The annular flow electrothermal ramjet

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Dept. of Mechanical Engineering, Colorado State University, For sale by the National Technical Information Service , Fort Collins, Colo, [Springfield, Va
Arc-jet rocket en
Statementby Ben D. Shaw
SeriesNASA CR -- 174704, NASA contractor report -- 174704
ContributionsColorado State University. Dept. of Mechanical Engineering, Lewis Research Center
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL14929498M

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The annular flow, electrothermal, plug ramjet is examined as a possible means of achieving rapid projectile acceleration to velocities for such applications as direct launch of spacebound payloads. referred to as the annular flow, plug ramjet is well suited to this application and that such a device should exhibit good performance.

The general concept of the electrothermal plug ramjet is shown in Fig. The projectile, which is a solid centerbody, is shown traveling down the circular tube. It The annular flow electrothermal ramjet book shown that the performance of the conventional ramjet is superior to that of the annular flow, electrothermal ramjet.

However, it is argued that the mechanical complexities The annular flow electrothermal ramjet book with the conventional ramjet would make it impractical, and for this reason the annular flow, electro-thermal ramjet is more desirable as a launch Size: 2MB.

Theoretical analysis of the annular flow, electrothermal, plug ramjet was completed and the results are described in Ref. 3 so the results of this work will also simply be summarized here. In Ref.

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3 the ramjet is examined as a possible means of achieving rapid projectile acceleration. A model to predict ramjet flow conditions is developed in the next section. THEORETICAL MODEL FOR THERMALLY CHOKED ELECTROTHERMAL RAMJET OPERATION.

The ramjet configuration studied here is different from the thermally choked ram accelerator in that an external force (from a magnetic field) is needed to hold the arc in place behind the : B.D Shaw. Performance would be the same as a nuclear thermal rocket, about 9 km/s exhaust velocity, since both use heated Hydrogen limited by the melting point of the engine components.

It requires very high power levels for large vehicles: 44 MW / ton / g acceleration. Since. Design and Thermal Analysis of Ramjet Engine for Supersonic Speeds Valli of Mechanical Engineering, Annamacharya Instsitute of Technologies and Sciences, Kadapa.

ABSTRACT: In this project, flow through the Ramjet’s convergent divergent nozzle study is carried out by using boles'stext book and calculations are explained in File Size: KB.

Design and Fabrication of a Ramjet Inlet Clinton Humphrey 1 California Polytechnic State University, San Luis Obispo, CA, In this report, the design and fabrication of the inlet to a.

The nozzle accelerates the flow, and the reaction to this acceleration produces thrust. To maintain the flow through the nozzle, the combustion must occur at a pressure that is higher than the pressure at the nozzle exit. In a ramjet, the high pressure is produced by "ramming" external air into the combustor using the forward speed of the vehicle.

Not surprisingly, the number of books dealing with the subject is volumi-nous. For the student or researcher in the field of multiphase flow this broad 7 FLOW PATTERNS INTRODUCTION Annular flow instability 8 INTERNAL FLOW ENERGY CONVERSION INTRODUCTION FRICTIONAL LOSS IN DISPERSE FLOW File Size: 6MB.

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The combustion chamber model of a turbo-ramjet combination engine was tested on horsepower bench at Les Gatines. Only the secondary flow was supplied; the primary flow was not simulated.

The measurement methods and th data analysis procedures were developed from the first stage of the tests; also, the behavior of the test implements were verified and improved.

Description The annular flow electrothermal ramjet EPUB

The general objective of the project is fundamental mathematical modeling of a complex TSA system with electrothermal desorption step, with adsorbers assembled of one or more cartridge-type, radial flow fixed beds and with in-vessel condensation of the desorbed Size: 6MB.

Intradiscal electrothermal therapy (IDET) is a percutaneous intervention used to treat pain from internal disc disruption. We reviewed the patients who underwent this procedure in our practice.

For the ramjet, there is a terminal normal shock in the inlet that brings the flow to subsonic conditions at the burner. As speed increases, the losses through this shock eventually decrease the level of pressure that can be achieved in the burner, and this sets a limit on the use of ramjets.

An armament system provides a launch tube filled with a mixture of gaseous propellant and a projectile possessing an external surface configuration which is effective to initiate a ram jet effect between the external surface of said projectile and the inner wall of said launch tube when said projectile is inserted at a high velocity into and along said tube.

His engineering and technical background ranges from instruments to heavy engineering and he has run his own optical instrument business for decades.

Antony is also an avid pilot. He is the author of German Jet Engine and Gas Turbine Development. Nevertheless, a single air turbo-rocket is modeled to characterize the flow throughout the six units of the propulsion plant. The dual-mode ramjet (stations 80 to ) in the center discharges to the nozzle core, and the air turbo-rockets exhaust within the outer annulus of the by: American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA 07/03/ 1 Ideal Ramjet Parametric Cycle Analysis © SIM University.

All rights reserved. Introduction • T he steps of parametric cycle analysis to an idealFile Size: KB. Multi-variant three-dimensional numerical simulations demonstrate the feasibility of the continuous- detonation process in an annular combustor of a ramjet power plant operating on hydrogen as fuel and air as oxidant in conditions of flight at a Mach number of M 0 = and an altitude of 20 km.

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Conceptual schemes of an axisymmetric power plant, mm in external diameter and to m in Cited by: 9. GBA GBA GBA GBA GB A GB A GB A GB A GB A GB A GB A GB A GB A GB A GB A GB A Authority GB United Kingdom Prior art keywords cathode propellant anode tip arc Prior art date Legal status (The legal status is an assumption and is not a legal.

Fulfilling the Army's need for engines of simple design that are easy to operate and maintain, the gas turbine engine is used in all helicopters of Active Army and Reserve Components, and most of the fixedwing aircraft to include the Light Air Cushioned Vehicle (LACV).

Flow Separation Characteristics of An Asymmetric Nozzle Kang-min Lee(Korea Aerospace University) AJCPP Analysis of Thermal Throat Characteristics of a Wide-Range RBCC Combustor at Ramjet Mode LUO Feiteng(Science and Technology on Scramjet Laboratory Beijing Power Machin-ery Research Institute) AJCPP Thruster Publications: 1) T.R.

Barker and P.J. Wilbur, "Impingement-Current Erosion Characteristics of Accelerator Grids on Two-Grid Thrusters," 32nd Joint Propulsion Conference Paper AIAAJuly, Lake Buena Vista, FL. PUBLICATIONS: 1) Wilbur, Paul J. and Robert G. Jahn, "Energy Transfer from a Pulse Network to a Propagating Current Sheet," AIAA PaperJanu Ramjet Combustion Chamber Paul Cameron Stone California Polytechnic State University, 1 Grand Avenue, San Luis Obispo, California, A ramjet combustion chamber is designed and some initial assembly fabrication and test completed as a component of a ramjet graduate project for California Polytechnic State.

An electrically-powered spacecraft propulsion system uses electrical energy to change the velocity of a spacecraft. Most of these kinds of spacecraft propulsion systems work by electrically expelling propellant (reaction mass) at high speed, but electrodynamic tethers work by interacting with a.

A combustor is a component or area of a gas turbine, ramjet, or scramjet engine where combustion takes place. It is also known as a burner, combustion chamber or flame a gas turbine engine, the combustor or combustion chamber is fed high pressure air by the compression system.

The combustor then heats this air at constant pressure. After heating, air passes from the combustor through.Like an annular combustor, the DAC is a continuous ring without separate combustion zones around the radius.

The difference is that the combustor has two combustion zones around the ring; a pilot zone and a main zone. The pilot zone acts like that of a single annular combustor, and is the only zone operating at low power levels. At high power levels, the main zone is used as well, increasing air and mass flow .Colorado State University Electric Propulsion & Plasma Engineering (CEPPE) Laboratory.

The CEPPE Laboratory researches ion and hall thrusters, plasma propulsion technologies, and spacecraft propulsion systems as well as other applications of plasma technology including hydroxyapatite thin films, erosion and sputtering problems, ion optics, and computational modeling.