Space Flight Dynamics, 2Nd Edition Craig A

Total Page：16

File Type：pdf, Size：1020Kb

To purchase this product, please visit https://www.wiley.com/en-az/9781119157823 Space Flight Dynamics, 2nd Edition Craig A. Kluever E-Book 978-1-119-15784-7 March 2018 €83.99 Hardcover 978-1-119-15782-3 March 2018 €93.30 DESCRIPTION Thorough coverage of space flight topics with self-contained chapters serving a variety of courses in orbital mechanics, spacecraft dynamics, and astronautics This concise yet comprehensive book on space flight dynamics addresses all phases of a space mission: getting to space (launch trajectories), satellite motion in space (orbital motion, orbit transfers, attitude dynamics), and returning from space (entry flight mechanics). It focuses on orbital mechanics with emphasis on two-body motion, orbit determination, and orbital maneuvers with applications in Earth-centered missions and interplanetary missions. Space Flight Dynamics presents wide-ranging information on a host of topics not always covered in competing books. It discusses relative motion, entry flight mechanics, low-thrust transfers, rocket propulsion fundamentals, attitude dynamics, and attitude control. The book is filled with illustrated concepts and real-world examples drawn from the space industry. Additionally, the book includes a “computational toolbox” composed of MATLAB M-files for performing space mission analysis. Key features: • Provides practical, real-world examples illustrating key concepts throughout the book • Accompanied by a website containing MATLAB M-files for conducting space mission analysis • Presents numerous space flight topics absent in competing titles Space Flight Dynamics is a welcome addition to the field, ideally suited for upper-level undergraduate and graduate students studying aerospace engineering. ABOUT THE AUTHOR Craig A. Kluever is C. W. LaPierre Professor of Mechanical and Aerospace Engineering, University of Missouri-Columbia, USA. He has industry experience as an aerospace engineer on the Space Shuttle program and has performed extensive research at the University of Missouri in collaboration with NASA involving trajectory optimization, space mission design, entry flight mechanics, and guidance and control of aerospace vehicles. RELATED RESOURCES Instructor View Instructor Companion Site Contact your Rep for all inquiries SERIES Aerospace Series To purchase this product, please visit https://www.wiley.com/en-az/9781119157823.

Copy Link

Recommended publications

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.
[Show full text]
Rocket Nozzles: 75 Years of Research and Development
Sådhanå Ó (2021) 46:76 Indian Academy of Sciences https://doi.org/10.1007/s12046-021-01584-6Sadhana(0123456789().,-volV)FT3](0123456789().,-volV) Rocket nozzles: 75 years of research and development SHIVANG KHARE1 and UJJWAL K SAHA2,* 1 Department of Energy and Process Engineering, Norwegian University of Science and Technology, 7491 Trondheim, Norway 2 Department of Mechanical Engineering, Indian Institute of Technology Guwahati, Guwahati 781039, India e-mail: [email protected]; [email protected] MS received 28 August 2020; revised 20 December 2020; accepted 28 January 2021 Abstract. The nozzle forms a large segment of the rocket engine structure, and as a whole, the performance of a rocket largely depends upon its aerodynamic design. The principal parameters in this context are the shape of the nozzle contour and the nozzle area expansion ratio. A careful shaping of the nozzle contour can lead to a high gain in its performance. As a consequence of intensive research, the design and the shape of rocket nozzles have undergone a series of development over the last several decades. The notable among them are conical, bell, plug, expansion-deflection and dual bell nozzles, besides the recently developed multi nozzle grid. However, to the best of authors’ knowledge, no article has reviewed the entire group of nozzles in a systematic and comprehensive manner. This paper aims to review and bring all such development in one single frame. The article mainly focuses on the aerodynamic aspects of all the rocket nozzles developed till date and summarizes the major findings covering their design, development, utilization, benefits and limitations.
[Show full text]
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.
[Show full text]
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.
[Show full text]
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.
[Show full text]
GE Marine Gas Turbine Propulsion for Frigates
GE Marine Gas Turbines for Frigates March 2018 GE’s Marine Solutions One Neumann Way MD S156 Cincinnati, Ohio USA 45215 www.ge.com/marine GE Marine Gas Turbines for Frigates Introduction The important role of a frigate is to escort and protect other high value fleet and merchant ships the world over. Frigates operate independently and possess sufficient capabilities (i.e. anti-submarine, anti-ship and anti-air) to provide missions in maritime and wartime environments. With GE being the market leader in the supply of marine propulsion gas turbines and seeing the proliferation in the demand for frigates, we wanted to know how our gas turbines and product roadmap compared to the needs of frigates. Before we could answer that question, we needed to answer the following two questions: 1. What are propulsion trends for frigates? 2. What are key attributes or requirements, and how do they translate to gas turbine propulsion characteristics? The key attributes of a frigate were taken from the July 2017 United States Navy Future Guided Missile Frigate (FFG(X)) Request for Information (RFI). It is anticipated the attributes would be common to many of the world’s frigates. Frigate Propulsion Trends and GE LM2500 Family Gas Turbine Suitability GE performed an analysis of all the frigates built since 1960 excluding certain countries such as Russia and China. Classification of a ship as a frigate is a gray area as there is blending of smaller corvettes and larger destroyers. For this analysis, we used the Wikipedia listing of frigates. All of the following ship data was obtained from public information such as Wikipedia and IHS Jane’s Fighting Ships.
[Show full text]
Introduction to Aircraft Stability and Control Course Notes for M&AE 5070
Introduction to Aircraft Stability and Control Course Notes for M&AE 5070 David A. Caughey Sibley School of Mechanical & Aerospace Engineering Cornell University Ithaca, New York 14853-7501 2011 2 Contents 1 Introduction to Flight Dynamics 1 1.1 Introduction....................................... 1 1.2 Nomenclature........................................ 3 1.2.1 Implications of Vehicle Symmetry . 4 1.2.2 AerodynamicControls .............................. 5 1.2.3 Force and Moment Coefficients . 5 1.2.4 Atmospheric Properties . 6 2 Aerodynamic Background 11 2.1 Introduction....................................... 11 2.2 Lifting surface geometry and nomenclature . 12 2.2.1 Geometric properties of trapezoidal wings . 13 2.3 Aerodynamic properties of airfoils . ..... 14 2.4 Aerodynamic properties of finite wings . 17 2.5 Fuselage contribution to pitch stiffness . 19 2.6 Wing-tail interference . 20 2.7 ControlSurfaces ..................................... 20 3 Static Longitudinal Stability and Control 25 3.1 ControlFixedStability.............................. ..... 25 v vi CONTENTS 3.2 Static Longitudinal Control . 28 3.2.1 Longitudinal Maneuvers – the Pull-up . 29 3.3 Control Surface Hinge Moments . 33 3.3.1 Control Surface Hinge Moments . 33 3.3.2 Control free Neutral Point . 35 3.3.3 TrimTabs...................................... 36 3.3.4 ControlForceforTrim. 37 3.3.5 Control-force for Maneuver . 39 3.4 Forward and Aft Limits of C.G. Position . ......... 41 4 Dynamical Equations for Flight Vehicles 45 4.1 BasicEquationsofMotion. ..... 45 4.1.1 ForceEquations .................................. 46 4.1.2 MomentEquations................................. 49 4.2 Linearized Equations of Motion . 50 4.3 Representation of Aerodynamic Forces and Moments . 52 4.3.1 Longitudinal Stability Derivatives . 54 4.3.2 Lateral/Directional Stability Derivatives .
[Show full text]
Alexander 2013 Principles-Of-Animal-Locomotion.Pdf
.................................................... Principles of Animal Locomotion Principles of Animal Locomotion ..................................................... R. McNeill Alexander PRINCETON UNIVERSITY PRESS PRINCETON AND OXFORD Copyright © 2003 by Princeton University Press Published by Princeton University Press, 41 William Street, Princeton, New Jersey 08540 In the United Kingdom: Princeton University Press, 3 Market Place, Woodstock, Oxfordshire OX20 1SY All Rights Reserved Second printing, and ﬁrst paperback printing, 2006 Paperback ISBN-13: 978-0-691-12634-0 Paperback ISBN-10: 0-691-12634-8 The Library of Congress has cataloged the cloth edition of this book as follows Alexander, R. McNeill. Principles of animal locomotion / R. McNeill Alexander. p. cm. Includes bibliographical references (p. ). ISBN 0-691-08678-8 (alk. paper) 1. Animal locomotion. I. Title. QP301.A2963 2002 591.47′9—dc21 2002016904 British Library Cataloging-in-Publication Data is available This book has been composed in Galliard and Bulmer Printed on acid-free paper. ∞ pup.princeton.edu Printed in the United States of America 1098765432 Contents ............................................................... PREFACE ix Chapter 1. The Best Way to Travel 1 1.1. Fitness 1 1.2. Speed 2 1.3. Acceleration and Maneuverability 2 1.4. Endurance 4 1.5. Economy of Energy 7 1.6. Stability 8 1.7. Compromises 9 1.8. Constraints 9 1.9. Optimization Theory 10 1.10. Gaits 12 Chapter 2. Muscle, the Motor 15 2.1. How Muscles Exert Force 15 2.2. Shortening and Lengthening Muscle 22 2.3. Power Output of Muscles 26 2.4. Pennation Patterns and Moment Arms 28 2.5. Power Consumption 31 2.6. Some Other Types of Muscle 34 Chapter 3.
[Show full text]
Interactions Between Flight Dynamics and Propulsion Systems of Air-Breathing Hypersonic Vehicles
Interactions between Flight Dynamics and Propulsion Systems of Air-Breathing Hypersonic Vehicles by Derek J. Dalle A dissertation submitted in partial fulﬁllment of the requirements for the degree of Doctor of Philosophy (Aerospace Engineering) in the University of Michigan 2013 Doctoral Committee: Professor James F. Driscoll, Chair Michael A. Bolender, Air Force Research Laboratory Associate Professor Joaquim R. R. A. Martins Assistant Professor David J. Singer ©Derek J. Dalle 2013 DEDICATION This dissertation is dedicated to Sara Spangelo, who showed me that graduate school is more than fun, games, doing re- search, and writing papers. Among other things, it was also a lot of running, eating, running, and making pretty graph- ics. She also strongly recommended that I dedicate this dis- sertation to her. ii Acknowledgments I would like to thank Professor Driscoll for guiding me through the Ph.D. program and being a great advisor. My experience here was about as close to perfect as I could hope to expect, and Jim is more responsible for that than anyone else. My colleague Dr. Sean M. Torrez, who was also a Ph.D. student of Professor Driscoll, was essential in the creation of the MASIV and MASTrim models. Also, we made a very good team. I would also like to thank my committee for their support and work in reviewing my thesis. This research was funded by the Air Force Research Laboratory/Air Vehicles Directorate grant FA 8650-07-2-3744 for the Michigan/AFRL Collaborative Center in Control Sciences. iii TABLE OF CONTENTS Dedication ....................................... ii Acknowledgments ................................... iii List of Figures ....................................
[Show full text]
A Coupled Lateral/Directional Flight Dynamics and Structural Model for Flight Control Applications
A Coupled Lateral/Directional Flight Dynamics and Structural Model for Flight Control Applications Ondrej Juhasz∗ San Jose State University Research Foundation, Moffett Field, CA Mark B. Tischlery U.S. Army Aviation Development Directorate-AFDD, Moffett Field, CA Steven G. Hagerott,z David Staples,x and Javier Fuentealba { Cessna Aircraft Company, Wichita, KS A lateral/directional flight dynamics model which includes airframe flexibility is de- veloped in the frequency domain using system-identification methods. At low frequency, the identified model tracks a rigid-body (static-elastic) model. At higher frequencies, the model tracks a finite-element NASTRAN structural model. The identification technique is implemented on a mid-sized business jet to obtain a state-space representation of the air- craft equations of motion including two structural modes. Low frequency structural modes and their associated notch filters impact the flight control frequency range of interest. For a high bandwidth control system, this frequency range may extend up to 30 rad/sec. These modes must be accounted for by the control system designer to ensure aircraft stability is retained when a control system is implemented to help avoid aeroservoelastic coupling. A control system is developed and notch filters are selected for the developed coupled air- craft model to demonstrate the importance of including the structural modes in the design process. Nomenclature β Sideslip angle ζdr Dutch-roll damping ratio ζstrn Damping ratio of structural mode n ηδn Control derivative
[Show full text]
Department of Aerospace Engineering 1
Department of Aerospace Engineering 1 7. An ability to communicate effectively Department of 8. The broad education necessary to understand the impact of engineering solutions in a global, economic, environmental, and Aerospace Engineering societal context 9. A recognition of the need for, and an ability to engage in life-long Aerospace Engineering learning 10. A knowledge of contemporary issues The aerospace engineering discipline involves the design, production, 11. An ability to use the techniques, skills, and modern engineering tools operation, and support of aircraft and spacecraft. Aerospace engineers necessary for engineering practice solve problems, design aircraft and spacecraft, conduct research, and improve processes for the aerospace industry. Undergraduate Programs Mission The curriculum includes traditional courses in aerodynamics, KUAE fosters a world-class community of choice for students, flight dynamics and control, propulsion, structures, manufacturing, educators, researchers and industry partners by strategically aligning instrumentation, and spacecraft systems. Capstone design courses are our teaching, research and service missions to prepare students for offered in aircraft, propulsion, and spacecraft design. successful professional careers by providing them with foundational The Bachelor of Science degree in aerospace engineering is accredited knowledge in and experience with aerospace engineering disciplines by the Engineering Accreditation Commission of ABET, http:// and interdisciplinary systems integration, while advancing the state-of- www.abet.org. the-art. A world-class graduate and undergraduate education focused on designing, simulating, building, testing, and flying aerospace vehicles is provided. The department invests in research infrastructure and Graduate Programs chooses outstanding students, faculty, and staff to conduct basic and The Department of Aerospace Engineering offers traditional Master of applied research of relevance to aerospace vehicles and systems.
[Show full text]
Flight Dynamics and Control of a Vertical Tailless Aircraft
cs & Aero ti sp au a n c o e r E e n Bras et al., J Aeronaut Aerospace Eng 2013, 2:4 A g f i o n Journal of Aeronautics & Aerospace l e DOI: 10.4172/2168-9792.1000119 a e r n i r n u g o J Engineering ISSN: 2168-9792 Research Article Open Access Flight Dynamics and Control of a Vertical Tailless Aircraft Bras M1, Vale J1, Lau F1 and Suleman A2* 1Instituto Superior Técnico, Lisbon, Portugal 2University of Victoria, Victoria BC, Canada Abstract The present work aims at studying a new concept of a vertical tailless aircraft provided with a morphing tail solution with the purpose of eliminating the drag and weight created by the vertical tail structure. The solution consists on a rotary horizontal tail with independent left and right halves to serve as control surfaces. Different static scenarios are studied for different tail configurations. The proposed morphing configurations are analyzed in terms of static and dynamic stability and compared with a conventional configuration. The stability derivatives defining the limits of static stability are calculated for the whole range of tail rotation angles. The aircraft’s dynamic model is developed and feedback control systems are implemented. A sideslip suppression system, a heading control system and a speed and altitude hold system are studied for three different configurations, MC1, MC2 and MC3 configurations. Static results show that the aircraft is longitudinally stable for a wide range of tail rotation angles. Variation of tail dihedral and rotation angles are two mechanisms able to maintain directional and lateral stability but only the last is able to produce lateral force and yawing moment.
[Show full text]