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Abstract: Research on the dynamic properties of a plasma sheath coupled with pitching motion of the vehicle has great significance in solving the problem of communication interruption in the process of vehicle reentry. This paper investigates the dynamic properties of the plasma sheath by using the simplified conventional Burnett (SCB) equations and the Navier-Stokes (NS) equations with the thermochemical non-equilibrium effect. The eleven-species chemical kinetic models are applied to the comparison and there is verification of a dynamic plasma sheath simulation for the first time. After the introduction of vehicle pitching motion, the dynamic results are more consistent with the experimental data than the simulated results when treating it as static state. The plasma sheath characteristic parameters show periodic properties, whose changing period is the same as the pitching motion period. However, because of different velocities of the pitching motion, phase shifts exist in different positions of the vehicle. The enhancement of the rarefied effect weakens the disturbance to the plasma sheath. This research reveals the distribution and regularities of the dynamic plasma sheath. It is significant in solving the ionization blackout problem and the design of the reentry vehicle, and provides reliable data for further research on the dynamic plasma sheath.

The dynamic properties of the plasma sheath coupled with the pitching motion of the reentry vehicle has been investigated numerically, and the numerical approaches employed in the current study have been validated against the experimental data of RAM-C II vehicle. At the same time, several chemical reaction kinetics models have been taken into consideration for comparison. This research provides a great help for the analysis of the surrounding environment around the reentry vehicle.

俯仰运动下等离子鞘套动态特性数值研究

[1]Akey ND, Cross AE, 1970. Radio Blackout Alleviation and Plasma Diagnostic Results from a 25000 Foot per Second Blunt-body Reentry. NASA Technical Note, NASA TND-5615, National Aeronautics and Space Administration, Washington, USA.

[2]Andrienko DA, Shang JS, Surzhikov ST, et al., 2014. Non-equilibrium flow field of RAM-C II probe. Proceedings of the 45th AIAA Plasmadynamics and Lasers Conference.

[3]Boyd ID, 2007. Modeling of associative ionization reactions in hypersonic rarefied flows. Physics of Fluids, 19(9):096102.

[4]Candler GV, 1988. The Computation of Weakly Ionized Hypersonic Flows in Thermo-chemical Nonequilibrium. PhD Thesis, Stanford University, California, USA.

[5]Chapman S, 1916. On the law of distribution of molecular velocities, and on the theory of viscosity and thermal conduction, in a non-uniform simple monatomic gas. Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences, 216(538-548):279-348.

[6]Dunn MG, Kang S, 1973. Theoretical and Experimental Studies of Reentry Plasmas. NASA CR-2232, National Aeronautics and Space Administration, Washington, USA.

[7]Edquist KT, 2005. Afterbody heating predictions for a Mars science laboratory entry vehicle. Proceedings of the 38th AIAA Thermophysics Conference.

[8]Gupta RN, Yos JM, Thompson RA, et al., 1990. A Review of Reaction Rates and Thermodynamic and Transport Properties for an 11-Species Air Model for Chemical and Thermal Nonequilibrium Calculations to 30 000 K. NASA STI/Recon Technical Report N, NASA, Washington, USA.

[9]Hu HJ, Liu J, Ma M, 2006. Radar and USB capture and track the re-entry module in the black block area. Manned Spaceflight, (3):49-53 (in Chinese).

[10]Kim KH, Kim C, Rho OH, 2001. Methods for the accurate computations of hypersonic flows: I. AUSMPW+scheme. Journal of Computational Physics, 174(1):38-80.

[11]Li DH, 2005. Development of main mission antenna system of Shenzhou spacecraft. Journal of Manned Space, (3):23-27 (in Chinese).

[12]Mazumder S, 2016. Numerical Methods for Partial Differential Equations. Academic Press, New York, USA, p.277-338.

[13]Ohler SG, Gilchrist BE, Gallimore AD, 1999. Electromagnetic signal modification in a localized high-speed plasma flow: simulations and experimental validation of a stationary plasma thruster. IEEE Transactions on Plasma Science, 27(2):587-594.

[14]Park C, 1985. Problems of rate chemistry in the flight regimes of aeroassisted orbital transfer vehicles. In: Nelson HF (Ed.), Progress in Astronautics and Aeronautics: Thermal Design of Aeroassisted Orbital Transfer Vehicles. AIAA, New York, USA, p.511-537.

[15]Piziali RA, 1994. 2-D and 3-D Oscillating Wing Aerodynamics for a Range of Angles of Attack Including Stall. NASA TM 4632, National Aeronautics and Space Administration, Washington, USA.

[16]Scalabrin LC, Boyd ID, 2006. Numerical simulation of weakly ionized hypersonic flow for reentry configurations. Proceedings of the 9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference.

[17]Walters RW, Cinnella P, Slack DC, et al., 1992. Characteristic-based algorithms for flows in thermochemical nonequilibrium. AIAA Journal, 30(5):1304-1313.

[18]Wang CS, Uhlenbeck GE, 1948. On the transport phenomena in rarefied gases. Studies in Statistical Mechanics, 5:1-17.

[19]Wright MJ, Prabhu DK, Martinez ER, 2004. Analysis of afterbody heating rates on the Apollo command modules, part I: AS-202. Proceedings of the 37th AIAA Thermophysics Conference.

[20]Yang HW, Tang WC, Kong XK, 2007. Calculation of the effect on the reflection of the plane electromagnetic wave for non-magnetized plasma with different electron density distributions. International Journal of Infrared and Millimeter Waves, 28(7):547-556.

[21]Yang LX, Shen DH, Shi WD, 2013. Analyses of electromagnetic scattering characteristics for 3D time-varying plasma medium. Acta Physica Sinica, 62(10):104101 (in Chinese).

[22]Yoon S, Jameson A, 1986. A Multigrid LU-SSOR Scheme for Approximate Newton Iteration Applied to the Euler Equations. NASA Contractor Report 179524, National Aeronautics and Space Administration, Washington, USA.

[23]Yoon S, Jameson A, 1987. An LU-SSOR scheme for the Euler and Navier-Stokes equations. Proceedings of the 25th AIAA Aerospace Sciences Meeting.

[24]Zhao WW, Chen WF, Agarwal RK, 2015. Computation of rarefied hypersonic flows using modified form of conventional Burnett equations. Journal of Spacecraft and Rockets, 52(3):789-803.

[25]Zhong XL, MacCormack RW, Chapman DR, 1993. Stabilization of the Burnett equations and application to hypersonicflows. AIAA Journal, 31(6):1036-1043.