CN103090745A - Guided missile with middle-section speed change and anti-intercept method thereof - Google Patents

Guided missile with middle-section speed change and anti-intercept method thereof Download PDF

Info

Publication number
CN103090745A
CN103090745A CN 201310043273 CN201310043273A CN103090745A CN 103090745 A CN103090745 A CN 103090745A CN 201310043273 CN201310043273 CN 201310043273 CN 201310043273 A CN201310043273 A CN 201310043273A CN 103090745 A CN103090745 A CN 103090745A
Authority
CN
Grant status
Application
Patent type
Prior art keywords
guided
missile
level
small
anti
Prior art date
Application number
CN 201310043273
Other languages
Chinese (zh)
Inventor
朱旭望
Original Assignee
朱旭望
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date

Links

Abstract

The invention discloses a guided missile with middle-section speed change and an anti-intercept method of the guided missile, and relates to the technical field of guided missile anti-intercept. The guided missile comprises a third level guided missile warhead, a second level booster and a first level booster. A speed change anti-intercept system which is formed by 4-8 small rockets is arranged on a main body of the second level booster. Four speed change anti-intercept small guided missiles are arranged among the small rockets. The small rockets and the small guided missiles are evenly arranged around a cylinder body of the second level booster. The boosting direction of the small rockets is uniform with the direction of the third level guided missile warhead. The running direction of the small guided missiles after the small guided missiles are launched is opposite to the running direction of the third level guided missile warhead. A sudden anti-guided-missile system is installed on the third level guided missile warhead, the sudden anti-guided-missile system is formed by 4-15 small guided missiles, and the running direction of the small guided missiles is the same as the direction of the third level guided missile warhead. The guided missile with the middle-section speed change can effectively overcome the problem that the guided missile is intercepted easily after the first level drops and the second level (middle section) flies at a uniform speed. The guided missile is an anti-intercept missile with the middle-section speed change, and can effectively realize the anti-intercept function.

Description

一种带中段变速的导弹及防拦截方法 Between Missile and anti-intercept method of shifting the middle zone

技术领域 FIELD

[0001] 本发明涉及导弹防拦截技术领域,特别是一种带中段变速的导弹及防拦截方法。 [0001] The present invention relates to the field of missile defense interceptor technology, missiles and particularly to a method for preventing interception with the middle of the shift. 背景技术 Background technique

[0002] 导弹是现代战争中常用的一种武器,导弹在第一级助推器脱落后,第二级(中段)以均速飞行。 [0002] missile is commonly used in modern warfare weapons, missiles after the first-stage boosters fall off, the second stage (middle) at steady flight. 目前对导弹的各种拦截技术也是日新月异,特别是导弹在中段均速飞行时,更容易遭到来自侧面、前面、后面的拦截。 Currently a variety of missile interception technology is changing, especially in the middle of the average rate of the missile flight, more vulnerable to interception from the side, front, back. 随着导弹技术的不断提高,对导弹本身的防拦截技术一直是科学家们研究的重要课题,虽然现在已有各种防拦截技术,但一般效果都不是很理想,而且结构复杂、制造成本高昂。 With the continuous improvement of missile technology, anti-missile interception technology itself has been an important topic of research scientists, although it has a variety of anti-blocking technology, but the general effect is not very satisfactory, and complex structure, expensive to manufacture.

发明内容 SUMMARY

[0003] 本发明提供一种带中段变速的导弹及防拦截方法,本发明解决了导弹在中段均速飞行时,容易遭到来自侧面、前面、后面的拦截的问题。 [0003] The present invention provides a method of intercepting a missile and anti-shift of the middle band, the present invention solves both the missile flight speed in the middle, vulnerable to the problem from the side, front, back intercepted.

[0004] 为解决上述问题,本发明采用如下技术方案:一种带中段变速的导弹,包括第三级导弹弹头3、第二级助推器2和第一级助推器I ;第二级助推器2的主体上设有由4-8枚小火箭组成的变速防拦截系统4,在小火箭之间设置有4枚变速防拦截小导弹6,小火箭和小导弹均匀设置于第二级助推器圆柱体周围,小火箭助推方向与第三级导弹弹头方向一致,小导弹发射后运行方向与第三级导弹弹头运行方向相反; [0004] In order to solve the above problems, the present invention adopts the following technical solution: A tape middle shift missile, missile warheads comprising a third stage 3, the second booster stage 2 and the first booster stage I; second stage preventing transmission system provided by the interceptor missiles 4-8 small rocket booster body composed of 2 4, provided between the small rocket four small missile interceptors 6 anti-shift, and small rocket uniformly disposed on the second small missiles around stage booster cylinder, coincides with the direction of small rocket propelled missile warheads direction of the third stage, the third stage running direction of the running direction opposite to missile warhead after a small missile;

[0005] 在第三级导弹弹头3上安装有突防导弹系统5,突防导弹系统5由4-12枚小导弹构成,小导弹发射运行方向和第三级导弹弹头方向一致。 [0005] The third stage is mounted on a missile warhead penetration missile system with a 3 5, Penetration 4-12 missile system 5 is constituted by small pieces of missile, missile same direction of operation and a small third stage missile warheads direction.

[0006] 一种带中段变速的导弹防拦截方法: [0006] An anti-missile interception with the middle shift method:

[0007](一)所述导弹包括第三级导弹弹头3、第二级助推器2和第一级助推器I ;第二级助推器2的主体上设有由4-8枚小火箭组成的变速防拦截系统4,在小火箭之间设置有4枚变速防拦截小导弹6,小火箭和小导弹均匀设置于第二级助推器圆柱体周围,小火箭助推方向与第三级导弹弹头方向一致,小导弹发射后运行方向与第三级导弹弹头运行方向相反; [0007] (a) the missile warheads 3 comprises a third stage, the second stage booster 2 and the first booster stage I; the body of the second booster stage 2 is provided by a 4-8 pieces preventing transmission interception system consisting of four small rocket, a rocket is provided between the small gear 4 6 anti-missile interceptor small, small and small rocket missile uniformly disposed around the booster cylinder of the second stage, the direction of small rocket propelled and third stage missile warheads in the same direction, the direction of the third stage missile warhead after a small running direction opposite to missile launch;

[0008] 在第三级导弹弹头3上安装有突防导弹系统5,突防导弹系统5由4-12枚小导弹构成,小导弹发射运行方向和第三级导弹弹头方向一致; [0008] The third stage is mounted on a missile warhead penetration missile system with a 3 5, Penetration 4-12 missile system 5 is constituted by small pieces of missiles, consistent with the direction of small missile warheads direction and a third stage;

[0009] ( 二)防拦截步骤: [0009] (ii) anti-intercept the steps of:

[0010] I)第二级助推器周围平行设置有多枚小火箭组成的变速防拦截系统和4枚小导弹组成的。 [0010] I) a second booster stage is provided around the plurality of parallel shift preventing pieces small rocket interception system consisting of small missiles and 4 thereof. 同时小火箭助推方向与第三级导弹弹头方向一致,4枚小导弹发射后运行方向与第三级导弹弹头运行方向相反; While small rocket propelled direction consistent with the direction of the third stage missile warheads, four small missile after launching the direction of the third stage missile warhead run in the opposite direction;

[0011] 2)第三级导弹弹头周围同样增设有多枚小导弹,发射运行方向和第三级导弹弹头方向一致。 Missile warheads around the [0011] 2) The third stage is also adding a number of small pieces of missiles, launch and consistent with the direction of the third stage missile warheads direction. 由上所述第三级导弹弹头周围平行设置小导弹最佳为4-12枚。 Provided by the surrounding warheads on the third-stage parallel small pieces missile most preferably 4-12.

[0012] 变速防拦截与突防步骤如下: [0012] Penetration and shift prevention knockdown following steps:

[0013] I)通过导弹的雷达装置或地面控制台的卫星监控系统监测拦截导弹的方向和速度;当监测发现导弹受到侧面拦截时,导弹通过接收信号点燃2枚以上小火箭,改变导弹飞行速度,避开拦截导弹,使得拦截失败; [0013] I) monitoring the direction and speed of the interceptor missile surveillance system via satellite or ground missile radar device console; found when monitoring the subject side interceptor missile, missile ignited two or more signals received by the small rocket, missile flight speed change avoid interceptor missile that failed to intercept;

[0014] 2)当监测发现导弹受到前面拦截时,导弹通过接收信号一次可点燃第三级导弹弹头周围的二枚小导弹,击落前方拦截导弹; [0014] 2) When the monitoring results by the foregoing interceptor missile, the missile may be ignited by receiving a signal around the third stage missile warhead two small missile interceptor missile to shoot down the front;

[0015] 3)当监测发现导弹受到后面拦截时,导弹通过接收信号一次可点燃第二级助推器上的4枚小导弹中的二枚向后发射击落后方的追踪导弹; [0015] 3) When monitoring found by back when the missile interceptors, missile may be ignited by receiving signals on four small missiles second stage booster shot of the two rearwardly emitted backward tracking a missile;

[0016] 4)在导弹突防过程中,在导弹末端向目标攻击时(即进入大气层后向目标飞行至一半距离开始)第三级导弹弹头周围的小导弹定时连续向目标射击,为第三级导弹弹头攻击目标,扫清道路,击毁拦截导弹,如无遇到拦截导弹可以直接攻击目标使目标受到创伤,为了后面的第三级导弹弹头重创目标创造有利条件。 [0016] 4) missile penetration process, the target to attack (i.e., into the atmosphere at the end of the missile to the target flight distance to half start) surrounding the third stage missile missile warhead small continuous timing of the target shooting, the third class guided missile warhead targets, clear the way, destroy interceptor missiles, such as missile interceptors can not meet the target directly targeted by trauma, in order behind the third-class missile warhead hit the target to create favorable conditions.

[0017] 本发明可以有效克服导弹在第一级脱落后,第二级(中段)以均速飞行时容易遭到拦截的问题。 [0017] The present invention can effectively overcome the problem of the missile off after the first stage, second stage (middle) at steady flight vulnerable to interception. 本发明为中段变速的防拦截导弹,可有效实现防拦截,而且结构简单、制造成本低廉。 The present invention is in the middle shift anti interceptor missiles, effective to achieve the anti-blocking, and simple structure, low manufacturing cost.

附图说明 BRIEF DESCRIPTION

[0018] 图1是本发明整体结构示意图; [0018] FIG. 1 is an overall schematic view of the present invention;

[0019] 图2是本发明变速防拦截系统结构示意图。 [0019] FIG. 2 is a schematic view of the shift preventing interception system structure of the present invention.

[0020] 图3是本发明的突防导弹系统结构示意图 [0020] FIG. 3 is a schematic diagram Penetration missile system structure of the invention

[0021] 图中符号说明:第三级导弹弹头3、第二级助推器2、第一级助推器1、变速防拦截系统4 ;突防导弹系统5 ;变速防拦截小导弹6。 [0021] REFERENCE SIGNS: 3 missile warheads third stage, the second stage booster 2, a first booster stage 1, the shift preventing interception system 4; 5 Penetration missile system; anti shift interceptor missile 6 small.

具体实施方式 detailed description

[0022] 下面用最佳的实施例对本发明做详细的说明。 [0022] The following detailed description of the present invention is a preferred embodiment.

[0023] 如图1-3所示,一种带中段变速的导弹,包括第三级导弹弹头3、第二级助推器2和第一级助推器I ;第二级助推器2的主体上设有由4-8枚小火箭组成的变速防拦截系统4,在小火箭之间设置有4枚变速防拦截小导弹6,小火箭和小导弹均匀设置于第二级助推器圆柱体周围,小火箭助推方向与第三级导弹弹头方向平行,小导弹发射后运行方向与第三级导弹弹头运行方向相反; [0023] As shown, the middle shift missile 1-3 A tape comprising a third stage missile warhead 3, the second booster stage 2 and the first booster stage I; the second booster stage 2 preventing transmission system provided by the interceptor missiles 4-8 small rocket composition on the body 4, between the small rocket provided with four small missile interceptors 6 anti-shift, and small small rocket missile booster uniformly disposed in the second stage around the cylindrical body, the direction of the small rocket propelled missile warheads a direction parallel to the third stage, the third stage running direction of the running direction opposite to missile warhead after a small missile;

[0024] 在第三级导弹弹头3上安装有突防导弹系统5,突防导弹系统5由4-12枚小导弹构成,小导弹发射运行方向和第三级导弹弹头方向一致。 [0024] The third stage is mounted on a missile warhead penetration missile system with a 3 5, Penetration 4-12 missile system 5 is constituted by small pieces of missile, missile same direction of operation and a small third stage missile warheads direction.

[0025] 一种带中段变速的导弹防拦截方法: [0025] An anti-missile interception with the middle shift method:

[0026](一)所述导弹包括第三级导弹弹头3、第二级助推器2和第一级助推器I ;第二级助推器2的主体上设有由4-8枚小火箭组成的变速防拦截系统4,在小火箭之间设置有4枚变速防拦截小导弹6,小火箭和小导弹均匀设置于第二级助推器圆柱体周围,小火箭助推方向与第三级导弹弹头方向一致,小导弹发射后运行方向与第三级导弹弹头运行方向相反; [0026] (a) the missile warheads 3 comprises a third stage, the second stage booster 2 and the first booster stage I; the body of the second booster stage 2 is provided by a 4-8 pieces preventing transmission interception system consisting of four small rocket, a rocket is provided between the small gear 4 6 anti-missile interceptor small, small and small rocket missile uniformly disposed around the booster cylinder of the second stage, the direction of small rocket propelled and third stage missile warheads in the same direction, the direction of the third stage missile warhead after a small running direction opposite to missile launch;

[0027] 在第三级导弹弹头3上安装有突防导弹系统5,突防导弹系统5由4-12枚小导弹构成,小导弹发射运行方向和第三级导弹弹头方向一致; [0027] The third stage is mounted on a missile warhead penetration missile system with a 3 5, Penetration 4-12 missile system 5 is constituted by small pieces of missiles, consistent with the direction of small missile warheads direction and a third stage;

[0028] ( 二)防拦截步骤: [0028] (ii) anti-intercept the steps of:

[0029] I)第二级助推器周围平行设置有多枚小火箭组成的变速防拦截系统和4枚小导弹组成的。 [0029] I) a second booster stage is provided around the plurality of parallel shift preventing pieces small rocket interception system consisting of small missiles and 4 thereof. 同时小火箭助推方向与第三级导弹弹头方向一致,4枚小导弹发射后运行方向与第三级导弹弹头运行方向相反; While small rocket propelled direction consistent with the direction of the third stage missile warheads, four small missile after launching the direction of the third stage missile warhead run in the opposite direction;

[0030] 2)第三级导弹弹头周围同样增设有多枚小导弹,发射运行方向和第三级导弹弹头方向一致。 Missile warheads around the [0030] 2) The third stage is also adding a number of small pieces of missiles, launch and consistent with the direction of the third stage missile warheads direction. 由上所述第三级导弹弹头周围平行设置小导弹最佳为4-12枚。 Provided by the surrounding warheads on the third-stage parallel small pieces missile most preferably 4-12.

[0031] 变速防拦截与突防步骤如下: [0031] Penetration and shift prevention knockdown following steps:

[0032] I)通过导弹的雷达装置或地面控制台的卫星监控系统监测拦截导弹的方向和速度;当监测发现导弹受到侧面拦截时,导弹通过接收信号点燃2枚以上小火箭,改变导弹飞行速度,避开拦截导弹,使得拦截失败; [0032] I) monitoring the direction and speed of the interceptor missile surveillance system via satellite or ground missile radar device console; found when monitoring the subject side interceptor missile, missile ignited two or more signals received by the small rocket, missile flight speed change avoid interceptor missile that failed to intercept;

[0033] 2)当监测发现导弹受到前面拦截时,导弹通过接收信号一次可点燃第三级导弹弹头周围的二枚以上小导弹,击落前方拦截导弹; [0033] 2) When the missile been found when the front monitor to intercept missile once ignited by receiving signals around the third stage missile warheads two or more small missile interceptor missile to shoot down the front;

[0034] 3)当监测发现导弹受到后面拦截时,导弹通过接收信号一次可点燃第二级助推器上的4枚小导弹中的二枚向后发射击落后方的追踪导弹; [0034] 3) When monitoring found by back when the missile interceptors, missile may be ignited by receiving signals on four small missiles second stage booster shot of the two rearwardly emitted backward tracking a missile;

[0035] 4)在导弹突防过程中,在导弹末端向目标攻击时(即进入大气层后向目标飞行至一半距离开始)第三级导弹弹头周围的小导弹定时连续向目标射击,为第三级导弹弹头攻击目标,扫清道路,击毁拦截导弹,如无遇到拦截导弹可以直接攻击目标使目标受到创伤,为了后面的第三级导弹弹头重创目标创造有利条件。 [0035] 4) missile penetration process, the target to attack (i.e., into the atmosphere at the end of the missile to the target flight distance to half start) surrounding the third stage missile missile warhead small continuous timing of the target shooting, the third class guided missile warhead targets, clear the way, destroy interceptor missiles, such as missile interceptors can not meet the target directly targeted by trauma, in order behind the third-class missile warhead hit the target to create favorable conditions.

[0036] 本发明在收到卫星及其它通信设备提供的将要遭受拦截的信息后,可根据拦截速度点燃小型火箭,来改变导弹的飞行速度,变速防拦截系统也可按原先设定的时间与速度要求变速或根据远程控制台来远程遥控达到,避开拦截的导弹。 [0036] In the present invention receives satellite and other communication devices to provide information to be subject to interception, the interception ignitable small rocket according to the speed of the missile flight speed is changed, the shift preventing interception system can also be pre-set time and the transmission speed requirements or remote console to achieve remote control, avoid intercepting missiles. 此种改变导弹的飞行速度的方法,可有效实现难以拦截的效果,而且结构简单,生产成本低,易实施。 Such missile flight speed change method, effective to achieve an effect difficult to intercept, simple structure, low cost, easy to implement.

[0037] 最后应说明的是:显然,上述实施例仅仅是为清楚地说明本发明所作的举例,而并非对实施方式的限定。 [0037] Finally, it should be noted that: Obviously, the above-described embodiments are merely to clearly illustrate the present invention made by way of example, but not limited to the embodiment. 对于所属领域的普通技术人员来说,在上述说明的基础上还可以做出其它不同形式的变化或变动。 Those of ordinary skill in the art, on the basis of the above described variations or changes may be made in various other forms. 这里无需也无法对所有的实施方式予以穷举。 It is unnecessary and can not be exhaustive of all embodiments. 而由此所引申出的显而易见的变化或变动仍处于本发明的保护范围之中。 And obvious variations or variations therefrom come out of the still in the scope of the present invention.

Claims (4)

  1. 1.一种带中段变速的导弹,包括第三级导弹弹头(3)、第二级助推器(2)和第一级助推器(I);其特征在于:第二级助推器(2)的主体上设有由4-8枚小火箭组成的变速防拦截系统(4),在小火箭之间设置有(4)枚变速防拦截小导弹(6),小火箭和小导弹均匀设置于第二级助推器圆柱体周围,小火箭助推方向与第三级导弹弹头方向一致,小导弹发射后运行方向与第三级导弹弹头运行方向相反。 A middle gear with missile, missile warheads comprising a third stage (3), a second booster stage (2) and the first booster stage (the I); wherein: the second booster stage preventing transmission system provided by the interceptor missiles 4-8 small rocket composition (2) of the body (4), is provided between the small rocket (4) pieces of small interceptor missile anti-shift (6), small rocket and small missiles uniformly disposed around the booster cylinder of the second stage, in line with the small rocket propelled missile warheads third stage direction, opposite to the running direction of the small missile warheads with the third stage running direction.
  2. 2.按权利要求1所述一种带中段变速的导弹,其特征在于,在第三级导弹弹头(3)上安装有突防导弹系统(5),突防导弹系统(5)由4-12枚小导弹构成,小导弹发射运行方向和第三级导弹弹头方向一致。 2. A tape as claimed in claim 1 said middle gear missile, characterized in that, in the third stage missile warhead (3) is attached to penetration missile system (5), penetration missile system (5) from 4- 12 small missiles constitute a consistent run small missile launch direction and the direction of the third stage missile warheads.
  3. 3.一种带中段变速的导弹防拦截方法,其特征在于: (一)所述导弹包括第三级导弹弹头(3)、第二级助推器(2)和第一级助推器(I);第二级助推器(2)的主体上设有由4-8枚小火箭组成的变速防拦截系统(4),在小火箭之间设置有4枚变速防拦截小导弹(6),小火箭和小导弹均匀设置于第二级助推器圆柱体周围,小火箭助推方向与第三级导弹弹头方向一致,小导弹发射后运行方向与第三级导弹弹头运行方向相反; 在第三级导弹弹头(3)上安装有突防导弹系统(5),突防导弹系统(5)由4-12枚小导弹构成,小导弹发射运行方向和第三级导弹弹头方向一致; (二)防拦截步骤: 1)第二级助推器周围平行设置有多枚小火箭组成的变速防拦截系统和4枚小导弹组成的。 An anti-missile interceptor central segment shift method, wherein: (a) the missile warheads comprising a third stage (3), a second booster stage (2) and the first stage booster ( the I); provided by the transmission prevention interceptor missiles 4-8 small rocket body composed of a second stage booster (2) (4), is provided between the four small rocket shift preventing small missile interceptor (6 ), and small rocket boosters small missiles uniformly disposed around the cylindrical body of the second stage, in line with the small rocket propelled missile warheads direction of the third stage, the third stage running direction of the running direction opposite to missile warhead after a small missile; in the third stage is mounted on a missile warhead (3) penetration missile system (5), penetration missile system (5) consists of 4-12 pieces of small missiles, consistent with the direction of small missile warheads direction and a third stage; (ii) anti-intercept steps: 1) around the second stage booster provided with a plurality of parallel shift preventing pieces small rocket interception system consisting of small missiles and 4 thereof. 同时小火箭助推方向与第三级导弹弹头方向一致,4枚小导弹发射后运行方向与第三级导弹弹头运行方向相反; 2)第三级导弹弹头周围同样增设有多枚小导弹,发射运行方向和第三级导弹弹头方向一致。 While small rocket propelled direction consistent with the direction of the third stage missile warheads, four small missile after launching the direction of the third stage missile warhead run in the opposite direction; missile warhead around 2) the third stage is also adding a number of small pieces of missiles, launchers running the same direction and the direction of the third stage missile warheads. 由上所述第三级导弹弹头周围平行设置小导弹最佳为4-12枚。 Provided by the surrounding warheads on the third-stage parallel small pieces missile most preferably 4-12.
  4. 4.按权利要求3所述一种带中段变速的导弹防拦截方法,其特征在于:变速防拦截与突防步骤如下: 1)通过导弹的雷达装置或地面控制台的卫星监控系统监测拦截导弹的方向和速度;当监测发现导弹受到侧面拦截时,导弹通过接收到的信号点燃2枚以上小火箭,改变导弹飞行速度,避开拦截导弹,使得拦截失败; 2)当监测发现导弹受到前面拦截时,导弹通过接收信号一次可点燃第三级导弹弹头周围的二枚小导弹,击落前方拦截导弹; 3)当监测发现导弹受到后面拦截时,导弹通过接收信号一次可点燃第二级助推器上的4枚小导弹中的二枚向后发射击落后方的追踪导弹; 4)在导弹突防过程中,在第三级导弹弹头向目标攻击时(即进入大气层后向目标飞行至一半距离开始)第三级导弹弹头周围的小导弹定时连续向目标射击,为第三级导弹弹头攻击目标,扫清道路, Anti-missile interception method according to claim 3 4. A tape of the middle gear, wherein: the speed change preventing interception Penetration following steps: 1) a satellite monitoring system for a radar device or console monitor ground missile interceptors the direction and speed; found when monitoring the subject side interceptor missile, missile ignition signal received by two or more small rocket, missile flight speed changes, the interceptor missile to avoid such failure interception; 2) when it is monitored by detecting a missile to intercept the front when, a signal received by the missile may be ignited around the third stage missile warhead two smaller missiles shot forward interceptors; 3) when monitored by detecting a missile interceptor behind the missile may be ignited by a second received signal level boosters 4 small missile on the launch of two back-seeking missiles to shoot down behind; 4) in the missile penetration process, in the third stage missile warhead to the target attacks (that is, into the atmosphere to half the distance to the target flight start) third stage missile warhead small around missiles timed to target continuous shooting, the third-class missile warhead targets, clear the way, 毁拦截导弹,如无遇到拦截导弹可以直接攻击目标使目标受到创伤,为了后面的第三级导弹弹头重创目标创造有利条件。 Destroy interceptor missiles, such as missile interceptors can not meet the target directly targeted by trauma, in order behind the third-class missile warhead hit the target to create favorable conditions.
CN 201310043273 2013-02-05 2013-02-05 Guided missile with middle-section speed change and anti-intercept method thereof CN103090745A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 201310043273 CN103090745A (en) 2013-02-05 2013-02-05 Guided missile with middle-section speed change and anti-intercept method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN 201310043273 CN103090745A (en) 2013-02-05 2013-02-05 Guided missile with middle-section speed change and anti-intercept method thereof

Publications (1)

Publication Number Publication Date
CN103090745A true true CN103090745A (en) 2013-05-08

Family

ID=48203624

Family Applications (1)

Application Number Title Priority Date Filing Date
CN 201310043273 CN103090745A (en) 2013-02-05 2013-02-05 Guided missile with middle-section speed change and anti-intercept method thereof

Country Status (1)

Country Link
CN (1) CN103090745A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105890470A (en) * 2014-09-12 2016-08-24 王正铉 An intercontinental missile capable of intercepting and attacking land-air-sea targets of enemies midway

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1430720A (en) * 2000-05-25 2003-07-16 斯托姆金属有限公司 Directional control of missiles
CN1525135A (en) * 2003-02-28 2004-09-01 王建钧 Active guiding missile
US20060065150A1 (en) * 2000-01-24 2006-03-30 Metal Storm Limited Anti-missile missiles
CN101055164A (en) * 2000-12-09 2007-10-17 施仲伟 Rocket propulsion enhancing design
CN102661685A (en) * 2012-04-17 2012-09-12 张景军 Interception preventing missile
CN203203482U (en) * 2013-02-05 2013-09-18 朱旭望 Guided missile with variable-speed middle section

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060065150A1 (en) * 2000-01-24 2006-03-30 Metal Storm Limited Anti-missile missiles
CN1430720A (en) * 2000-05-25 2003-07-16 斯托姆金属有限公司 Directional control of missiles
CN101055164A (en) * 2000-12-09 2007-10-17 施仲伟 Rocket propulsion enhancing design
CN1525135A (en) * 2003-02-28 2004-09-01 王建钧 Active guiding missile
CN102661685A (en) * 2012-04-17 2012-09-12 张景军 Interception preventing missile
CN203203482U (en) * 2013-02-05 2013-09-18 朱旭望 Guided missile with variable-speed middle section

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105890470A (en) * 2014-09-12 2016-08-24 王正铉 An intercontinental missile capable of intercepting and attacking land-air-sea targets of enemies midway

Similar Documents

Publication Publication Date Title
US6920827B2 (en) Vehicle-borne system and method for countering an incoming threat
US5509357A (en) Dual operating mode warhead
US7137588B2 (en) Ballistic target defense system and methods
US20080291075A1 (en) Vehicle-network defensive aids suite
US5275110A (en) Vented projectile
Nordeen Air warfare in the missile age
US20110226149A1 (en) Less-than-lethal ammunition utilizing a sustainer motor
Morrow Jr Expectation and reality: The great war in the air
US6640723B2 (en) Mission responsive ordnance
US3126544A (en) Method of deception for an aircraft
CN85107110A (en) Intercepting bomb for defencive purpose
US2986973A (en) Low-recoil, variable-range missile projector
CN101392999A (en) Aeromodelling interception method and device
CN102087082A (en) Firing table fitting-based low-altitude low-speed small object intercepting method
US5363766A (en) Remjet powered, armor piercing, high explosive projectile
US6990885B2 (en) Missile interceptor
US2939395A (en) Sabot for high velocity projectile
FR2721996A1 (en) Missile able to confront defensive armaments as laser guided missile
Lambeth Kosovo and the continuing SEAD challenge
DE3216142C1 (en) Fast-flying projectile with direction-forming charges
CN2684139Y (en) Anti-interception missile
US7795567B2 (en) Guided kinetic penetrator
CN201569357U (en) Simulative laser shooting simulation training system
US20100313741A1 (en) Applications of directional ammunition discharged from a low velocity cannon
Pradun From bottle rockets to lightning bolts: China's missile revolution and PLA strategy against US military intervention

Legal Events

Date Code Title Description
C06 Publication
C10 Entry into substantive examination
C02 Deemed withdrawal of patent application after publication (patent law 2001)