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.
概要
目的
通过对俯仰运动情况下的钝锥体等离子鞘套进行数值模拟, 揭示动态等离子鞘套的分布规律, 提高数据的可靠性, 为进一步研究入射电磁波与动态等离子鞘套的相互作用机理提供有力依据, 并为再入飞行器黑障问题的解决和再入飞行器设计提供参考.
创新点
考虑热化学非平衡效应的简化常规 Burnett (SCB) 方程能够更准确地描述再入飞行器等离子鞘套的动态分布规律.
方 法
1. 提出稀薄流域稳态与动态等离子鞘套数值模拟方法; 2. 对不同化学反应动力学模型和热力学模型进行数值比较和验证; 3. 引入俯仰运动后对再入飞行器等离子鞘套的动态特性进行数值模拟.
结 论
在稀薄流条件下 SCB 方程模拟得到的激波更厚, 对等离子鞘套的刻画更为准确精细. 2. 7 组元 Gupta 化学反应模型与 Park 双温模型的计算结果优于其他模型. 3. 引入俯仰运动后, 飞行器不同位置的碰撞频率等关键参数与俯仰运动的周期存在相位差; 同时增强稀薄效应将减弱俯仰运动对动态等离子鞘套的扰动.
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References
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.
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. https://doi.org/10.2514/6.2014-2376
Boyd ID, 2007. Modeling of associative ionization reactions in hypersonic rarefied flows. Physics of Fluids, 19(9):096102. https://doi.org/10.1063/1.2771662
Candler GV, 1988. The Computation of Weakly Ionized Hypersonic Flows in Thermo-chemical Nonequilibrium. PhD Thesis, Stanford University, California, USA.
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. https://doi.org/10.1098/rsta.1916.0006
Dunn MG, Kang S, 1973. Theoretical and Experimental Studies of Reentry Plasmas. NASA CR-2232, National Aeronautics and Space Administration, Washington, USA.
Edquist KT, 2005. Afterbody heating predictions for a Mars science laboratory entry vehicle. Proceedings of the 38th AIAA Thermophysics Conference. https://doi.org/10.2514/6.2005-4817
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 30000 K. NASA STI/Recon Technical Report N, NASA, Washington, USA.
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).
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. https://doi.org/10.1006/jcph.2001.6873
Li DH, 2005. Development of main mission antenna system of Shenzhou spacecraft. Journal of Manned Space, (3):23–27 (in Chinese).
Mazumder S, 2016. Numerical Methods for Partial Differential Equations. Academic Press, New York, USA, p.277–338. https://doi.org/10.1016/B978-0-12-849894-1.00006-8
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. https://doi.org/10.1109/27.772290
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.
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.
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. https://doi.org/10.2514/6.2006-3773
Walters RW, Cinnella P, Slack DC, et al., 1992. Characteristic-based algorithms for flows in thermochemical nonequilibrium. AIAA Journal, 30(5):1304–1313. https://doi.org/10.2514/3.11065
Wang CS, Uhlenbeck GE, 1948. On the transport phenomena in rarefied gases. Studies in Statistical Mechanics, 5:1–17.
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. https://doi.org/10.2514/6.2004-2456
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. https://doi.org/10.1007/s10762-007-9226-8
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). https://doi.org/10.7498/aps.62.104101
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.
Yoon S, Jameson A, 1987. An LU-SSOR scheme for the Euler and Navier-Stokes equations. Proceedings of the 25th AIAA Aerospace Sciences Meeting. https://doi.org/10.2514/6.1987-600
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. https://doi.org/10.2514/1.A33059
Zhong XL, MacCormack RW, Chapman DR, 1993. Stabilization of the Burnett equations and application to hypersonicflows. AIAA Journal, 31(6):1036–1043. https://doi.org/10.2514/3.11726
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De-yang TIAN designed the research. De-yang TIAN and Guo-chao FAN processed the corresponding data. De-yang TIAN wrote the first draft of the manuscript. Guo-chao FAN and Wei-fang CHEN helped to organize the manuscript. De-yang TIAN and Wei-fang CHEN revised and edited the final version.
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De-yang TIAN, Guo-chao FAN, and Wei-fang CHEN declare that they have no conflict of interest.
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Tian, Dy., Fan, Gc. & Chen, Wf. Numerical investigation of dynamic properties of plasma sheath with pitching motion. J. Zhejiang Univ. Sci. A 21, 209–217 (2020). https://doi.org/10.1631/jzus.A1900503
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DOI: https://doi.org/10.1631/jzus.A1900503