Scholarlink

<p>In modern warfare, the requirement for highly maneuverable military aircraft has made thrust vectoring a vital capability. Shock vector control (SVC) is an effective method in which shock waves are utilized to deflect the flow. Shock waves are formed by the injection of jets of secondary fluid through injection ports into the divergent section of a de-Laval nozzle. The pressure at the secondary injection port plays an important role in the performance of SVC. This study numerically investigates the effects of the secondary pressure ratio (SPR) and injection pressure ratio (IPR) on the thrust vectoring performance of SVC. Simulations are performed at SPR values of 0.35–1 and IPR values of 0.5–1.5, at a constant nozzle pressure ratio of 10. The flow properties are estimated by solving Navier–Stokes equations in conjunction with the realizable k–ε turbulence model. The study investigates flow behavior and shock wave patterns inside the nozzle with different injector configurations. A sudden rise in pressure is observed as the flow passes through the shock wave, followed by rapid pressure recovery. Increasing the SPR and IPR values increases the thrust vector angle and the peak pressure after the shock wave. Furthermore, the thrust coefficient decreases with rising SPR and IPR. Consequently, the greater thrust vectoring angles are associated with increased net thrust loss. The deflection efficacy factor changes quadratically with the thrust vector angle. Interestingly, it is deduced that the SVC technique is efficient when the thrust vector angle exceeds 6°.</p>

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Achieving Efficient Thrust Vectoring in Shock Vector Control: Investigating Secondary Fluid Injection Pressure for Single- and Dual-Injector Configurations

  • 期刊论文

  • 发表日期：

    2026年3月2日

查看全文
  • Shubham Yadav,
  • Srimayee Dastidar,
  • Kumar Gaurav

摘要

In modern warfare, the requirement for highly maneuverable military aircraft has made thrust vectoring a vital capability. Shock vector control (SVC) is an effective method in which shock waves are utilized to deflect the flow. Shock waves are formed by the injection of jets of secondary fluid through injection ports into the divergent section of a de-Laval nozzle. The pressure at the secondary injection port plays an important role in the performance of SVC. This study numerically investigates the effects of the secondary pressure ratio (SPR) and injection pressure ratio (IPR) on the thrust vectoring performance of SVC. Simulations are performed at SPR values of 0.35–1 and IPR values of 0.5–1.5, at a constant nozzle pressure ratio of 10. The flow properties are estimated by solving Navier–Stokes equations in conjunction with the realizable k–ε turbulence model. The study investigates flow behavior and shock wave patterns inside the nozzle with different injector configurations. A sudden rise in pressure is observed as the flow passes through the shock wave, followed by rapid pressure recovery. Increasing the SPR and IPR values increases the thrust vector angle and the peak pressure after the shock wave. Furthermore, the thrust coefficient decreases with rising SPR and IPR. Consequently, the greater thrust vectoring angles are associated with increased net thrust loss. The deflection efficacy factor changes quadratically with the thrust vector angle. Interestingly, it is deduced that the SVC technique is efficient when the thrust vector angle exceeds 6°.