Longitudinal Control And Footprint Analysis For A Reusable Military Launch Vehicle
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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.
Footprint Determination For Reusable Launch Vehicles Experiencing Control Effector Failures
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Author : David B. Doman
language : en
Publisher:
Release Date : 2002
Footprint Determination For Reusable Launch Vehicles Experiencing Control Effector Failures written by David B. Doman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with Launch vehicles (Astronautics) categories.
The ability to compute the maximum area on the earth's surface (footprint) reachable by an autonomous air vehicle can be useful in planning for the vehicle's safe operations. The information can be important when the vehicle experiences subsystem failures causing it to be unable to maintain its nominal performance. In this paper, we present a method to calculate the footprint of a reusable launch vehicle that experiences a failure in one or more of its aero-control surfaces. During a control effector failure, the maximum attainable moments of the vehicle are reduced, which may decrease the range of conditions that the vehicle can maintain a trimmed condition. Additionally, the lift and drag characteristics of the vehicle can change when control effectors are moved to off-nominal positions to correct for moment imbalance caused by failures or damage. As a result, the footprint of the vehicle is reduced. A technique for calculating the available effectiveness of the aero-control surfaces is used in conjunction with a footprint generation algorithm to include the effects of rotational trim on the vehicle footprint.
Concepts Of Operations For A Reusable Launch Vehicle
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Author : Michael A. Rampino
language : en
Publisher:
Release Date : 1997
Concepts Of Operations For A Reusable Launch Vehicle written by Michael A. Rampino and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1997 with Launch vehicles (Astronautics) categories.
The United States is embarked on a journey toward maturity as a spacefaring nation. One key step along the way is development of a reusable launch vehicle (RLV). The most recent National Space Transportation Policy (August 1994) assigned improvement and evolution of current expendable launch vehicles to the Department of Defense while National Aeronautical Space Administration (NASA) is responsible for working with industry on demonstrating RLV technology. The purpose of this study is to help ensure the US military, especially the USAF, is prepared to take advantage of RLVs should the NASA-led effort to develop an RLV demonstrator prove successful. The focus of this study is an explanation of how the US military could use RLVs, by describing and analyzing two concepts of operations. Four major conclusions resulted from the analysis. First, RLVs have military potential. They can perform a variety of missions including responsive spacelift, reconnaissance, and strike. However, the economic feasibility of using RLVs for earth-to-earth transportation is questionable. Second, design choices for an operational RLV will have effects on risk, cost, capability, and operations efficiency. Trade-offs will have to be made between NASA, commercial, and military requirements if all three parties are to use the same fleet of RLVs. Third, increased investment in propulsion technology development is warranted to ensure success. Fourth, the top priority for the RLV program, even from the military's perspective, should remain cheap and responsive access to space. The research led to three recommendations. First, the US military should become a more active participant in the RLV program to ensure its requirements are defined and incorporated. Second, America should not pursue development of operational RLVs before the technology is ready.
Analysis Of The Staging Maneuver And Booster Glideback Guidance For A Two Stage Winged Fully Reusable Launch Vehicle
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Author : J. Christopher Naftel
language : en
Publisher:
Release Date : 1993
Analysis Of The Staging Maneuver And Booster Glideback Guidance For A Two Stage Winged Fully Reusable Launch Vehicle written by J. Christopher Naftel and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1993 with Launch vehicles (Astronautics) categories.
Reusable Launch Vehicle
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Author : National Research Council
language : en
Publisher: National Academies Press
Release Date : 1996-01-08
Reusable Launch Vehicle written by National Research Council and has been published by National Academies Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996-01-08 with Science categories.
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.
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.
Commercial Satellite Launch Vehicle Attitude Control Systems Design And Analysis H Infinity Loop Shaping And Coprime Approach
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Author : Chong Hun Kim
language : en
Publisher: Lulu.com
Release Date : 2007
Commercial Satellite Launch Vehicle Attitude Control Systems Design And Analysis H Infinity Loop Shaping And Coprime Approach written by Chong Hun Kim and has been published by Lulu.com this book supported file pdf, txt, epub, kindle and other format this book has been release on 2007 with Technology & Engineering categories.
This book is written for aerospace engineers who have completed their BS degree and are interested in the design and analysis of rocket attitude control systems. It introduces a new approach to the design, characterized by its robustness. Current LV attitude control systems are designed based on classical SISO control theory, and they lack robustness. The theory used here truly offers a technique that enables us to design control systems that are reasonably insensitive to math modeling errors and can withstand disturbances such as gust, and in addition it doesn’t need external states estimator, such as Kalman filtering. Extensive simulation results, which demonstrate the effectiveness of this approach, are presented in this book. Basic rocket theory and a concept of H-infinity control system design technique are explained for those who are new in these fields of study.
Payload Performance Analysis For A Reusable Two Stage To Orbit Vehicle
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-05-22
Payload Performance Analysis For A Reusable Two Stage To Orbit Vehicle written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-05-22 with categories.
This paper investigates a unique approach in the development of a reusable launch vehicle where, instead of designing the vehicle to be reusable from its inception, as was done for the Space Shuttle, an expendable two stage launch vehicle is evolved over time into a reusable launch vehicle. To accomplish this objective, each stage is made reusable by adding the systems necessary to perform functions such as thermal protection and landing, without significantly altering the primary subsystems and outer mold line of the original expendable vehicle. In addition, some of the propellant normally used for ascent is used instead for additional propulsive maneuvers after staging in order to return both stages to the launch site, keep loads within acceptable limits and perform a soft landing. This paper presents a performance analysis that was performed to investigate the feasibility of this approach by quantifying the reduction in payload capability of the original expendable launch vehicle after accounting for the mass additions, trajectory changes and increased propellant requirements necessary for reusability. Results show that it is feasible to return both stages to the launch site with a positive payload capability equal to approximately 50 percent of an equivalent expendable launch vehicle. Further discussion examines the ability to return a crew/cargo capsule to the launch site and presents technical challenges that would have to be overcome. Tartabini, Paul V. and Beaty, James R. and Lepsch, Roger A. and Gilbert, Michael G. Langley Research Center PAYLOADS; PERFORMANCE PREDICTION; REUSABLE LAUNCH VEHICLES; MULTISTAGE ROCKET VEHICLES; ASCENT; LAUNCHING SITES; PROPELLANTS; SOFT LANDING; TRAJECTORIES; THERMAL PROTECTION; AERODYNAMIC HEATING; REENTRY EFFECTS; CARGO; SPACECREWS; SPACECRAFT MODULES; HEAT SHIELDING
Life Cycle Cost Assessments For Military Transatmospheric Vehicles
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Author :
language : en
Publisher:
Release Date : 1997
Life Cycle Cost Assessments For Military Transatmospheric Vehicles written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1997 with categories.
The X-33 and X-34 technology demonstration programs currently under way by NASA may ultimately lead to a commercial reusable launch vehicle (RLV). The first flight test for the X-33 vehicle is planned for early 1999. With NASA fully committed to the development of this first-ever completely reusable vehicle, it is prudent for the Air Force to examine the potential benefits, requirements, and costs for a military transatmospheric vehicle (TAV). This vehicle would take advantage of technologies developed during RLV-related programs. Although similar in concept, a military TAV may differ significantly in design and in capability from an RLV produced to satisfy commercial market needs.
Taming Liquid Hydrogen
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Author : Virginia Parker Dawson
language : en
Publisher:
Release Date : 2004
Taming Liquid Hydrogen written by Virginia Parker Dawson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2004 with Centaur rocket categories.