Ignition overpressure (IOP) is a principal dynamic load experienced by a launch vehicle during liftoff. The IOP arises due to the sudden ignition of the solid rocket boosters (SRBs) of a launch vehicle. The present work attempts to simulate the ignition of an SRB with an impulsively started supersonic $M_d=2.0$ jet generated using a quick-open valve. High-speed schlieren flow visualization is used to document the evolution of an impulsively started jet flowfield that included the characteristic precursor shock wave (that simulates the blast wave causing the IOP) and the following vortex ring. The dynamic interactions between the impulsively started supersonic jet and an established steady supersonic jet from another nozzle ($M_d=2.0$) in close proximity are also investigated. Both the precursor shock wave and the vortex ring interact strongly with the established steady-jet column as they proceed downstream from the nozzle exit, thereby introducing new sources of acoustic waves. When a generic jet blast deflector is introduced downstream of the nozzles, the precursor shock wave reflected from it, propagating upstream toward the nozzle exit. The reflected shock wave is recognized as the source of IOP experienced by the launch vehicle. The results show that the quick-open valve presents a unique way to generate impulsively started jets for understanding transients associated with the ignition of the SRB leading to the IOP, without the complexity associated with the use of open-ended shock tubes for carrying out such simulations.

点火超压 (IOP) 是运载火箭在升空过程中承受的主要动态载荷。IOP 是由于运载火箭的固体火箭助推器 (SRB) 突然点火而产生的。目前的工作试图用脉冲启动的超音速模拟 SRB 的点火。${米}_d=2.0$使用快开阀产生的射流。高速纹影流可视化用于记录脉冲启动射流流场的演变，其中包括特征前驱冲击波（模拟导致 IOP 的冲击波）和随后的涡环。脉冲启动的超音速射流与来自另一个喷嘴的已建立的稳定超音速射流之间的动态相互作用（${米}_d=2.0$) 附近也进行了调查。前体激波和涡环在从喷嘴出口向下游前进时与已建立的稳定射流柱强烈相互作用，从而引入新的声波源。当通用射流偏转器被引入喷嘴下游时，前驱激波从它反射，向上游传播到喷嘴出口。反射激波被认为是运载火箭所经历的眼压的来源。结果表明，快速打开的阀门提供了一种独特的方式来产生脉冲启动射流，以了解与导致 IOP 的 SRB 点火相关的瞬态，而没有与使用开放式冲击管进行此类操作相关的复杂性模拟。