Rocket Nozzles: 75 Years of Research and Development
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Vulcan Centaur
VULCAN CENTAUR The Vulcan Centaur rocket design leverages the flight-proven success of the Delta IV and Atlas V launch vehicles while introducing new technologies and innovative features to ensure a reliable and aordable space launch service. Vulcan Centaur will service a diverse range of markets including 225 ft commercial, civil, science, cargo and national security space customers. 1 The spacecraft is encapsulated in a 5.4-m- (17.7-ft-) diameter payload fairing (PLF), a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates the spacecraft. The payload attach fitting (PAF) is a similar sandwich composite structure creating the mating interface from spacecraft to second stage. The PLF separates using a debris-free horizontal and vertical separation system with 2 200 ft spring packs and frangible joint assembly. The payload fairing is available in the 15.5-m (51-ft) standard and 21.3-m (70-ft) 1 long configurations. The Centaur upper stage is 5.4 m (17.7 ft) in diameter and 3 11.7 m (38.5 ft) long with a 120,000-lb propellant capacity. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle, with two RL10C 4 engines. The Vulcan Centaur Heavy vehicle, flies the upgraded 2 Centaur using RL10CX engines with nozzle extensions. The 5 175 ft cryogenic tanks are insulated with spray-on foam insulation (SOFI) to manage boil o of cryogens during flight. An aft equipment shelf provides the structural mountings for vehicle electronics. -
Different Types of Rocket Nozzles
Different Types of Rocket Nozzles 5322- Rocket Propulsion Project Report By Patel Harinkumar Rajendrabhai(1001150586) 1. Introduction 1.1 What is Nozzle and why they are used? A nozzle is a device designed to control the direction or characteristics of a fluid flow (especially to increase velocity) as it exits (or enters) an enclosed chamber or Pipe[9]. Nozzles are frequently used to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the stream that emerges from them. In nozzle velocity of fluid increases on the expense of its pressure energy. A Water Nozzle[9] Rotator Style Pivot Sprinkler[9] 1.2 What is Rocket Nozzle? A rocket engine nozzle is a propelling nozzle (usually of the de Laval type) used in a rocket engine to expand and accelerate the hot gases from combustion so as to produce thrust according to Newton’s law of motion. Combustion gases are produced by burning the propellants in combustor, they exit the nozzle at very high Speed (hypersonic). 1.3 Properties of Rocket Nozzle Nozzle produces thrust. Exhaust gases from combustion are pushed into throat region of nozzle. Throat is smaller cross-sectional area than rest of engine, gases are compressed to high pressure. Nozzle gradually increases in cross-sectional area allowing gases to expand and push against walls creating thrust. Convert thermal energy of hot chamber gases into kinetic energy and direct that energy along nozzle axis.[1] Mathematically, ultimate purpose of nozzle is to expand gases as efficiently as possible so as to maximize exit velocity.[1] Rocket Engine[1] F m eVe Pe Pa Ae Neglecting Pressure losses F m eVe 2 Different types of Rocket Nozzle Configuration(shape) The rocket nozzles can have many shapes configurations. -
The Propulsion of Sea Ships – in the Past, Present and Future –
The Propulsion of Sea Ships – in the Past, Present and Future – (Speech by Bernd Röder on the occasion of the VHT General Meeting on 11.12.2008) To prepare for today’s topic, more specifically for the topic: ship propulsion of the future, I did what every reasonable person would have done in my situation if he should have a look into the future – I dug out our VHT crystal ball. As you know, our crystal ball is a reliable and cost-efficient resource which we have been using for a long time with great suc- cess. Among other things, we’ve been using it to provide you with the repair costs or their duration or the probable claims experience of a policy, etc. or to create short-term damage statistics, as well. So, I asked the crystal ball: What does ship propulsion of the future look like? Every future and all statistics lie in the crystal ball I must, however, admit that what I saw there was somewhat irritating, and it led me to only the one conclusion – namely, that we’re taking a look into the very distant future at a time in which humanity has not only used up all of the oil reserves but also the entire wind. This time, we’re not really going to get any further with the crystal ball. Ship propulsion of the future or 'back to the roots'? But, sometimes it helps to have a look into the past to be able to say something about the fu- ture. According to the principle, draw a line connecting the distant past to today and simply extend it into the future. -
Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft Through Parametric Studies
energies Article Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies Andrew Ridgway, Ashish Alex Sam * and Apostolos Pesyridis College of Engineering, Design and Physical Sciences, Brunel University London, London UB8 3PH, UK; [email protected] (A.R.); [email protected] (A.P.) * Correspondence: [email protected]; Tel.: +44-1895-267-901 Received: 26 September 2018; Accepted: 7 December 2018; Published: 10 December 2018 Abstract: This paper aims to contribute to developing a potential combined cycle air-breathing engine integrated into an aircraft design, capable of performing flight profiles on a commercial scale. This study specifically focuses on the single expansion ramp nozzle (SERN) and aircraft-engine integration with an emphasis on the combined cycle engine integration into the conceptual aircraft design. A parametric study using computational fluid dynamics (CFD) have been employed to analyze the sensitivity of the SERN’s performance parameters with changing geometry and operating conditions. The SERN adapted to the different operating conditions and was able to retain its performance throughout the altitude simulated. The expansion ramp shape, angle, exit area, and cowl shape influenced the thrust substantially. The internal nozzle expansion and expansion ramp had a significant effect on the lift and moment performance. An optimized SERN was assembled into a scramjet and was subject to various nozzle inflow conditions, to which combustion flow from twin strut injectors produced the best thrust performance. Side fence studies observed longer and diverging side fences to produce extra thrust compared to small and straight fences. Keywords: scramjet; single expansion ramp nozzle; hypersonic aircraft; combined cycle engines 1. -
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. -
Propulsion and Flight Controls Integration for the Blended Wing Body Aircraft
Cranfield University Naveed ur Rahman Propulsion and Flight Controls Integration for the Blended Wing Body Aircraft School of Engineering PhD Thesis Cranfield University Department of Aerospace Sciences School of Engineering PhD Thesis Academic Year 2008-09 Naveed ur Rahman Propulsion and Flight Controls Integration for the Blended Wing Body Aircraft Supervisor: Dr James F. Whidborne May 2009 c Cranfield University 2009. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright owner. Abstract The Blended Wing Body (BWB) aircraft offers a number of aerodynamic perfor- mance advantages when compared with conventional configurations. However, while operating at low airspeeds with nominal static margins, the controls on the BWB aircraft begin to saturate and the dynamic performance gets sluggish. Augmenta- tion of aerodynamic controls with the propulsion system is therefore considered in this research. Two aspects were of interest, namely thrust vectoring (TVC) and flap blowing. An aerodynamic model for the BWB aircraft with blown flap effects was formulated using empirical and vortex lattice methods and then integrated with a three spool Trent 500 turbofan engine model. The objectives were to estimate the effect of vectored thrust and engine bleed on its performance and to ascertain the corresponding gains in aerodynamic control effectiveness. To enhance control effectiveness, both internally and external blown flaps were sim- ulated. For a full span internally blown flap (IBF) arrangement using IPC flow, the amount of bleed mass flow and consequently the achievable blowing coefficients are limited. For IBF, the pitch control effectiveness was shown to increase by 18% at low airspeeds. -
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. -
Multidisciplinary Design Project Engineering Dictionary Version 0.0.2
Multidisciplinary Design Project Engineering Dictionary Version 0.0.2 February 15, 2006 . DRAFT Cambridge-MIT Institute Multidisciplinary Design Project This Dictionary/Glossary of Engineering terms has been compiled to compliment the work developed as part of the Multi-disciplinary Design Project (MDP), which is a programme to develop teaching material and kits to aid the running of mechtronics projects in Universities and Schools. The project is being carried out with support from the Cambridge-MIT Institute undergraduate teaching programe. For more information about the project please visit the MDP website at http://www-mdp.eng.cam.ac.uk or contact Dr. Peter Long Prof. Alex Slocum Cambridge University Engineering Department Massachusetts Institute of Technology Trumpington Street, 77 Massachusetts Ave. Cambridge. Cambridge MA 02139-4307 CB2 1PZ. USA e-mail: [email protected] e-mail: [email protected] tel: +44 (0) 1223 332779 tel: +1 617 253 0012 For information about the CMI initiative please see Cambridge-MIT Institute website :- http://www.cambridge-mit.org CMI CMI, University of Cambridge Massachusetts Institute of Technology 10 Miller’s Yard, 77 Massachusetts Ave. Mill Lane, Cambridge MA 02139-4307 Cambridge. CB2 1RQ. USA tel: +44 (0) 1223 327207 tel. +1 617 253 7732 fax: +44 (0) 1223 765891 fax. +1 617 258 8539 . DRAFT 2 CMI-MDP Programme 1 Introduction This dictionary/glossary has not been developed as a definative work but as a useful reference book for engi- neering students to search when looking for the meaning of a word/phrase. It has been compiled from a number of existing glossaries together with a number of local additions. -
Session 15 FLOWS THROUGH NOZZLE Outline
Session 15 FLOWS THROUGH NOZZLE Outline • Definition • Types of nozzle • Flow analysis • Ideal Gas Relationship • Mach Number and Speed of Sound • Isentropic flow of an ideal gas • De Laval nozzle • Nozzle efficiency • Calculation examples Definition Nozzle is a duct by flowing through which the velocity of a fluid increases at the expense of pressure drop. A duct which decreases the velocity of a fluid and causes a corresponding increase in pressure is called a diffuser Types of Nozzles There are three types of nozzles a. Convergent nozzle b. Divergent nozzle c. Convergent-divergent nozzle Flow Analysis • Incompressible flow • Compressible Flow The variation of fluid density for compressible flows requires attention to density and other fluid property relationships. The fluid equation of state, often unimportant for incompressible flows, is vital in the analysis of compressible flows. Also, temperature variations for compressible flows are usually significant and thus the energy equation is important. Curious phenomena can occur with compressible flows. Flow Analysis • For simplicity, the gas is assumed to be an ideal gas. • The gas flow is isentropic. • The gas flow is constant • The gas flow is along a straight line from gas inlet to exhaust gas exit • The gas flow behavior is compressible Ideal Gas Relationship The equation of state for an ideal gas is: For an ideal gas, internal energy, û is considered to be a function of temperature only Thus, Ideal Gas Relationship The fluid property enthalpy, ĥ is defined as Since for an ideal gas, enthalpy is a function of temperature only, the ideal gas specific heat at constant pressure, Cp can be expressed as And, Ideal Gas Relationship We see that changes in internal energy and enthalpy are related to changes in temperature by values of Cp and Cv. -
Spacecraft Propulsion
SPACECRAFT PROPULSION WITH THRUST AND PRECISION INTO SPACE SPACECRAFT PROPULSION THRUST AND PRECISION INTO SPACE ArianeGroup is a market leader in spacecraft propulsion systems and equipment. Since over 50 years, customers worldwide benefit from a competitive portfolio of high quality products and services. We cover the complete range of products and services related to orbital propulsion, from chemical monopropellant systems for smaller satellites to chemical bipropellant systems for larger platforms and completed with the electric propulsion portfolio based on the RIT technology. At ArianeGroup, customers have a single point of contact for the complete propulsion system at all phases of the value chain. From system design up to after-launch services. All key equipment of ArianeGroup propulsion systems (thrusters, propellant tanks and fluidic equipment) are produced in-house. 2 ALL ABOUT PRECISION With our orbital propulsion thrusters and engines our customers can be ensured that their mission requirements related to propulsion will be fulfilled with accurate precision. Our biggest orbital propulsion thruster, the 400N apogee engine, has placed hundreds of satellites in its final orbit With micro precision the RIT µX thruster brings space missions to the exact orbit 2 3 SPACECRAFT PROPULSION ELECTRIC PROPULSION Radio frequency ion propulsion for orbit raising, station keeping and deep space missions ArianeGroup’s electric space propulsion expertise is based on the space proven Radio Frequency Ion Technology (RIT). Within this field, we produce complete propulsion systems, modules, thrusters and related components. This technology features numerous advantages like high specific impulse therefore maximum propellant saving. Low system complexity is another strength of the RIT Technology. -
Three Gray Classics on the Biomechanics of Animal Movement
View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Harvard University - DASH Three Gray Classics on the Biomechanics of Animal Movement The Harvard community has made this article openly available. Please share how this access benefits you. Your story matters Citation Lauder, G. V., Eric Tytell. 2004. Three Gray Classics on the Biomechanics of Animal Movement. Journal of Experimental Biology 207, no. 10: 1597–1599. doi:10.1242/jeb.00921. Published Version doi:10.1242/jeb.00921 Citable link http://nrs.harvard.edu/urn-3:HUL.InstRepos:30510313 Terms of Use This article was downloaded from Harvard University’s DASH repository, and is made available under the terms and conditions applicable to Other Posted Material, as set forth at http:// nrs.harvard.edu/urn-3:HUL.InstRepos:dash.current.terms-of- use#LAA JEB Classics 1597 THREE GRAY CLASSICS locomotor kinematics, muscle dynamics, JEB Classics is an occasional ON THE BIOMECHANICS and computational fluid dynamic column, featuring historic analyses of animals moving through publications from The Journal of OF ANIMAL MOVEMENT water. Virtually every recent textbook in Experimental Biology. These the field either reproduces one of Gray’s articles, written by modern experts figures directly or includes illustrations in the field, discuss each classic that derive their inspiration from his paper’s impact on the field of figures (e.g. Alexander, 2003; Biewener, biology and their own work. A 2003). PDF of the original paper accompanies each article, and can be found on the journal’s In his 1933a paper, Gray aimed to website as supplemental data. -
Abstract US Patent References
Architecture for Reusable Responsive Exploration Systems: ARES - Platform and Reusable Responsive Architecture for Innovative Space Exploration: PRAISE (Part 1) PATENT PENDING Abstract A comprehensive Modular Reusable Responsive Space Exploration Platform (Architecture) composed of multiple modular reusable elements such that the assemblies can be flexibly configured into systems for low earth orbits launches and for long-range exploration such as orbits to moon, Lagrange points and others. This platform & architecture is named as Architecture for Reusable Responsive Exploration System (acronym ARES) / Platform and Reusable Responsive Architecture for Innovative Space Exploration (acronym PRAISE), in short ARES/PRAISE or simply ARES. It is also known as Alpha Spaces Architecture and Platform (acronym ASAP), in short as “αPlatform” or “αArchitecture”, or “αAres”. As an example, the configuration involves reusable lightweight wing, core stage, (optional booster stages) combination of expendable upper stage and reusable crew capsule. Further, the expendable upper stage can be re-used to serve as in-orbit fuel depots and for other innovative uses. This is first part of the multi part patent application. Inventor: Atreya, Dinesh S. US Patent References US Patent 6158693 - Recoverable booster stage and recovery method US Patent 4878637 - Modular space station US Patent 6726154 - Reusable space access launch vehicle system US Patent 6113032 - Delivering liquid propellant in a reusable booster stage US Patent 4557444 - Aerospace vehicle US Patent 4880187 - Multipurpose modular spacecraft US Patent 4452412 - Space shuttle with rail system and aft thrust structure securing solid rocket boosters to external tank US Patent 4802639 - Horizontal-takeoff transatmospheric launch system US Patent 4884770 - Earth-to-orbit vehicle providing a reusable orbital stage US Patent 4265416 - Orbiter/launch system U.S.