DOCSLIB.ORG

The Peacekeeper Post Boost Vehicle for Civil Space Applications

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
The Peacekeeper Post Boost Vehicle for Civil Space Applications I I THE PEACEKEEPER POST BOOST VEHICLE FOR I CIVIL SPACE APPLICATIONS Paul G. Phillips, P.E. I Science Applications International Corporation Dr. Stephen J. Hoffman I Science Applications International Corporation James S. Moore I NASA Johnson Space Center Abstract Orbital UV Jovian Observer missions. The con­ I Ownership of several Peacekeeper fourth stages figurations and preliminary performance require­ has been transferred from the USAF to NASA ments of these missions are discussed. for use in the civil space program. The produc­ I tion of Peacekeeper missiles was discontinued This paper concludes that the Peacekeeper PBV although several of the fourth stages known as provides adequate performance for these mis­ I Post Boost Vehicles or PBV's were in production sions and is worthy of further consideration in and in various stages of completion. This paper the Discovery Program or other programs as a examines the potential use of these PBV's for booster stage or a spacecraft bus. The PBV is I small civil space missions, especially Discovery found to be a versatile spacecraft requiring some class missions. technical work but costing far less than an I equivalently capable three-axis stabilized vehicle. Several configurations of the PBV with small in­ terplanetary missions are examined. The deliv­ Introduction I ered configuration of the PB V is described along As the cold war ends, the possibilities of convert­ with modifications necessary to make them flight ing weapons related equipment to use in civil ready. This paper examines the use of the PBV space program become more and more intriguing. I as a booster stage and as a spacecraft bus. The This is especially true for the upper stage of the booster configurations examined include use of Peacekeeper missile. The Air Force will be dis­ I the PB Valone and in combination with solid continuing production of this weapons system rocket motors. The Delta II and Shuttle launch and has in fact already canceled orders for any systems are considered as launch vehicles for more of them. Some of the upper stages known I these combinations. as Post Boost Vehicles or PBV's are currently on the production line and in various stages of com­ I Discovery Mission performance requirements and pletion. Since they will not be needed for de­ compatibility with the PBV is reviewed. Four of fense purposes, ownership of some of the PBV's the missions which appear to be compatible with has been transferred to NASA for use in the civil I the PBV include the MESUR Pathfinder, the space program. The purpose of this paper is to Near Earth Asteroid Rendezvous, the Venus examine the issues and some of the possibilities I Atmosphere Composition Probe, and the Earth- I 1 I of using these PBV's for small civil space mis­ not the same as space booster or spacecraft bus I sions. missions so the PBV will require some adapta­ tion. The number missions is limited in this study to a I representative set of interplanetary missions. By The PBV is a capable spacecraft. Figure I is an examining this set of missions most of the topics illustration of the PBV itself. It uses a pressure­ surrounding use of the PBV will be covered. fed monomethyl-hydrazine and nitrogen-tetroxide I The Discovery Program of small scale, rapid propulsion system. The system includes a sin­ tum-around, cost constrained interplanetary mis­ gle, gimbal ed, 11400 N (2563 lbf) thrust primary I sions offers a number of opportunities for use engine and eight 311 N (70 lbf) thrust attitude with the PBV. The PBV is compatible with the control engines for three-axis control. The Delta II launch vehicle which is a constraint of the structure is robust consisting of an aluminum I Discovery Program. To illustrate more of the is­ isogrid skin with strong interior primary and sec­ sues of integration, this study also focuses on the ondary elements. It is 96 inches in diameter to I use of the Shuttle for launch purposes. At the match its launch vehicle and is approximately 43 time of this writing, it appears the Shuttle may be inches in its axial direction. These dimensions a available due to possible down-scaling of its leave a significant amount of interior space avail­ I commitment to Space Station Freedom missions. able. Well over 100 of these stages have been The study, then, of the PBV use in civil space built and 18 have been successfully flight tested. I programs will be limited, for this exercise, to the PBV with Discovery missions and will concen­ trate on the Shuttle as a launch vehicle. I The primary options for use of a PBV for I Discovery missions include booster type mis­ sions and spacecraft bus missions. For some missions the best use of the PBV is as a three­ I axis-stabilized stage for injection of the primary spacecraft into its interplanetary trajectory. In I some cases, the mission is such that the PBV can be used as an actual supporting spacecraft bus. This later option involves the use of the PBV as Figure 1 - Peacekeeper Post Boost Vehicle I the primary spacecraft for the mission. The basic PBV is delivered without its Guidance, Navigation and Control system and power sys­ I The Post Boost Vehicle tem, and does not include a thermal control or a The PBV is an integrated, bipropeUant stage de­ communication system. The power or avionics signed to deliver multiple warheads onto highly I subsystem hardware would be clearly inappro­ accurate trajectories. Its design mission is about priate for most civil space applications and may 30 minutes in duration and begins after an ex­ not have been declassified. The PBV never had tended idle period in a missile silo. The entire I communications or thermal control systems be­ missile system is designed to launch into and cause its mission did not require them. The PBV through a hostile environment. This mission is I 2 I I I is structurally robust but does not have launch vehicle or payload mating accommodations. The PBV Performance modifications necessary for adaptation of the Figure 2 shows the performance capabilities of I PBV to civil space missions include design de­ the PBV in various configurations. Shuttle con­ velopment and integration of avionics, power and figurations include the PBV by itself and a light­ thermal system as required along with structural ened version of the PBV with extra propellant. I adaptation to launch vehicles and payloads. This lightened version is assumed to have struc­ ture removed and tanks added such that the dry I The NASA Johnson Space Center owns 12 mass remains constant and the mass of propellant PBV's in various stages of completion. is doubled. Performance figures for the PBV Rocketdyne, the manufacturer, has 4 stages with alone and with extra propellant are shown in solid I all components available and requiring only final lines. As will be shown later, these capabilities assembly. There 6 units for which the compo­ are inadequate for any of the Discovery missions. I nents are nearly complete and piece-parts and raw materials are available on the remaining 2. Cost The PBV capacity as a booster can be enhanced estimates for bringing the PBV's to flight ready by the addition of a solid rocket motor. In these I status including the NASA added subsystems cases the combination of solid rocket and PBV is such as avionics are in the neighborhood of $ 5 a two-stage upper stage with primary control by I million for each PBV. The availability and esti­ the PBV. The performance ofthe PBV launched mated cost of the PBV make it a good candidate in Shuttle with a Morton Thiokol Star 48b and a for a number of applications. Star ·63f are also shown with solid lines and, I relative to the single stage PBV configurations, PBV Use in Civil Launch Systems have correspondingly increased capability. I A PBV is currently planned for the low-earth­ orbit, Liquid Plume Generator (LPG) mission, an The shaded lines in Figure 2 illustrate the perfor­ SDIO mission launched from the Shuttle. mance of the PBV with the Delta IT launch sys­ I Consequently, avionics, power, and thermal tem. The first line indicates PBV performance control subsystems for a non-Peacekeeper appli­ without the standard Star 48b Delta third stage I cation have been designed. In addition, the and is strikingly close to that of the Shuttle Star structural adaptations and safety reviews have 48b line. The second line, which is to the right been completed for PB V integration into the represents PBV performance with the Delta IT and I Shuttle. No required safety modifications have its third stage. This line indicates that a PBV been identified. The choice of launch vehicle will with a Star 48 can provide better performance on make little difference in the work required to a Delta than when launched from Shuttle. This I make the PBV flight ready. So, while the PBV difference is due to the fact that the Delta can will require some adaptation for civil space mis­ place the PBV directly on its injection trajectory I sions, much of the work has already been ac­ without the need to circularize as with Shuttle. complished. I I I 3 I 1000 I 2000 BOO ....'iii' ~ !i 1500 t I ! ! 600 :I :I ! 1000 ! .... .... 400 8 8 I >. E 500 : 200 I 0 0 0 1000 2000 3000 4000 5000 6000 7000 Delta V (melerslllec) I I I I I I I ! I I I I I 0 2 4 6 B 10 12 14 16 1B 20 22 -A- DelIa + PaV Delta V (thousand feet/sec) ......
Load more

Recommended publications
  • Collezione Per Genova
    1958-1978: 20 anni di sperimentazioni spaziali in Occidente La collezione copre il ventennio 1958-1978 che è stato particolarmente importante nella storia della esplorazio- ne spaziale, in quanto ha posto le basi delle conoscenze tecnico-scientifiche necessarie per andare nello spa- zio in sicurezza e per imparare ad utilizzare le grandi potenzialità offerte dallo spazio per varie esigenze civili e militari. Nel clima di guerra fredda, lo spazio è stato fin dai primi tempi, utilizzato dagli Americani per tenere sotto con- trollo l’avversario e le sue dotazioni militari, in risposta ad analoghe misure adottate dai Sovietici. Per preparare le missioni umane nello spazio, era indispensabile raccogliere dati e conoscenze sull’alta atmo- sfera e sulle radiazioni che si incontrano nello spazio che circonda la Terra. Dopo la sfida lanciata da Kennedy, gli Americani dovettero anche prepararsi allo sbarco dell’uomo sulla Luna ed intensificarono gli sforzi per conoscere l’ambiente lunare. Fin dai primi anni, le sonde automatiche fecero compiere progressi giganteschi alla conoscenza del sistema solare. Ben presto si imparò ad utilizzare i satelliti per la comunicazione intercontinentale e il supporto alla navigazio- ne, per le previsioni meteorologiche, per l’osservazione della Terra. La Collezione testimonia anche i primi tentativi delle nuove “potenze spaziali” che si avvicinano al nuovo mon- do dei satelliti, che inizialmente erano monopolio delle due Superpotenze URSS e USA. L’Italia, con San Mar- co, diventò il terzo Paese al mondo a lanciare un proprio satellite e allestì a Malindi la prima base equatoriale, che fu largamente utilizzata dalla NASA. Alla fine degli anni ’60 anche l’Europa entrò attivamente nell’arena spaziale, lanciando i propri satelliti scientifici e di telecomunicazione dalla propria base equatoriale di Kourou.
    [Show full text]
  • L'étrange Histoire Du Premier Moteur-Fusée À Liquides Par Jean-Jacques Serra, Membre De L’IFHE
    #19 - janvier 2017 LES LANCEMENTS DE 1967 15 ANS D’ANDROMEDE 50 ANS D’APOLLO-1 50 ANS DE SOYOUZ-1 ESPACE & TEMPS Le mot du président IFHE Institut Français d’Histoire de l’Espace adresse de correspondance : 2, place Maurice Quentin Chers amis, 75039 Paris Cedex 01 e-mail : [email protected] Je vous souhaite à tous une très bonne année 2017. L’année Tél : 01 40 39 04 77 écoulée a vu la sortie des deux livres qui ont nécessité cinq ans de travail : 50 ans de coopération spatiale France-URSS/Russie et L’institut Français d’Histoire de l’Espace (IFHE) est une L’Observation spatiale de la Terre optique et radar - La france et association selon la Loi de 1901 créée le 22 mars 1999 l’Europe pionnières. qui s’est fixée pour obiectifs de valoriser l’histoire de Nous avons organisé des présentations lors des conférences l’espace et de participer à la sauvegarde et à la préserva- du 20 janvier et du 7 avril à Paris. Par ailleurs, ils ont été présentés tion du patrimoine documentaire. Il est administré par à Toulouse le 20 février (Observation de la Terre), le 13 juin et le 5 un Conseil, et il s’est doté d’un Conseil Scientifique. décembre (50 ans de coopération spatiale). Au 31 octobre 2016, l’éditeur a établi un compte d’exploi- Conseil d’administration tation provisoire : l’Observation de la Terre avait été vendu à 828 Président d’honneur.......Michel Bignier exemplaires et le 50 ans de coopération spatiale à 625 exemplaires.
    [Show full text]
  • JASON D. FIEGE, B.Sc.H, M-Sc
    FILAMENTARY MOLECULAR CLOUDS AND THEIR PROLATE CORES BY JASON D. FIEGE, B.Sc.H, M-Sc. A Thesis Submitted to the School of Graduate Studies in Partial Fulfilment of the Requirements for the Degree Doctor of Philosophy McMaster University @ Copyright by Jason D. Fiege, 1999 National Library Bibliothèque nationale 1*1 of Canada du Canada Acquisitions and Acquisitions et Bibliographie Services services bibliographiques 395 WeUington Street 395, rue Wellington OttawON KIAON4 OttawaON KlAûN4 Canada Canada The author has granted a non- L'auteur a accordé une licence non exclusive licence allowing the exclusive permettant à la National Lhrary of Canada to Bibliothèque nationale du Cana& de reproduce, loan, distribute or sell reproduire, prêter, distribuer ou copies of this thesis in rnicrofom, vendre des copies de cette thèse sous paper or electronic formats. la forme de microfiche/nlm, de reproduction sur papier ou sur format électronique. The author retains ownership of the L'auteur conserve la propriété du copyright in this thesis. Neither the droit d'auteur qui protège cette thèse. thesis nor substantial extracts fiom it Ni la thèse ni des extraits substantiels may be printed or othewise de celle-ci ne doivent être imprimés reproduced without the author's ou autrement reproduits sans son permission. autorisation. FILAMENTARY MOLECULAR CLOUDS AND THEIR PROLATE CORES DOCTOR OF PHILOSOPHY McMaster University (Physics and Astronomy) Hamilton, Ontario TITLE: Filamentary Molecular Clouds and Their Prolate Cores AUTHOR: Jason D. Fiege, B.Sc., M.Sc. (Queen's University) SUPERVISOR: Dr. Mph E. Pudritz NUMBER OF PAGES: xiv, 252. Abstract We develop a mode1 of self-gravitating, pressure truncated, filarnentary molecdar clouds wi t h a rather general helical magnetic field topology.
    [Show full text]
  • The Delta Launch Vehicle- Past, Present, and Future
    The Space Congress® Proceedings 1981 (18th) The Year of the Shuttle Apr 1st, 8:00 AM The Delta Launch Vehicle- Past, Present, and Future J. K. Ganoung Manager Spacecraft Integration, McDonnell Douglas Astronautics Co. H. Eaton Delta Launch Program, McDonnell Douglas Astronautics Co. Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Ganoung, J. K. and Eaton, H., "The Delta Launch Vehicle- Past, Present, and Future" (1981). The Space Congress® Proceedings. 7. https://commons.erau.edu/space-congress-proceedings/proceedings-1981-18th/session-6/7 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]. THE DELTA LAUNCH VEHICLE - PAST, PRESENT AND FUTURE J. K. Ganoung, Manager H. Eaton, Jr., Director Spacecraft Integration Delta Launch Program McDonnell Douglas Astronautics Co. McDonnell Douglas Astronautics Co. INTRODUCTION an "interim space launch vehicle." The THOR was to be modified for use as the first stage, the The Delta launch vehicle is a medium class Vanguard second stage propulsion system, was used expendable booster managed by the NASA Goddard as the Delta second stage and the Vanguard solid Space Flight Center and used by the U.S. rocket motor became Delta's third stage. Government, private industry and foreign coun­ Following the eighteen month development program tries to launch scientific, meteorological, and failure to launch its first payload into or­ applications and communications satellites.
    [Show full text]
  • 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 .
    [Show full text]
  • INTRODUCTION This Study of Reentry Vehicle (RV)
    INTRODUCTION This study of Reentry Vehicle (RV) systems and their associated operations was conducted for the Department of Transportation/Office of Commercial Space Transportation. The purpose of the study was to investigate and present an overview of reentry vehicle systems and to identify differences in mission requirements and operations. This includes reentry vehicle system background, system design considerations, description of past/present/future reentry systems, and hazards associated with reentry vehicles that attain orbit, reenter, and are recovered. A general literature search that included the OCST data base, NASA, Air Force, and other technical libraries and personal contact with various government or private industry organizations knowledgeable in reentry system vehicles was performed. A reference page is provided at the end of this report. A history of early manned reentry vehicle launches is shown in Appendix I. A listing of some of the agencies and companies found to be most knowledgeable in the reentry vehicle area is provided in Appendix II. The following sections provide more detailed information on reentry system vehicles. A. Background - The development of reentry vehicles began in the late 1950's due to the need for Department of Defense and Central Intelligence Agency photo reconnaissance of Soviet ICBM sites. NASA has also been involved in the use of reentry vehicles since the early 1960's, including manned space programs Mercury, Gemini and Apollo. The following sections describe the evolution of reentry system development in the United States and foreign countries: 1. Discoverer1 - The Discoverer program was of major importance because it provided a vehicle for testing orbital maneuvering capability and reentry techniques and it played a large role in enabling the first United States manned space flights to be conducted in Project Mercury.
    [Show full text]
  • Delta Natural Gas Company, Inc. Case No. 2010-001 16
    DELTA NATURAL GAS COMPANY, INC. CASE NO. 2010-001 16 ATTORNEY GENERAL'S ]INITIAL REQUEST F R INFORMATION DATED MAY 24,2010 1. Please provide copies of June year-to-date financial, operating and/or statistical reports for 2006,2007,2008 and 2009 (when available). Response: See PSC-1 Item 41 for financial statements subsequent to the test year. See our application, tab 37 for a copy of the January, 2009 through December, 2009. The financial reports for 2006 through 2008 are on file with the Public Service Commission. Sponsoring Witness: Matthew D. Wesalosky DEL,TA NATURAL GAS COMPANY, INC. CASE NO. 2010-001 16 ATTORNEY GENERAL'S INITIAL,REQUEST FOR INFORMATION DATED MAY 24,2010 2. Please provide a copy of the Board of Directors minutes for 2007, 2008, 2009 and 2010 to date. Response: The Board minutes have been filed under seal with motion for confidential treatment. Sponsoring Witness: John B. Brown DELTA NATURAL GAS COMPANY, INC. CASE NO. 201 0-001 16 ATTORNEY GENERAL'S INITIAL REQUEST FOR INFORMATION DATED MAY 24,2010 3. Please explain in detail any major changes in accounting treatment for O&M expenses, retirements, replacements and removal costs instituted by the Company since 2003. Response: The most significant change resulted from changing our capitalization threshold from $500 to $2,000 in 2004. For SEC reporting purposes, the Company reclassified cost of removal out of accumulated depreciation into regulatory liabilities, adopted SFAS 143 and adopted FIN 47. None of these changes have any impact on this rate case, as Delta has excluded all of these balances in the pro forma numbers.
    [Show full text]
  • 1947.Full.Pdf
    Copyright Ó 2006 by the Genetics Society of America DOI: 10.1534/genetics.106.061630 Structure–Function Analysis of Delta Trafficking, Receptor Binding and Signaling in Drosophila Annette L. Parks,1 Jane R. Stout,1,2 Scott B. Shepard,1,3 Kristin M. Klueg,4 Ana A. Dos Santos,5 Todd R. Parody,6 Martina Vaskova7 and Marc A. T. Muskavitch8 Biology Department, Boston College, Chestnut Hill, Massachusetts 02467 Manuscript received June 19, 2006 Accepted for publication September 18, 2006 ABSTRACT The transmembrane proteins Delta and Notch act as ligand and receptor in a conserved signaling pathway required for a variety of cell fate specification events in many organisms. Binding of Delta to Notch results in a proteolytic cascade that releases the Notch intracellular domain, allowing it to participate in transcriptional activation in the nucleus. Recent research has implicated the endocytic and ubiquitylation machinery as essential components of Delta–Notch signaling. Our analysis of chimeric and missense Delta variants has delineated a number of structural requirements for Delta trafficking, receptor binding, and signaling. We find that while the Delta N-terminal domain is necessary and sufficient for binding to Notch, the integrity of the epidermal-growth-factor-like repeat (ELR) 2 is also required for Notch binding. Screening of 117 Delta mutant lines for proteins that exhibit aberrant subcellular trafficking has led to the identification of 18 Delta alleles (DlTD alleles) that encode ‘‘trafficking-defective’’ Delta proteins. We find, unexpectedly, that many DlTD alleles contain missense mutations in ELRs within the Delta extracellular domain. Finally, we find that two DlTD alleles contain lysine missense mutations within the Delta intracellular domain (DeltaICD) that may identify residues important for DeltaICD mono-ubiquitylation and subsequent Delta endocytosis and signaling.
    [Show full text]
  • Access to the Outer Solar System
    Interstellar Probe Study Webinar Series Access to the Outer Solar System Presenters • Michael Paul • Program Manager, Interstellar Probe Study, Johns Hopkins APL • Robert Stough • Payload Utilization Manager for NASA’s SLS Rocket, NASA Marshall Space Flight Center 12:05 PM EDT Thursday, 9 July 2020 Interstellar Probe Study Website http://interstellarprobe.jhuapl.edu NOW: The Heliosphere and the Local Interstellar Medium Our Habitable Astrosphere Sol G2V Main Sequence Star 24 km/s Habitable Mira BZ Camelopardalis LL Orionis IRC+10216 Zeta Ophiuchi Interstellar Probe Study 9 July 2020 2 Voyager – The Accidental Interstellar Explorers Uncovering a New Regime of Space Physics Global Topology Cosmic Ray Shielding Unexpected Field Direction Force Balance Not Understood Required Hydrogen Wall Measured (Voyager) Interstellar Probe Study 9 July 2020 3 Opportunities Across Disciplines Modest Cross-Divisional Contributions with High Return Extra-Galactic Background Light Dwarf Planets and KBOs Early galaxy and star formation Solar system formation Today Arrokoth Big Bang Pluto 13.7 Gya First Stars & Galaxies Circum-Solar Dust Disk ~13Gya Imprint of solar system evolution Sol 4.6 Ga HL-Tau 1 Ma! Poppe+2019 Interstellar Probe Study 9 July 2020 4 Earth-Jupiter-Saturn Sequences • Point Solutions indicated per year (capped at C3 = 312.15km2/s2) C3 Speed Dest. 2037 2 2 Year Date (km /s ) CA_J (rJ) CA_S (rS) (AU/yr) (Lon, Lat) 2036 17 Sept 182.66 1.05 2.0 5.954 (247,0) 2038 2037 15 Oct 312.15 1.05 2.0 7.985 (230,0) 2038 14 Nov 312.15 1.05 2.0 7.563 (241,0.1) 2036 2039 2039 15 Nov 274.65 1.05 2.0 5.055 (256,0.3) Interstellar Probe Study 9 July 2020 5 SPACE LAUNCH SYSTEM INTERSTELLAR PROBE Robert Stough SLS Spacecraft/Payload Integration & Evolution (SPIE) July 9, 2020 0760 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft.
    [Show full text]
  • Shuttle Derived In-Line Heavy Lift Vehicle
    https://ntrs.nasa.gov/search.jsp?R=20050207383 2019-08-29T20:37:26+00:00Z Shuttle Derived In-Line Heavy Lift Vehicle Terry Greenwood.* NASA MSFC, Huntsville, Alabama, 35812 Wallace Twichell’ and Daniel Fedt Lockheed Martin Space Systems, Michoud Operations, Nav Orleans, LA, 70189-0304 and Frederick Kuck# Boeing - Rocketdyne, Canoga Park; CA, 91309-7922 ~- This paper introduces an evolvable Space Shuttle derived family of launch vehicles. It details the steps in the evolution of the vehicle family, noting how the evolving lift capability compares with the evolving lift requirements. A system description is given for each vehicle. The cost of each development stage is described. Also discussed are demonstration programs, the merits of the SSME vs. an expendable rocket engine (RS-68), and finally, the next steps needed to refine this concept. Nomenclature SSME Space Shuttle Main Engine SSP Space Shuttle Program mt metric tons CEV Crew Exploration Vehicle HLL V Heavy Lift Launch Vehicle Klb thousands of pounds MPTA Main Propulsion Test Article SRB Solid Rocket Booster MPS Main Propulsion System APU Auxiliary Power Unit isp specific impulse. I. Introduction n response to President Bush’s Space Exploration Vision, both NASA and the aerospace industry have proposed Ivarious exploration architectures. The launch vehicles are a key element of these architectures. While some architectures are geared to exploit existing launch vehicles, many require the development of new vehicles to support manned flights and heavy lift. Three principle approaches are the “clean sheet” vehicle, further evolving the evolved expendable vehicles (Atlas V, Delta IV), or a new vehicle based on existing Shuttle elements and technology.
    [Show full text]
  • Now That It Looks Like We Will Have Additional Project Reports That Will
    NEMI 2006 iNEMI Optoelectronic Substrates Project Report Optoelectronic Substrates Project Report 1 November 1, 2006 The 2002 iNEMI Roadmap identified the potential for an optoelectronics interconnection system to replace existing copper interconnect systems for high bandwidth applications. The unresolved issues were, what bandwidth will be required for various applications, and at what bandwidth will the cost of optoelectronics interconnect systems become cost effective. The optoelectronic system would have an optoelectronics substrate on which to mount optoelectronic components including devices and connectors. An Optoelectronics Substrates Project group was formed in 2003 to address this emerging issue. Many iNEMI member companies were interested in participating. This project was the result of these discussions. The group has served as an excellent forum for interaction among members of the current progress, future direction, and implications of optoelectronic developments within the industry. Now four years later, it is not as clear as to when optoelectronic substrates will be needed by industry. Firms are continuing to improve the performance of copper systems, and wireless systems are rapidly expanding. This report serves to document the accomplishments of this project over the past four years. If future roadmaps identify the impending need of optoelectronic substrates, it is hoped that this report can serve as a starting point for future projects. Sincerely Robert Pfahl Vice President of Operations iNEMI Optoelectronic Substrates
    [Show full text]
  • A Status Report Lockheed Launch Vehicle
    I A STATUS REPORT LOCKHEED LAUNCH VEHICLE I for the 7th ANNUAL AIM-UTAH STATE UNIVERSITY I CONFERENCE ON SMALL SATEWTES D.E. Davis, J.W. AngelP, A.J. MaeLaren2 I Lockheed Missiles & Spaee Co.,lne Abstract: This paper discusses a new collocated product development team family of small and medium space launch with the mandate to use our engineering, vehicles being developed by Lockheed manufacturing, and flight test I Missiles & Space Company, Inc. The experience, but - and an important but development program will culminate in - to be innovative in our approaches. a demonstration launch in November For example we elected to use, as much I 1994. The paper gives a brief as possible, existing hardware; to use background and gives the program status aluminum structure rather than as of the date of this paper. composites - although Lockheed builds Supporting graphics are included. much composite structure; and to I simplify the way we do business. Background: We have streamlined our Lockheed Missiles & Space Co, paperwork system. The product I Inc. has been studying small space development team has informal reviews launch vehicles since 1987. The - informal in the sense that their are no original approach then was to use dry-runs, and hand drawn graphics are I surplus or excess ballistic missile acceptable. The technical caliber of assets, primarily the 1st and 2nd stages the presentations is as professional as if from the Poseidon C-3 missile as the it were our traditional government basis, replacing the weapon system customer instead of just ourselves. I guidance and control with state of the art Rather than tell our prospective technology, and adding a 3rd stage with subcontractors how they should design a Star 48 solid rocket motor.
    [Show full text]