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公开(公告)号：US20140028486A1
公开(公告)日：2014-01-30
申请号：US13607739
申请日：2012-09-09
Applicant: Pascal CORNIC , Patrick GARREC , Jean-Paul ARTIS
Inventor： Pascal CORNIC , Patrick GARREC , Jean-Paul ARTIS
IPC: G01S5/02
CPC classification number: G01S5/0247 , F41G7/301 , F41G7/305 , G01S1/14
Abstract: A location and guidance system including a flying craft and a reception device. The flying craft includes a plurality of antennas distributed around its fuselage and emitting rearwards with rectilinear polarization, the emitted signals being specific to each antenna, the positions and the dimensions of the antennas being configured such that the body of the flying craft avoids by masking for at least one antenna the reflections of the signal emitted by this antenna off the ground or off lateral obstacles whatever the position of the flying craft. The reception device is placed substantially on a trajectory axis of the flying craft and configured to be oriented to sight the rear thereof and includes at least two single-pulse antennas operating in orthogonal planes determines a position of the flying craft by analysing the emitted signals received by the antennas of the reception device.
Abstract translation: 包括飞行器和接收装置的位置和引导系统。 飞行器包括分布在其机身周围并以直线偏振向后发射的多个天线，所发射的信号是特定于每个天线的，天线的位置和尺寸被配置为使得飞行器的主体通过屏蔽来避免 至少有一个天线，由天线发射的信号离开地面或侧向障碍物的反射，无论飞行器的位置如何。 接收装置基本上放置在飞行器的轨迹轴上并且被配置为朝向其后方瞄准，并且包括在正交平面中操作的至少两个单脉冲天线通过分析所接收到的发射信号来确定飞行器的位置 通过接收设备的天线。
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公开(公告)号：US20050174559A1
公开(公告)日：2005-08-11
申请号：US10516538
申请日：2003-12-09
Applicant: Bernard Teneze , Frank Bernoux
Inventor： Bernard Teneze , Frank Bernoux
CPC classification number: F41G7/301 , H04B10/1121
Abstract: The invention concerns a method and a device for producing an optical link with laser pulses for locating a mobile. The invention is characterized in that it consists in varying the energy of said successive laser pulses (4) as an increasing function of the time (t) elapsing from the start of the emission of said laser pulses more or less in the direction of said receiver. The start of the emission of said laser impulse is delayed relative to the start of the mobile.
Abstract translation: 本发明涉及用于产生具有用于定位移动台的激光脉冲的光学链路的方法和装置。 本发明的特征在于它包括随着从所述接收器的方向上发射所述激光脉冲的开始或多或少地开始的时间（t）的增加函数，改变所述连续激光脉冲（4）的能量 。 所述激光脉冲的发射开始相对于移动台的开始而延迟。
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公开(公告)号：US06845938B2
公开(公告)日：2005-01-25
申请号：US09955151
申请日：2001-09-19
Applicant: Randall J. Muravez
Inventor： Randall J. Muravez
IPC: F41G7/00
CPC classification number: F41G7/301 , F41G7/2213 , F41G7/2286 , G05D1/12
Abstract: A system and method that guides a device to an object using periodically adaptive guidance. The guidance and control system creates a reconstructed line-of-sight (LOS) vector to avoid system destabilization associated with small angle approximation during high bore sight engagements. The guidance system adaptively estimates the periodic maneuver of evasive objects with a set of harmonically balance Kalman filter banks. The Harmonically Balanced Kalman filter banks generate a set of probabilities that weight the effect of each individual Kalman filters on a resultant guidance command signal. The guidance command signal generated by the system acts perpendicular to the object LOS. The guidance and control system uses vectored proportional navigation guidance laws, optimal proportion navigation laws and periodically adaptive augmented guidance laws to generate a guidance command signal to supply to an autopilot.
Abstract translation: 使用周期性自适应指导将设备引导到对象的系统和方法。 引导和控制系统创建重建的视线（LOS）矢量，以避免在高视野接合期间与小角度近似相关的系统不稳定性。 引导系统通过一套谐波平衡卡尔曼滤波器组自适应地估计回避物体的周期性动作。 谐波平衡卡尔曼滤波器组产生一组概率，其对每个单独的卡尔曼滤波器对结果指导命令信号的影响进行加权。 由系统产生的指导指令信号垂直于对象LOS。 指导和控制系统采用矢量比例导航法，最优比例导航法和周期性适应性增强指导法，生成指导信号供给自动驾驶仪。
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公开(公告)号：US6142410A
公开(公告)日：2000-11-07
申请号：US166184
申请日：1998-10-05
Applicant: Frederic Naccache
Inventor： Frederic Naccache
Abstract: A device for guiding an aircraft includes an image sensor mounted on the aircraft, a data transmission unit for transmitting the images provided by the image sensor, a guide station for receiving the images which includes a touch-sensitive screen for displaying the images sensed by the image sensor. The touch-sensitive screen permits touch selection of a guide point representing a specific location displayed on the screen to which the aircraft is guided. A calculating unit calculates the instructions to guide the aircraft to the area represented by the guide point. The touch sensitive screen can include a light pen for selection of the guide point.
Abstract translation: 用于引导飞行器的装置包括安装在飞机上的图像传感器，用于传输由图像传感器提供的图像的数据传输单元，用于接收图像的引导站，所述导向站包括用于显示由 图像传感器。 触摸屏幕允许触摸选择指示点，其指示飞机被引导到的屏幕上显示的特定位置。 计算单元计算用于将飞行器引导到由引导点表示的区域的指令。 触敏屏幕可以包括用于选择引导点的光笔。
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5.发明授权
公开(公告)号：US5722614A
公开(公告)日：1998-03-03
申请号：US741035
申请日：1996-10-30
Applicant: Dallas C. Wicke
Inventor： Dallas C. Wicke
CPC classification number: F41G7/301
Abstract: A method and system for limiting missile guidance correction within the physical control capabilities of the missile, while fully utilizing missile maneuver and control capabilities. The method and system of the present invention are applied through missile guidance control electronics. First, a dynamic rate limit is calculated to prevent aerodynamic trim limit overshoot, which is directly related to body attitude rate. Second, a dynamic angle of attack limit is calculated to control aerodynamic trim limit based on thrust deflection and/or aerodynamic control surface deflection. Third, a dynamic angular acceleration limit is calculated to balance control moments produced by mechanisms such as thrust deflection and/or aerodynamic control surface deflection with vehicle moments of inertia. Fourth, the dynamic limit on rate of change of angular acceleration is set to maintain control system margins in terms of maximum enforceable moment in excess of the trim moment at the current angle of attack and maximum slew rate of the thrust deflector.
Abstract translation: 在导弹的物理控制能力范围内限制导弹引导修正的方法和系统，同时充分利用导弹的机动和控制能力。 本发明的方法和系统通过导弹引导控制电子装置应用。 首先，计算动态速率限制，以防止空气动力学修整极限过冲，这与身体姿态速率直接相关。 第二，计算动态的攻角限制，以根据推力偏转和/或空气动力学控制表面偏转来控制空气动力学修正极限。 第三，计算动态角加速度极限以平衡由诸如推力偏转和/或空气动力学控制表面偏转的机构产生的控制力矩与车辆惯性矩。 第四，设定角加速度变化率的动态极限，以便在最大可执行力矩范围内保持控制系统的裕度超过目前的迎角和推力偏转器的最大转换速度。
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Patent Agency Ranking6.发明授权
公开(公告)号：US5106033A
公开(公告)日：1992-04-21
申请号：US673619
申请日：1991-03-22
Applicant: Dzung V. Phan
Inventor： Dzung V. Phan
Abstract: A tube-launched, optically-tracked, wire guided (TOW) portable guided missile system (10) includes a launch tube (16) mounted on a tripod (18) or vehicle, and an optical/thermal sighting and tracking assembly (22) mounted on and aligned with the launch tube (16). The system operator (20) mechanically trains the assembly (22) to maintain a target (38) visually centered in a reticle, thereby establishing a line-of-sight (40) to the target (38). The assembly (22) tracks the target (38) optically or thermally, and feeds guidance signals to the missile (14) through a wire (46) to maintain the missile flight path coincident with the line-of-sight (40). An improved missile guidance electronics unit (44) is environmentally sealed in a small housing (60) which removably fits into a compartment (52) in the sighting and tracking assembly (22), thereby enabling the optical/thermal sighting and tracking elements (26,28) and guidance electronics (88) to be integrated into a compact, unitary assembly (22).
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公开(公告)号：US4149166A
公开(公告)日：1979-04-10
申请号：US108960
申请日：1961-05-09
Applicant: Fay E. Null
Inventor： Fay E. Null
Abstract: 1. A Doppler decoy protection device comprising a missile capable of being launched from a space craft whose protection is sought, and to travel in advance thereof and at a speed greater than the speed of said space craft, guide means extendable rearwardly from said missile, Doppler decoy means slidable on said guide means for simulating the Doppler characteristics of the craft whose protection is sought, means for damping the speed of travel of said decoy means rearwardly on said guide means so that the resultant forward speed of said decoy means will substantially equal the speed of the craft whose protection is sought.
Abstract translation: 1.一种多普勒诱饵保护装置，包括能够从寻求保护的太空飞船发射的导弹，并且以比所述太空飞船的速度大的速度行进导弹，导弹装置可从所述导弹向后延伸， 多普勒诱饵装置可在所述引导装置上滑动，用于模拟寻求保护的飞行器的多普勒特性，用于在所述引导装置上向后阻尼所述诱饵装置的行进速度的装置，使得所述诱饵装置的合成前进速度将基本相等 需要保护的工艺的速度。
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8.发明授权Feedback PDM encoder and method for actuating a pneumatic actuator with a digital autopilot 失效反馈PDM编码器和用于启动具有数字自动驾驶仪的气动执行器的方法
公开(公告)号：US4033525A
公开(公告)日：1977-07-05
申请号：US638476
申请日：1975-12-08
Applicant: John P. Leonard , Robert E. Yates
Inventor： John P. Leonard , Robert E. Yates
CPC classification number: F41G7/301 , G05D1/0202 , G05D3/18
Abstract: A feedback PDM encoder and method is presented which permits utilization ofneumatic pulse duration modulation (PDM) actuators with potentiometer position pickoffs in a digital autopilot loop. The actuator is directly driven by a signal derived in the digital autopilot which is in the pulse duration modulation (PDM) format. This signal is derived within the autopilot digital computer using conventional digital techniques. Analog feedback from the potentiometer which indicates angular excursion of the actuator is formatted into a PDM format. This method yields all signals necessary to operate the actuator in a closed loop missile control system.
Abstract translation: 提出了一种反馈PDM编码器和方法，其允许在数字自动驾驶仪环路中利用具有电位计位置传感器的气动脉冲持续时间调制（PDM）致动器。 致动器由在数字自动驾驶仪中得到的信号直接驱动，该信号处于脉冲宽度调制（PDM）格式。 该信号是使用传统的数字技术在自动驾驶仪数字计算机内导出的。 来自电位计的模拟反馈表示执行器的角度偏移被格式化为PDM格式。 该方法产生在闭环导弹控制系统中操作执行器所需的所有信号。
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公开(公告)号：US3946968A
公开(公告)日：1976-03-30
申请号：US494682
申请日：1974-08-02
Applicant: David V. Stallard
Inventor： David V. Stallard
Abstract: An improved flight control system for use in guided missiles having a plurality of individually actuable control surfaces is shown. In order to overcome the deleterious effects of aerodynamic cross-coupling between control surfaces at a high angle of attack, the disclosed system includes means for first determining the lift force and roll moment of each control surface, and then, in accordance with the determined values of such forces and moments, controlling separately the total pitch lift force, yaw lift force and roll moment generated by all control surfaces. Any desired maneuver, either in pitch or yaw (or both), may therefore be executed without causing any unwanted motion of the missile, such as motion in an undesired plane or rolling of the missile.
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公开(公告)号：US3396629A
公开(公告)日：1968-08-13
申请号：US53908166
申请日：1966-03-31
Applicant: FAISANDIER JACQUES
Inventor： FAISANDIER JACQUES
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