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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >CHALLENGES IN SOLID BOOSTER SEPARATION DYNAMICS ANALYSIS FOR A WINGED BODY
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CHALLENGES IN SOLID BOOSTER SEPARATION DYNAMICS ANALYSIS FOR A WINGED BODY

机译：有翼飞机的固体提升动力学分析中的挑战

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摘要

The jettisoning of burnt solid rocket booster stage (HS9) from winged body configuration under hypersonic regime has been analyzed. The separation event takes place in the deceleration period of the vehicle i.e., aerodynamic drag is more dominating than the thrust generated by tail off phase of the solid booster. The separation environment in terms of dynamic pressure and Mach No are synthesized with all possibilities of HS9 stage performance and finalized the separation system requirement. The separation system realized should be able to take away separated HS9 stage sufficiently away from TDV stage as well as to avoid collision with TDV component such as rudder, hydraulic lines at the end of separation plane. A six-degree of freedom rigid body separation dynamics analysis has been carried out using the vehicle data and aerodynamic properties at the instant of separation. The aerodynamic coefficient data for HS9 stage is derived from wind tunnel test in Time March approach. The procedure for time march studies are described in detail in this paper. Also there are critical protrusions like hydraulic lines located around separation plane which are to be examined in detail during the pull out phase. It is to be ensured that separated HS9 stage does not collide with the protrusions at TDV aft end and vertical fin. This paper attempts to bring out the design and analysis efforts made during the separation of HS9 stage from winged body. Subsequently from the flight data analysis it is evidenced that the separation performance is normal and collision free.
机译：分析了高超声速条件下机翼构型对固体火箭助推器级（HS9）的抛射。分离事件发生在车辆的减速期间，即，空气阻力比固体助力器的尾部关闭阶段产生的推力更为主要。综合了动压和马赫数方面的分离环境以及HS9级性能的所有可能性，并最终确定了分离系统的要求。实现的分离系统应能够将分离的HS9级平台从TDV级平台上带走，并避免与TDV组件（例如，舵，分离平面末端的液压管路）发生碰撞。利用车辆数据和分离瞬间的空气动力学特性，进行了六自由度刚体分离动力学分析。 HS9阶段的空气动力学系数数据来自“时间行进”方法中的风洞测试。本文详细介绍了时间进行研究的过程。此外，在分离平面周围还有一些重要的突起，例如液压管路，在拔出阶段将对其进行详细检查。确保分离的HS9级不与TDV后端和垂直鳍片上的突起碰撞。本文试图带出HS9机翼与机翼分离过程中所做的设计和分析工作。随后从飞行数据分析中证明分离性能正常且无碰撞。

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  • 来源
    《Journal of Aerospace Sciences and Technologies》 |2017年第3a期|502-514|共13页
  • 作者

    R. Yuvaraj; K.K. Raveendra Babu; R. Saravanan; J.A. Tennyson; S. Subramanian; R. Kalimuthu; Sanjoy Kumar Sana; K. Suresh; B. Karthik; T. Sivamurugan; C. Ravikumar; Abhay Kumar;

  • 作者单位

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

    Vikram Sarabhai Space Centre (VSSC), ISRO Post Thiruvananthapuram-695 022, India;

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  • 正文语种 eng
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  • 关键词

    HS9 Stage; TDV Stage; Dynamics; Collision; Separation; Time March Approach; Protrusions;

    机译：HS9舞台;TDV舞台;动力学;碰撞;分离;时间行进法;突出物;

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