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利用数值模拟方法,对二元喉道倾斜矢量喷管的调节方法进行了研究。研究结果表明,当喉道注气流量不变,随着扩张段注气流量逐渐增大,喷管内出现三种典型流动状态。当扩张段注气流量比较小时,喉道处声速线的形状和位置没有明显变化,在扩张段注气口前面形成亚声速区域;当喷管扩张段注气流量比较大时,喷管中出现了强激波系和上下贯通的亚声速区域,这时喷管内的流动损失最大,推力系数最低;进一步增大扩张段注气流量,声速线会从喷管喉道移动到喉道注气口和扩张段注气口之间,出现典型的喉道倾斜现象。单独控制流量系数可通过保持扩张段注气流量不变,改变喉道注气流量来实现;矢量角的控制可通过保持喉道注气流量不变,改变扩张段注气流量来实现。
Using numerical simulation method, the adjustment method of binary throat inclined vector nozzle was studied. The results show that when the flow rate of gas injected into the throat is constant, three kinds of typical flow conditions appear in the nozzle as the gas injection flow increases gradually. When the gas injection flow in the expansion section is relatively small, the shape and position of the sound velocity line at the throat do not change obviously, and the subsonic sound velocity area forms in front of the gas injection port in the expansion section. When the gas injection flow rate in the expansion section of the nozzle section is relatively large, Strong shock wave system and up and down through the sub-sonic zone, then the maximum loss of flow within the nozzle, the lowest coefficient of thrust; to further expand the expansion of gas injection flow, the sound velocity line from the nozzle throat move to the throat gas inlet and expansion Between the section gas injection port, a typical phenomenon of throat tilt. Independent control of flow coefficient can be achieved by maintaining constant injection gas flow in the expansion section and changing the injection flow of the throat. The control of the vector angle can be achieved by keeping the flow rate of the injection gas in the throat constant and changing the injection flow rate in the expansion section.