Overview of Public Offering for Small Secondary Satellite Launch Opportunity
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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. -
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. -
Small Satellite Doldrums
25 Years of Small Satellites AC4/5 MISSION Siegfried Janson The Aerospace Corporation Presented August 9, 2011 © The Aerospace© The Aerospace Corporation Corporation 2010 2011 Microsatellite Launch History: Last 25 years Microsatellite launch rates rose rapidly in the early 1960’s, and peaked in 1965. Non-Strela microsatellite launch rates hit bottom from 1977 to 1987; the “Small 2 Satellite Doldrums”. They’ve recovered over the past 25 years. Nanosatellite Launch History: About 3 nanosatellites were launched per year during the first decade of space exploration. Launch rates hit zero between 1972 to 1989, but stabilized at ~2 per year 3 through 2002. The CubeSat paradigm has enabled a rapid rise in launch rates. Picosatellite Launch History: Only two active picosatellites were flown before 2000. The Stanford Orbiting Picosatellite Automated Launcher (OPAL) ejected 6 picosatellites into orbit, kicking- st 4 off a 21 century return of picosatellites and the CubeSat Era. Small Satellite Launch History: The First 30 years • The 1960’s: Boom and Bust - Small satellite launch rates rapidly increase in early 1960’s as the Space Age unfolds - Small satellite launch rates decrease in latter half of decade as launch vehicle throw weight capability increases and satellites get bigger (on average). • The 1970’s: Soviet Microsatellites Dominate - Strela-1M constellation deployed; it eventually requires over 300 spacecraft - Western small satellite launch rates continue to decline as satellites grow in size • The 1980’s: Small Satellite Doldrums (1977-1987) - No nanosatellites or picosatellites launched - Less than 5 Western microsatellites launched per year - DARPA initiates LightSat program; holds workshop in 1987 - First AIAA/USU Small Satellite Conference in 1987 - “Doldrums” end in 1987 By 1986, the Soviet Union was actively launching military communications microsatellites, but the rest of the world was experiencing a dearth of new small 5 satellites. -
Prototype Design and Mission Analysis for a Small Satellite Exploiting Environmental Disturbances for Attitude Stabilization
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis and Dissertation Collection 2016-03 Prototype design and mission analysis for a small satellite exploiting environmental disturbances for attitude stabilization Polat, Halis C. Monterey, California: Naval Postgraduate School http://hdl.handle.net/10945/48578 NAVAL POSTGRADUATE SCHOOL MONTEREY, CALIFORNIA THESIS PROTOTYPE DESIGN AND MISSION ANALYSIS FOR A SMALL SATELLITE EXPLOITING ENVIRONMENTAL DISTURBANCES FOR ATTITUDE STABILIZATION by Halis C. Polat March 2016 Thesis Advisor: Marcello Romano Co-Advisor: Stephen Tackett Approved for public release; distribution is unlimited THIS PAGE INTENTIONALLY LEFT BLANK REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704–0188 Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instruction, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188) Washington, DC 20503. 1. AGENCY USE ONLY 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED (Leave blank) March 2016 Master’s thesis 4. TITLE AND SUBTITLE 5. FUNDING NUMBERS PROTOTYPE DESIGN AND MISSION ANALYSIS FOR A SMALL SATELLITE EXPLOITING ENVIRONMENTAL DISTURBANCES FOR ATTITUDE STABILIZATION 6. AUTHOR(S) Halis C. Polat 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING Naval Postgraduate School ORGANIZATION REPORT Monterey, CA 93943-5000 NUMBER 9. -
H-2 Family Home Launch Vehicles Japan
Please make a donation to support Gunter's Space Page. Thank you very much for visiting Gunter's Space Page. I hope that this site is useful a nd informative for you. If you appreciate the information provided on this site, please consider supporting my work by making a simp le and secure donation via PayPal. Please help to run the website and keep everything free of charge. Thank you very much. H-2 Family Home Launch Vehicles Japan H-2 (ETS 6) [NASDA] H-2 with SSB (SFU / GMS 5) [NASDA] H-2S (MTSat 1) [NASDA] H-2A-202 (GPM) [JAXA] 4S fairing H-2A-2022 (SELENE) [JAXA] H-2A-2024 (MDS 1 / VEP 3) [NASDA] H-2A-204 (ETS 8) [JAXA] H-2B (HTV 3) [JAXA] Version Strap-On Stage 1 Stage 2 H-2 (2 × SRB) 2 × SRB LE-7 LE-5A H-2 (2 × SRB, 2 × SSB) 2 × SRB LE-7 LE-5A 2 × SSB H-2S (2 × SRB) 2 × SRB LE-7 LE-5B H-2A-1024 * 2 × SRB-A LE-7A - 4 × Castor-4AXL H-2A-202 2 × SRB-A LE-7A LE-5B H-2A-2022 2 × SRB-A LE-7A LE-5B 2 × Castor-4AXL H-2A-2024 2 × SRB-A LE-7A LE-5B 4 × Castor-4AXL H-2A-204 4 × SRB-A LE-7A LE-5B H-2A-212 ** 1 LRB / 2 LE-7A LE-7A LE-5B 2 × SRB-A H-2A-222 ** 2 LRB / 2 × 2 LE-7A LE-7A LE-5B 2 × SRB-A H-2A-204A ** 4 × SRB-A LE-7A Widebody / LE-5B H-2A-222A ** 2 LRB / 2 × LE-7A LE-7A Widebody / LE-5B 2 × SRB-A H-2B-304 4 × SRB-A Widebody / 2 LE-7A LE-5B H-2B-304A ** 4 × SRB-A Widebody / 2 LE-7A Widebody / LE-5B * = suborbital ** = under stud y Performance (kg) LEO LPEO SSO GTO GEO MolO IP H-2 (2 × SRB) 3800 H-2 (2 × SRB, 2 × SSB) 3930 H-2S (2 × SRB) 4000 H-2A-1024 - - - - - - - H-2A-202 10000 4100 H-2A-2022 4500 H-2A-2024 5000 H-2A-204 6000 H-2A-212 -
A Sample AMS Latex File
PLEASE SEE CORRECTED APPENDIX A IN CORRIGENDUM, JOSS VOL. 6, NO. 3, DECEMBER 2017 Zea, L. et al. (2016): JoSS, Vol. 5, No. 3, pp. 483–511 (Peer-reviewed article available at www.jossonline.com) www.DeepakPublishing.com www. JoSSonline.com A Methodology for CubeSat Mission Selection Luis Zea, Victor Ayerdi, Sergio Argueta, and Antonio Muñoz Universidad del Valle de Guatemala, Guatemala City, Guatemala Abstract Over 400 CubeSats have been launched during the first 13 years of existence of this 10 cm cube-per unit standard. The CubeSat’s flexibility to use commercial-off-the-shelf (COTS) parts and its standardization of in- terfaces have reduced the cost of developing and operating space systems. This is evident by satellite design projects where at least 95 universities and 18 developing countries have been involved. Although most of these initial projects had the sole mission of demonstrating that a space system could be developed and operated in- house, several others had scientific missions on their own. The selection of said mission is not a trivial process, however, as the cost and benefits of different options need to be carefully assessed. To conduct this analysis in a systematic and scholarly fashion, a methodology based on maximizing the benefits while considering program- matic risk and technical feasibility was developed for the current study. Several potential mission categories, which include remote sensing and space-based research, were analyzed for their technical requirements and fea- sibility to be implemented on CubeSats. The methodology helps compare potential missions based on their rele- vance, risk, required resources, and benefits. -
Thermal Analysis of a Small Satellite in Post- Mission Phase
Journal of Multidisciplinary Engineering Science and Technology (JMEST) ISSN: 2458-9403 Vol. 6 Issue 2, February - 2019 Thermal Analysis of a Small Satellite in Post- Mission Phase Ahmed Elhefnawy Ahmed Elweteedy Space Technology Center Military Technical College Cairo, Egypt Cairo, Egypt [email protected] [email protected] Abstract— The objective of satellite thermal perigee altitude of 354 km, an apogee altitude of 1447 control is maintaining all satellite components km and an inclination of 71˚. A passive thermal control within their operational temperature range for system was used, with a small electric heater for the different missions. Most small satellites are battery. Thermal models were developed within both designed to have passive thermal control system. MATLAB/Simulink and ESATAN/ESARAD In this paper the thermal analysis of a small environments. satellite in post-mission phase is introduced. The Dinh [4] illustrated the modeling of a nanosatellite European Student Earth Orbiter (ESEO) satellite using Thermal Desktop software. The satellite has a was chosen in this study. This phase starts at the passive thermal control system. It was designed to end of the operational phase and should last at operate in LEO with altitude of 400 km. least 2 years for the chosen satellite. A finite Bulut et al [5] described the thermal control system difference thermal model using a commercial of Turksat-3U Nanosatellite [6]. The satellite orbit is software “Thermal Desktop” was described for the sun-synchronous orbit with altitude 600 km and selected satellite. Model results verification were inclination 98˚. The satellite has passive thermal performed by varying design variables and seeing control system. -
And Cubesats) Has Come: Analyzing the Numbers
SSC13-IX-01 The Long-Threatened Flood of University-Class Spacecraft (and CubeSats) Has Come: Analyzing the Numbers Michael Swartwout Saint Louis University 3450 Lindell Boulevard St. Louis, Missouri 63103; (314) 977-8240 [email protected] ABSTRACT We have covered the statistical history of university-class small satellites for nearly a decade, revisiting the numbers every two years. In every previous paper, we have promised/threatened that the number of university-class missions will increase, only to spend the next paper explaining why that flood has not happened – but is definitely going to happen next year. This year, at last, we can break the cycle: the flood of university-class spacecraft has come, in the form of CubeSats; more than 30 are known to be manifested for 2013, with equal (or greater) numbers for 2014. For this paper, we will revise previous studies in two ways: 1) Include the results of the past two years, which will show a continued upward trend in the number of university- class missions, a continued downward trend in the size of the spacecraft, and a not-so-continued dominance of the flagship universities. Have we hit a second turning point in the history of CubeSats, where they switch from novelties to actually-useful missions? (The preliminary answer: maybe.) 2) Expand the study to consider other small spacecraft mission types: specifically the professionally-built CubeSats. We will perform side-by-side comparison of the two. The results will be used in a brave but ultimately naive attempt to predict the next few years in university-class and CubeSat-class flights: numbers, capabilities, and mix of participants. -
Financial Operational Losses in Space Launch
UNIVERSITY OF OKLAHOMA GRADUATE COLLEGE FINANCIAL OPERATIONAL LOSSES IN SPACE LAUNCH A DISSERTATION SUBMITTED TO THE GRADUATE FACULTY in partial fulfillment of the requirements for the Degree of DOCTOR OF PHILOSOPHY By TOM ROBERT BOONE, IV Norman, Oklahoma 2017 FINANCIAL OPERATIONAL LOSSES IN SPACE LAUNCH A DISSERTATION APPROVED FOR THE SCHOOL OF AEROSPACE AND MECHANICAL ENGINEERING BY Dr. David Miller, Chair Dr. Alfred Striz Dr. Peter Attar Dr. Zahed Siddique Dr. Mukremin Kilic c Copyright by TOM ROBERT BOONE, IV 2017 All rights reserved. \For which of you, intending to build a tower, sitteth not down first, and counteth the cost, whether he have sufficient to finish it?" Luke 14:28, KJV Contents 1 Introduction1 1.1 Overview of Operational Losses...................2 1.2 Structure of Dissertation.......................4 2 Literature Review9 3 Payload Trends 17 4 Launch Vehicle Trends 28 5 Capability of Launch Vehicles 40 6 Wastage of Launch Vehicle Capacity 49 7 Optimal Usage of Launch Vehicles 59 8 Optimal Arrangement of Payloads 75 9 Risk of Multiple Payload Launches 95 10 Conclusions 101 10.1 Review of Dissertation........................ 101 10.2 Future Work.............................. 106 Bibliography 108 A Payload Database 114 B Launch Vehicle Database 157 iv List of Figures 3.1 Payloads By Orbit, 2000-2013.................... 20 3.2 Payload Mass By Orbit, 2000-2013................. 21 3.3 Number of Payloads of Mass, 2000-2013.............. 21 3.4 Total Mass of Payloads in kg by Individual Mass, 2000-2013... 22 3.5 Number of LEO Payloads of Mass, 2000-2013........... 22 3.6 Number of GEO Payloads of Mass, 2000-2013.......... -
Satellites Frequency List Update
All Satellites Frequency List Update 30 Sept 2013, Latest Update by JE9PEL Satellite Number Uplink Downlink Beacon Mode Callsign Active ------------ ----- ----------- ----------- ------- ----------------- ------------ ------ AO-1 (Oscar-1) 00214 . 144.983 CW AO-2 (Oscar-2) 00305 . 144.983 CW AO-3 (Oscar-3) 01293 145.975-146.025 144.325-375 . SSB,CW AO-4 (Oscar-4) 01902 432.145-155 144.300-310 . SSB,CW AO-5 (Oscar-5) 04321 . 29.450 144.050 CW AO-6 (Phase-2A) 06236 145.900-999 29.450-550 . SSB,CW AO-7 (Phase-2B) 07530 145.850-950 29.400-500 29.502 A * AO-7 (Phase-2B) 07530 432.125-175 145.975-925 145.970 B,C * AO-7 (Phase-2B) 07530 . 2304.100 435.100 D(RTTY) AO-8 (Phase-2D) 10703 145.850-900 29.400-500 29.402 SSB,CW AO-8 (Phase-2D) 10703 145.900-999 435.200-100 435.095 SSB,CW UO-9 (UoSAT-1) 12888 . 145.825/435.025 2401.000 SSB,CW AO-10 (Phase-3B) 14129 435.030-180 145.975-825 145.810 SSB,CW UO-11 (UoSAT-2) 14781 . 145.826/435.025 2401.500 (V)FM,(S)PSK UOSAT-2 * MIR 16609 145.985 145.985 145.985 Packet R0MIR-1 RS-12 (Sputnik) 21089 21.210-250 29.410-450 29.408 SSB,CW RS-13 (Sputnik) 21089 21.260-300 145.860-900 145.862 SSB,CW AO-13 (Phase-3C) 19216 435.423-573 145.975-825 145.812 SSB,CW UO-14 (UoSAT-3) 20437 145.975 435.070 . -
University of Florida Thesis Or Dissertation Formatting
DELAY TOLERANT NETWORKING FOR CUBESAT TOPOLOGIES AND PLATFORMS By PAUL MURI A DISSERTATION PRESENTED TO THE GRADUATE SCHOOL OF THE UNIVERSITY OF FLORIDA IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY UNIVERSITY OF FLORIDA 2013 1 © 2013 Paul Muri 2 To my beloved parents, Theresa Muri and David Muri; and to my colleagues, friends, and family who believe in me 3 ACKNOWLEDGMENTS I would like to express my sincerest gratitude to my academic advisor, Prof. Janise McNair, for her invaluable guidance and continuous support throughout my undergrad and graduate studies at the University of Florida. Her openness and encouragement of my ideas helped me become a better researcher. Without her excellent advice, patience, and support, this doctoral dissertation would not be possible. I would like to thank all of my committee members, Prof. Jenshan Lin, Prof. Jasmeet Judge, and Prof. Norman Fitz-Coy, for serving on my committee. The committee’s valuable comments and constructive criticism helped to improve this dissertation greatly. I also would like extend my appreciation to the Wireless and Mobile System laboratory colleagues. They always gave me valuable suggestions, generous support, and fruitful “jam sessions” during my graduate studies at the University of Florida. I thank all of my labmates, Gokul Bhat, Obul Challa, Max Xiang Mao, Sherry Xiaoyuan Li, Jing Qin, Jose Alomodovar, Krishna Chaitanya, Dante Buckley, Ritwik Dubey, Bom Leenhapat Navaravong, Dexiang Wang, Jing Jing Pan, Gustavo Vejarano, Seshupriya Alluru, Eric Graves, and Corey Baker, in no particular order. All of them made my days in the lab more enjoyable. -
A Multiple Payload
Hi this is Steve Nerlich from Cheap Astronomy www.cheapastro.com and this is A multiple payload. There is an HIIA rocket launch planned for May 18 2010 from the Tanegashima Space Center, on the island of Tanegashima, which is south of the most of the rest of Japan. The HIIA rocket’s primary payload is the Akatsuki mission to Venus, developed by the Japanese Aerospace Exploration Agency - or JAXA. But, as an example of the principle of why launch just one thing when you can launch six, the mission will include the world's first interplanetary solar sail, the UNITEC-1 probe and three pico-satellites. But let’s start with Akatsuki, also known as the Venus Climate Orbiter. If the 18th of May launch goes according to plan, this 640kg spacecraft, fitted with hydrazine thrusters and solar arrays for electrical power, will arrive at Venus in December 2010 and enter a highly elliptical orbit for a science mission that will last at least 2 years. Akatsuki's science goals include trying to understand Venus’ meteorology - including how the atmosphere formed and why it screams around the planet at such a phenomenal rate – much faster than the planet spins, although still in the same direction as that spin. Also, Akatsuki will look for any evidence of active volcanic activity on the surface of Venus. Akatsuki will scan Venus’ atmosphere, monitoring different wavelengths from infra-red to ultra-violet with the hope of gaining cross-sectional views of the atmosphere at different altitudes. From right at the top at 90 kilometres altitude, down to the cloud tops at about 65 kilometres altitude and then all the way down to 0 kilometres altitude.