Rocket or Satellite Launch Vehicle's (SLV) Nose Cone Shape's Aerodynamic Drag Coefficients in Various Mach Numbers (Subsonic - Transonic - Supersonic) - PART 1

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.

火箭的鼻锥形状是通过将少量圆锥截面（一者为一）进行融合（两个圆锥截面结合）而生成的，并针对马赫数从亚音速至跨音速直至超声速的仿真条件进行了模拟。对于每种形状，针对每种马赫数，都记录了空气动力学阻力系数。自古以来，再入大气层、行星着陆和发射过程中的空气动力学阻力和加热问题一直备受关注。迄今为止，通过研究与实践，见证了从半球系列、椭圆、斜切和抛物线系列等用于太空运载火箭鼻锥设计的演变。本研究工作深入研究了亚音速、跨音速和超声速条件下，沿卫星运载火箭（SLV）飞行轨迹的空气动力学和热通量参数。文章的核心内容突出了其创新性，通过在CAD软件CATIA V5中的适当设计以及借助ANSYS平台上的Fluent方法进行的计算比较分析，探讨了诸如（i）混合形状鼻锥（将抛物线凹面、抛物线凸面、椭圆形和半球形进行融合与收缩）和（ii）刺状鼻锥等不同独特形状，并考虑了各自尺寸的变化。性能量化基准是基于SLV鼻锥形状在车辆不同速度范围内的空气动力学参数和热传导参数。定性的关系和结果将有助于原型设计的构建，以提供对SLV空气动力学阻力系数的控制/平衡。在需要快速轨道发射的情况下，锥形应穿透激波屏障以增加动量，而着陆情况下则需要阻力作为联盟，并采用更为钝的锥形。在任何运行条件下，车辆表面的传热不应显著，从鼻锥形状分析的角度来看，应提高这两个参数的最佳比例。本研究对于未来在操作中可转换的鼻锥具有重要意义，通过技术进步（例如形状记忆合金、机械传感器）来提高效率并增加由加热引起的车辆、乘员/宇航员/系统的安全性，以适应不断变化的周围环境。