固体火箭发射初期导流载荷特性数值研究

Numerical Study on the Characteristics of Diversion Load in the Initial Stage of Solid Rocket Launch

摘要

在固体火箭发射阶段，发动机喷管尾部喷出高温高速高压燃气，射流冲击导流器并产生随时间变化的导流载荷，从而实现射流定向偏转。为揭示该非定常流场在发射过程中的演化规律及其气动力学机制，基于计算流体力学理论并结合动网格技术，对发射筒约束条件下固体火箭后方冲击流场及后续自由射流场开展全过程数值模拟。对发射过程中经发射筒壁面反射后冲击流场特性进行了分析，对比近场不同距离、形状和尺寸导流结构的导流载荷的变化特点，并结合流场结构分析冲击载荷的响应规律及其成因。结果表明：在发射筒后方近场区域内，随着发射筒与导流结构相对距离逐渐增大，冲击载荷峰值强度变化较小，但各载荷峰值出现时刻明显提前。导流结构几何特性对载荷输出具有显著调节作用；在发射初期，锥形流场核心区前移使导流器载荷呈明显周期性波动，且随着发射过程推进，载荷峰值逐渐衰减。该研究揭示了复杂气动环境下导流器的受力机制，可为高性能发射导流系统的结构优化与载荷预测提供理论依据和数据支撑。

Abstract

During the launch phase of a solid rocket, high-temperature high-velocity high-pressure gas is ejected from the nozzle. The jet impinges on the deflector, generating time-varying loads to achieve the directional deflection of the jet. To reveal the evolution characteristics of this unsteady flow field during the launch process and its aerodynamic mechanism, a full-process numerical simulation of the impinging flow field behind the solid rocket under the constraint of the launch tube and the subsequent free-jet field was conducted based on computational fluid dynamics (CFD) and dynamic mesh techniques. The characteristics of the impinging flow-field reflected by the inner wall of the launch tube during the launch process were analyzed. The variations of the load of the deflector with different near-field distances, shapes and sizes were compared. Combined with the flow field structure, the response characteristics and causes of the impinging load were investigated. The results indicate that in the near-field region behind the launch tube, as the relative distance between the launch tube and the deflector gradually increases, the peak intensity of the impinging load decreases slightly, but the occurrence time of each load peak shifts significantly earlier. The geometric properties of the deflector structure have a significant influence on the load output. In the initial launch stage, the forward movement of the core region of the conical flow-field causes the load on the deflector to exhibit distinct periodic fluctuation characteristics. As the launch process proceeds, the load peak gradually attenuates. This study reveals the loading mechanisms of the deflector under complex aerodynamic environments, and can provide an important theoretical basis and data support for the structural optimization and load prediction of high-performance launch deflector systems.

关键词

固体火箭 / 射流流场 / 导流载荷 / 动网格

Key words

solid rocket / jet flow-field / deflector load / dynamic mesh

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