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Benchmark Characterization For Reusable Launch Vehicle Onboard Trajectory Generation Using A Legendre Psuedospectral Sic Optimization Method
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Book Synopsis Benchmark Characterization for Reusable Launch Vehicle Onboard Trajectory Generation Using a Legendre Psuedospectral [sic] Optimization Method by : Theodore Robert Dyckman
Download or read book Benchmark Characterization for Reusable Launch Vehicle Onboard Trajectory Generation Using a Legendre Psuedospectral [sic] Optimization Method written by Theodore Robert Dyckman and published by . This book was released on 2002 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Book Synopsis A Legendre Pseudospectral Method for Rapid Optimization of Launch Vehicle Trajectories by : Jeremy Ryan Rea
Download or read book A Legendre Pseudospectral Method for Rapid Optimization of Launch Vehicle Trajectories written by Jeremy Ryan Rea and published by . This book was released on 2001 with total page 261 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Optimal Trajectory Designs and Systems Engineering Analyses of Reusable Launch Vehicles by : Hung-i Bruce Tsai
Download or read book Optimal Trajectory Designs and Systems Engineering Analyses of Reusable Launch Vehicles written by Hung-i Bruce Tsai and published by . This book was released on 2003 with total page 640 pages. Available in PDF, EPUB and Kindle. Book excerpt: Realizing a reusable launch vehicle (RLV) that is low cost with highly effective launch capability has become the "Holy Grail" within the aerospace community world-wide. Clear understanding of the vehicle's operational limitations and flight characteristics in all phases of the flight are preponderant components in developing such a launch system. This dissertation focuses on characterizing and designing the RLV optimal trajectories in order to aid in strategic decision making during mission planning in four areas: 1) nominal ascent phase, 2) abort scenarios and trajectories during ascent phase including abort-to-orbit (ATO), transoceanic-abort-landing (TAL) and return-to-launch-site (RTLS), 3) entry phase (including footprint), and 4) systems engineering aspects of such flight trajectory design. The vehicle chosen for this study is the Lockheed Martin X-33 lifting-body design that lifts off vertically with two linear aerospike rocket engines and lands horizontally. An in-depth investigation of the optimal endo-atmospheric ascent guidance parameters such as earliest abort time, engine throttle setting, number of flight phases, flight characteristics and structural design limitations will be performed and analyzed to establish a set of benchmarks for making better trade-off decisions. Parametric analysis of the entry guidance will also be investigated to allow the trajectory designer to pinpoint relevant parameters and to generate optimal constrained trajectories. Optimal ascent and entry trajectories will be generated using a direct transcription method to cast the optimal control problem as a nonlinear programming problem. The solution to the sparse nonlinear programming problem is then solved using sequential quadratic programming. Finally, guidance system hierarchy studies such as work breakdown structure, functional analysis, fault-tree analysis, and configuration management will be developed to ensure that the guidance system meets the definition of vehicle design requirements and constraints.
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.
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 New Methodologies for Onboard Generation of Terminal Area Energy Management Trajectories for Autonomous Reusable Launch Vehicles by : Andrew Clay Grubler
Download or read book New Methodologies for Onboard Generation of Terminal Area Energy Management Trajectories for Autonomous Reusable Launch Vehicles written by Andrew Clay Grubler and published by . This book was released on 2001 with total page 145 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Book Synopsis Longitudinal Control and Footprint Analysis for a Reusable Military Launch Vehicle by : Anhtuan D. Ngo
Download or read book Longitudinal Control and Footprint Analysis for a Reusable Military Launch Vehicle written by Anhtuan D. Ngo and published by . This book was released on 2003 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this paper, we will examine a configuration for a reusable military launch vehicle (RMLS) concept. This configuration allows for the vehicle to land in an inverted attitude. Such inverted landing improves the turnaround time of the vehicle by reducing the maintenance requirements of the vehicle's thermal protection system. An analysis is performed to examine the impacts by the configuration on stability, control, and footprint for an RMLS configuration.
Book Synopsis Optimal Three Dimensional Launch Vehicle Trajectories with Attitude and Attitude Rate Constraints by : Fred Teren
Download or read book Optimal Three Dimensional Launch Vehicle Trajectories with Attitude and Attitude Rate Constraints written by Fred Teren and published by . This book was released on 1969 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Improvements to a Hybrid Algorithm for Rapid Generation of 3-D Optimal Launch Vehicle Ascent Trajectories by : Peter F. Gath
Download or read book Improvements to a Hybrid Algorithm for Rapid Generation of 3-D Optimal Launch Vehicle Ascent Trajectories written by Peter F. Gath and published by diplom.de. This book was released on 1999-12-15 with total page 103 pages. Available in PDF, EPUB and Kindle. Book excerpt: Inhaltsangabe:Abstract: This thesis presents improvements to FLOAT, a hybrid analytical/numerical algorithm for rapid generation of three dimensional, optimal launch vehicle ascent trajectories. Improvements have been made to the terminal constraints, which are now available in a more general form to allow for an optimal attachment point to the target orbit.The existing algorithm also has been extended with logic that allows for vehicles with low thrust to weight ratios in the upper stage and successful convergence of problems with path constraints for normal force and angle of attack Another major extension made to the code is the introduction of coasting arcs. Coasting arcs are implemented using a completely analytical solution for the prediction of states and costates as well as for the required sensitivity matrix. This allows for a very fast and accurate calculation even with long coasting arcs. Finally, an approach for the optimization of start and end time of coast arcs is presented.This approach was implemented and the results of a test case compare very well with results generated with OTIS for the same case. At the end, suggestions for future development are made. Inhaltsverzeichnis:Table of Contents: Summaryi Acknowledgementsii Contentsiii Nomenclaturev Figuresviii Introduction1 1.Problem description3 1.1Describing the final orbit3 1.2Coordinate frame5 1.3Dynamic system6 1.4Initial conditions7 1.5Path constraints7 1.6Performance index7 1.7Terminal constraints8 1.8Solution method8 1.9Non-dimensionalization of the variables9 2.Solving the two-point boundary value problem10 2.1Vacuumsolution10 2.1.1Simplified model equations10 2.1.2Optimal control for vacuum solution11 2.1.3Thrust integrals and closed form solution for ascent in vacuum12 2.2Atmospheric solution13 2.2.1Dynamic system and collocation variables13 2.2.2Optimality condition to solve for 1b14 2.2.3Differential equations for the costate variables16 2.3Terminal constraints16 2.3.1Attaching at perigee17 2.3.2Free attachment point17 2.4Transversality conditions18 2.4.1Final costates for attaching at perigee18 2.4.2Final costates for free attachment point19 2.4.3Equatorial orbits22 2.5Adjusting final time22 2.6Computation procedure23 2.7Numerical results24 3.Low thrust upper stages27 3.1Typical low thrust case27 3.2Problems with low thrust upper stages28 3.3Upper stage modification30 3.4Advantage of free attachment point for low thrust [...]
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722150853 Total Pages :66 pages Book Rating :4.1/5 (58 download)
Book Synopsis A Trajectory Generation and System Characterization Model for Cislunar Low-Thrust Spacecraft. Volume 2 by : National Aeronautics and Space Administration (NASA)
Download or read book A Trajectory Generation and System Characterization Model for Cislunar Low-Thrust Spacecraft. Volume 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: The documentation of the Trajectory Generation and System Characterization Model for the Cislunar Low-Thrust Spacecraft is presented in Technical and User's Manuals. The system characteristics and trajectories of low thrust nuclear electric propulsion spacecraft can be generated through the use of multiple system technology models coupled with a high fidelity trajectory generation routine. The Earth to Moon trajectories utilize near Earth orbital plane alignment, midcourse control dependent upon the spacecraft's Jacobian constant, and capture to target orbit utilizing velocity matching algorithms. The trajectory generation is performed in a perturbed two-body equinoctial formulation and the restricted three-body formulation. A single control is determined by the user for the interactive midcourse portion of the trajectory. The full spacecraft system characteristics and trajectory are provided as output. Korsmeyer, David J. and Pinon, Elfego, III and Oconnor, Brendan M. and Bilby, Curt R. Unspecified Center...
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.
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 1996-02-08 with total page 99 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.
Book Synopsis Launch Vehicle Error Sensitivity Study by : Richard C. Rosenbaum
Download or read book Launch Vehicle Error Sensitivity Study written by Richard C. Rosenbaum and published by . This book was released on 1970 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis On-line Robust Approach and Landing Trajectory Generation for Reusable Launch Vehicles by : Zhesheng Jiang
Download or read book On-line Robust Approach and Landing Trajectory Generation for Reusable Launch Vehicles written by Zhesheng Jiang and published by . This book was released on 2009 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
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