Optimal Jet Thruster Control of an Atmospheric Rocket PDF Download

Author: Dieter Schwarzmann
Publisher:
ISBN:
Category :
Languages : en
Pages : 226

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Author: DP Mishra
Publisher: CRC Press
ISBN: 1351708414
Category : Technology & Engineering
Languages : en
Pages : 364

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The book follows a unified approach to present the basic principles of rocket propulsion in concise and lucid form. This textbook comprises of ten chapters ranging from brief introduction and elements of rocket propulsion, aerothermodynamics to solid, liquid and hybrid propellant rocket engines with chapter on electrical propulsion. Worked out examples are also provided at the end of chapter for understanding uncertainty analysis. This book is designed and developed as an introductory text on the fundamental aspects of rocket propulsion for both undergraduate and graduate students. It is also aimed towards practicing engineers in the field of space engineering. This comprehensive guide also provides adequate problems for audience to understand intricate aspects of rocket propulsion enabling them to design and develop rocket engines for peaceful purposes.

Author: Bradley Thomas Burchett
Publisher:
ISBN:
Category : Rockets (Ordnance)
Languages : en
Pages : 348

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Uncontrolled direct fire rockets exhibit high impact point dispersion, even at relatively short range, and as such have been employed as area weapons on the battlefield. In order to reduce the dispersion of a direct fire rocket, feedback control is employed to fire short-duration solid rocket pulses mounted near the nose of the projectile and acting perpendicular to the projectile axis of symmetry. The feedback law is developed by first determining a piece wise linear model of the projectile swerving motion, subsequently using this linear model to predict the projectile impact point both with and without control, and using the results to command pulses at appropriate times to drive the impact point closer to the specified target. Candidate optimal control laws are formed using rules based on decision grids, and a global control strategy search algorithm. The global search control law proves to be prohibitively computationally expensive for on-line implementation. The performance of the baseline control law is found to be comparable to the rule based and global search optimal control laws. The control gains of the baseline control law are optimized in the presence of parametric plant uncertainty using a Monte Carlo simulation. Performance of the system in the presence of parametric plant uncertainty using the optimized gains is deemed comparable to performance of the baseline controller with no plant uncertainty. The level of uncertainty of several plant parameters is varied in order to compare robustness of the controller when optimized with uncertainty viz. without uncertainty.

Author: Dan M. Goebel
Publisher: John Wiley & Sons
ISBN: 0470436263
Category : Technology & Engineering
Languages : en
Pages : 528

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Throughout most of the twentieth century, electric propulsion was considered the technology of the future. Now, the future has arrived. This important new book explains the fundamentals of electric propulsion for spacecraft and describes in detail the physics and characteristics of the two major electric thrusters in use today, ion and Hall thrusters. The authors provide an introduction to plasma physics in order to allow readers to understand the models and derivations used in determining electric thruster performance. They then go on to present detailed explanations of: Thruster principles Ion thruster plasma generators and accelerator grids Hollow cathodes Hall thrusters Ion and Hall thruster plumes Flight ion and Hall thrusters Based largely on research and development performed at the Jet Propulsion Laboratory (JPL) and complemented with scores of tables, figures, homework problems, and references, Fundamentals of Electric Propulsion: Ion and Hall Thrusters is an indispensable textbook for advanced undergraduate and graduate students who are preparing to enter the aerospace industry. It also serves as an equally valuable resource for professional engineers already at work in the field.

Author: Thanat Jitpraphai
Publisher:
ISBN:
Category : Flight control
Languages : en
Pages : 256

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Impact point dispersion of a direct fire rocket can be drastically reduced with a ring of appropriately sized lateral pulse jets coupled to a trajectory tracking flight control system. The system is shown to work well against uncertainty in the form of initial off-axis angular velocity perturbations as well as atmospheric winds. For an example case examined, dispersion was reduced by a factor of one hundred. Dispersion reduction and mean miss distance are strong functions of the number of individual pulse jets, the pulse jet impulse, and the trajectory tracking window size. Proper selection of these parameters for a particular rocket and launcher combination is required to achieve optimum dispersion reduction to the pulse jet control mechanism. For the lateral pulse jet control mechanism that falls into the category of an impulse control mechanism, the trajectory tracking flight control law provides better reduction in dispersion and mean miss distance than the proportional navigation guidance law especially when small number of individual pulse jets is used. Estimation of body frame components of angular velocity and angular acceleration of a rigid body projectile undergoing general three-dimensional motion using linear acceleration measurements is considered. The results are comparable to those obtained from a conventional Inertial Measurement Unit (IMU) that composes of accelerometers and gyroscopes. From the study of the effect of sensor errors to the measurement and the control performance, the sensitivity of the angular rate estimation to the sensor noise is a strong function of the constellation of these three accelerometers. When more than three point measurements are used, the most effective method to fuse data is with one cluster that contains all sensors. In the conventional IMU, the dispersion and miss distance are less sensitive to the errors from accelerometers than to the gyroscopes. The estimation of angular rates plays essential roles in the performance of the control system in the reduction of dispersion and miss distance. The use of many accelerometers does not guarantee to reduce the sensitivity to errors. The selection of constellation among accelerometers in the data fusion process must be carefully taken into account.

Author: Martin J. L. Turner
Publisher: Springer Science & Business Media
ISBN: 9783540221906
Category : Science
Languages : en
Pages : 360

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A clear, accessible and up to date exposition of the principles and practice of rocket and spacecraft propulsion.

Author: National Research Council
Publisher: National Academies Press
ISBN: 0309102472
Category : Technology & Engineering
Languages : en
Pages : 288

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Book Description
Rocket and air-breathing propulsion systems are the foundation on which planning for future aerospace systems rests. A Review of United States Air Force and Department of Defense Aerospace Propulsion Needs assesses the existing technical base in these areas and examines the future Air Force capabilities the base will be expected to support. This report also defines gaps and recommends where future warfighter capabilities not yet fully defined could be met by current science and technology development plans.

Author: Gabi Ben-Dor
Publisher: World Scientific
ISBN: 9814439053
Category : Technology & Engineering
Languages : en
Pages : 697

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This important monograph is the first comprehensive compendium of engineering models used in high-speed penetration mechanics.The book consists of two parts. The first part (more than a quarter of the book's content) is in fact a handbook giving a very detailed summary of the engineering models used for the analysis of high-speed penetration of rigid projectiles into various media (concrete, metals, geological media). The second part of the book demonstrates the possibilities and efficiency of using approximate models for investigating traditional and nontraditional problems of penetration mechanics.Different chapters in the books are devoted to different classes of problems and can be read independently. Each chapter is self-contained, which includes a comprehensive literature survey of the topic, and carries a list of used notations. The bibliography includes more than 700 references.This monograph is a reliable and indispensable reference guide for anyone interested in using engineering models in high-speed penetration mechanics.

Author: Thanat Jitpraphai
Publisher:
ISBN:
Category : Precision guided munitions
Languages : en
Pages : 21

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Compared to gun launch ammunition, uncontrolled direct fire atmospheric rockets are terribly inaccurate, to the point where they are used most effectively on the battlefield as area weapons. Dispersion characteristics can be dramatically improved by outfitting the rocket with a suitable control mechanism and sensor suite. In the work reported here, a lateral pulse jet control mechanism is considered. The lateral pulse jet mechanism consists of a finite number of small thrusters spaced equally around the circumference of the rocket. Using a simulation model that includes projectile, flight control system, and inertial measurement unit dynamics, three different control laws are contrasted, namely, proportional navigation guidance, parabolic and proportional navigation guidance, and trajectory tracking control laws. When the number of individual pulse jets is small, a trajectory tracking control law provides superior dispersion reduction. However, as the number of pulse jets is increased, the relative performance of the parabolic and proportional navigation guidance control law is slightly better than the trajectory tracking control law. When the number of pulse jets is small, the proportional navigation guidance, as well as the parabolic and proportional navigation guidance control laws, exhibits large mean miss distance. All control laws appear to be equally susceptible to accelerometer and gyroscope errors that corrupt inertial measurement unit rocket state feedback.

Author: George Paul Sutton
Publisher: Wiley-Interscience
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 584

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