Thrust random modulation numerical simulation for SRM

Zhang, Weihua; Guo, Jingjie; Xie, Liangbo; Zhang, G.; Jiao, Shi

doi:10.2514/6.1996-2596

Cited by 1 publication

(2 citation statements)

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“…Natan et al (1982) mainly investigated the influence of oxygen content in control flow and mass flow ratio of control flow to main flow on the modulation performance of vortex valve SRM with variable thrust. Zhang et al (1996) conducted theoretical research on the design parameters of vortex valve SRM with variable thrust, established a computational model, and obtained meaningful conclusions. Guo et al (1996) investigated how control flow, such as hightemperature combustion gas, nitrogen, and air, influences the modulation performance of vortex valve SRM with variable thrust and concluded that the modulation performance of high-temperature control flow is higher than that of low-temperature control flow.…”

Section: Introductionmentioning

confidence: 99%

“…Zhang et al (1996) conducted theoretical research on the design parameters of vortex valve SRM with variable thrust, established a computational model, and obtained meaningful conclusions. Guo et al (1996) investigated how control flow, such as hightemperature combustion gas, nitrogen, and air, influences the modulation performance of vortex valve SRM with variable thrust and concluded that the modulation performance of high-temperature control flow is higher than that of low-temperature control flow. Lin et al (2002) simulated the performances of two vortex valves by using CFL3D codes developed by NASA Langley Research Center; their results showed that the geometric shape of a vortex valve significantly influences on its modulation performance.…”

Section: Introductionmentioning

confidence: 99%

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Swirl Characteristics of Vortex Valve Variable-Thrust Solid Rocket Motor

Wei

2018

JAFM

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In accordance with the flow characteristics of vortex valve variable-thrust solid rocket motors, a cold flow experimental system based on Particle Image Velocimetry was established. A flow velocity vector diagram of vortex chamber was generated, and the vortex structure was analyzed. The results provided an experimental foundation for numerical simulation. The flow characteristics in vortex chamber and in the throat and divergent sections of the nozzle were modeled and simulated. The flow in the vortex chamber conformed to the complex Rankine vortex, and the flow field was divided into three different zones. The vortex core was the primary influence factor for thrust modulation. The resultant velocity reached Mach number 1 before gas arrived at nozzle throat, and the axial velocity still reached Mach number 1 at nozzle throat. Hence, the axial velocity can be used to judge the occurrence of choking at the nozzle throat. The intensity of swirl flow in divergent section of the nozzle was evidently lower than that in vortex chamber and throat. As a result, a lowpressure zone emerged around the central axis, thereby causing thrust losses.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%