Computational design of an experimental laser-powered thruster

Cover of: Computational design of an experimental laser-powered thruster |

Published by National Aeronautics and Space Administration in [Washington, DC .

Written in English

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  • Plasma rockets.,
  • Rocket engines -- Thrust.

Edition Notes

Book details

SeriesNASA-CR -- 183587., NASA contractor report -- NASA CR-183587.
ContributionsUnited States. National Aeronautics and Space Administration.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL15278228M

Download Computational design of an experimental laser-powered thruster

The computer code was used to study the behavior of laser-sustained plasmas within a pipe over a wide range of forced convection and optical arrangements before it was applied to the thruster design, and these theoretical calculations agree well with existing experimental results.

COMPUTATIONAL DESIGN OF AN EXPERIMENTAL LASER-POWERED THRUSTER Submitted by San-Mou Jeng, Ronald Litchford and Dennis Keefer Center for Laser Applications The University of Tennessee Space Institute Tullahoma, TN () Ma Final Report, Contract Number NAS Computational design of an experimental laser-powered.

Get this from a library. Computational design of an experimental laser-powered thruster. [United States. National Aeronautics and Space Administration.;]. The experimental program thus demonstrated the potential of the mini-helicon discharge as an excellent space thruster design, given its high throughput, absence of internal electrodes and cathodes.

1. Introduction. Laser propulsion has been studied as one of the propulsions that are used in space or atmosphere. Laser propulsion has an acceleration mechanism that the propellant gas is heated by laser-sustained plasma (LSP), which absorbs the high-power laser beam from a remote site and is maintained in the thruster, and the gas enthalpy is recovered as thrust by a nozzle.

Jeng S, Litchford R, Keefer D. Computational design of an experimental laser-powered thruster. NASA CRLaser-sustained argon plasmas for thermal rocket propulsion. overcome these difficulties. Therefore, the thruster was successfully designed using ideal rocket equations and the design was successfully confirmed using CFD and FEA.

NUMERICAL MODELING This thruster model dimensions are taken from standard data book. Design model is "HIPAT N (bf) Dual mode high performance liquid apogee thruster.". Experimental measurements reveal a mean potential drop inside the AC which lies between both two mobility models.

In particular, this Bohm model seem best suited to the AC region of the thruster while the wall-collision model better captures the sharp potential drop at the exit plane of the thruster.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Formalization of design for physical model of the azimuth thruster with two degrees of freedom by computational fluid dynamics methods.

Based on theoretical and practical studies into the causes of losses of propellers, caused by the axial inflows, employing the methods of computational fluid dynamics, we calculated the geometry of physical. The pump-jet is a steerable pump-based thruster suitable for shallow water and non-standard applications, which can be used both as a maneuvering aid and as the main thruster.

It provides degrees of continuous steering, a compact design, installation flush with the hull, and virtually no risk of damage from grounding or floating debris. Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design book series (NNFM, volume ) Summary An experimental and computational study of a supersonic missile with a slender cylin drical airframe and a divert jet thruster system for attitude control was a co op eration of the French-German Research Institute of Saint-Louis.

Chapter: An Experimental and Computational Study of the Effects of Propulsion Computational design of an experimental laser-powered thruster book the Free-Surface Flow Astern of Model Unfortunately, this book can't be printed from the OpenBook.

If you need to print pages from this book, we recommend downloading it as a PDF. Visit to get more. This paper describes the design, construction, and testing of a biomimetic pectoral (side) fin with actively controlled curvature for UUV propulsion. First, a 3D unsteady computational fluid dynamics (CFD) analysis tool has been adapted to computationally optimize any fin design, followed by a full parametric study based on our findings.

Second, this said fin has been constructed, and our. Books. AIAA Education Series; Library of Flight; Progress in Astronautics and Aeronautics; Experimental and computational studies of the secondary flow at the endwall of a supersonic compressor cascade.

Denver Osborne, Design of a subscale propellant slag evaluation motor using two-phase fluid dynamic analysis. Computational design of a high-efficiency accelerator grid for a miniature ion thruster by full-aperture ion optics simulations Various experimental and theoretical studies aimed at the the propellant utilization efficiency was increased from 31 to 49% at the beginning of the thruster operation.

The results of off-design performance. Underwater vehicles have become an important tool to develop oceans. The design of the shape, hardware circuit and software of a water jet propulsion spherical underwater vehicle was introduced, and the characteristics of water jet pump were presented.

The design of the thruster and computation of the thrust was proposed, too. A desired movement result was achieved by the designed spherical. The design of the attitude control thruster is depicted in Figure 7 and that of the driver thruster appears in Figure 8. The remaining propulsion system components consist of the oxidizer (H 2 O 2) and fuel (2-propanol) tanks, the valves and manifold.

EXPERIMENTAL INVESTIGATIONS OF PLASMA PARAMETERS AND SPECIES. Ion Engine and Hall Thruster Development at the NASA - NTRS. The computational results are validated with the experimental data.

Through this investigation a very efficient form of electrodynamic heating-modelling is developed. The very good results show the quality of the present method and encourage further utilisation and development. 20 hours ago  From the Journal: Physics of Fluids Link to article: Pulsed-jet propulsion of a squid-inspired swimmer at high Reynolds number DOI: / WASHINGTON, November 3, — Squids and other cephalopods use a form of jet propulsion that is not well understood, especially when it comes to their hydrodynamics under turbulent flow conditions.

Traditional magnetic field design techniques for dc ion thrusters typically focus on closing a sufficiently high maximum closed magnetic contour, B cc, inside the discharge this study, detailed computational analysis of several modified NSTAR thruster 3-ring and 4-ring magnetic field geometries reveals that the magnetic field line shape as well as B cc determines important aspects.

Experimental and Computational Multiphase Flow Home. deqo. Experimental and computational studies of electrochemical. Computational results are presented in the form of velocity profiles and pressure contours in the stern region; they are compared with available experimental data.

In addition, to facilitate the flow visualization and discussion, computed par- ticle trace are also included.

The length scale was normalized with reference length L = cm. Case 1. 11 Woronowicz, M.S., "Experimental Validation Of A Simple Bipropellant Thruster Plume Model," AIAA Paper No.

38" 1 AIAA Aerospace Sciences Meeting, Reno, NV, January 12 Woronowicz, M.S., "Alternative Description of MMH-Nitrate Formation Due to Bipropellant Thrusters," AIAA Paper No.38 s11 AIAA Aerospace Sciences. The year-old physics professor has developed what a thruster design that he hopes will serve as a proof of concept for how humans can someday achieve interstellar travel.

Computational case-based redesign for people with ability. Experimental and Numerical Examination of the BHT Hall Posted on Saturday, June 27th, at in by cuzat Ion Engine and Hall Thruster Development at the NASA - NTRS.

The algorithm estimates each thruster’s effect on the vehicle’s attitude and position. The estimated parameters are used to maintain the robot’s attitude and position. The algorithm operates by measuring impulse response of individual thrusters and thruster combinations.

Statistical metrics are. This paper discusses the design of a combined backstepping/Lyapunov controller for the attitude, velocity and height control of an unmanned, unstable, fin- Design and Experimental Validation of a Nonlinear Low-Level Controller for an Unmanned Fin-Less Airship - IEEE Journals & Magazine.

Hall thruster (HT) is one of the thrusters that are systematically applied in space. If to compare HT with plasma ion thrusters, it has lower lifetime and specific impulse.

HT has a set of advantages, and that is why interest to this plasma thruster is high. It has relatively simple design and technology of production. HT does not require a complex power supply unit, and it is very important. @article{osti_, title = {Helical plasma thruster}, author = {Beklemishev, A.

D., E-mail: [email protected]}, abstractNote = {A new scheme of plasma thruster is proposed. It is based on axial acceleration of rotating magnetized plasmas in magnetic field with helical corrugation. The idea is that the propellant ionization zone can be placed into the local magnetic well, so that initially the.

Alternatively, with CFD different vessel designs and thruster layouts can be investigated for thruster interaction effects in a cost-efficient manner early in the design process. This paper presents a practical method for modelling thrusters, describing the propeller blades as an actuator disk.

The computational model consists of the coupling of the micro gas flow in the trans-sonic thruster application (e.g. [1]) with the heating mechanism of the electron motion including the partial ionization of the subsonic flow of the electric propulsion system. The computational results are validated with the experimental data.

The cylindrical Hall thruster (CHT) is fundamentally different from the conventional design in the way the electrons are confined and the ion space charge is neutralized. The performances of both more» the large (9-cm channel diameter, W) and miniaturized (cm channel diameter, W) CHTs are comparable with those of the state.

Author(s) J. Eshraghi, E. Kosari, P. Hadikhani, A. Amini, M. Ashjaee, P. Hanafizadeh. Abstract. This paper analyses adiabatic gas bubble formation, growth, and detachment which are produced from a submerged needle in water with the aim of elucidating the impact of surface tension on bubble properties.

An ion thruster ionizes a neutral gas by extracting some electrons out of atoms, creating a cloud of positive ion thrusters rely mainly on electrostatics as ions are accelerated by the Coulomb force along an electric arily stored electrons are finally reinjected by a neutralizer in the cloud of ions after it has passed through the electrostatic grid, so the gas becomes.

About. The Penn State Department of Aerospace Engineering, established in and the only aerospace engineering department in Pennsylvania, is consistently recognized as one of the top aerospace engineering departments in the nation, and is also an international leader in aerospace education, research, and engagement.

Whitcomb LL, Yoerger DR () Development, comparison, and preliminary experimental validation of nonlinear dynamic thruster models. IEEE J Oceanic Eng 24(4) Google Scholar Cross Ref; Yoerger DR, Cooke JG, Slotine J-JE () The influence of thruster dynamics on underwater vehicle behavior and their incorporation into control system.

Invited Chapters in Books • Kinnas, S.A.“Theory and Numeric, al Methods for the Hydrodynamic Analysis of Marine Propulsors,” in Advances in Marine Hydrodynamics, Computational Mechanics Publications, Ch.

6, pp.• Kinnas, S.A., “Super-cavitating 2-D Hydrofoils: Prediction of Performance and - Design,” in CD. A side benefit is the compact installation footprint compared to a retractable thruster or inline jet thruster. Where draft is not limited, a drop-down and non-retractable azimuthing thrusters will provide higher thrust for the same engine/motor input power.

Project Presentation Day Schedule Aerospace Engineering Higgins Labs, Room am Experimental and Computational Investigation of a Dual-Bell Nozzle Katlin Davis, Elizabeth Fortner, Michael.

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