Download or read book Hypersonic Plasma Generator written by Andre LeBlanc and published by . This book was released on 1962 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Special Materials Tests for the Hypersonic Plasma Generator written by K. J. Touryan and published by . This book was released on 1965 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Hypersonic Plasma Converter I written by K. J. Touryan and published by . This book was released on 1964 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Theoretical and experimental analyses are presented which describe the operation of the hypersonic plasma generator as ASP (Aerodynamic Supply of Power). Previous investigations are reviewed, corrected and summarized. Additional information is introduced to bring the present status of the generator up to date.

Download or read book Hypersonic Plasma Thermionic Generator written by Andre LeBlanc and published by . This book was released on 1962 with total page 438 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Hypersonic Plasma Thermionic Generator written by William J. Byatt and published by . This book was released on 1964 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Hypersonic Plasma Converter II written by K. J. Touryan and published by . This book was released on 1964 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: As a continuation to Part I (SC-4960(RR)) of the hypersonic plasma generator known as ASP (Aerodynamic Supply of Power), experimental analyses have been extended to investigate in detail the various parameters that govern the operation of the generator. A final feasibility study was made, and possible modifications to the theory are outlined. Test runs in the Sandia Corporation arc jet with air as the working fluid at 12,000 BTU/lb have generated 8 amp/sq in short circuit currents and 2.3 volts open circuit voltage. Under favorable conditions, fullsize re-entry vehicles in the altitude range of 200,000 to 80,000 feet are expected to yield several kilowatts of power. (Author).

Download or read book Hypersonic Plasma Thermionic Generator written by Andre LeBlanc and published by . This book was released on 1962 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Hypersonic Plasma Thermionic Generator written by and published by . This book was released on 1963 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Hypersonic Plasma Thermionic Generator written by C. W. Bryan and published by . This book was released on 1963 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Hypersonic Plasma Thermocouple Generator written by C. W. Bryan and published by . This book was released on 1963 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Study on Supersonic and Hypersonic Flows Around Models with On Board Plasma Generators written by and published by . This book was released on 1998 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this report, the results of experiments on the contract SPC-97-4042 in the wind tunnel T-113 of TsAGI at Mach number M = 4 and static pressure equal 29 torr are presented. The tests were carried out with three types of axisymmetical models. Two of them were equipped by plasma generators and had the different form of the nose part. In front of the bluntness, these models had the needle. Besides, the nose parts of them were produced of two different isolator materials. The plasma generators were supplied by energy either from the alternating current source of electric power or from the capacity storage. The third type of the model was the body contour of which was close the optimal one for M = 4 and did not have any generator. The models equipped by plasma generators were produced by MTC, the model of the third type was made by TsAGI. In all runs, the balance measurements and schlieren photo registrations were carried out. In the experiments with the models equipped by plasma generators, the spectroscopic diagnostic of the discharges by MSU (to the end of determination of rotation and vibration temperatures) and ordinary photography were also fulfilled. Full results of the aerodynamic experiments and significant results of other investigations will be further presented. In these experiments, the effect of the drag decrease at the discharge presence did not exceed 14 % and the model of the optimal form had the drag coefficient less than the models with working plasma generators.

Download or read book Automated Design Optimization for Hypersonic Plasma aerodynamics written by Ramakanth Munipalli and published by . This book was released on 2005 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the first part we present our ongoing work on the optimization of an MHD energy by-pass concept. Here we consider the optimization of the power generator and accelerator components individually, and are in the process of a simultaneous optimization of an integrated generator-combustor-accelerator concept in a 2-D sense. We have concentrated our efforts on developing an optimization scheme that couples a flow solver (perfect gas Euler and equilibrium gas N-S) with a Poisson solver for the electric field including Hall effects. The architecture/algorithm of the optimization scheme is such that geometric and/or physical parameters can be optimized for a given set of free-stream conditions and objective function. The objective function was MHD power extracted in the case of a MHD generator, and thrust in the case of an accelerator. The second part of this report presents some ideas on how to extend this development and the associated real-gas MHD technology at HyPerComp Inc. into a potential Phase-II. We have developed a higher (4% order and beyond,) order accurate solver for MHD developed under an AFRL contract. We consider possibilities involving the usage of this solver in accurate boundary layer calculations and plasma effects in shear layers as a potential Phase-II extension. The current study of energy bypass concepts may itself be extended into an extensive exploration of finite rate processes in such systems coupled with an efficient optimization routine based on adjoint methods. A masters thesis supported in part by this contract on the optimization problem setup for hypersonic inlets to improve mass capture has been completed. Relevant portions of this thesis have been appended to this report in the third part.

Download or read book Stationary Electric Arc Plasma Generator for Influencing on Supersonic Gas Flow written by and published by . This book was released on 2003 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: Studies of plasma jet interaction with cross flows has been made for development of the concept of enhancing of combustion and ignition at application of plasma jets. A computer simulation of a cross flow nitrogen plasma nitrogen jet from the divergent plasma generator in nitrogen has been carried out. This model involves a realistic equation of state, plasma radiation associated with plasma formation inside the plasma jet as well as coupling between the internal nozzle with external flow fields. Our model facilitates the application of the implicit free-Lagrange method for carrying out of computations, which have been carried out for jet injection angles 135 degrees into the cross flow. These show the complex and non-homogeneous structure of the flow. They represent the necessary step in understanding of applicability of the divergent plasma jets for propulsion enhancement.

Download or read book Computations of Stationary Electric Arc Plasma Generator for Influencing on Supersonic Gas Flow written by and published by . This book was released on 2003 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt: Studies of plasma jet interaction with cross flows has been made for development of the concept of enhancing of combustion and ignition at application of plasma jets. A computer simulation of a cross flow nitrogen plasma nitrogen jet from the divergent plasma generator in nitrogen has been carried out. This model involves a realistic equation of state, plasma radiation associated with plasma formation inside the plasma jet as well as coupling between the internal nozzle with external flow fields. Our model facilitates the application of the implicit free-Lagrange method for carrying out of computations, which have been carried out for jet injection angles 135 into the cross flow. These show the complex and non-homogeneous structure of the flow. They represent the necessary step in understanding of applicability of the divergent plasma jets for propulsion enhancement.

Download or read book Hypersonic Vehicle Electric Power System Technology Delivery Order 0003 MHD Generator Magnet Analysis Design Modeling and Simulation written by and published by . This book was released on 2004 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypersonic aircraft have limited on-board electrical power unless this power can be generated from the flow-stream itself. Since turbines are not feasible at high Mach numbers, the only known technology remaining is magnetohydrodynamics. This is made feasible because the air when slowed to Mach 1 is heated to a plasma state (3000 K+) which is electrically conductive, enhanced even further by injecting potassium into the flow-stream. The magnetic field necessary to divert the charged particles is a dipole with a central field of 4 T, which is limited to the domain of a superconducting magnet. The geometry is circular due to constraints on the generator, which resides in the bore of the magnet. A dipole field is produced in circular geometry using saddle coils, a configuration requiring a 100 mm thick cylindrical structure to resist the Lorentz forces. The baseline conductor is Niobium-Titanium because of its high current density at 4.2 K and concomitant low mass. Depending on the mission profile and material availability, high-temperature superconductors and cryo-aluminum may be attractive substitutes because they may be cooled with the cryogenic hydrogen fuel instead of on-board cryocoolers.

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Weakly Ionized Plasmas and MHD for Enhanced Performance of Hypersonic Vehicles written by and published by . This book was released on 2004 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerospace Applications of Weakly Ionized Plasmas: * Power generation using MHD * Use of power to control aerodynamics and propulsion: (1) Surface plasmas for separation and turbulent transition control (virtual shapes) (2) Virtual shapes created by off-body energy addition for drag reduction, steering, shock control, flow turning (3) Plasma-assisted combustion. * Power extraction from one region and its use in another region (MHD bypass) * Dual-use MHD devices (both power generation and flow control): (1) Forces created by magnetic and electric fields acting on charged particles (transferred to neutral gas by collisions) (2) Ionization level per se is not critical if plasmas are used as a means of delivering energy to the flow (3) Ionization is critical in MHD power generation and flow control, and in cold-plasma generation of radicals (4) At high T (reentry, scramjet combustor) -- thermal ionization with alkali seed (5) At low T, artificial ionization is needed, and the ionization cost determines design and performance (6) Similar to ionization, cold plasma generation of chemically active species for combustion can have considerable energy cost (7) Both energy addition and extraction result in flow heating and losses of total pressure and (if in propulsion flowpath) thrust.