针对宽域高速飞行器轴对称尾喷管宽域高性能、出口几何可调和高效推力矢量能力的迫切需求，设计了一种宽域高超声速飞行器可调矢量喷管及内-中-外三套环调节方案，对该喷管在典型工况下进行数值模拟，分析了不同模态下喷管的流场结构和性能。结果表明，通过平动调节中、外套环的位置，喷管既可以调节出口面积，又具备推力矢量能力。非矢量模态，由于喷管出口面积可调，有效缓解了低落压比工况下的过膨胀现象，推力性能显著提高，相较于固定几何喷管，推力系数最多增加32.75%；矢量模态下，马赫数7工况最高能产生大于10°的矢量角，同时推力系数仍大于0.92。为进一步降低低马赫数下喷管的底阻，提出了次流进气的流动控制方法，通过降低次流通道的内外压差，最大可以减少78.5%的底阻。最后开展了风洞缩比试验，试验结果与数值仿真结果吻合良好，验证了该宽域高超声速飞行器可调矢量喷管设计方案的有效性。

In response to the urgent requirements of wide-range high performance, geometric adaptability of the exit, and efficient thrust vectoring capability of axisymmetric nozzles for wide-range high-speed aircraft, an adjustable vector nozzle for wide-range hypersonic aircraft and internal-middle-outer three-ring adjustment scheme were designed. Numerical simula-tions were con-ducted on the nozzle under typical operating conditions, and the flow field structure and performance of the nozzle under different modes were analyzed. The results showed that by adjusting the position of the middle and out-er rings through translational motion, the nozzle can adjust the exit area and has thrust vectoring capability. In the non-thrust vectoring mode, due to the adjustable exit area of the nozzle, the overexpansion phenomenon under low nozzle pressure ratio conditions is effectively alleviated, and the thrust performance is significantly improved. Compared with fixed geometry nozzle, the thrust coefficient can be increased by up to 32.75%. In the thrust vectoring mode, vector angle at Mach 7 condition can generate more than 10°, while the thrust coefficient is still greater than 0.92. In order to further reduce the base drag of the nozzle under low Mach number conditions, a flow control method for secondary flow intake was proposed, which can reduce the base drag by up to 78.5% by reducing the internal and external pressure difference of the secondary flowpath. Finally, a wind tunnel scale-down experiment was conducted, and the experiment results were in good agreement with the numerical simulation results, verifying the effectiveness of the design scheme of adjustable vector nozzle for wide-range hypersonic aircraft.