Mars 2020 Perseverance Launch Press Kit
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Heraldry in the Republic of Macedonia (1991-2019)
Preprints (www.preprints.org) | NOT PEER-REVIEWED | Posted: 1 September 2021 doi:10.20944/preprints202109.0027.v1 Article Heraldry in the Republic of Macedonia (1991-2019) Jovan Jonovski1, * 1 Macedonian Heraldic Society; [email protected] * Correspondence: [email protected]; Tel.: +38970252989 Abstract: Every country has some specific heraldry. In this paper, we will consider heraldry in the Republic of Macedonia, understood by the multitude of coats of arms, and armorial knowledge and art. The paper covers the period from independence until the name change (1991-2019). It co- vers the state coat of arms of the Republic of Macedonia especially the 2009 change. Special atten- tion is given to the development of the municipal heraldry, including the legal system covering the subject. Also personal heraldry developed in 21 century is considered. The paper covers the de- velopment of heraldry and the heraldic thought in the given period, including the role of the Macedonian Heraldic Society and its journal Macedonian Herald in development of theoretic and practical heraldry, as well as its Register of arms and the Macedonian Civic Heraldic System. Keywords: Heraldry in Macedonia; Macedonian civic heraldry; Republic of Macedonia. 1. Introduction The Republic of Macedonia became independent from the Socialist Federative Re- public of Yugoslavia with the Referendum of 8 September 1991. The Democratic Federal Macedonia was formed during the first session of the Anti-Fascist Assembly for the Na- tional Liberation of Macedonia (ASNOM) on 2 August 1944 (it later became the People’s Republic of Macedonia, a federal unit of the Federal People’s Republic of Yugoslavia). -
Lara (Lander Radioscience) on the Exomars 2020 Surface Platform
EPSC Abstracts Vol. 13, EPSC-DPS2019-891-1, 2019 EPSC-DPS Joint Meeting 2019 c Author(s) 2019. CC Attribution 4.0 license. LaRa (Lander Radioscience) on the ExoMars 2020 Surface Platform. Véronique Dehant1,2, Sébastien Le Maistre1, Rose-Marie Baland1, Özgür Karatekin1, Marie-Julie Péters1, Attilio Rivoldini1, Tim Van Hoolst1, Bart Van Hove1, Marie Yseboodt1, and Alexander Kosov3 (1) Royal Observatory of Belgium (ROB), Brussels, Belgium, (2) Université catholique de Louvain, Louvain-la-Neuve, Belgium, (3) Space Research Institute Russian Academy of Sciences (IKI), Moscow, Russia Abstract The surface platform Kazachok will house the radio science experiment LaRa (Lander Radioscience) to support specific scientific objectives of the ExoMars 2020 mission. The LaRa experiment is described and the scientific objectives and strategies are detailed in this presentation. Figure 1. LaRa principle. 1. Introduction 2. The LaRa instrument In the last decade, several missions and observations As LaRa performs a coherent retransmission of the have brought new data on the planet Mars, obtained uplink carrier to the downlink carrier, the downlink by either spacecraft orbiting around Mars or landers frequency is scaled by a constant multiplier, the and rovers on the surface. Among other things, the transponder ratio (880/749). By emitting the uplink information acquired will improve our understanding signal from Earth, the masers in the ground stations of Mars’ interior, evolution and habitability. Data ensure frequency stability of LaRa’s radiosignal. obtained by new space missions are driving further The LaRa instrument is built in collaboration with progress in this field. In 2020, the European Space other Belgian actors under the lead of ESA PRODEX, Agency ESA and the Russian space agency and ROB providing the instrument specifications. -
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. -
Exomars Schiaparelli Direct-To-Earth Observation Using GMRT
TECHNICAL ExoMars Schiaparelli Direct-to-Earth Observation REPORTS: METHODS 10.1029/2018RS006707 using GMRT S. Esterhuizen1, S. W. Asmar1 ,K.De2, Y. Gupta3, S. N. Katore3, and B. Ajithkumar3 Key Point: • During ExoMars Landing, GMRT 1Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA, USA, 2Cahill Center for Astrophysics, observed UHF transmissions and California Institute of Technology, Pasadena, CA, USA, 3National Centre for Radio Astrophysics, Pune, India Doppler shift used to identify key events as only real-time aliveness indicator Abstract During the ExoMars Schiaparelli separation event on 16 October 2016 and Entry, Descent, and Landing (EDL) events 3 days later, the Giant Metrewave Radio Telescope (GMRT) near Pune, India, Correspondence to: S. W. Asmar, was used to directly observe UHF transmissions from the Schiaparelli lander as they arrive at Earth. The [email protected] Doppler shift of the carrier frequency was measured and used as a diagnostic to identify key events during EDL. This signal detection at GMRT was the only real-time aliveness indicator to European Space Agency Citation: mission operations during the critical EDL stage of the mission. Esterhuizen, S., Asmar, S. W., De, K., Gupta, Y., Katore, S. N., & Plain Language Summary When planetary missions, such as landers on the surface of Mars, Ajithkumar, B. (2019). ExoMars undergo critical and risky events, communications to ground controllers is very important as close to real Schiaparelli Direct-to-Earth observation using GMRT. time as possible. The Schiaparelli spacecraft attempted landing in 2016 was supported in an innovative way. Radio Science, 54, 314–325. A large radio telescope on Earth was able to eavesdrop on information being sent from the lander to other https://doi.org/10.1029/2018RS006707 spacecraft in orbit around Mars. -
Emirates Mars Mission Countdown Starts
Received by NSD/FARA Registration Unit 07/06/2020 5:05:13 PM Emirates Mars Mission Countdown Starts Mors Hope Probe to Launch in 10 Days Abu Dhabi, United Arab Emirates, 6 July 2020 - The Emirates Mars Mission, the first interplanetary exploration undertaken by an Arab nation, today confirmed the launch of its Mars Hope Probe in 10 days - on the 15 July 2020 at 5.51am (JST) / 14 July 2020 at 4:51am (EST) from Tanegashima Space Center in Kagoshima Prefecture, southwestern Japan, on a Mitsubishi MH-IIA rocket. The launch will be livestreamed at http://www.emm.ae/live. The Emirates Mars Mission (EMM) will send the Mars Hope probe on a 495,000,000km journey to reach and orbit the Red Planet in February 2021. Hope aims to build the first full picture of Mars' climate throughout the Martian year. "The launch of Mars Hope comes at the end of a six-year journey of development by the team at the Mohammed bin Rashid Space Centre, an accelerated time frame by interplanetary mission standards. The team has overcome remarkable challenges, not least those presented by the Covid-19 pandemic, but we're all good to go now," said Omran Sharaf, EMM Mission Lead. EMM and the Hope probe are the culmination of a knowledge transfer and development effort started in 2006, which has seen Emirati engineers working with partners around the world to develop the UAE's spacecraft design, engineering and manufacturing capabilities. It is part of a long-term integrated effort to create economic opportunity around leadership in space sciences, research and exploration. -
The Mystery of Methane on Mars and Titan
The Mystery of Methane on Mars & Titan By Sushil K. Atreya MARS has long been thought of as a possible abode of life. The discovery of methane in its atmosphere has rekindled those visions. The visible face of Mars looks nearly static, apart from a few wispy clouds (white). But the methane hints at a beehive of biological or geochemical activity underground. Of all the planets in the solar system other than Earth, own way, revealing either that we are not alone in the universe Mars has arguably the greatest potential for life, either extinct or that both Mars and Titan harbor large underground bodies or extant. It resembles Earth in so many ways: its formation of water together with unexpected levels of geochemical activ- process, its early climate history, its reservoirs of water, its vol- ity. Understanding the origin and fate of methane on these bod- canoes and other geologic processes. Microorganisms would fit ies will provide crucial clues to the processes that shape the right in. Another planetary body, Saturn’s largest moon Titan, formation, evolution and habitability of terrestrial worlds in also routinely comes up in discussions of extraterrestrial biology. this solar system and possibly in others. In its primordial past, Titan possessed conditions conducive to Methane (CH4) is abundant on the giant planets—Jupiter, the formation of molecular precursors of life, and some scientists Saturn, Uranus and Neptune—where it was the product of chem- believe it may have been alive then and might even be alive now. ical processing of primordial solar nebula material. On Earth, To add intrigue to these possibilities, astronomers studying though, methane is special. -
Terrestrial Impact Structures Provide the Only Ground Truth Against Which Computational and Experimental Results Can Be Com Pared
Ann. Rev. Earth Planet. Sci. 1987. 15:245-70 Copyright([;; /987 by Annual Reviews Inc. All rights reserved TERRESTRIAL IMI!ACT STRUCTURES ··- Richard A. F. Grieve Geophysics Division, Geological Survey of Canada, Ottawa, Ontario KIA OY3, Canada INTRODUCTION Impact structures are the dominant landform on planets that have retained portions of their earliest crust. The present surface of the Earth, however, has comparatively few recognized impact structures. This is due to its relative youthfulness and the dynamic nature of the terrestrial geosphere, both of which serve to obscure and remove the impact record. Although not generally viewed as an important terrestrial (as opposed to planetary) geologic process, the role of impact in Earth evolution is now receiving mounting consideration. For example, large-scale impact events may hav~~ been responsible for such phenomena as the formation of the Earth's moon and certain mass extinctions in the biologic record. The importance of the terrestrial impact record is greater than the relatively small number of known structures would indicate. Impact is a highly transient, high-energy event. It is inherently difficult to study through experimentation because of the problem of scale. In addition, sophisticated finite-element code calculations of impact cratering are gen erally limited to relatively early-time phenomena as a result of high com putational costs. Terrestrial impact structures provide the only ground truth against which computational and experimental results can be com pared. These structures provide information on aspects of the third dimen sion, the pre- and postimpact distribution of target lithologies, and the nature of the lithologic and mineralogic changes produced by the passage of a shock wave. -
Outline of Aurora Funding
Outline of Aurora funding The £3 million from the Aurora Science Programme has gone to the following 17 academics and individual scientists working at UK research organisations: 1. An improved understanding of Mars photochemistry using NOMAD and ACS measurements – Professor Paul Palmer, Edinburgh University - £73,442 The proposal aims to develop the existing photochemistry (the chemistry effects of light) to prepare for measurements collected by the NOMAD and ACS instruments aboard the Trace Gas Orbiter. They will develop the chemical mechanism so it can be used to interpret observed variations of atmospheric gases on Mars. 2. Dust storms and the dust transport cycle: their impact on the Martian climate in a multi annual reanalysis of MCS, THEMIS and TGO/ACS data – Professor Peter Read, Oxford University - £346,592 The proposal aims to improve our understanding of the Martian dust cycle, its impact on climate and the physical features of the Martian surface. Using a new approach towards analysing daily variations in the Martian atmosphere it is proposed to extend this dataset using measurements of the Martian atmosphere from the Mars Reconnaissance Orbiter and Mars Odyssey missions in orbit around Mars, and from the Atmospheric Chemistry Suite (ACS) on ESA's Trace Gas Orbiter mission when they become available. This may be useful for future spacecraft operations at the Martian surface, as well as to improve our understanding of both the present and past states of the Martian climate. 3. ExoMars TGO Guest Investigator Support – Dr Matt Balme, Open University - £56,367 This proposal seeks funding for a Guest Investigator position on ESA's ExoMars Trace Gas Orbiter mission. -
Deep Space 2: the Mars Microprobe Project and Beyond
First International Conference on Mars Polar Science 3039.pdf DEEP SPACE 2: THE MARS MICROPROBE PROJECT AND BEYOND. S. E. Smrekar and S. A. Gavit, Mail Stop 183-501, Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Drive, Pasa- dena CA 91109, USA ([email protected]). Mission Overview: The Mars Microprobe Proj- System Design, Technologies, and Instruments: ect, or Deep Space 2 (DS2), is the second of the New Telecommunications. The DS2 telecom system, Millennium Program planetary missions and is de- which is mounted on the aftbody electronics plate, signed to enable future space science network mis- relays data back to earth via the Mars Global Surveyor sions through flight validation of new technologies. A spacecraft which passes overhead approximately once secondary goal is the collection of meaningful science every 2 hours. The receiver and transmitter operate in data. Two micropenetrators will be deployed to carry the Ultraviolet Frequency Range (UHF) and data is out surface and subsurface science. returned at a rate of 7 Kbits/second. The penetrators are being carried as a piggyback Ultra-low-temperature lithium primary battery. payload on the Mars Polar Lander cruise ring and will One challenging aspect of the microprobe design is be launched in January of 1999. The Microprobe has the thermal environment. The batteries are likely to no active control, attitude determination, or propulsive stay no warmer than -78° C. A lithium-thionyl pri- systems. It is a single stage from separation until mary battery was developed to survive the extreme landing and will passively orient itself due to its aero- temperature, with a 6 to 14 V range and a 3-year shelf dynamic design (Fig. -
Aerothermodynamic Design of the Mars Science Laboratory Heatshield
Aerothermodynamic Design of the Mars Science Laboratory Heatshield Karl T. Edquist∗ and Artem A. Dyakonovy NASA Langley Research Center, Hampton, Virginia, 23681 Michael J. Wrightz and Chun Y. Tangx NASA Ames Research Center, Moffett Field, California, 94035 Aerothermodynamic design environments are presented for the Mars Science Labora- tory entry capsule heatshield. The design conditions are based on Navier-Stokes flowfield simulations on shallow (maximum total heat load) and steep (maximum heat flux, shear stress, and pressure) entry trajectories from a 2009 launch. Boundary layer transition is expected prior to peak heat flux, a first for Mars entry, and the heatshield environments were defined for a fully-turbulent heat pulse. The effects of distributed surface roughness on turbulent heat flux and shear stress peaks are included using empirical correlations. Additional biases and uncertainties are based on computational model comparisons with experimental data and sensitivity studies. The peak design conditions are 197 W=cm2 for heat flux, 471 P a for shear stress, 0.371 Earth atm for pressure, and 5477 J=cm2 for total heat load. Time-varying conditions at fixed heatshield locations were generated for thermal protection system analysis and flight instrumentation development. Finally, the aerother- modynamic effects of delaying launch until 2011 are previewed. Nomenclature 1 2 2 A reference area, 4 πD (m ) CD drag coefficient, D=q1A D aeroshell diameter (m) 2 Dim multi-component diffusion coefficient (m =s) ci species mass fraction H total enthalpy -
Atmospheric Dust on Mars: a Review
47th International Conference on Environmental Systems ICES-2017-175 16-20 July 2017, Charleston, South Carolina Atmospheric Dust on Mars: A Review François Forget1 Laboratoire de Météorologie Dynamique (LMD/IPSL), Sorbonne Universités, UPMC Univ Paris 06, PSL Research University, Ecole Normale Supérieure, Université Paris-Saclay, Ecole Polytechnique, CNRS, Paris, France Luca Montabone2 Laboratoire de Météorologie Dynamique (LMD/IPSL), Paris, France & Space Science Institute, Boulder, CO, USA The Martian environment is characterized by airborne mineral dust extending between the surface and up to 80 km altitude. This dust plays a key role in the climate system and in the atmospheric variability. It is a significant issue for any system on the surface. The atmospheric dust content is highly variable in space and time. In the past 20 years, many investigations have been conducted to better understand the characteristics of the dust particles, their distribution and their variability. However, many unknowns remain. The occurrence of local, regional and global-scale dust storms are better documented and modeled, but they remain very difficult to predict. The vertical distribution of dust, characterized by detached layers exhibiting large diurnal and seasonal variations, remains quite enigmatic and very poorly modeled. Nomenclature Ls = Solar Longitude (°) MY = Martian year reff = Effective radius τ = Dust optical depth (or dust opacity) CDOD = Column Dust Optical Depth (i.e. τ integrated over the atmospheric column) IR = Infrared LDL = Low Dust Loading (season) HDL = High Dust Loading (season) MGS = Mars Global Surveyor (NASA spacecraft) MRO = Mars Reconnaissance Orbiter (NASA spacecraft) MEX = Mars Express (ESA spacecraft) TES = Thermal Emission Spectrometer (instrument aboard MGS) THEMIS = Thermal Emission Imaging System (instrument aboard NASA Mars Odyssey spacecraft) MCS = Mars Climate Sounder (instrument aboard MRO) PDS = Planetary Data System (NASA data archive) EDL = Entry, Descending, and Landing GCM = Global Climate Model I. -
The Minor Planet Bulletin
THE MINOR PLANET BULLETIN OF THE MINOR PLANETS SECTION OF THE BULLETIN ASSOCIATION OF LUNAR AND PLANETARY OBSERVERS VOLUME 36, NUMBER 3, A.D. 2009 JULY-SEPTEMBER 77. PHOTOMETRIC MEASUREMENTS OF 343 OSTARA Our data can be obtained from http://www.uwec.edu/physics/ AND OTHER ASTEROIDS AT HOBBS OBSERVATORY asteroid/. Lyle Ford, George Stecher, Kayla Lorenzen, and Cole Cook Acknowledgements Department of Physics and Astronomy University of Wisconsin-Eau Claire We thank the Theodore Dunham Fund for Astrophysics, the Eau Claire, WI 54702-4004 National Science Foundation (award number 0519006), the [email protected] University of Wisconsin-Eau Claire Office of Research and Sponsored Programs, and the University of Wisconsin-Eau Claire (Received: 2009 Feb 11) Blugold Fellow and McNair programs for financial support. References We observed 343 Ostara on 2008 October 4 and obtained R and V standard magnitudes. The period was Binzel, R.P. (1987). “A Photoelectric Survey of 130 Asteroids”, found to be significantly greater than the previously Icarus 72, 135-208. reported value of 6.42 hours. Measurements of 2660 Wasserman and (17010) 1999 CQ72 made on 2008 Stecher, G.J., Ford, L.A., and Elbert, J.D. (1999). “Equipping a March 25 are also reported. 0.6 Meter Alt-Azimuth Telescope for Photometry”, IAPPP Comm, 76, 68-74. We made R band and V band photometric measurements of 343 Warner, B.D. (2006). A Practical Guide to Lightcurve Photometry Ostara on 2008 October 4 using the 0.6 m “Air Force” Telescope and Analysis. Springer, New York, NY. located at Hobbs Observatory (MPC code 750) near Fall Creek, Wisconsin.