The History of Solid-Propellant Rocketry: What We Do and Do Not Know
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The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
Nasa X-15 Program
5 24,132 6 9 NASA X-15 PROGRAM By: T.D. Barnes - NASA Contractor - 1960s NASA contractors for the X-15 program were Bendix Field Engineering followed by Unitec, Inc. The NASA High Range Tracking stations were located at Ely and Beatty Nevada with main control being at Dryden/Edwards AFB in California. Personnel at the tracking stations consisted of a Station Manager, a Technical Advisor, and field engineers for the Mod-2 Radar, Data Transmission System, Communications, Telemetry, and Plant Maintenance/Generators. NASA had a site monitor at each tracking station to monitor our contractor operations. Though supporting flights of the X-15 was their main objective, they also participated in flights of the XB-70, the three Lifting Bodies, experimental Lunar Landing vehicles, and an occasional A-12/YF-12/SR-71 Blackbird flight. On mission days a NASA van picked up each member of the crew at their residence for the 4:20 a.m. trip to the tracking station 18 miles North of Beatty on the Tonopah Highway. Upon arrival each performed preflight calibrations and setup of their various systems. The liftoff of the B-52, with the X-15 tucked beneath its wing, seldom occurred after 9:00 a.m. due to the heat effect of the Mojave Desert making it difficult for the planes to acquire altitude. At approximately 0800 hours two pilots from Dryden would proceed uprange to evaluate the condition of the dry lake beds in the event of an emergency landing of the X-15 (always buzzing our station on the way up and back). -
Rocket Propulsion Fundamentals 2
https://ntrs.nasa.gov/search.jsp?R=20140002716 2019-08-29T14:36:45+00:00Z Liquid Propulsion Systems – Evolution & Advancements Launch Vehicle Propulsion & Systems LPTC Liquid Propulsion Technical Committee Rick Ballard Liquid Engine Systems Lead SLS Liquid Engines Office NASA / MSFC All rights reserved. No part of this publication may be reproduced, distributed, or transmitted, unless for course participation and to a paid course student, in any form or by any means, or stored in a database or retrieval system, without the prior written permission of AIAA and/or course instructor. Contact the American Institute of Aeronautics and Astronautics, Professional Development Program, Suite 500, 1801 Alexander Bell Drive, Reston, VA 20191-4344 Modules 1. Rocket Propulsion Fundamentals 2. LRE Applications 3. Liquid Propellants 4. Engine Power Cycles 5. Engine Components Module 1: Rocket Propulsion TOPICS Fundamentals • Thrust • Specific Impulse • Mixture Ratio • Isp vs. MR • Density vs. Isp • Propellant Mass vs. Volume Warning: Contents deal with math, • Area Ratio physics and thermodynamics. Be afraid…be very afraid… Terms A Area a Acceleration F Force (thrust) g Gravity constant (32.2 ft/sec2) I Impulse m Mass P Pressure Subscripts t Time a Ambient T Temperature c Chamber e Exit V Velocity o Initial state r Reaction ∆ Delta / Difference s Stagnation sp Specific ε Area Ratio t Throat or Total γ Ratio of specific heats Thrust (1/3) Rocket thrust can be explained using Newton’s 2nd and 3rd laws of motion. 2nd Law: a force applied to a body is equal to the mass of the body and its acceleration in the direction of the force. -
How to Make Gun Powder the Old Fashioned Way in Less Than 30 Minutes - Ask a Prepper
10/8/2019 How To Make Gun Powder The Old Fashioned Way in Less Than 30 Minutes - Ask a Prepper DIY Terms of Use Privacy Policy Ask a Prepper Search something.. Survival / Prepping Solutions My Instagram Feed Demo Facebook Demo HOME ALL ARTICLES EDITOR’S PICK SURVIVAL KNOWLEDGE HOW TO’S GUEST POSTS CONTACT ABOUT CLAUDE DAVIS Social media How To Make Gun Powder The Old Fashioned Way in Less Than 30 Minutes Share this article By James Walton Print this article Send e-mail December 30, 2016 14:33 FOLLOW US PREPPER RECOMMENDS IF YOU SEE THIS PLANT IN YOUR BACKYARD BURN IT IMMEDIATELY ENGINEERS CALL THIS “THE SOLAR PANEL KILLER” THIS BUG WILL KILL MOST by James Walton AMERICANS DURING THE NEXT CRISIS Would you believe that this powerful propellant, that has changed the world as we know it, was made as far back as 142 AD? 22LBS GONE IN 13 DAYS WITH THIS STRANGE “CARB-PAIRING” With that knowledge, how about the fact that it took nearly 1200 years for us to TRICK figure out how to use this technology in a gun. The history of this astounding 12X MORE EFFICIENT THAN substance is one that is inextricably tied to the human race. Imagine the great SOLAR PANELS? NEW battles and wars tied to this simple mixture of sulfur, carbon and potassium nitrate. INVENTION TAKES Mixed in the right ratios this mix becomes gunpowder. GREEK RITUAL REVERSES In this article, we are going to talk about the process of making gunpowder. DIABETES. DO THIS BEFORE BED! We have just become such a dependent bunch that the process, to most of us, seems like some type of magic that only a Merlin could conjure up. -
Privacy Statement Link at the Bottom of Aerojet Rocketdyne Websites
Privacy Notice Aerojet Rocketdyne – For external use Contents Introduction ...................................................................................................................... 3 Why we collect personal information? ............................................................................. 3 How we collect personal information? ............................................................................. 3 How we use information we collect? ............................................................................... 4 How we share your information? .................................................................................... 4 How we protect your personal information? ..................................................................... 4 How we collect consent? .............................................................................................. 4 How we provide you access? ........................................................................................ 4 How to contact Aerojet Rocketdyne privacy?.................................................................... 5 Collection of personal information .................................................................................. 5 Disclosure of personal information.................................................................................. 5 Sale of personal information .......................................................................................... 6 Children’s online privacy .............................................................................................. -
Orion Capsule Launch Abort System Analysis
Orion Capsule Launch Abort System Analysis Assignment 2 AE 4802 Spring 2016 – Digital Design and Manufacturing Georgia Institute of Technology Authors: Tyler Scogin Michel Lacerda Jordan Marshall Table of Contents 1. Introduction ......................................................................................................................................... 4 1.1 Mission Profile ............................................................................................................................. 7 1.2 Literature Review ........................................................................................................................ 8 2. Conceptual Design ............................................................................................................................. 13 2.1 Design Process ........................................................................................................................... 13 2.2 Vehicle Performance Characteristics ......................................................................................... 15 2.3 Vehicle/Sub-Component Sizing ................................................................................................. 15 3. Vehicle 3D Model in CATIA ................................................................................................................ 22 3.1 3D Modeling Roles and Responsibilities: .................................................................................. 22 3.2 Design Parameters and Relations:............................................................................................ -
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. -
Chemical Resistance: Deco-Trowel
CHEMICAL RESISTANCE DECO-TROWEL ® SERIES 223 Tnemec Company, Inc. 6800 Corporate Drive Kansas City, Missouri 64120-1372 +1 816-483-3400 www.tnemec.com © December 16, 2019 by Tnemec Company, Inc. Chem223 Page 1 of 19 CHEMICAL RESISTANCE DECO-TROWEL ® | SERIES 223 COMMON PROBLEM AREAS FOR COATINGS AND SOLUTIONS Problem: Coating Solution: Points of failure Carefully and due to thin spots fully coat in coating Problem: Rough Pinhole Solution: Uneven Undercut Grind smooth welds Problem: Gaps between Solution: plates, coating Continuous can not cover welds Problem: Gaps between Solution: plates, coating Continuous can not cover welds Problem: Coating Sharp surface Solution: contours create Round the thin spots in contours coating Problem: Skip welding Solution: creates gaps Continuous that coating welds can not cover Problem: Skip welding Solution: creates gaps Continuous that coating welds can not cover 2 channels back to back IMPORTANT: Definitions for the terms and acronyms used in this guide to describe the recommended exposures, along with other important information, can be found on the cover page of this guide or by contacting Tnemec Technical Service. Coatings should not be applied in a chemical exposure environment until the user has thoroughly read and understood the product information and full project details have been discussed with Tnemec Technical Service. Tnemec Company, Inc. 6800 Corporate Drive Kansas City, Missouri 64120-1372 +1 816-483-3400 www.tnemec.com © December 16, 2019 by Tnemec Company, Inc. Chem223 Page 2 of 19 CHEMICAL RESISTANCE DECO-TROWEL ® | SERIES 223 ¹ Product is NOT suitable for direct or indirect food contact. Intended Use and temperature information relates to product’s performance capabilities only. -
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) -
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. -
1 American Institute of Aeronautics and Astronautics from Air Bubbles Cast in the Fuel (Voids) Can Cause Problems During Hot-Fire Operations
Genetic Algorithm Optimization of a Cost Competitive Hybrid Rocket Booster George Story1 NASA MSFC Huntsville, Al Performance, reliability and cost have always been drivers in the rocket business. Hybrid rockets have been late entries into the launch business due to substantial early development work on liquid rockets and solid rockets. Slowly the technology readiness level of hybrids has been increasing due to various large scale testing and flight tests of hybrid rockets. One remaining issue is the cost of hybrids vs the existing launch propulsion systems. This paper will review the known state-of-the-art hybrid development work to date and incorporate it into a genetic algorithm to optimize the configuration based on various parameters. A cost module will be incorporated to the code based on the weights of the components. The design will be optimized on meeting the performance requirements at the lowest cost. I. Introduction Hybrids, considered part solid and part liquid propulsion system, have been caught in the middle of development goals of the various NASA and military programs. Solid rocket motor technology has matured due to the design simplicity, on-demand operational characteristics and low cost. The reliability of solids, given minimal maintenance requirements, made them the ideal system for military applications. On the other hand, liquid rocket engine technology has matured due to their higher specific impulse (ISP) over solids and variable control thrust capability. Hybrid Rockets have been used in only one flight-production application (Teledyne Ryan AQM-81A ‘Firebolt Supersonic Aerial Target) and one series of recent manned flight demonstrations (Burt Rutan’s SpaceshipOne), suggesting that advantages have been overlooked in some potential applications. -
Gallery of USAF Weapons Note: Inventory Numbers Are Total Active Inventory Figures As of Sept
Gallery of USAF Weapons Note: Inventory numbers are total active inventory figures as of Sept. 30, 2011. ■ 2012 USAF Almanac Bombers B-1 Lancer Brief: A long-range, air refuelable multirole bomber capable of flying intercontinental missions and penetrating enemy defenses with the largest payload of guided and unguided weapons in the Air Force inventory. Function: Long-range conventional bomber. Operator: ACC, AFMC. First Flight: Dec. 23, 1974 (B-1A); Oct. 18, 1984 (B-1B). Delivered: June 1985-May 1988. IOC: Oct. 1, 1986, Dyess AFB, Tex. (B-1B). Production: 104. Inventory: 66. Aircraft Location: Dyess AFB, Tex.; Edwards AFB, Calif.; Eglin AFB, Fla.; Ellsworth AFB, S.D. Contractor: Boeing, AIL Systems, General Electric. Power Plant: four General Electric F101-GE-102 turbofans, each 30,780 lb thrust. Accommodation: pilot, copilot, and two WSOs (offensive and defensive), on zero/zero ACES II ejection seats. Dimensions: span 137 ft (spread forward) to 79 ft (swept aft), length 146 ft, height 34 ft. B-1B Lancer (SSgt. Brian Ferguson) Weight: max T-O 477,000 lb. Ceiling: more than 30,000 ft. carriage, improved onboard computers, improved B-2 Spirit Performance: speed 900+ mph at S-L, range communications. Sniper targeting pod added in Brief: Stealthy, long-range multirole bomber that intercontinental. mid-2008. Receiving Fully Integrated Data Link can deliver nuclear and conventional munitions Armament: three internal weapons bays capable of (FIDL) upgrade to include Link 16 and Joint Range anywhere on the globe. accommodating a wide range of weapons incl up to Extension data link, enabling permanent LOS and Function: Long-range heavy bomber.