| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 无线引爆系统、无线引爆方法和用于其的雷管及炸药单元 | CN201380069749.5 | 2013-12-26 | CN104919270A | 2015-09-16 | 彦根智; 田崎阳治 |
| 本发明涉及一种无线引爆雷管(10)，其具有引爆部(10A)、控制部(10B)、管体(10X)及引爆侧天线(30)，其中，所述控制部(10B)与引爆部连接并对引爆部点火；所述管体(10X)收容引爆部及控制部；所述引爆侧天线(30)为控制部在无线通信中使用的天线，并不分别具有发送专用天线及接收专用天线就能够用于发送接收，引爆侧天线为软磁性线圈天线，控制部(10B)通过引爆侧天线(30)接收100kHz以上500kHz以下频率的操作频率的发送信号。 | ||||||
| 2 | 一种交互式数字化无线遥控起爆器及其设计和控制方法 | CN201710164709.9 | 2017-03-20 | CN106707905A | 2017-05-24 | 孙伟 |
| 本发明涉及一种交互式数字化无线遥控起爆系统，包括多个起爆执行模块(1)、多个现场控制器(2)、电源模块(3)、无线通信模块(4)、远程控制器(5)，其特征在于:起爆执行模块(1)，用于向其相连的雷管输出起爆电流，引爆爆炸装置；现场控制器(2)，用于等待接收远程控制器(5)的操作命令，并作出相应的动作，控制电源模块(3)输出恒定电流信号，控制起爆执行模块(1)的继电器输出电流信号至外接雷管，同时将现场控制器(2)的状态实时发送回远程控制器(5)；该发明的设计方案可以对系统的各个状态进行实时监控，解决了之前设备中起爆状态无法判断的缺陷。 | ||||||
| 3 | 无线引爆系统、无线引爆方法和用于其的雷管及炸药单元 | CN201380069749.5 | 2013-12-26 | CN104919270B | 2017-03-22 | 彦根智; 田崎阳治 |
| 本发明涉及一种无线引爆雷管(10)，其具有引爆部(10A)、控制部(10B)、管体(10X)及引爆侧天线(30)，其中，所述控制部(10B)与引爆部连接并对引爆部点火；所述管体(10X)收容引爆部及控制部；所述引爆侧天线(30)为控制部在无线通信中使用的天线，并不分别具有发送专用天线及接收专用天线就能够用于发送接收，引爆侧天线为软磁性线圈天线，控制部(10B)通过引爆侧天线(30)接收100kHz以上500kHz以下频率的操作频率的发送信号。 | ||||||
| 4 | 在接近目标处引爆炮弹的装置 | CN88106990 | 1988-09-29 | CN1009387B | 1990-08-29 | 科劳斯·蒙兹尔 |
| 当在目标Z附近引爆炮弹G时，炮弹的碎片S沿一确定方向飞向目标。为使尽可能多的碎片击中目标。必须以一特定的角度(所谓点火角ZW)引爆炮弹。该点火角取决于炮弹和目标的相遇速度VB■根据本发明，利用射击指挥仪计算出相遇速度VB■和系数■并存贮在装置DS中以确定相遇速度VB■位于炮弹中的装置DS确定VB，计算■并与■相比较。只要该系数达到■■过■，就引爆。 | ||||||
| 5 | 在接近目标处引爆炮弹的装置 | CN88106990 | 1988-09-29 | CN1034425A | 1989-08-02 | 科劳斯·蒙兹尔 |
| 当在目标Z附近引爆炮弹G时，炮弹的碎片S沿一确定方向飞向目标。为使尽可能多的碎片击中目标，必须以一特定的角度(所谓点火角ZW)引爆炮弹。该点火角取决于炮弹和目标的相遇速度VB。根据本发明，利用射击指挥仪计算出相遇速度VBg和系数并存贮在装置DS中以确定相遇速度VB。位于炮弹中的装置DS确定VB，计算，并与相比较。只要该系数达到并超过，就引爆。 | ||||||
| 6 | JPH0254912B2 - | JP16282183 | 1983-09-05 | JPH0254912B2 | 1990-11-22 | SAITO OSAMU |
| 7 | Dopller type proximity fuse | JP6792080 | 1980-05-23 | JPS56164972A | 1981-12-18 | KOJIMA YASUO; KOUNO MINORU; FUNADA TOSHIO |
| PURPOSE:To improve altitude detection accuracy by comparing Doppler detected output voltage and the prescribed divided voltage of the Doppler detected output voltage before a fixed period and determining altitude. CONSTITUTION:A flying body 1 such as a cannon ball generates the Doppler detected output En at altitude Hn by way of an antenna 3, etc. by the reflected waves from a target 2. This output En is divided by a voltage dividing circuit 6 in accordance with the ratio alpha between the altitude Hn and the altitude Hn-1. On the other hand, when the count value of a counter 8 attains the count value corresponding to the time when the body 1 falls from the altitude Hn-1 down to Hn for a distance D, it is compared with the voltage En-1 having been held in a sample holding circuit 7, and whether the conditions of the equation I corresponding to the arrival at the altitude Hn or not is detected. By this constitution, the highly accurate altitude detection of whether initiating altitude was attained or not is accomplished. | ||||||
| 8 | Device for controlling initial explosive of shooter fuse | JP5449876 | 1976-05-14 | JPS51140400A | 1976-12-03 | RICHIYAADO TOOMASU JIMUBA; MAARON DEYUANE EGUTOBETSUTSU |
| 9 | Electric field enabled proximity fusing system | JP32052290 | 1990-11-22 | JPH03217799A | 1991-09-25 | RICHIYAADO TOOMASU TSUIINBA |
| PURPOSE: To restrict explosion of a warhead until encountering a flying target, by a method wherein an arming signal generated in response to a voltage of a probe as a missile approaches into an electric field inherently associated with the flying target is applied to a first detecting part to detonate the warhead. CONSTITUTION: Current proportional to the voltage of a probe 24 to be generated as a missile approaches an electric field of a target is converted to a voltage of a signal and amplified to be supplied to a microprocessor 30. When an attack target is captured, the microprocessor 30 outputs an arming signal to make a fuse 36 of a warhead of the missile ready for operation. An RF receiver 38 of an active type proximity searching part transmits a signal via a radar antenna 26 and receives a signal returned from the target 10 to generate a signal for triggering the fuse by a microprocessor 40, which is applied to the other output side of a coincidence gate 34. But a gate 34 will not operate until the missile enters a range of a target detecting distance of a passive type detecting part 29, thereby preventing earlier detonation of the fuser 36. COPYRIGHT: (C)1991,JPO | ||||||
| 10 | Proximity fuse for guided flying body | JP14236182 | 1982-08-17 | JPS5932879A | 1984-02-22 | ISHIDA SHIZUO; WADA ATSUSHI |
| PURPOSE:To prevent the activation of a detonation signal due to a clutter signal generated from the ground surface or the sea surface by receiving a signal from a target accurately with a narrow band filter changed in the center frequency of a Doppler amplifier according to the speed of the target. CONSTITUTION:As a target airplane comes into a beam of an antenna 1, a Doppler signal is produced with a Doppler deviation in the beam proportional to the relative speed between the guided flying body and the target airplane as same with a reflected wave from the ground surface or the sea surface and enters a Doppler amplifier 7. The Doppler amplifier 7 is provided with a narrow band filter varying in the center frequency according to changes in the frequency of the Doppler signal of a Doppler tracking device 6 and can capture a signal from the target airplane accurately. Outputs of the Doppler amplifier 7 and a clutter amplifier 8 enter a detector 9 provided with threshold for the generation of a detonation signal. The threshold of the detector 9 is determined by the output of the clutter amplifier 8 for amplifying clutters. As exceeding the threshold of the detector 9, the output is provided to a detonation circuit 10 to trigger a warhead 11. | ||||||
| 11 | Kinsetsushinkanochijoseigyosadosuru sochi | JP13205075 | 1975-10-31 | JPS5171000A | 1976-06-19 | RARUSU ERITSUKU SUKAGERURUNTO |
| 12 | JPS4976400A - | JP11773473 | 1973-10-19 | JPS4976400A | 1974-07-23 | |
| 13 | 신관 장입기 및 신관 장입 방법 | KR1020130162004 | 2013-12-24 | KR1020150074337A | 2015-07-02 | 박효환; 최성대; 박현묵 |
| 본발명은신관장입기및 신관장입방법에관한것으로서, 상세하게는신관에데이터를장입함에있어서대량의데이터를전송하는시간을절감하여장입효율을제고할수 있고, 기준비행경로를산출하여장입함으로써탄도수정신관이장착될수 있는다양한범용포탄및 별도의유도조종장치를갖는정밀유도포탄등에적용할수 있는신관장입기및 신관장입방법에관한것이다. 이러한목적을달성하기위한본 발명은, GPS데이터또는기상데이터또는임무수행데이터중 적어도어느하나를수신하고, 수신된데이터를기초로신관이장착된발사체의기준비행경로(Nominal Flight Path)를연산하는제어장치와; 상기제어장치와통신가능하게마련되고상기제어장치로부터상기 GPS데이터또는기상데이터또는임무수행데이터중 적어도어느하나와상기발사체의기준비행경로에관한데이터를수신하여저장하고, 이를신관에전달할수 있도록마련되는장입장치를포함하되, 상기장입장치는자기장을이용하여신관의센서를동작시켜신관을활성화시키고, 무선통신을이용하여데이터들을상기신관에전달하고정상장입을확인할수 있도록마련되는것을특징으로하는신관장입기및 신관장입방법을제공한다. | ||||||
| 14 | 無線起爆雷管、親ダイ、無線起爆システム、及び無線起爆方法 | JP2013000909 | 2013-01-08 | JP5849972B2 | 2016-02-03 | 彦根 智; 田崎 陽治 |
| 15 | Radio detonator, primer, radio detonation system, and radio detonation method | JP2013000909 | 2013-01-08 | JP2014134298A | 2014-07-24 | HIKONE SATOSHI; TAZAKI YOJI |
| PROBLEM TO BE SOLVED: To provide a radio detonator, a primer, a radio detonation system, and a radio detonation method that can make shorter a time of work nearby a face plane.SOLUTION: There is provided a radio detonator 10 including a detonation part 10A, a control part 10B which is connected to the detonation part and fires the detonation part 10a, a tube body 10X which houses the detonation part and control part, and a detonation-side antenna 30 which is an antenna that the control part uses for radio communication, and can be used for transmission and reception without individually having an antenna only for transmission and an antenna only for reception. The detonation-side antenna is a soft magnetic body coil antenna, and the control part 10B receives a transmission signal having an operation frequency of 100 to 500 KHz through the detonation-side antenna 30. | ||||||
| 16 | JPH0423228B2 - | JP2554984 | 1984-02-14 | JPH0423228B2 | 1992-04-21 | SAITO OSAMU |
| 17 | Device to effect detonating of bullet in vicinity of target | JP23022588 | 1988-09-16 | JPH01114700A | 1989-05-08 | KURAUSU MIYUNTSUERU |
| PURPOSE: To accurately decide an encounter speed by considering all factors by a method wherein firing is effected as soon as the encounter speed attains a stored value and exceeds the value. CONSTITUTION: A calculating value of an encounter speed Bg is stored in a mode of, for example, fo/KfD1=C/2VBgK, wherein Fo is an oscillator frequency, K is a dividing factor, and fD1 is a frequency of a signal reflected from a target to a bullet. As soon as a Doppler sensor DS for a flying bullet G is charged, the Doppler sensor transmits a beam of the frequency fo. A beam reflected by a target Z has a frequency fo+fD. This value reaches a counter 2 through a low path TP, an amplifier V, and a comparator K. The value fo/KfD=C/2VBK is introduced to a digital comparator 3 from the counter 2. Simultaneously, a value stored in the memory device 1 is similarly introduced to the comparator 3. The two values are compared with each other at the comparator 3. When the two values are equal to each other, a detonating signal ZS is immediately generated and a bullet G is detonated. COPYRIGHT: (C)1989,JPO | ||||||
| 18 | JPS6134080B2 - | JP5449876 | 1976-05-14 | JPS6134080B2 | 1986-08-05 | RICHAADO TOOMASU JIMUBA; MAARON DEYUANE EGUTOBETSUTSU |
| 19 | Active proximity fuse | JP2554984 | 1984-02-14 | JPS60169785A | 1985-09-03 | SAITOU OSAMU |
| PURPOSE:To attain to enhance the target shoot-down capacity of a guided missile having an active proximity fuse mounted thereto, by correcting an earth gate signal on the basis of guided flight altitude and controlling a target detection available distance so as to bring the same to a missile available distance at said altitude. CONSTITUTION:A guide missile shooting altitude setting part 20 stores guided missile shooting altitude (H0) supplied from the outside and outputs a signal to a guided missile flight altitude calculation part 22. A guided missile pitch direction and speed detection part 21 detects the speed (VMP) of a guided missile in the pitch direction and outputs a signal to the calculation part 22. This calculation part 22 calculates the flight altitude of the guided missile after shooting from the signal H0 and the signal VMP and outputs a signal to a detection available distance altitude correction circuit 23. The circuit 23 corrects the output signal of a distance-between-clutters detection gate signal setting part 12 on the basis of altitude by the altitude signal inputted from the calculation part 22 to outputs an earth gate correction signal. Therefore, by controlling a target detection available distance so as to bring the same to a missile available distance at said altitude, the enhancement of the target shoot-down capacity of a guided missile can be attained. | ||||||
| 20 | Active proximity fuse | JP16282183 | 1983-09-05 | JPS6053865A | 1985-03-27 | SAITOU OSAMU |
| PURPOSE:To attain to enhance shoot-down power of a target by preventing the narrowing of a detection effective range to a low altitude target, by performing control so as to make the target detecting distance of an upper side antenna receiving no influence of clutter constant. CONSTITUTION:A demodulation part 21 sends out a warhead demodulation signal on the basis of a signal through an antenna 7 and a circulator 5 and a warhead gate signal from a setting part 20. A detection circuit 22 judges whether the distance from the warhead demodulation signal to a target 10 is present in the inside or outside with respect to the warhead effective range always set constantly and, in the case of the outside, outputs a low level signal and, in the inside, outputs a high level signal. An OR circuit 23 outputs a low level signal when the outputs of the detection circuit 22 and a detection circuit 18 for detecting the invasion of the target in the target detection effective distance are together a low level. Therefore, even if the distance between clutters are invaded into the warhead effective distance of an active proximity fuse N', the detection distance of a lower side antenna 8 is short and the detection distance of an upper side antenna 7 always keeps the warhead effective distance. | ||||||
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