公开(公告)号：US4375641A

公开(公告)日：1983-03-01

申请号：US227081

申请日：1980-12-23

Applicant: Lars G. Josefsson ,  Karl-Erik I. Oderland ,  Jan-Olov Winnberg

Inventor： Lars G. Josefsson ,  Karl-Erik I. Oderland ,  Jan-Olov Winnberg

IPC: G01S13/26 ,  G01S7/36 ,  G01S13/08 ,  G01S13/18 ,  G01S13/24 ,  G01S13/64 ,  G01S13/70

CPC classification number: G01S13/70 ,  G01S13/24

Abstract: The invention relates to a method for a tracking radar which transmits radar pulses towards a certain target whose target range from the beginning is known. The carrier frequency of the transmitted radar pulses are during the target tracking varied from one pulse to the next following, so that a pulse series including a certain number M of carrier frequencies is treated. The number M is chosen with reference to the continuously measured target range and as long as this range is less than a certain value. If the target range exceeds this value the number M of carrier frequencies is changed and a new pulse series including this new number is transmitted. The unambiguous range to the followed target becomes dependent on the frequency repetition frequency in the transmitted pulse series instead of the PRF of the radar.

Abstract translation: PCT No.PCT / SE80 / 00122 Sec。 371日期1980年12月25日第 102（e）1980年12月23日日期PCT提交1980年4月23日PCT公布。 出版物WO80 / 0232500 日期为1980年10月30日。本发明涉及一种跟踪雷达的方法，该方法将雷达脉冲朝向某一目标发射，目标范围从一开始就已知。 发射雷达脉冲的载波频率在目标跟踪期间从一个脉冲到下一个脉冲变化，从而处理包括一定数量M的载波频率的脉冲序列。 参考连续测量的目标范围选择数量M，只要该范围小于一定值即可。 如果目标范围超过该值，则载波频率的数量M被改变，并且发送包括该新号码的新的脉冲序列。 跟随目标的明确范围取决于发射脉冲序列中的频率重复频率，而不是雷达的PRF。

公开(公告)号：US4258362A

公开(公告)日：1981-03-24

申请号：US78879

申请日：1979-09-26

Applicant: Joel E. Brown ,  Kelly C. Overman

Inventor： Joel E. Brown ,  Kelly C. Overman

IPC: G01S13/70

CPC classification number: G01S13/70

Abstract: A tracker for predicting the occurrence of an arbitrary number of phase coherent signals comprising a signal train, which predicts the phase and pulse repetition intervals for each individual signal and which maintains phase coherence of all signals provided at least one signal is present. A multiplexing system permits tracking of a multiple of phase coherent signal trains by successively connecting a series of tracker channel memories with the phase and pulse repetition interval error correction circuitry required for a single tracker. Each channel maintains phase coherency for all signals of its associated signal train while at least one signal of the train is present.

Abstract translation: 一种跟踪器，用于预测包括信号序列的任意数量的相位相位信号的发生，该信号序列预测每个单独信号的相位和脉冲重复间隔，并且保持提供至少一个信号的所有信号的相位相干性。 复用系统允许通过将一系列跟踪信道存储器连续地连接到单个跟踪器所需的相位和脉冲重复间隔误差校正电路来跟踪多个相位相干信号列。 每个信道对于其相关联的信号列的所有信号保持相位一致性，同时存在列车的至少一个信号。

公开(公告)号：US4041485A

公开(公告)日：1977-08-09

申请号：US641458

申请日：1975-12-17

Applicant: Howard R. Stevenson, Jr.

Inventor： Howard R. Stevenson, Jr.

IPC: G01S13/70 ,  G01S9/16

CPC classification number: G01S13/70

Abstract: A split gate radar pulse tracking circuit employs sequential and contiguously generated early and late gate sampling pulses for sampling a radar video signal containing a target pulse to be tracked in range. The video signal is fed into a first (X) input port of an integrated circuit multiplier and the early and late gate pulses are fed into the positive and negative terminals of the second (Y) multiplier input port. The gain networks of the multiplier are set so that when the early and late gate pulses are not present, the gain of the Y channel is 0 and the multiplier output is also 0. When a sampling pulse is present, the gain of the Y channel is 1 and the multiplier output is a replica of the video input. Because the early and late gate pulses are fed to positive and negative multiplier inputs, presentation of the late gate pulse reverses the polarity at the multiplier output. The latter is fed to an integrating amplifier which has its output fed back to control the time of occurrence of the early and late gate pulses whereby the timing of the early and late gate pulses is servoed to track the target pulse. The output of the integrating amplifier represents the range of the target pulse.

Abstract translation: 分裂门雷达脉冲跟踪电路采用连续和连续生成的早期和晚期门采样脉冲，用于对包含待跟踪的目标脉冲的雷达视频信号进行采样。 视频信号被馈送到集成电路倍增器的第一（X）输入端口，并且早和晚门脉冲被馈送到第二（Y）乘法器输入端口的正和负端子。 设置乘法器的增益网络，使得当不存在早期和晚期门脉冲时，Y通道的增益为0，乘法器输出也为0.当存在采样脉冲时，Y通道的增益 是1，乘法器输出是视频输入的副本。 因为早期和晚期门脉冲被馈送到正和负乘法器输入，所以晚期门脉冲的呈现反转乘法器输出处的极性。 后者被馈送到积分放大器，其输出反馈以控制早期和晚期门脉冲的发生时间，由此早期和晚期门脉冲的定时被伺服以跟踪目标脉冲。 积分放大器的输出表示目标脉冲的范围。

公开(公告)号：US4000490A

公开(公告)日：1976-12-28

申请号：US545687

申请日：1975-01-30

Applicant: Leon J. Lader

Inventor： Leon J. Lader

IPC: G01S13/70 ,  G01S9/14

CPC classification number: G01S13/70

Abstract: The specification discloses a variable range gate for time tracking a video echo signal reflected from a target. Range gate correction is effected by the output of a logic circuit which determines the location of the maximum echo signal on a multiple tap delay line.

Abstract translation: 本说明书公开了一种用于时间跟踪从目标反射的视频回波信号的可变范围门。 范围门限校正由逻辑电路的输出实现，该逻辑电路确定多抽头延迟线上的最大回波信号的位置。

公开(公告)号：US3936823A

公开(公告)日：1976-02-03

申请号：US494262

申请日：1974-08-01

Applicant: Charles A. Weber

Inventor： Charles A. Weber

IPC: G01S13/70 ,  G01S13/78 ,  G01S9/14 ,  G01S9/56

CPC classification number: G01S13/70 ,  G01S13/785

Abstract: A fast search system for DME generates range gates at the time an analog sweep voltage rises to the magnitude of an analog integrator waveform, the latter having a slope less than that of the sweep voltage and provided with a constant current source input. The current source is selectively inhibited by digital control means responsive to the relative time occurrence of range gates and reply pulses such that the range gate occurs during an instant interrogation period at a point in time corresponding to a predetermined percentage of the time at which appeared the first received reply pulse in a preceding interrogation period.

Abstract translation: DME的快速搜索系统在模拟扫描电压上升到模拟积分波形的幅度时产生量程门，后者的斜率小于扫描电压的斜率，并具有恒定电流源输入。 电流源被数字控制装置选择性地禁止，该控制装置响应于距离门和应答脉冲的相对时间出现，使得范围门在对应于出现时间的预定百分比的时间点的即时询问周期期间发生 在先前的询问期间首先收到回复脉冲。

公开(公告)号：US3900868A

公开(公告)日：1975-08-19

申请号：US45361374

申请日：1974-03-22

Applicant: SPERRY RAND CORP

Inventor： BOCK JOSEPH J ,  DUNHAM WILLIAM S

IPC: G01S13/76 ,  G01S13/66 ,  G01S13/70 ,  G01S13/78 ,  G01S9/14 ,  G01S9/56

CPC classification number: G01S13/70 ,  G01S13/787

Abstract: A pulse tracker particularly for use in airborne distance measuring equipment (DME). A transmitter-receiver in the aircraft transmits a coded pulse pair to a ground based transponder which, in response thereto, transmits another coded pulse pair for receipt by the airborne receiver. A second order digital recursive servo in the aircraft effects a predictive routine during each pulse transmission interval to predict the time of receipt of the next following pulse thereby predicting the range for that pulse interval. A range gate is generated in accordance with the predicted range to coincide with the expected arrival time of the next following pulse. Precision clock pulses are gated into a counter in accordance with the time interval between the transmission of a pulse and the receipt of the corresponding pulse from the transponder thereby providing a digital measure of the actual range of the aircraft with respect to the transponder. The predictive routine obtains the difference between the measured range and the predicted range thereby providing a range error. The current range error is added to the accumulated sum of past range errors from prior pulse intervals. The current range error and the accumulated range errors are each multiplied by respective constants less than unity by shifting operations. The predictive routine adds the current range error multiplied by its constant and the sum of the range errors multiplied by its constant to the predicted range for the current pulse interval to obtain the predicted range for the next pulse interval. The averaging effect of accumulating the range errors and multiplying by a constant less than unity accurately provides additional bits of resolution than could be obtained from the basic system clock frequency.

Abstract translation: 特别用于机载距离测量设备（DME）的脉冲跟踪器。 飞机中的发射机 - 接收机将编码的脉冲对发送到基于地面的应答器，其响应于此，发送另一编码脉冲对以供机载接收机接收。 飞机中的二阶数字递归伺服器在每个脉冲传输间隔期间影响预测程序，以预测接下来的后续脉冲的时间，从而预测该脉冲间隔的范围。 根据预测的范围产生量程门，以与下一个跟随脉冲的预期到达时间一致。 精确的时钟脉冲根据脉冲发射和从应答器接收相应脉冲之间的时间间隔门控到计数器中，从而提供飞行器相对于应答器的实际范围的数字测量。 预测程序获得测量范围与预测范围之间的差异，从而提供范围误差。 电流范围误差被加到先前脉冲间隔的过去范围误差的累加和。 电流范围误差和累积范围误差各自乘以小于1的相应常数，通过移位操作。 预测程序将电流范围误差乘以其常数和乘以其常数的范围误差之和与当前脉冲间隔的预测范围相加，以获得下一个脉冲间隔的预测范围。 积分范围误差并乘以一个小于1的精度的平均效应可以提供比从基本系统时钟频率得到的分辨率更多的位。

公开(公告)号：US3900850A

公开(公告)日：1975-08-19

申请号：US80977869

申请日：1969-03-24

Applicant: WESTINGHOUSE ELECTRIC CORP

Inventor： ULMAN LYNN J ,  GREEN RAYMOND G

IPC: G01S7/02 ,  G01S13/70 ,  G01S9/14

CPC classification number: G01S13/70 ,  G01S7/021

Abstract: A pulse train tracking system completely digital in operation is capable of tracking pulse trains in a dense signal environment. An acquisition circuit determines the existence of a unique pulse combination by measurement of the interpulse period between successive pulses within a preselected range of minimum and maximum interpulse periods. Acquired pulse trains are tracked by an available one of several tracking circuits, adapted to individually track different pulse trains of the same or different pulse repetition frequencies. The trackers predict the interpulse period, for a train being tracked and define a gate within which the predicted pulse should occur. The trackers correct the phasing of the gate relative to a received pulse within each period and correct the predicted inter-pulse period at a proportioned rate. Tracking is maintained in the absence of pulses for a preselected number of interpulse periods.

Abstract translation: 完全数字化的脉冲序列跟踪系统能够在密集信号环境中跟踪脉冲串。 采集电路通过测量在最小和最大脉冲间期间的预选范围内的连续脉冲之间的脉冲间隔来确定唯一脉冲组合的存在。 获取的脉冲串由几个跟踪电路中的一个跟踪，适用于单独跟踪相同或不同脉冲重复频率的不同脉冲串。 跟踪器预测脉冲周期，对于正在被跟踪的列车并且定义预定脉冲应在其中发生的门。 跟踪器在每个周期内校正门相对于接收脉冲的相位，并以比例的速率校正预测的脉冲间周期。 在不存在用于预选数量的脉冲间隔的脉冲的情况下维持跟踪。

公开(公告)号：US3833904A

公开(公告)日：1974-09-03

申请号：US32976473

申请日：1973-02-05

Applicant: HUGHES AIRCRAFT CO

Inventor： GEBHARDT R ,  SIDLO R ,  GOLDBERG G ,  SCHEIDLER S ,  KING D ,  PARKE D ,  PRIESTER W ,  MUCHLINSKI D

IPC: G01S13/10 ,  G01S13/12 ,  G01S13/524 ,  G01S13/528 ,  G01S13/66 ,  G01S13/70 ,  G01S13/87 ,  H01Q1/28 ,  H01Q25/00 ,  G01S9/02

CPC classification number: H01Q1/28 ,  G01S13/106 ,  G01S13/12 ,  G01S13/524 ,  G01S13/528 ,  G01S13/66 ,  G01S13/70 ,  G01S13/87 ,  G01S13/872 ,  H01Q25/00

Abstract: An airborne radar system is disclosed utilizing multiple fixed antenna arrays mounted within the periphery of the aircraft to avoid aerodynamic modifications and optimumly placed to achieve 360* surveillance coverage. The arrays preferably include a fore mounted array, an aft mounted array, a port mounted array and a starboard mounted array for respectively firing beams in different azimuth sectors relative to the aircraft. Each array is comprised of dipole elements having phase shifters coupled thereto for steering a beam within the corresponding sector. The radar system may include both primary and secondary radar subsystems with the dipole elements of primary and secondary radar antennas being physically interleaved in the aforementioned antenna arrays. The primary radar antennas time share an exciter, transmitter, receiver and signal processor through switching devices. The secondary radar antennas (typically an IFF/SIF system) similarly time share transmitting and receiving equipment. Time allocation between antennas of each subsystem and between operational modes such as ''''search'''' or ''''track'''' is based on various factors such as mission objectives, current target characteristics and radar purpose. Time allocation is preferably determined by an ''''on line'''' stored program digital computer which generates a radar control command to define the parameters for each beam to be fired. Typically, the control command specifies (1) array (2) beam elevation (3) beam azimuth (4) total number of fill and data pulses (5) number of fill pulses (6) frequency and (7) pulse repetition rate or frequency. For each radar subsystem, this control command is interpreted by a radar control unit which responds by controlling various system elements including the exciter, transmitter, switches, phase shifters and duplexers to cause the defined beam to be fired. Each control command also preferably specifies parameters utilized to interpret the return beam including (8) ground doppler offset (9) threshold (10) range start time and (11) range end time. This latter information is employed by the radar control unit to enable primarily the receiver and signal processor to generate a beam return report which is then communicated by the radar control unit to the digital computer. The beam return report typically includes a header portion specifying the (1) clutter level and (2) jam level for each different frequency. The report also includes a subreport for each return beam which specifies (3) range (4) amplitude (5) doppler filter number and (6) ratio of signal to clutter plus noise. The digital computer then utilizes the beam return report to determine subsequent control commands.

公开(公告)号：US3821736A

公开(公告)日：1974-06-28

申请号：US22928962

申请日：1962-10-05

Applicant: US NAVY

Inventor： KUCK J ,  STAAKE D

IPC: G01S13/58 ,  G01S13/70 ,  G01S9/26

CPC classification number: G01S13/581 ,  G01S13/70

Abstract: 4. A frequency diversity pulse Doppler radar system comprising a directive antenna, transmitting means for providing a plurality of signals of different fixed frequencies connected to said antenna so as to generate exploratory pulses of electromagnetic energy, a stable local oscillator, modulating means connected to said transmitting means and said local oscillator for providing a timing reference signal, a first mixer connected to said modulator and said antenna for combining said timing reference signal and a target echo signal to produce a carrier Doppler signal, a second mixer connected to said first mixer and said local oscillator for detecting the Doppler portion of said target echo signal, a plurality of mechanical phase shifters having their outputs connected to said second mixer, a first switch means connected to each of said mechanical phase shifters and to said local oscillator for selectively connecting said oscillator to one of said mechanical phase shifters, and a control means for driving each phase shifter at a continuously varying speed until a proper Doppler signal is detected by said second mixer and for driving each phase shifter at a speed equal to the frequency of the Doppler ambiguity produced by a corresponding transmitted frequency after a proper Doppler signal is detected by said second mixer.

公开(公告)号：US3820119A

公开(公告)日：1974-06-25

申请号：US29901672

申请日：1972-10-19

Applicant: DASSAULT ELECTRONIQUE

Inventor： VALLAS G ,  CASSE R ,  ROBIN H

IPC: G01S13/70 ,  G01S9/16

CPC classification number: G01S13/70

Abstract: A system computing the distance of a reflecting object from the position of an echo pulse within a range gate or telemetering window includes, as the second one of two cascaded integrators, an incrementor for converting the output voltage of the first integrator into a train of counting pulses with a cadence proportional to speed, these counting pulses being fed to a distance register which is periodically discharged into a countdown register to provide a pulse count proportional to distance. The countdown register is progressively read out by clock pulses over a period beginning with the emission of a highfrequency burst by the radar transmitter and ending upon the attainment of a zero count, or possibly a negative count establishing the lower limit of a range gate, as determined by an associated decoder controlling the telemetering-window generator. The output voltage of the decoder may be used to ascertain, with the aid of a comparator receiving a fixed reference voltage, the instant when a craft equipped with the radar system approaches a target to within a critical distance whereupon the first integrator is disconnected from the radar receiver to operate as a speed memory on the basis of data previously stored therein; the decoder output then continues its decrease, by extrapolation, in accordance with the diminishing target distance until another comparator gives rise to a firing pulse detonating a charge aboard the craft.