公开(公告)号：US5619206A

公开(公告)日：1997-04-08

申请号：US560186

申请日：1995-11-20

Applicant: Elbert L. Cole, Jr. ,  Richard A. Enstrom ,  Terence E. Olver

Inventor： Elbert L. Cole, Jr. ,  Richard A. Enstrom ,  Terence E. Olver

IPC: G01S13/44 ,  G01S13/76 ,  G01S13/78 ,  G01S13/91

CPC classification number: G01S13/781 ,  G01S13/4454 ,  G01S13/765

Abstract: A secondary radar uses monopulse reception techniques to improve the estimate of the aircraft position and to improve the reliability of the reply decoding process. Digital signal processing techniques are utilized to replace the analog circuit used in the prior implementations. The secondary radar implements monopulse processing using a half angle phase method wherein the sum and difference signals are encoded in a complete phasor. The detection of the signal and extraction of the azimuth angle data is implemented using a digital receiver concept. The complex phasor is sampled at an intermediate frequency, down converted to baseband and detected. The azimuth angle is computed using arithmetic methods implemented by digital signal processing circuitry.

Abstract translation: 二次雷达使用单脉冲接收技术来改善飞机位置的估计并提高应答解码过程的可靠性。 利用数字信号处理技术代替在先实现中使用的模拟电路。 二次雷达使用半角相位法实现单脉冲处理，其中和和信号以完整的相量编码。 使用数字接收机概念实现信号的检测和方位角数据的提取。 复相量以中间频率采样，下变频到基带并检测。 使用由数字信号处理电路实现的算术方法来计算方位角。

公开(公告)号：US2771476A

公开(公告)日：1956-11-20

申请号：US37698853

申请日：1953-08-27

Applicant: UPJOHN CO

Inventor： LYTTLE DOUGLAS A ,  LEVIN ROBERT H

IPC: C07J5/00 ,  C07J75/00

CPC classification number: C07J5/00 ,  C07J75/00

公开(公告)号：US2376152A

公开(公告)日：1945-05-15

申请号：US51592743

申请日：1943-12-28

Applicant: SINGER MFG CO

Inventor： KARLE JOHN D

IPC: A61B17/06

CPC classification number: A61B17/06123

公开(公告)号：US07469168B1

公开(公告)日：2008-12-23

申请号：US10814707

申请日：2004-03-30

Applicant: Ronald K. Richey

Inventor： Ronald K. Richey

IPC: G05D1/02 ,  B63H25/06

CPC classification number: B63H25/36 ,  B63H25/02 ,  B63H25/04

Abstract: A rudder control system having adjustable rudder drive turn off and “turn on,” and component wear monitoring. The rudder drive “turn off” being adjusted in accordance with the rudder stop position relative to the rudder order stop position, thereby improving position accuracy. Frequency of system “turn on” is compared to an acceptable “turn on” frequency for solenoid operation. Should the “turn on” frequency exceed the acceptable “turn on” frequency, the rudder angle at which “turn on” is implemented is adjusted to protect solenoids in the system from burnout. The rate of change of the rudder repeatback signal is monitored. A slow rate of change providing an indication of some component problem.

Abstract translation: 具有可调舵驱动器的方向舵控制系统关闭并“打开”，组件磨损监控。 方向舵驱动器“关闭”根据方向舵停止位置相对于舵位置停止位置进行调整，从而提高了位置精度。 频率与系统“开启”频率与电磁操作频率可接受的“开启”相比较。 如果“开启”频率超过可接受的“开启”频率，则实施“开启”的方向舵角度被调整，以保护系统中的电磁铁不致烧坏。 监测方向舵重复信号的变化率。 缓慢的变化率提供了一些组件问题的指示。

公开(公告)号：US07194049B2

公开(公告)日：2007-03-20

申请号：US10271100

申请日：2002-10-15

Applicant: Cyrus A. Dhalla ,  Michael S. Munoz

Inventor： Cyrus A. Dhalla ,  Michael S. Munoz

IPC: H04L27/08

CPC classification number: H03G3/3089

Abstract: A digital automatic level control system employs delay elements, which enable information about a signal parameter from the past, present and future to be processed to provide an optimal gain that can be used to level rapidly varying signals, such as bursty signals. As digital time samples of a signal are passed through first and second buffers, first and second accumulators maintain running sums that are related to the sum of the samples presently in the first and second buffers, respectively. The sums in the first and second accumulators represent information about the signal parameter for the future and the past, respectively. By choosing the maximum of these two values, the system can anticipate the beginning of a signal burst, and still have enough delay to compensate the end of a signal burst. In one embodiment of the invention, multiple channel signals can be leveled, either individually or in groups.

Abstract translation: 数字自动电平控制系统采用延迟元件，其使得能够处理关于来自过去，现在和将来的信号参数的信息，以提供可用于对快速变化的信号（例如突发信号）进行等级的最佳增益。 当信号的数字时间采样通过第一和第二缓冲器时，第一和第二累加器分别保持与当前在第一和第二缓冲器中的采样的总和相关的运行和。 第一和第二累加器中的和分别表示关于未来和过去的信号参数的信息。 通过选择这两个值的最大值，系统可以预测信号突发的开始，并且仍然具有足够的延迟来补偿信号突发的结束。 在本发明的一个实施例中，可以单独地或分组地对多个信道信号进行调平。

公开(公告)号：US20060236762A1

公开(公告)日：2006-10-26

申请号：US11112203

申请日：2005-04-21

Applicant: A. Meyer

Inventor： A. Meyer

IPC: G01P15/08

CPC classification number: G01H9/00 ,  G01P15/093

Abstract: A proof mass is suspended in a cavity in a housing. The proof mass moves along a sensing axis in response to linear acceleration. Elastic support members are connected between the proof mass and the housing and are arranged to exert a reaction force on the proof mass in response to displacement of the proof mass along the sensing axis. An optical fiber is connected between the proof mass and opposite sidewall portions of the housing such that displacement of the proof mass along the sensing axis elongates a first portion of the optical fiber and shortens another portion. An optical signal source provides a broadband optical signal input to the optical fiber. A fiber optic Bragg grating is formed in the optical fiber and arranged to reflect a portion of the optical signal. Acceleration of the proof mass modulates the wavelength of the reflected optical signal.

Abstract translation: 将检测质量悬浮在壳体中的空腔中。 响应于线性加速度，检测质量沿感测轴线移动。 弹性支撑构件连接在检测质量体和壳体之间，并且被布置成响应于沿着感测轴的检测质量块的位移而在检测质量块上施加反作用力。 光纤连接在壳体的检测质量块和相对的侧壁部分之间，使得检测质量块沿检测轴的位移使光纤的第一部分伸长并缩短另一部分。 光信号源为光纤提供宽带光信号输入。 在光纤中形成光纤布拉格光栅，并布置成反射光信号的一部分。 检测质量的加速度调制反射光信号的波长。

公开(公告)号：US6089503A

公开(公告)日：2000-07-18

申请号：US231281

申请日：1999-01-15

Applicant: John Alan Volk

Inventor： John Alan Volk

IPC: B64C3/38

CPC classification number: B64C3/38

Abstract: In accordance with the present invention, there is provided an aerodynamic control system which is attachable to an aircraft body and is operable between enhanced control and radar evasive modes. The aerodynamic control system is provided with an aerodynamic support structure which extends from the aircraft body. The support structure is rotatably attached to the aircraft body about a support structure rotational axis. The support structure has an outboard support and an inboard support which is disposed adjacent the aircraft body. The aerodynamic control system is further provided with an elongate torque member which extends from the aircraft body. The torque member has a torque rotational axis which is co-linear with the support structure rotational axis. The torque member further has an outboard end which is fixedly attached to the outboard support of the support structure. In the normal fight mode the inboard and outboard supports cooperatively rotate in response to rotation of the torque member. In the radar evasive mode the outboard support rotates relative to the inboard support in response to rotation of the torque member, thereby altering the aerodynamic characteristics of the aerodynamic control system for aircraft control.

Abstract translation: 根据本发明，提供一种可附接到飞行器主体并且可在增强的控制和雷达回避模式之间操作的空气动力学控制系统。 空气动力学控制系统具有从飞行器主体延伸的空气动力学支撑结构。 支撑结构围绕支撑结构旋转轴线可旋转地附接到飞行器本体。 支撑结构具有外侧支撑件和靠近飞行器主体设置的内侧支撑件。 空气动力学控制系统还设置有从飞行器主体延伸的细长扭矩构件。 扭矩构件具有与支撑结构旋转轴线共线的转矩旋转轴。 扭矩构件还具有固定地附接到支撑结构的外侧支撑件的外侧端部。 在正常的打斗模式中，内侧和外侧支撑件响应于扭矩构件的旋转协同地旋转。 在雷达回避模式中，响应于扭矩构件的旋转，外侧支撑件相对于内侧支撑件旋转，从而改变用于飞行器控制的空气动力学控制系统的空气动力特性。