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1. 发明申请

US20110272521A1 FLIGHT UNIT CONTROL SYSTEM, FLIGHT CONTROL DEVICE INCLUDING SUCH A SYSTEM, AND USE OF SUCH A SYSTEM 有权
标题翻译：飞行单元控制系统，包括这种系统的飞行控制装置，以及这种系统的使用
公开(公告)号：US20110272521A1
公开(公告)日：2011-11-10
申请号：US13101369
申请日：2011-05-05
申请人： Franck Bouillot , Cédric Milord
发明人： Franck Bouillot , Cédric Milord
IPC分类号： B64C9/00 , B23P6/00 , F16B31/02 , B64C13/00 , B64C5/10
CPC分类号： B64C13/28 , B64C9/02 , Y10T29/4973
摘要： The present invention relates to a flight unit control system (S), comprising at least one instrumented fastening bolt (6) connecting an aircraft carrier structure (34) and a load path (36a, 36b), the instrumented bolt having at least one measurement area (61; 62) for detecting that the load path in under load. The system comprises fastening means (4, 11) capable of locking the instrumented bolt (6) in a position relative to the aircraft carrier structure (34) and to the load path (36). The or each measurement area (61; 62) of the instrumented bolt (6) comprises two cavities and at least one strain gauge. The fastening means (4, 11) comprise a fastening plate (4) which is positioned at a threaded end (6f) of the instrumented bolt (6), bearing against the aircraft carrier structure (34) or the load path (36), and which extends perpendicularly to the axis (X6) of the bolt (6), and a nut (11) which is placed at the threaded end (6f) of the instrumented bolt (6) and is capable of immobilizing the instrumented bolt (6) relative to the aircraft carrier structure (34) or the load path (36) against which the fastening plate (4) bears. The invention also relates to a flight control device, especially for an actuator of the THSA type, the secondary load path of which comprises such a system (S). Finally, the invention relates to the use of such a system (S) for replacing a pre-existing system.
摘要翻译：技术领域本发明涉及一种飞行单元控制系统（S），其包括连接航空母舰结构（34）和负载路径（36a，36b）的至少一个仪表式紧固螺栓（6），所述装置螺栓具有至少一个测量用于检测负载中的负载路径的区域（61; 62）。该系统包括能够将仪表化螺栓（6）相对于航空母舰结构（34）和负载路径（36）锁定的位置的紧固装置（4,11）。仪表式螺栓（6）的每个测量区域（61; 62）包括两个空腔和至少一个应变仪。紧固装置（4,11）包括紧固板（4），该固定板（4）定位在装备的螺栓（6）的螺纹端（6f）处，抵靠航空母舰结构（34）或负载路径（36）并且其垂直于所述螺栓（6）的轴线（X6）延伸，以及螺母（11），其被放置在所述装置螺栓（6）的螺纹端部（6f）处，并且能够固定所述装置螺栓（6））相对于航空母舰结构（34）或紧固板（4）所承载的载荷路径（36）。本发明还涉及一种飞行控制装置，特别是用于THSA型的致动器，其次级载荷路径包括这种系统（S）。最后，本发明涉及这种系统（S）用于替换预先存在的系统的用途。

2. 发明授权

US08820172B2 Flight unit control system, flight control device including such a system, and use of such a system 有权
标题翻译：飞行单位控制系统，包括这种系统的飞行控制装置，以及这种系统的使用
公开(公告)号：US08820172B2
公开(公告)日：2014-09-02
申请号：US13101369
申请日：2011-05-05
申请人： Franck Bouillot , Cédric Milord
发明人： Franck Bouillot , Cédric Milord
IPC分类号： F16B31/02 , B64C13/28 , B64C9/02
CPC分类号： B64C13/28 , B64C9/02 , Y10T29/4973
摘要： A flight unit control system having at least one instrumented fastening bolt connecting an aircraft carrier structure and a load path, the instrumented bolt having at least one measurement area for detecting that the load path is under load and including a fastener for locking the instrumented bolt in a position relative to the aircraft carrier structure and load path and wherein the measurement area has two cavities and at least one strain gauge and wherein the fastener includes a plate which is positioned at a threaded end of the instrumented bolt which bears against one of the aircraft carrier structure and the load path and which extends perpendicularly to an axis of the bolt and a nut which is placed at the threaded end of the instrumented bolt to immobilize the instrumented bolt relative to the aircraft structure or the load path.
摘要翻译：一种飞行单元控制系统，其具有连接航空母舰结构和负载路径的至少一个仪表式紧固螺栓，所述仪表螺栓具有至少一个测量区域，用于检测所述负载路径处于负载状态，并且包括用于将所述装置螺栓锁定的紧固件相对于航空母舰结构和载荷路径的位置，并且其中所述测量区域具有两个空腔和至少一个应变计，并且其中所述紧固件包括板，所述板位于所述仪表螺栓的螺纹端部，载体结构和载荷路径，并且其垂直于螺栓的轴线延伸，并且螺母被放置在仪表螺栓的螺纹端，以固定相对于飞机结构或载荷路径的仪表螺栓。

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