Space Innovators Confident They Are Building America's Next Large
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Douglas Missile & Space Systems Division
·, THE THOR HISTORY. MAY 1963 DOUGLAS REPORT SM-41860 APPROVED BY: W.H.. HOOPER CHIEF, THOR SYSTEMS ENGINEERING AEROSPACE SYSTEMS ENGINEERING DOUGLAS MISSILE & SPACE SYSTEMS DIVISION ABSTRACT This history is intended as a quick orientation source and as n ready-reference for review of the Thor and its sys tems. The report briefly states the development of Thor, sur'lli-:arizes and chronicles Thor missile and booster launch inGs, provides illustrations and descriptions of the vehicle systcn1s, relates their genealogy, explains sane of the per fon:iance capabilities of the Thor and Thor-based vehicles used, and focuses attention to the exploration of space by Douelas Aircraf't Company, Inc. (DAC). iii PREFACE The purpose of The Thor History is to survey the launch record of the Thor Weapon, Special Weapon, and Space Systems; give a systematic account of the major events; and review Thor's participation in the military and space programs of this nation. The period covered is from December 27, 1955, the date of the first contract award, through May, 1963. V �LE OF CONTENTS Page Contract'Award . • • • • • • • • • • • • • • • • • • • • • • • • • 1 Background • • • • • • • • • • • • • • • • • • • • • • • • • • • • l Basic Or�anization and Objectives • • • • • • • • • • • • • • • • 1 Basic Developmenta� Philosophy . • • • • • • • • • • • • • • • • • 2 Early Research and Development Launches • • • ·• • • • • • • • • • 4 Transition to ICBM with Space Capabilities--Multi-Stage Vehicles . 6 Initial Lunar and Space Probes ••••••• • • • • • • • -
Materials for Liquid Propulsion Systems
https://ntrs.nasa.gov/search.jsp?R=20160008869 2019-08-29T17:47:59+00:00Z CHAPTER 12 Materials for Liquid Propulsion Systems John A. Halchak Consultant, Los Angeles, California James L. Cannon NASA Marshall Space Flight Center, Huntsville, Alabama Corey Brown Aerojet-Rocketdyne, West Palm Beach, Florida 12.1 Introduction Earth to orbit launch vehicles are propelled by rocket engines and motors, both liquid and solid. This chapter will discuss liquid engines. The heart of a launch vehicle is its engine. The remainder of the vehicle (with the notable exceptions of the payload and guidance system) is an aero structure to support the propellant tanks which provide the fuel and oxidizer to feed the engine or engines. The basic principle behind a rocket engine is straightforward. The engine is a means to convert potential thermochemical energy of one or more propellants into exhaust jet kinetic energy. Fuel and oxidizer are burned in a combustion chamber where they create hot gases under high pressure. These hot gases are allowed to expand through a nozzle. The molecules of hot gas are first constricted by the throat of the nozzle (de-Laval nozzle) which forces them to accelerate; then as the nozzle flares outwards, they expand and further accelerate. It is the mass of the combustion gases times their velocity, reacting against the walls of the combustion chamber and nozzle, which produce thrust according to Newton’s third law: for every action there is an equal and opposite reaction. [1] Solid rocket motors are cheaper to manufacture and offer good values for their cost. -
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. -
Orbital Fueling Architectures Leveraging Commercial Launch Vehicles for More Affordable Human Exploration
ORBITAL FUELING ARCHITECTURES LEVERAGING COMMERCIAL LAUNCH VEHICLES FOR MORE AFFORDABLE HUMAN EXPLORATION by DANIEL J TIFFIN Submitted in partial fulfillment of the requirements for the degree of: Master of Science Department of Mechanical and Aerospace Engineering CASE WESTERN RESERVE UNIVERSITY January, 2020 CASE WESTERN RESERVE UNIVERSITY SCHOOL OF GRADUATE STUDIES We hereby approve the thesis of DANIEL JOSEPH TIFFIN Candidate for the degree of Master of Science*. Committee Chair Paul Barnhart, PhD Committee Member Sunniva Collins, PhD Committee Member Yasuhiro Kamotani, PhD Date of Defense 21 November, 2019 *We also certify that written approval has been obtained for any proprietary material contained therein. 2 Table of Contents List of Tables................................................................................................................... 5 List of Figures ................................................................................................................. 6 List of Abbreviations ....................................................................................................... 8 1. Introduction and Background.................................................................................. 14 1.1 Human Exploration Campaigns ....................................................................... 21 1.1.1. Previous Mars Architectures ..................................................................... 21 1.1.2. Latest Mars Architecture ......................................................................... -
Interstellar Probe on Space Launch System (Sls)
INTERSTELLAR PROBE ON SPACE LAUNCH SYSTEM (SLS) David Alan Smith SLS Spacecraft/Payload Integration & Evolution (SPIE) NASA-MSFC December 13, 2019 0497 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft. Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter Core Stage Core Stage Core Stage Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo > 26 t (57k lbs) > 26 t (57k lbs) 38–41 t (84k-90k lbs) 41-44 t (90k–97k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon Launch in the late 2020s and early 2030s 0497 IS THIS ROCKET REAL? 0497 SLS BLOCK 1 CONFIGURATION Launch Abort System (LAS) Utah, Alabama, Florida Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle RL10 Engine Lockheed Martin, 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Florida Booster (2) Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) Utah, KSC Boeing/United Launch Alliance, California, Alabama Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama Core Stage & Avionics Boeing Louisiana, Alabama RS-25 Engine (4) -
Delta IV Parker Solar Probe Mission Booklet
A United Launch Alliance (ULA) Delta IV Heavy what is the source of high-energy solar particles. MISSION rocket will deliver NASA’s Parker Solar Probe to Parker Solar Probe will make 24 elliptical orbits an interplanetary trajectory to the sun. Liftoff of the sun and use seven flybys of Venus to will occur from Space Launch Complex-37 at shrink the orbit closer to the sun during the Cape Canaveral Air Force Station, Florida. NASA seven-year mission. selected ULA’s Delta IV Heavy for its unique MISSION ability to deliver the necessary energy to begin The probe will fly seven times closer to the the Parker Solar Probe’s journey to the sun. sun than any spacecraft before, a mere 3.9 million miles above the surface which is about 4 OVERVIEW The Parker percent the distance from the sun to the Earth. Solar Probe will At its closest approach, Parker Solar Probe will make repeated reach a top speed of 430,000 miles per hour journeys into the or 120 miles per second, making it the fastest sun’s corona and spacecraft in history. The incredible velocity trace the flow of is necessary so that the spacecraft does not energy to answer fall into the sun during the close approaches. fundamental Temperatures will climb to 2,500 degrees questions such Fahrenheit, but the science instruments will as why the solar remain at room temperature behind a 4.5-inch- atmosphere is thick carbon composite shield. dramatically Image courtesy of NASA hotter than the The mission was named in honor of Dr. -
Space Coast Is Getting Busy: 6 New Rockets Coming to Cape Canaveral, KSC
4/16/2019 Space Coast is getting busy: 6 new rockets coming to Cape Canaveral, KSC Space Coast is getting busy: 6 new rockets coming to Cape Canaveral, Kennedy Space Center Emre Kelly, Florida Today Published 4:04 p.m. ET April 11, 2019 | Updated 7:53 a.m. ET April 12, 2019 COLORADO SPRINGS, Colo. – If schedules hold, the Space Coast will live up to its name over the next two years as a half-dozen new rockets target launches from sites peppered across the Eastern Range. Company, government and military officials here at the 35th Space Symposium, an annual space conference, have reaffirmed their plans to launch rockets ranging from more traditional heavy-lift behemoths to smaller vehicles that take advantage of new manufacturing technologies. Even if some of these schedules slip, at least one thing is apparent to several spaceflight experts here: The Eastern Range is seeing an unprecedented growth in commercial space companies and efforts. Space Launch System: 2020 NASA's Space Launch System rocket launches from Kennedy Space Center's pad 39B in this rendering by the agency. (Photo: NASA) NASA's long-awaited SLS, a multibillion-dollar rocket announced in 2011, is slated to become the most powerful launch vehicle in history if it can meet a stringent late 2020 deadline. The 322-foot-tall rocket is expected to launch on its first flight – Exploration Mission 1 – from Kennedy Space Center with an uncrewed Orion capsule for a mission around the moon, which fits in with the agency's wider goal of putting humans on the surface by 2024. -
Omega-3 Fatty Acids Fact Sheet for Consumers
Omega-3 Fatty Acids Fact Sheet for Consumers What are omega-3 fatty acids and what do they do? Omega-3 fatty acids are found in foods, such as fish and flaxseed, and in dietary supplements, such as fish oil. The three main omega-3 fatty acids are alpha-linolenic acid (ALA), eicosapentaenoic acid (EPA), and docosahexaenoic acid (DHA). ALA is found mainly in plant oils such as flaxseed, soybean, and canola oils. DHA and EPA are found in fish and other seafood. ALA is an essential fatty acid, meaning that your body can’t make it, so you must get it from the foods and beverages you consume. Your body can convert some ALA into EPA and then to DHA, but only in very small amounts. Therefore, getting EPA and DHA from foods (and dietary supplements if you take them) is the only practical way to increase levels of these omega-3 fatty acids in your body. Omega-3s are important components of the membranes that surround each cell in your body. DHA levels are especially high in retina (eye), brain, and sperm cells. Omega-3s also provide calories to give your body energy and have many functions in your heart, blood vessels, lungs, immune system, and endocrine system (the network of hormone-producing glands). How much omega-3s do I need? Omega-3s are found in foods Experts have not established recommended amounts for omega-3 fatty acids, except such as fatty fish and plant oils. for ALA. Average daily recommended amounts for ALA are listed below in grams (g). -
An Investigation of the Performance Potential of A
AN INVESTIGATION OF THE PERFORMANCE POTENTIAL OF A LIQUID OXYGEN EXPANDER CYCLE ROCKET ENGINE by DYLAN THOMAS STAPP RICHARD D. BRANAM, COMMITTEE CHAIR SEMIH M. OLCMEN AJAY K. AGRAWAL A THESIS Submitted in partial fulfillment of the requirements for the degree of Master of Science in the Department of Aerospace Engineering and Mechanics in the Graduate School of The University of Alabama TUSCALOOSA, ALABAMA 2016 Copyright Dylan Thomas Stapp 2016 ALL RIGHTS RESERVED ABSTRACT This research effort sought to examine the performance potential of a dual-expander cycle liquid oxygen-hydrogen engine with a conventional bell nozzle geometry. The analysis was performed using the NASA Numerical Propulsion System Simulation (NPSS) software to develop a full steady-state model of the engine concept. Validation for the theoretical engine model was completed using the same methodology to build a steady-state model of an RL10A-3- 3A single expander cycle rocket engine with corroborating data from a similar modeling project performed at the NASA Glenn Research Center. Previous research performed at NASA and the Air Force Institute of Technology (AFIT) has identified the potential of dual-expander cycle technology to specifically improve the efficiency and capability of upper-stage liquid rocket engines. Dual-expander cycles also eliminate critical failure modes and design limitations present for single-expander cycle engines. This research seeks to identify potential LOX Expander Cycle (LEC) engine designs that exceed the performance of the current state of the art RL10B-2 engine flown on Centaur upper-stages. Results of this research found that the LEC engine concept achieved a 21.2% increase in engine thrust with a decrease in engine length and diameter of 52.0% and 15.8% respectively compared to the RL10B-2 engine. -
Hrp Series Water Source Hi-Rise Vertical Stacked Heat Pumps
HRP SERIES WATER SOURCE HI-RISE VERTICAL STACKED HEAT PUMPS TECHNICAL CATALOGUE DEVELOPMENT “D” HRP SERIES | OMEGA TABLE OF CONTENTS 1. PRODUCT OVERVIEW .......................................................................................................................... 1 1.1 Key Features .......................................................................................................................................................3 1.2 Engineering Design ...........................................................................................................................................4 1.3 System Flow Options .........................................................................................................................................6 1.4 Flow Direction Details .......................................................................................................................................7 2. PRODUCT DETAILS ............................................................................................................................. 9 2.1 Cabinet Design .................................................................................................................................................10 2.2 Unit Details ........................................................................................................................................................11 2.3 Chassis Details .................................................................................................................................................13 -
Do Not Circulate
LA-7328-PR Progress Report a . Laser Fusion Program July 1—December 31, 1977 ,- .. .. .. ..-— — DO NOT CIRCULATE PERMANENT RETENTION ! REQUIREDBY CONTRACT v LOS ALAMOS SCIENTIFIC LABORATORY Lail!lik — post Office Box 1663 Los Alamos, New Mexico 87545 An AffumativeAction/EqualOpportunityEmployex . The four most recent reports in this series,un- classified, are LA-65 10-PR, LAY6 16-PR, LA4834-PR, and LA-6982-PR. This work was supported by the US Department of Energy, Office of Laser Fusion. TM. report was prep.rcd as m .CLWUII1O( work sponsored by the United SUICS Go”enlme”l. Neither the Un,ted Stiles I nor the United Slates Department cd Enersy. nor any of their employees. nor any 0( their CO.114C10rS. subcontrar tom. or their ●w.loyecs. makes any warranty. .xD,,!s O, irnPlled. ., P .isume. any Iesal Ii. biiity or responsibkbw for the accuracy. cmnpletcncm. y usefulness of any information. app.; .t.s. product. or Pro..= dl=losed. or rrpreacnm that its w would “.1 i“fri”le privately owned rlthls. UNITED STATES DEPARTMENT OF CNCRGV CONTRACT W-7408 -CNO. S6 LA-7328-PR Progress Report UC-21 IssI,W: December 1978 . Laser Fusion Program at LASL July 1—December 31, 1977 Compiled by Frederick Skoberne 4 .! L-. — .— - . ABSTRACT . ...”” 1 SUMMARY . ...0000oo 2 Introduction . 2 CO, Laser Program . 2 Antares . 2 CO, Laser Technology . 3 Laser Fusion Theory, Experiments, and Target Design . 3 Laser Fusion Target Fabrication . 4 1, CO, LASER PROGRAM . 6 Single-Beam System . 6 llvo-Beam System . 6 Eight-Beam System . 8 II. ANTARES-HIGH-ENERGY GAS IJM3ERFAClLITY . -
Additive Manufacturing Development Methodology for Liquid Rocket Engines
Additive Manufacturing Development Methodology for Liquid Rocket Engines Quality in the Space and Defense Industry Forum Cape Canaveral, FL March 8, 2016 Jeff Haynes Aerojet Rocketdyne Distribution Statement A: Approved for public release, distribution is unlimited Presentation Outline •The additive manufacturing “opportunity” •Specific additive manufacturing process considerations •Scale up challenges •Aerojet Rocketdyne development and production approach •Considerations and gaps to be closed for production Distribution Statement A: Approved for public release, distribution is unlimited Demonstrated Benefits of Additive Manufacturing Liquid Rocket Engine Attributes Additive Manufacturing Low production volumes Print parts when needed High complexity, compact designs Complexity adds no cost High value = high quality levels Bulk material like wrought not cast Additive Manufacturing • Part count reduction • No plating / no braze • No tooling • 60% lead time savings • 70% cost savings • Reduced weight 9-lbs Heritage Saturn V F1 Gas Generator Injector Printed F1 GG Injector (2009) Early Demonstrated Realization of Potential Distribution Statement A: Approved for public release, distribution is unlimited Demonstrated Benefits of Additive Manufacturing Transforming heritage engines and … enabling new ones 14-inch • Complex injector assemblies diameter Reduce part count Eliminates long lead forgings Eliminates high touch labor machining RS-25 Ball Shaft (left) Eliminates hundreds of braze joints RL10 Main Injector (right) • Sheet