6. the INTELSAT 17 Satellite
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Ariane-5 Completes Flawless Third Test Flight
r bulletin 96 — november 1998 Ariane-5 Completes Flawless Third Test Flight A launch-readiness review conducted on Friday engine shut down and Maqsat-3 was 16 and Monday 19 October had given the go- successfully injected into GTO. The orbital ahead for the final countdown for a launch just parameters at that point were: two days later within a 90-minute launch Perigee: 1027 km, compared with the window between 13:00 to 14:30 Kourou time. 1028 ± 3 km predicted The launcher’s roll-out from the Final Assembly Apogee: 35 863 km, compared with the Building to the Launch Zone was therefore 35 898 ± 200 km predicted scheduled for Tuesday 20 October at 09:30 Inclination: 6.999 deg, compared with the Kourou time. 6.998 ± 0.05 deg predicted. On 21 October, Europe reconfirmed its lead in providing space Speaking in Kourou immediately after the flight, transportation systems for the 21st Century. Ariane-5, on its third Fredrik Engström, ESA’s Director of Launchers qualification flight, left no doubts as to its ability to deliver payloads and the Ariane-503 Flight Director, confirmed reliably and accurately to Geostationary Transfer Orbit (GTO). The new that: “The third Ariane-5 flight has been a heavy-lift launcher lifted off in glorious sunshine from the Guiana complete success. It qualifies Europe’s new Space Centre, Europe’s spaceport in Kourou, French Guiana, at heavy-lift launcher and vindicates the 13:37:21 local time (16:37:21 UT). technological options chosen by the European Space Agency.” This third Ariane-5 test flight was intended ESA’s Director -
Federal Communications Collll1lwion Record 11 FCC Red No
DA 96-122 Federal Communications Collll1lWion Record 11 FCC Red No. 4 fore find that the public interest will be served by a grant Before the of Comsat's application for the launch of the INTELSAT Federal Communications Commission 707 satellite as conditioned. Washington, D.C. 20554 5. Accordingly, IT IS ORDERED that Comsat's applica tion to participate in the launch and test program of the INTELSAT 707 satellite to be positioned at 359° East Lon In the Matter of gitude, IS GRANTED subject to the following terms and conditions: COMSAT CORPORATION File No. CSS-94-005-LA (a) This authorization is limited to the described Application for authority program. Any change in the authorized location due to participate in the launch to a launch delay or other circumstances will be of the INTELSAT VII-A (F-7) considered upon a proper request by Comsat for authority; (b) Comsat shall furnish via the INTELSAT 707 sat ellite only those channels of communication for com mercial service which have been, or may be, ORDER AND AUTHORIZATION authorized by the Commission under Section 214 of the Communications Act of 1934, as amended; Adopted: January 26, 1996; Released: February 9, 1996 (c) Within 30 days after completion of the testing program, Comsat shall provide the Commission with By the Chief, Satellite and Radiocommunication Divi a summary report of its results and, upon request, sion: shall make the detailed test data available; (d) Conduct of the program authorized herein shall 1. The Commission has under consideration the above be without interruption of commercial satellite ser captioned application filed by the COMSAT Corporation vice now authorized at U.S. -
ARIANE 5 Data Relating to Flight 225
KOUROU August 2015 ARIANE 5 Data relating to Flight 225 EUTELSAT 8 West B Intelsat 34 Data relating to Flight 225 Flight 225 Ariane 5 Satellites: EUTELSAT 8 WEST B – INTELSAT 34 Content 1. Introduction .................................................................... 3 2. Launcher L579 ............................................................... 4 3. Mission V225 ............................................................... 10 4. Payloads ...................................................................... 19 5. Launch campaign ........................................................ 32 6. Launch window ............................................................ 35 7. Final countdown .......................................................... 36 8. Flight sequence ........................................................... 40 9. Airbus Defence and Space and the ARIANE programmes ........................................................................ 42 2 Data relating to Flight 225 1. Introduction Flight 225 is the 81st Ariane 5 launch and the fourth in 2015. It follows on from a series of 66 consecutive successful Ariane 5 launches. This is the 51st ARIANE 5 ECA (Cryogenic Evolution type A), the most powerful version in the ARIANE 5 range. Flight 225 is a commercial mission for Ariane 5. The L579 launcher is the twenty-fifth to be delivered by Airbus Defence and Space to Arianespace as part of the PB production batch. The PB production contract was signed in March 2009 to guarantee continuity of the launch service after completion -
Paper Session II-A-Current Status of the Ariane 4 Program and of The
1994 (31st) Space Exploration and Utilization The Space Congress® Proceedings for the Good of the World Apr 27th, 1:00 PM - 4:00 PM Paper Session II-A - Current Status of the Ariane 4 Program and of the Ariane 5 Development James R. Youdale Arianespace Inc. Washington, D.C. Douglas A. Heydon Arianespace Inc. Washington, D.C. Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Youdale, James R. and Heydon, Douglas A., "Paper Session II-A - Current Status of the Ariane 4 Program and of the Ariane 5 Development" (1994). The Space Congress® Proceedings. 16. https://commons.erau.edu/space-congress-proceedings/proceedings-1994-31st/april-27-1994/16 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. Current Status of the Ariane 4 Program and of the Ariane 5 Development James R. Youdale1 and Douglas A. Heyden~ Arianespace Inc. Washington, D.C. Abstract This paper provides an overview of the commercial siruation of Arianespace, a general update regarding its technical and operational activities and its near and medium term prospects. A summary of the Ariane 4 "track record" is given and the latest improvement to its third staae the HIO III, is presented. Operational improvements that reduce the interval between two = ' consecutive laWlches are also addressed. The ratiollale for going to Ariane 5 is discussed and the current status of the Ariane 5 development program is reviewed. -
Launch Vehicle Control Center Architectures
Launch Vehicle Control Center Architectures Michael D. Watson1, Amy Epps2, and Van Woodruff3 NASA Marshall Space Flight Center, Huntsville, AL 35812 Michael Jacob Vachon4 NASA Johnson Space Center, Houston, TX 77058 Julio Monreal5 European Space Agency, Launchers Directorate, Paris, France Marl Levesque6 United Launch Alliance, Vandenberg AFB and Randall Williams7 and Tom McLaughlin8 Aerospace Corporation, El Segundo, CA 90245 Launch vehicles within the international community vary greatly in their configuration and processing. Each launch site has a unique processing flow based on the specific launch vehicle configuration. Launch and flight operations are managed through a set of control centers associated with each launch site. Each launch site has a control center for launch operations; however flight operations support varies from being co-located with the launch site to being shared with the space vehicle control center. There is also a nuance of some having an engineering support center which may be co-located with either the launch or flight control center, or in a separate geographical location altogether. A survey of control center architectures is presented for various launch vehicles including the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures shares some similarities in basic structure while differences in functional distribution also exist. The driving functions which lead to these factors are considered and a model of control center architectures is proposed which supports these commonalities and variations. I. INTRODUCTION Launch vehicles in both Europe and the United States have been operating successfully for several decades. -
Indian Remote Sensing Satellites (IRS)
Topic: Indian Remote Sensing Satellites (IRS) Course: Remote Sensing and GIS (CC-11) M.A. Geography (Sem.-3) By Dr. Md. Nazim Professor, Department of Geography Patna College, Patna University Lecture-5 Concept: India's remote sensing program was developed with the idea of applying space technologies for the benefit of human kind and the development of the country. The program involved the development of three principal capabilities. The first was to design, build and launch satellites to a sun synchronous orbit. The second was to establish and operate ground stations for spacecraft control, data transfer along with data processing and archival. The third was to use the data obtained for various applications on the ground. India demonstrated the ability of remote sensing for societal application by detecting coconut root-wilt disease from a helicopter mounted multispectral camera in 1970. This was followed by flying two experimental satellites, Bhaskara-1 in 1979 and Bhaskara-2 in 1981. These satellites carried optical and microwave payloads. India's remote sensing programme under the Indian Space Research Organization (ISRO) started off in 1988 with the IRS-1A, the first of the series of indigenous state-of-art operating remote sensing satellites, which was successfully launched into a polar sun-synchronous orbit on March 17, 1988 from the Soviet Cosmodrome at Baikonur. It has sensors like LISS-I which had a spatial resolution of 72.5 meters with a swath of 148 km on ground. LISS-II had two separate imaging sensors, LISS-II A and LISS-II B, with spatial resolution of 36.25 meters each and mounted on the spacecraft in such a way to provide a composite swath of 146.98 km on ground. -
Vega: the European Small-Launcher Programme
r bulletin 109 — february 2002 Vega: The European Small-Launcher Programme R. Barbera & S. Bianchi Vega Department, ESA Directorate of Launchers, ESRIN, Frascati, Italy Background The programme was adopted by ESA in June The origins of the Vega Programme go back to 1998, but the funding was limited to a Step 1, the early 1990s, when studies were performed with the aim of getting the full approval by the in several European countries to investigate the European Ministers meeting in Brussels in May possibility of complementing, in the lower 1999. This milestone was not met, however, payload class, the performance range offered because it was not possible to obtain a wide by the Ariane family of launchers. The Italian consensus from ESA’s Member States for Space Agency (ASI) and Italian industry, in participation in the programme. This gave rise to particular, were very active in developing a period of political uncertainty and to a series concepts and starting pre-development work of negotiations aimed at finding an agreeable based on established knowhow in solid compromise. It is important, on the other hand, propulsion. When the various configuration to record that during the same period the options began to converge and the technical technical definition work continued without feasibility was confirmed, the investigations major disruption, and development tests on the were extended to include a more detailed Zefiro motor were successfully conducted. definition in terms of a market analysis and related cost targets. The subsequent extension of the duration of Step 1 provided the opportunity to revisit and By the end of 2001, the development programme for Europe’s new update the market analysis, based on the small Vega launcher was well underway. -
Technology Acceleration Process for the THEMIS Low Cost and Reusable Prototype
DOI: 10.13009/EUCASS2019-97 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) Technology acceleration process for the THEMIS low cost and reusable prototype Jerome VILA* and Jeremie HASSIN** *ArianeWorks / CNES [email protected] **ArianeWorks / CNES [email protected] Abstract While Ariane 6 and Vega-C are about to being fielded and entering operations, CNES and Arianegroup are already actively preparing next generation of European launchers. With the PROMETHEUS oxygen/methan engine starting subsystems testing in 2018, and the CALLISTO experimental reusable vehicle about to complete Preliminary Design, engineering work has been initiated for next step on the European roadmap: THEMIS. THEMIS is both a demonstrator and a prototype of a low cost and reusable first stage, meant as the centrepiece of future Ariane architectures. It is intended to feature PROMETHEUS and will build upon technologies and lessons learned from the CALLISTO programme. Several challenges lie ahead for THEMIS, with two highlights: meeting an aggressive cost targets consistent with the 50% launch cost cut sought beyond Ariane 6, and keeping a swift tempo for getting THEMIS ready well before 2025. To address those challenges, a specific initiative was undertaken by CNES and Arianegroup, under codename ArianeWorks: combining both a “Skunkworks like” approach and an open-innovation platform, ArianeWorks is tasked with getting the project done quicker and bolder than through a conventional organization. The paper will discuss the system engineering approach adopted for THEMIS design, by identifying and then allocating technical objectives related to Ariane 6 evolution/Ariane NEXT between CALLISTO and different sized THEMIS options. Then, the early hardware/testing “agile” development process will be detailed, with an aim at speeding up design iterations and technology maturations. -
Commercial Spacecraft Mission Model Update
Commercial Space Transportation Advisory Committee (COMSTAC) Report of the COMSTAC Technology & Innovation Working Group Commercial Spacecraft Mission Model Update May 1998 Associate Administrator for Commercial Space Transportation Federal Aviation Administration U.S. Department of Transportation M5528/98ml Printed for DOT/FAA/AST by Rocketdyne Propulsion & Power, Boeing North American, Inc. Report of the COMSTAC Technology & Innovation Working Group COMMERCIAL SPACECRAFT MISSION MODEL UPDATE May 1998 Paul Fuller, Chairman Technology & Innovation Working Group Commercial Space Transportation Advisory Committee (COMSTAC) Associative Administrator for Commercial Space Transportation Federal Aviation Administration U.S. Department of Transportation TABLE OF CONTENTS COMMERCIAL MISSION MODEL UPDATE........................................................................ 1 1. Introduction................................................................................................................ 1 2. 1998 Mission Model Update Methodology.................................................................. 1 3. Conclusions ................................................................................................................ 2 4. Recommendations....................................................................................................... 3 5. References .................................................................................................................. 3 APPENDIX A – 1998 DISCUSSION AND RESULTS........................................................ -
Quarterly Launch Report
Commercial Space Transportation QUARTERLY LAUNCH REPORT Featuring the launch results from the previous quarter and forecasts for the next two quarters 1st Quarter 1998 U n i t e d S t a t e s D e p a r t m e n t o f T r a n s p o r t a t i o n • F e d e r a l A v i a t i o n A d m i n i s t r a t i o n A s s o c i a t e A d m i n i s t r a t o r f o r C o m m e r c i a l S p a c e T r a n s p o r t a t i o n QUARTERLY LAUNCH REPORT 1 1ST QUARTER 1998 REPORT Objectives This report summarizes recent and scheduled worldwide commercial, civil, and military orbital space launch events. Scheduled launches listed in this report are vehicle/payload combinations that have been identified in open sources, including industry references, company manifests, periodicals, and government documents. Note that such dates are subject to change. This report highlights commercial launch activities, classifying commercial launches as one or more of the following: • Internationally competed launch events (i.e., launch opportunities considered available in principle to competitors in the international launch services market), • Any launches licensed by the Office of the Associate Administrator for Commercial Space Transportation of the Federal Aviation Administration under U.S. -
A Case Study in UML Model-Based Dynamic Validation: the Ariane-5 Launcher Software?
Noname manuscript No. (will be inserted by the editor) A case study in UML model-based dynamic validation: the Ariane-5 launcher software? Iulian Ober1, Susanne Graf1, David Lesens2 1 VERIMAG 2, av. de Vignate 38610 Gi`eres, France e-mail: {iulian.ober,susanne.graf}@imag.fr 2 EADS SPACE Transportation 66, route de Verneuil - BP 3002 78133 Les Mureaux Cedex - France e-mail: [email protected] The date of receipt and acceptance will be inserted by the editor Abstract The aim of this paper is to show the use- 1 Introduction fulness of IFx, an extension of the IF validation toolset for timed and complex systems, for the validation of de- Model-driven engineering is making its way through the signs represented using the UML profile defined in the habits of software and system designers and developers, IST Omega project. pushed forward by the increasing maturity of modeling This demonstration is done on hand of a realistic case languages and tools. This paradigm promotes a com- study, a model of the Ariane-5 launcher software. In this plete re-foundation of software engineering activities on case study, we do not address the correctness of the con- the basis of models, as well as the use of automatic tools trol algorithms, which may be specified as global trans- for most if not all post-design activities like getting a actions and validated with the help of synchronous tools platform-specific implementation, generating and exe- such as Scade. We are rather interested in the expression cuting tests, deployment, etc. -
China Dream, Space Dream: China's Progress in Space Technologies and Implications for the United States
China Dream, Space Dream 中国梦,航天梦China’s Progress in Space Technologies and Implications for the United States A report prepared for the U.S.-China Economic and Security Review Commission Kevin Pollpeter Eric Anderson Jordan Wilson Fan Yang Acknowledgements: The authors would like to thank Dr. Patrick Besha and Dr. Scott Pace for reviewing a previous draft of this report. They would also like to thank Lynne Bush and Bret Silvis for their master editing skills. Of course, any errors or omissions are the fault of authors. Disclaimer: This research report was prepared at the request of the Commission to support its deliberations. Posting of the report to the Commission's website is intended to promote greater public understanding of the issues addressed by the Commission in its ongoing assessment of U.S.-China economic relations and their implications for U.S. security, as mandated by Public Law 106-398 and Public Law 108-7. However, it does not necessarily imply an endorsement by the Commission or any individual Commissioner of the views or conclusions expressed in this commissioned research report. CONTENTS Acronyms ......................................................................................................................................... i Executive Summary ....................................................................................................................... iii Introduction ................................................................................................................................... 1