KR20230171331A - Aircraft rear defense system - Google Patents

Abstract

The present invention relates to an aircraft rear defense system for shooting down projectiles from enemy aircraft or enemy aircraft pursuing from behind, including a rear detection radar mounted on the aircraft to detect projectiles from enemy aircraft or enemy aircraft from behind; A shoot-down missile configured to shoot down an enemy aircraft by having a propellant at the rear of the body; And a rotator that changes the direction of the forward-facing shootdown missile to be mounted rearward or toward the rear; including, capable of preemptively attacking or defending against a projectile from an enemy aircraft or an enemy aircraft tracking from the rear without changing the direction of the aircraft. It is characterized by

Description

Aircraft rear defense system {AIRCRAFT REAR DEFENSE SYSTEM}

The present invention relates to a rear defense system for an aircraft, which is capable of detecting projectiles from enemy aircraft or enemy aircraft pursuing from behind the aircraft and attacking or defending against them.

Fighter planes are the main means of achieving air superiority, and air superiority is an essential requirement for victory, especially in modern warfare. Fighter jets are relatively small, fast, and maneuverable compared to other military aircraft. In addition, it is optimized for anti-aircraft defense and attack compared to any anti-aircraft weapon or anti-aircraft tank, so most fighters are basically equipped with weapons such as anti-aircraft cannons, machine guns, missiles, or rockets.

As the battlefield expands due to the development of combat technology, the ability to first discover and attack targets outside of the enemy's threat is becoming more important. However, considering the aerial engagement capabilities of current domestic fighter jets, it is difficult to meet such capabilities.

In this regard, Japanese Patent No. 2640905 discloses an anti-aircraft missile for rear targets so as to shoot down flying vehicles in the rear. The above prior patent document refers to the body part before the missile, the control wing or fixed wing for a stable flight in the direction of its own speed until the speed decreases after release, and the tail part of the missile, and the tail part of the missile after confirmation of the decrease in speed. A rear-target anti-aircraft missile is being disclosed that includes a TVC device covered by a detachable dome that accelerates in a direction opposite to the direction of velocity.

As such, in the conventional case, many prior literature have proposed a device attached to an aircraft to defend the rear, but there is a disadvantage that the missile for rear defense always faces the rear and cannot be used for front attack.

Japanese Patent No. 2640905

In order to overcome the above shortcomings, the present invention provides a rear defense system for an aircraft that can detect a rear enemy aircraft or a projectile from an enemy aircraft from a radar mounted at the rear of the aircraft and can change the direction of a missile mounted on the aircraft. The purpose.

In order to achieve the above object, the present invention provides a rear defense system for an aircraft to shoot down a projectile from an enemy aircraft or an enemy aircraft pursuing from behind, comprising: a rear detection radar mounted on the aircraft to detect projectiles from an enemy aircraft or an enemy aircraft from the rear; A shoot-down missile configured to shoot down an enemy aircraft by having a propellant at the rear of the body; And a rotator that changes the direction of the forward-facing shootdown missile to be mounted rearward or toward the rear; including, capable of preemptively attacking or defending against a projectile from an enemy aircraft or an enemy aircraft tracking from the rear without changing the direction of the aircraft. It is characterized by

Preferably, the rear detection radar may be mounted on the rear of the aircraft or on the side of the wing of the aircraft.

Preferably, the rotator can change the direction of the shoot-down missile to face rearward when the rear-view radar detects an enemy aircraft.

Preferably, the rotator can change the direction of the shoot-down missile to face forward when the rear detection radar does not detect an enemy aircraft.

Preferably, the rotator has a pillar shape, and includes a rotating part configured to be rotatable by 180 degrees or 360 degrees by vertically coupling one side of the pillar to the lower part of the aircraft; and a mounting portion that has a disk shape and is configured such that the upper surface of the disk is coupled to one surface of the rotating portion so that it can rotate with the rotating portion, and the shooting down missile is mounted on the lower surface of the disk.

According to the present invention, the rear detection radar has the advantage of being able to detect an enemy aircraft pursuing from behind or a projectile from an enemy aircraft from the front.

Additionally, the present invention has the advantage of being able to attack backwards with the aircraft facing forward instead of tracking the enemy aircraft backwards using a rotator.

Figure 1 shows an example of mounting a rear defense missile in an aircraft rear defense system according to an embodiment of the present invention.
Figure 2 shows a configuration diagram of an aircraft rear defense radar system according to an embodiment of the present invention.
Figure 3 shows an example in which the rear detection radar according to an embodiment of the present invention is mounted on the rear of an aircraft.
Figure 4 shows a rotator provided in an aircraft according to an embodiment of the present invention.
Figure 5 shows a configuration diagram of a rotator according to an embodiment of the present invention.

Hereinafter, the present invention will be described in detail with reference to the accompanying drawings. However, the present invention is not limited or limited by the exemplary embodiments. The same reference numerals in each drawing indicate members that perform substantially the same function.

The purpose and effect of the present invention can be naturally understood or become clearer through the following description, and the purpose and effect of the present invention are not limited to the following description. Additionally, in describing the present invention, if it is determined that a detailed description of known techniques related to the present invention may unnecessarily obscure the gist of the present invention, the detailed description will be omitted.

Figure 1 shows an example of rear defense of the aircraft rear defense system 10 according to an embodiment of the present invention. Referring to FIG. 1, the aircraft rear defense system 10 is capable of shooting down projectiles from enemy aircraft or enemy aircraft pursuing from the rear. The aircraft rear defense system 10 can preemptively attack a projectile from an enemy aircraft or an enemy aircraft tracking from behind without changing the direction of the aircraft 1.

The vehicle rear defense system 10 can change the direction of a missile mounted toward the front by orienting it toward the rear of the vehicle 1 or using a rotator. The aircraft rear defense system 10 can backpropel a missile to shoot down an enemy aircraft pursuing the aircraft 1 or a projectile from an enemy aircraft. The aircraft rear defense system 10 can overcome the speed difference with a high-performance fighter pursuing at close range in an air battle and improve the survivability of the aircraft 1.

Figure 2 shows a configuration diagram of the aircraft rear defense system 10 according to an embodiment of the present invention. Referring to FIG. 2, the aircraft rear defense system 10 may include a rear detection radar 100, a shooting down missile 300, and a rotator 500.

The rear detection radar 100 is mounted on the aircraft 1 and can detect enemy aircraft behind. The rear detection radar 100 is created on the aircraft 1 and can detect approaching enemy aircraft or projectiles from enemy aircraft. The rear detection radar 100 can calculate the distance and angle to an object approaching the aircraft 1. The rear detection radar 100 is designed to have wide-angle coverage and can cover a wide 3D space.

Figure 3 shows an example in which the rear detection radar 100 according to an embodiment of the present invention is mounted on the rear of the aircraft 1. Referring to FIG. 3, the rear detection radar 100 may be mounted on the rear of the aircraft 1. The rear detection radar 100 is mounted on the rear of the aircraft 1 and can detect enemy aircraft pursuing from behind or projectiles from enemy aircraft even when the aircraft 1 is facing forward. The rear detection radar 100 is mounted on the rear of the aircraft 1 and can intensively detect enemy aircraft or projectiles from enemy aircraft approaching from the rear. The rear detection radar 100 can improve rear beam pattern steering and gain by directing the beam toward the rear of the aircraft 1.

The rear detection radar 100 may be mounted on the side of the wing of the aircraft 1. The rear detection radar 100 is mounted on both sides of the wing of the aircraft 1 and can widely detect enemy aircraft approaching from the rear of the aircraft. Beamforming technology may be applied to the rear detection radar 100.

The rear detection radar 100 can detect an enemy aircraft pursuing from behind and transmit the corresponding information to the rotator 500. The rear detection radar 100 can provide information on whether an enemy plane exists behind the rotator 500, which serves as a standard for changing direction.

The shoot-down missile 300 may be configured to shoot down an enemy aircraft by having a propellant at the rear of the body. The shooting down missile 300 may be composed of a missile generally used in fighter aircraft. The shoot-down missile 300 can obtain propulsion through a propellant coupled to the rear. The direction in which the shot down missile 300 is propelled can be changed through the rotator 500. The shooting down missile 300 may be equipped with a missile cap to reduce air resistance.

The shooting down missile 300 can be aimed at the front of the aircraft 1 so as to intercept enemy planes, enemy forces, etc. that appear in front during normal times. The shoot-down missile 300 can be directed to the rear of the aircraft 1 by the pilot's operation of the rotator 500 in order to shoot down an enemy aircraft appearing behind. When the rear detection radar 100 detects an enemy aircraft, the shoot-down missile 300 can automatically operate the rotator 500 and aim at the rear of the aircraft 1.

When the shoot-down missile 300 is launched toward the front of the aircraft 1 to intercept an enemy aircraft in front, it moves in the same direction as the enemy aircraft, so its relative speed is small, making it difficult to intercept the enemy aircraft. When the shoot-down missile 300 is launched to the rear of the aircraft 1 to intercept an enemy aircraft at the rear, the missile 300 moves in the opposite direction to the enemy aircraft, so its relative speed is large, making it easier to intercept the enemy aircraft. In other words, unlike a typical fighter jet missile that only attacks forward, the shoot-down missile 300 has an advantage in terms of relative speed by attacking backward while the flying vehicle 1 is facing forward.

The shot down missile 300 may include missile control fins. The speed of the shot down missile 300 may be reduced during free fall by the missile control blades. The shooting down missile 300 can intercept the enemy aircraft by calculating the position and direction of the enemy aircraft through radar. In other words, the shoot-down missile 300 may be configured as a guided missile.

Figure 4 shows a rotator 500 provided in the aircraft 1 according to an embodiment of the present invention. Referring to FIG. 4, the rotator 500 can change the direction of the forward-facing shootdown missile 300 to be mounted rearward or toward the rear. The rotator 500 can change the direction of the forward-facing missile 300 to the opposite direction to create a state in which the enemy aircraft pursuing from the rear can be attacked first. The rotator 500 can provide an advantage in terms of relative speed by allowing the shot down missile 300 to be propelled in a direction opposite to that of the vehicle 1.

The rotator 500 may be provided at the bottom of the aircraft 1. The rotator 500 may be provided inside the aircraft 1. When provided inside the aircraft 1, the rotator 500 can change the direction of the shot-down missile 300 to the rear and then cause the shot-down missile 300 to fall freely. Here, the free-falling shooting down missile 300 can intercept an enemy aircraft by operating a propellant coupled to the rear.

The rotator 500 can manually or automatically change the direction of the shot down missile 300. The rotator 500 can change the direction of the shot-down missile 300 through the pilot's manipulation. The rotator 500 can automatically change the direction of the shoot-down missile 300 depending on whether there is an enemy aircraft behind.

When the rear detection radar 100 detects an enemy aircraft, the rotator 500 can change the direction of the shoot-down missile 300 to face rearward. When an enemy aircraft from behind is detected, the rotator 500 can automatically change the direction of the shoot-down missile 300 to face rearward without manual manipulation by the pilot. The rotator 500 can change the direction of the shoot-down missile 300 to face forward when the rear detection radar 100 does not detect an enemy aircraft. That is, the rotator 500 can automatically change the direction of the shoot-down missile 300 to face forward so that it can attack the enemy aircraft ahead when there is no enemy aircraft behind.

Figure 5 shows a configuration diagram of a rotator 500 according to an embodiment of the present invention. Referring to FIG. 5 , the rotator 500 may include a rotating part 510 and a mounting part 530.

The rotating part 510 has a pillar shape, and one side of the pillar is vertically coupled to the lower part of the aircraft and can be configured to rotate 180 degrees or 360 degrees. The rotating part 510 may be configured in a pillar shape to connect the aircraft 1 and the mounting part 520. The rotating part 510 may have a cylindrical shape, but is not limited to this and can have any shape as long as it is easy to design or manufacture.

The rotation unit 510 can rotate 180 degrees when the shooting down missile 300 changes from the front to the rear. The rotation unit 510 may rotate in the direction opposite to the existing rotation or rotation when the shooting down missile 300 changes from the rear to the front.

The mounting unit 530 has a disc shape, and the upper surface of the disc is coupled to one surface of the rotating unit so that it can rotate together with the rotating unit 510, and the shoot-down missile can be mounted on the lower surface of the disc. The mounting unit 530 may be configured so that the shootdown missile 300 is mounted and can be separated and launched in case of emergency. The mounting unit 530 may have a disk shape to facilitate rotation according to the rotation of the rotating unit 510, but is not limited thereto. The shape of the mounting portion 530 may vary depending on the ease of design or manufacturing.

The mounting unit 530 may include a binding module on which the shootdown missile 300 is mounted on the lower surface. The binding module can release the binding of the shot down missile 300 and cause it to fall freely when the missile is launched.

Although the present invention has been described in detail through representative embodiments above, those skilled in the art will understand that various modifications can be made to the above-described embodiments without departing from the scope of the present invention. will be. Therefore, the scope of rights of the present invention should not be limited to the described embodiments, but should be determined not only by the claims described later, but also by all changes or modified forms derived from the claims and the concept of equivalents.

1: Air vehicle
10: Aircraft rear defense system
100: Rear detection radar
300: Shoot down missile
500: Rotator
510: rotating part
530: Mounting part

Claims (5)

In the aircraft rear defense system for shooting down projectiles from enemy aircraft or enemy aircraft pursuing from the rear,
A rear-view radar mounted on the aircraft to detect enemy aircraft or projectiles from behind them;
A shoot-down missile configured to shoot down an enemy aircraft by having a propellant at the rear of the body; and
Including a rotator that changes the direction of the forward-facing shootdown missile to be mounted rearward or toward the rear.
An aircraft rear defense system characterized in that it can preemptively attack or defend against projectiles from enemy aircraft or enemy aircraft tracking from the rear without changing the direction of the aircraft.
According to claim 1,
The rear detection radar,
An aircraft rear defense system, characterized in that it is mounted on the rear of the aircraft or on the side of the aircraft wings.
According to claim 1,
The rotator is,
A rear defense system for an aircraft, characterized in that when the rear detection radar detects an enemy aircraft, the direction of the shot down missile is changed to face rearward.
According to claim 3,
The rotator is,
A rear defense system for an aircraft, characterized in that when the rear detection radar does not detect an enemy aircraft, the direction of the shot down missile is changed to face forward.
According to claim 1,
The rotator is,
A rotating part that has a pillar shape and is configured so that one side of the pillar is vertically coupled to the lower part of the aircraft and can rotate 180 degrees or 360 degrees; and
It has a disc shape, the upper surface of the disc is coupled to one surface of the rotating part and is configured to rotate together with the rotating part, and the lower surface of the disc is a mounting part on which the shoot-down missile is mounted. A rear defense system for an aircraft comprising a. .