SPACE PROPULSION B. Tech VI Semester by DR
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Chap21 Rockets Fundamentals.Pdf
Chapter 21.indd 449 1/9/08 12:12:24 PM There is an explanation for everything that a rocket does. The explanation is most always based on the laws of physics and the nature of rocket propellants. Experimentation is required to find out whether a new rocket will or will not work. Even today, with all the knowledge and expertise that exists in the field of rocketry, experimentation occasionally shows that certain ideas are not practical. In this chapter, we will look back in time to the early developers and users of rocketry. We will review some of the physical laws that apply to rocketry, discuss selected chemicals and their combinations, and identify the rocket systems and their components. We also will look at the basics of rocket propellant efficiency. bjectives Explain why a rocket engine is called a reaction engine. Identify the country that first used the rocket as a weapon. Compare the rocketry advancements made by Eichstadt, Congreve and Hale. Name the scientist who solved theoretically the means by which a rocket could escape the earth’s gravitational field. Describe the primary innovation in rocketry developed by Dr. Goddard and Dr. Oberth. Explain the difference between gravitation and gravity. Describe the contributions of Galileo and Newton. Explain Newton’s law of universal gravitation. State Newton’s three laws of motion. Define force, velocity, acceleration and momentum. Apply Newton’s three laws of motion to rocketry. Identify two ways to increase the thrust of a rocket. State the function of the combustion chamber, the throat, and nozzle in a rocket engine. -
Turbojet Runs Precursor to Hypersonic Engine Heat Exchanger Tests
Turbojet Runs Precursor to Hypersonic Engine Heat Exchanger Tests Aviation Week & Space Technology Guy Norris Tue, 2018-05-15 04:00 Advanced propulsion developer Reaction Engines is nearing its first step toward validating its novel air-breathing hybrid rocket design at hypersonic conditions by firing up a vintage General Electric J79 turbojet to act as a heat source for testing, expected later this month. The ex-military engine, formerly used in a McDonnell Douglas F-4, is a central element of Reaction’s specially developed high-temperature airflow test site, which will soon be commissioned at Front Range Airport, near Watkins, Colorado. The J79 will provide heated gas flow in excess of 1,000C (1,800F) which, together with conditioned ambient air, will be mixed to replicate inlet conditions representative of flight speeds up to and including Mach 5. The flow will verify the operability and performance of the pre-cooler heat exchanger (HTX), which is at the core of Reaction’s Sabre (synergistic air-breathing rocket engine). It is also key to extracting oxygen from the atmosphere to enable acceleration to hypersonic speed from a standing start. The HTX will chill airflow to minus 150C in less than 1/20th of a second, and pass it through a turbo- compressor and into the rocket combustion chamber where it will be burned with sub-cooled liquid hydrogen (LH) fuel. Beyond Mach 5, and at an altitude approaching 100,000 ft. the inlet will be closed and the engine will continue to operate as a closed-cycle rocket engine fueled by onboard liquid oxygen and LH. -
Liquid Propollant Rocket Engines
THERMAL TO MECHANICAL ENERGY CONVERSION: ENGINES AND REQUIREMENTS – Vol. II - Liquid Propellant Rocket Engines - V.M. Polyaev and V.A. Burkaltsev LIQUID PROPELLANT ROCKET ENGINES V.M. Polyaev and V.A. Burkaltsev Department of Rocket engines, Bauman Moscow State Technical University, Russia. Keywords: Liquid rocket engine, liquid rocket propellant, chamber, combustion products, pressure, temperature, density, cooling, supply system, turbopump assembly, gas generator, engine installation, thrust, specific impulse, specific mass. Contents 1. Introduction 2. LRE general information 3. Main LRE parameters 4. LRE structure and liquid rocket engine installations (LREI) schemes 5. Historical reference 6. LRE development tendencies 7. Conclusions Acknowledgment Glossary Bibliography Biographical Sketches 1. Introduction All chemical rocket engines have two common characteristics. They utilize chemical reactions in a thrust chamber to produce a high-pressure, high-temperature gas at the entrance to a converging-diverging exhaust nozzle. The hot propellant gas expands in flowing through the nozzle, and the expansion process converts a portion of the thermal energy released by the chemical reaction into kinetic energy associated with a high- velocity gaseous-exhaust jet. 2. LRE general information The liquid propellant rocket engine (LRE) is a direct reaction engine using the liquid rocket propellantUNESCO stored on a flight vehicle – board EOLSS for thrust creation. The liquid rocket propellant (LRP) is a substance in the liquid state which is capable to be converted intoSAMPLE a reactive gas jet discharging CHAPTERS from the engine and creating a thrust as a result of the exothermal reaction associated with heat release. LRP consists of liquid components. The propellant components can include one substance or a mixture of individual chemical substances. -
Aviation Fuels Technical Review
Aviation Fuels Technical Review | Chevron Products Aviation Fuels Company Technical Review Chevron Products Company 6001 Bollinger Canyon Road San Ramon, CA 94583 Chevron Products Company is a division of a wholly owned subsidiary of Chevron Corporation. http://www.chevron.com/productsservices/aviation/ © 2007 Chevron U.S.A. Inc. All rights reserved. Chevron and the Caltex, Chevron and Texaco hallmarks are federally registered trademarks of Chevron Intellectual Property LLC. Recycled/RecyclableRecycled/recyclable paper paper IDC 1114-099612 MS-9891 (11/14) Table of Contents Notes General Introduction ............................................................i 8 • Aviation Gasoline Performance ............................ 45 Performance Properties 1 • Aviation Turbine Fuel Introduction ........................... 1 Cleanliness Types of Fuel Safety Properties Fuel Consumption 9 • Aviation Gasoline 2 • Aviation Turbine Fuel Performance .........................3 Specifications and Test Methods .......................... 54 Performance Properties Specifications Cleanliness Future Fuels Safety Properties Test Methods Emissions 10 • Aviation Gasoline Composition ............................. 63 3 • Aviation Turbine Fuel Composition Specifications and Test Method ...............................14 Property/Composition Relationships Specifications Additives Test Methods 11 • Aviation Gasoline Refining ..................................... 66 4 • Aviation Turbine Fuel Composition ........................24 Alkylation Base Fuel Avgas Blending -
19820018505.Pdf
NASA CR 167885 NASA-CR-167885 19820018505 '." ....... _, 1.:.,. NI\S/\ - .. '.' 1 CHARACTERIZATION OF ADVANCED ELECTRIC PROPULSION SYSTEMS PREPARED FOR LEWIS RESEARCH CENTER NATIONAL AERONAUTICS AND SPACE ADMINISTRATION GRANT NAG 3-76 '" 1982 L':::""o' ," r;'S,;.R::~ CENTER Final Report I ;:"~~ I (.';1, VIRGINIA May 1982 Pradosh K. Ray Department of Mechanical Engineering Tuskegee Institute Tuskegee Institute, Alabama 1111111111111 1111 11111 1111111111 11111 1111 1111 NF02692 1. Report No. I 2. Government AcclISsion No. 3. Recipient's Catalog No. NASA CR 167885 4. Title and Subtitle 5. Report Date Characterization of Advanced Electric May, 1982 Propulsion Systems 6. Performing Organization Code 7.. Author(s) 8. Performing Organization Report No. Pradosh K. Ray 10. Work Unit No. 9. Performing Organization Nlme and Addr... Department of Mechanical Engineering 11. Contract or Grant No. Tuskegee Institute Tuskegee Institute, Alabama 36088 NAG 3-76 13. Type of Report and Period Covered 12. Sponsoring AgencV Name and Addresl June 1, 1980-January 31, 198;: National Aeronautics and Space Administration Washington, D.C. 20546 14. Sponsoring Agency Code 15. Supplementary Notes Grant Monitor--William Kerslake, NASA Lewis Research Center Cleveland, Ohio 44135 16. Abstract Characteristics of several advanced electric propulsion systems are evaluated and compared. The propulsion systems studied are mass driver, rail gun, MPD thruster, hydrogen free radical thruster and mercury electron bombardment ion engine. These are characterized by specific impulse, overall effiCiency, input power, average thrust, power to average thrust ratio and average thrust to dry weight ratio. Several important physical characteristics such as dry system mass, accelerator length, bore size and current pulse requirement are also evaluated in appropriate cases. -
Nasa Tm X-52391 Memorandum
. NASA TECHNICAL NASA TM X-52391 MEMORANDUM I GPO PRICE $ CSFTl PRlCE(S) $ Hard copy (HC) .- Microfiche (MF) - ff 653 July 65 EXPLORING IN AEROSPACE ROCKETRY 4. THERMODYNAMICS by Marshall C. Burrows Lewis Research Center Cleveland, Ohio Presented to Lewis Aerospace Explorers Cleveland, Ohio 1966 -67 N NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D.C. 1968 EXPLORING IN AEROSPACE ROCKETRY 4. THERMODYNAMICS Marshall C. Burrows Presented to Lewis Aerospace Explorers Cleveland, Ohio 1966 -67 Advisor, James F. Connors NATIONAL AERONAUTICS AND SPACE ADMINISTRATION NASA Technical Chapter Memorandum 1 AEROSPACE ENVIRONMENT John C. Evvard ........................... X-52388 2 PROPULSION FUNDAMENTALS James F. Connors .......................... X-52389 3 CALCULATION OF ROCKET VERTICAL-FLIGHT PERFORMANCE John C. Evvard ............................ X-52390 4 THERMODYNAMICS I Marshall C. Burrows ........................ X-52391 5 MATERIALS William D. Klopp ........................... X - 523 92 6 SOLID-PROPELLANT ROCKET SYSTEMS Joseph F. McBride .......................... X-52393 7 LIQUID-PROPELLANT ROCKET SYSTEMS E. William Conrad .......................... X-52394 8 ZERO - GRAVITY EFFECTS William J. Masica .......................... X-52395 9 ROCKET TRAJECTORIES, DRAG, AND STABILITY Roger W. Luidens .......................... X-52396 10 SPACE MISSIONS Richard J. Weber. .......................... X - 52397 11 LAUNCH VEHICLES Arthur V. Zimmerman ........................ X-52398 12 INERTIAL GUIDANCE SYSTEMS Daniel J. Shramo .......................... -
Modeling and Simulation of Air-Vehicle Entry Scheme Based on Composite Precooling Engine
2018 International Conference on Physics, Mathematics, Statistics Modelling and Simulation (PMSMS 2018) ISBN: 978-1-60595-558-2 Modeling and Simulation of Air-Vehicle Entry Scheme Based on Composite Precooling Engine Xin-lei YANG, Wan-sheng NIE*, Hai-qing WANG, Hui WANG and Ling-yu SU Space Engineering University, Beijing, China *Corresponding author Keywords: Composite precooling engine, Air-vehicle entry scheme, Modeling and simulation. Abstract. Based on the composite precooling engine, a Single-Stage-To-Orbit (SSTO) scheme is proposed. The climbing process is divided into three stages. The dynamic model, the air-vehicle model and the motion model are set up, and the feasibility of SSTO is studied using the numerical simulation. In order to improve the SSTO scheme, a SSTO scheme based on launching vehicle is proposed and a Two-Stage-To-Orbit (TSTO) powered by the composite precooling engine in the first stage and the rocket engine in the second stage is proposed. The results show that if the SSTO scheme is achieved, the structural coefficient of the air-vehicle should be less than 0.13, which has great technical difficulty. By adopting the SSTO scheme based on launching vehicle, the structural coefficient can be relaxed to 0.19, and the technical difficulty will be greatly reduced. The adoption of the TSTO scheme can not only effectively reduce the technical difficulty, but also increase the payload from 15t to 20.31t. Introduction In recent years, the aerospace powers led by the United States and Russia have proposed and are implementing a series of design and development plans for combined cycle engines [1] . -
Electric Hypersonic Space Aircraft
1 Article Electric Hypersonic Aircraft 5 31 14 after Shmuel Electric Hypersonic Space Aircraft Alexander Bolonkin C&R, USA [email protected] Abstract Aviation, in general, and aerospace in particular needs new propulsion systems which allow a craft to reach high speeds by cheaper and more efficient methods. Author offers a new high efficiency propulsion system using electrons for acceleration of the craft. As this system does not heat the air, it does not have the heating limitations of conventional air ramjet hypersonic engines. Offered engine can produce a thrust from a zero flight speed up to the desired escape velocity for space launch. It can work in any planet atmosphere (gas, liquid) and at high altitude. The system can use apparatus surface for thrust and braking. For energy the system uses high voltage electricity which is not a problem if you have an appropriate electrostatic generator connected with any suitable engine. The new propulsion system applies to hypersonic long-range aviation, for launch of space craft and as a high efficiency rocket in solar space. This can be actualized using current technology. ------------------------------------------------------- Key words: Electron propulsion, hypersonic propulsion, space propulsion, ABEP. 1. INTRODUCTION Let us consider the status of the problem succinctly. Aviation and space launch. In the last half century, development of aviation and space launch proceeded very slowly. The last major advance in aviation was the introduction of the reactive engine. Space launch started using a chemical rocket and is still using it at the present time. For more than thirty years, employing the same old engines researchers unsurprisingly come up against the same barriers which do not allow significantly improving flight. -
Review on Cryogenic and Jet Engine
International Research Journal of Engineering and Technology (IRJET) e-ISSN: 2395-0056 Volume: 08 Issue: 07 | July 2021 www.irjet.net p-ISSN: 2395-0072 Review on Cryogenic and Jet Engine Abhishiktha Pagadala1, G Ritvik2, Lagumavarapu Venkata Guru Abhiram3 1,2,3Student, Dept. of Aerospace Engineering, Amrita School of Engineering, Tamil Nadu, India. ---------------------------------------------------------------------***--------------------------------------------------------------------- Abstract - This paper gives an insight to the technology Jet engines are reaction engines. They are mainly used behind jet and cryogenic engines. A cryogenic engine uses to propel aircrafts. They draw air from the atmosphere, liquid fuel and oxidizer stored at extremely low temperatures increase its pressure by squeezing it and hence, use it for combustion, whereas a jet engine burns its fuel with the for the most required combustion reaction. The help of air sucked in from the atmosphere. This paper gives resulting hot gases are released from the nozzle of the an overview on how a cryogenic engine is different from a jet engine, providing enough thrust to the aircraft to move forward. engine. Also, the components and working of both cryogenic Jet aircrafts use turbojet engines which usually utilize engine and jet engine have been discussed. The liquid fuel and an afterburn, which is a second combustion chamber, oxidizer, when stored at extreme conditions, gives high placed between the turbine and the nozzle of the enthalpy of combustion on reaction, which makes it more engine. An afterburn elevates the temperature of the efficient when compared to jet engine. CE-20 is the first hot gases, thereby increasing the thrust of the aircraft indigenous cryogenic engine, which has proved to be highly by almost 40% during take-off and much higher during effective when used in GSLV MK-III. -
Spacecraft and Their Boosters. Aerospace Education I
DOCUMENT RESUNE ED 111 611 SE 017 448 AUTHOR Coard, E. A. TITLE Spacecraft and their Boosters. AejOspace Education INSTITUTION Air Univ., Maxwell AFB, Ala. Junior Reserve Office Training, Corps. PUB DATE 72 NOTE 200p.; Colored drawings may not reproduce.clearly. For the accompanying Instructor Handbook, see SE 017 449 EDRS PRICE MF-$0.76 HC-$9.51 Plus Postage DESCRIPTORS *Aerospace Education; *Aerospace Technology; *Astronomy; Aviation Technology; Energy; *Instructional Materials; National Defense; *Pkysical Sciences; Secondary Education; Textbooks IDENTIFIERS Air Force Junior ROTC; *Spacecraltt zJ ABSTRACT This book, one in the series on Aerospace.Education I, provides a description of some of the discoveries that spacecraft have made possible and of the experience that American astronauts have had in piloting spacecraft. The basic principles behind the operation of spacecraft and their boosters are explained. Descriptions are also included on unmanned and manned spacecraft. Brief mention is made of space stations, reusable spice vehicles, and spacecraft fitted with specialized equipment for planetary exploration. The book is designed for use in the Air Force Junior ROTC program. (PS) *********************************************************************** Documents acquired by ERIC include many informal unpublished * materials not available from other sources. ERIC makes every effort * * to obtain the best copy available. nevertheless, items of marginal * * reprodlicibility are often encounte'red and this affects the quality, * * of the microfiche and hardcopy reproductions ERIC makes available * * via the ERIC Document Reproduction Service (EDRS). EDRS'is not * responsible for the quality of the original document. Reproductions * * supplied. by EDRS are the best that can be made from the original. *********************************************************************** S DEPARTMENT OF0EALTH EOLICATiON LwELFAIRE KAT,ONAt. -
Aircraft Propulsion Systems NORTH AMERICA Propellers Are the Most Representative Symbol of Aerial Propulsion
EUROPE LATIN AMERICA MIDDLE EAST Aircraft propulsion systems NORTH AMERICA Propellers are the most representative symbol of aerial propulsion. aertecsolutions.com An aircraft’s propulsion system is directly related to They are made up of a variable number of blades which, when rotating the tasks and objectives it carries out around a shaft, generate a propulsive force. Aeronautical milestones Internal combustion engine Reaction engines Rocket engine Other aeronautical Up until the Second World War, the only propulsion system Reaction engines operate by taking air from outside through Rocket engines generate thrust by expelling gases from propulsion systems Did you know...? used in aircraft was internal combustion engines. The a diffuser, compressing it in the compressor, passing it the combustion chamber into the atmosphere. They technique they employ consists of transmitting the power through a combustion chamber mixed with fuel, and burning combine both the fuel and a comburent (oxidiser). These Electric motor 1785 obtained from a reciprocating engine to a rotating shaft. it to raise the pressure and temperature. It then passes are the most powerful types of engine known, and their Their main Jean Pierre Blanchard The shaft is solidly attached to a propeller that is ultimately through a turbine, where the pressure and temperature are weight/power ratio makes them ideal for use in spacecraft. components are the crossed the English responsible for propulsion, as its rotational movement reduced in exchange for mechanical power to drive the battery, controller, Channel in a balloon that generates thrust in the required direction. compressor. The air is expelled at high speed through the Solid motor and rotor. -
Part Iii : Space Transportation, Propulsion and Pathway Options
SICSA SPACE ARCHITECTURE SEMINAR LECTURE SERIES PART III : SPACE TRANSPORTATION, PROPULSION AND PATHWAY OPTIONS www.sicsa.uh.edu LARRY BELL, SASAKAWA INTERNATIONAL CENTER FOR SPACE ARCHITECTURE (SICSA) GERALD D.HINES COLLEGE OF ARCHITECTURE, UNIVERSITY OF HOUSTON, HOUSTON, TX The Sasakawa International Center for SICSA routinely presents its publications, Space Architecture (SICSA), an research and design results and other organization attached to the University of information materials on its website Houston’s Gerald D. Hines College of (www.sicsa.uh.edu). This is done as a free Architecture, offers advanced courses service to other interested institutions and that address a broad range of space individuals throughout the world who share our systems research and design topics. In interests. 2003 SICSA and the college initiated Earth’s first MS-Space Architecture This report is offered in a PowerPoint format with degree program, an interdisciplinary 30 the dedicated intent to be useful for academic, credit hour curriculum that is open to corporate and professional organizations who participants from many fields. Some wish to present it in group forums. The document students attend part-time while holding is the third in a series of seminar lectures that professional employment positions at SICSA has prepared as information material for NASA, affiliated aerospace corporations its own academic applications. We hope that and other companies, while others these materials will also be valuable for others complete their coursework more rapidly