公开(公告)号：US06892981B2

公开(公告)日：2005-05-17

申请号：US10408981

申请日：2003-04-08

Applicant: Jay Lipeles

Inventor： Jay Lipeles

IPC: B64C3/30 ,  B64C3/56 ,  B64C39/02 ,  B64C39/10 ,  B64D33/04 ,  B64C39/00

CPC classification number: B64C39/024 ,  B64C3/30 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/105 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  B64C2201/22 ,  B64D33/04 ,  B64D2033/045

Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机（UAV）。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围，当放气以便于运输时，例如通过携带在行李箱中，成为小包装。 织物结构，具有冷却排气的小型内燃机和机翼翘曲控制相结合，使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制，这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的，并补充了稳定性增强。

公开(公告)号：US06474593B1

公开(公告)日：2002-11-05

申请号：US09733291

申请日：2000-12-08

Applicant: Jay Lipeles ,  R. Glenn Brosch

Inventor： Jay Lipeles ,  R. Glenn Brosch

IPC: F42B1000

CPC classification number: F42B10/62

Abstract: A projectile having a plurality of micro electromechanical (MEMS) devices disposed about the axis of flight for active control of the trajectory of the projectile. The MEMS devices each form an integral control surface/actuator. Control circuitry installed within the projectile housing includes both rotation and lateral acceleration sensors. Flap portions of the MEMS devices are extended into the air stream flowing over the projectile in response to the rate of rotation of the projectile, thereby forming a standing wave of flaps operable to impart a lateral force on the projectile. MEMS devices utilizing an electrostatically controllable rolling flap portion provide a large range of motion while consuming a small amount of power. The MEMS devices may be arranged in longitudinal strips along an ogive portion of the projectile. Packaging concepts for projectiles as small as a 30 caliber bullet are described.

Abstract translation: 具有围绕飞行轴设置的多个微机电（MEMS）装置的弹丸，用于主动控制射弹的轨迹。 MEMS器件各自形成一体的控制表面/致动器。 安装在射弹壳内的控制电路包括旋转和横向加速度传感器。 MEMS器件的翼片部分响应于弹丸的旋转速度而延伸到流过射弹的空气流中，从而形成可操作以在射弹上施加横向力的襟翼驻波。 利用静电可控制的襟翼部分的MEMS装置在消耗少量功率的同时提供大范围的运动。 MEMS器件可以沿着射弹的原始部分布置成纵向条带。 描述了小到30口径的弹丸的包装概念。

公开(公告)号：US20070032951A1

公开(公告)日：2007-02-08

申请号：US11279608

申请日：2006-04-13

Applicant: Martin Tanenhaus ,  Jay Lipeles

Inventor： Martin Tanenhaus ,  Jay Lipeles

IPC: G01C21/00

CPC classification number: G01C21/165 ,  G01C21/16 ,  G01C25/00

Abstract: A self-contained, integrated micro-cube-sized inertial measurement unit is provided wherein accuracy is achieved through the use of specifically oriented sensors, the orientation serving to substantially cancel noise and other first-order effects, and the use of a noise-reducing algorithm such as wavelet cascade denoising and an error correcting algorithm such as a Kalman filter embedded in a digital signal processor device. In a particular embodiment, a pair of three sets of angle rate sensors are orientable triaxially in opposite directions, wherein each set is mounted on a different sector of a base orientable normal to the other two and comprising N gyroscopes oriented at 360/N-degree increments, where N≧2. At least one accelerometer is included to provide triaxial data. Signals are output from the angle rate sensors and accelerometer for calculating a change in attitude, position, angular rate, acceleration, and/or velocity of the unit.

Abstract translation: 提供了一个独立的，集成的微立方体尺寸的惯性测量单元，其中通过使用特定定向的传感器实现精度，该取向用于基本上消除噪声和其它一级效应，以及使用降噪 诸如小波级联去噪的算法和嵌入在数字信号处理器设备中的卡尔曼滤波器等纠错算法。 在特定实施例中，一组三组角速度传感器可在相反的方向上三轴定向，其中每组安装在与其它两个法线垂直定向的基座的不同部分上，并且包括以360度/ N度取向的N个陀螺仪 增量，其中N> = 2。 包含至少一个加速度计以提供三轴数据。 信号从角速率传感器和加速度计输出，用于计算单元的姿态，位置，角速率，加速度和/或速度的变化。

公开(公告)号：US06422507B1

公开(公告)日：2002-07-23

申请号：US09608987

申请日：2000-06-30

Applicant: Jay Lipeles

Inventor： Jay Lipeles

IPC: F41G724

CPC classification number: F42B10/62 ,  F41G7/305

Abstract: A smart bullet capable of in-flight maneuvers generated by the selective extension of a spoiler from a de-spun control section of the bullet into the stream of air passing the bullet. A micro gyro located in the control section provides a rotation signal used in the control of a motor rotatably attached between the control section and a spinning section of the bullet. A rearward facing lens and optical detector receive guidance information from a gun-mounted guidance system. The direction of extension of the spoiler is selectively controlled by controlling the operation of the motor in response to the guidance information. The detector and pre-amplifier circuit are bonded to the lens structure to minimize microphonic noise generation. An optical link is used to communicate information between the spinning and control sections of the bullet.

Abstract translation: 能够通过将子弹的旋转控制部分选择性地延伸到通过子弹的空气流中产生的飞行中机动的智能子弹。 位于控制部分中的微型陀螺仪提供用于控制旋转地安装在控制部分和子弹的旋转部分之间的马达的旋转信号。 向后的镜头和光学检测器从枪装导向系统接收引导信息。 通过响应于引导信息控制电动机的操作来选择性地控制扰流板的延伸方向。 检测器和前置放大器电路结合到透镜结构以最小化麦克风噪声产生。 光链路用于在子弹的旋转和控制部分之间传送信息。