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RD-180—Or Bust?
RD-180—or By Autumn A. Arnett, Associate Editor As it stands, the US could sustain its Bust? manifest for two years with the current supply of RD-180 engines. But a new he United States’ sustained access he doesn’t really know what that R&D engine could take seven or more years to space is in question. Heavily amounts to, but said he is hopeful the to be operational, making LaPlante’s Treliant on the Russian-made En- partnership will mean a new engine on “$64 million question” a “hydra-headed ergomash RD-180 engine to power its the market soon. monster,” in the words of former AFSPC launches, US military space personnel “Three years of development is better Commander Gen. William L. Shelton. are looking for a replacement because than starting at ground zero,” Hyten said. “I don’t think we build the world’s best of the tense and uncertain status of “If we start at ground zero to build a rocket engine,” Shelton said last July. “I American and Russian relations. new engine in the hydrocarbon technology would love for us as a nation to regain the Funds are already being appropriated area we’re fi ve years away from produc- lead in liquid rocket propulsion.” for research and development of a new tion, roughly, maybe four, maybe six. Both LaPlante and Hyten are propo- engine, but Gen. John E. Hyten, com- The one thing you would have to do is nents of the United States continuing to mander of Air Force Space Command, spend the next year or two driving down fund research and development of a new considers the issue to be urgent. -
Qualification Over Ariane's Lifetime
r bulletin 94 — may 1998 Qualification Over Ariane’s Lifetime A. González Blázquez Directorate of Launchers, ESA, Paris M. Eymard Groupe Programme CNES/Arianespace, Evry, France Introduction Similarly, the RL10 engine on the Centaur stage The primary objectives of the qualification of the Atlas launcher has been the subject of an activities performed during the operational ongoing improvement programme. About 5000 lifetime of a launcher are: tests were performed before the first flight, and – to verify the qualification status of the vehicle 4000 during the subsequent ten years. – to resolve any technical problems relating to subsystem operations on the ground or in On-going qualification activities of a similar flight. nature were started for the Ariane-3 and 4 launchers in 1986, and for Ariane-5 in 1996. Before focussing on the European family of They can be classified into two main launchers, it is perhaps informative to review categories: ‘regular’ and ‘one-off’. just one or two of the US efforts in the area of solid and liquid propulsion in order to put the Ariane-3/4 accompanying activities Ariane-related activities into context. Regular activities These activities are mainly devoted to In principle, the development programme for a launcher ends with the verification of the qualification status of the qualification phase, after which it enters operational service. In various launcher subsystems. They include the practice, however, the assessment of a launcher’s reliability is a following work packages: continuing process and qualification-type activities proceed, as an – Periodic sampling of engines: one HM7 and extension of the development programme (as is done in aeronautics), one Viking per year, tested to the limits of the over the course of the vehicle’s lifetime. -
ULA Atlas V Launch to Feature Full Complement of Aerojet Rocketdyne Solid Rocket Boosters
April 13, 2018 ULA Atlas V Launch to Feature Full Complement of Aerojet Rocketdyne Solid Rocket Boosters SACRAMENTO, Calif., April 13, 2018 (GLOBE NEWSWIRE) -- The upcoming launch of the U.S. Air Force Space Command (AFSPC)-11 satellite aboard a United Launch Alliance Atlas V rocket from Cape Canaveral Air Force Station, Florida, will benefit from just over 1.74 million pounds of added thrust from five AJ-60A solid rocket boosters supplied by Aerojet Rocketdyne. The mission marks the eighth flight of the Atlas V 551 configuration, the most powerful Atlas V variant that has flown to date. The Atlas V 551 configuration features a 5-meter payload fairing, five AJ-60As and a Centaur upper stage powered by a single Aerojet Rocket RL10C-1 engine. This configuration of the U.S. government workhorse launch vehicle is capable of delivering 8,900 kilograms of payload to geostationary transfer orbit (GTO), and also has been used to send scientific probes to explore Jupiter and Pluto. The Centaur upper stage also uses smaller Aerojet Rocketdyne thrusters for pitch, yaw and roll control, while both stages of the Atlas V employ pressurization vessels built by Aerojet Rocketdyne's ARDÉ subsidiary. "The Atlas V is able to perform a wide variety of missions for both government and commercial customers, and the AJ-60A is a major factor in that versatility," said Aerojet Rocketdyne CEO and President Eileen Drake. "Aerojet Rocketdyne developed the AJ-60A specifically for the Atlas V, delivering the first booster just 42 months after the contract award, which underscores our team's ability to design and deliver large solid rocket motors in support of our nation's strategic goals and efforts to explore our solar system." The flight of the 100th AJ-60A, the largest monolithically wound solid rocket booster ever flown, took place recently as part of a complement of four that helped an Atlas V 541 place the nation's newest weather satellite into GTO. -
High-Thrust In-Space Liquid Propulsion Stage: Storable Propellants
View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Institute of Transport Research:Publications Space Propulsion 2014 – ID 2968378 High-Thrust in-Space Liquid Propulsion Stage: Storable Propellants Etienne Dumont, Alexander Kopp, Carina Ludwig, Nicole Garbers DLR, Space Launcher Systems Analysis (SART), Bremen, Germany [email protected] Abstract In the frame of a project funded by ESA, a consortium led Subscripts, Abbreviations by Avio in cooperation with Snecma, Cira, and DLR is ATV Automated Transfer Vehicle performing the preliminary design of a High-Thrust in- CDF Concurrent Design Facility Space Liquid Propulsion Stage for two different types of ECSS European Cooperation on Space manned missions beyond Earth orbit. For these missions, Standardization one or two 100 ton stages are to be used to propel a Elec assy electronic assembly manned vehicle. Three different propellant combinations; EPS Etage à propergols stockables (Ariane 5’s LOx/LH2, LOx/CH4 and MON-3/MMH are being storable propellant stage) compared. GNC Guidance Navigation and Control HTS High-Thrust Stage The preliminary design of the storable variant (MON- IF Interface 3/MMH) has been performed by DLR. The Aestus II ISS International Space Station engine with a large nozzle expansion ratio has been LEO Low Earth Orbit chosen as baseline. A first iteration has demonstrated, that LEOP Launch and Early Orbit Phase it indeed provides the best performance for the storable LH2 Liquid Hydrogen propellant combination, when considering all engines LOx Liquid Oxygen available today or which may be available in a short- to MLI Multi-Layer Insulation medium term. -
MTU-Museum Triebwerksgeschichte – Gestern, Heute Und Morgen MTU Museum 07 2009 01.Qxd 27.08.2009 13:47 Uhr Seite 4
MTU_Museum_07_2009_01.qxd 27.08.2009 13:47 Uhr Seite 3 MTU-Museum Triebwerksgeschichte – gestern, heute und morgen MTU_Museum_07_2009_01.qxd 27.08.2009 13:47 Uhr Seite 4 Inhaltsverzeichnis Vorwort 3 Unternehmen mit Tradition und Zukunft 4 Bewegte Geschichte 5 GP7000 – Antrieb für den Mega-Airbus 8 PW6000 – Antrieb des kleinen Airbus A318 8 EJ200 – Schub für den Eurofighter 9 PW4000 – Triebwerk der Boeing B777-200 10 MTR390 – Triebwerk des Tigers 10 V2500 – Antrieb für den Airbus A320 11 PW500 – Antrieb für Geschäftsreiseflugzeuge 12 RR250-C20 – Antrieb für Hubschrauber 12 RB199 – Antrieb des Tornado 13 CF6 – Power für Großraumflugzeuge 14 Lycoming GO-480-B1A6 – Lizenzfertigung bei BMW 15 MTU7042 – Erprobung einer LKW-Gasturbine 15 T64-MTU-7 – Lizenzbau in Deutschland 16 RB145R – Antrieb des VJ101C 16 RB193-12 – Antrieb für Senkrechtstarter 17 RB153 – Antrieb des VJ101E 17 J79 – Triebwerk des Starfighters 18 Tyne – Antrieb der Transall 19 BMW 6022 – Antrieb für den Bo105 19 DB 720 – Daimler-Nachkriegsära beginnt 20 BMW 801 – erster deutscher Doppelsternmotor 20 BMW 114 – Diesel-Flugmotor 21 BMW 003E – Schub für den Volksjäger 22 Riedel-Anlasser – Starter für Strahltriebwerke 23 BRAMO 323 R-1 „Fafnir“ – erfolgreichster BRAMO-Flugmotor 23 Daimler-Benz DB 605 – der „kleine“ Mercedes-Benz-Flugmotor 24 BMW 132 – Nachfolger des Hornet-Motors 25 Sh14A – erfolgreichster Siemens-Flugmotor 26 BMW VI – Erfolgsmotor der 1920er-Jahre 26 Daimler-Benz F4A – Vorläufer der DB 600-Familie 27 Daimler D IIIa – Ära der Kolbenflugmotoren beginnt 27 Exponate 28 Chirurg der Motoren 31 2 MTU_Museum_07_2009_01.qxd 27.08.2009 13:47 Uhr Seite 5 Vorwort Die Museumswelt wird nicht nur von großen Ausstellungen und Kunstgalerien jeder Couleur geprägt, sondern auch von technischen Samm- lungen, wie etwa dem Deutschen Museum in München. -
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. -
PCEC V2.3 (For Real This Time)
PCEC v2.3 (For Real This Time) 2021 NASA Cost & Schedule Symposium 14 Apr 2021 Brian Alford Mark Jacobs Booz Allen Hamilton TGS Consultants Shawn Hayes Richard Webb TGS Consultants KAR Enterprises NASA MSFC Victory MIPSSSolutions Team SB Diversity Outline • PCEC Overview • Robotic SC Updates • CASTS Updates • PCEC v2.3 Interface Updates • Closing Victory Solutions MIPSS Team 2 What is PCEC? • The Project Cost Estimating Capability (PCEC) is the primary NASA in-house developed parametric tool for estimating the cost of robotic missions, launch vehicles, crewed vehicles, etc. – Overarching tool for creating an estimate that spans the full NASA WBS – CERs included out-of-the-box for estimating the costs of a flight system (e.g., thermal) and support functions (e.g., project management) – Connects to other NASA-sponsored specialized tools to cover the complete NASA WBS (e.g., NICM, MOCET) – Excel-based (presented as add-in in the Ribbon) with completely visible calculations and code – Consists of the PCEC Interface (the Ribbon and supporting code) and the PCEC Library (the artifacts used to estimate cost) – Available to the General Public Victory Solutions MIPSS Team 3 What is PCEC? Cont’d • PCEC comprises two primary ‘models’, offered seamlessly to the user under a single, integrated tool – Robotic Spacecraft (Robotic SC) – Crewed and Space Transportation Systems (CASTS) • These models have separate data normalizations, collections of CERs, core WBSs, modeling approaches, estimating template worksheets, and scope – Estimating artifacts constitute -
6. Chemical-Nuclear Propulsion MAE 342 2016
2/12/20 Chemical/Nuclear Propulsion Space System Design, MAE 342, Princeton University Robert Stengel • Thermal rockets • Performance parameters • Propellants and propellant storage Copyright 2016 by Robert Stengel. All rights reserved. For educational use only. http://www.princeton.edu/~stengel/MAE342.html 1 1 Chemical (Thermal) Rockets • Liquid/Gas Propellant –Monopropellant • Cold gas • Catalytic decomposition –Bipropellant • Separate oxidizer and fuel • Hypergolic (spontaneous) • Solid Propellant ignition –Mixed oxidizer and fuel • External ignition –External ignition • Storage –Burn to completion – Ambient temperature and pressure • Hybrid Propellant – Cryogenic –Liquid oxidizer, solid fuel – Pressurized tank –Throttlable –Throttlable –Start/stop cycling –Start/stop cycling 2 2 1 2/12/20 Cold Gas Thruster (used with inert gas) Moog Divert/Attitude Thruster and Valve 3 3 Monopropellant Hydrazine Thruster Aerojet Rocketdyne • Catalytic decomposition produces thrust • Reliable • Low performance • Toxic 4 4 2 2/12/20 Bi-Propellant Rocket Motor Thrust / Motor Weight ~ 70:1 5 5 Hypergolic, Storable Liquid- Propellant Thruster Titan 2 • Spontaneous combustion • Reliable • Corrosive, toxic 6 6 3 2/12/20 Pressure-Fed and Turbopump Engine Cycles Pressure-Fed Gas-Generator Rocket Rocket Cycle Cycle, with Nozzle Cooling 7 7 Staged Combustion Engine Cycles Staged Combustion Full-Flow Staged Rocket Cycle Combustion Rocket Cycle 8 8 4 2/12/20 German V-2 Rocket Motor, Fuel Injectors, and Turbopump 9 9 Combustion Chamber Injectors 10 10 5 2/12/20 -
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. -
Design for Demise Analysis for Launch Vehicles
A first design for demise analysis for launch vehicles Henrik Simon, Stijn Lemmens Space debris: Inactive, manmade objects in space Source: ESA Overview Introduction Fundamentals Modelling approach Results and discussion Summary and outlook What is the motivation and task? INTRODUCTION Motivation . Mitigation: Prevention of creation and limitation of long-term presence . Guidelines: LEO removal within 25 years . LEO removal within 25 years after mission end . Casualty risk limit for re-entry: 1 in 10,000 Rising altitude Decay & re-entry above 2000 km Source: NASA Source: NASA Solution: Design for demise Source: ESA Scope of the thesis . Typical design of upper stages . General Risk assessment . Design for demise solutions to reduce the risk ? ? ? Risk A Risk B Risk C Source: CNES How do we assess the risk and simulate the re-entry? FUNDAMENTALS Fundamentals: Ground risk assessment Ah = + 2 Ai � ℎ = =1 � Source: NASA Source: NASA 3.5 m 5.0 m 2 2 ≈ ≈ Fundamentals: Re-entry simulation tools SCARAB: Spacecraft-oriented approach . CAD-like modelling . 6 DoF flight dynamics . Break-up / fragmentation computed How does a rocket upper stage look like? MODELLING Modelling approach . Research on typical design: . Elongated . Platform . Solid Rocket Motor . Lack of information: . Create common intersection . Deliberately stay top-level and only compare effects Modelling approach Modelling approach 12 Length [m] 9 7 5 3 2 150 300 500 700 800 1500 2200 Mass [kg] How much is the risk and how can we reduce it? SIMULATIONS Example of SCARAB re-entry simulation 6x Casualty risk of all reference cases Typical survivors Smaller Smaller fragments fragments Pressure tanks Pressure tanks Main tank Engine Main structure + tanks Design for Demise . -
Read PDF # Articles on Aircraft Engine
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