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首页> 外文期刊>SAMPE Journal >Composite Guidance Section Fuselage Trade Study and Prototype Overwrap Evaluation for a Supersonic, Air Breathing Threat Interceptor
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Composite Guidance Section Fuselage Trade Study and Prototype Overwrap Evaluation for a Supersonic, Air Breathing Threat Interceptor

机译：超声速呼吸威胁拦截器的复合制导段机身贸易研究和原型外包装评估

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A study has been made to modify an existing Sparrow Guidance Section (GS) for the Evolved Sea Sparrow Missile (ESSM). Sparrow is a legacy Air Intercept Missile (AIM) while the ESSM is an Air Breathing Threat (ABT) interceptor. The Sparrow GS Fuselage, an aluminum structure originally designed in the early 1970's for jet fighter air carriage, was evaluated for use in the ESSM flight loads and thermal environments. This paper summarizes the legacy research and trade studies performed that led to a recommended structural approach for the ESSM GS Fuselage design. The critical ESSM flight requirement driving the structural analysis was the terminal phase maneuver, occurring 5 to 10 seconds after rocket motor burn-out, when the airframe is experiencing maximum flight temperatures. The superposition of temperature and loading was not seen in the Sparrow environments. Due to the superposition of temperature and stress, severe degradation of an ESSM aluminum shell structure was predicted since the allowable stresses were reduced to a fraction of the values exhibited at room temperature. Five redesign options were identified to enable the GS Fuselage to withstand the new ABT interceptor flight requirements, but only three options were judged to be promising, given the launcher weight constraints for the surface-to-air configured missile. The first, low risk solution was to simply overwrap the aluminum GS Fuselage and Proximity Fuze Antennas with tape wound, quartz-reinforced bismaleimide (BMI) to serve as a thermal protection system (TPS), increasing cost and weight while degrading Fuze Antenna performance. The second solution proposed was to convert the GS Fuselage to titanium, assuming the weight and cost increase can be absorbed elsewhere within the ESSM vehicle. The third, more innovative, approach is to redesign the GS Fuselage with high temperature fiber-reinforced organic materials, incorporating the quartz/BMI TPS of the first option as the redesigned Fuze Antenna Radome. A BMI tape wound cylindrical airframe with titanium, or corrosion resistant steel (CRES), metal rings at the joint interfaces is a lower cost and lighter weight concept compared to the two previous, more traditional options. Weight and cost would be further reduced if the Fuze Antennas can be cocured into the GS composite laminate structure, minimizing fabrication process difficulties and inspection requirements. This study supports other Raytheon examinations into the applicability of high temperature composite materials for supersonic interceptor airframes because of their considerable advantages in weight reduction, manufacturing flexibility, performance enhancements, and lower cost.
机译：已经进行了一项研究，以修改现有的“进化的麻雀导弹”（ESSM）的麻雀制导部门（GS）。 Sparrow是传统的空中拦截导弹（AIM），而ESSM是空中呼吸威胁（ABT）拦截器。 Sparrow GS机身最初是在1970年代初期设计的，用于喷气式战斗机的铝制结构，经评估可用于ESSM飞行载荷和热环境。本文总结了传统研究和贸易研究，这些研究和研究为ESSM GS机身设计提供了建议的结构方法。进行结构分析的关键ESSM飞行要求是末期操纵，当飞机发动机处于最高飞行温度时，发生在火箭发动机烧尽后5到10秒。在麻雀的环境中看不到温度和负荷的叠加。由于温度和应力的叠加，可以预测ESSM铝壳结构会严重退化，因为允许应力降低到室温下显示的值的一部分。确定了五个重新设计的选项，以使GS机身能够承受新的ABT拦截器的飞行要求，但考虑到发射器对地空导弹的重量限制，只有三个选项被认为是有前途的。第一个低风险的解决方案是用带缠绕的石英增强双马来酰亚胺（BMI）简单包裹铝制GS机身和接近引信天线，以用作热保护系统（TPS），增加成本和重量，同时降低引信天线的性能。提出的第二个解决方案是将GS机身转换为钛，前提是重量和成本的增加可以吸收到ESSM车辆内的其他地方。第三种更具创新性的方法是使用高温纤维增强的有机材料重新设计GS机身，将首选的石英/ BMI TPS作为重新设计的引信天线天线罩。与前两个传统选项相比，BMI缠绕式圆柱形机身采用钛合金或耐腐蚀钢（CRES），在连接界面处具有金属环，是一种成本更低，重量更轻的概念。如果可以将引信天线共固化到GS复合层压板结构中，则重量和成本将进一步降低，从而最大程度地减少了制造过程中的困难和检查要求。这项研究支持雷神公司对高温复合材料在超音速拦截机机身中的适用性的其他研究，因为它们在减轻重量，制造灵活性，性能提高和成本降低方面具有相当大的优势。

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