Cubesat Communication Systems
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
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. -
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 .................................................................................................... -
Spacecraft System Failures and Anomalies Attributed to the Natural Space Environment
NASA Reference Publication 1390 - j Spacecraft System Failures and Anomalies Attributed to the Natural Space Environment K.L. Bedingfield, R.D. Leach, and M.B. Alexander, Editor August 1996 NASA Reference Publication 1390 Spacecraft System Failures and Anomalies Attributed to the Natural Space Environment K.L. Bedingfield Universities Space Research Association • Huntsville, Alabama R.D. Leach Computer Sciences Corporation • Huntsville, Alabama M.B. Alexander, Editor Marshall Space Flight Center • MSFC, Alabama National Aeronautics and Space Administration Marshall Space Flight Center ° MSFC, Alabama 35812 August 1996 PREFACE The effects of the natural space environment on spacecraft design, development, and operation are the topic of a series of NASA Reference Publications currently being developed by the Electromagnetics and Aerospace Environments Branch, Systems Analysis and Integration Laboratory, Marshall Space Flight Center. This primer provides an overview of seven major areas of the natural space environment including brief definitions, related programmatic issues, and effects on various spacecraft subsystems. The primary focus is to present more than 100 case histories of spacecraft failures and anomalies documented from 1974 through 1994 attributed to the natural space environment. A better understanding of the natural space environment and its effects will enable spacecraft designers and managers to more effectively minimize program risks and costs, optimize design quality, and achieve mission objectives. .o° 111 TABLE OF CONTENTS -
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. -
March 21–25, 2016
FORTY-SEVENTH LUNAR AND PLANETARY SCIENCE CONFERENCE PROGRAM OF TECHNICAL SESSIONS MARCH 21–25, 2016 The Woodlands Waterway Marriott Hotel and Convention Center The Woodlands, Texas INSTITUTIONAL SUPPORT Universities Space Research Association Lunar and Planetary Institute National Aeronautics and Space Administration CONFERENCE CO-CHAIRS Stephen Mackwell, Lunar and Planetary Institute Eileen Stansbery, NASA Johnson Space Center PROGRAM COMMITTEE CHAIRS David Draper, NASA Johnson Space Center Walter Kiefer, Lunar and Planetary Institute PROGRAM COMMITTEE P. Doug Archer, NASA Johnson Space Center Nicolas LeCorvec, Lunar and Planetary Institute Katherine Bermingham, University of Maryland Yo Matsubara, Smithsonian Institute Janice Bishop, SETI and NASA Ames Research Center Francis McCubbin, NASA Johnson Space Center Jeremy Boyce, University of California, Los Angeles Andrew Needham, Carnegie Institution of Washington Lisa Danielson, NASA Johnson Space Center Lan-Anh Nguyen, NASA Johnson Space Center Deepak Dhingra, University of Idaho Paul Niles, NASA Johnson Space Center Stephen Elardo, Carnegie Institution of Washington Dorothy Oehler, NASA Johnson Space Center Marc Fries, NASA Johnson Space Center D. Alex Patthoff, Jet Propulsion Laboratory Cyrena Goodrich, Lunar and Planetary Institute Elizabeth Rampe, Aerodyne Industries, Jacobs JETS at John Gruener, NASA Johnson Space Center NASA Johnson Space Center Justin Hagerty, U.S. Geological Survey Carol Raymond, Jet Propulsion Laboratory Lindsay Hays, Jet Propulsion Laboratory Paul Schenk, -
SGAC-Annual-Report-2014.Pdf
ANNUAL REPORT SPACE GENERATION ADVISORY COUNCIL 2014 In support of the United Nations Programme on Space Applications A. TABLE OF CONTENTS A. Table of Contents 2 In support of the United Nations Programme B. Sponsors and Partners 4 on Space Applications 1. Introduction 10 1.1 About the SGAC 12 14 c/o European Space Policy Institute (ESPI) 1.2 Letter from the Co-chairs 15 Schwarzenbergplatz 6 1.3 Letter from the Executive Director 16 Vienna A-1030 1.4 SGAC output at a glance AUSTRIA 2. SGAC Background 22 2.1 History of the SGAC 24 26 [email protected] 2.2 Leadership and Structure 27 www.spacegeneration.org 2.3 Programme +41 1 718 11 18 30 3. The organisation in 2014 30 32 +43 1 718 11 18 99 3.1 Goal Achievement Review 3.2 SGAC Activity Highlights 36 42 © 2015 Space Generation Advisory Council 3.3 Space Generation Fusion Forum Report 3.4 Space Generation Congress Report 50 3.5 United Nations Report 62 3.6 SGAC Regional Workshops 66 3.7 SGAC Supported Events 68 3.8 Financial Summary 72 Acknowledgements 4. Projects 78 4.1 Project Outcomes and Highlights 80 The SGAC 2014 Annual Report was compiled and 4.2 Space Technologies for Disaster Management Project Group 81 edited by Minoo Rathansabapathy (South Africa/ 4.3 Near Earth Objects Project Group 82 Australia), Andrea Jaime (Spain), Laura Rose (USA) 4.4 Space Law and Policy Project Group 84 and Arno Geens (Belgium) with the assistance of 4.5 Commercial Space Project Group 86 Candice Goodwin (South Africa), Justin Park (USA), 4.6 Space Safety and Sustainability Project Group 88 Nikita Marwaha (United Kingdom), Dario Schor 4.7 Small Satellites Project Group 90 (Argentina/Canada), Leo Teeney (UK) and Abhijeet 4.8 Space Exploration Project Group 92 Kumar (Australia) in editing. -
Commercial Orbital Transportation Services
National Aeronautics and Space Administration Commercial Orbital Transportation Services A New Era in Spaceflight NASA/SP-2014-617 Commercial Orbital Transportation Services A New Era in Spaceflight On the cover: Background photo: The terminator—the line separating the sunlit side of Earth from the side in darkness—marks the changeover between day and night on the ground. By establishing government-industry partnerships, the Commercial Orbital Transportation Services (COTS) program marked a change from the traditional way NASA had worked. Inset photos, right: The COTS program supported two U.S. companies in their efforts to design and build transportation systems to carry cargo to low-Earth orbit. (Top photo—Credit: SpaceX) SpaceX launched its Falcon 9 rocket on May 22, 2012, from Cape Canaveral, Florida. (Second photo) Three days later, the company successfully completed the mission that sent its Dragon spacecraft to the Station. (Third photo—Credit: NASA/Bill Ingalls) Orbital Sciences Corp. sent its Antares rocket on its test flight on April 21, 2013, from a new launchpad on Virginia’s eastern shore. Later that year, the second Antares lifted off with Orbital’s cargo capsule, (Fourth photo) the Cygnus, that berthed with the ISS on September 29, 2013. Both companies successfully proved the capability to deliver cargo to the International Space Station by U.S. commercial companies and began a new era of spaceflight. ISS photo, center left: Benefiting from the success of the partnerships is the International Space Station, pictured as seen by the last Space Shuttle crew that visited the orbiting laboratory (July 19, 2011). More photos of the ISS are featured on the first pages of each chapter. -
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, -
Commercial Space Transportation Year in Review
2007 YEAR IN REVIEW INTRODUCTION INTRODUCTION The Commercial Space Transportation: 2007 upon liftoff, destroying the vehicle and the Year in Review summarizes U.S. and interna- satellite. tional launch activities for calendar year 2007 and provides a historical look at the past five Overall, 23 commercial orbital launches years of commercial launch activity. occurred worldwide in 2007, representing 34 percent of the 68 total launches for the year. The Federal Aviation Administration’s This marked an increase over 2006, which Office of Commercial Space Transportation saw 21 commercial orbital launches (FAA/AST) licensed four commercial orbital worldwide. launches in 2007. Three of these licensed launches were successful, while one resulted Russia conducted 12 commercial launch in a launch failure. campaigns in 2007, bringing its international commercial launch market share to 52 per- Of the four orbital licensed launches, cent for the year, a record high for Russia. three used a U.S.-built vehicle: the United Europe attained a 26 percent market share, Launch Alliance Delta II operated by Boeing conducting six commercial Ariane 5 launches. Launch Services. Two of the Delta II vehi- FAA/AST-licensed orbital launch activity cles, in the 7420-10 configuration, deployed accounted for 17 percent of the worldwide the first two Cosmo-Skymed remote sensing commercial launch market in 2007. India satellites for the Italian government. The conducted its first ever commercial launch, third, a Delta II 7925-10, launched the for four percent market share. Of the 68 WorldView 1 commercial remote sensing worldwide orbital launches, there were three satellite for DigitalGlobe. launch failures, including one non-commer- cial launch and two commercial launches. -
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