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首页> 外文期刊>Journal of the Aeronautical Society of India >EFFECT OF AERODYNAMIC HEATING ON SEPARATION MECHANISM USED IN ROCKETS AND NEED OF THERMAL PROTECTION FOR SUCH STRUCTURES
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EFFECT OF AERODYNAMIC HEATING ON SEPARATION MECHANISM USED IN ROCKETS AND NEED OF THERMAL PROTECTION FOR SUCH STRUCTURES

机译：气动加热对火箭分离机理的影响以及此类结构的热防护需求

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摘要

During the ascent flight of a rocket, when the vehicle passes through the dense atmosphere, the outer skin of the structure is subjected to aerodynamic heating loads. Due to this heating load, the structure is heated and the strength of the structure deteriorates rapidly due to temperature rise of the structure. The structure needs to be thermally protected to restrict the temperature rise in order to maintain its structural integrity. However, in certain components of rockets, like in separation mechanism that is heated due to aerodynamic heating loads, the structure also needs thermal protection to minimize the large temperature gradients which if not controlled can result in thermal expansion and jamming of the separation system. Therefore it is very important to thermally protect such structures from aerodynamic heating to minimize the temperature gradients across the structure and avoid a likely mission failure. In this paper, a theoretical study is carried out to study the separation mechanism of a rocket which is subjected to aerodynamic heating. Methodology to estimate the aerodynamic heating using the actual flight trajectory of the rocket is also detailed. A 1-D approach is used to estimate the temperature rise of the joint using finite difference schemes. The joint is also idealised using a 2-D finite element mesh to carry out the thermal response analysis of the mechanism. Comparison of the results of the analysis shows that 2-D approach gives a realistic picture of the temperature, distribution across the separation mechanism compared to 1-D approach.
机译：在火箭升空过程中，当车辆经过浓密的大气层时，结构的外蒙皮会承受空气动力加热负荷。由于该热负荷，结​​构被加热，并且结构的强度由于结构的温度升高而迅速劣化。为了保持结构的完整性，需要对结构进行热保护以限制温度上升。但是，在火箭的某些组件中，例如在由于空气动力加热负荷而被加热的分离机构中，该结构还需要热保护以最小化较大的温度梯度，如果不加以控制，则可能导致分离系统的热膨胀和堵塞。因此，对此类结构进行热保护以免受到空气动力加热，以最小化整个结构的温度梯度并避免可能的任务失败，这一点非常重要。本文进行了理论研究，以研究受空气动力加热的火箭的分离机理。还详细介绍了使用火箭的实际飞行轨迹估算空气动力热量的方法。一维方法用于使用有限差分方案估算接头的温度升高。关节也可以使用二维有限元网格进行理想化，以进行机构的热响应分析。分析结果的比较表明，与一维方法相比，二维方法可真实显示温度，整个分离机理的分布。

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