公开(公告)号：US5482230A

公开(公告)日：1996-01-09

申请号：US083999

申请日：1993-06-25

Applicant: Michael S. Bird ,  Andreas Demopolous

Inventor： Michael S. Bird ,  Andreas Demopolous

IPC: B64C1/10 ,  B64D11/00 ,  B64D25/04 ,  B64C1/12

CPC classification number: B64D11/0023 ,  B64C1/10 ,  B64D2201/00

Abstract: A safety system for reducing the risk of injury during a survivable crash of a high-speed passenger vehicle. The safety system includes at least one bulkhead support base mounted to a vehicle within a passenger compartment and a bulkhead panel mounted to a portion of the bulkhead support base. In addition, the device includes energy-absorbing means associated with the bulkhead panel for absorbing the energy of a passenger impacting on the bulkhead panel. In this manner, the system minimizes injury to a passenger striking upon a bulkhead wall or class-divider wall within the vehicle. A triggering system is also provided for electronically activating the safety system when necessary.

Abstract translation: 一种安全系统，用于在高速乘用车遇难事故时降低受伤风险。 安全系统包括至少一个安装在乘客舱内的车辆上的舱壁支撑基座和安装在舱壁支撑座的一部分上的舱壁板。 此外，该装置包括与隔板面板相关联的能量吸收装置，用于吸收撞击在舱壁板上的乘客的能量。 以这种方式，该系统使撞击在车辆内的舱壁或分类器壁上的乘客的伤害最小化。 还提供触发系统，用于在必要时电子地激活安全系统。

公开(公告)号：US5340057A

公开(公告)日：1994-08-23

申请号：US850913

申请日：1992-03-13

Applicant: Hugh Schmittle

Inventor： Hugh Schmittle

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C29/02 ,  B64C3/385 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

Abstract: The VTOL aircraft includes a free wing having wings on opposite sides of the fuselage connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators, rudder and the differential pitch settings of the wings, respectively. At launch, the elevator pitches the fuselage nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing freely rotates relative to the fuselage into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and tile aircraft may be gently recovered in or on a resilient surface such as a net.

Abstract translation: 垂直起落架飞机包括一个自由翼，在机身的相对两侧具有彼此连接的翼，用于联合自由旋转，并在飞行员，计算机或遥控器下进行差距俯仰设置。 在垂直发射时，俯仰，偏航和侧倾控制分别由电梯，方向舵和翼的差距俯仰设置来实现。 在发射时，升降机将机身鼻部向下倾斜以改变推力矢量并向飞行器提供水平速度，由此自由翼相对于机身自由旋转成大致水平的方向以在水平飞行期间提供升力。 从水平飞行到垂直飞行的过渡是通过相反的过程实现的，瓦片飞机可以在诸如网络的弹性表面中或其上轻轻地回收。

公开(公告)号：US5211358A

公开(公告)日：1993-05-18

申请号：US699031

申请日：1991-05-13

Applicant: Cloy J. Bagley

Inventor： Cloy J. Bagley

IPC: B64C3/56 ,  F42B10/20

CPC classification number: F42B10/20 ,  B64D2201/00

Abstract: A deflated airbag is located on the outside of a missile or other vehicle beneath a folded, pivotally mounted airfoil member prior to launch, and a supply of pressurized gas is connected to the interior of the airbag via a suitable valve. After launch, or after lowering of a launch platform in the case of launch from an aircraft, an actuator such as an acceleration sensing device or timing device opens the valve, supplying gas to inflate the bag and simultaneously urge the airfoil into an extended, working position. After the airfoil is locked in its extended position, the airbag rapidly deflates and may be dropped off or retracted. Where more than one airfoil is to be deployed, separate airbags are located beneath each of the folded airfoils and a common gas supply is connected to all of the airbags.

Abstract translation: 放气的气囊位于导弹或其他车辆的外侧，在发射前在折叠的，可枢转地安装的翼型件下方，并且加压气体的供应通过合适的阀连接到气囊的内部。 在发射之后或在从飞行器发射的情况下降低发射平台之后，诸如加速度感测装置或定时装置的致动器打开阀，供应气体以使袋膨胀并且同时将翼型推进延伸的工作 位置。 在翼型件被锁定在其延伸位置之后，气囊迅速放气并且可能脱落或缩回。 在需要部署多于一个翼型件的情况下，每个折叠翼型件下方都有独立的安全气囊，并且公共气体源连接到所有安全气囊。

公开(公告)号：US4765569A

公开(公告)日：1988-08-23

申请号：US34911

申请日：1987-04-06

Applicant: Joseph M. Higgins

Inventor： Joseph M. Higgins

IPC: B60R21/00 ,  B60R21/16 ,  B60R21/261 ,  B60R21/276 ,  B64D25/02

CPC classification number: B60R21/16 ,  B60R21/26 ,  B64D25/02 ,  B60R2021/0093 ,  B60R2021/23153 ,  B60R2021/2615 ,  B64D2201/00

Abstract: The specification discloses a passive restraint system for high speed vehicles utilizing inflatable bags placed in the backs of the seats of the vehicle. The bags are connected by headers to a manifold which communicates with the exterior of the vehicle and, when open, allows air at high speed to enter and inflate the bags. A relief valve is provided in the cabin to open moments before the bags inflate to remove any danger of pressure shock from the rapid inflation of the bags and to, in some cases, aid in the inflation thereof. In some applications, an optional compressed air and/or compressed gas supply is also disclosed.

Abstract translation: 本说明书公开了一种用于高速车辆的被动约束系统，其利用放置在车辆的座椅后部的充气袋。 袋子通过集管连接到与车辆外部连通的歧管，并且当打开时允许高速空气进入并充气袋。 在舱室内设置安全阀，以在袋子充气之前打开时间，以消除袋子的快速膨胀造成的压力冲击的危险，并且在一些情况下有助于其膨胀。 在一些应用中，还公开了可选的压缩空气和/或压缩气体供应。

公开(公告)号：US4032088A

公开(公告)日：1977-06-28

申请号：US675004

申请日：1976-04-08

Applicant: John Jerome McAvoy

Inventor： John Jerome McAvoy

IPC: B60V3/08 ,  B64C39/02 ,  B64C25/56

CPC classification number: B60V3/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187 ,  B64D2201/00

Abstract: An air bag landing system for an aircraft. The landing system has an air bag assembly which is stored in the fuselage of the aircraft during cruise and which extends for landing. The assembly consists of a rigid arm with either two or three folding portions and an inflatable bag attached to the underside of the arm. The inflatable bag cushions the impact of the aircraft at landing. Actuators are provided to extend and retract the assembly.

Abstract translation: 飞机的气囊着陆系统。 着陆系统具有气囊组件，其在巡航期间存储在飞行器的机身中并且延伸以着陆。 该组件包括具有两个或三个折叠部分的刚性臂和附接到臂的下侧的可充气袋。 充气袋缓冲飞机在着陆时的冲击。 提供致动器以延伸和缩回组件。

公开(公告)号：US2964139A

公开(公告)日：1960-12-13

申请号：US65630457

申请日：1957-05-01

Applicant: GOODYEAR TIRE & RUBBER

Inventor： WITTL CASIMIR T ,  JENKINS FRANK J

IPC: B64D1/14

CPC classification number: B64D1/14 ,  B64D2201/00