Optimal Guidance Command Generation And Tracking For The Reentry Of A Reusable Launch Vehicle Preprint

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Optimal Guidance Command Generation and Tracking for the Reentry of a Reusable Launch Vehicle (PREPRINT).

Author :
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (742 download)

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Book Synopsis Optimal Guidance Command Generation and Tracking for the Reentry of a Reusable Launch Vehicle (PREPRINT). by :

Download or read book Optimal Guidance Command Generation and Tracking for the Reentry of a Reusable Launch Vehicle (PREPRINT). written by and published by . This book was released on 2006 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this work, optimal outer-loop guidance commands are generated from an off-line reference trajectory and then tracked by a reconfigurable inner-loop control law. The primary motivation for this work is a "stepping-stone" towards online, optimal trajectory generation, footprint determination, and retargeting capabilities in the presence of control effector failures or vehicle structural/ aerodynamic degradation, uncertainty, and external disturbances. The presented guidance and control architecture uses a 6-degree-of-freedom simulation and an inner-loop controller to track body-name angular rates (roll, pitch, and yaw), generated from an optimal psuedo-4-degree-of-freedom reference trajectory that is computed using a direct pseudo spectral method. The innerloop control law is capable of reacting and compensating for off-nominal conditions by employing its nonlinear control allocation, dynamic inversion, and model-following/anti-windup prefilters. The results show that the inner-loop control can adequately track the desired optimal guidance commands; thus, confirming the applicability of this control architecture for future development involving on-line, optimal trajectory generation and high-fidelity footprint determination for reentry vehicles.

Optimal Guidance Command Generation and Tracking for Reusable Launch Vehicle Reentry (Preprint).

Author :
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.:/5 (227 download)

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Book Synopsis Optimal Guidance Command Generation and Tracking for Reusable Launch Vehicle Reentry (Preprint). by :

Download or read book Optimal Guidance Command Generation and Tracking for Reusable Launch Vehicle Reentry (Preprint). written by and published by . This book was released on 2006 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this work is to develop a robust guidance and control architecture for autonomous reusable launch vehicles that incorporates elements of recent advances in the areas of optimal trajectory generation and reconfigurable control. This work integrates three separately developed methods to form a coherent architecture with the potential to manage control effector failures, vehicle structural/aerodynamic degradation, uncertainty, and external disturbances. Outer-loop guidance commands in the form of body-frame angular rates (roll, pitch, and yaw) are generated from an optimal reference trajectory that is computed off-line with a direct pseudospectral method and then tracked by a reconfigurable inner-loop control law. The appropriate open-loop state histories from the pseudo-four-degree-of-freedom reference trajectory are converted using a modified backstepping approach that complements the inner-loop control law in a six-degree-of-freedom simulation. The inner-loop control law is capable of reacting and compensating for off-nominal conditions by employing nonlinear reconfigurable control allocation, dynamic inversion, and model-following/anti-windup prefilters. The results show that the inner loop control can adequately track the desired optimal guidance commands; thus, confirming that applicability of this control architecture for future development involving on-line, optimal trajectory generation and high-fidelity guidance and control for reentry vehicles.

Fault Tolerant Optimal Trajectory Generation for Reusable Launch Vehicles

Author : Patrick J. Shaffer
Publisher :
ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Fault Tolerant Optimal Trajectory Generation for Reusable Launch Vehicles by : Patrick J. Shaffer

Download or read book Fault Tolerant Optimal Trajectory Generation for Reusable Launch Vehicles written by Patrick J. Shaffer and published by . This book was released on 2006 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reconfigurable inner-loop control laws improve the fault tolerance of a vehicle to control effector failures; however, in order to preserve stability, the unfailed effectors may be deployed to off-nominal positions to compensate for undesirable perturbations caused by the failed effectors. The effectors acting under the influence of a reconfigurable control law can produce significant perturbations to the nominal forces produced by the wing and body and can also affect the range of flight conditions over which the vehicle can be controlled. Three degree-of-freedom (3 DOF) dynamical models used in trajectory optimization for aerospace vehicles typically include wing-body aerodynamic force effects but ignore the aerodynamic forces produced by the control surfaces. In this work, a method for including these trim effects as well as control induced trajectory constraints in a 3 DOF model is presented.

High-Fidelity Real-Time Trajectory Optimization for Reusable Launch Vehicles

Author : Kevin P. Bollino
Publisher :
ISBN 13 :
Total Pages : 445 pages
Book Rating : 4.:/5 (227 download)

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Book Synopsis High-Fidelity Real-Time Trajectory Optimization for Reusable Launch Vehicles by : Kevin P. Bollino

Download or read book High-Fidelity Real-Time Trajectory Optimization for Reusable Launch Vehicles written by Kevin P. Bollino and published by . This book was released on 2006 with total page 445 pages. Available in PDF, EPUB and Kindle. Book excerpt: Creating simplicity out of complexity, this research abandons the traditional guidance and control architecture for aerospace vehicles and embraces a revolutionary concept based on the principles of nonlinear optimal control theory. Motivated by the emerging needs of the next generation of reusable space vehicles, an autonomous integrated guidance and control system is developed that provides a safe approach to the highly constrained and nonlinear reentry problem. A pseudospectral-based optimal guidance scheme is used to generate high-fidelity, vehicle-tailored solutions to reentry trajectory optimization and guidance problems. To provide an autonomous, onboard capability of satisfying final-approach requirements, a new method is developed that includes an automatic generation of landing constraints given any runway geometry. This unique and simple approach avoids significant complexities arising from previous ideas of trajectory segmentation, trimmed flight, and trajectory tracking schemes. When demonstrating the new ideas, it is shown that the proposed approach can easily compensate for large uncertainties and disturbances consisting of hurricane-force wind gusts. An investigation of these new principles for the complete, nonlinear six degree-of-freedom system dynamics indicates that while the results are quite promising, a substantial amount of new theoretical and computational problems remain open, particularly in the area of over-actuated dynamical systems.

Reusable Launch Vehicle

Author : National Research Council
Publisher : National Academies Press
ISBN 13 : 0309175860
Total Pages : 98 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Reusable Launch Vehicle by : National Research Council

Download or read book Reusable Launch Vehicle written by National Research Council and published by National Academies Press. This book was released on 1996-01-08 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: The key to opening the use of space to private enterprise and to broader public uses lies in reducing the cost of the transportation to space. More routine, affordable access to space will entail aircraft-like quick turnaround and reliable operations. Currently, the space Shuttle is the only reusable launch vehicle, and even parts of it are expendable while other parts require frequent and extensive refurbishment. NASA's highest priority new activity, the Reusable Launch Vehicle program, is directed toward developing technologies to enable a new generation of space launchers, perhaps but not necessarily with single stage to orbit capability. This book assesses whether the technology development, test and analysis programs in propulsion and materials-related technologies are properly constituted to provide the information required to support a December 1996 decision to build the X-33, a technology demonstrator vehicle; and suggest, as appropriate, necessary changes in these programs to ensure that they will support vehicle feasibility goals.

Automated Trajectory Generation and Guidance for a New Launch Vehicle Flight Phases

Author : Kenneth R. Horneman
Publisher :
ISBN 13 :
Total Pages : 129 pages
Book Rating : 4.:/5 (872 download)

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Book Synopsis Automated Trajectory Generation and Guidance for a New Launch Vehicle Flight Phases by : Kenneth R. Horneman

Download or read book Automated Trajectory Generation and Guidance for a New Launch Vehicle Flight Phases written by Kenneth R. Horneman and published by . This book was released on 2010 with total page 129 pages. Available in PDF, EPUB and Kindle. Book excerpt: Much effort has been put into developing technologies for next generation re-usable launch vehicles. Fully re-usable launch vehicles include a booster stage that is designed to land, usually near the launch site, after it has released the upper-stage, which continues to orbit. The fuel reserve needed to turn the booster stage around will usually be minimal For this reason, once the booster stage has completed a rocket-back maneuver, it will typically be at a high altitude (exo-atmospheric) but with low kinetic energy and a steep flight path angle on re-entry. Traditional re-entry guidance is designed for vehicles with a high velocity, and shallow flight path angle, and thus these traditional approaches are not appropriate for a low energy re-entry (LOER). The current research presents a set of guidance algorithms that will successfully guide a vehicle to landing starting from LOER condition. The guidance algorithms are designed to ensure the vehicle can achieve near optimal range performance when required and also to execute a sharp pull-up maneuver that balances the load factor constraint against the need to pull-up quickly before the dynamic pressure constraint is exceeded. The guidance approach has been tested for a wide variety of vehicles and mission scenarios, including more traditional initial conditions that would occur at the end of a High Energy Re-entry (HIER) from orbit. Thus, the guidance approach we have developed can be used as a more robust version of Terminal Area Energy Management (TAEM) guidance, as well as for LOER and has been tested for a wide range of vehicles, including the Space Shuttle and vehicles with a wide variety of L/D capability. Significant development has also gone into the engineering considerations needed to implement the guidance algorithms on a real vehicle. Program execution time, application of vehicle constraints, trajectory repeatability and other factors are all addressed in order to meet this need.

A Reconfigurable Guidance Approach for Reusable Launch Vehicles

Author :
Publisher :
ISBN 13 :
Total Pages : 12 pages
Book Rating : 4.:/5 (644 download)

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Book Synopsis A Reconfigurable Guidance Approach for Reusable Launch Vehicles by :

Download or read book A Reconfigurable Guidance Approach for Reusable Launch Vehicles written by and published by . This book was released on 2001 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: A guidance system with reconfiguration capabilities has been developed for reusable launch vehicles (RLVs). The focus of the development is on reconfiguration after a catastrophic effector failure during final approach - a failure that would otherwise cause loss of the vehicle. We assume here that the vehicle employs a reconfigurable inner-loop control system that recovers some maneuvering capabilities and maintains attitude stability. However, for RLVs, it is often the case that nominal performance cannot be fully recovered, and the outer-loop guidance system must account for the degraded response characteristics. Two approaches are presented. The first approach augments the existing production guidance system with adaptation capabilities. A case study shows that stability is maintained following a primary pitch effector failure. However, it is shown that the trajectory commands to the guidance loops must also be re-targeted in order to achieve a safe landing. The second approach employs an on-line optimal trajectory re-targeting algorithm. A database of neighboring optimal trajectories is encoded in an efficient manner and interrogated on line at regular intervals. Given the current states and certain vehicle parameters, this procedure generates optimal guidance commands and integrates the optimal trajectory to the next update point. A proof-of-concept study of this approach was performed. Following a primary speed control failure, the study shows that this approach achieves acceptable landing conditions.

Adaptive Guidance Systems for Hypersonic Reusable Launch Vehicles

Author :
Publisher :
ISBN 13 :
Total Pages : 13 pages
Book Rating : 4.:/5 (644 download)

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Book Synopsis Adaptive Guidance Systems for Hypersonic Reusable Launch Vehicles by :

Download or read book Adaptive Guidance Systems for Hypersonic Reusable Launch Vehicles written by and published by . This book was released on 2001 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents an adaptive guidance system approach applied to hypersonic Reusable Launch Vehicles (RLVs). After an effector failure, it is assumed that the inner-closed-loop system utilizes a reconfigurable control algorithm to recover nominal maneuvering capabilities to the extent possible. However, nominal performance will typically not be fully recovered for RLVs, and the outer-loop guidance system must account for the degraded vehicle response. Two main approaches for the adaptive guidance system are presented. The first approach augments the existing production guidance system by adding adaptation capabilities. A case study shows that stability is maintained following a primary pitch effector failure. This is achieved by adapting gains in the guidance feedback loops. However, it is shown that the trajectory commands to the guidance loops must also be re-targeted in order to achieve a safe landing. The second approach employs an on-line optimal trajectory re-targeting algorithm. Here, the calculus of variations is used to generate a database of admissible neighboring extremals. This database is then encoded in an efficient manner to generate mappings between the current states and vehicle capabilities and the costates defining the admissible optimal trajectories. These mappings are interrogated on-line at regular intervals to obtain the optimal guidance commands. A proof-of-concept case study of this approach shows that the final landing conditions are achieved following a primary speed control effector failure.

Sub-optimal Analytic Guidance for Reusable Launch Vehicles

Author : Katie Amanda Grantham
Publisher :
ISBN 13 :
Total Pages : 120 pages
Book Rating : 4.:/5 (548 download)

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Book Synopsis Sub-optimal Analytic Guidance for Reusable Launch Vehicles by : Katie Amanda Grantham

Download or read book Sub-optimal Analytic Guidance for Reusable Launch Vehicles written by Katie Amanda Grantham and published by . This book was released on 2003 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: "This thesis presents a guidance scheme for the Terminal Area Energy Management (TAEM) and Approach and Landing phases of flight for the next generation of reusable launch vehicles (RLVs). The guidance scheme presented is developed in two parts, the kappa guidance section and the touchdown trajectory section."--Abstract, p. iii.

Closed-loop Endo-atmospheric Ascent Guidance for Reusable Launch Vehicle

Author : Hongsheng Sun
Publisher :
ISBN 13 :
Total Pages : 178 pages
Book Rating : 4.:/5 (71 download)

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Book Synopsis Closed-loop Endo-atmospheric Ascent Guidance for Reusable Launch Vehicle by : Hongsheng Sun

Download or read book Closed-loop Endo-atmospheric Ascent Guidance for Reusable Launch Vehicle written by Hongsheng Sun and published by . This book was released on 2005 with total page 178 pages. Available in PDF, EPUB and Kindle. Book excerpt: This dissertation focuses on the development of a closed-loop endo-atmospheric ascent guidance algorithm for the 2nd generation reusable launch vehicle. Special attention has been given to the issues that impact on viability, complexity and reliability in on-board implementation. The algorithm is called once every guidance update cycle to recalculate the optimal solution based on the current flight condition, taking into account atmospheric effects and path constraints. This is different from traditional ascent guidance algorithms which operate in a simple open-loop mode inside atmosphere, and later switch to a closed-loop vacuum ascent guidance scheme. The classical finite difference method is shown to be well suited for fast solution of the constrained optimal three-dimensional ascent problem. The initial guesses for the solutions are generated using an analytical vacuum optimal ascent guidance algorithm. Homotopy method is employed to gradually introduce the aerodynamic forces to generate the optimal solution from the optimal vacuum solution. The vehicle chosen for this study is the Lockheed Martin X-33 lifting-body reusable launch vehicle. To verify the algorithm presented in this dissertation, a series of open-loop and closed-loop tests are performed for three different missions. Wind effects are also studied in the closed-loop simulations. For comparison, the solutions for the same missions are also obtained by two independent optimization softwares. The results clearly establish the feasibility of closed-loop endo-atmospheric ascent guidance of rocket-powered launch vehicles. ATO cases are also tested to assess the adaptability of the algorithm to autonomously incorporate the abort modes.

Model Predictive Control for Terminal Area Energy Management and Approach and Landing for a Reusable Launch Vehicle

Author :
Publisher :
ISBN 13 :
Total Pages : 235 pages
Book Rating : 4.:/5 (742 download)

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Book Synopsis Model Predictive Control for Terminal Area Energy Management and Approach and Landing for a Reusable Launch Vehicle by :

Download or read book Model Predictive Control for Terminal Area Energy Management and Approach and Landing for a Reusable Launch Vehicle written by and published by . This book was released on 2002 with total page 235 pages. Available in PDF, EPUB and Kindle. Book excerpt: The space industry plans to develop new reusable launch vehicles. The new vehicles will need advanced, new guidance and control systems. Since 1996 Draper Laboratory has been developing the next generation guidance and control for reusable launch vehicles in which guidance and control is integrated into one correlated system. Draper's research of integrated guidance and control originated with a single loop multivariable control scheme using time-invariant linear quadratic regulator theory. The research has since evolved into the use of model predictive control theory. The main focus of this thesis is the theory and design of model predictive control for entry of aerospace vehicles. The goal is to develop design criteria and guidelines explaining how to select the model predictive control parameters: prediction horizon, simulation rates, and weighting matrices. A secondary goal is to tightly couple an onboard trajectory generation algorithm with the model predictive controller to improve tracking performance and robustness. Favorable tracking is achieved through two model predictive control architectures, which are discussed. The first architecture has an inner loop stability augmentation system with model predictive control used as an outer loop. The second architecture replaces the inner and outer loops with a single model predictive controller. The two architectures demonstrate the flexibility of model predictive control to adapt to new vehicles; the model predictive control may be used to augment an existing inner loop or may be used as a stand-alone controller. The design focuses primarily on the architecture without a stability augmentation system.

Onboard Trajectory Generation for the Unpowered Landing of Autonomous Reusable Launch Vehicles

Author : André René Girerd
Publisher :
ISBN 13 :
Total Pages : 168 pages
Book Rating : 4.:/5 (498 download)

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Book Synopsis Onboard Trajectory Generation for the Unpowered Landing of Autonomous Reusable Launch Vehicles by : André René Girerd

Download or read book Onboard Trajectory Generation for the Unpowered Landing of Autonomous Reusable Launch Vehicles written by André René Girerd and published by . This book was released on 2001 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Optimal Trajectory Reconfiguration and Retargeting for a Reusable Launch Vehicle

Author :
Publisher :
ISBN 13 :
Total Pages : 15 pages
Book Rating : 4.:/5 (742 download)

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Book Synopsis Optimal Trajectory Reconfiguration and Retargeting for a Reusable Launch Vehicle by :

Download or read book Optimal Trajectory Reconfiguration and Retargeting for a Reusable Launch Vehicle written by and published by . This book was released on 2005 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: Autonomous reusable launch vehicles (RLV) are being pursued as low-cost alternatives to expendable launch vehicles and the Shuttle. The employment of autonomous reusable launch vehicles requires additional guidance and control robustness to fulfill the role of an adaptive human pilot, in the event of failures or unanticipated conditions. The guidance and control of these vehicles mandate new guidance strategies that are able to identify and adapt to vehicle failures during the flight and still return to earth safely. This work utilizes an online trim algorithm that provides the outer loop with the feasible range of Mach number and angle of attack, for which the vehicle can be rotationally trimmed. The algorithm allows one to include 6-degree-of-freedom (DOF) trim effects and constraints in a reduced order dynamical model which is used in the solution of an optimal control problem. A direct pseudospectral method is used to solve a two-point-boundary-value problem which determines the optimal entry trajectory subject to appropriate constraints such as normal load, dynamic pressure limits, heat load limits, and state dependent constraints.

Flight Mechanics and Control for an Unpowered Reusable Launch Vehicle

Author : Steven Edward McKee
Publisher :
ISBN 13 :
Total Pages : 161 pages
Book Rating : 4.:/5 (748 download)

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Book Synopsis Flight Mechanics and Control for an Unpowered Reusable Launch Vehicle by : Steven Edward McKee

Download or read book Flight Mechanics and Control for an Unpowered Reusable Launch Vehicle written by Steven Edward McKee and published by . This book was released on 2011 with total page 161 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new strategy has been developed to aid in allowing a reusable launch vehicle to complete the Trajectory Area Energy Management (TAEM) phase of reentry. Using the new trajectory planning and tracking strategy, the reusable launch vehicle will complete TAEM with a higher degree of accuracy than what has been accomplished in the past. The reusable launch vehicle will also be better prepared to adapt to unpredictable conditions, which in the past were a hindrance to an accurate and safe reentry. The new strategy is composed of two distinct components. The first component provides the vehicle with a new way to track the Heading Alignment Cone (HAC) using dynamic gain values. The new dynamic gains values are found through a combination of linearization, state-space representation, and pole-placement. The second component provides the vehicle with an extremely accurate groundtrack predictor. The groundtrack predictor allows the vehicle to accurately determine an ideal trajectory to the next reentry phase, Approach and Landing. The groundtrack predictor utilizes a combination of HAC size and location modifications in order to provide the vehicle with an accurate prediction.

Optimal Trajectory Reconfiguration and Retargeting for the X-33 Reusable Launch Vehicle

Author : Patrick J. Shaffer
Publisher :
ISBN 13 : 9781423519539
Total Pages : 151 pages
Book Rating : 4.5/5 (195 download)

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Book Synopsis Optimal Trajectory Reconfiguration and Retargeting for the X-33 Reusable Launch Vehicle by : Patrick J. Shaffer

Download or read book Optimal Trajectory Reconfiguration and Retargeting for the X-33 Reusable Launch Vehicle written by Patrick J. Shaffer and published by . This book was released on 2004-09-01 with total page 151 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis considers the problem of generating optimal entry trajectories for a reusable launch vehicle following a control surface failure. The thesis builds upon the work of Dr. David Doman, Dr. Michael Oppenheimer and Dr. Michael Bolender of the Air Vehicles Directorate, Air Force Research Lab Dayton Ohio. The primary focus of this work is to demonstrate the feasibility of inner loop reconfiguration and outer loop trajectory retargeting and replanning for the X-33 reusable launch vehicle (RLV) following the imposition of a control surface failure. The trajectory generation model employs path constraints generated by an AFRL trim deficiency algorithm coupled with an inner loop control allocator and aerodynamic database that captures the full 6-DOF vehicle aerodynamic effects while utilizing an outer loop 3-DOF model. The resulting optimal trajectory does not violate the trim deficiency constraints and provides additional margins for trajectories flown during failure conditions. The footprints generated by the thesis show that contemporary footprint analysis for vehicles experiencing control surface failures are overly optimistic when compared to those footprints that consider vehicle aerodynamic stability and realistic landable attitudes at the threshold of the landing runway. The results of the thesis also show the performance reductions resulting from decoupling the inner and outer loop and that trajectories can be generated to the landing runway without using a region of terminal area energy management.

Neural Dynamic Trajectory Design for Reentry Vehicles

Author : Ajay Verma
Publisher :
ISBN 13 :
Total Pages : 14 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Neural Dynamic Trajectory Design for Reentry Vehicles by : Ajay Verma

Download or read book Neural Dynamic Trajectory Design for Reentry Vehicles written by Ajay Verma and published by . This book was released on 2007 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: The next generation of reentry vehicles is envisioned to have onboard autonomous capability of real-time trajectory planning to provide capability of responsive launch and delivering payload anywhere with precise flight termination. This capability is also desired to overcome, if possible, in-flight vehicle damage or control effector failure resulting in degraded vehicle performance. An aerial vehicle is modeled as a nonlinear multi-input-multi-output (MIMO) system. An ideal optimal trajectory control design system generates a series of control commands to achieve a desired trajectory under various disturbances and vehicle model uncertainties including aerodynamic perturbations caused by geometric damage to the vehicle. Conventional approaches suffer from the nonlinearity of the MIMO system, and the high-dimensionality of the system state space. In this paper, we apply a Neural Dynamic Optimization (NDO) based approach to overcome these difficulties. The core of an NDO model is a multilayer perceptron (MLP) neural network, which generates the control parameters online. The advantage of the NDO system is that it is very fast and gives the trajectory almost instantaneously. The bulk of the time consuming computation is required only during off-line training. The inputs of the MLP are the time-variant states of the MIMO systems. The outputs of the MLP are the near optimal control parameters.

Integrated Design for Space Transportation System

Author : B.N. Suresh
Publisher : Springer
ISBN 13 : 8132225325
Total Pages : 792 pages
Book Rating : 4.1/5 (322 download)

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Book Synopsis Integrated Design for Space Transportation System by : B.N. Suresh

Download or read book Integrated Design for Space Transportation System written by B.N. Suresh and published by Springer. This book was released on 2015-11-20 with total page 792 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book addresses the overall integrated design aspects of a space transportation system involving several disciplines like propulsion, vehicle structures, aerodynamics, flight mechanics, navigation, guidance and control systems, stage auxiliary systems, thermal systems etc. and discusses the system approach for design, trade off analysis, system life cycle considerations, important aspects in mission management, the risk assessment, etc. There are several books authored to describe the design aspects of various areas, viz., propulsion, aerodynamics, structures, control, etc., but there is no book which presents space transportation system (STS) design in an integrated manner. This book attempts to fill this gap by addressing systems approach for STS design, highlighting the integrated design aspects, interactions between various subsystems and interdependencies. The main focus is towards the complex integrated design to arrive at an optimum, robust and cost effective space transportation system. The orbital mechanics of satellites including different coordinate frames, orbital perturbations and orbital transfers are explained. For launching the satellites to meet specific mission requirements, viz., payload/orbit, design considerations, giving step by step procedure are briefed. The selection methodology for launch vehicle configuration, its optimum staging and the factors which influence the vehicle performance are summarized. The influence of external, internal and dynamic operating environments experienced by the vehicle subsystems and the remedial measures needed are highlighted. The mission design strategies and their influence on the vehicle design process are elaborated. The various critical aspects of STS subsystems like flight mechanics, propulsion, structures and materials, thermal systems, stage auxiliary systems, navigation, guidance and control and the interdependencies and interactions between them are covered. The design guidelines, complexity of the flight environment and the reentry dynamics for the reentry missions are included. The book is not targeted as a design tool for any particular discipline or subsystem. Some of the design related equations or expressions are not attempted to derive from the first principle as this is beyond the scope of this book. However, the important analytical expressions, graphs and sketches which are essential to provide in-depth understanding for the design process as well as to understand the interactions between different subsystems are appropriately included.