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1. 发明申请

WO2005103600A3 MISSILE WITH MULTIPLE NOSECONES 审中-公开
标题翻译：与多个NOSECONES的MISSILE
公开(公告)号：WO2005103600A3
公开(公告)日：2005-12-08
申请号：PCT/US2004034567
申请日：2004-10-19
申请人： RAYTHEON CO , FACCIANO ANDREW B , MOORE ROBERT T , PARRY JAMES E , WHITE JOHN T
发明人： FACCIANO ANDREW B , MOORE ROBERT T , PARRY JAMES E , WHITE JOHN T
IPC分类号： F41G7/00 , F42B10/00 , F42B10/02 , F42B10/46
CPC分类号： F42B10/46
摘要： A missile (10) includes a payload assembly (16) that has a pair of nosecones (18, 20). The nosecones may be optimized for different environments and/or phases of flight, for example, having different shapes, different shell materials, different types of seals, and/or different separation mechanisms. The first (outer) nosecone (18) may have a more streamlined shape, be made of more thermally-protective material, and may meet less stringent sealing requirements, than the second (inner) nosecone (20). Separation of the outer nosecone from the payload assembly may cause backward movement of a center of pressure of the payload assembly, bringing the center of pressure of the assembly closer to a center of gravity of the assembly. This may make the payload assembly easier to maneuver, for example, reducing or eliminating the need for intervention by an attitude control system, to maintain the payload assembly on a desired course.
摘要翻译：导弹（10）包括有效载荷组件（16），所述有效载荷组件（16）具有一对旋转体（18,20）。对于不同的环境和/或飞行阶段，例如具有不同形状，不同的外壳材料，不同类型的密封件和/或不同的分离机构，可以优化鼻锥体。第一（外）鼻锥（18）可以具有更加流线型的形状，由更多的热保护材料制成，并且可以满足比第二（内）鼻锥（20）更不严格的密封要求。外部鼻锥与有效载荷组件的分离可能导致有效载荷组件的压力中心向后移动，使组件的压力中心更接近组件的重心。这可以使得有效负载组件更容易操纵，例如，减少或消除对姿态控制系统的干预的需要，以将有效负载组件保持在期望的过程上。

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