JP2013221660A - Aircraft defense device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an aircraft defense device and aircraft defending method, for defending an aircraft from a rear threat, in which a probability of destroying the threat is enhanced.SOLUTION: An aircraft defense device is equipped with a missile that flies using an initial velocity received from an aircraft at the time of release from the aircraft. The missile includes a seeker that locks on a flying object behind the missile, a steering blade, a steering device that drives the steering blade so that the missile and the flying object may get relatively close, and a warhead 37 that disperses a plurality of fragments 53 towards the rear side of the missile in a cone-shaped form.

Description

  The present invention relates to an aircraft defense device and an aircraft defense method.

  In recent years, air-to-air missiles (AAMs) mounted on aircraft have been able to launch not only forward targets but also side targets due to improved aircraft turning capabilities and expanded seeker vision. Regarding the backward target, the idea of a missile launched backward from its own aircraft has existed for a long time. However, missiles that are launched rearward have a problem that it is difficult to control the movement of the aircraft because the airspeed temporarily becomes zero after launch, and have not yet been put into practical use.

  Therefore, the enemy aircraft behind cannot be excluded, and attacks using missiles or fixed armament by enemy aircraft behind are a great threat. As a defense method against a missile that attacks the aircraft from behind, a method of deceiving the missile by using flare, chaff, or ECM (Electronic Counter Measurements) is used. However, in recent years, the identification ability of seekers mounted on missiles has improved, making it difficult to deceive missiles.

  FIG. 1 shows a rear target anti-air missile 102 described in Patent Document 1 as a technique related to the present invention. The missile 102 includes a control wing 104 and a TVC (Thrust Vector Control) device 107. The control wing 104 is provided in the front trunk portion 103 of the missile 102, and the TVC device 107 is provided in the tail portion of the missile 102. The nozzle 108 of the main rocket motor of the TVC device 107 is covered with a removable dome 106.

  When a threat such as an enemy fighter or missile approaching from behind the aircraft occurs, the missile 102 is dropped backward from the aircraft. After the dropping, until the speed of the missile 102 drops to a certain speed, the missile 102 flies stably in the speed direction of its own aircraft by steering the control wing 104. When the speed of the missile 102 drops to a certain speed, the main rocket motor of the TVC device 107 is ignited. The jet flow from the nozzle 108 generates a thrust force that separates the dome 106 in the speed direction of the own machine and accelerates the missile 102 in the direction opposite to the speed direction of the own machine. Thereafter, the control wing 104 is used as a front wing, and the guidance and control of the missile 102 is executed by a combination of steering by the front wing 104 and TVC by the TVC device 107.

  Since the TVC device 107 is installed, it is considered that the missile 102 can ensure a certain degree of airframe movement ability even when the airspeed is zero. However, if the TVC device 107 is mounted, it is difficult to reduce the size of the missile 102, and it is considered that a large number of missiles 102 cannot be mounted on the own aircraft.

  Patent Document 2 discloses an aircraft defense device. Aircraft defense devices are used when threats such as enemy fighters and missiles approaching from behind the aircraft occur, and have a flying object that uses the initial speed received from the aircraft when released from the aircraft. To do. The flying object includes a seeker that locks on a flying object behind the flying object, a steering wing, and a steering device that drives the steering wing so that the flying object and the flying object are relatively close to each other. In order to fly using the initial speed received from the aircraft, the flying object does not need to have a propulsion device. Therefore, the flying object can be reduced in size, and a large number of flying objects can be mounted on the aircraft.

JP-A-6-341798 JP 2012-21754 A

  An object of the present invention is to increase the probability of destroying a threat in an aircraft defense device and an aircraft defense method for protecting an aircraft from a rear threat.

  The means for solving the problem will be described below using the numbers used in the (DETAILED DESCRIPTION). These numbers are added to clarify the correspondence between the description of (Claims) and (Mode for Carrying Out the Invention). However, these numbers should not be used to interpret the technical scope of the invention described in (Claims).

  The aircraft defense device according to the present invention includes a flying body (30) that uses the initial speed received from the aircraft when released from the aircraft (10). In the flying object, the seeker (33) that locks on the flying object (80) behind the flying object, the steering wing (40), and the flying object and the flying object relatively approach each other. Thus, the steering device (39) for driving the steering wing and the warhead (37) for scattering a plurality of fragments (53) conically toward the rear of the flying body.

  The plurality of fragments are preferably made of metal.

  The warhead is composed of a frustum (51) formed into a frustum or a cone with a narrow rear side of the flying body, and a bullet (52) disposed on the rear side of the flying body with respect to the glaze. It is preferable to provide. It is preferable that when the warhead detonates, the bullets are crushed to generate the plurality of fragments.

  The aircraft defense method according to the present invention includes a step of releasing a flying body (30) having a seeker (33) for locking on a flying object (80) behind the aircraft (10), and when released from the aircraft The flying object relatively approaching the flying object while flying using the initial velocity received from the aircraft, and the flying object after the flying object relatively approaches the flying object A body warhead (37) scatters a plurality of fragments (53). In the step of releasing the flying object from the aircraft, the flying object is released in a posture in which the seeker faces the rear of the aircraft. The step of relatively approaching the flying object to the flying object includes a step of driving a steering wing (40) of the flying object based on a signal output from the seeker. In the step in which the warhead scatters the plurality of fragments, the plurality of fragments are scattered in a conical shape toward the rear of the flying body.

  ADVANTAGE OF THE INVENTION According to this invention, the probability of destroying a threat can be raised in the aircraft defense apparatus and the aircraft defense method for protecting an aircraft from a back threat.

FIG. 1 is a schematic view of a conventional rear target anti-air missile. FIG. 2 is a conceptual diagram of the aircraft defense device and the aircraft defense method according to the first embodiment of the present invention. FIG. 3 is a block diagram of a flying object discharge apparatus provided in the aircraft defense apparatus according to the first embodiment. FIG. 4 is a perspective view of a flying body provided in the aircraft defense device according to the first embodiment. FIG. 5 is a schematic view showing the structure of a flying warhead. FIG. 6 is a conceptual diagram showing a fragment scattering pattern at the time of warhead detonation. FIG. 7 is a conceptual diagram of a flying object destruction mechanism caused by fragments. FIG. 8 is a conceptual diagram of another destruction mechanism of a flying object by fragments.

  With reference to the accompanying drawings, a mode for carrying out an aircraft defense device and an aircraft defense method according to the present invention will be described below.

(First embodiment)
Referring to FIG. 2, the aircraft defense device according to the first embodiment of the present invention is used to protect a flying aircraft 10 from a backward threat such as a flying object 80. Hereinafter, although the case where the flying object 80 is an air-to-air missile (AAM) will be described, the flying object 80 may be a flying object other than AAM such as an enemy aircraft. The aircraft 10 includes a tail 11 and a body tail (fuselage tail) 10a. Although the aircraft 10 is shown as a fighter in the figure, the aircraft 10 may be a transport aircraft or a patrol aircraft.

  The aircraft defense device according to the first embodiment includes a flying object discharge device 20 and a flying object 30. The flying object discharge device 20 is provided in the body tail part 10a. The flying object 30 is discharged from the aircraft tail 10a by the flying object discharge device 20.

  Referring to FIG. 3, the flying object discharge device 20 includes a discharge mechanism 21. Hereinafter, although the case where the flying body 30 is released from the release mechanism 21 provided in the body tail portion 10a will be described, the release mechanism 21 may be provided in the pylon or the fuselage body of the aircraft 10.

  Referring to FIG. 4, a flying body 30 includes a fuselage 31, a wing 32, a seeker 33, an autopilot 34, an inertial device 35, a fuze 36, a warhead 37, a servo amplifier 38, and a steering device. 39, a steering blade 40, and a fairing 41. The body 31 has a cylindrical shape with the flying body axis S as an axis. The wing 32 is, for example, a fixed stable wing provided at the rear portion of the body 31. The seeker 33 is provided at the rear part of the body 31 so that the target behind the flying body 30 can be locked on. The autopilot 34, the inertia device 35, the fuse 36, the warhead 37, the servo amplifier 38, and the steering device 39 are provided in the body 31. The steering blade 40 is provided in the steering device 39. The fairing 41 is provided at the tip of the body 31. The steering device 39 drives the steering blade 40. The seeker 33 outputs an acceleration command signal in order to guide the flying object 30 to the target. The inertial device 35 detects the acceleration of the flying object 30 and outputs the detected acceleration. The autopilot 34 outputs a steering angle command based on the acceleration command and the detected acceleration. The servo amplifier 38 controls the steering device 39 so that the steering angle command and the steering angle of the steering blade 40 coincide. That is, the steering device 39 drives the steering blade 40 so that the target on which the seeker 33 is locked on and the flying object 30 are relatively close to each other. The fuze 36 is a proximity fuze and detonates the warhead 37 near the target. The detonated warhead 37 scatters a number of fragments. Fragments destroy targets.

  Since the flying body 30 does not include a propulsion device, the flying body 30 can be downsized. Therefore, a large number of flying bodies 30 can be mounted on the aircraft 10.

  The structure of the warhead 37 will be described with reference to FIG. The warhead 37 has a structure suitable for scattering a plurality of fragments conically toward the rear of the flying body 30. The warhead 37 includes, for example, a spray 51 formed on a frustum (conical frustum or truncated pyramid) having a narrow rear side of the flying body 30 and having the flying body axis S as an axis, and the flying body 30 more than the spray 51. And a bullet 52 arranged on the rear side. The elastic shell 52 has a shape in which a concave portion corresponding to the shape of the medicine 51 is formed in a column body (cylindrical body or prismatic body) having the flying body axis S as an axis. Bullet 52 is made of metal or other material. The glaze 51 is disposed in the concave portion of the spring 52. It is preferable that a lattice-like groove is formed in the bullet 52 so that the warhead 37 is easily crushed when detonated. The structure of the warhead 37 is not limited to the example shown in FIG. The glaze 51 may be formed into a cone (cone or pyramid) with the flying body axis S as the axis and the rear side of the flying body 30 is thin.

  Hereinafter, the aircraft defense method according to the present embodiment will be described.

  The discharge mechanism 21 holds the flying body 30 with the seeker 33 facing the rear of the aircraft 10. When the pilot of the aircraft 10 notices the flying object 80 approaching from behind the aircraft 10, the pilot of the aircraft 10 generates a discharge trigger signal by manual operation. In response to the release trigger signal, the release mechanism 21 releases the flying body 30 in a posture in which the seeker 33 faces the rear of the aircraft 10. That is, the relative speed of the flying object 30 with respect to the aircraft 10 at the moment of release is almost zero.

  Here, since the flying body 30 is released from the body tail portion 10a, the flying body 30 is prevented from colliding with the tail wing 11.

  The flying object 30 may be released after the seeker 33 locks on the flying object 80, and the seeker 33 may lock on the flying object 80 after the release.

  The flying body 30 flies using the initial speed received from the aircraft 10 when released. Based on the signal output from the seeker 33, the steering device 39 moves the steering wing 40 so that the flying object 30 and the flying object 80 relatively approach each other so that the flying object 80 catches up from behind the flying object 30. To drive. Here, the flying body 30 performs autonomous guidance by obtaining the aerodynamic force necessary for the body motion control of the flying body 30 only at the initial speed without using the propulsion device. The flying object 30 approaches the flying object 80 while the velocity is gradually reduced due to air resistance, and detonates the flying object 80 in the vicinity of the flying object 80 to destroy the flying object 80. As described above, the aircraft defense device according to the present embodiment protects the aircraft 10 from the rear threat.

  Here, since the flight is performed using the initial speed received from the aircraft 10 when the flying object 30 is released, the airspeed directions of the flying object 30 and the flying object 80 coincide. Therefore, the relative speed between the flying object 30 and the flying object 80 is reduced, and the induction time is increased. Therefore, according to the present embodiment, it is possible to guide the flying body 30 in the vicinity of the flying object 80 as compared with a normal flying body that has a thrust device and flies at an air speed toward the target. It becomes easy.

  The fragment scattering pattern when the warhead 37 detonates will be described with reference to FIG. When the warhead 37 detonates, the bomb 52 is crushed by the combustion of the powder 51 to generate a plurality of fragments 53, and the plurality of fragments 53 are directed toward the rear of the flying object 30 with the flying object axis S as the axis. It is scattered in a conical shape. The flying object 80 is destroyed by the scattered fragment 53. In addition, when the bomb 52 is made of metal, a metal fragment 53 is generated.

  With reference to FIG. 7, the destruction mechanism of the flying object 80 by the fragment 53 is demonstrated. The flying object 80 is destroyed by colliding the fragment 53. By scattering the plurality of fragments 53 toward the rear of the flying object 30, the average value of the relative speed between the fragment 53 and the flying object 80 increases, and the destructive force due to the collision of the fragments 53 can be increased. In particular, the effect of destroying the tip of the flying object 80 on which the seeker is mounted can be enhanced. Further, by scattering the fragments 53 in a conical shape, it takes longer for the fragments 53 to be densely present on the traveling extension line of the flying object 80 than when the same number of fragments 53 are scattered in a spherical shape. The probability that the flying object 80 collides can be increased. That is, the probability of destroying the flying object 80 can be increased by scattering the plurality of fragments 53 conically toward the rear of the flying body 30.

  With reference to FIG. 8, the other destruction mechanism of the flying object 80 by the fragment 53 is demonstrated. When the plurality of fragments 53 are made of metal and the flying object 80 includes a radar proximity fuze and warhead, the radar proximity fuze of the flying object 80 is made of metal before the flying object 80 approaches the aircraft 10. The radar reflected wave reflected by the fragment 53 is detected and the warhead of the flying object 80 is detonated. Compared with the case where the same number of metal fragments 53 are scattered in a spherical shape by scattering the metal fragments 53 in a conical shape toward the rear of the flying body 30, the metal fragments 53 are formed on the flying object 80. The time of being densely present on the traveling extension line becomes longer, and the probability that the warhead of the flying object 80 is detonated by the radar reflected wave reflected by the metal fragment 53 can be increased.

  The aircraft defense device and the aircraft defense method according to the present invention have been described above with reference to the embodiments. However, the aircraft defense device and the aircraft defense method according to the present invention are not limited to the above embodiments. It is possible to add a change to the said embodiment. For example, the flying object discharge device 20 may automatically release the flying object 30.

DESCRIPTION OF SYMBOLS 10 ... Aircraft 10a ... Aircraft tail part 11 ... Tail 20 ... Flying object discharge device 21 ... Release mechanism 22 ... Backward warning sensor 23 ... Calculation part 30 ... Flying object 31 ... Body 32 ... Wing 33 ... Seeker 34 ... Autopilot 35 ... Inertial device 36 ... Fuze 37 ... Warhead 38 ... Servo amplifier 39 ... Steering device 40 ... Steering blade 41 ... Fairing 51 ... Splashing 52 ... Strike 53 ... Fragment 60 ... Radar reflected wave S ... Flying body axis 102 ... Back target Anti-aircraft missile 103 ... Front trunk 104 ... Control blade 106 ... Dome 107 ... TVC device 108 ... Propulsion nozzle

Claims (4)

Comprising a flying object that uses the initial speed received from the aircraft when released from the aircraft;
The flying object is
A seeker that locks on the flying object behind the flying object;
The steering wing,
A steering device that drives the steering wing so that the flying object and the flying object are relatively close to each other;
An aircraft defense apparatus comprising: a warhead that scatters a plurality of fragments in a conical shape toward the rear of the flying body. The aircraft defense apparatus according to claim 1, wherein the plurality of fragments are made of metal. The warhead is
A glaze that is formed into a thin frustum or cone on the rear side of the flying body; and
It is provided with a striking element arranged on the rear side of the flying body rather than the sachet,
The aircraft defense apparatus according to claim 1 or 2, wherein when the warhead detonates, the bullet is crushed to generate the plurality of fragments. Releasing a flying object with a seeker to lock on a flying object behind the aircraft;
The flying object relatively approaching the flying object while flying using the initial speed received from the aircraft when released from the aircraft;
The projectile warhead scatters a plurality of fragments after the projectile is relatively close to the flying object;
In the step of releasing the flying object from the aircraft, the seeker releases the flying object in a posture facing the rear of the aircraft;
The step of the flying body relatively approaching the flying object comprises a step of driving a steering wing of the flying body based on a signal output by the seeker,
In the step of causing the warhead to scatter the plurality of fragments, the plurality of fragments scatter in a conical shape toward the rear of the flying body.

Images