公开(公告)号：US20070023568A1

公开(公告)日：2007-02-01

申请号：US11139483

申请日：2005-05-31

Applicant: Hanan Rom

Inventor： Hanan Rom

IPC: B64C3/38

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/182 ,  B64F1/02

Abstract: A system for slowing an air vehicle, including an independently supported aerodynamic drag device designed so that, after contact is made between the flying air vehicle and the aerodynamic drag device, one or more parts of the aerodynamic drag device are carried along by the air vehicle thereby decelerating the air vehicle, so that a majority of a kinetic energy dissipation of a combination of the air vehicle and the aerodynamic drag device is due to an aerodynamic drag of the aerodynamic drag device

Abstract translation: 一种用于减速飞行器的系统，包括独立支撑的气动阻力装置，其设计成使得在飞行空气车辆与空气动力学牵引装置接触之后，空气动力拖曳装置的一个或多个部分由机动车辆 从而使空中车辆减速，使得空中车辆和空气阻力装置的组合的大部分动能耗散是由于气动阻力装置的空气动力学阻力

公开(公告)号：US06297486B1

公开(公告)日：2001-10-02

申请号：US08946978

申请日：1997-10-08

Applicant: Hanan Rom ,  Zvi Weinberg

Inventor： Hanan Rom ,  Zvi Weinberg

IPC: F42B1034

CPC classification number: F42B10/44

Abstract: A device for reducing base drag on cylindrical rear truncated objects moving in a fluid, caused by the shedding of vortices at the base of the object. The device consists of ring shaped winglets attached to the rear of the object which may be sub-divided into a plurality of hinged partial winglets. The parameters of distance of winglet from cylinder shaped object, winglet circumference, angle, profile and chord length may be varied automatically for optimum drag-reducing capability.

Abstract translation: 用于减少在流体中移动的圆柱形后截面物体上的基底阻力的装置，其由物体底部的涡流脱落引起。 该装置由附接到物体后部的环形小翼片组成，其可分为多个铰接的部分小翼。 从圆柱形物体，小翼圆周，角度，轮廓和弦长度的小翼距离的参数可以自动变化，以获得最佳的减阻能力。

公开(公告)号：US5326049A

公开(公告)日：1994-07-05

申请号：US3045

申请日：1993-01-11

Applicant: Hanan Rom ,  Oded Yehezkeli

Inventor： Hanan Rom ,  Oded Yehezkeli

IPC: F42B10/14

CPC classification number: F42B10/14 ,  Y10S343/02

Abstract: A device, particularly a missile, includes a body having an appendage, e.g., a wing, normally folded in an inoperative position and to be unfolded to an operative position when the body is accelerated in the direction of the longitudinal axis of the body. The appendage is pivotally mounted about a first pivot axis extending perpendicularly to the longitudinal axis of the body, and also about a second pivot axis extending parallel to the longitudinal axis of the body. The center of gravity of the appendage is outwardly of the first pivot axis in the folded condition of the appendage such that the acceleration of the body produces a moment pivotting the appendage about the first pivot axis.

Abstract translation: 一种装置，特别是导弹，包括具有附件的主体，例如机翼，其通常折叠在不工作的位置，并且当主体沿着身体的纵向轴线的方向被加速时展开到操作位置。 附件围绕垂直于主体的纵向轴线延伸的第一枢转轴线枢转地安装，并且还围绕平行于主体的纵向轴线延伸的第二枢转轴线枢转地安装。 在附件的折叠状态下，附件的重心在第一枢转轴线的外侧，使得身体的加速度产生使附件围绕第一枢转轴线枢转的力矩。

公开(公告)号：US07611094B2

公开(公告)日：2009-11-03

申请号：US11139483

申请日：2005-05-31

Applicant: Hanan Rom

Inventor： Hanan Rom

IPC: B64F1/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/182 ,  B64F1/02

Abstract: A system for slowing an air vehicle, including an independently supported aerodynamic drag device designed so that, after contact is made between the flying air vehicle and the aerodynamic drag device, one or more parts of the aerodynamic drag device are carried along by the air vehicle thereby decelerating the air vehicle, so that a majority of a kinetic energy dissipation of a combination of the air vehicle and the aerodynamic drag device is due to an aerodynamic drag of the aerodynamic drag device.

Abstract translation: 一种用于减速飞行器的系统，包括独立支撑的气动阻力装置，其设计成使得在飞行空气车辆与空气动力学牵引装置接触之后，空气动力拖曳装置的一个或多个部分由机动车辆 从而使空中车辆减速，使得空中车辆和空气动力学牵引装置的组合的大部分动能耗散是由于空气阻力装置的气动阻力。

公开(公告)号：US06209820B1

公开(公告)日：2001-04-03

申请号：US09356986

申请日：1999-07-19

Applicant: Oded M. Golan ,  Hanan Rom ,  Oded Yehezkely

Inventor： Oded M. Golan ,  Hanan Rom ,  Oded Yehezkely

IPC: F41G722

CPC classification number: F41G7/34 ,  F41G7/2206

Abstract: A system for intercepting targets having predictable flight trajectory, the system comprising a platform carrying an interceptor missile which includes a seeker unit, propulsion system steering system and destruction capability system, all communicating with a processor device. The processor device is further coupled to a data link for communicating with the platform. In response to launching of the intercepting missile, the processor device controls the steering system and propulsion system for steering the missile in one of the following flight modes: (a) approach mode, wherein said intercepting missile closes on said target; (b) trajectory matching mode wherein the interceptor velocity vector is modified to bring the trajectory of the interceptor to match the predicted trajectory of the target so that the interceptor moves in the same direction as the target in a relatively small closing velocity with respect to the target; and (c) end game mode wherein the interceptor is maneuvered to a distance sufficiently close to the target whereby the target destruction capability can be activated efficiently.

Abstract translation: 一种用于拦截具有可预测的飞行轨迹的目标的系统，该系统包括承载拦截器导弹的平台，该拦截器导弹包括与处理器装置通信的寻求者单元，推进系统转向系统和破坏能力系统。 处理器设备进一步耦合到用于与平台通信的数据链路。 为了响应拦截导弹的发射，处理器装置控制用于以下列飞行模式之一转向导弹的转向系统和推进系统：（a）接近模式，其中所述拦截导弹在所述目标上关闭; （b）轨迹匹配模式，其中拦截器速度矢量被修改以使得拦截器的轨迹与目标的预测轨迹相匹配，使得拦截器以相对于目标的相对方向相对于相对小的关闭速度相对于目标移动 目标; 和（c）结束游戏模式，其中拦截器被操纵到足够靠近目标的距离，从而可以有效地激活目标破坏能力。