首页> 外文期刊>Aerospace science and technology >Numerical investigation of vented plume into a supersonic flow in the early stage of rocket hot separation
【24h】

Numerical investigation of vented plume into a supersonic flow in the early stage of rocket hot separation

机译:火箭热分离早期通风流入超声波流量的数值研究

获取原文
获取原文并翻译 | 示例
           

摘要

In the early stage of rocket hot separation, the vented plume from separation gap interacts with the supersonic incoming flow, causing lateral interference which affects separation safety and flight stability. In this work, steady interstage interference flow fields of a two-stage rocket in different incoming flow conditions (Mach number from 2.5 to 5.5, angle of attack from 0 degrees to 6 degrees, flight altitude from 16 Km to 24 Km) are numerically studied by the compressible Reynolds Averaged Navier-Stokes equations with SST turbulence model. An annular lateral jet is used to simulate the vented plume near the separation gap. Firstly, the interference flow fields with and without angle of attack are analyzed in detail to illustrate the interference mechanism of lateral jet. Then, the effects of flight altitude, jet total pressure, separation distance and free-stream Mach number on lateral jet interaction are investigated. With the increase of flight altitude, jet total pressure and separation distance, the upstream separation length and the pressure peak increase, and the peak position moves upstream. Nevertheless, with the increase of free stream Mach number, the upstream separation length is shortened, the pressure peak raises and the peak position shifts to the downstream. Besides, a combined parameter named momentum ratio is introduced to involve various factors, and the upstream separation length increases linearly with the momentum ratio when the momentum ratio is between 0.03 and 0.173. Finally, the influences of angle of attack on the disturbing force and moment of the upper stage are discussed. Numerical results indicate that the direction of the disturbing force is downward and the magnitude first rises and then falls with the angle of attack. The disturbing moment makes the upper stage have a tendency of subduction and increases with the angle of attack. (c) 2020 Elsevier Masson SAS. All rights reserved.
机译:在火箭热分离的早期阶段,来自分离间隙的通气羽流与超声波进入流动相互作用,导致影响分离安全和飞行稳定性的横向干扰。在这项工作中,在不同的传入流动条件下的两级火箭稳定的干扰流场(从2.5到5.5的马赫数,从0度到6度的攻角,从16公里到24km到24km的飞行高度)进行了数量研究由可压缩的雷诺斯平均具有SST湍流模型的Navier-Stokes方程。环形横向射流用于模拟分离间隙附近的排气羽流。首先,详细分析具有和不具有攻角的干扰流场,以说明横向射流的干涉机构。然后,研究了飞行高度,射流总压力,分离距离和自由流马赫数对横向喷射相互作用的影响。随着飞行高度的增加,喷射总压力和分离距离,上游分离长度和压力峰值增加,峰值位置上游移动。然而,随着自由流马赫数的增加,上游分离长度缩短,压力峰值升高,峰值位置偏移到下游。此外,引入了名为动量比的组合参数以涉及各种因素,并且当动量比在0.03和0.173之间时,上游分离长度随着动量比而导致线性增加。最后,讨论了攻击角度对上阶段的令人不安力和时刻的影响。数值结果表明,令人不安的力方向向下,幅度首先升高,然后随着攻角落下。令人不安的时刻使上阶段具有俯冲趋势并随着攻角增加而增加。 (c)2020 Elsevier Masson SAS。版权所有。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号