Solar Electric Propulsion: Introduction, Applications and Status
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Telecommunikation Satellites: the Actual Situation and Potential Future Developments
Telecommunikation Satellites: The Actual Situation and Potential Future Developments Dr. Manfred Wittig Head of Multimedia Systems Section D-APP/TSM ESTEC NL 2200 AG Noordwijk [email protected] March 2003 Commercial Satellite Contracts 25 20 15 Europe US 10 5 0 1995 1996 1997 1998 1999 2000 2001 2002 2003 European Average 5 Satellites/Year US Average 18 Satellites/Year Estimation of cumulative value chain for the Global commercial market 1998-2007 in BEuro 35 27 100% 135 90% 80% 225 Spacecraft Manufacturing 70% Launch 60% Operations Ground Segment 50% Services 40% 365 30% 20% 10% 0% 1 Consolidated Turnover of European Industry Commercial Telecom Satellite Orders 2000 30 2001 25 2002 3 (7) Firm Commercial Telecom Satellite Orders in 2002 Manufacturer Customer Satellite Astrium Hispasat SA Amazonas (Spain) Boeing Thuraya Satellite Thuraya 3 Telecommunications Co (U.A.E.) Orbital Science PT Telekommunikasi Telkom-2 Indonesia Hangar Queens or White Tails Orders in 2002 for Bargain Prices of already contracted Satellites Manufacturer Customer Satellite Alcatel Space New Indian Operator Agrani (India) Alcatel Space Eutelsat W5 (France) (1998 completed) Astrium Hellas-Sat Hellas Sat Consortium Ltd. (Greece-Cyprus) Commercial Telecom Satellite Orders in 2003 Manufacturer Customer Satellite Astrium Telesat Anik F1R 4.2.2003 (Canada) Planned Commercial Telecom Satellite Orders in 2003 SES GLOBAL Three RFQ’s: SES Americom ASTRA 1L ASTRA 1K cancelled four orders with Alcatel Space in 2001 INTELSAT Launched five satellites in the last 13 month average fleet age: 11 Years of remaining life PanAmSat No orders expected Concentration on cash flow generation Eutelsat HB 7A HB 8 expected at the end of 2003 Telesat Ordered Anik F1R from Astrium Planned Commercial Telecom Satellite Orders in 2003 Arabsat & are expected to replace Spacebus 300 Shin Satellite (solar-array steering problems) Korea Telecom Negotiation with Alcatel Space for Koreasat Binariang Sat. -
The Development of a Pulsed Plasma Thruster As a Solid Fuel Plasma Source for a High Power Helicon
The Development of a Pulsed Plasma Thruster as a Solid Fuel Plasma Source for a High Power Helicon Ian Kronheim Johnson A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science The University of Washington 2011 Program authorized to offer degree: Aeronautics and Astronautics University of Washington Graduate School This is to certify that I have examined this copy of a master’s thesis by Ian Kronheim Johnson and have found that is it complete and satisfactory in all respects, and that any and all revisions required by the final examining committee have been made. Committee Members: Professor Robert Winglee, Department of Earth and Space Sciences, Chair Professor Tom Jarboe, Department of Aeronautics and Astronautics Date: The University of Washington ii In presenting this thesis in partial fulfillment of the requirements for a master’s degree at the University of Washington, I agree that the Library shall make its copies freely available for inspection. I further agree that extensive copying of this thesis is allowable only for scholarly purposes, consistent with “fair use” as prescribed in the U.S. Copyright Law. Any other reproduction for any purposes or by any means shall not be allowed without my written permission. Signature: Date: The University of Washington iii University of Washington Abstract The Development of a Pulsed Plasma Thruster as a Solid Fuel Plasma Source for a High Power Helicon Ian Kronheim Johnson Chair of the Supervisory Committee: Professor Robert Winglee Earth and Space Sciences As space exploration shifts to lower mass and lower cost missions, the need for improved on-board propulsion systems is growing. -
Boeing 702 Fleet
Boeing 702 Fleet ! List of Boeing 702 Satellite operators have Programs responded enthusiastically to the vastly increased ! List of 702s On Order capabilities represented by the Boeing 702. Boeing Satellite Systems (BSS) announced the innovative satellite series in October 1995. Evolved from the popular, proven 601 and 601HP (high-power) spacecraft, the body- stabilized Boeing 702 is the 01PR 01507 world leader in capacity, High resolution image available here performance and cost- efficiency. As of June 2005, 19 of these powerful satellites had been ordered, with options for six more. The first satellite was launched in 1999. The satellite can carry more than 100 high-power transponders, and deliver any communications frequencies that customers request. The Boeing 702 design is directly responsive to what customers said they wanted in a communications satellite, beginning with lower cost and including the high reliability for which the company is renowned. For maximum customer value and producibility at minimum total cost, the Boeing 702 offers a broad spectrum of modularity. A primary example is payload/bus integration. After the payload is tailored to customer specifications, the payload module mounts to the common bus module at only four locations and with only six electrical connectors. This design simplicity confers major advantages. First, nonrecurring program costs are reduced, because the bus does not need to be changed for every payload, and payloads can be freely tailored without affecting the bus. Second, the design permits significantly faster parallel bus and payload processing. This leads to the third advantage: a short production schedule. Further efficiency derives from the 702's advanced xenon ion propulsion system (XIPS), which was pioneered by BSS and is produced today by Boeing Electron Dynamic Devices, Inc. -
1 Iac-06-C4.4.7 the Innovative Dual-Stage 4-Grid Ion
IAC-06-C4.4.7 THE INNOVATIVE DUAL-STAGE 4-GRID ION THRUSTER CONCEPT – THEORY AND EXPERIMENTAL RESULTS Cristina Bramanti, Roger Walker, ESA-ESTEC, Keplerlaan 1, 2201 AZ Noordwijk, The Netherlands [email protected], Roger. Walker @esa.int Orson Sutherland, Rod Boswell, Christine Charles Plasma Research Laboratory, Research School of Physical Sciences and Engineering, The Australian National University, Canberra, ACT 0200, Australia [email protected], [email protected], [email protected]. David Fearn EP Solutions, 23 Bowenhurst Road, Church Crookham, Fleet, Hants, GU52 6HS, United Kingdom [email protected] Jose Gonzalez Del Amo, Marika Orlandi ESA-ESTEC, Keplerlaan 1, 2201 AZ Noordwijk, The Netherlands [email protected], [email protected] ABSTRACT A new concept for an advanced “Dual-Stage 4-Grid” (DS4G) ion thruster has been proposed which draws inspiration from Controlled Thermonuclear Reactor (CTR) experiments. The DS4G concept is able to operate at very high specific impulse, power and thrust density values well in excess of conventional 3-grid ion thrusters at the expense of a higher power-to-thrust ratio. A small low-power experimental laboratory model was designed and built under a preliminary research, development and test programme, and its performance was measured during an extensive test campaign, which proved the practical feasibility of the overall concept and demonstrated the performance predicted by analytical and simulation models. In the present paper, the basic concept of the DS4G ion thruster is presented, along with the design, operating parameters and measured performance obtained from the first and second phases of the experimental campaign. -
Innovative Commercial Satellite Approaches for Space Related Ground Systems
Ground Systems Architecture Workshop 2014 Mobility Briefing Innovative Commercial Satellite Approaches for Space Related Ground Systems February• August 26, 2011 2014 Mark Daniels VP Engineering and Operations Intelsat General Corporation © 2014 by Intelsat General Corporation. Published by The Aerospace Corporation with permission Proprietary & Confidential 1 General Shelton Quote On January 7, 2014 In Response To Question About Commercial Industry’s Role In Military Space: “ Why couldn’t we contract for all standard wideband communication services? “Why couldn’t that be written by commercial providers instead of us buying our own satellites?” June 28, 2010 The U.S. government will use commercial space products and services in fulfilling governmental needs, invest in new and advanced technologies and concepts, and use a broad array of partnerships with industry to promote innovation. 2 SM 50+ satellites in geostationary orbit IntelsatOne 40,000 miles of MPLS terrestrial infrastructure Global presence, global footprint 3 Intelsat Satellite Operations Experience Currently 76 Satellites Operated (51 Intelsat and 25 Third Party) 14 Bus platforms Astrium E2000 Astrium E3000 Boeing 381 Boeing 393 Boeing 601 Boeing 601HP Boeing 601MEO Boeing 702 Boeing 702MP LM 7000 OSC Star 2 SSL 1300 Omega SSL FS1300 Thales Spacebus 3000B 4 Satellite Operations • Fully redundant primary and back up control centers in Washington, DC and Long Beach, CA • Operational experience with all major manufacturers and satellite platforms • Highly functional and automated -
The Physics of Space Security a Reference Manual
THE PHYSICS The Physics of OF S P Space Security ACE SECURITY A Reference Manual David Wright, Laura Grego, and Lisbeth Gronlund WRIGHT , GREGO , AND GRONLUND RECONSIDERING THE RULES OF SPACE PROJECT RECONSIDERING THE RULES OF SPACE PROJECT 222671 00i-088_Front Matter.qxd 9/21/12 9:48 AM Page ii 222671 00i-088_Front Matter.qxd 9/21/12 9:48 AM Page iii The Physics of Space Security a reference manual David Wright, Laura Grego, and Lisbeth Gronlund 222671 00i-088_Front Matter.qxd 9/21/12 9:48 AM Page iv © 2005 by David Wright, Laura Grego, and Lisbeth Gronlund All rights reserved. ISBN#: 0-87724-047-7 The views expressed in this volume are those held by each contributor and are not necessarily those of the Officers and Fellows of the American Academy of Arts and Sciences. Please direct inquiries to: American Academy of Arts and Sciences 136 Irving Street Cambridge, MA 02138-1996 Telephone: (617) 576-5000 Fax: (617) 576-5050 Email: [email protected] Visit our website at www.amacad.org or Union of Concerned Scientists Two Brattle Square Cambridge, MA 02138-3780 Telephone: (617) 547-5552 Fax: (617) 864-9405 www.ucsusa.org Cover photo: Space Station over the Ionian Sea © NASA 222671 00i-088_Front Matter.qxd 9/21/12 9:48 AM Page v Contents xi PREFACE 1 SECTION 1 Introduction 5 SECTION 2 Policy-Relevant Implications 13 SECTION 3 Technical Implications and General Conclusions 19 SECTION 4 The Basics of Satellite Orbits 29 SECTION 5 Types of Orbits, or Why Satellites Are Where They Are 49 SECTION 6 Maneuvering in Space 69 SECTION 7 Implications of -
Electrostatic Ion Thrusters for Space Debris Removal
Theoretical Physics Electrostatic ion thrusters for space debris removal Oscar Larsson, [email protected] Gustav Hedengren, [email protected] SA114X Degree Project in Engineering Physics, First Level Department of Theoretical Physics Royal Institute of Technology (KTH) Supervisor: Christer Fuglesang October 28, 2018 Abstract The current levels of space debris are critical and actions are needed to prevent collisions. In this paper it is examined whether an electrostatic ion thruster can be powerful enough to slow down the debris in a sufficient manner. Furthermore, it is looked into whether the process can be repeated for a significant number of pieces by maneuvering between them. We conclude that the removal process seems possible although some improvements are needed. Maneuvering is costly but despite conservative assumptions, we estimate that about 800 pieces can be removed in one journey made by a satellite weighing ten tonnes of which nine are xenon. Abstract Den nuvarande nivån av rymdskrot är kritisk och åtgärder krävs för att förhindra kollisioner. I denna artikel undersöks det huruvida en elektrostatisk jonkanon är kraftfull nog för att bromsa skrot tillräckligt. Fortsättningsvis undersöks det om denna process är effectiv nog för att återupprepas för ett betydande antal bitar, inklusive manövrering bitarna emellan. Vi drar slutsatsen att processen verkar möjlig att genomföra även om vissa förbättringar behövs. Manövreringen är kostsam men trots konservativa antaganden uppskattar vi att ungefär 800 bitar kan tas ned under en resa av en satellit med vikt 10 ton varav nio ton är xenon. Contents 1 Introduction 2 2 Background 2 2.1 The space debris problem . .2 2.2 The Dual-stage 4 grid ion thruster (DS4G) . -
Electric Propulsion 4
Technology Forum on Small Body Scientific Exploration – 4th Meeting of the NASA Small Bodies Assessment Group Michael Patterson NASA Glenn Research Center John Brophy Jet Propulsion Laboratory California Institute of Technology January 24, 2011 National Aeronautics and Space Administration www.nasa.gov 1. In-Space Propulsion Overview 2. Current In-Space Investments for Robotic Missions 3. Description of Electric Propulsion 4. Current Technology Investments and Development Status 2 3 Flight System Development Future Applications Non-toxic propellant-based propulsion systems (LOX, LH2, LCH4, Ethanol) Main Propulsion Systems (MPS) Propulsion systems for orbit transfer, orbit injection, spacecraft maneuvering, landing, and ascent Development of component technologies (igniters, exciters, injectors , combustion chambers, nozzles) for non-toxic propellants Current Focus Areas • LOX/LCH4 propulsion technologies for main propulsion systems (MPS), reaction control systems (RCS), and propellant storage and distribution • Development of Orion Service Module propulsion system Reaction Control Systems (RCS) • Preliminary trade studies, requirements development, and planning for Altair ascent propulsion subsystem Research and Technology Development Materials Evaluation Combustion Diagnostics Ignition Performance Propellant Properties 4 Future Applications • Next generation ion propulsion system for deep-space science missions (NEXT) • Propulsion systems for Earth orbital applications including satellite servicing, repositioning, re-boost, orbital -
End to End Optimization of Three Dimensional Chemical-Electric Orbit Raising Missions
END TO END OPTIMIZATION OF THREE DIMENSIONAL CHEMICAL-ELECTRIC ORBIT RAISING MISSIONS David Y. Oh and Scott Kimbrel Space Systems/Loral 3825 Fabian Way M/S G-80 Palo Alto, CA 94303-4604 Manuel Martinez-Sanchez Massachusetts Institute of Technology 77 Massachusetts Avenue Cambridge, MA 02139 IEPC-03-036 Abstract A low thrust trajectory optimization model is combined with a launch vehicle performance model to derive mass optimized three dimensional end-to-end chemical-electric orbit raising (C-EOR) profiles to geostationary orbit (GEO). Optimized profiles are derived for the Sea Launch, Ariane 4, Atlas V, Delta IV, and Proton launch vehicles. Optimum EOR starting orbits are shown and payload mass benefits are calculated for each vehicle. The payload mass benefit is shown to be between 5.9 and 7.6 kg/day with two SPT-140 thrusters, or up to 680 kg. for 90 days of electric orbit raising. A previously presented analytic staging model is used as a basis for a simple parametric performance model covering multiple launch vehicles. The model is an ideal tool for system level analysis of electric orbit raising missions and matches calculated performance to within 10%. This work demonstrates Space Systems/Loral’s ability to optimize electric orbit raising missions to GEO with major commercial launch vehicles, an important and enabling step to the use of optimized C-EOR trajectories on commercial satellites. Nomenclature Isp = specific impulse (sec) mo = spacecraft mass, beginning of orbit raising P = Thruster input power (W) (kg) T2 = electric thruster -
Optimal Orbit-Raising and Attitude Control of All-Electric Satellites
OPTIMAL ORBIT-RAISING AND ATTITUDE CONTROL OF ALL-ELECTRIC SATELLITES A Dissertation by Suwat Sreesawet Master of Science, Wichita State University, 2014 Bachelor of Engineering, Kasetsart University, 2009 Submitted to the Department of Aerospace Engineering and the faculty of the Graduate School of Wichita State University in the partial fulfillment of the requirements for the degree of Doctor of Philosophy December 2018 c Copyright 2018 by Suwat Sreesawet All Rights Reserved OPTIMAL ORBIT-RAISING AND ATTITUDE CONTROL OF ALL-ELECTRIC SATELLITES The following faculty members have examined the final copy of this dissertation for form and content, and recommend that it be accepted in partial fulfillment of the requirement for the degree of Doctor of Philosophy, with a major in Aerospace Engineering. Atri Dutta, Committee Chair James E. Steck, Committee Member Roy Myose, Committee Member Animesh Chakravarthy, Committee Member John Watkins, Committee Member Accepted for the College of Engineering Steven Skinner, Interim Dean Accepted for the Graduate School Dennis Livesay, Dean iii DEDICATION To my family, my mother, father, and sister who have always supported me and provided me the warmth to my heart for entire life, even though I am on the other side of world. To my future wife who always cares for me, and to my friends with whom I have spent many great times together. iv ACKNOWLEDGMENTS First of all, I have many thanks for my family, my dad, mon and sister. They always keep supporting and encouraging me since the day I started breathing with my own nose. I always perceive their love and support even I have been in the opposite side of the world for many years. -
Boeing Low-Thrust Geosynchronous Transfer Mission Experience Mark Poole and Monte Ho Boeing Satellite Development Center, 2260 E
Boeing Low-Thrust Geosynchronous Transfer Mission Experience Mark Poole and Monte Ho Boeing Satellite Development Center, 2260 E. Imperial Hwy, El Segundo, CA, 90245 [email protected], [email protected], ABSTRACT Since 2000, Boeing 702 satellites have used electric propulsion for transfer to geostationary orbits. The use of the 25cm Xenon Ion Propulsion System (25cm XIPS) results in more than a tenfold increase in specific impulse with the corresponding decrease in propellant mass needed to complete the mission when compared to chemical propulsion[1]. In addition to more favorable mass properties, with the use of XIPS, the 702 has been able to achieve orbit insertions with higher accuracy than it would have been possible with the use of chemical thrusters. This paper describes the experience attained by using the 702 XIPS ascent strategy to transfer satellite to geosynchronous orbits. Keywords XIPS, low-thrust, Boeing 702 1. INTRODUCTION The Boeing 702 offers the option of XIPS orbit raising. Using XIPS to augment transfer orbit reduces the amount of propellant necessary to achieve the desired orbit, due to the high specific impulse (Isp) of the XIPS thrusters. Larger payloads can thus be accommodated, with greater flexibility in the choice and use of a launch vehicle. Chemical propellant is used to place the satellite into a 24-hour synchronous elliptical transfer orbit, and XIPS maneuvers are used to circularize the orbit and position the satellite in its final orbit. 2. XIPS ASCENT 2.1 Mission Design For the 702 XIPS ascent phase, a “minimum time-of-flight” trajectory is targeted. -
Evolution of the AIRBUS DS Gmbh Radio Frequency Ion Thruster Family
Evolution of the AIRBUS DS GmbH Radio Frequency Ion Thruster Family IEPC-2015- 90830 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International Electric Propulsion Conference and 6th Nano-satellite Symposium, Hyogo-Kobe, Japan July 4 – 10, 2015 H. J. Leiter1, Ch.Altmann2, R.Kukies3, J.Kuhmann4, J.-P. Porst5 Airbus DS GmbH, Lampoldshausen, Germany Marcel Berger6 and Michael Rath7 Airbus DS GmbH, Bremen, Germany Abstract: The Airbus DS Radio Frequency Ion Thruster "RIT" family and its evolution is presented. The first member of the family was RIT-10. Over the years the engine was carefully evolved. The recent RIT-10 EVO represents the state-of-the art in the 500W class. Taking benefit of the excellent scalability of the RIT technology the family grew in both directions and a thrust range from view micro Newtons to more than 200mN is covered. RIT-μX is the smallest engine for the low Milli- and Micro-Newton regime. In the 5kW class the RIT 2X series replaces RIT-22. The basics of the radio-frequency ion thruster technology are provided. It is a flight proven technology: RIT-10 marked two milestones in the history of electric propulsion. Following a brief historical recall of the RIT-family the three thrusters RIT-μX, RIT-10 EVO and the RIT 2X series are presented together with their embedding systems. I. Introduction lectric propulsion (EP) has become state of the art for commercial geostationary satellites. More and more Eoperators realize the advantages of EP for North South Station keeping and thanks to sufficient electric power on telecom platforms also electric orbit transfer will soon become standard.