PDF Download Real
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
CRUISE MISSILE THREAT Volume 2: Emerging Cruise Missile Threat
By Systems Assessment Group NDIA Strike, Land Attack and Air Defense Committee August 1999 FEASIBILITY OF THIRD WORLD ADVANCED BALLISTIC AND CRUISE MISSILE THREAT Volume 2: Emerging Cruise Missile Threat The Systems Assessment Group of the National Defense Industrial Association ( NDIA) Strike, Land Attack and Air Defense Committee performed this study as a continuing examination of feasible Third World missile threats. Volume 1 provided an assessment of the feasibility of the long range ballistic missile threats (released by NDIA in October 1998). Volume 2 uses aerospace industry judgments and experience to assess Third World cruise missile acquisition and development that is “emerging” as a real capability now. The analyses performed by industry under the broad title of “Feasibility of Third World Advanced Ballistic & Cruise Missile Threat” incorporate information only from unclassified sources. Commercial GPS navigation instruments, compact avionics, flight programming software, and powerful, light-weight jet propulsion systems provide the tools needed for a Third World country to upgrade short-range anti-ship cruise missiles or to produce new land-attack cruise missiles (LACMs) today. This study focuses on the question of feasibility of likely production methods rather than relying on traditional intelligence based primarily upon observed data. Published evidence of technology and weapons exports bears witness to the failure of international agreements to curtail cruise missile proliferation. The study recognizes the role LACMs developed by Third World countries will play in conjunction with other new weapons, for regional force projection. LACMs are an “emerging” threat with immediate and dire implications for U.S. freedom of action in many regions . -
Study and Numerical Simulation of Unconventional Engine Technology
STUDY AND NUMERICAL SIMULATION OF UNCONVENTIONAL ENGINE TECHNOLOGY by ANJALI SHEKHAR B.E Aeronautical Engineering VTU, Karnataka, 2013 A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science, Aerospace Engineering, College of Engineering and Applied Science, University of Cincinnati, Ohio 2018 Thesis Committee: Chair: Ephraim Gutmark, Ph.D. Member: Shaaban Abdallah, Ph.D. Member: Mark Turner, Sc.D. An Abstract of Study and Numerical Simulation of Unconventional Engine Technology by Anjali Shekhar Submitted to the Graduate Faculty as partial fulfillment of the requirements for the Master of Science Degree in Aerospace Engineering University of Cincinnati December 2018 The aim of this thesis is to understand the working of two unconventional aircraft propul- sion systems and to setup a two-dimensional transient simulation to analyze its operational mechanism. The air traffic has nearly increased by about 40% in past three decades and calls for alternative propulsion techniques to replace or support the current traditional propulsion methodology. In the light of current demand, the thesis draws motivation from renewed inter- est in two non-conventional propulsion techniques designed in the past and had not been given due importance due to various flaws/drawbacks associated. The thesis emphasizes on the work- ing of Von Ohains thermal compression engine and pulsejet combustors. Computational Fluid Dynamics is used in current study as it offers very high flexibility and can be modified easily to incorporate the required changes. Thermal Compression engine is a design suggested by Von Ohain in 1948. The engine works on the principle of pressure rise caused inside the engine which completely depends on the temperature of working fluid and independent of rotations per minute. -
WPP Presentation
AE705 /153M/ 152 Introduction to Flight Fatima Salehbhai Third Year U G Student Mechanical Engg. Deptt. IIT Bombay Types of Propulsion Systems AE-705 Introduction to Flight Lecture No 11 Capsule-06 What is propulsion? • Moving or Pushing an object forward Propulsion = pro (forward) + pellere (drive) Why is propulsion needed in aircraft? • Getting aloft - thrust + lift • produces thrust to push an object • used to accelerate, gain altitude, and to maneuver AE-705 Introduction to Flight Lecture No 11 Capsule-06 Revising Thrust • Drives an airplane forward • To sustain lift and counteract drag http://howthingsfly.si.edu/media/thrust • Energy required • Heat by the combustion • Propulsion system • A machine that accelerates air backwards https://www.nasa.gov/audience/forstudents/k-4/stories /nasa-knows/what-is-aerodynamics-k4.html AE-705 Introduction to Flight Lecture No 11 Capsule-06 Propulsion Systems Mechanisms to produce thrust for flight AE-705 Introduction to Flight Lecture No 11 Capsule-06 Types of Propulsion Systems We'll discuss the following : • Pistonpropeller • Pulsejet • Turbojet • Ramjet • Afterburning Turbojet • Scramjet • Turbofan • Electric Propulsion • Turboprop • Ionic Propulsion • Turboshaft AE-705 Introduction to Flight Lecture No 11 Capsule-06 Powerplant Selection based on mission Source: D. P. Raymer, Aircraft Design, A Conceptual Approach, AIAA Education Series, 4th edition, 2006 AE-705 Introduction to Flight Lecture No 11 Capsule-06 Reciprocating Engines Primary powerplant for general aviation image source: https://www.comsol.com/blogs/improving-the-operational-lifetime-of-a-reciprocating-engine/ -
Study and Optimization of a Cad/Cfd Model for Valveless Pulsejets
VOL. 13, NO. 21, NOVEMBER 2018 ISSN 1819-6608 ARPN Journal of Engineering and Applied Sciences ©2006-2018 Asian Research Publishing Network (ARPN). All rights reserved. www.arpnjournals.com STUDY AND OPTIMIZATION OF A CAD/CFD MODEL FOR VALVELESS PULSEJETS Luca Piancastelli1, Stefano Cassani2, Eugenio Pezzuti3 and Luca Lipparini1 1Department of Industrial Engineering, Alma Mater Studiorum University of Bologna, Viale Risorgimento, Bologna (BO), Italy 2MultiProjecta, Via Casola Canina, Imola (BO), Italy 3Università di Roma "Tor Vergata", Dip. di Ingegneria dell’Impresa "Mario Lucertini”, Via del Politecnico, Roma, Italy E-Mail: [email protected] ABSTRACT The method introduced in this paper aims to find a feasible method to evaluate the static thrust of a “valveless” pulsejet, starting from a CAD model. CFD (Computational Fluid Dynamic) simulation and golden section were used for this purpose. Even for new pulsejet designs, it is possible to evaluate the pulsating frequency from equations available in literature or with a mono-dimensional pressure wave model. Then the combustion energy should be introduced in the engine. In this CFD model, the heat flow due to the combustion is simulated through the application of a pulsating flow of hot gases through the walls of the combustion chamber. To minimize the error of this added flow, a stoichiometric combustion of pure oxygen is introduced. The temperature value of the hot gases was optimized with the Golden Section Method in order to obtain the same experimental results of the Department of Aerospace Engineering of California Polytechnic State University, San Luis Obispo [2]. In this way, it is possible to evaluate the performance of a new design of different geometry and size. -
Ejector Enhanced Pulsejet Based Pressure Gain Combustors: an Old Idea with a New Twist
NASA/TM—2005-213854 AIAA–2005–4216 Ejector Enhanced Pulsejet Based Pressure Gain Combustors: An Old Idea With a New Twist Daniel E. Paxson Glenn Research Center, Cleveland, Ohio Kevin T. Dougherty QSS Group, Inc., Cleveland, Ohio August 2005 The NASA STI Program Office . in Profile Since its founding, NASA has been dedicated to • CONFERENCE PUBLICATION. Collected the advancement of aeronautics and space papers from scientific and technical science. The NASA Scientific and Technical conferences, symposia, seminars, or other Information (STI) Program Office plays a key part meetings sponsored or cosponsored by in helping NASA maintain this important role. NASA. The NASA STI Program Office is operated by • SPECIAL PUBLICATION. Scientific, Langley Research Center, the Lead Center for technical, or historical information from NASA’s scientific and technical information. The NASA programs, projects, and missions, NASA STI Program Office provides access to the often concerned with subjects having NASA STI Database, the largest collection of substantial public interest. aeronautical and space science STI in the world. The Program Office is also NASA’s institutional • TECHNICAL TRANSLATION. English- mechanism for disseminating the results of its language translations of foreign scientific research and development activities. These results and technical material pertinent to NASA’s are published by NASA in the NASA STI Report mission. Series, which includes the following report types: Specialized services that complement the STI • TECHNICAL PUBLICATION. Reports of Program Office’s diverse offerings include completed research or a major significant creating custom thesauri, building customized phase of research that present the results of databases, organizing and publishing research NASA programs and include extensive data results . -
Aviation Magazine – Index Général Simplifié @ Dominique Mahieu (2010)
Aviation Magazine – Index Général Simplifié @ Dominique Mahieu (2010) / www.aero-index.com Numéro 101 du 01/07/1954 Mémoires d’Adolf Galland Les leçons de Dien Bien Phu Les erreurs de pilotage (J. Lecarme) Le GC 1/1 Corse Meetings de l’entre deux guerre La kermesse de Toussus-le-Noble Le SE Aquilon Air-Tourist Numéro 102 du 15/07/1954 Mémoires d’Adolf Galland J’ai piloté le Caproni F.5 De France en Angleterre le Hurel Dubois 31 50 ans d’aviation à Coventry Paris-Biarritz : première course vélivole par étapes Le Piel CP-30 Emeraude Vickers Viscount d’Air France Championnats du monde de vol à voile à Camp Hill Numéro 103 du 01/08/1954 Mémoires d’Adolf Galland J’ai piloté le Miles Aries Ecole complète du vol à voile : Saint-Auban L’Aéronautique navale au Tonkin Le Marcel Brochet MB-100 L’Aéro-club Paul-Tissandier Numéro 104 du 15/08/1954 Mémoires d’Adolf Galland Le meeting de Nice en 1922 L’invitation polonaise (festival international de vol à voile) Championnat du monde de vol à voile (Gérard Pierre champion du monde 1954) Les avions d’entraînement de l’OTAN à Villacoublay Le De Havilland Canada DHC-3 Otter Numéro 105 du 01/09/1954 Mémoires d’Adolf Galland Les meetings de Vincennes Classiques ou laminaires Saint-Yan : victoire éclatante des soviétiques (championnats du monde de parachutisme) Le Breguet 901 L’Aéro-club Jean Réginensi Numéro 106 du 15/09/1954 Mémoires d’Adolf Galland Le turbopropulseur Napier Eland Le Tour de France aérien 1954 L’Avro Canada CF-100 L’Aéro-club Jean Maridor Numéro 107 du 01/10/1954 Mémoires d’Adolf Galland Farnborough 1954 Numéro 108 du 15/10/1954 Mémoires d’Adolf Galland Farnborough 1954 Le colonel Cressaty Opération Shooting Star (exercice aérien) Le porte-avions « Ville de Paris » Le Pasotti Airone F.6 Numéro 109 du 01/11/1954 Mémoires d’Adolf Galland J’ai essayé le Pasotti F.6 Airone Les décrochages (J. -
Combustion of Acetylene and Its Performance in Valveless Pulse Jet
Published by : International Journal of Engineering Research & Technology (IJERT) http://www.ijert.org ISSN: 2278-0181 Vol. 5 Issue 06, June-2016 Combustion of Acetylene and its Performance in Valveless Pulse Jet Engine M. Dhananiya Lakshmi Sri L. Oblisamy PG Scholar Assistant Professor Department of Aeronautical Engineering Department of Aeronautical Engineering Nehru Institute of Engineering and Technology Nehru Institute of Engineering and Technology Coimbatore, Tamil Nadu Coimbatore, Tamil Nadu G. Mari Prabu Assistant Professor Department of Aeronautical Engineering Sri Shakthi Institute of Engineering and Technology Coimbatore, Tamil Nadu Abstract—This paper summarizes the significance of barriers engine). Decreases non-linearly with decreasing characteristic involved in using acetylene as alternate fuel for valve less pulse engine length scale. Also, small scale engines with moving jet engine. Acetylene gas produces 2210 to 3300 degree Celsius parts are more prone to breakdown due to fatigue of the temperatures when allowed to combust with atmospheric air. moving components. Pulsejets, especially valveless The idea of high temperature engines is innovatory due to water pulsejets, are attractive as candidates for miniaturization due thermolysis which could accompany the combustion of to their extremely simple design.[7] acetylene. The use of acetylene will reduce emission and increase combustion efficiency. The project investigates the process of combustion of acetylene stoichiometrically with atmospheric air and also with oxygen computationally with the ANSYS Fluent commercial software in a valve less Bailey Machine Services hobby scale pulse jet of 15 centimeter class. The measurement of Pressure, thrust, temperature and concentrations of Carbon monoxide, Nitrous oxide and Hydrocarbons at the exit of pulse jet with acetylene and water thermolysis, Acetylene without water thermolysis and aviation gas without water thermolysis is analyzed and calculated. -
Aces of the Luftwaffe
Aces of the Luftwaffe Below are profiles of some of the Luftwaffe’s greatest pilots. Germany had the top 108 scoring aces of the Second World War, with scores ranging from 352 to 99 kills (for the top 108). The term ace can mean different things for different countries. Wikipedia puts it as this: “In World War II, many air forces credited fractional shares of aerial victories, resulting in fractions or decimal scores, such as 11½ or 26.83. Some U.S. commands also credited aircraft destroyed on the ground as equal to aerial victories. The Soviets distinguished between solo and group kills, as did the Japanese, though the IJN stopped crediting individual victories in 1943. The Luftwaffe continued the tradition of "one pilot, one kill", and now referred to top scorers as experten.” So German pilots got a kill for every aircraft they shot down. Name: Erich Hartmann Life: April 19, 1922 – September 20, 1993 Kills: 352 Notes: Erich Hartmann is the top scoring ace of all time, of any country. His 352 kills are 51 more than that of his closest rival, Gerhard Barkhorn. 345 of his kills were against the Soviets, as he fought mainly on the Ostfront (Eastern Front), and 260 of these were fighters. He also won the Ritterkreuz mit Eichenlaub, Schwerten und Brillianten (Knight's Cross of the Iron Cross with Oak Leaves, Swords and Diamonds), the second highest award in the German forces. He was imprisoned by the Soviets for 10 and a half years, and once released, went to West Germany and was put in charge of the post war JG 71 “Richtofen”, and retired in 1970. -
Secret Weapons, Experimental Designs, Jet Aircraft, Rockets & Missiles • Miscellaneous Aircraft & Topics
44 SECRET WEAPONS, EXPERIMENTAL DESIGNS, JET AIRCRAFT, ROCKETS & MISSILES • MISCELLANEOUS AIRCRAFT & TOPICS Messerschmitt Me 262 Manfred Griehl. De- Germany’s V-2 Rocket Gregory P. Kennedy. Mistel: The Piggy-Back Aircraft of the tailed one-volume short history of the legendary Although dwarfed by today’s giant rockets, the Luftwaffe H.P. Dabrowski. This unusual late- WWII-era Lufwaffe jet fighter. V-2 represented a quantum leap beyond anything war tandem bomb was actually used by the Size: 8.5”x11” • 80 color/bw photos • 52pp. previously built. During the last six months of the Luftwaffe during WWII. Covered are technical ISBN: 0-88740-820-6 • soft • $14.95 war in Europe, Germany launched thousands details of aircraft used, as well as operational info. of these missiles against the Allies. This book Size: 8.5”x11” • 80 bw photos/drawings • 52pp. traces the origins and development of the V-2, ISBN: 0-88740-668-8 • soft • $9.95 from groups of individual experimenters in the 1930s to its use as a weapon system. Size: 8.5”x11” • 130 bw photos • 136pp. ISBN: 0-7643-2452-7 • hard • $39.95 Natter & other German Rocket Jet German Guided Missiles Heinz Projects. Short history of the unusual J. Nowarra. Rare look at WWII-era German Nightfighters WWIIMan - WWII-era Luftwaffe manned rocket German air-to-air, surface-to-air, and fred Griehl. Concise photo history of the powered interceptor aircraft. air-to-ground guided missiles. wide variy of WWII Luftwaffe aircraft Size: 11”x8.5” • 80 bw photos • 48pp. Size: 11”x8.5” • 80 bw photos/drawings used in nightfighter mode. -
Jet Propulsion Test Stand P371
P.A. Hilton Ltd Jet Propulsion Test Stand P371 Demonstration and thermodynamic investigation of the simplest form of heat engine. Low cost, aircraft propulsion system investigation. Negligible operating cost and no moving parts requiring maintenance Two year warranty Page 1 Edition 2 P.A. Hilton Ltd Introduction Ram Jet Engine The ramjet, the simplest concept of aircraft For operation the ramjet requires incoming air propulsion, consists of an almost cylindrical to have a significant approach velocity in order duct, open at both ends. It relies on its forward to maintain combustion. The forward speed is speed to ram air into the forward opening. Fuel simulated by a single stage blower delivering is burnt inside the duct to accelerate the air air through a 76mm diameter nozzle mounted stream, which together with the products of 200mm in front of the air intake. The use of combustion, issues from the rear as a high gaseous fuel makes a low operating speed and velocity jet. The change in momentum in the therefore a moderate air supply requirement engine provides the propulsive force. well within the reach of any engineering Also supplied is a pulsejet engine, which laboratory. utilises a cyclic combustion process but is unique in design in that like the ramjet, it has no moving parts. The Hilton P371 Jet Propulsion Test Stand will provide interesting and instructive experimental activity for all students studying thermodynamics and propulsion and will be of particular interest to those studying: • Thermodynamics The ramjet engine is fabricated from a heat • Heat Transfer resistant alloy and requires no maintenance • Aeronautical engineering even after many years of operation. -
Pulsejet Engine Dynamics in Vertical Motion Using Momentum Conservation Tiberius O
Pulsejet engine dynamics in vertical motion using momentum conservation Tiberius O. Cheche University of Bucharest, Faculty of Physics, Bucharest 077125, Romania E-mail: [email protected] Received date Keywords: momentum conservation, pulsejet, V-1 flying bomb, turbojet, cephalopod, octopus Abstract. The momentum conservation law is applied to analyse the dynamics of pulsejet engine in vertical motion in a uniform gravitational field in the absence of friction. The model predicts existence of a terminal speed given frequency of the short pulses. The conditions that the engine does not return to the starting position are identified. The number of short periodic pulses after which the engine returns to the starting position is found to be independent of the exhaust velocity and gravitational field intensity for certain frequency of the pulses. The pulsejet engine and turbojet engine aircraft models of dynamics are compared. Also the octopus dynamics is modelled. The paper is addressed to intermediate undergraduate students of classical mechanics and aerospace engineering. 1. Introduction Systems generating reaction thrust by periodic fluid intake/exhaust cycle is common in nature and technology, for example the motion of some cephalopods [1, 2] and the pulsejet-powered aircrafts [3-5]. The basic processes occurring in these types of engines are well understood. The engine works by consumption of energy in an intake/exhaust cycle in which a fluid amount is taken into the engine and then expelled from it at a high relative velocity. A simple model for the pulsejet engine dynamics can be constructed by using one of the fundamental laws of the mechanics, namely, the principle of conservation of linear momentum, and ignoring the physical characteristics of the cycle (which, for example, in the case of aircraft would involve a thermodynamic description of air compression by ignition of air-fuel mixture). -
Thermodynamic Analysis and Preliminary Design of the Cooling
Thermodynamic analysis and preliminary design of the cooling system of a pulsejet for aeronautic propulsion TRANCOSSI, Michele, MOHAMMEDALAMIN, Omer, PASCOA, Jose and RODRIGUES, Frederico Available from Sheffield Hallam University Research Archive (SHURA) at: http://shura.shu.ac.uk/13960/ This document is the author deposited version. You are advised to consult the publisher's version if you wish to cite from it. Published version TRANCOSSI, Michele, MOHAMMEDALAMIN, Omer, PASCOA, Jose and RODRIGUES, Frederico (2016). Thermodynamic analysis and preliminary design of the cooling system of a pulsejet for aeronautic propulsion. International Journal of Heat and Technology, 34 (2), S528-S534. Copyright and re-use policy See http://shura.shu.ac.uk/information.html Sheffield Hallam University Research Archive http://shura.shu.ac.uk INTERNATIONAL JOURNAL OF A publication of IIETA HEAT AND TECHNOLOGY ISSN: 0392-8764 Vol. 34, Special Issue 2, October 2016, pp. S528-S534 DOI: https://doi.org/10.18280/ijht.34S247 Licensed under CC BY-NC 4.0 http://www.iieta.org/Journals/IJHT Thermodynamic Analysis and Preliminary Design of the Cooling System of a Pulsejet for Aeronautic Propulsion Michele Trancossi 1*, Omer Mohammedalamin 2, Jose C. Pascoa 3 and Frederico Rodrigues 3 1 Material and Engineering Research Insitute, ACES, Sheffield Hallam University, City Campus, Howard Street, Sheffield S1 1WB, UK, 2 Faculty of Arts, Computing, Engineering and Sciences, Sheffield Hallam University, City Campus, Howard Street, Sheffield S1 1WB, UK 3 Center for Mechanical and Aerospace Science and Technology, Universitade da Beira Interior, 6200-Covilhã, PT Email: [email protected] ABSTRACT This paper is a preliminary step through an effective redesign of valved pulsejet.