supersonic / hypersonic flow field numerical simulation of plasma and electromagnetic properties

Title: supersonic / hypersonic flow field numerical simulation of plasma and electromagnetic properties ofAuthor: Chang YuDegree-granting units: National Defense University of Science and TechnologyKeywords: hypersonic flow around;; thermo-chemical non-equilibrium;; re-entry;; large eddy simulation;; magnetic hydrodynamics;; electromagnetic waves;; radar cross section;; plasma;; stealthSummary:Achieve a strategic missile defense penetration and control of space vehicles, including hypersonic aircraft, including the re-entry occurs when the Rare earth magnets communication disruption of our military technology and aerospace engineering in the urgent need to address the important issue. In this paper, the subject carried out a number of relevant studies, the design unit to provide technical support.Theoretical basis of this subject is covered in the electromagnetic wave and the plasma sheath around the set of aircraft and wake flow interaction mechanism between the plasma. Control electromagnetic wave equation is the interaction with the plasma MHD equations. It is the basic equation of fluid mechanics and electrodynamics basic simultaneous equations made of coupled equations. Numerical simulation of the coupled equations for the efficiency of computer memory and demanding. This is the first application of MHD theory, the equations for the dimensionless equations that appear in the coupling term in order for the amount of analysis. On the level of theory, demonstrated that in the current range of the radar output power, fluid mechanics and electrodynamics equations can be decoupled equation solving. Thus greatly reducing the numerical simulation of electromagnetic waves with plasma mechanism of the computer memory requirements and improve the computational efficiency.Insight into the plasma sheath sets and the distribution of electromagnetic parameters of the plasma wake characteristics of electromagnetic wave-plasma interaction is discussed on the premise. Based on the above facts and in accordance with the decoupling solution given earlier conclusion, based on extensive research literature, integrated absorption of the numerical simulation of hypersonic flow of the latest developments in the use of 11-component reactive two-temperature http://www.chinamagnets.biz/faq.php model 20, using the finite volume method, implementation of the LU-SGS implicit fully discrete Navier-Stokes equations, programming and procedures are verified, the formation of a calculation software modules. Turn on the ball and two typical blunt cone hypersonic flow field around the aircraft to simulate, on a careful numerical analysis of the results given hypersonic vehicle flow field around the plasma ionized gas as required to meet the re-entry conditions, the establishment of a re-entry plasma model.This paper carefully discusses solving the propagation characteristics of electromagnetic waves in the plasma of various algorithms. After comparing the merits of the algorithm, from PLRC, JEC-FDTD algorithm, combined with ADI technology, electromagnetic waves and plasma derived from the role of PLRC, JEC-ADI-FDTD algorithm to improve the computational efficiency of the traditional FDTD method. The stability of the algorithm required to meet the conditions, the grid size selection and related key technologies were reasonable and in-depth analysis. Using PLRC, JEC, PLJERC-ADI-FDTD algorithm, the preparation of a full-band electromagnetic wave and the role of non-magnetized plasma characterization procedures and procedures for the verification, the formation of a calculation software modules.Two typical hypersonic vehicle based around the results of numerical simulation of flow field, the application of the FDTD program has a modular, re-entry of spacecraft plasma wave propagation characteristics of radar targets and a large number of comparative calculations and analysis. This is the first re-entry is given to the RCS with plasma after hydrodynamic dimensionless parameters Re and Ma / Re ~ (1 / 2) changes in the relationship, analysis of the flow state changes on the aircraft radar target characteristics. Plasma waves and re-examined the mechanism of action, verify the value of plasma stealth is achievable.Study of plasma stealth technology works, the method of plasma stealth, stealth efficiency and other factors, the authors view of the wake flow field often in a turbulent flow, vortex plasma stealth idea was first proposed, and the first application of numerical simulation study based on fluid properties of the plasma vortex stealth mechanism. To this end the preparation of large-eddy simulation of turbulent flow calculation procedure, the formation of a calculation software modules. Numerical simulation shows the free shear layer vortex formation and development movement, get vortex structure characteristics. Then the application of existing procedures for numerical simulation of FDTD electromagnetic waves in the propagation characteristics of the plasma vortex. Numerical simulation confirmed that plasma vortices can be effectively attenuated and refracted waves, with a good stealth performance.In short, this set of software modules for the calculation of the formation of supersonic / hypersonic flow field numerical simulation of plasma and magnetic properties of as one, both numerical simulation of flow around a hypersonic vehicle flow, gives the aerodynamic characteristics, electromagnetic characteristics and parameters of the turbulent eddy formation and development, hypersonic vehicle aerodynamics and thermal protection design to provide technical support for the study of aircraft penetration, control of the breakdown in communications designed to provide flow data; numerical simulation of electromagnetic waves and can flow with the role of plasma characteristics of electromagnetic waves and coated hypersonic vehicle plasma sheath around the set and the plasma wake plasma stealth mechanism and the mechanism of penetration for the hypersonic vehicle design and control of communications designed to provide technical support interrupts.Degree Year: 2009