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Vulcan Centaur
VULCAN CENTAUR The Vulcan Centaur rocket design leverages the flight-proven success of the Delta IV and Atlas V launch vehicles while introducing new technologies and innovative features to ensure a reliable and aordable space launch service. Vulcan Centaur will service a diverse range of markets including 225 ft commercial, civil, science, cargo and national security space customers. 1 The spacecraft is encapsulated in a 5.4-m- (17.7-ft-) diameter payload fairing (PLF), a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates the spacecraft. The payload attach fitting (PAF) is a similar sandwich composite structure creating the mating interface from spacecraft to second stage. The PLF separates using a debris-free horizontal and vertical separation system with 2 200 ft spring packs and frangible joint assembly. The payload fairing is available in the 15.5-m (51-ft) standard and 21.3-m (70-ft) 1 long configurations. The Centaur upper stage is 5.4 m (17.7 ft) in diameter and 3 11.7 m (38.5 ft) long with a 120,000-lb propellant capacity. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle, with two RL10C 4 engines. The Vulcan Centaur Heavy vehicle, flies the upgraded 2 Centaur using RL10CX engines with nozzle extensions. The 5 175 ft cryogenic tanks are insulated with spray-on foam insulation (SOFI) to manage boil o of cryogens during flight. An aft equipment shelf provides the structural mountings for vehicle electronics. -
Rocket Nozzles: 75 Years of Research and Development
Sådhanå Ó (2021) 46:76 Indian Academy of Sciences https://doi.org/10.1007/s12046-021-01584-6Sadhana(0123456789().,-volV)FT3](0123456789().,-volV) Rocket nozzles: 75 years of research and development SHIVANG KHARE1 and UJJWAL K SAHA2,* 1 Department of Energy and Process Engineering, Norwegian University of Science and Technology, 7491 Trondheim, Norway 2 Department of Mechanical Engineering, Indian Institute of Technology Guwahati, Guwahati 781039, India e-mail: [email protected]; [email protected] MS received 28 August 2020; revised 20 December 2020; accepted 28 January 2021 Abstract. The nozzle forms a large segment of the rocket engine structure, and as a whole, the performance of a rocket largely depends upon its aerodynamic design. The principal parameters in this context are the shape of the nozzle contour and the nozzle area expansion ratio. A careful shaping of the nozzle contour can lead to a high gain in its performance. As a consequence of intensive research, the design and the shape of rocket nozzles have undergone a series of development over the last several decades. The notable among them are conical, bell, plug, expansion-deflection and dual bell nozzles, besides the recently developed multi nozzle grid. However, to the best of authors’ knowledge, no article has reviewed the entire group of nozzles in a systematic and comprehensive manner. This paper aims to review and bring all such development in one single frame. The article mainly focuses on the aerodynamic aspects of all the rocket nozzles developed till date and summarizes the major findings covering their design, development, utilization, benefits and limitations. -
Status of the Space Shuttle Solid Rocket Booster
The Space Congress® Proceedings 1980 (17th) A New Era In Technology Apr 1st, 8:00 AM Status of The Space Shuttle Solid Rocket Booster William P. Horton Solid Rocket Booster Engineering Office, George C. Marshall Space Flight Center, Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Horton, William P., "Status of The Space Shuttle Solid Rocket Booster" (1980). The Space Congress® Proceedings. 3. https://commons.erau.edu/space-congress-proceedings/proceedings-1980-17th/session-1/3 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]. STATUS OF THE SPACE SHUTTLE SOLID ROCKET BOOSTER William P. Horton, Chief Engineer Solid Rocket Booster Engineering Office George C. Marshall Space Flight Center, AL 35812 ABSTRACT discuss retrieval and refurbishment plans for Booster reuse, and will address Booster status Two Solid Rocket Boosters provide the primary for multimission use. first stage thrust for the Space Shuttle. These Boosters, the largest and most powerful solid rocket vehicles to meet established man- BOOSTER CONFIGURATION rated design criteria, are unique in that they are also designed to be recovered, refurbished, It is appropriate to review the Booster config and reused. uration before describing the mission profile. The Booster is 150 feet long and is 148 inches The first SRB f s have been stacked on the in diameter (Figure 1), The inert weight Mobile Launch Platform at the Kennedy Space is 186,000 pounds and the propellant weight is Center and are ready to be mated with the approximately 1.1 million pounds for each External Tank and Orbiter in preparation for Booster. -
Atlas V Cutaway Poster
ATLAS V Since 2002, Atlas V rockets have delivered vital national security, science and exploration, and commercial missions for customers across the globe including the U.S. Air Force, the National Reconnaissance Oice and NASA. 225 ft The spacecraft is encapsulated in either a 5-m (17.8-ft) or a 4-m (13.8-ft) diameter payload fairing (PLF). The 4-m-diameter PLF is a bisector (two-piece shell) fairing consisting of aluminum skin/stringer construction with vertical split-line longerons. The Atlas V 400 series oers three payload fairing options: the large (LPF, shown at left), the extended (EPF) and the extra extended (XPF). The 5-m PLF is a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates both the Centaur upper stage and the spacecraft, which separates using a debris-free pyrotechnic actuating 200 ft system. Payload clearance and vehicle structural stability are enhanced by the all-aluminum forward load reactor (FLR), which centers the PLF around the Centaur upper stage and shares payload shear loading. The Atlas V 500 series oers 1 three payload fairing options: the short (shown at left), medium 18 and long. 1 1 The Centaur upper stage is 3.1 m (10 ft) in diameter and 12.7 m (41.6 ft) long. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle. It uses a single RL10 engine producing 99.2 kN (22,300 lbf) of thrust. -
Evolved Expendable Launch Operations at Cape Canaveral, 2002-2009
EVOLVED EXPENDABLE LAUNCH OPERATIONS AT CAPE CANAVERAL 2002 – 2009 by Mark C. Cleary 45th SPACE WING History Office PREFACE This study addresses ATLAS V and DELTA IV Evolved Expendable Launch Vehicle (EELV) operations at Cape Canaveral, Florida. It features all the EELV missions launched from the Cape through the end of Calendar Year (CY) 2009. In addition, the first chapter provides an overview of the EELV effort in the 1990s, summaries of EELV contracts and requests for facilities at Cape Canaveral, deactivation and/or reconstruction of launch complexes 37 and 41 to support EELV operations, typical EELV flight profiles, and military supervision of EELV space operations. The lion’s share of this work highlights EELV launch campaigns and the outcome of each flight through the end of 2009. To avoid confusion, ATLAS V missions are presented in Chapter II, and DELTA IV missions appear in Chapter III. Furthermore, missions are placed in three categories within each chapter: 1) commercial, 2) civilian agency, and 3) military space operations. All EELV customers employ commercial launch contractors to put their respective payloads into orbit. Consequently, the type of agency sponsoring a payload (the Air Force, NASA, NOAA or a commercial satellite company) determines where its mission summary is placed. Range officials mark all launch times in Greenwich Mean Time, as indicated by a “Z” at various points in the narrative. Unfortunately, the convention creates a one-day discrepancy between the local date reported by the media and the “Z” time’s date whenever the launch occurs late at night, but before midnight. (This proved true for seven of the military ATLAS V and DELTA IV missions presented here.) In any event, competent authorities have reviewed all the material presented in this study, and it is releasable to the general public. -
Feasibility of Reusable Continuous Thrust Spacecraft for Cargo Resupply Missions to Mars
Feasibility of reusable continuous thrust spacecraft for cargo resupply missions to Mars by C. B. Rabotin M.S., ESIEE Paris, 2011 A thesis submitted to the Faculty of the Graduate School of the University of Colorado in partial fulfillment of the requirements for the degree of Masters of Science in Aerospace Engineering Sciences Ann and H.J. Smead Aerospace Engineering Sciences 2017 This thesis entitled: Feasibility of reusable continuous thrust spacecraft for cargo resupply missions to Mars written by C. B. Rabotin has been approved for the Ann and H.J. Smead Aerospace Engineering Sciences Dr. Hanspeter Schaub Dr. Natasha Bosanac Dr. Jay McMahon Date The final copy of this thesis has been examined by the signatories, and we find that both the content and the form meet acceptable presentation standards of scholarly work in the above mentioned discipline. Rabotin, C. B. (M.Sc., Aerospace) Feasibility of reusable continuous thrust spacecraft for cargo resupply missions to Mars Thesis directed by Dr. Hanspeter Schaub Continuous thrust propulsion systems benefit from a much greater efficiency in vacuum than chemical rockets, at the expense of lower instantaneous thrust and high power requirements. The satellite telecommunications industry, known for greatly emphasizing heritage over innovation, now uses electric propulsion for station keeping on a number of spacecraft, and for orbit raising for some smaller satellites, such as the Boeing 702SP platform. Only a few interplanetary missions have relied on continuous thrust for most of their mission, such as ESA's 367 kg SMART-1 and NASA's 1217 kg Dawn mission. The high specific impulse of these continuous thrust engines should make them suitable for transportation of heavy payloads to inner solar system destinations in such a way to limit the dependency on heavy rocket launches. -
Internal Aerodynamics in Solid Rocket Propulsion (L’Aérodynamique Interne De La Propulsion Par Moteurs-Fusées À Propergols Solides)
NORTH ATLANTIC TREATY RESEARCH AND TECHNOLOGY ORGANISATION ORGANISATION AC/323(AVT-096)TP/70 www.rta.nato.int RTO EDUCATIONAL NOTES EN-023 AVT-096 Internal Aerodynamics in Solid Rocket Propulsion (L’aérodynamique interne de la propulsion par moteurs-fusées à propergols solides) The material in this publication was assembled to support a RTO/VKI Special Course under the sponsorship of the Applied Vehicle Technology Panel (AVT) and the von Kármán Institute for Fluid Dynamics (VKI) presented on 27-31 May 2002 in Rhode-Saint-Genèse, Belgium. Published January 2004 Distribution and Availability on Back Cover NORTH ATLANTIC TREATY RESEARCH AND TECHNOLOGY ORGANISATION ORGANISATION AC/323(AVT-096)TP/70 www.rta.nato.int RTO EDUCATIONAL NOTES EN-023 AVT-096 Internal Aerodynamics in Solid Rocket Propulsion (L’aérodynamique interne de la propulsion par moteurs-fusées à propergols solides) The material in this publication was assembled to support a RTO/VKI Special Course under the sponsorship of the Applied Vehicle Technology Panel (AVT) and the von Kármán Institute for Fluid Dynamics (VKI) presented on 27-31 May 2002 in Rhode-Saint-Genèse, Belgium. The Research and Technology Organisation (RTO) of NATO RTO is the single focus in NATO for Defence Research and Technology activities. Its mission is to conduct and promote co-operative research and information exchange. The objective is to support the development and effective use of national defence research and technology and to meet the military needs of the Alliance, to maintain a technological lead, and to provide advice to NATO and national decision makers. The RTO performs its mission with the support of an extensive network of national experts. -
SOLID BOOSTERS How Far Have We Come? How Far Can We Go? by J
View down through the center of the world's largest solid rocket shows rubberlike propellant charge framing two Aerojet- I General engineers as they stand between the center pair of the motor's segments. Rocket develops half million pounds thrust. The big solid-rocket program, a USAF responsibility, is now going to get its chance . SOLID BOOSTERS How Far Have We Come? How Far Can We Go? By J. S. Butz, Jr. TECHNICAL EDITOR, AIR FORCE MAGAZINE . S OLID rockets have now attained a really solid Today, the situation has been completely reversed. position in our space planning. The big solid rocket is going to get its chance. Devel- A year ago, few people familiar with the US opment of these boosters has been made an Air Force space effort would have bet much money that solid responsibility, and about $60 million has been pro- propellants would ever be used as "superboosters," de- vided to begin the job in earnest during this fiscal veloping upward of fifteen million pounds of thrust. year. All signs point toward a maximum-effort devel- By last fall, in fact, the large solid-rocket program opment program that will be pushed as fast as tech- apparently was stuck for good on the treadmill of end- nology will allow. less study and research. Several factors contributed to this sudden change Since Sputnik I opened the space age, the nation's of fortune. Yuri Gagarin's orbital flight in April—in solid-rocket experts had contended that multimil- which the Red flyer became history's first spaceman— lion-pound-thrust solid-propellant boosters would be certainly was instrumental. -
2020 Florida Space Day Handout
2020 Florida Space Day is a milestone event that presents an opportunity to educate and bring awareness to Florida legislators on the significance of the aerospace industry and its impact on Florida’s economy. Florikan Scientific Instruments Scientific Lighting Solutions Zero Gravity Solutions BIOS Lighting Sarasota County Palm Beach County Brevard County Palm Beach County Brevard County The aerospace industry represents billions of dollars Has partnered with Supplies Kennedy Space Builds high-speed camera Has developed a micronutrient Is using NASA LED technology in annual economic impact and employs NASA multiple times to Center, as well as other space systems to detect and map formula, BAM-FX, that increases to create lighting systems for create a more robust and medical companies, with lightning strikes before the nutritional value and yield of unique applications, such as thousands of residents in the state’s 67 counties. polymer coating for its silicon diode sensors capable launches. The technology also crops. Nutrient-rich foods like maximizing plant photosynthesis controlled-release of tracking temperatures has applications in protecting these will be necessary for future and inducing wakefulness in fertilizer and to develop hundreds of degrees wind farms and investigating long-term space missions. humans by outputting only fertilizer to meet the below zero. insurance claims. certain wavelengths of light. needs of plants growing in space. 2020 SPACE DAY PARTNERS ECONOMIC DEVELOPMENT COMMISSION FLORIDA’S SPACE COAST FloridaSpaceDay.com » #FLSpaceDay The Florida Space Day is an organized and united effort to communicate to the Governor, Lt. Governor and Legislators an appreciation of their support to the space industry, educate them on the state wide economic impact of space and to develop and advocate for key initiatives that will enhance the competitiveness and viability of the state of Florida in the space sector. -
Paper Session I-A - Liquid Rocket Boosters for Shuttle
The Space Congress® Proceedings 1989 (26th) Space - The New Generation Apr 25th, 2:00 PM Paper Session I-A - Liquid Rocket Boosters for Shuttle James E. Hughes Manager, LRB Studies, Marshall Space Flight Center, NASA Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Hughes, James E., "Paper Session I-A - Liquid Rocket Boosters for Shuttle" (1989). The Space Congress® Proceedings. 8. https://commons.erau.edu/space-congress-proceedings/proceedings-1989-26th/april-25-1989/8 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]. LIQUID ROCKET BOOSTERS FOR SHUTTLE James E. Hughes, Manager LRB Studies Marshall Space Flight Center, NASA ABSTRACT The Liquid Rocket Booster study was initiated vehicles, and a pressure fed system, once by NASA to define an alternative to the Solid referred to as the "Big Dumb Booster". The Rocket Boosters used on the STS. These prime study contractors, Martin Marietta Cor studies have involved MSFC, JSC and KSC poration and General Dynamics Space Sys and their contractors. The prime study con tems, were assisted considerably by the ef tractors, Martin Marietta Corporation and forts of Lockheed Space Operations Co. General Dynamics Space Systems, have (LSOC) at the Kennedy Space Center and identified Liquid Booster configurations which Lockheed Engineering and Sciences Co. would replace the SRB's in the Shuttle stack. (LESC) at Johnson Space Center, as well as wind tunnel testing at MSFC, and other sup The Liquid Rocket Booster increases Shuttle port. -
Large Reusable Liquid Rocket Booster
Determination of the Nose Cone Shape for a Large Reusable Liquid Rocket Booster by ROBERT LAUREN ACKER B.S., Massachusetts Institute of Technology 1987 SUBMITTED IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE IN AERONAUTICS AND ASTRONAUTICS at the MASSACHUSETTS INSTITUTE OF TECHNOLOGY February 1988 ©Robert L. Acker 1988 The author hereby grants M.I.T. and Hughes Aircraft Company permission to reproduce and to distribute copies of this thesis document in whole or in part. Signature of Author Department of Aeronautics and Astronautics January 12, 1988 Reviewed by C. P. Rubin Hughes Aircraft Company Certified by - rv -- - Prof. Walter M. Hollister Thesis Supervisor, Deprtment of Aeronautics and Astronautics Accepted by , {"' Prof. Harold Y. Wachman Chairman, Department Graduate Committee Department of Aeronautics and Astronautics MASSACHUSETTSINST:7, a OF TECHNOLOGY WHDAWN I FEB 0 4198 M.LT.W LIB-RAiES , J Determination of the Nose Cone Shape for a Large Reusable Liquid Rocket Booster by Robert L. Acker Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics January 15, 1988 Abstract Recently there has been a lot of interest in making reusable space vehicles in an effort to lower launch costs. In addition, the use of liquid propellant in a multistage vehicle provides for the maximum performance. This study examines the forces on the nose cone of the first stage of such a rocket and uses them to determine the best shape for the nose cone. The specific stage looked at is a strap-on booster on a design proposed at Hughes Aircraft Company. -
Soviet Reusable Space Systems Program: Implications for Space Operations in the 1990S
) (I ' ·-·.;;;;:, .. Dire.ctorate of . ttJ _)\ Intelligence . G0 Soviet Reusable Space Systems Program: Implications for Space Operations in the 1990s An Intelligence Assessment SOV 88-10061 sw 88-/IJOj6 Stpu'"hu J9RR Copy Warning Notice Intelligence Sources or Methods Involved (WNINTEL) National &curity Unauthorized Disclosure Information Subject to Criminal Sanctions Oissc:mination Control Abbr~riations NOFORN (NFJ Not releasable to foreien nationals NOSONTR~_CT_CN_C_I ___~N_o_t~re_lc_•_s•_b_le_t~o_c_M_l~rz~~-o_rs_o.,.r~c_o~nl_rz_c~lo_r~/c_o_ns_u_h_z_nt_s PROP IN (PRJ Caution-proprietary inform;.tion involved OR CON (OCJ Dissemination and Cltraction of inform.1tion ---···----------,--,---,---.,.---------,-----controlled by oricinator REl___ This inform3.tion h.u been :~uthorizcd for release to ... ___________,_ __ W_N ______ --:----- WNI ~TEL-Intcllia:cncc sources or mel hods involved A microfiche copy o( I his docu- Clauillcd bl men! is available front OIR/ Declassify: OADR DLB (~82-7177~ printed copies Derived from muhiplc sources from CPAS/IMC(~&l-HOJ; or AIM request to uscrid CPASIMCJ. Rceulu rcccip! of 01 reports can be am need chrouch CPAS/IMC. All material on this ~r:c . --·-------------------- is Unclassified. ') / ' Directorate or lntdligrocc Soviet Reusable Space Systems Program: Implications for Space Operations in the 1990s An lntdligcnce Assessment This paper was prepared b ,Qflicc of Soviet Anal)'sis. an<'.- ~f Science and Weapons Rescare #:ontributions fro. t?_o~ . Comments znd queries arc welcome and may be dircctcdl\0 . or to . USWR. J yrf sov 88-10061 SWS8-100l6 Scpumba 1933 I ' Soviet Reusable Space Systems Program: Implications for Space Operations in the_l990! Key Judgments The Soviets arc developing at least one, and possibly two, reusable space llffurmation availabl~ systems.