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Closed Loop Nominal And Abort Atmospheric Ascent Guidance For Rocket Powered Launch Vehicles
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Book Synopsis Closed-loop Nominal and Abort Atmospheric Ascent Guidance for Rocket-powered Launch Vehicles by : Greg A. Dukeman
Download or read book Closed-loop Nominal and Abort Atmospheric Ascent Guidance for Rocket-powered Launch Vehicles written by Greg A. Dukeman and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: An advanced ascent guidance algorithm for rocket-powered launch vehicles is developed. The ascent guidance function is responsible for commanding attitude, throttle and setting during the powered ascent phase of flight so that the vehicle attains target cutoff conditions in a near-optimal manner while satisfying path constraints such as maximum allowed bending moment and maximum allowed axial acceleration. This algorithm cyclically solves the calculus-of-variations two-point boundary-value problem starting at vertical rise completion through orbit insertion. This is different from traditional ascent guidance algorithms which operate in an open-loop mode until the high dynamic pressure portion of the trajectory is over, at which time there is a switch to a closed loop guidance mode that operates under the assumption of negligible aerodynamic forces. The main contribution of this research is an algorithm of the predictor-corrector type wherein the state/costate system is propagated with known (navigated) initial state and guessed initial costate to predict the state/costate at engine cutoff. The initial costate guess is corrected, using a multi-dimensional Newton?s method, based on errors in the terminal state constraints and the transversality conditions. Path constraints are enforced within the propagation process. A modified multiple shooting method is shown to be a very effective numerical technique for this application. Results for a single stage to orbit launch vehicle are given. In addition, the formulation for the free final time multi-arc trajectory optimization problem is given. Results for a two-stage launch vehicle burn-coast-burn ascent to orbit in a closed-loop guidance mode are shown. An abort to landing site formulation of the algorithm and numerical results are presented. A technique for numerically treating the transversality conditions is discussed that eliminates part of the analytical and coding burden associated with optimal control theory.
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.
Book Synopsis A Fixed-point Framework for Launch Vehicle Ascent Guidance by : Lijun Zhang
Download or read book A Fixed-point Framework for Launch Vehicle Ascent Guidance written by Lijun Zhang and published by . This book was released on 2006 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt: Recent, interests in responsive launch have highlighted the need for rapid and fully automated ascent guidance planning and guidance parameter generation for launch vehicles. This dissertation aims at developing methodology and algorithms for on-demand generation of optimal launch vehicle ascent trajectories from lift-off to achieving targeting conditions outside the atmosphere. The entire ascent trajectory from lift-off to final target point is divided into two parts: atmospheric ascent portion and vacuum ascent portion. The two portions are integrated via a fixed-point iteration based on the continuity condition at the switch point between atmospheric ascent portion and vacuum ascent portion. The previous research works on closed-loop endo-atmospheric ascent guidance shows that the classical finite difference method is well suited for fast solution of the constrained optimal three-dimensional ascent problem. The exploitation of certain unique features in the integration procedure between the atmospheric portion and vacuum portion and the finite difference method, allows us to cast the atmospheric ascent problem into a nested fixed-point iteration problem. Therefore a novel Fixed-Point Iteration algorithm is presented for solving the endo-atmospheric ascent guidance problem. Several approaches are also provided for facilitating the convergence of the fixed-point iteration. The exo-atmospheric ascent portion allows an optimal coast in between the two vacuum powered stages. The optimal coast enables more efficient usage of the propellant. The Analytical Multiple-Shooting algorithm is developed to find the optimal trajectory for this portion. A generic launch vehicle model is adopted in the numerical simulation. A series of open-loop and closed-loop simulations are performed. The results verify the effectiveness, robustness and reliability of the Fixed-Point Iteration (FPI) algorithm and Analytical Multiple-Shooting (AMS) algorithm developed in this research. In comparison to Finite Difference (FD) algorithm, the Fixed-Point Iteration algorithm is more adaptive to the "cold start" case for endo-atmospheric ascent guidance. The simulations also validate the feasibility of the methodology presented in this research in rapid panning and guidance for ascent through atmosphere.
Book Synopsis Assessment of Adaptive Guidance for Responsive Launch Vehicles and Spacecraft by : Ping Lu
Download or read book Assessment of Adaptive Guidance for Responsive Launch Vehicles and Spacecraft written by Ping Lu and published by . This book was released on 2009 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: "This project sets out to identify and address the need for adaptive ascent guidance techniques necessary for responsive launch. This report provides comprehensive details to two recent advanced ascent guidance algorithms, tailored to endo-atmospheric and exo-atmospheric optimal ascent with possibly multiple stages, respectively. These algorithms generate optimal ascent guidance commands based on the current state of the vehicle, the currently selected targeting condition, and available vehicle/environment modeling and wind information. The algorithms depend on no vehicle-specific characteristics therefore are applicable to different types of launch vehicles without the need for significantly modifying the software. Verification, validation and extensive testing of the algorithms are performed with many mission scenarios and a number of different launch vehicle configurations, including winged reusable and conventional expandable, single-stage and multiple-stage, launch vehicles. This work demonstrates that promising techniques and algorithms have reached a level where launch ascent planning can benefit from automation based on these advances to significantly reduce ascent guidance planning time and potential realization of fully closed-loop optimal ascent guidance from liftoff to orbital insertion is possible."--Report documentation page.
Book Synopsis Analysis of the Staging Maneuver and Booster Glideback Guidance for a Two-stage, Winged, Fully Reusable Launch Vehicle by : J. Christopher Naftel
Download or read book Analysis of the Staging Maneuver and Booster Glideback Guidance for a Two-stage, Winged, Fully Reusable Launch Vehicle written by J. Christopher Naftel and published by . This book was released on 1993 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Piloted Simulation Study of Manual Guidance of the Upper Stages of a Large Launch Vehicle by : Richard L. Kurkowski
Download or read book A Piloted Simulation Study of Manual Guidance of the Upper Stages of a Large Launch Vehicle written by Richard L. Kurkowski and published by . This book was released on 1967 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Launch Options for the Future written by and published by . This book was released on 1988 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Rendezvous Capability of Horizontal-take-off Launch Vehicle with Air-breathing Propulsion by : Charlie M. Jackson
Download or read book Rendezvous Capability of Horizontal-take-off Launch Vehicle with Air-breathing Propulsion written by Charlie M. Jackson and published by . This book was released on 1964 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Journal of Guidance, Control, and Dynamics by :
Download or read book Journal of Guidance, Control, and Dynamics written by and published by . This book was released on 2008 with total page 696 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Open-Loop Pitch Table Optimization for the Maximum Dynamic Pressure Orion Abort Flight Test by : Ryan A. Stilwater
Download or read book Open-Loop Pitch Table Optimization for the Maximum Dynamic Pressure Orion Abort Flight Test written by Ryan A. Stilwater and published by BiblioGov. This book was released on 2013-06 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: NASA has scheduled the retirement of the space shuttle orbiter fleet at the end of 2010. The Constellation program was created to develop the next generation of human spaceflight vehicles and launch vehicles, known as Orion and Ares respectively. The Orion vehicle is a return to the capsule configuration that was used in the Mercury, Gemini, and Apollo programs. This configuration allows for the inclusion of an abort system that safely removes the capsule from the booster in the event of a failure on launch. The Flight Test Office at NASA's Dryden Flight Research Center has been tasked with the flight testing of the abort system to ensure proper functionality and safety. The abort system will be tested in various scenarios to approximate the conditions encountered during an actual Orion launch. Every abort will have a closed-loop controller with an open-loop backup that will direct the vehicle during the abort. In order to provide the best fit for the desired total angle of attack profile with the open-loop pitch table, the table is tuned using simulated abort trajectories. A pitch table optimization program was created to tune the trajectories in an automated fashion. The program development was divided into three phases. Phase 1 used only the simulated nominal run to tune the open-loop pitch table. Phase 2 used the simulated nominal and three simulated off nominal runs to tune the open-loop pitch table. Phase 3 used the simulated nominal and sixteen simulated off nominal runs to tune the open-loop pitch table. The optimization program allowed for a quicker and more accurate fit to the desired profile as well as allowing for expanded resolution of the pitch table.
Book Synopsis Optimal Guidance Law Development for an Advanced Launch System by : National Aeronautics and Space Adm Nasa
Download or read book Optimal Guidance Law Development for an Advanced Launch System written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-08 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this research effort was to develop a real-time guidance approach for launch vehicles ascent to orbit injection. Various analytical approaches combined with a variety of model order and model complexity reduction have been investigated. Singular perturbation methods were first attempted and found to be unsatisfactory. The second approach based on regular perturbation analysis was subsequently investigated. It also fails because the aerodynamic effects (ignored in the zero order solution) are too large to be treated as perturbations. Therefore, the study demonstrates that perturbation methods alone (both regular and singular perturbations) are inadequate for use in developing a guidance algorithm for the atmospheric flight phase of a launch vehicle. During a second phase of the research effort, a hybrid analytic/numerical approach was developed and evaluated. The approach combines the numerical methods of collocation and the analytical method of regular perturbations. The concept of choosing intelligent interpolating functions is also introduced. Regular perturbation analysis allows the use of a crude representation for the collocation solution, and intelligent interpolating functions further reduce the number of elements without sacrificing the approximation accuracy. As a result, the combined method forms a powerful tool for solving real-time optimal control problems. Details of the approach are illustrated in a fourth order nonlinear example. The hybrid approach is then applied to the launch vehicle problem. The collocation solution is derived from a bilinear tangent steering law, and results in a guidance solution for the entire flight regime that includes both atmospheric and exoatmospheric flight phases. Calise, Anthony J. and Leung, Martin S. K. Unspecified Center ADVANCED LAUNCH SYSTEM (STS); ALGORITHMS; ASCENT TRAJECTORIES; INJECTION GUIDANCE; LAUNCH VEHICLES; OPTIMAL CONTROL; PERTURBATION THEORY; PROBLEM SOLVING; REAL TIME OPERATION; SPACEC...
Book Synopsis Non-Rocket Space Launch and Flight by : Alexander Bolonkin
Download or read book Non-Rocket Space Launch and Flight written by Alexander Bolonkin and published by Elsevier. This book was released on 2010-07-07 with total page 488 pages. Available in PDF, EPUB and Kindle. Book excerpt: In recent years scientists have investigated a series of new methods for non-rocket space launch, which promise to revolutionize space launches and flight. Particularly in the current political climate new, cheaper, and more ‘fuel efficient’ methods are being investigated. Such new methods include the gas tube method, cable accelerators, tether launch systems, space elevators, solar and magnetic sails, circle launcher space keepers and more. The author of Non-Rocket Space Launch and Flight brings a vast amount of experience to the topic, having worked as a engineer, designer, project director and researcher at key institutes including NASA and the US Air Force. Explores all the new non-rocket space launch methods, and compares them with each other and traditional rockets Investigates the unifying principles of the different systems and shows how to select the best design suited to the mission Author brings together technical and theoretical expertise from both industry and academia
Book Synopsis Dissertation Abstracts International by :
Download or read book Dissertation Abstracts International written by and published by . This book was released on 2005 with total page 794 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :Paul Zarchan Publisher :AIAA (American Institute of Aeronautics & Astronautics) ISBN 13 : Total Pages :650 pages Book Rating :4.3/5 (91 download)
Book Synopsis Tactical and Strategic Missile Guidance by : Paul Zarchan
Download or read book Tactical and Strategic Missile Guidance written by Paul Zarchan and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 1997 with total page 650 pages. Available in PDF, EPUB and Kindle. Book excerpt: For both experts and novices, presents the principles of both tactical and strategic missile guidance in a common language, notation, and perspective, with numerous examples to illustrate the concepts. This revised edition (1st ed., 1990) adds three new chapters on the fundamentals of endoatmospheric ballistic targets; a new chapter showing how covariance analysis can be used to analyze missile guidance systems; two new appendices; and included Macintosh and IBM compatible formatted disks containing the FORTRAN code listings presented in the text. Annotation copyright by Book News, Inc., Portland, OR
Book Synopsis Research and Technology of the Lyndon B. Johnson Space Center by :
Download or read book Research and Technology of the Lyndon B. Johnson Space Center written by and published by . This book was released on 1988 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Launch Vehicle Design Process: Characterization, Technical Integration, and Lessons Learned by : J. C. Blair
Download or read book Launch Vehicle Design Process: Characterization, Technical Integration, and Lessons Learned written by J. C. Blair and published by . This book was released on 2001 with total page 264 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Reusable Booster System by : National Research Council
Download or read book Reusable Booster System written by National Research Council and published by National Academies Press. This book was released on 2013-01-10 with total page 115 pages. Available in PDF, EPUB and Kindle. Book excerpt: On June 15, 2011, the Air Force Space Command established a new vision, mission, and set of goals to ensure continued U.S. dominance in space and cyberspace mission areas. Subsequently, and in coordination with the Air Force Research Laboratory, the Space and Missile Systems Center, and the 14th and 24th Air Forces, the Air Force Space Command identified four long-term science and technology (S&T) challenges critical to meeting these goals. One of these challenges is to provide full-spectrum launch capability at dramatically lower cost, and a reusable booster system (RBS) has been proposed as an approach to meet this challenge. The Air Force Space Command asked the Aeronautics and Space Engineering Board of the National Research Council to conduct an independent review and assessment of the RBS concept prior to considering a continuation of RBS-related activities within the Air Force Research Laboratory portfolio and before initiating a more extensive RBS development program. The committee for the Reusable Booster System: Review and Assessment was formed in response to that request and charged with reviewing and assessing the criteria and assumptions used in the current RBS plans, the cost model methodologies used to fame [frame?] the RBS business case, and the technical maturity and development plans of key elements critical to RBS implementation. The committee consisted of experts not connected with current RBS activities who have significant expertise in launch vehicle design and operation, research and technology development and implementation, space system operations, and cost analysis. The committee solicited and received input on the Air Force launch requirements, the baseline RBS concept, cost models and assessment, and technology readiness. The committee also received input from industry associated with RBS concept, industry independent of the RBS concept, and propulsion system providers which is summarized in Reusable Booster System: Review and Assessment.
