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Development Of An Implosion Driven Hypervelocity Launcher For Orbital Debris Impact Simulation
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Book Synopsis Development of an Implosion-driven Hypervelocity Launcher for Orbital Debris Impact Simulation by : Justin Huneault
Download or read book Development of an Implosion-driven Hypervelocity Launcher for Orbital Debris Impact Simulation written by Justin Huneault and published by . This book was released on 2013 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: "The ability to soft-launch projectiles to velocities exceeding 10 km/s is of interest for a number of scientific fields, including orbital debris impact testing. Current soft-launch technologies have reached a performance plateau below this operating range. In the implosion-driven launcher (IDL) concept, explosives are used to linearly implode a pressurized steel tube, thereby dynamically compressing a light driver gas to significantly higher pressures and temperatures than typical light-gas launchers. As a result, the IDL has the potential to significantly outperform current state of the art hypervelocity launchers. This work will focus on establishing an understanding of the critical design parameters of the IDL with the goal of improving the velocity potential of the launcher. For this purpose, a computational gasdynamics solver capable of simulating the internal ballistics of the IDL has been developed. The elevated pressure and temperature in the driver gas lead to a number of non-ideal effects during the launch cycle, including expansion of the launcher walls, convective heat transfer, and gas leakage, which have a significant effect on launcher performance. These effects have been simulated by coupling the gasdynamics solver to loss models. Specifically, a structural hydrocode has been developed to provide a realistic model of reservoir and launch tube expansion, which has been identified as the main source of performance loss in the launch cycle. The complete internal ballistics solver will be used in conjunction with classical internal ballistics theory and experimental results, in order to gain valuable understanding of the key design parameters of the launcher and improve the design of the McGill IDL. This analysis has led to the development of an IDL capable of launching a 0.1-g projectile to 9.1 km/s." --
Book Synopsis Concepts for Increasing the Projectile Velocity of an Implosion Driven Launcher by : Myles Hildebrand
Download or read book Concepts for Increasing the Projectile Velocity of an Implosion Driven Launcher written by Myles Hildebrand and published by . This book was released on 2017 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: "The ability to soft-launch projectiles of considerable mass (~1 g) to velocities exceeding 10 km/s is of interest in a number of scientific fields, including orbital debris impact testing. While all current technologies are limited to 10 km/s for this range of masses, the implosion-driven launcher uses explosives to shock-compress helium, driving well-characterized projectiles in the mass range of 0.1 - 10 g to velocities exceeding 10 km/s. The design shows excellent scalability, reaching similar velocities across different projectile sizes. A "virtual piston" driven by the implosion of a thin-walled tube replaces the pump tube of a conventional two-stage light gas gun. While the basic single-stage launcher is capable of regularly exceeding 10 km/s, this study outlines various modifications that could enable higher velocities. Elementary concepts including pressure and material considerations to increase projectile velocity are initially investigated. Advanced concepts aimed at reducing the initial shock loading while providing subsequent compressions to maintain a high driving pressure are also investigated. Experiments are performed with down-bore Photonic Doppler Velocimetry. A 1550 nm laser collimator is pointed down the end of the launch tube and is used to continuously measure the velocity of the projectile. The effects of the various concepts are evaluated by comparing these continuous velocity histories. The projectile integrity and terminal velocity are also verified using a high-speed camera. Projectile integrity at ultra-high accelerations is considered by examining the possibility of spall fracture as well as Rayleigh-Taylor instability. The ablation of the launch tube wall due to extreme temperatures and pressures is also investigated with a parallel experimental series, providing direct quantification of mass loss. The ablation and its counter intuitive positive effect on projectile velocity are discussed." --
Book Synopsis Development of a Single-stage Implosion-driven Hypervelocity Launcher by : Daniel Szirti
Download or read book Development of a Single-stage Implosion-driven Hypervelocity Launcher written by Daniel Szirti and published by . This book was released on 2008 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720782254 Total Pages :30 pages Book Rating :4.7/5 (822 download)
Book Synopsis Simulation of Hypervelocity Impact on Aluminum-Nextel-Kevlar Orbital Debris Shields by : National Aeronautics and Space Administration (NASA)
Download or read book Simulation of Hypervelocity Impact on Aluminum-Nextel-Kevlar Orbital Debris Shields written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An improved hybrid particle-finite element method has been developed for hypervelocity impact simulation. The method combines the general contact-impact capabilities of particle codes with the true Lagrangian kinematics of large strain finite element formulations. Unlike some alternative schemes which couple Lagrangian finite element models with smooth particle hydrodynamics, the present formulation makes no use of slidelines or penalty forces. The method has been implemented in a parallel, three dimensional computer code. Simulations of three dimensional orbital debris impact problems using this parallel hybrid particle-finite element code, show good agreement with experiment and good speedup in parallel computation. The simulations included single and multi-plate shields as well as aluminum and composite shielding materials. at an impact velocity of eleven kilometers per second.Fahrenthold, Eric P.Johnson Space CenterSIMULATION; HYPERVELOCITY IMPACT; ALUMINUM; FINITE ELEMENT METHOD; COMPUTER PROGRAMS; KEVLAR (TRADEMARK); SHIELDING; SPACE DEBRIS; COMPUTATION; HYDRODYNAMICS; IMPACT VELOCITY; LAGRANGIAN FUNCTION; METAL MATRIX COMPOSITES; PARALLEL COMPUTERS
Book Synopsis Appraisal of UTIAS Implosion-driven Hypervelocity Launchers and Shock Tubes by : I. I. Glass
Download or read book Appraisal of UTIAS Implosion-driven Hypervelocity Launchers and Shock Tubes written by I. I. Glass and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: A critical appraisal is made of the design, research, development, and operation of the novel UTIAS implosion-driven hypervelocity launchers and shock tubes. Explosively-driven (PbN6-lead azide, PETN-pentaerythritetetranitrate) implosions in detonating stoichiometric hydrogen-oxygen mixtures have been successfully developed as drivers for hypervelocity launchers and shock tubes in a safe and reusable facility. Intense loadings at very high calculated pressures (almost megabar range), densities (g/cc) and temperatures (thousands deg K), at the implosion centre, cause severe problems with projectile integrity. Misalignment of the focal point can occur and add to the difficulty in using small calibre (6 to 8 mm dia.) projectiles. In addition, the extreme driving conditions cause barrel expansion, erosion, and possible gas leakage from the base to the head of the projectile which cut the predicted muzzle velocities to half or a third of the lossless calculated values. However, in the case of a shock-tube operation these difficulties are minimized or eliminated and the possibilities of approaching Jovian reentry velocities are encouraging. In a recent run using about 100g of explosive PETN and 400 psi 2H2 + O2 a shock Mach number approx. 60 was obtained in air at an initial pressure of 1 torr in 1.0 in. dia. shock tube channel. In addition, the use of focused, explosive-driven implosion waves may have many other physical and technological applications. (Author).
Book Synopsis Implosion Driven Hypervelocity Launcher Performance Using Gaseous Detonation Waves by : John D. Watson
Download or read book Implosion Driven Hypervelocity Launcher Performance Using Gaseous Detonation Waves written by John D. Watson and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :University of Toronto. Institute for Aerospace Studies Publisher :Institute for Aerospace Studies, University of Toronto ISBN 13 : Total Pages :26 pages Book Rating :4.:/5 (227 download)
Book Synopsis Implosion Driven Hypervelocity Launcher Performance Using Gaseous Detonation Waves by : University of Toronto. Institute for Aerospace Studies
Download or read book Implosion Driven Hypervelocity Launcher Performance Using Gaseous Detonation Waves written by University of Toronto. Institute for Aerospace Studies and published by Institute for Aerospace Studies, University of Toronto. This book was released on 1967 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the performance of an Implosion-Driven Hypervelocity Launcher was made in preparation for the investigation of launcher performance using explosive liners. Initial gaseous mixtures of stoichiometric hydrogen and oxygen diluted with hydrogen or helium in the initial pressure range from 100 psi to 500 psi were used. The detonation velocities and the subsequent trajectories of the reflected shock waves in the hemispherical combustion chamber were determined for the various initial mixtures. The measured detonation velocities in this high-pressure range agree very well with theory. Gun performance for the various reservoir conditions was investigated and the performance utilizing imploding shock waves is compared to the performance using deflagrating or constant volume combustion. (Author).
Book Synopsis Development of Explosively Driven Launcher for Meteoroid Studies by : Dennis W. Baum
Download or read book Development of Explosively Driven Launcher for Meteoroid Studies written by Dennis W. Baum and published by . This book was released on 1973 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a continuing program to develop an explosively driven 2-stage hypervelocity launcher capable of achieving velocities between 15 and 20 km/sec are described. Previous efforts had identified incomplete barrel collapse as a limiting factor in launcher performance. Correlation of experimental and computational results obtained in the present study indicate that boundary-layer gases within the barrel act to prevent complete closure. Simplified calculations suggest that in-contact explosives may have insufficient energy densities to collapse the barrel against a developed boundary layer. Higher energy densities, sufficient to produce complete closure, were obtained with the use of steel flyer plates accelerated by a phased explosive lens. However, when flat flyer plates were impacted on the barrel, the sides of the barrel were observed to rupture and leak gas prior to barrel closure. A promising solution to this problem (untested) is to produce a symmetrical collapse with a cylindrical tube around the barrel.
Download or read book Hypervelocity Impact Phenomena written by and published by . This book was released on 1995 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: There is a need to determine the equations of state of materials in regimes of extreme high pressures, temperatures and strain rates that are not attainable on current two-stage light-gas guns. Understanding high-pressure material behavior is crucial to address the physical processes associated with a variety of hypervelocity impact events related to space sciences-orbital-debris impact, debris-shield designs, high-speed plasma propagation, and impact lethality applications. At very high impact velocities material properties will be dominated by phase-changes, such as melting or vaporization, which cannot be achieved at lower impact velocities. Development of well-controlled and repeatable hypervelocity launch capabilities is the first step necessary to improve our understanding of material behavior at extreme pressures and temperatures not currently available using conventional two-stage light-gas gun techniques. In this paper, techniques that have been used to extend both the launch capabilities of a two-stage light gas gun to 16 km/s, and their use to determine the material properties at pressures and temperature states higher than those ever obtained in the laboratory are summarized. The newly developed hypervelocity launcher (HVL) can launch intact (macroscopic dimensions) plates to 16 km/s. Time-resolved interferometric techniques have been used to determine shock-loading/release characteristics of materials impacted by such fliers as well as shock-induced vaporization phenomena in fully vaporized states. High-speed photography or radiography has been used to evaluate the debris propagation characteristics resulting from disc impact of thin bumper sheets at hypervelocities in excess of 10 km/s using the HVL. Examples of these experiments are provided in this paper.
Book Synopsis The MK 2 UTIAS Implosion-driven Hypervelocity Launcher Design Analysis by : V. C. D. Dawson
Download or read book The MK 2 UTIAS Implosion-driven Hypervelocity Launcher Design Analysis written by V. C. D. Dawson and published by . This book was released on 1970 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Shock and Combustion-wave Dynamics in an Implosion-driven Hypervelocity Launcher by : Irvine I. Glass
Download or read book Shock and Combustion-wave Dynamics in an Implosion-driven Hypervelocity Launcher written by Irvine I. Glass and published by . This book was released on 1965 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt: In order to solve many existing problems in planetary entry it is necessary to have facilities that are capable of launching undamaged projectiles at hypervelocities in excess of 50,000 ft/sec. Unfortunately, conventional lightgas guns appear to have reached a velocity plataeu of about 30,000 ft/sec or less for launching integral aerodynamic models. It is shown that by a novel application of combustion-wave and shock-wave dynamics in gases and explosives that it is theoretically possible to achieve projectile velocities in the desired hypervelocity range. Some details are presented of the analysis, facility, and the research results obtained to date on spherical combustion of stoichiometric mixtures of oxygen and hydrogen diluted with helium or hydrogen, the initiation of propellants and explosives by using deflagration and detonation waves, and some initial launchings. (Author).
Book Synopsis An Optimization Study of the UTIAS Implosion-driven Hypervelocity Launcher MK 2 by : Robert F. Flagg
Download or read book An Optimization Study of the UTIAS Implosion-driven Hypervelocity Launcher MK 2 written by Robert F. Flagg and published by . This book was released on 1968 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The MK II UTIAS Implosion-driven Hypervelocity Launcher Design Analysis by : V. C. D. Dawson
Download or read book The MK II UTIAS Implosion-driven Hypervelocity Launcher Design Analysis written by V. C. D. Dawson and published by . This book was released on 1970 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt: Based on initial experiments carried out on the 8 in. dia. implosion-driven hypervelocity launcher, as well as on a preliminary design study of a larger launcher facility, the design of a 30 in. dia. hypervelocity launcher was completed, and a set of detailed workshop were prepared. The report describes the basic functioning of the implosion-driven hypervelocity launcher, as well as its mechanical design, operation and firing procedures. A separate section is devoted to the strength requirements and initial stressing. By using a simple analogy with a spherical pressure chamber, the authors endeavour to estimate the plastic/elastic stress level, from which some prediction of fatigue life for such a launcher was derived. The last two sections of this report give some recommendations for the proof-testing of the launcher, as well as some basic aspects regarding safety. (Author).
Book Synopsis An Optimization Study of the UTIAS Implosion-driven Hypervelocity Launcher MK II by : Robert Finch Flagg
Download or read book An Optimization Study of the UTIAS Implosion-driven Hypervelocity Launcher MK II written by Robert Finch Flagg and published by . This book was released on 1968 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Explosively Driven Hypervelocity Launcher: Second-stage Augmentation Techniques by :
Download or read book Explosively Driven Hypervelocity Launcher: Second-stage Augmentation Techniques written by and published by . This book was released on 1973 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :P. A. L. Sevray Publisher :University of Toronto, Institute for Aerospace Studies ISBN 13 : Total Pages :23 pages Book Rating :4.:/5 (75 download)
Book Synopsis Performance Analysis of UTIAS Implosion-driven Hypervelocity Launcher by : P. A. L. Sevray
Download or read book Performance Analysis of UTIAS Implosion-driven Hypervelocity Launcher written by P. A. L. Sevray and published by University of Toronto, Institute for Aerospace Studies. This book was released on 1968 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: A performance analysis of the UTIAS Implosion-Driven Hypervelocity Launcher is presented which is based on a numerical code using the artificial viscosity technique. The numerical calculations are inviscid as no losses are taken into account and the analytical results yield performances that are at least 50 percent greater than the available experimental data. From the results obtained numerically, detailed wave-diagrams of the processes in the launcher are given. The launching conditions at the base of the projectile are emphasized. An optimization study of the existing launcher (8 in. dia.) hemispherical implosion chamber and several barrel sizes was also made followed by an analysis of what should be the optimum parameters of a second generation launcher that is able to launch one-inch diameter projectiles to hypervelocities. In order to make this calculation more realistic, a number of points should be studied and these are outlined in the conclusions. (Author).
Book Synopsis An Optimization of Study of the Utias Implosion-driven Hypervelocity Launcher Mk Ii by : Robert F. Flagg
Download or read book An Optimization of Study of the Utias Implosion-driven Hypervelocity Launcher Mk Ii written by Robert F. Flagg and published by . This book was released on 1970 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt: A detailed study is presented of the optimization of the projectile velocity of the proposed UTIAS MK II Implosion-Driven, Hypervelocity Launcher. The projectile velocity was optimized with respect to four variables, namely explosive weight, initial loading pressure, hemispherical cavity size, and peak projectile acceleration or base pressure. The details of the dynamics of the waves which occur in the chamber and the dynamics of the projectile in the barrel were determined using a finite-difference computer program coded for use with the IBM 1130 computing machine. The code, which uses the von Neumann artificial viscosity technique to solve a set of nonlinear partial differential equations that describe the motion of the gas and projectile, did not contain such effects as radiative or convective heat losses, projectile-barrel friction, or ablation. The calculations therefore represent an ideal performance and set an upper bound on what can be expected in practice. (Author).
