公开(公告)号：US4593870A

公开(公告)日：1986-06-10

申请号：US530987

申请日：1983-09-09

申请人： James D. Cronkhite ,  Thomas J. Haas ,  Raymond W. Mort

发明人： James D. Cronkhite ,  Thomas J. Haas ,  Raymond W. Mort

IPC分类号： B64C1/06 ,  F16F7/12

CPC分类号： B64C1/068 ,  B64C1/062 ,  F16F7/12 ,  B64C27/04

摘要： An energy absorber is provided. The energy absorber includes a thin panel (78) formed of composite materials (84) for reacting compression forces in the plane of the panel (78) between two opposed edges thereof. The panel (78) is constructed to resist overall bending failure when force is applied to the opposite edges. The energy absorber further includes force receiving structure (90, 92) for receiving forces directly to one of the edges and for receiving forces to the opposite edge of the panel (78) to initiate local folding parallel to the other edge for progressing crushing and local folding of the panel (78).

摘要翻译： 提供能量吸收器。 能量吸收器包括由复合材料（84）形成的薄板（78），用于使面板（78）的平面内的压缩力在其两个相对的边缘之间进行反应。 面板（78）被构造为当力施加到相对边缘时抵抗整体弯曲故障。 所述能量吸收器还包括用于将力直接地接收到所述边缘中的一个边缘并且用于将力接收到所述面板（78）的相对边缘的力接收结构（90,92），以启动平行于另一边缘的局部折叠，以进行破碎和局部 折叠面板（78）。

公开(公告)号：US06394393B1

公开(公告)日：2002-05-28

申请号：US09648841

申请日：2000-08-25

申请人： Raymond W. Mort

发明人： Raymond W. Mort

IPC分类号： B64D1106

CPC分类号： B64D11/0619 ,  B64D11/06 ,  B64D11/0698

摘要： A crashworthy aircraft seat for protecting a passenger during a crash of the aircraft includes a support structure coupled to the aircraft, a seat assembly slidingly associated with the support structure, guide means coupled to the support structure for guiding upright members of the seat assembly as the seat assembly slides relative to the support structure, and means for variably attenuating kinetic energy as the seat assembly and the passenger move downward relative to the support structure from an initial static start position to an end position during the crash.

摘要翻译： 在飞机碰撞期间用于保护乘客的防撞飞机座椅包括联接到飞行器的支撑结构，与支撑结构滑动相关联的座椅组件，联接到支撑结构的引导装置，用于引导座椅组件的直立构件，作为 座椅组件相对于支撑结构滑动，以及用于当座椅组件和乘客在碰撞期间从初始静止起始位置到终止位置相对于支撑结构向下移动时可变地衰减动能的装置。

公开(公告)号：US06585190B2

公开(公告)日：2003-07-01

申请号：US10155445

申请日：2002-05-24

申请人： Raymond W. Mort

发明人： Raymond W. Mort

IPC分类号： B64D1106

CPC分类号： B64D11/0619 ,  B64D11/06 ,  B64D11/0698

摘要： A crashworthy aircraft seat for protecting a passenger during a crash of the aircraft includes a support structure coupled to the aircraft, a seat assembly slidingly associated with the support structure, guide means coupled to the support structure for guiding upright members of the seat assembly as the seat assembly slides relative to the support structure, and means for variably attenuating kinetic energy as the seat assembly and the passenger move downward relative to the support structure from an initial static start position to an end position during the crash.

公开(公告)号：US5398498A

公开(公告)日：1995-03-21

申请号：US239037

申请日：1994-05-06

申请人： Raymond W. Mort ,  James E. Goble

发明人： Raymond W. Mort ,  James E. Goble

IPC分类号： F02K9/38 ,  F42B15/36 ,  F02K1/16

CPC分类号： F42B15/36 ,  F02K9/38 ,  F05D2250/25

摘要： The joint construction is employed between a military rocket motor and a warhead adapted to be propelled by the motor. The motor includes a motor tube with a cylindrical front portion having an internal cylindrical surface therein. The warhead comprises an adapter ring having a cylindrical rear portion with an external cylindrical surface which is telescopically receivable within the internal cylindrical surface. The internal and external cylindrical surfaces are formed with respective confronting aligned internal and external helical screw thread grooves for receiving a fusible substantially helical joint member to form a secure connection between the rocket motor and the warhead. The helical joint member is made of a material having a low melting temperature, preferably a eutectic metal alloy, whereby the heat of a fire or the like will melt the joint member to disconnect the warhead from the rocket motor. The motor tube has a front wall with a vent opening therein, normally closed by a plug member. The adapter ring includes means for retaining the plug member in the vent opening. The melting of the fusible joint member is effective to release the retaining action of the adapter ring, whereby any pressure in the motor tube expels the plug member and the adapter ring from the motor tube.

摘要翻译： 联合结构用于军用火箭发动机和适于由电动机推动的弹头之间。 马达包括具有圆柱形前部的马达管，其内部具有圆柱形表面。 弹头包括具有圆柱形后部的适配环，其具有可伸缩地容纳在内部圆柱形表面内的外部圆柱形表面。 内部和外部圆柱形表面形成有各自相对的对齐的内部和外部螺旋螺纹槽，用于接收可熔的基本上螺旋形的接头构件，以在火箭发动机和弹头之间形成牢固的连接。 螺旋接头构件由具有低熔点的材料制成，优选为共晶金属合金，由此火等的热量将熔化接合构件以使弹头与火箭发动机断开连接。 马达管具有前壁，其中具有通气口，通常由塞构件封闭。 适配器环包括用于将插塞构件保持在通气口中的装置。 可熔接头构件的熔化有效地释放适配环的保持作用，由此马达管中的任何压力将塞子构件和适配环从马达管排出。

公开(公告)号：US5394803A

公开(公告)日：1995-03-07

申请号：US195126

申请日：1994-02-14

申请人： Raymond W. Mort

发明人： Raymond W. Mort

IPC分类号： F02K9/38 ,  F42B15/36 ,  F42B39/14

CPC分类号： F02K9/38 ,  F42B15/36

摘要： The joint construction comprises a coupling ring slidably received in a motor tube connected to the front end of the military rocket motor. The coupling ring is formed with longitudinal slots alternating with flexible fingers having locking projections engageable with a locking channel and an adjacent locking flange within the tube. An adapter ring is connected to the warhead by first screw threads and is adapted to be connected to the coupling ring by second screw threads including external threads on the adapter ring and internal threads in the coupling ring. The adapter ring has a reduced tapered end portion for receiving a wedging tapered expansion ring made of a eutectic metal alloy having a low melting point. As the second screw threads are engaged, the expansion ring flexes the fingers outwardly by a wedging action and causes the projections to interlock with the channel and the flange. If the joint construction is exposed to the heat of a fire or the like, the expansion ring melts and allows the fingers to spring inwardly whereby the projections are unlocked from the channel and the flange, so that the warhead is disconnected from the rocket motor before it is heated sufficiently to ignite the propellant charge therein.

摘要翻译： 接头结构包括可滑动地容纳在连接到军用火箭发动机的前端的马达管中的联接环。 联接环形成有纵向槽与柔性指状物交替，柔性指状物具有可与锁定通道和管内的相邻锁定凸缘接合的锁定突起。 适配环通过第一螺纹连接到弹头，并且适于通过第二螺纹连接到联接环，第二螺纹包括适配环上的外螺纹和联接环中的内螺纹。 接合环具有减小的锥形端部，用于接收由具有低熔点的共晶金属合金制成的楔形锥形膨胀环。 当第二螺纹接合时，膨胀环通过楔入动作向外弯曲指状物，并使突起与通道和法兰互锁。 如果接头结构暴露于火等的热量，则膨胀环熔化并允许指状物向内弹力，由此突起从通道和凸缘解锁，使得弹头在与火箭发动机之前断开 它被充分加热以点燃其中的推进剂电荷。