高超声速目标在再入大气层过程中会产生覆盖在目标表面的等离子体鞘套，其对电磁波具有复杂的调制作用，并显著影响高超声速目标的散射特性。本文分析了等离子体鞘套包覆高超声速目标的双站极化散射特性。基于数值模拟的典型高度和速度下等离子鞘套参数，采用电流密度卷积法模拟了线极化平面电磁波与高超声速飞行器之间的相互作用过程。采用远场外推方法得到在俯仰角-90°~90°之间的双站极化散射分量（共极化和交叉极化）。通过对典型雷达工作频点下不同飞行和入射波条件下极化散射方向分布特性的分析，得到了飞行高度、入射角和极化模式对等离子鞘套包覆钝锥双站极化RCS的影响。

The plasma sheath covering the vehicle’s surface will be generated during the reentry of the hypersonic vehicle， which has a complex modulation effect on the electromagnetic （EM） wave and significantly affects the scattering characteristics of the hypersonic vehicle. This paper analyzes the bistatic polarization scattering characteristics of a plasma-sheath-covered hypersonic vehicle. Based on the plasma sheath parameters at typical heights and velocities solved by numerical simulation， the current density convolution method was used to simulate the interaction between the linearly polarized plane EM wave and the hypersonic vehicle. The bistatic scattering components （co-polarization and cross-polarization） at the pitch angles of -90°-90° are obtained by the far-field extrapolation method. Through studying the direction distribution characteristics of polarization scattering under different conditions of flight and incident wave at typical radar operating frequency points， this paper analyzes the effects of flight height， incident angle and polarization mode on the bistatic polarization RCS of the plasma-sheath-covered blunt cone.