JP2007085627A - Guided missile - Google Patents

Guided missile Download PDF

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Publication number
JP2007085627A
JP2007085627A JP2005274027A JP2005274027A JP2007085627A JP 2007085627 A JP2007085627 A JP 2007085627A JP 2005274027 A JP2005274027 A JP 2005274027A JP 2005274027 A JP2005274027 A JP 2005274027A JP 2007085627 A JP2007085627 A JP 2007085627A
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Japan
Prior art keywords
stage
guided missile
flying
missile
autopilot
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Pending
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JP2005274027A
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Japanese (ja)
Inventor
Yoshihisa Matsuda
良久 松田
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Mitsubishi Electric Corp
三菱電機株式会社
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Priority to JP2005274027A priority Critical patent/JP2007085627A/en
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Pending legal-status Critical Current

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Abstract

The present invention provides a guided missile that does not require the setting of a wide safety zone around the launch point and is not subject to operational restrictions such as changing the launch direction or flight route of the guided missile.
In an N-stage guided missile, each of the M-th stages (M is an integer of 1 to N-1), which is a lower layer to be separated, includes a GPS 103 that detects position information of the guided missile, and a guided missile. The flying calculator 104 that calculates the flying range of guided missiles based on the position information and flying characteristics of the aircraft, and the falling point that selects the falling position within the flying range from the local information that does not cause damage when falling A selection computer 106 and an autopilot 107 that controls flying of the M-th stage after separation toward the selected drop position are provided, and the N-th stage controls the guided missile before separating the lower stage. And an autopilot 207 for controlling the flight after all lower layers are separated.
[Selection] Figure 1

Description

  The present invention relates to a guided missile that intercepts a target, and more particularly, to a guided missile that is configured not to be restricted by a drop point of a lower stage that is separated in a multistage guided missile.

  For example, when a two-stage guided missile is fired, the first stage that is first cut off may fall over a wide area near the launch point. In order to prevent the falling first stage from damaging the ground facilities, it was necessary to set a safe zone and a warning zone around the launch point. Alternatively, when this safety zone cannot be set, it has been necessary to place restrictions on operation, such as changing the launch direction and flight route of guided missiles.

  On the other hand, for example, as a method of solving the above-mentioned problem, the first stage rocket motor after being separated is dispersed into fine debris by the mounted gunpowder, and damage to the residents and buildings at the fall point There is a conventional technique for reducing the size (for example, see Patent Document 1). In addition, there is a conventional technique that uses a drag chute to reduce the drop speed of the first stage rocket motor to prevent the occurrence of damage (see, for example, Patent Document 2).

Japanese Patent Laid-Open No. 2002-228400 (first page, FIG. 1) JP 2003-20000 (first page, FIG. 1)

  However, the prior art has the following problems. Although conventional multistage guided missiles have taken measures such as dispersal into fine fragments or reduced drop speed, the separated lower stage has no control over its fall flight path. There is a possibility of falling over a wide range near the launch point. Therefore, it is necessary to set a wide safety zone and a warning area around the launch point where the falling lower stage may cause damage to the ground facilities, or change the launch direction and flight route of the guided missile, etc. The problem of having to restrict operation is basically unresolved.

  The present invention was made in order to solve the above-described problems, and there is no need for a wide safety zone setting around the launch point, and operational restrictions such as changing the launch direction and flight route of the guided missile The aim is to obtain a guided missile that does not receive any settings.

  The guided missile according to the present invention is an N-stage guided missile having first to N-th stages (N is an integer equal to or greater than 2). ~ N-1 (integer) each is the M-th stage GPS that detects the position information of the guided missile and the range of the guided missile to fly based on the position information of the guided missile and the flying characteristics of the guided missile. It has a flight calculator to calculate the M-th stage and a storage unit that stores in advance the area information that will not be damaged when falling as a digital map. The Mth stage drop point selection computer to be selected and the Mth stage that controls the flying of the Mth stage after separation toward the selected drop position after the Mth stage is separated from the main body of the guide missile. M stage The Nth stage, which is equipped with an autopilot, controls the guided missile before separating the lower stage and controls the flight after separating all the lower stages. It is equipped with an eye autopilot.

  According to the present invention, it is possible to continue the flight control for the separated lower tier, and to set a drop point that is set in advance as an area where the occurrence of damage is predicted to be extremely small even if the lower tier falls. By accurately guiding the lower stage, it is possible to suppress damage to residents and buildings near the launch point of the guided missile, there is no need for a wide safety zone around the launch point, and the guided missile It is possible to obtain a guided missile that is not subject to operational restrictions such as changing the launch direction or flight route.

Embodiment 1 FIG.
FIG. 1 is a configuration diagram of a guide missile according to Embodiment 1 of the present invention. FIG. 1 shows a two-stage guided missile having a first stage 100 and a second stage 200. The first stage 100 includes a separation mechanism 101, a separation detector 102, a global positioning system 103 (hereinafter referred to as GPS (Global Positioning System)), a flying calculator 104, a digital map storage unit 105, a drop point selection calculator. 106, an autopilot 107, a changeover switch 108, a steering device 109, a steering blade 110, and a rocket motor 111.

  On the other hand, the second stage 200 includes an autopilot 207, a steering device 209, and a steering blade 210.

  The separation mechanism 101 is a mechanism unit that couples the first stage 100 and the second stage 200 and separates them according to a command from the second stage autopilot 207. The separation detector 102 is a detector that detects that the first stage 100 and the second stage 200 are disconnected. The GPS 103 is a global positioning system for obtaining flight position information of the first stage 100.

  The flight calculator 104 is a calculation unit that calculates its own flight reachable range from self-position information from the GPS 103 and data of its own flight characteristics stored in advance in a storage unit (not shown). The digital map storage unit 105 is a storage unit that stores in advance, as a digital map, regional data that is predicted to cause very little damage even if the first stage 100 falls near the launch point of the guide missile.

  The drop point selection computer 106 is a calculation unit that selects the drop point of the first stage 100 from the information in the digital map storage unit 105 based on the calculation result of the flying computer 104. The autopilot 107 is a control unit that receives a command from the drop point selection computer 106 and guides the first stage 100 to the drop point while referring to self-position information from the GPS 103.

  The changeover switch 108 is switched to the second-stage autopilot 207 side until the first stage 100 and the second stage 200 are separated by the separation detector 102, and only the first stage 100 is disconnected. Is a switching means for switching to the first stage autopilot 107 side.

  The steering device 109 is a steering control unit that drives the steering blade 110 based on a command from the autopilot 107 or the autopilot 207 connected by switching the changeover switch 108. Furthermore, the rocket motor 111 is a rocket motor provided in the first stage 100.

  On the other hand, the autopilot 207 of the second stage 200 is a control unit that performs the flight control calculation both in the state where the first stage 100 and the second stage 200 are combined and in the state where only the second stage 200 is present. Further, the steering device 209 is a steering control unit that drives the steering blade 210 based on a command from the autopilot 207.

  FIG. 2 is a schematic diagram showing the operation of the guided missile in the first embodiment of the present invention. The two-stage guided missile launched from the launcher 11 of the guided missile will cause the second stage 200 to fly toward the target 12 to be intercepted, and damage will occur even if it falls near the launch point of the guided missile The state where the first stage 100 after separation is flying toward the selectable fall region 13 that is predicted to be extremely small is shown.

  Next, the operation will be described. FIG. 3 is a diagram showing an outline of the operation of the guide missile according to Embodiment 1 of the present invention. The first stage 100 and the second stage 200 of the two-stage guided missile are launched in a combined state. Thereafter, when the combustion of the rocket motor 111 at the first stage 100 is completed, the first stage 100 is separated by the separation mechanism 101 that has received a command from the autopilot 207 at the second stage 200.

  The second stage 200 continues to fly toward the target 12, but the first stage 100, after the combustion of the rocket motor 111 of the first stage 100 is finished, starts dropping after being disconnected. Here, if the first stage 100 falls freely as it is, there is a possibility of damaging the facilities on the ground. Therefore, the flight computer 104 installed in the first stage 100 uses the information on the self-location detected by the installed GPS 103 and the data of its own flight characteristics to determine its own flight reachable range. calculate.

  In the vicinity of the launch point of the guided missile, data of the selectable fall region 13 that is predicted to be extremely small in damage even if the first stage 100 falls is stored in advance in the digital map storage unit 105 as a digital map. Therefore, the drop point selection computer 106 is based on the calculation result of the flight computer 104, and the selectable fall area where damage is predicted to be extremely small even if the first stage 100 falls within a certain flight reachable range. The point closest to 13 or the point that can be reached in the shortest time is selected as an appropriate drop point.

  Further, the autopilot 107 of the first stage 100 receives the command of the selected drop point from the drop point selection computer 106, and refers to the self-position data from the GPS 103, and the separated first stage guide missile. The guidance calculation for guiding to the drop point is performed, and the first stage missile is guided by the steering device 109 and the steering blade 110.

  According to the first embodiment, the first stage is accurately guided to the preset drop point by providing the first stage to be separated with a means capable of flying control after being separated from the main body. it can. This makes it possible to prevent damage to the residents and buildings near the launch point of the guided missile, there is no need for a wide safety zone around the launch point, and the launch direction and flight of the guided missile. It is possible to obtain a guided missile that is not subject to operational restrictions such as changing the glide route.

Embodiment 2. FIG.
FIG. 4 is a configuration diagram of the guide missile according to the second embodiment of the present invention. In the second embodiment, the two-stage guided missile in the first embodiment is expanded to a three-stage guided missile, and is composed of a first stage 100, a second stage 200, and a third stage 300. The first stage 100 and the second stage 200 in FIG. 4 have the same configuration as the first stage 100 shown in FIG. Further, the third stage 300 in FIG. 4 has the same configuration as the second stage 200 shown in FIG.

  Here, the third stage autopilot 307 is in a state where the first stage 100, the second stage 200, and the third stage 300 are coupled, the first stage 100 is disconnected, and the second stage 200 and the third stage 300 are connected. The flight control calculation is performed in a state in which the first stage 100 and the second stage 200 are both separated and only the third stage 300 is obtained.

  In this way, when the third-stage autopilot 307 performs overall control, for example, the first-stage 100 separation mechanism 101 separates the first-stage according to a command from the third-stage autopilot 307. Further, the first-stage changeover switch 108 is switched to the third-stage autopilot 307 side until the first-stage 100 and the second-stage 200 are separated by the separation detector 102, and the first-stage changeover switch 108 is disconnected. When only 100 is reached, switch to the first-stage autopilot 107 side. The same applies to the second stage.

  As a result, the steering device 109 of the first stage 100 to be separated is controlled by the third stage autopilot 307 before being separated from the main body, and after being separated from the main body, it is controlled by the autopilot 107 it has. The Similarly, the steering device 209 of the second stage 200 to be separated is controlled by the third stage autopilot 307 before being separated from the main body, and after being separated from the main body, it is controlled by its own autopilot 207. The As a result, the first stage 100 and the second stage 200 after separation can continue to be controlled.

  FIG. 5 is a schematic diagram showing the operation of the guided missile in the second embodiment of the present invention. The three-stage guided missile launched from the launcher 11 of the guided missile will cause the third stage 300 to fly toward the target 12 to be intercepted, and damage will occur even if it falls near the launch point of the guided missile. The state of the first stage 100 and the second stage 200 after being separated is shown flying toward the selectable fall region 13 that is predicted to be extremely small.

  According to the second embodiment, in the N-stage guided missile (N is an integer of 3 or more), each of the 1st to (N-1) -th stages, which are the lower-stage stages to be separated, is a means capable of continuing flight control. 1 to (N-1) stage can be accurately guided to the drop point set in advance. This makes it possible to prevent damage to the residents and buildings near the launch point of the guided missile, there is no need for a wide safety zone around the launch point, and the launch direction and flight of the guided missile. It is possible to obtain a guided missile that is not subject to operational restrictions such as changing the glide route.

  In the above-described embodiment, the case where the N-stage autopilot performs the overall control of the lower stage in the N-stage guided missile (N is an integer of 3 or more) has been described. It is not limited. For example, in a three-stage guided missile, the separation mechanism 101 in the first stage 100 is not moved from the instruction from the third-stage autopilot 307, but by the instruction from the second-stage autopilot 207 one stage up. It is also possible to separate the eyes.

  Furthermore, the first-stage selector switch 108 is not the third-stage autopilot 307 but the second-stage upper stage until the first-stage 100 and the second-stage 200 are separated by the separation detector 102. When switching to the autopilot 207 side and being cut off to become only the first stage 100, it is also possible to switch to the first stage autopilot 107 side.

  In the above description, the drop point selection computer 106 has described the case where the nearest point or the point that can be reached in the shortest time is selected as an appropriate fall point within the flight reachable range. It is not limited. For example, by assigning priorities to selectable fall areas in advance, it is possible to select the position with the highest priority within the flight reachable range as the drop point.

It is a block diagram of the guidance missile in Embodiment 1 of this invention. It is a schematic diagram which shows the operation | movement of the guidance missile in Embodiment 1 of this invention. It is a figure which shows the operation | movement outline | summary of the guidance missile in Embodiment 1 of this invention. It is a block diagram of the guidance missile in Embodiment 2 of this invention. It is a schematic diagram which shows the operation | movement of the guidance missile in Embodiment 2 of this invention.

Explanation of symbols

  11 Launcher of guided missile, 12 target, 13 selectable fall area, 100 1st stage, 101 separation mechanism, 102 separation detector, 103 global positioning system, 104 flight calculator, 105 digital map storage unit, 106 Drop point selection computer, 107 Autopilot, 108 changeover switch, 109 Steering device, 110 Steering blade, 111 Rocket motor, 200 2nd stage, 201 Separation mechanism, 202 Detach detector, 203 Global positioning system, 204 Computer, 205 Digital map storage unit, 206 Drop point selection computer, 207 Autopilot, 208 changeover switch, 209 Steering device, 210 Steering blade, 211 Rocket motor, 300 3rd stage, 307 Autopilot, 309 Steering device, 310 Steering blade .

Claims (2)

  1. In the N-stage guided missile having the first stage to the N-th stage (N is an integer of 2 or more),
    Each of the M-th stages (M is an integer of 1 to N-1) which is a lower layer to be separated,
    M-th stage GPS for detecting the position information of the guide missile;
    An M-th stage flying calculator for calculating a flying possible range of the guided missile based on position information of the guided missile and flying characteristics of the guided missile;
    A M-th stage drop point selection that has a storage unit that stores in advance a digital map of area information that does not cause damage when dropped, and selects a fall position within the possible flying range from the area information of the digital map A calculator,
    An M-th stage autopilot for controlling the flying of the M-th stage after separation toward the selected drop position after the M-th stage is separated from the main body of the guide missile;
    The Nth stage to fly toward the target is
    The guided missile is equipped with an N-th stage autopilot that controls the missile before it is separated from the lower stage and controls the flight after all the lower stages are separated.
  2. The guided missile of claim 1,
    The drop point selection computer, when selecting the fall position within the flying range from the area information of the digital map, the fall position that can reach the position information of the guided missile in the nearest or the shortest time A guided missile characterized by selecting a position.
JP2005274027A 2005-09-21 2005-09-21 Guided missile Pending JP2007085627A (en)

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JP2005274027A JP2007085627A (en) 2005-09-21 2005-09-21 Guided missile

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JP2005274027A JP2007085627A (en) 2005-09-21 2005-09-21 Guided missile

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009190593A (en) * 2008-02-15 2009-08-27 Mitsubishi Heavy Ind Ltd Spacecraft system
JP2010516989A (en) * 2007-01-18 2010-05-20 レイセオン カンパニー Scalable electronics architecture
CN106081140A (en) * 2016-07-13 2016-11-09 西藏长源动力科技有限公司 Unmanned plane automatic pilot installing rack penetrated by a kind of big gun

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010516989A (en) * 2007-01-18 2010-05-20 レイセオン カンパニー Scalable electronics architecture
JP2009190593A (en) * 2008-02-15 2009-08-27 Mitsubishi Heavy Ind Ltd Spacecraft system
CN106081140A (en) * 2016-07-13 2016-11-09 西藏长源动力科技有限公司 Unmanned plane automatic pilot installing rack penetrated by a kind of big gun

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