制退器对尾翼稳定制导炮弹的炮口扰动研究

Study on Muzzle Disturbance of Tail-stabilized Guided Projectile With Muzzle Brake

摘要

摘要:尾翼稳定制导炮弹经过炮口制退器时，制退器内部复杂的冲击波流场与尾翼随机装填姿态相互作用，进而影响炮弹初始飞行稳定性。针对此问题，以四片尾翼稳定制导炮弹为研究对象，建立了带反作用式炮口制退器的三维非定常流场模型。通过数值模拟研究了尾翼稳定炮弹出炮口过程的流场特性及尾翼受力情况，分析了尾翼与制退器侧孔不同相对角度下的压力分布规律，并利用混沌多项式方法对炮口扰动进行了不确定性量化分析。研究结果表明，尾翼姿态导致炮口流场呈现非对称分布，随着尾翼与侧孔相对角度的增大，翼片径向压力梯度显著增加，受力呈现随机性；扰动力矩近似服从正态分布，均值约为 131N·m，导致弹丸出炮口产生约 0.011rad/s 的初始角速度；尾翼姿态引起的扰动具有较大的不确定性，设计时应充分考虑其对炮弹飞行稳定性的影响，研究结果可为尾翼稳定制导炮弹的设计提供技术支撑。

Abstract

Abstract:The interaction between the complex shock wave flow-field inside the muzzle brake and the random loading attitude of the tail fins affects the initial flight stability of tail-stabilized guided projectiles passing through the muzzle brake. Aiming at this problem, a four-fin tail-stabilized guided projectile was taken as the research object, and a three-dimensional unsteady flow-field model with a reaction-type muzzle brake was established. The flow field characteristics and tail fin forces during the projectile exiting the muzzle were studied through numerical simulation. The pressure distribution laws under different relative angles between the tail fins and the side holes of the brake were analyzed, and the uncertainty of the muzzle disturbance was quantitatively analyzed using the Polynomial Chaos (PC) method. The results show that the tail fin attitude leads to an asymmetric distribution of the muzzle flow field. As the relative angle between the tail fins and the side holes increases, the radial pressure gradient on the fins increases significantly, and the force exhibits randomness. The disturbance moment approximately follows normal distribution with a mean value of about 131N·m, resulting in an initial angular velocity of approximately 0.011rad/s as the projectile exits the muzzle. The disturbance caused by the tail fin attitude exhibits significant uncertainty, which should be fully considered in the design for its impact on flight stability. The research results can provide technical support for the design of tail-stabilized guided projectile.

关键词

关键词:制导炮弹 / 尾翼稳定 / 炮口扰动 / 流场分析 / 数值模拟

Key words

Keywords: guided projectile / tail-stabilization / muzzle disturbance / flow field analysis / numerical simulation

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