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1. 发明申请

WO2009116978A2 TORSIONAL SPRING AIDED CONTROL ACTUATOR FOR A ROLLING MISSILE 审中-公开
标题翻译：扭转弹簧控制执行器用于滚动故障
公开(公告)号：WO2009116978A2
公开(公告)日：2009-09-24
申请号：PCT/US2008013558
申请日：2008-12-10
申请人： RAYTHEON CO , SIRIMARCO SAMUEL D , VAN ZEE GERALD E
发明人： SIRIMARCO SAMUEL D , VAN ZEE GERALD E
IPC分类号： F42B15/01 , B63H25/00 , F42B19/01
CPC分类号： F42B10/64
摘要： A control actuator system. The novel system includes a control surface mounted on a body and adapted to move in a first direction relative to the body, and a first mechanism for storing energy as the control surface moves in the first direction and releasing the stored energy to move the control surface in a second direction opposite the first direction. In an illustrative embodiment, the system is adapted to rotate an aerodynamic control surface of a rolling missile, and the first mechanism is a torsional spring arranged such that rotating the control surface in the first direction winds up the spring and releasing the spring causes the control surface to oscillate back and forth, alternating between the first and second directions. In a preferred embodiment, the spring has a spring constant such that the control surface oscillates at a natural frequency matching a roll rate of the missile.
摘要翻译：控制执行器系统。所述新颖系统包括安装在主体上并适于相对于所述主体沿第一方向移动的控制表面，以及当所述控制表面沿着所述第一方向移动时储存能量的第一机构，并且释放所存储的能量以移动所述控制表面在与第一方向相反的第二方向上。在说明性实施例中，系统适于旋转滚动导弹的空气动力学控制表面，并且第一机构是扭转弹簧，其被布置成使得在第一方向上旋转控制表面向上弹起并释放弹簧使控制表面来回摆动，在第一和第二方向之间交替。在优选实施例中，弹簧具有弹簧常数，使得控制表面以与导弹的滚动速率相匹配的固有频率振荡。

2. 发明申请

WO2009116978A4 TORSIONAL SPRING AIDED CONTROL ACTUATOR FOR A ROLLING MISSILE 审中-公开
标题翻译：扭转弹簧控制执行器用于滚动故障
公开(公告)号：WO2009116978A4
公开(公告)日：2010-04-15
申请号：PCT/US2008013558
申请日：2008-12-10
申请人： RAYTHEON CO , SIRIMARCO SAMUEL D , VAN ZEE GERALD E
发明人： SIRIMARCO SAMUEL D , VAN ZEE GERALD E
IPC分类号： F42B10/06
CPC分类号： F42B10/64
摘要： A control actuator system. The novel system includes a control surface mounted on a body and adapted to move in a first direction relative to the body, and a first mechanism for storing energy as the control surface moves in the first direction and releasing the stored energy to move the control surface in a second direction opposite the first direction. In an illustrative embodiment, the system is adapted to rotate an aerodynamic control surface of a rolling missile, and the first mechanism is a torsional spring arranged such that rotating the control surface in the first direction winds up the spring and releasing the spring causes the control surface to oscillate back and forth, alternating between the first and second directions. In a preferred embodiment, the spring has a spring constant such that the control surface oscillates at a natural frequency matching a roll rate of the missile.
摘要翻译：控制执行器系统。所述新颖系统包括安装在主体上并适于相对于所述主体沿第一方向移动的控制表面，以及当所述控制表面沿着所述第一方向移动时储存能量的第一机构，并且释放所存储的能量以移动所述控制表面在与第一方向相反的第二方向上。在说明性实施例中，系统适于旋转滚动导弹的空气动力学控制表面，并且第一机构是扭转弹簧，其被布置成使得在第一方向上旋转控制表面弹簧弹簧并释放弹簧使控制表面来回摆动，在第一和第二方向之间交替。在优选实施例中，弹簧具有弹簧常数，使得控制表面以与导弹的滚动速率相匹配的固有频率振荡。

3. 发明申请

WO2009116978A3 TORSIONAL SPRING AIDED CONTROL ACTUATOR FOR A ROLLING MISSILE 审中-公开
公开(公告)号：WO2009116978A3
公开(公告)日：2009-09-24
申请号：PCT/US2008/013558
申请日：2008-12-10
申请人： RAYTHEON COMPANY , SIRIMARCO, Samuel, D. , VAN ZEE, Gerald, E.
发明人： SIRIMARCO, Samuel, D. , VAN ZEE, Gerald, E.
IPC分类号： F42B10/06
摘要： A control actuator system. The novel system includes a control surface mounted on a body and adapted to move in a first direction relative to the body, and a first mechanism for storing energy as the control surface moves in the first direction and releasing the stored energy to move the control surface in a second direction opposite the first direction. In an illustrative embodiment, the system is adapted to rotate an aerodynamic control surface of a rolling missile, and the first mechanism is a torsional spring arranged such that rotating the control surface in the first direction winds up the spring and releasing the spring causes the control surface to oscillate back and forth, alternating between the first and second directions. In a preferred embodiment, the spring has a spring constant such that the control surface oscillates at a natural frequency matching a roll rate of the missile.

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