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Orbital Lifetime Predictions
Orbital LIFETIME PREDICTIONS An ASSESSMENT OF model-based BALLISTIC COEFfiCIENT ESTIMATIONS AND ADJUSTMENT FOR TEMPORAL DRAG co- EFfiCIENT VARIATIONS M.R. HaneVEER MSc Thesis Aerospace Engineering Orbital lifetime predictions An assessment of model-based ballistic coecient estimations and adjustment for temporal drag coecient variations by M.R. Haneveer to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Thursday June 1, 2017 at 14:00 PM. Student number: 4077334 Project duration: September 1, 2016 – June 1, 2017 Thesis committee: Dr. ir. E. N. Doornbos, TU Delft, supervisor Dr. ir. E. J. O. Schrama, TU Delft ir. K. J. Cowan MBA TU Delft An electronic version of this thesis is available at http://repository.tudelft.nl/. Summary Objects in Low Earth Orbit (LEO) experience low levels of drag due to the interaction with the outer layers of Earth’s atmosphere. The atmospheric drag reduces the velocity of the object, resulting in a gradual decrease in altitude. With each decayed kilometer the object enters denser portions of the atmosphere accelerating the orbit decay until eventually the object cannot sustain a stable orbit anymore and either crashes onto Earth’s surface or burns up in its atmosphere. The capability of predicting the time an object stays in orbit, whether that object is space junk or a satellite, allows for an estimate of its orbital lifetime - an estimate satellite op- erators work with to schedule science missions and commercial services, as well as use to prove compliance with international agreements stating no passively controlled object is to orbit in LEO longer than 25 years. -
China's Space Program
China’s Space Program An Introduction China’s Space Program ● Motivations ● Organization ● Programs ○ Satellites ○ Manned Space flight ○ Lunar Exploration Program ○ International Relations ● Summary China’s Space Program Motivations Stated Purpose ● Explore outer space and to enhance understanding of the Earth and the cosmos ● Utilize outer space for peaceful purposes, promote human civilization and social progress, and to benefit the whole of mankind ● Meet the demands of economic development, scientific and technological development, national security and social progress ● Improve the scientific and cultural knowledge of the Chinese people ● Protect China's national rights and interests ● Build up China’s national comprehensive strength National Space Motivations • Preservation of its political system is overriding goal • The CCP prioritizes investments into space technology ○ Establish PRC as an equal among world powers ○ Space for international competition and cooperation ○ Manned spaceflight ● Foster national pride ● Enhance the domestic and international legitimacy of the CCP. ○ Space technology is metric of political legitimacy, national power, and status globally China’s Space Program Organization The China National Space Administration (CNSA) ● The China National Space Administration (CNSA, GuóJiā HángTiān Jú,) ○ National space agency of the People's Republic of China ○ Responsible for the national space program. ■ Planning and development of space activities. The China National Space Administration ● CNSA and China Aerospace -
Cubesat Data Analysis Revision
371-XXXXX Revision - CubeSat Data Analysis Revision - November 2015 Prepared by: GSFC/Code 371 National Aeronautics and Goddard Space Flight Center Space Administration Greenbelt, Maryland 20771 371-XXXXX Revision - Signature Page Prepared by: ___________________ _____ Mark Kaminskiy Date Reliability Engineer ARES Corporation Accepted by: _______________________ _____ Nasir Kashem Date Reliability Lead NASA/GSFC Code 371 1 371-XXXXX Revision - DOCUMENT CHANGE RECORD REV DATE DESCRIPTION OF CHANGE LEVEL APPROVED - Baseline Release 2 371-XXXXX Revision - Table of Contents 1 Introduction 4 2 Statement of Work 5 3 Database 5 4 Distributions by Satellite Classes, Users, Mass, and Volume 7 4.1 Distribution by satellite classes 7 4.2 Distribution by satellite users 8 4.3 CubeSat Distribution by mass 8 4.4 CubeSat Distribution by volume 8 5 Annual Number of CubeSats Launched 9 6 Reliability Data Analysis 10 6.1 Introducing “Time to Event” variable 10 6.2 Probability of a Successful Launch 10 6.3 Estimation of Probability of Mission Success after Successful Launch. Kaplan-Meier Nonparametric Estimate and Weibull Distribution. 10 6.3.1 Kaplan-Meier Estimate 10 6.3.2 Weibull Distribution Estimation 11 6.4 Estimation of Probability of mission success after successful launch as a function of time and satellite mass using Weibull Regression 13 6.4.1 Weibull Regression 13 6.4.2 Data used for estimation of the model parameters 13 6.4.3 Comparison of the Kaplan-Meier estimates of the Reliability function and the estimates based on the Weibull regression 16 7 Conclusion 17 8 Acknowledgement 18 9 References 18 10 Appendix 19 Table of Figures Figure 4-1 CubeSats distribution by mass .................................................................................................... -
The 2009 Mars Telecom Orbier Mission
The 2009 Mars Telecom Orbiter Mission1,2 Stephen F. Franklina, John P. Slonski, Jr.a, Stuart Kerridgea, Gary Noreena, Joseph E. Riedela, Tom Komareka, Dorothy Stosica, Caroline Rachoa, Bernard Edwardsb, Don Borosonc a-Jet Propulsion Laboratory, California Institute of Technology; Pasadena, Ca. 91109; b-NASA Goddard Spaceflight Center, Greenbelt, Md. 20771 USA c-MIT-Lincoln Laboratory, Lexington, Ma, 02420 Abstract—This paper provides an overview of the Mars Mission and flight system requirements have been written. Telecom Orbiter (MTO) mission, and is an update to the The flight system requirements define the flight system paper presented at last year’s conference. Launched in performance and functionality to the competing system 2009, MTO will provide Mars-to-Earth relay services for contract proposers. NASA missions arriving at Mars between 2010 and 2020, enabling far higher science data return and lowering the A Rendezvous and Autonomous Navigation (RAN) telecom and operations costs for these missions. MTO demonstration has been added. An orbiting sample canister carries an optical communications payload, which will will be released and tracked by the ground using on-board demonstrate downlink bit rates from 1 Mbps up to and cameras. The spacecraft will then rendezvous with the possibly exceeding 30 Mbps. MTO will also demonstrate canister using its autonomous navigation capability, coming the ability to autonomously navigate, and to search for and to within ten meters of (but not capturing) the canister. This rendezvous with an orbiting sample, in preparation for operation demonstrates capabilities that the proposed NASA NASA’s proposed Mars Sample Return Mission. A to-be- Mars Sample Return orbiter will require to capture the Mars defined science instrument will also be carried. -
Mission Overview
CRS Orb-1 Mission Mission Overview Overview Under the Commercial Resupply Services (CRS) contract with NASA, Orbital will provide approximately 20 metric tons of cargo to the International Space Station over the course of eight missions. Orb-1 is the first of those missions. The Orb-1 mission builds on the successful Commercial Orbital Transportation Services (COTS) demonstration mission conducted from September 18 to October 23, 2013. The Orb-1 flight will carry substantially more cargo (1465 kg vs. 700 kg) than the COTS mission, including several time-sensitive payloads and Cygnus’ first powered payload, the Commercial Generic Bioprocessing Apparatus (CGBA) from Bioserve. Mission Overview, Cont. Antares® The configuration of the Antares launch vehicle for the Orb-1 Mission is much the same as the two previous Antares flights with a CASTOR 30B second stage motor instead of the CASTOR 30 used previously. The first stage includes a core that contains the tanks for the liquid oxygen and kerosene, the first stage avionics, and two AJ26 rocket engines. The second stage consists of the CASTOR® 30B solid rocket motor, an avionics section containing the flight computer and guidance/ navigation/control functions, an interstage that connects the solid rocket motor to the first stage, the Cygnus spacecraft, and a fairing that encloses and protects the Cygnus spacecraft during ascent. Continued on Next Page Mission Overview, Cont. Cygnus™ The Cygnus spacecraft is composed of two elements, the Service Module (SM) and the Pressurized Cargo Module (PCM). The SM provides the propulsion, power, guidance, navigation and control, and other “housekeeping” services for the duration of the mission. -
7. Operations
7. Operations 7.1 Ground Operations The Exploration Systems Architecture Study (ESAS) team addressed the launch site integra- tion of the exploration systems. The team was fortunate to draw on expertise from members with historical and contemporary human space flight program experience including the Mercury, Gemini, Apollo, Skylab, Apollo Soyuz Test Project, Shuttle, and International Space Station (ISS) programs, as well as from members with ground operations experience reaching back to the Redstone, Jupiter, Pershing, and Titan launch vehicle programs. The team had a wealth of experience in both management and technical responsibilities and was able to draw on recent ground system concepts and other engineering products from the Orbital Space Plane (OSP) and Space Launch Initiative (SLI) programs, diverse X-vehicle projects, and leadership in NASA/Industry/Academia groups such as the Space Propulsion Synergy Team (SPST) and the Advanced Spaceport Technology Working Group (ASTWG). 7.1.1 Ground Operations Summary The physical and functional integration of the proposed exploration architecture elements will occur at the primary launch site at the NASA Kennedy Space Center (KSC). In order to support the ESAS recommendation of the use of a Shuttle-derived Cargo Launch Vehicle (CaLV) and a separate Crew Launch Vehicle (CLV) for lunar missions and the use of a CLV for ISS missions, KSC’s Launch Complex 39 facilities and ground equipment were selected for conversion. Ground-up replacement of the pads, assembly, refurbishment, and/or process- ing facilities was determined to be too costly and time-consuming to design, build, outfit, activate, and certify in a timely manner to support initial test flights leading to an operational CEV/CLV system by 2011. -
In This Issue
Vol. 38 No.12, September 2013 Editor: Jos Heyman FBIS In this issue: Satellite Update 4 Cancelled projects: Conestoga 5 News Ardusat 3 Arirang-5 7 Dnepr 1 7 Dream Chaser 7 Eutelsat and Satmex 2 Fermi 7 Gsat-14 7 HTV-4 3 iBall 3 Kepler 4 Orion 7 PicoDragon 3 Proton M 2 RCM 2 Russian EVAs 2 SARah 4 SGDC-1 4 SPRINT A 4 TechEdSat-3 3 WGS-6 4 HTV-4 Unpressurised Logistics Carrier with STP-H4 TIROS SPACE INFORMATION Eutelsat and Satmex 86 Barnevelder Bend, Southern River WA 6110, Australia Tel + 61 8 9398 1322 Eutelsat has acquired Mexico’s Satmex, a major communicaions satellite operator in the Latin (e-mail: [email protected]) American region. o o The Tiros Space Information (TSI) - News Bulletin is published to promote the scientific exploration and Satmex has currently three satellites in orbit at 113 W (Satmex-6), 114.9 W (Satmex-5) and commercial application of space through the dissemination of current news and historical facts. 116.8 oW (Satmex-8) and it can be expected that, once the acquisition has been completed, In doing so, Tiros Space Information continues the traditions of the Western Australian Branch of the these satellites will be renamed as part of the Eutelsat family. In addition Satmex has the Astronautical Society of Australia (1973-1975) and the Astronautical Society of Western Australia (ASWA) Satmex-7 and -9 satellites on order from Boeing. It is not clear whether these satellites will (1975-2006). remain on order. The News Bulletin can be received worldwide by e-mail subscription only. -
Chang'e 5 Samples (Mexag) (Head-Final)
Chang’E 5 Lunar Sample Return Mission Update James w. Head Department of Earth, Environmental and Planetary Sciences Brown University Providence, RI 02912 USA Extraterrestrial Materials Analysis Group (ExMAG) Spring Meeting: April 7 - 8, 2021. Extraterrestrial Materials Analysis Group (ExMAG) Spring Meeting Barbara Cohen, ExMAG Chair. 2/10/21 • 1. Please provide an update on the Chang'e 5 Sample Return Mission. • 2. What is known of the collection so far? • 3. Please provide an overview of allocation procedures. • 4. Since US federally-funded researchers cannot work directly with China - Who outside of China is working with the mission team? • 5. We'd also appreciate your thoughts on: What NASA might be able to do to enable the US analysis community to collaborate on this sample collection? Extraterrestrial Materials Analysis Group (ExMAG) Spring Meeting Barbara Cohen, ExMAG Chair. 2/10/21 • 1. Some Myths and Realities. • 2. Organization of the Chinese Space Program. • 3. Chinese Lunar Exploration Program (CLEP) context for Chang’e 5. • 4. Chang’e 5 Landing Site Selection, Global Context, Key Questions, Mission Operations and Sample Return. • 5. Returned Sample Location, Storage, Preliminary Analysis and Distribution. • 6. Opportunities for International Cooperation. Extraterrestrial Materials Analysis Group (ExMAG) Spring Meeting Barbara Cohen, ExMAG Chair. 2/10/21 • 1. Some Myths and Realities. • 2. Organization of the Chinese Space Program. • 3. Chinese Lunar Exploration Program (CLEP) context for Chang’e 5. • 4. Chang’e 5 Landing Site Selection, Global Context, Key Questions, Mission Operations and Sample Return. • 5. Returned Sample Location, Storage, Preliminary Analysis and Distribution. • 6. Opportunities for International Cooperation. -
Cubesat-Services.Pdf
Space• Space Station Station Cubesat CubesatDeployment Services Deployment Services NanoRacks Cubesat Deployer (NRCSD) • 51.6 degree inclination, 385-400 KM • Orbit lifetime 8-12 months • Deployment typically 1-3 months after berthing • Soft stowage internal ride several times per year Photo credit: NASA NRCSD • Each NRCSD can deploy up to 6U of CubeSats • 8 NRCSD’s per airlock cycle, for a total of 48U deployment capability • ~2 Air Lock cycles per mission Photo Credit: NanoRacks LLC Photo credit: NASA 2. Launched by ISS visiting vehicle 3. NRCSDs installed by ISS Crew 5. Grapple by JRMS 4. JEM Air Lock depress & slide 6. NRCSDs positioned by JRMS table extension 1. NRCSDs transported in CTBs 7. Deploy 8. JRMS return NRCSD-MPEP stack to slide table; 9. ISS Crew un-install first 8 NRCSDs; repeat Slide table retracts and pressurizes JEM air lock install/deploy for second set of NRCSDs NanoRacks Cubesat Mission (NR-CM 3 ) • Orbital Sciences CRS-1 (Launched Jan. 9, 2014) • Planet Labs Flock1A, 28 Doves • Lithuanian Space Assoc., LitSat-1 • Vilnius University & NPO IEP, LituanicaSat-1 • Nanosatisfi, ArduSat-2 • Southern Stars, SkyCube • University of Peru, UAPSat-1 Photo credit: NASA Mission Highlights Most CubeSats launched Two countries attain in a single mission space-faring status World’s largest remote Kickstarter funding sensing constellation • NR-CM3 • Orbital Science CRS-1, Launch Jan 9, 2014 • Air Lock Cycle 1, Feb 11-15, 2014 Dove CubeSats • Deployers 1-8 (all Planet Labs Doves) Photo credit: NASA • NR-CM3 • Orbital Science CRS-1, -
Starttabelle 2013 2013-01A 2013-01B 2013-01C 2013-02A 2013-02B 2013-03A 2013-04A NOA-01 2013-05A 2013-05B 2013-05C 2013-05D 2013-05E 2013-05F 2013-06A 2013-06B
Raumfahrer.net Starttabelle 2013 Bahnnähe Bahnferne Inklination LandLandLand bzw.bzw.bzw. WiederWieder---- COSPAR Satellit StartStartStart (GMT) Trägerrakete Startort Umläuft Bemerkungen Bemannt (km)(km)(km) (km)(km)(km) (Grad) Organisation eintritt 2013-01A Kosmos 2482 15.01.2013 Rokot Plesezk 1.484 1.523 82,504 Erde Russland - Militärischer Datenrelais- Nein (Strela-3M 4) 16.25 satellit 2013-01B Kosmos 2483 15.01.2013 Rokot Plesezk 1.485 1.510 82,505 Erde Russland - Militärischer Datenrelais- Nein (Strela-3M 5) 16.25 satellit 2013-01C Kosmos 2484 15.01.2013 Rokot Plesezk 1.484 1.523 82,504 Erde Russland - Militärischer Datenrelais- Nein (Strela-3M 6) 16.25 satellit 2013-02A IGS-Radar 4 27.01.2013 H2-A Tanegashima 480 500 97 Erde Japan - Radar-Aufklärungssatellit Nein 4.40 2013-02B IGS-Optik 5V 27.01.2013 H2-A Tanegashima 480 500 97 Erde Japan - Optischer Aufklärungs- Nein 4.40 satellit 2013-03A STSat 2C 30.01.2013 Naro 1 Naro-Raumfahrt- 304 1.509 80,275 Erde Südkorea - Forschungs- und Technolo- Nein 7.00 zentrum giesatellit; ca. 100 kg 2013-04A TDRS K 31.01.2013 Atlas 5 Cape Canaveral 35.744 35.845 6,998 Erde USA - Bahnverfolgungs- und Nein 1.48 Datenrelaissatellit; 3.454 kg NOA-01 Intelsat 27 01.02.2013 Zenit 3 Sea-Launch-Plattform - - - - USA - Fehlfunktion der ersten Nein 7.56 Stufe und Absturz 2013-05A Globalstar M78 06.02.3013 Sojus 2 Baikonur 1.420 1.421 52,004 Erde USA - Sprach- und Datenkommu- Nein 16.04 nikationssatellit; 700 kg 2013-05B Globalstar M93 06.02.3013 Sojus 2 Baikonur 1.420 1.421 51,980 Erde USA - Sprach- und Datenkommu- -
Changes to the Database Document
Additions and Deletions for the 12-1-18 Release This version of the Database includes launches through November 30, 2018. There are currently 1,957 active satellites in the database. The changes to this version of the database include: • The addition of 141satellites • The deletion of 71 satellites • The addition of and corrections to some satellite data Satellites Removed Echostar-1 – 1995-073A Palapa C2 -- 1996-030A Measat-2 – 1996-063B Iridium 12 – 1997-030B Iridium 10 – 1997-030D Iridium 15 – 1997-034A Iridium 18 -- 1997-034D ABS-3 -- 1997-042A Iridium 25 – 1997-043B Iridium 37 – 1997-056D Iridium 41 – 1997-069B JCSat-1B – 1997-075A Iridium 47 – 1997-082C Globalstar FM4 – 1998-008B Iridium 52 – 1998-010A Iridium 56 – 1998-010B Iridium 50 – 1998-010D Iridium 53 – 1998-010E Iridium 62 -- 1998-021A Iridium 65 – 1998-021D Iridium 66 – 1998-021E Iridium 67 – 1998-021F Iridium 68 – 1998-021G Iridium 72 – 1998-032B Iridium 75 – 1998-032E Iridium 76 – 1998-048B Iridium 81 – 1998-051B Iridium 80 – 1998-051C Iridium 86 – 1998-066B Iridium 84 – 1998-066D Iridium 83 – 1998-066E Dove 2e-1 – 1998-067JD Dove 2e-5 – 1998-067JN Dove 2ep-5 – 1998-067JR Dove 2ep-14 – 1998-067KJ Dove 2ep-15 – 1998-067KL Dove 2ep-17 – 1998-067KN Dove 2ep-18 – 1998-067KM Dove 23p-20 – 1998-067KP Dove 2ep-19 – 1998-067KQ Lemur-2F20 -- 1998-067LD i-INSPIRE-2 – 1998-067ML Tomsk-TPU-120 -- 1998-067MZ Tanyusha 1 -- 1998-067NA Tanyusha 2 -- 1998-067NB TNS-0-2 Nanosputnik -- 1998-067ND SIMPL – 1998-067NF Iridium 20A – 1998-074A Iridium 11A – 1998-074B Globalstar M023 – 1999-004A -
The Annual Compendium of Commercial Space Transportation: 2017
Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2017 January 2017 Annual Compendium of Commercial Space Transportation: 2017 i Contents About the FAA Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 51 United States Code, Subtitle V, Chapter 509 (formerly the Commercial Space Launch Act). FAA AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA AST is directed to encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover art: Phil Smith, The Tauri Group (2017) Publication produced for FAA AST by The Tauri Group under contract. NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. ii Annual Compendium of Commercial Space Transportation: 2017 GENERAL CONTENTS Executive Summary 1 Introduction 5 Launch Vehicles 9 Launch and Reentry Sites 21 Payloads 35 2016 Launch Events 39 2017 Annual Commercial Space Transportation Forecast 45 Space Transportation Law and Policy 83 Appendices 89 Orbital Launch Vehicle Fact Sheets 100 iii Contents DETAILED CONTENTS EXECUTIVE SUMMARY .