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本文叙述了有关战斧巡航导弹增强热塑性塑料弹翼的研究工作。现用弹翼(即基准弹翼)是由整体的枢轴装置、框架和粘合剂粘接的蒙皮构成。框架是由127mm、136.1kg重的铝合金板经机加工而成。蒙皮用的铝合金板经化学铣削到一定厚度,然后粘接到框架上。设计和研究表明,与基准弹翼相比,热塑性复合材料弹翼能使生产成本和重量降低,并能减少雷达散射截面。研究和分析指出,注模填充聚矾的框架及单向凯芙拉和玻璃-聚砜蒙皮是可行的设计方案,用上述材料制造的弹翼能够满足战斧导弹的要求。对粘合剂和粘接加紧固件进行了评价,并对分部件样品进行了试验。制造了三个全尺寸巡航导弹热塑性复合材料弹翼。第一个弹翼用作静力破坏试验;第二个弹翼用作疲劳试验(直到破坏为止);第三个弹翼用于测量雷达散射截面。试验结果和费用分析表明,热塑性复合材料弹翼是可行的制造方案,同时能使生产成本大大降低。
This article describes the research work on enhanced thermoplastic plastic wing of the Tomahawk cruise missile. The active wing (ie, the reference wing) consists of an integral pivot assembly, frame and adhesive-bonded skin. The frame is made of 127mm, 136.1kg heavy aluminum alloy plate. The skinned aluminum alloy plate is chemically milled to a certain thickness and then glued to the frame. Design and research have shown that thermoplastic composite wings can reduce production costs and weight and reduce radar cross sections compared to baseline wings. The research and analysis point out that the frame of injection molding polyolefins and one-way Kevlar and glass-polysulfone skin are feasible designs. The wing made of the above materials can meet the requirements of Tomahawk missiles. Adhesives and adhesive fasteners were evaluated and sub-part samples were tested. Three full-size cruise missile thermoplastic composite wings were manufactured. The first wing serves as a static failure test; the second wing serves as a fatigue test (until failure); and the third wing measures the radar cross section. Test results and cost analysis show that the thermoplastic composite wing is a viable manufacturing program, while enabling the production cost is greatly reduced.