Rocket or Satellite Launch Vehicle's (SLV) Nose Cone Shape's Aerodynamic Drag Coefficients in Various Mach Numbers (Subsonic - Transonic - Supersonic) - PART 1
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The rocket nose-cone shapes have been generated by blending few conic sections together (two conic sections in one) and the simulated against mach number regime from subsonic through transonic to supersonic. The aerodynamic drag coefficients have been recoded for each shape for each mach number.Since ages, aerodynamic drag and heating in re-entering, planetary landing and launching has been a point of major concern. Thus far, witnessing through studies and practicality shown the evolution of usages from hemispherical series, ellipse, hack and ogive series for space launch vehicle nose design. This research work comprises of study of aerodynamic and heat flux parameters intensively in subsonic, transonic and supersonic regimes that’s along a journey of a SLV. Crux of the article highlights its novelty through proper design in CAD software CATIA V5 and computational comparative analysis with the aid of ANSYS platform on Fluent method, of various unique nose cone shapes such as (i) blended shape nose cones (blending and tapering the combination of parabolic concave, parabolic convex, elliptic and hemispherical) and (ii) spiked nose cones, with variation in individual sizes. The basis of performance quantification has been taken in terms of aerodynamic parameters and heat conduction parameters for SLV’s nose cone shape along the varying speed range of the vehicle. The qualitative relations and results would facilitate in prototyping possible design to provide the control/balance of both aerodynamic drag coefficient for SLV. In case of required fast orbital launching the shape of cone should be penetrating the shock barrier to gain an increase rate of momentum, in contrast the landing case requires the drag as alliance and a much blunt cone would be used. In any operating condition, the heat transfer to the surface of vehicle shouldn’t be significant, through the aspect of nose shape analysis optimum proportion of both parameters would be upraised. This study would mostly useful for in-operation convertible nosecones in future via technological advancements(e.g shape memory alloy, mechanical sensors) for enhancing efficiency and increasing safety of vehicle, crew/astronauts/systems from heating by adapting the shape required for varying surrounding conditions.
本数据集涵盖的火箭鼻锥外形通过将多个圆锥截面融合生成（典型为双截面融合），并在覆盖亚声速（subsonic）、跨声速（transonic）至超声速（supersonic）的全马赫数工况下开展仿真验证。针对每种鼻锥外形，各马赫数下的气动阻力系数（aerodynamic drag coefficient）均已记录存档。 长期以来，航天器再入、行星着陆与发射过程中的气动阻力与热载荷始终是行业核心关注问题。迄今为止，通过研究与工程实践可知，航天运载火箭（SLV，Space Launch Vehicle）鼻锥设计已历经半球型、椭圆型、截尖型与卵形等系列外形的迭代演进。 本研究针对航天运载火箭全飞行工况下的亚声速、跨声速与超声速区间，深入开展气动参数与热流参数（heat flux parameter）的研究分析。本文核心亮点在于其创新性：通过CATIA V5 CAD软件完成精准外形设计，并依托ANSYS平台的Fluent求解器开展多组独特鼻锥外形的计算对比分析，所涉外形包括：(i) 融合型鼻锥（将凹抛物面、凸抛物面、椭圆面与半球面进行融合与锥度渐变组合）；(ii) 尖头型鼻锥，且各外形均存在尺寸参数变化。 本研究以航天运载火箭鼻锥外形在全速度区间内的气动参数与热传导参数作为性能量化依据。若需快速入轨发射，鼻锥外形需突破激波屏障以提升动量增益速率；而着陆工况则需借助气动阻力，因此需采用钝头型鼻锥。在任何运行工况下，飞行器表面的热传递均需控制在合理范围内，通过鼻锥外形优化分析，可实现两类参数的最优平衡。 本研究成果可助力未来基于技术迭代（如形状记忆合金（shape memory alloy）、机械传感器（mechanical sensors））的可在轨变形鼻锥研发，通过适配不同外部环境所需的外形，提升飞行器运行效率，同时保障乘员、宇航员与系统免受热载荷威胁，增强飞行安全性。
