保护罩开启时高速飞行器内流场建立过程分析

doi:10.7527/S1000-6893.2025.32638

Abstract

Abstract:

The“simultaneous separation”sequence， involving the concurrent unlocking of the booster and protective cover from an air-breathing hypersonic vehicle， facilitates axial separation by utilizing the pressurized gas filling of the internal flow path. However， during the initial separation phase under this sequence， complex and variable pressure oscillations arise within the vehicle’ s internal flow path due to the interaction of moving shock waves， shock trains， and gas filling. Beyond conventional collision risks， a potential overpressure risk from the gas filling process is introduced into this sequence. Numerical simulations of developing flow field within the vehicle’ s internal flow path during protective cover separation were carried out， using overset moving mesh technology and solving the unsteady Reynolds-Averaged Navier-Stokes （RANS） equations. The temporal flow field structures and unsteady pressure characteristics within the internal flow path were obtained. The evolution mechanism of the internal flow field during protective cover separation， as well as the influence mechanism between protective cover motion and stage distance variation on the flow field development during initial separation phase， were analyzed. The results indicate that during the initial separation phase under the“simultaneous separation”sequence， the filling and venting process of the internal flow path exhibits five distinct stages characterized by significantly different flow phenomena： gap-induced jet flow， moving shock sweep， shock train forward movement， gas backflow， and venting transition. The maximum pressure observed within the internal flow path during protective cover separation is primarily attributable to shock system pressurization， shock train pressurization， and gas filling pressurization/accumulation， rather than the pressure jump induced by the moving shock. The operational state of the internal flow path， whether started or unstarted， determines if the influence of cover motion and stage distance variation on the internal flow field manifests as a unidirectional dependency or a coupled interaction relationship.

Key words: protective cover, internal flow field, multi-body separation, gas filling, pressure characteristics, unsteady flow

CLC Number:

V239.2

Jun ZHONG, Xiaoqiang FAN, Bing XIONG, Lei CHEN, Xiao TANG. Internal flow field development process of a hypersonic vehicle during protective cover separation[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(8): 132638.

Figures/Tables 22

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流场区域	压升比	波后压力/kPa	压升原因
内压缩段和隔离段	2.02~4.25	99.8~123.9	上行运动激波扫掠
燃烧室	2.31~6.49	321.3~464.4	激波串前移
尾喷管	2.28~4.96	52.5~160.0	激波串前移
尾喷管出口	2.70~4.07	102.6~162.5	运动激波反射

流场区域		脉冲宽度/ms	最大压力峰值/kPa	静压比	最大压力来源
内压缩段		0.32~2.77	235~580	39.5~80.4	激波系增压（Ph3）
隔离段	第1组高压	11.72~12.12	268~300	37.1~41.5	激波系增压（Ph3）
隔离段	第2组高压	8.72~13.32	252~291	34.9~40.3	高压前传（Ph4）
燃烧室		15.34~18.11	53.2~64.3	53.2~64.3	激波串增压（Ph3）或高压前传（Ph4）
尾喷管		18.19~20.80	411~502	56.9~69.5	压力积蓄（Ph4）

Internal flow field development process of a hypersonic vehicle during protective cover separation

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