发明名称 |
ROTATIONAL CANTED-JOINT MISSILE CONTROL SYSTEM |
摘要 |
The Rotational Canted-Joint Missile (RCJM) Control System utilizes a single or multiple body joints that rotate in planes that are not perpendicular to the missile body axis. The result is the deflection of a portion of the missile body for flight control purposes. The canted interface plane between any two adjacent movable sections of the missile body and a joint at the interface plane that allows one of the sections to be rotated by a pre-determined angle with respect to the other section comprise a rotational plane mechanism that offers an inclined bearing plane with a large mechanical advantage over typical "brute force" ball joint methods.
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申请公布号 |
US2003160129(A1) |
申请公布日期 |
2003.08.28 |
申请号 |
US20020083518 |
申请日期 |
2002.02.25 |
申请人 |
BERRY ROGER P.;LAWLESS DANIEL F.;CAYSON STEPHEN C.;AUMAN LAMAR M.;DUNAWAY J. C.;DIXON MARK D.;GIBSON DAVID A. |
发明人 |
BERRY ROGER P.;LAWLESS DANIEL F.;CAYSON STEPHEN C.;AUMAN LAMAR M.;DUNAWAY J. C.;DIXON MARK D.;GIBSON DAVID A. |
分类号 |
F41G7/22;F42B15/01;(IPC1-7):F41G7/00;F42B15/10;F42B15/20;F42B15/22 |
主分类号 |
F41G7/22 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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