JP5506581B2 - Aircraft defense device - Google Patents

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.

JP-A-6-341798

  An object of the present invention is to provide 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. And a steering device (39) for driving the steering blade.

  The flying body does not have a propulsion device.

  The aircraft defense device further includes a release mechanism (21) provided in the aircraft tail (10a) of the aircraft. The discharge mechanism discharges the flying body in a posture in which the seeker faces the rear of the aircraft.

  The aircraft defense device further includes a calculation unit (23) provided in the aircraft. The calculation unit automatically outputs a discharge trigger signal. The release mechanism releases the flying object in response to the release trigger signal.

  The aircraft defense device further includes a rear warning sensor (22) provided in the aircraft. The rear warning sensor warns the rear of the aircraft, and includes a relative velocity (V) and a relative distance (L) of the flying object viewed from the aircraft, a velocity vector of the aircraft, and a velocity vector of the flying object. The formed angle (θ) is detected. The calculation unit outputs the discharge trigger signal based on the relative speed, the relative distance, and the angle.

  The flying body includes a warhead (37) or a deception device (45).

  The flying body includes the warhead and the deception device.

  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 speed received from the aircraft. The flying body includes a steering wing (40). 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 the flying body relatively approaching the flying object includes a step of driving the steering wing based on a signal output from the seeker.

  In the step of releasing the flying object from the aircraft, the flying object is released from the aircraft tail (10a) of the aircraft.

  In the step in which the flying object relatively approaches the flying object, an aerodynamic force necessary for controlling the flying object's body motion is obtained only by the initial speed.

  In the step of releasing the flying object from the aircraft, the flying object is automatically released.

  The aircraft defense method detects a relative speed (V) and a relative distance (L) of the flying object viewed from the aircraft, and an angle (θ) formed by the velocity vector of the aircraft and the velocity vector of the flying object. And a step of automatically outputting a discharge trigger signal based on the relative velocity, the relative distance, and the angle. In the step of releasing the flying object from the aircraft, the flying object is released in response to the emission trigger signal.

  In the step of outputting the discharge trigger signal, the discharge trigger signal is output when the relative speed, the relative distance, and the angle satisfy the flying object discharge condition. The aircraft defense method further includes the step of changing the flying object emission condition based on characteristics of the flying object or environmental conditions around the aircraft.

  ADVANTAGE OF THE INVENTION According to this invention, the aircraft defense device and the aircraft defense method for protecting an aircraft from a back threat are provided.

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 perspective view of a flying body provided in an aircraft defense device according to the second embodiment of the present invention. FIG. 6 is a block diagram of a flying object discharge apparatus provided in an aircraft defense apparatus according to the third embodiment of the present invention. FIG. 7 is a conceptual diagram of an aircraft defense method according to the third embodiment.

  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)
With reference 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 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. The target is destroyed by a fragment in the air.

  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.

  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.

(Second Embodiment)
With reference to FIG. 5, the aircraft defense apparatus and the aircraft defense method according to the second embodiment of the present invention will be described. The aircraft defense device and the aircraft defense method according to the present embodiment are the same as the aircraft defense device and the aircraft defense method according to the first embodiment except for the following description. The flying body 30 according to the present embodiment includes a deception device 45 instead of the warhead 37 and the fuze 36. The deception device 45 is a flare emission device, a chaff emission device, or an ECM (Electronic Counter Measurements) device. While the flying object 30 is flying, the deception device 45 fires a flare, fires a chaff, or outputs an ECM (Electronic Counter Measurements). Here, the ECM is a radio wave that simulates a reflected wave reflected from the aircraft 10 by the radio wave output from the flying object 80.

  According to the present embodiment, by guiding the flying body 30 having the deception device 45 to the vicinity of the flying object 80, the signal / noise characteristics of the seeker mounted on the flying object 80 can be deteriorated. According to the present embodiment, a signal radiation source that deceives the flying object 80 as compared with a normal deception method in which a flare is emitted from a deception device mounted on the aircraft 10, a chaff is emitted, or an ECM is output. Since the distance between the reflection source and the flying object 80 can be shortened, the deception effect is increased.

  Note that all of the deception device 45, the warhead 37, and the fuze 36 may be mounted on the flying body 30. In this case, since the flying object 80 is guided to the flying object 30 or the vicinity thereof by the deception device 45, the possibility of destroying the flying object 80 by the explosion of the warhead 37 can be increased.

(Third embodiment)
The aircraft defense device and the aircraft defense method according to the third embodiment of the present invention are the same as the aircraft defense device and the aircraft defense method according to the first or second embodiment except for the following description. In the present embodiment, the flying object discharge device 20 automatically releases the flying object 30.

  With reference to FIG. 6, the flying object ejection device 20 according to the present embodiment includes a rear warning sensor 22 and a calculation unit 23 in addition to the ejection mechanism 21.

  Referring to FIG. 7, the rear warning sensor 22 warns behind the aircraft 10, detects the approach of the rear flying object 80, and tracks the flying object 80. The rear warning sensor 22 detects a relative speed V and a relative distance L of the flying object 80 viewed from the aircraft 10 and an angle θ formed by the speed vector of the aircraft 10 and the speed vector of the flying object 80.

  The calculation unit 23 performs a condition determination as to whether or not to output a release trigger signal. The computing unit 23 automatically outputs a discharge trigger signal based on the relative speed V, the relative distance L, and the angle θ. The calculation unit 23 outputs a release trigger signal when the relative speed V, the relative distance L, and the angle θ satisfy the flying object release condition. Here, the flying object release condition is set as a condition in which the flying object 30 can relatively approach the flying object 80. For example, the calculation unit 23 outputs a discharge trigger signal when the relative speed V is within the relative speed setting range, the relative distance L is within the relative distance setting range, and the angle θ is within the angle setting range. The release mechanism 21 releases the flying object 30 in response to the release trigger signal output from the calculation unit 23.

  After discharge, until the seeker 33 locks on the flying object 80, the flying object 30 performs inertial guided flight and approaches the flying object 80 roughly. In the inertial guided flight, the steering device 39 drives the steering wing 40 based on the relative speed V, the relative distance L, the angle θ, and the output of the inertia device 35 immediately before the release. After the seeker 33 locks on the flying object 80, the flying object 30 performs guided flight using the seeker 33 as described above and approaches the flying object 80 precisely.

  According to the present embodiment, since the flying body 30 is automatically released, the aircraft 10 can be automatically protected from the flying object 80 without depending on the pilot. In addition, since the computing device 23 outputs a release trigger signal based on the relative speed V, the relative distance L, and the angle θ, the flying object 30 locks on the flying object 80 behind the released object, and the flying object 80 The flying object 30 is released at a timing at which it can relatively approach. Since the flying body 30 is released under appropriate conditions, the effectiveness of the aircraft defense device and the aircraft defense method according to the present embodiment can be enhanced.

  Here, it is preferable that the calculation unit 23 changes the flying object discharge condition based on the characteristics of the target flying object 80 behind and the environmental conditions around the aircraft 10. For example, in the case of rain or snow, the distance over which the seeker 33 can lock on the flying object 80 is shortened, so the calculation unit 23 changes the relative distance setting range based on the environmental conditions around the aircraft 10.

  The present invention is not limited to the above embodiment. It is possible to combine the above-described embodiments or to add various changes to the above-described embodiments. For example, the flying object 80 may be damaged by causing the flying object 80 to directly hit the flying object 30 that does not include either the warhead 37 or the deception device 45.

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 45 ... Deception device 80 ... Flying object V ... Relative speed L ... Relative distance θ ... Angle 102 ... Anti-air missile for rear target 103 ... Front trunk 104 ... Control wing 106 ... Dome 107 ... TVC device 108 ... Propulsion nozzle

Claims (11)

A flying object that uses the initial speed received from the aircraft when released from the aircraft ;
A calculation unit provided in the aircraft and automatically outputting a discharge trigger signal;
A release mechanism provided in the aircraft for releasing the flying object in response to the release trigger signal ;
The flying object is
A seeker that locks on the flying object behind the flying object;
The steering wing,
An aircraft defense apparatus comprising: a steering device that drives the steering wing so that the flying object and the flying object are relatively close to each other. The aircraft defense apparatus according to claim 1, wherein the flying body does not include a propulsion device. The release mechanism is provided in the fuselage tail of the aircraft, before Symbol Seeker aircraft defense device according to claim 1 or 2 to release the flying object in a posture facing the rear of the aircraft. Further comprising a rear warning sensor provided in the aircraft,
The rear warning sensor is used to warn the rear of the aircraft and detect a relative speed and a relative distance of the flying object viewed from the aircraft, and an angle formed between the speed vector of the aircraft and the speed vector of the flying object. ,
The aircraft defense apparatus according to claim 1 , wherein the calculation unit outputs the emission trigger signal based on the relative speed, the relative distance, and the angle. The flying object is any one of the aircraft defense system of claims 1 to 4 comprising a warhead or deception device. The aircraft defense device according to claim 5 , wherein the flying body includes the warhead and the deception device. Releasing a flying object with a seeker to lock on a flying object behind the aircraft;
The flight object relatively approaching the flying object while flying using the initial speed received from the aircraft when released from the aircraft,
The flying object is
With steering wings,
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 the step of driving the steering wing based on a signal output by the seeker ,
An aircraft defense method for automatically releasing the flying object in the step of releasing the flying object from the aircraft. The aircraft defense method according to claim 7 , wherein in the step of releasing the flying object from the aircraft, the flying object is released from a tail part of the aircraft. The aircraft defense method according to claim 7 or 8 , wherein, in the step in which the flying body relatively approaches the flying object, an aerodynamic force necessary for controlling the flying body is controlled only by the initial speed. Detecting a relative velocity and a relative distance of the flying object viewed from the aircraft, and an angle formed by a velocity vector of the aircraft and a velocity vector of the flying object;
Automatically outputting a discharge trigger signal based on the relative velocity, the relative distance, and the angle;
The aircraft defense method according to claim 7 , wherein in the step of releasing the flying object from the aircraft, the flying object is released in response to the emission trigger signal. In the step of outputting the discharge trigger signal, the discharge trigger signal is output when the relative speed, the relative distance, and the angle satisfy the flying object discharge condition,
The aircraft defense method according to claim 10 , further comprising the step of changing the flying object emission condition based on characteristics of the flying object or environmental conditions around the aircraft.

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