Model Predictive Control For Terminal Area Energy Management And Approach And Landing For A Reusable Launch Vehicle By Robert C Lepome Ii
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Model Predictive Control For Terminal Area Energy Management And Approach And Landing For A Reusable Launch Vehicle By Robert C Lepome Ii
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Author : Robert C. LePome II
language : en
Publisher:
Release Date : 2002
Model Predictive Control For Terminal Area Energy Management And Approach And Landing For A Reusable Launch Vehicle By Robert C Lepome Ii written by Robert C. LePome II and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with categories.
Model Predictive Control For Terminal Area Energy Management And Approach And Landing For A Reusable Launch Vehicle
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Author : Robert Charles LePome
language : en
Publisher:
Release Date : 2002
Model Predictive Control For Terminal Area Energy Management And Approach And Landing For A Reusable Launch Vehicle written by Robert Charles LePome and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with categories.
Model Predictive Control For Terminal Area Energy Management And Approach And Landing For A Reusable Launch Vehicle
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Author :
language : en
Publisher:
Release Date : 2002
Model Predictive Control For Terminal Area Energy Management And Approach And Landing For A Reusable Launch Vehicle written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with categories.
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.
New Methodologies For Onboard Generation Of Terminal Area Energy Management Trajectories For Autonomous Reusable Launch Vehicles
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Author : Andrew Clay Grubler
language : en
Publisher:
Release Date : 2001
New Methodologies For Onboard Generation Of Terminal Area Energy Management Trajectories For Autonomous Reusable Launch Vehicles written by Andrew Clay Grubler and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with categories.
Optimal Trajectory Reconfiguration And Retargeting For The X 33 Reusable Launch Vehicle
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Author : Patrick J. Shaffer
language : en
Publisher:
Release Date : 2004-09-01
Optimal Trajectory Reconfiguration And Retargeting For The X 33 Reusable Launch Vehicle written by Patrick J. Shaffer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2004-09-01 with categories.
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.
Sub Optimal Analytic Guidance For Reusable Launch Vehicles
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Author : Katie Amanda Grantham
language : en
Publisher:
Release Date : 2003
Sub Optimal Analytic Guidance For Reusable Launch Vehicles written by Katie Amanda Grantham and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003 with Guidance systems (Flight) categories.
"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.
Flight Mechanics And Control For An Unpowered Reusable Launch Vehicle
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Author : Steven Edward McKee
language : en
Publisher:
Release Date : 2011
Flight Mechanics And Control For An Unpowered Reusable Launch Vehicle written by Steven Edward McKee and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011 with Electronic dissertations categories.
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.
Model Predictive Control For Ascent Load Management Of A Reusable Launch Vehicle
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Author : Andrew Allen Martin
language : en
Publisher:
Release Date : 2002-06-01
Model Predictive Control For Ascent Load Management Of A Reusable Launch Vehicle written by Andrew Allen Martin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002-06-01 with categories.
During the boost phase of ascent, winds have a significant impact on a launch vehicle's angle of attack, and can induce large structural loads on the vehicle. Traditional methods for mitigating these loads involve measuring the winds prior to launch and designing trajectories to minimize the vehicle angle of attack (0). The current balloon-based method of collecting wind field information produces wind profiles with significant uncertainty due to the inherent time delays associated with balloon measurement procedures. Managing the mission risk caused by these uncertain wind measurements has always been important to control system designers. This thesis will describe a novel approach to managing structural loads through the combination of a Light Detection and Ranging (LIDAR) wind sensor, and Model Predictive Control (MPC). LIDAR wind sensors can provide near real-time wind measurements, significantly reducing wind uncertainty at launch. MPC takes full advantage of this current wind information through a unique combination of proactive control, con-traint integration and tuning flexibility. This thesis describes the development of two types of MPC controllers, as well as a baseline controller representative of current control methods used by industry. A complete description of Model Predictive Control theory and derivation of the necessary control matrices is included. The performance of each MPC controller is compared to that of the baseline controller for a wide range of wind profiles from both the Eastern and Western U.S. Test Ranges. Both MPC controllers are shown to provide reductions of greater than 50% in 0, Qo and structural bending moments. In addition, the effects of wind measurement delays and uncertainty on the performance of each controller are investigated.
Longitudinal Control And Footprint Analysis For A Reusable Military Launch Vehicle
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Author : Anhtuan D. Ngo
language : en
Publisher:
Release Date : 2003
Longitudinal Control And Footprint Analysis For A Reusable Military Launch Vehicle written by Anhtuan D. Ngo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2003 with Launch vehicles (Astronautics) categories.
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.
Maximum Range Trajectories For An Unpowered Reusable Launch Vehicle
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Author : Josiah A. Bryan
language : en
Publisher:
Release Date : 2011
Maximum Range Trajectories For An Unpowered Reusable Launch Vehicle written by Josiah A. Bryan and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011 with Electronic Dissertations categories.
A software package has been developed that numerically maximizes the range of an unpowered reusable launch vehicle (RLV) during the Terminal Area Energy Management (TAEM) phase of reentry into Earth's atmosphere by adjusting the angle-of-attack control profile at preselected energy heights along its trajectory. The software computes the optimal trajectory in terms of angle-of-attack deviations from a maximum lift-to-drag trajectory, which is the traditional trajectory used to maximize range of an unpowered aerial vehicle. In order to test the optimization software, an aerodynamic model of the X-34 launch vehicle was developed to calculate lift and drag coefficients for a given angle of attack and Mach number. Consideration of different numbers of control nodes is made, primarily with gradient-based optimization, though particle-swarm optimization is briefly tested. The merits of alternative control laws, such as constant-velocity or constant-dynamic-pressure quasi-equilibrium glide (QEG) algorithms, have also been investigated in an attempt to find a control law that does not require the inherent computational costs associated with numerical optimization. A two-point boundary-value problem is set up using optimal control theory to describe the optimization problem with simplified aerodynamic and atmospheric models.