourt, France e-mail: [email protected] 2 Université de la Côte d’Azur, Observatoire de la Côte d’Azur (OCA), CNRS, Boulevard de l’Observatoire, 06304 Nice, France Received 23 October 2017 / Accepted 9 May 2018 ABSTRACT Context. In 2015, the International Astronomical Union (IAU) passed Resolution B3, which defined a set of nominal conversion constants for stellar and planetary astronomy. Resolution B3 defined a new value of the nominal solar radius (RN = 695 700 km) that is different from the canonical value used until now (695 990 km). The nominal solar radius is consistent with helioseismic estimates. Recent results obtained from ground-based instruments, balloon flights, or space-based instruments highlight solar radius values that are significantly different. These results are related to the direct measurements of the photospheric solar radius, which are mainly based on the inflection point position methods. The discrepancy between the seismic radius and the photospheric solar radius can be explained by the difference between the height at disk center and the inflection point of the intensity profile on the solar limb. At 535.7 nm (photosphere), there may be a difference of 330 km between the two definitions of the solar radius. -
Arthur C. Clarke Fred Körper, SFGH-Treffen 21.02.2009
SF-Klassiker: Arthur C. Clarke Fred Körper, SFGH-Treffen 21.02.2009 Sir Arthur Charles Clarke (* 16. Dezember 1917 in Minehead, Somerset, England; † 19. März 2008 in Colombo, Sri Lanka) war ein britischer Science-Fiction-Schriftsteller. Durch den Film 2001: Odyssee im Weltraum von Stanley Kubrick, der auf einer Kurzgeschichte Clarkes beruht und dessen Drehbuch Clarke gemeinsam mit Kubrick schrieb, wurde er auch außerhalb der Science-Fiction-Szene bekannt. Clarke gilt als Visionär neuer Technologien, die er außer in Science-Fiction-Romanen und Kurzgeschichten auch in wissenschaftlichen Artikeln beschrieb. 1 Leben 2 Werk 2.1 Romane 2.2 Erzählungen 2.3 Kurzgeschichtensammlungen 2.4 Gemeinschaftswerke 2.5 Autobiografisches 3 Verfilmungen (Auswahl) 4 Clarke'sche Gesetze Leben Arthur Charles Clarke wurde am 16.Dezember 1917 in der Grafschaft Somerset im Südwesten Englands geboren. Von 1927 bis 1936 besuchte er die Huish's Grammar School in Taunton/Somerset und las bereits als Jugendlicher die Werke von H. G. Wells und Olaf Stapledon. Da Clarke aus finanziellen Gründen ein Studium zunächst verwehr blieb, ging er 1936 nach London und arbeitete dort zunächst im Staatsdienst. 1941 trat er als Radaroffizier in die Royal Air Force ein. Diese Erfahrungen liegen dem Roman Glide Path zugrunde. Seine Idee, geostationäre Satelliten zur technischen Kommunikation zu nutzen, die er 1945 unter dem Titel Extra-terrestrial Relays – Can Rocket Stations Give World- wide Radio Coverage? in der wissenschaftlichen Zeitschrift Wireless World veröffentlichte, erlebte 1964 mit dem Saetelliten Syncom 3 ihre Verwirklichung. Ihm zu Ehren wird daher der geostationäre Orbit auch „Clarke Belt“ beziehungsweise „Clarke Orbit“ genannt. Von 1946 bis 1948 studierte er Mathematik und Physik am Londoner King's College. -
Exomars 2016
University of California, Davis Department of Mechanical and Aerospace Engineering ExoMars 2016 Critical Design Review Final Report David Bartolo Shazib Elahi Aaron Tun Junyi Zhang EAE 198: Intro to Space Vehicles Professor S. K. Robinson 3/23/2019 Contents 1. Introduction 4 1.1 ExoMars 2016 Overview 4 1.1.1 ExoMars Program Vision 4 1.1.2 Timeline of Events 6 1.1.3 Spacecraft and Launch Vehicle Specifications 6 1.2 ExoMars 2016 Mission Stakeholders and Requirements 7 1.3 Mission Objectives 7 1.3.1 Trace Gas Orbiter 7 1.3.2 Schiaparelli EDM 7 1.4 Concept of Operations 8 1.4.1 Space Segment 8 1.4.2 Ground Segment 9 1.5 Subsystems 10 1.5.1 Trace Gas Orbiter 10 1.5.2 Schiaparelli EDM 11 2. Background 12 2.1 Similar Spacecraft 13 2.1.1 Trace Gas Orbiter 13 2.1.2 Schiaparelli EDM 13 2.2 ExoMars 2016 Innovations 13 3. Modifications to Design 14 3.1 Functional Hierarchy Diagram, Analysis/Modification Requirements 14 3.2 Rationale for Chosen Requirements, Potential Benefits and Downsides 15 3.3 Modified Subsystem Requirements 16 4. Analyses 17 4.1 Major Analysis: Power 17 4.1.1 Goals of Analysis 17 4.1.2 Assumptions, Principles, and Methods 17 4.1.2.1 Power Generation and Sources 17 4.1.2.3 Power Regulation and Control 18 4.1.2.4 Power Regulators 19 4.1.2.5 Power Distribution and Heat Dissipation 19 4.1.3 Math, Models, and Code 19 4.1.3.1 Power Generation and Sources 19 2 4.1.3.2 Power Energy Storage 21 4.1.3.3 Power Regulation and Control 21 4.1.3.5 Power Distribution and Heat Dissipation 22 4.1.4 Results 22 4.1.5 Discussion of Importance of Results 26 4.2 Minor Analysis I: Deployable Array Design 26 4.2.1 Goals of Analysis 26 4.2.2 Assumptions, Principles, and Methods 26 4.2.3 Math, Models, and Code 29 4.2.4 Results 32 4.2.5 Discussion of Importance of Results 35 4.3 Minor Analysis II: Influence of Adding Solar Array on Lander 36 4.3.1 Goals of Analysis 36 4.3.2 Assumptions, Principles, and Methods 37 4.3.3 Math, Models, and Code 38 4.3.4 Results 42 4.3.5 Discussion 43 5. -
Multisatellite Determination of the Relativistic Electron Phase Space Density at Geosynchronous Orbit: Methodology and Results During Geomagnetically Quiet Times Y
JOURNAL OF GEOPHYSICAL RESEARCH, VOL. 110, A10210, doi:10.1029/2004JA010895, 2005 Multisatellite determination of the relativistic electron phase space density at geosynchronous orbit: Methodology and results during geomagnetically quiet times Y. Chen, R. H. W. Friedel, and G. D. Reeves Los Alamos National Laboratory, Los Alamos, New Mexico, USA T. G. Onsager NOAA, Boulder, Colorado, USA M. F. Thomsen Los Alamos National Laboratory, Los Alamos, New Mexico, USA Received 10 November 2004; revised 20 May 2005; accepted 8 July 2005; published 20 October 2005. [1] We develop and test a methodology to determine the relativistic electron phase space density distribution in the vicinity of geostationary orbit by making use of the pitch-angle resolved energetic electron data from three Los Alamos National Laboratory geosynchronous Synchronous Orbit Particle Analyzer instruments and magnetic field measurements from two GOES satellites. Owing to the Earth’s dipole tilt and drift shell splitting for different pitch angles, each satellite samples a different range of Roederer L* throughout its orbit. We use existing empirical magnetic field models and the measured pitch-angle resolved electron spectra to determine the phase space density as a function of the three adiabatic invariants at each spacecraft. Comparing all satellite measurements provides a determination of the global phase space density gradient over the range L* 6–7. We investigate the sensitivity of this method to the choice of the magnetic field model and the fidelity of the instrument intercalibration in order to both understand and mitigate possible error sources. Results for magnetically quiet periods show that the radial slopes of the density distribution at low energy are positive, while at high energy the slopes are negative, which confirms the results from some earlier studies of this type. -
Positioning: Drift Orbit and Station Acquisition
Orbits Supplement GEOSTATIONARY ORBIT PERTURBATIONS INFLUENCE OF ASPHERICITY OF THE EARTH: The gravitational potential of the Earth is no longer µ/r, but varies with longitude. A tangential acceleration is created, depending on the longitudinal location of the satellite, with four points of stable equilibrium: two stable equilibrium points (L 75° E, 105° W) two unstable equilibrium points ( 15° W, 162° E) This tangential acceleration causes a drift of the satellite longitude. Longitudinal drift d'/dt in terms of the longitude about a point of stable equilibrium expresses as: (d/dt)2 - k cos 2 = constant Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF EARTH ASPHERICITY VARIATION IN THE LONGITUDINAL ACCELERATION OF A GEOSTATIONARY SATELLITE: Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF SUN & MOON ATTRACTION Gravitational attraction by the sun and moon causes the satellite orbital inclination to change with time. The evolution of the inclination vector is mainly a combination of variations: period 13.66 days with 0.0035° amplitude period 182.65 days with 0.023° amplitude long term drift The long term drift is given by: -4 dix/dt = H = (-3.6 sin M) 10 ° /day -4 diy/dt = K = (23.4 +.2.7 cos M) 10 °/day where M is the moon ascending node longitude: M = 12.111 -0.052954 T (T: days from 1/1/1950) 2 2 2 2 cos d = H / (H + K ); i/t = (H + K ) Depending on time within the 18 year period of M d varies from 81.1° to 98.9° i/t varies from 0.75°/year to 0.95°/year Orbits Supplement GEO PERTURBATIONS (CONT'D) INFLUENCE OF SUN RADIATION PRESSURE Due to sun radiation pressure, eccentricity arises: EFFECT OF NON-ZERO ECCENTRICITY L = difference between longitude of geostationary satellite and geosynchronous satellite (24 hour period orbit with e0) With non-zero eccentricity the satellite track undergoes a periodic motion about the subsatellite point at perigee. -
Highlights in Space 2010
International Astronautical Federation Committee on Space Research International Institute of Space Law 94 bis, Avenue de Suffren c/o CNES 94 bis, Avenue de Suffren UNITED NATIONS 75015 Paris, France 2 place Maurice Quentin 75015 Paris, France Tel: +33 1 45 67 42 60 Fax: +33 1 42 73 21 20 Tel. + 33 1 44 76 75 10 E-mail: : [email protected] E-mail: [email protected] Fax. + 33 1 44 76 74 37 URL: www.iislweb.com OFFICE FOR OUTER SPACE AFFAIRS URL: www.iafastro.com E-mail: [email protected] URL : http://cosparhq.cnes.fr Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law The United Nations Office for Outer Space Affairs is responsible for promoting international cooperation in the peaceful uses of outer space and assisting developing countries in using space science and technology. United Nations Office for Outer Space Affairs P. O. Box 500, 1400 Vienna, Austria Tel: (+43-1) 26060-4950 Fax: (+43-1) 26060-5830 E-mail: [email protected] URL: www.unoosa.org United Nations publication Printed in Austria USD 15 Sales No. E.11.I.3 ISBN 978-92-1-101236-1 ST/SPACE/57 *1180239* V.11-80239—January 2011—775 UNITED NATIONS OFFICE FOR OUTER SPACE AFFAIRS UNITED NATIONS OFFICE AT VIENNA Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law Progress in space science, technology and applications, international cooperation and space law UNITED NATIONS New York, 2011 UniTEd NationS PUblication Sales no. -
An Introduction to Rockets -Or- Never Leave Geeks Unsupervised
An Introduction to Rockets -or- Never Leave Geeks Unsupervised Kevin Mellett 27 Apr 2006 2 What is a Rocket? • A propulsion system that contains both oxidizer and fuel • NOT a jet, which requires air for O2 3 A Brief History • 400 BC – Steam Bird • 100 BC – Hero Engine • 100 AD – Gunpowder Invented in China – Celebrations – Religious Ceremonies – Bamboo Misfires? 4 A Brief History • Chinese Invent Fire Arrows 13th c – First True Rockets •16th c Wan-Hu – 47 Rockets 5 A Brief History •13th –16th c Improvements in Technology – English Improved Gunpowder – French Improved Guidance by Shooting Through a Tube “Bazooka Style” – Germans Invented “Step Rockets” (Staging) 6 A Brief History • 1687 Newton Publishes Principia Mathematica 7 Newton’s Third Law MOMENTUM is the key concept of rocketry 8 A Brief History • 1903 KonstantineTsiolkovsky Publishes the “Rocket Equation” – Proposes Liquid Fuel ⎛ Mi ⎞ V = Ve*ln⎜ ⎟ ⎝ Mf ⎠ 9 A Brief History • Goddard Flies the First Liquid Fueled Rocket on 16 Mar 1926 – Theorized Rockets Would Work in a Vacuum – NY Times: Goddard “…lacks the basic physics ladeled out in our high schools…” 10 A Brief History • Germans at Peenemunde – Oberth and von Braun lead development of the V-2 – Amazing achievement, but too late to change the tide of WWII – After WWII, USSR and USA took German Engineers and Hardware 11 Mission Requirements • Launch On Need – No Time for Complex Pre-Launch Preps – Long Shelf Life • Commercial / Government – Risk Tolerance –R&D Costs 12 Mission Requirements • Payload Mass and Orbital Objectives – How much do you need, and where do you want it? Both drive energy requirements. -
Richard Dalbello Vice President, Legal and Government Affairs Intelsat General
Commercial Management of the Space Environment Richard DalBello Vice President, Legal and Government Affairs Intelsat General The commercial satellite industry has billions of dollars of assets in space and relies on this unique environment for the development and growth of its business. As a result, safety and the sustainment of the space environment are two of the satellite industry‘s highest priorities. In this paper I would like to provide a quick survey of past and current industry space traffic control practices and to discuss a few key initiatives that the industry is developing in this area. Background The commercial satellite industry has been providing essential space services for almost as long as humans have been exploring space. Over the decades, this industry has played an active role in developing technology, worked collaboratively to set standards, and partnered with government to develop successful international regulatory regimes. Success in both commercial and government space programs has meant that new demands are being placed on the space environment. This has resulted in orbital crowding, an increase in space debris, and greater demand for limited frequency resources. The successful management of these issues will require a strong partnership between government and industry and the careful, experience-based expansion of international law and diplomacy. Throughout the years, the satellite industry has never taken for granted the remarkable environment in which it works. Industry has invested heavily in technology and sought out the best and brightest minds to allow the full, but sustainable exploitation of the space environment. Where problems have arisen, such as space debris or electronic interference, industry has taken 1 the initiative to deploy new technologies and adopt new practices to minimize negative consequences.