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公开(公告)号：US4431150A
公开(公告)日：1984-02-14
申请号：US371044
申请日：1982-04-23
摘要： A projectile body has a gyro mounted therein including a rotor and a mechanism for supporting the rotor for rotation about a spin axis initially coincident with the longitudinal axis of the projectile body and pivotable away from the longitudinal axis of the projectile body. The rotor is initially locked to the projectile body so that it is spun with the projectile body during launch. Thereafter, the rotor is unlocked and the projectile body is de-spun to a relatively slow rate of rotation while transferring angular momentum to the free spinning rotor which continues to rotate at a high rate relative to the projectile body. Rotationally phased steering commands, which are generated from on-board homing sensor signals or up-link data signals received from a remote error sensor, are applied to a linear actuator within the projectile body. The actuator pivots the spin axis of the rotor away from the longitudinal axis of the projectile body. The resulting precession torque of the spinning rotor induces a change in the angle of attack between the projectile body axis and the actual velocity vector of the projectile thereby inducing midcourse trajectory shaping.
摘要翻译： 抛射体具有安装在其中的陀螺仪，其包括转子和用于支撑转子的机构，所述旋转器围绕最初与射弹体的纵向轴线重合并且可远离射弹体的纵向轴线枢转的旋转轴旋转。 转子最初被锁定在射弹体上，使其在发射过程中与射弹体旋转。 此后，将转子解锁，并将射弹体旋转到相对较慢的旋转速度，同时将角动量传递到相对于射弹体以高速率继续旋转的自由旋转转子。 通过从远程误差传感器接收的车载归位传感器信号或上行链路数据信号产生的旋转相位转向命令被施加到射弹体内的线性致动器。 执行器使转子的旋转轴远离射弹体的纵向轴线。 旋转转子的进动转矩引起弹丸体轴线与射弹的实际速度矢量之间的迎角变化，从而引起中线轨迹整形。
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公开(公告)号：US5457471A
公开(公告)日：1995-10-10
申请号：US648433
申请日：1984-09-10
IPC分类号： H01Q1/42
CPC分类号： H01Q1/42
摘要： A radome useful with high-speed guided missiles has an inner conical shell made of a strong, high temperature resistant material transparent to radiant energy in the operative frequency range of a sensor mounted inside the shell. An outer ablative layer covers the exterior surface of the shell. This layer is made of a material which is also transparent to radiant energy in the sensor frequency range and which melts or sublimes and displaces from the shell at a predetermined elevated temperature and/or velocity during high-speed flight. The thickness of the ablative layer is selected so that it compensates for increased thickness and/or refraction resulting from thermal expansion of the shell, thereby minimizing guidance errors.
摘要翻译： 与高速导弹有用的天线罩具有内部锥形外壳，该外壳由安装在外壳内部的传感器的工作频率范围内透过耐辐射能的强耐高温材料制成。 外部烧蚀层覆盖壳体的外表面。 该层由对传感器频率范围内的辐射能透明的材料制成，并且在高速飞行期间以预定的升高的温度和/或速度从壳体中熔化或升华和移位。 选择可烧蚀层的厚度，以便补偿由壳体的热膨胀引起的厚度增加和/或折射，从而最小化引导误差。
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