Download or read book Launch Condition Deviations of Reusable Launch Vehicle Simulation written by Peter H. Urschel and published by . This book was released on 2003 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Launch Condition Deviations of Reusable Launch Vehicle Simulations in Exo Atmospheric Zoom Climbs written by Peter H. Urschel and published by . This book was released on 2003 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Launch Condition Deviations of Reusable Launch Vehicle Simulations in Exo Atmospheric Zoom Climbs written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-15 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Defense Advanced Research Projects Agency has proposed a two-stage system to deliver a small payload to orbit. The proposal calls for an airplane to perform an exo-atmospheric zoom climb maneuver, from which a second-stage rocket is launched carrying the payload into orbit. The NASA Dryden Flight Research Center has conducted an in-house generic simulation study to determine how accurately a human-piloted airplane can deliver a second-stage rocket to a desired exo-atmospheric launch condition. A high-performance, fighter-type, fixed-base, real-time, pilot-in-the-loop airplane simulation has been modified to perform exo-atmospheric zoom climb maneuvers. Four research pilots tracked a reference trajectory in the presence of winds, initial offsets, and degraded engine thrust to a second-stage launch condition. These launch conditions have been compared to the reference launch condition to characterize the expected deviation. At each launch condition, a speed change was applied to the second-stage rocket to insert the payload onto a transfer orbit to the desired operational orbit. The most sensitive of the test cases was the degraded thrust case, yielding second-stage launch energies that were too low to achieve the radius of the desired operational orbit. The handling qualities of the airplane, as a first-stage vehicle, have also been investigated.Urschel, Peter H. and Cox, Timothy H.Armstrong Flight Research CenterAEROMANEUVERING; CLIMBING FLIGHT; REUSABLE LAUNCH VEHICLES; TRANSFER ORBITS; PAYLOAD TRANSFER; SIMULATION; TRAJECTORIES; CONTROLLABILITY
Download or read book Footprint Determination for Reusable Launch Vehicles Experiencing Control Effector Failures written by David B. Doman and published by . This book was released on 2002 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Testing the Effects of Cannibalization on the Reusable Launch Vehicle Repair Cycle written by and published by . This book was released on 2001 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
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:
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.
Download or read book An Exploratory Study of Parallel stage Separation of Reusable Launch Vehicles written by John P. Decker and published by . This book was released on 1968 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Structures and Materials Technology Issues for Reusable Launch Vehicles written by and published by . This book was released on 1985 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Demonstration and Analysis of Reusable Launch Vehicle Operations written by John Garvey and published by . This book was released on 2006 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Report developed under SBIR contract for topic AF05-201. The increased use of reusable systems continues to be one of the most promising options for creating advancements in the daily maintenance of rocket systems, lowering hours for preparation and diminishing expenses for preparation. However, since the end of the DC-X/XA Delta Clipper program, flight testing of candidate reusable launch vehicle (RLV) designs, technologies and operations has come to a halt. This project addressed this situation through the development and flight testing during Phase I of an early prototype RLV that could ultimately evolve into the first stage of an operational nanosat launch vehicle (NLV). This LOX/ethanol-propellant vehicle -the Prospector 7 -took flight twice within a 3.5 hour period after less than a day of pre-launch field preparations, thereby establishing a new reference metric for RLV-type responsive, fast turn-around launch operations. Besides serving as an operational pathfinder, this RLV test bed also manifested several academic payloads in support of a related goal of assessing candidate nanosat-class payload accommodations. In a solid demonstration of the commercial potential for this kind of capability, the Prospector 7 itself has already been assigned to non-SBIR follow-on flight test activities.
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.
Download or read book Maximum range Trajectories for an Unpowered Reusable Launch Vehicle written by Josiah A. Bryan and published by . This book was released on 2011 with total page 181 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Launch Vehicle Language LVL Data Model for Evaluating Reusable Launch Vehicle ConceptsJeremy Vander Kam Peter Gage written by Jeremy Vander Kam and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Study Task for Determining the Effects of Boost Phase Environments on Densified Propellants Thermal Conditions for Expendable Launch Vehicles written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-17 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A thermodynamic study has been conducted that investigated the effects of the boost-phase environment on densified propellant thermal conditions for expendable launch vehicles. Two thermodynamic models were developed and utilized to bound the expected thermodynamic conditions inside the cryogenic liquid hydrogen and oxygen propellant tanks of an Atlas IIAS/Centaur launch vehicle during the initial phases of flight. The ideal isentropic compression model was developed to predict minimum pressurant gas requirements. The thermal equilibrium model was developed to predict the maximum pressurant gas requirements. The models were modified to simulate the required flight tank pressure profiles through ramp pressurization, liquid expulsion, and tank venting. The transient parameters investigated were: liquid temperature, liquid level, and pressurant gas consumption. Several mission scenarios were analyzed using the thermodynamic models, and the results indicate that flying an Atlas IIAS launch vehicle with densified propellants is feasible and beneficial but may require some minor changes to the vehicle.Haberbusch, Mark S. and Meyer, Michael L. (Technical Monitor)Glenn Research CenterROCKET PROPELLANTS; PROPELLANT TANKS; FUEL TANK PRESSURIZATION; PRESSURIZING; THERMODYNAMICS; SIMULATION; ATLAS CENTAUR LAUNCH VEHICLE; DENSIFICATION; TRAJECTORY ANALYSIS
Download or read book Reduced order Trajectory Guidance for a Reusable Launch Vehicle written by David T. Chen and published by . This book was released on 1999 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reusable Launch Vehicle RLV Technology written by David P. Radzanowski and published by . This book was released on 1995 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt:
