Construct Functional Strap-On Booster Motor Pods
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Flying Model Rocket Catalog
Flying Model Rocket Catalog TM TABLE OF CONTENTS Model Rocket Basics . 5 Fly Big with Advanced Rockets/Pro Series II . 66 Get Started with Launch Sets . 10 Model Rocket Engine Performance Chart . 70 Easy to Build Beginner Rockets . 16 Engine Time/Thrust Curves . 72-73 Challenge Yourself a Little More! . 22 Building Supplies . 84 Payload Rockets . 30 Altitude Tracking . 82 Multi-Stage Rockets . 34 Estes Education . 86 Fun Recovery Rockets . 40 Bulk Packs for Education . 88 Designer Signature Series . 45 Lifetime Launch System . 94 Imagine New Worlds with Space Voyagers . 46 Phantom Classroom Demonstrator Rocket . 96 Destination Mars™ Rockets . 50 Rocket Science Starter Set . 98 Space Corps™ Rockets . 54 Model Rocket Safety Code . 100 Scale Model Rockets . 58 Index . 102 Welcome to the exciting world of model rocketry. now this rocket science! here is no thrill quite like launching a model rocket you have built, watching it streak skyward, reach apogee (peak altitude), then gently Treturn to earth on its parachute. In a very real sense, model rocketeers experience the same excitement felt by America’s space scientists and astronauts as they push humankind’s horizons relentlessly forward to the stars. The best way to get started is with an Estes® launch set or starter set (see pages 10-15). Each launch set has nearly everything you need to build and fly your first rocket. Estes Industries, LLC encourages membership As you increase your rocketry skills, you can progress to new and exciting in the National Association projects including multi-stage rockets, payload experiments and scale models. of Rocketry for the active Whether you are a hobby beginner or expert, Estes Industries will help you model rocketry enthusiast. -
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. -
Water Rocket Booklet
A guide to building and understanding the physics of Water Rockets Version 1.02 June 2007 Warning: Water Rocketeering is a potentially dangerous activity and individuals following the instructions herein do so at their own risk. Exclusion of liability: NPL Management Limited cannot exclude the risk of accident and, for this reason, hereby exclude, to the maximum extent permissible by law, any and all liability for loss, damage, or harm, howsoever arising. Contents WATER ROCKETS SECTION 1: WHAT IS A WATER ROCKET? 1 SECTION 3: LAUNCHERS 9 SECTION 4: OPTIMISING ROCKET DESIGN 15 SECTION 5: TESTING YOUR ROCKET 24 SECTION 6: PHYSICS OF A WATER ROCKET 29 SECTION 7: COMPUTER SIMULATION 32 SECTION 8: SAFETY 37 SECTION 9: USEFUL INFORMATION 38 SECTION 10: SOME INTERESTING DETAILS 40 Copyright and Reproduction Michael de Podesta hereby asserts his right to be identified as author of this booklet. The copyright of this booklet is owned by NPL. Michael de Podesta and NPL grant permission to reproduce the booklet in part or in whole for any not-for-profit educational activity, but you must acknowledge both the author and the copyright owner. Acknowledgements I began writing this guide to support people entering the NPL Water Rocket Competition. So the first acknowledgement has to be to Dr. Nick McCormick, who founded the competition many years ago and who is still the driving force behind the activity at NPL. Nick’s instinct for physics and fun has brought pleasure to thousands. The inspiration to actually begin writing this document instead of just saying that someone ought to do it, was provided by Andrew Hanson. -
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. -
Model Rocketry Technical Manual Welcome to the Exciting World of Estes Model Rocketry!
™ Model Rocketry Technical Manual Welcome to the Exciting World of Estes Model Rocketry! By William Simon Updated and edited by Thomas Beach and Joyce Guzik EstesEducator.com ® [email protected] 800.820.0202 © 2012 Estes-Cox Corp. INTRODUCTION TABLE OF CONTENTS Topic Page Welcome to the exciting world of Estes® Why Estes Model Rocketry 3 A Safe Program 3 Your First Model Rocket 3 model rocketry! This technical manual was Construction Techniques 3 Types of Glues 3 written to provide both an easy-to-follow guide Finishing 6 Stability 7 for the beginner and a reference for the experi- Swing Test For Stability 8 Preparing For Flight 8 enced rocket enthusiast. Here you’ll find the Igniter Installation 9 Launching 9 answers to the most frequently asked ques- Countdown Checklist 10 Tracking 10 Trackers 10 tions. More complete technical information on Recovery Systems 11 Multi-Staging 11 all the subjects can be found on the Estes® Clustering 13 Model Rocket Engines 14 website (www.estesrockets.com) and the Estes NAR Safety Code 15 Publications back cover Educator™ website (www.esteseducator.com) *Copyright 1970, 1989,1993, 2003 Estes-Cox Corp. All Rights Reserved. Estes is a registered trademark of Estes-Cox Corp. 2 WHY ESTES MODEL ROCKETRY? As your knowledge of rocketry and your modeling skills increase you can move up to building higher skill level models, The hobby of model rocketry originated at the dawn of the and eventually to building your own custom designs from parts space age in the late 1950’s. Seeing space boosters carry the available in the Estes catalog. -
Economic Benefits of Reusable Launch Vehicles for Space Debris Removal
68th International Astronautical Congress (IAC), Adelaide, Australia, 25-29 September 2017. Copyright ©2017 by the International Astronautical Federation (IAF). All rights reserved. IAC-17-A6.8.5 Economic Benefits of Reusable Launch Vehicles for Space Debris Removal Matthew P. Richardsona*, Dominic W.F. Hardyb a Department of Aeronautics and Astronautics, University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo, Japan 113- 8656, [email protected] b Nova Systems, 53 Ellenborough Street, Ipswich, Queensland, Australia 4305, [email protected] * Corresponding Author Abstract An analysis of cost savings which could be realized on active debris removal missions through the use of reusable launch vehicles has been performed. Launch vehicle price estimates were established for three levels of reusable launch vehicle development, based on varying levels of technological development and market competition. An expendable launch vehicle price estimate was also established as a point of comparison. These price estimates were used to form two separate debris removal mission cost estimates, based on previously-proposed debris removal mission concepts. The results of this analysis indicate that reusable launch vehicles could reduce launch prices to levels between 19.6% and 92.8% cheaper than expendable launch vehicles, depending on the level of RLV maturity. It was also determined that a reusable launch vehicle could be used to realize total active debris removal mission cost savings of between 2.8% (for a partially reusable launch -
Investigation of Surface Roughness on the Transient Point of a Blunt Nose Cone
Investigation of Surface Roughness on the Transient Point of a Blunt Nose Cone A Project Presented to The Faculty of the Department of Aerospace Engineering San Jose State University In Partial Fulfillment to the Requirements of the Degree Master of Science in Aerospace Engineering By Terrence Soares Approved by Dr. Periklis E. Papadopoulos Faculty Advisor ©May 2020 Table of Contents Table of contents i List of figures iii List of tables iv Abstract v Nomenclature v Symbols vi Greek symbols vi Subscripts vi Acronyms vi 1. Introduction 1 1.1 Motivation 1 1.2 Literature 1 1.2.1 Additive manufacturing 1 1.2.2 Surface roughness 5 1.2.3 Blunt nose cone angle 6 1.2.4 Boundary layer transitions 9 1.2.5 Shock wave - oblique v expansion 10 1.2.6 Turbulent heating 12 1.3 Project proposal 13 1.4 Methodology 13 2. Experimental tools and methods 17 2.1 Blunt cone designs 17 2.2 3D Models 21 2.3 Simulations 22 2.3.1 Enclosure 22 2.3.2 Mesh 24 2.3.3 Setup 26 3. Results 28 3.1 Reda results 28 3.2 ANSYS results 28 3.2.1 Cone angle 30 degrees 28 3.2.2 Cone angle 45 degrees 30 3.2.3 Cone angle 60 degrees 32 4. Discussion 35 4.1 Reda vs base model CFD 35 4.2 CFD nose cone comparison 35 i 4.2.1 Surface roughness 35 4.2.2 Nose cone angle 36 4.2.3 Transient point 37 5. Conclusion 38 6. -
Status of Space Shuttle External Tank, Solid Rocket Booster, and Main Engine
The Space Congress® Proceedings 1979 (16th) Space: The Best Is Yet To Come Apr 1st, 8:00 AM Status of Space Shuttle External Tank, Solid Rocket Booster, and Main Engine Robert E. Lindstrom Manager, Shuttle Projects Office, Marshal I Space Fl ight Center Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Lindstrom, Robert E., "Status of Space Shuttle External Tank, Solid Rocket Booster, and Main Engine" (1979). The Space Congress® Proceedings. 4. https://commons.erau.edu/space-congress-proceedings/proceedings-1979-16th/session-1/4 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 SPACE SHUTTLE EXTERNAL TANK SOLID ROCKET BOOSTER and MAIN ENGINE Mr. Robert E. Lindstrom Manager, Shuttle Projects Office Marshal I Space Fl ight Center ABSTRACT success. The Sol id Rocket Booster, whose recovery and reusability make the Space Shuttle economically The paper will cover the current status of three feasible, provides the additional power necessary major propulsion elements for the Space Transporta to boost the Shuttle off the launch pad towards tion System: the Space Shuttle Main Engine (SSME), orbit. the External Tank (ET) and the Solid Rocket Booster (SRB). Presented will be the Test and Manufactur ing experience in the last year, the Test and Manu EXTERNAL TANK facturing plans for the coming year and the current status of hardware to support the first manned or The External Tank is that element of the Space bital fl ight. -
Finding of No Significant Impact for Boost-Back and Landing of Falcon Heavy Boosters at Landing Zone-1, Cape Canaveral Air Force Station, Florida
DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Office of Commercial Space Transportation Adoption of the Environmental Assessment and Finding of No Significant Impact for Boost-back and Landing of Falcon Heavy Boosters at Landing Zone-1, Cape Canaveral Air Force Station, Florida Summary The U.S. Air Force (USAF) acted as the lead agency, and the Federal Aviation Administration (FAA) was a cooperating agency, in the preparation of the February 2017 Supplemental Environmental Assessment to the December 2014 EA for Space Exploration Technologies Vertical Landing of the Falcon Vehicle and Construction at Launch Complex 13 at Cape Canaveral Air Force Station, Florida (2017 SEA), which analyzed the potential environmental impacts of Space Exploration Technologies Corp. (SpaceX) conducting boost-backs and landings of up to three Falcon Heavy boosters at Landing Zone 1 (LZ-1) at Cape Canaveral Air Force Station (CCAFS), Florida during the same mission. LZ-1 is also known as Launch Complex 13 (LC-13). The scope of the action analyzed in the 2017 SEA also included the option of landing one or two Falcon Heavy boosters on SpaceX’s autonomous droneship in the Atlantic Ocean. The 2017 SEA also addressed construction of two landing pads as well as construction and operation of a processing and testing facility for SpaceX’s Dragon spacecraft. The National Aeronautics and Space Administration (NASA) also participated as a cooperating agency in the preparation of the 2017 SEA. The 2017 SEA was prepared in accordance with the National Environmental Policy Act of 1969, as amended (NEPA; 42 United States Code [U.S.C.] § 4321 et seq.); Council on Environmental Quality NEPA implementing regulations (40 Code of Federal Regulations [CFR] parts 1500 to 1508); the USAF’s Environmental Impact Analysis Process (32 CFR 989); and FAA Order 1050.1F, Environmental Impacts: Policies and Procedures. -
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. -
Shuttle Fact Sheet
NASA Facts National Aeronautics and Space Administration Marshall Space Flight Center Huntsville, Alabama 35812 FS-2003-06-62-MSFC June 2003 Space Shuttle Propulsion Systems managed by the Marshall Space Flight Center The Space Shuttle is NASA’s reusable space vehicle designed for transport of people, spacecraft and equipment to and from Earth orbit. The propulsion elements of the Space Shuttle, including the Main Engine, External Tank and Solid Rocket Boosters that propel the Space Shuttle into orbit are managed at the Marshall Space Flight Center in Huntsville, Alabama. The Space Shuttle Main Engines number of flights between required overhauls. The Space The three Space Shuttle Main Engines are clustered Shuttle Main Engines are built by Rocketdyne Propulsion at the aft end of the orbiter and have a combined thrust and Power Division of the Boeing Company in Canoga of more than 1.2 million pounds (5.4 million newtons) Park, Calif. The engine turbopump is built by Pratt and at sea level. They are high performance, liquid propel- Whitney of West Palm Beach, Fla. The turbopumps are lant rocket engines whose thrust can be varied over made by Pratt and Whitney of West Palm Beach, Fla. a range of 65 to 109 percent of their rated The External Tank Low-Pressure power level. They are Oxidizer Oxidizer The External Tank the world’s first reus- Preburner Turbopump is a giant cylinder High-Pressure able rocket engines Main Injector container with a Oxidizer Turbopump and are 14 feet long Fuel rounded, or ogive, (4.3 meters) and 7.5 Preburner top -- higher than a Low-Pressure feet (2.3 meters) in Fuel Turbopump Hot Gas 15-story building, with diameter at the nozzle Manifold a length of 154 feet exit.