Design and Optimization of a Small Reusable Launch Vehicle Using Vertical Landing Techniques Stephane Contant Delft University of Technology
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Validation of Wind Tunnel Test and Cfd Techniques for Retro-Propulsion (Retpro): Overview on a Project Within the Future Launchers Preparatory Programme (Flpp)
VALIDATION OF WIND TUNNEL TEST AND CFD TECHNIQUES FOR RETRO-PROPULSION (RETPRO): OVERVIEW ON A PROJECT WITHIN THE FUTURE LAUNCHERS PREPARATORY PROGRAMME (FLPP) D. Kirchheck, A. Marwege, J. Klevanski, J. Riehmer, A. Gulhan¨ German Aerospace Center (DLR) Supersonic and Hypersonic Technologies Department Cologne, Germany S. Karl O. Gloth German Aerospace Center (DLR) enGits GmbH Spacecraft Department Todtnau, Germany Gottingen,¨ Germany ABSTRACT and landing (VTVL) spacecraft, assisted by retro-propulsion. Up to now, in Europe, knowledge and expertise in that field, The RETPRO project is a 2-years activity, led by the Ger- though constantly growing, is still limited. Systematic stud- man Aerospace Center (DLR) in the frame of ESA’s Future ies were conducted to compare concepts for possible future Launchers Preparatory Program (FLPP), to close the gap of European launchers [2, 3], and activities on detailed inves- knowledge on aerodynamics and aero-thermodynamics of tigations of system components of VTVL re-usable launch retro-propulsion assisted landings for future concepts in Eu- vehicles (RLV) recently started in the RETALT project [4, 5]. rope. The paper gives an overview on the goals, strategy, and Nevertheless, validated knowledge on the aerodynamic current status of the project, aiming for the validation of inno- and aerothermal characteristics of such vehicles is still lim- vative WTT and CFD tools for retro-propulsion applications. ited to a small amount of experimental and numerical inves- Index Terms— RETPRO, retro-propulsion, launcher tigations mostly on lower altitude VTVL trajectories, e. g. aero-thermodynamics, wind tunnel testing, CFD validation within the CALLISTO project [6, 7, 8]. Other studies were conducted to analyze the aerothermodynamics of a simplified generic Falcon 9 geometry during its re-entry and landing 1. -
Spacex Launch Manifest - a List of Upcoming Missions 25 Spacex Facilities 27 Dragon Overview 29 Falcon 9 Overview 31 45Th Space Wing Fact Sheet
COTS 2 Mission Press Kit SpaceX/NASA Launch and Mission to Space Station CONTENTS 3 Mission Highlights 4 Mission Overview 6 Dragon Recovery Operations 7 Mission Objectives 9 Mission Timeline 11 Dragon Cargo Manifest 13 NASA Slides – Mission Profile, Rendezvous, Maneuvers, Re-Entry and Recovery 15 Overview of the International Space Station 17 Overview of NASA’s COTS Program 19 SpaceX Company Overview 21 SpaceX Leadership – Musk & Shotwell Bios 23 SpaceX Launch Manifest - A list of upcoming missions 25 SpaceX Facilities 27 Dragon Overview 29 Falcon 9 Overview 31 45th Space Wing Fact Sheet HIGH-RESOLUTION PHOTOS AND VIDEO SpaceX will post photos and video throughout the mission. High-Resolution photographs can be downloaded from: http://spacexlaunch.zenfolio.com Broadcast quality video can be downloaded from: https://vimeo.com/spacexlaunch/videos MORE RESOURCES ON THE WEB Mission updates will be posted to: For NASA coverage, visit: www.SpaceX.com http://www.nasa.gov/spacex www.twitter.com/elonmusk http://www.nasa.gov/nasatv www.twitter.com/spacex http://www.nasa.gov/station www.facebook.com/spacex www.youtube.com/spacex 1 WEBCAST INFORMATION The launch will be webcast live, with commentary from SpaceX corporate headquarters in Hawthorne, CA, at www.spacex.com. The webcast will begin approximately 40 minutes before launch. SpaceX hosts will provide information specific to the flight, an overview of the Falcon 9 rocket and Dragon spacecraft, and commentary on the launch and flight sequences. It will end when the Dragon spacecraft separates -
By Tamman Montanaro
4 Reusable First Stage Rockets y1 = 15.338 m m1 = 2.047 x 10 kg 5 y2 = 5.115 m m2 = 1.613 x 10 kg By Tamman Montanaro What is the moment of inertia? What is the force required from the cold gas thrusters if we assume constancy. Figure 1. Robbert Goddard’s design of the first ever rocket to fly in 1926. Source: George Edward Pendray. The moment of inertia of a solid disk: rper The Rocket Formula Now lets stack a bunch of these solid disk on each other: Length = l Divide by dt Figure 2: Flight path for the Falcon 9; After separation, the first stage orientates itself and prepares itself for landing. Source: SpaceX If we do the same for the hollow cylinder, we get a moment of inertia Launch of: Specific impulse for a rocket: How much mass is lost? What is the mass loss? What is the moment of inertia about the center of mass for these two objects? Divide by m Figure 3: Falcon 9 first stage after landing on drone barge. Source: SpaceX nd On December 22 2015, the Falcon 9 Orbcomm-2 What is the constant force required for its journey halfway (assuming first stage lands successfully. This is the first ever orbital- that the force required to flip it 90o is the equal and opposite to class rocket landing. From the video and flight logs, we Flip Maneuver stabilize the flip). can gather specifications about the first stage. ⃑ How much time does it take for the first stage to descend? We assume this is the time it takes � Flight Specifications for the first stage to reorientate itself. -
Cape Canaveral Air Force Station Support to Commercial Space Launch
The Space Congress® Proceedings 2019 (46th) Light the Fire Jun 4th, 3:30 PM Cape Canaveral Air Force Station Support to Commercial Space Launch Thomas Ste. Marie Vice Commander, 45th Space Wing Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Ste. Marie, Thomas, "Cape Canaveral Air Force Station Support to Commercial Space Launch" (2019). The Space Congress® Proceedings. 31. https://commons.erau.edu/space-congress-proceedings/proceedings-2019-46th/presentations/31 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]. Cape Canaveral Air Force Station Support to Commercial Space Launch Colonel Thomas Ste. Marie Vice Commander, 45th Space Wing CCAFS Launch Customers: 2013 Complex 41: ULA Atlas V (CST-100) Complex 40: SpaceX Falcon 9 Complex 37: ULA Delta IV; Delta IV Heavy Complex 46: Space Florida, Navy* Skid Strip: NGIS Pegasus Atlantic Ocean: Navy Trident II* Black text – current programs; Blue text – in work; * – sub-orbital CCAFS Launch Customers: 2013 Complex 39B: NASA SLS Complex 41: ULA Atlas V (CST-100) Complex 40: SpaceX Falcon 9 Complex 37: ULA Delta IV; Delta IV Heavy NASA Space Launch System Launch Complex 39B February 4, 2013 Complex 46: Space Florida, Navy* Skid Strip: NGIS Pegasus Atlantic Ocean: Navy Trident II* Black text – current programs; -
Space Launch System (Sls) Motors
Propulsion Products Catalog SPACE LAUNCH SYSTEM (SLS) MOTORS For NASA’s Space Launch System (SLS), Northrop Grumman manufactures the five-segment SLS heavy- lift boosters, the booster separation motors (BSM), and the Launch Abort System’s (LAS) launch abort motor and attitude control motor. The SLS five-segment booster is the largest solid rocket motor ever built for flight. The SLS booster shares some design heritage with flight-proven four-segment space shuttle reusable solid rocket motors (RSRM), but generates 20 percent greater average thrust and 24 percent greater total impulse. While space shuttle RSRM production has ended, sustained booster production for SLS helps provide cost savings and access to reliable material sources. Designed to push the spent RSRMs safely away from the space shuttle, Northrop Grumman BSMs were rigorously qualified for human space flight and successfully used on the last fifteen space shuttle missions. These same motors are a critical part of NASA’s SLS. Four BSMs are installed in the forward frustum of each five-segment booster and four are installed in the aft skirt, for a total of 16 BSMs per launch. The launch abort motor is an integral part of NASA’s LAS. The LAS is designed to safely pull the Orion crew module away from the SLS launch vehicle in the event of an emergency on the launch pad or during ascent. Northrop Grumman is on contract to Lockheed Martin to build the abort motor and attitude control motor—Lockheed is the prime contractor for building the Orion Multi-Purpose Crew Vehicle designed for use on NASA’s SLS. -
IAC-17-D2.4.3 Page 1 of 18 IAC-17
68th International Astronautical Congress (IAC), Adelaide, Australia, 25-29 September 2017. Copyright ©2017 by DLR-SART. Published by the IAF, with permission and released to the IAF to publish in all forms. IAC-17- D2.4.3 Evaluation of Future Ariane Reusable VTOL Booster stages Etienne Dumonta*, Sven Stapperta, Tobias Eckerb, Jascha Wilkena, Sebastian Karlb, Sven Krummena, Martin Sippela a Department of Space Launcher Systems Analysis (SART), Institute of Space Systems, German Aerospace Center (DLR), Robert Hooke Straße 7, 28359 Bremen, Germany b Department of Spacecraft, Institute of Aerodynamics and Flow Technology, German Aerospace Center (DLR), Bunsenstraße 10, 37073 Gottingen, Germany *[email protected] Abstract Reusability is anticipated to strongly impact the launch service market if sufficient reliability and low refurbishment costs can be achieved. DLR is performing an extensive study on return methods for a reusable booster stage for a future launch vehicle. The present study focuses on the vertical take-off and vertical landing (VTOL) method. First, a restitution of a flight of Falcon 9 is presented in order to assess the accuracy of the tools used. Then, the preliminary designs of different variants of a future Ariane launch vehicle with a reusable VTOL booster stage are described. The proposed launch vehicle is capable of launching a seven ton satellite into a geostationary transfer orbit (GTO) from the European spaceport in Kourou. Different stagings and propellants (LOx/LH2, LOx/LCH4, LOx/LC3H8, subcooled LOx/LCH4) are considered, evaluated and compared. First sizing of a broad range of launcher versions are based on structural index derived from existing stages. -
Corporate Initiative for Space Tourism
UNIVERSITY OF LJUBLJANA FACULTY OF ECONOMICS MASTER’S THESIS “OUT OF THIS WORLD” BUSINESS: CORPORATE INITIATIVE FOR SPACE TOURISM Ljubljana, March 2014 JAN KRIŠTOF RAMOVŠ AUTHORSHIP STATEMENT The undersigned Jan K. Ramovš, a student at the University of Ljubljana, Faculty of Economics, (hereafter: FELU), declare that I am the author of the master’s thesis entitled “Out Of This World” Business: Corporate Initiative for Space Tourism, written under supervision of Prof. Dr. Metka Tekavčič. In accordance with the Copyright and Related Rights Act (Official Gazette of the Republic of Slovenia, Nr. 21/1995 with changes and amendments) I allow the text of my master’s thesis to be published on the FELU website. I further declare the text of my master’s thesis to be based on the results of my own research; the text of my master’s thesis to be language-edited and technically in adherence with the FELU’s Technical Guidelines for Written Works which means that I o cited and / or quoted works and opinions of other authors in my master’s thesis in accordance with the FELU’s Technical Guidelines for Written Works and o obtained (and referred to in my master’s thesis) all the necessary permits to use the works of other authors which are entirely (in written or graphical form) used in my text; to be aware of the fact that plagiarism (in written or graphical form) is a criminal offence and can be prosecuted in accordance with the Criminal Code (Official Gazette of the Republic of Slovenia, Nr. 55/2008 with changes and amendments); to be aware of the consequences a proven plagiarism charge based on the submitted master’s thesis could have for my status at the FELU in accordance with the relevant FELU Rules on Master’s Thesis. -
Supersonic Retropropulsion Wind Tunnel Testing
NASA/TM—2012-217746 AIAA–2012–401 Entry, Descent, and Landing With Propulsive Deceleration: Supersonic Retropropulsion Wind Tunnel Testing Bryan Palaszewski Glenn Research Center, Cleveland, Ohio December 2012 NASA STI Program . in Profi le Since its founding, NASA has been dedicated to the • CONFERENCE PUBLICATION. Collected advancement of aeronautics and space science. The papers from scientifi c and technical NASA Scientifi c and Technical Information (STI) conferences, symposia, seminars, or other program plays a key part in helping NASA maintain meetings sponsored or cosponsored by NASA. this important role. • SPECIAL PUBLICATION. Scientifi c, The NASA STI Program operates under the auspices technical, or historical information from of the Agency Chief Information Offi cer. It collects, NASA programs, projects, and missions, often organizes, provides for archiving, and disseminates concerned with subjects having substantial NASA’s STI. The NASA STI program provides access public interest. to the NASA Aeronautics and Space Database and its public interface, the NASA Technical Reports • TECHNICAL TRANSLATION. English- Server, thus providing one of the largest collections language translations of foreign scientifi c and of aeronautical and space science STI in the world. technical material pertinent to NASA’s mission. Results are published in both non-NASA channels and by NASA in the NASA STI Report Series, which Specialized services also include creating custom includes the following report types: thesauri, building customized databases, organizing and publishing research results. • TECHNICAL PUBLICATION. Reports of completed research or a major signifi cant phase For more information about the NASA STI of research that present the results of NASA program, see the following: programs and include extensive data or theoretical analysis. -
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. -
ESPA Ring Datasheet
PAYLOAD ADAPTERS | ESPA ESPA THE EVOLVED SECONDARY PAYLOAD ADAPTER ESPA mounts to the standard NSSL (formerly EELV) interface bolt pattern (Atlas V, Falcon 9, Delta IV, OmegA, Vulcan, Courtesy of Lockheed Martin New Glenn) and is a drop-in component in the launch stack. Small payloads mount to ESPA ports featuring either a Ø15-inch bolt circle with 24 fasteners or a 4-point mount with pads at each corner of a 15-inch square; both of these interfaces have become small satellite standards. ESPA is qualified to carry 567 lbs (257 kg), and a Heavy interface Courtesy of NASA (with Ø5/16” fastener hardware) has been introduced with a capacity of 991 lbs (450 kg). All small satellite mass capabilities require the center of gravity (CG) to be within 20 inches (50.8 cm) of the ESPA port surface. Alternative configurations can be accommodated. ESPA GRANDE ESPA Grande is a more capable version of ESPA with Ø24-inch ports; the ring height is typically 42 inches. The Ø24-inch port has been qualified by test to Courtesy of ORBCOMM & Sierra Nevada Corp. carry small satellites up to 1543 lb (700 kg). ESPA ESPA IS ADAPTABLE TO UNIQUE MISSION REQUIREMENTS • The Air Force’s STP-1 mission delivered multiple small satellites on an Atlas V. • NASA’s Lunar Crater Observation and Sensing Satellite (LCROSS): ESPA was the spacecraft hub for the LCROSS shepherding satellite in 2009. • ORBCOMM Generation 2 (OG2) launched stacks of two and three ESPA Grandes on two different Falcon 9 missions and in total deployed 17 satellites. -
Grand Challenges and Vast Opportunities
Near Term Space Settlement: Risk Reduction Missions Kent Nebergall Macroinvent.com Mars Society Conference, 2017 © 2017 Kent Nebergall All rights reserved. The Grand Challenges of Space Settlement (2014) Launch/LEO Deep Space Moon/Mars Settlement Affordable Launch Solar Flares Moon Landing Air/Water Large Vehicle Launch GCR: Cell Damage Mars EDL Fuel Mass Fraction beyond Medication/ Spacesuit Lifespan Power Earth Orbit (Refueling) Food Expiration Space Junk Life Support Closed Reliable Ascent Vehicle Food Loop Microgravity Medical Entropy Reliable Return Vehicle Assembly (health issues) in Orbit Psychology Flight to Earth Mining Mechanical Entropy Earth Reentry Manufacture Funded Projects NASA Focus Commercial Focus Gaps © 2017 Kent Nebergall All rights reserved. Preparing for the NewSpace Revolution Year Energy Information Invention Affordability 2017 Falcon 9 Block 5 Falcon Heavy 2018 Crewed Dragon Blockchain Matures Crewed Starliner 2019 LEO Internet 2020 Low Latency Global Bigelow BA330 New Glenn Internet Satellites 50 MT satellites have two 2021 Quantum Computing? launch platforms, both AI Capabilities cheap and rapid NASA Space turnaround ISS Replacement 2022 Nuclear Power Groundwork Nuclear propulsion © 2017 Kent Nebergall All rights reserved. NASA Nuclear Projects BWXT Nuclear Thermal Rocket TDU 10-100 KW KiloPower 1-10 KW © 2017 Kent Nebergall All rights reserved. Driving Critical Mass for the NewSpace Revolution • Deep Space Risk Reduction Missions • Organizing for Direct Solutions Deep Space DragonLab 1 • Exposure test items that are altered when exposed to deep space to test the risk • Launch into high (lunar distance apogee) orbit to expose to unfiltered cosmic rays and solar flares • After mission simulating full trip to/on/from Mars, return the cargo and examine results. -
Since Our Last SIA Member News Summary, Press Releases and Posts
SIA PRESIDENT’S REPORT – MEMBER NEWS FOR OCT 2020 Since our last SIA Member News Summary, press releases and posts from many SIA Members including AGI, Blue Origin, Hawkeye 360, Inmarsat, Integrasys, Iridium, Kymeta, Lockheed Martin, OneWeb, Planet, SES, SpaceX, Spire, Telesat and XTAR have released news. Please see the summary of stories and postings below and click on the COMPANY LINK for more details. PLANET (above) On Oct 28th, Planet announced the successful launch of nine Flock 4e latest-generation SuperDove satellites onboard a Rocket Lab Electron rocket from New Zealand. The Flock 4e’ SuperDoves were deployed into an approximately 500 km, morning-crossing Sun Synchronous Orbit (SSO), joining the rest of the constellation providing medium-resolution Earth imagery with unprecedented coverage and frequency of update. The nine SuperDoves are equipped with 8 spectral bands that provide high image quality and accurate surface reflectance values for advanced algorithms and time-series analysis. Planet’s SuperDoves are also interoperable with publicly available imagery, like Copernicus’ Sentinel-2, enabling innovative applications and use cases. (Photo credit: Image courtesy of Planet and Rocket Lab) AGI On Oct 26th, Analytical Graphics Inc., (AGI) announced that AGI and Ansys, a leading innovator of engineering software, had entered into a definitive acquisition agreement. According to the terms of the agreement, Ansys would acquire AGI. The purchase price for the transaction, which is expected to close in Q4 of 2020 pending regulatory clearance, is $700 million. SPACEX On Oct 24th, SpaceX announced that a Falcon 9 rocket had launched 60 Starlink satellites to orbit from Space Launch Complex 40 (SLC-40) at Cape Canaveral Air Force Station in Florida.