KR102725814B1 - Aircraft rear defense system - Google Patents

Abstract

The present invention relates to a rear defense system for an aircraft for shooting down an enemy aircraft pursuing from the rear or a projectile from an enemy aircraft, comprising: a rear detection radar mounted on the aircraft for detecting an enemy aircraft pursuing from the rear or a projectile from an enemy aircraft; a shooting down missile having a propellant at the rear of the body and configured to shoot down the enemy aircraft; and a rotator for changing the direction of the shooting down missile facing forward to be mounted rearward or facing rearward; and is characterized in that it is possible to preemptively attack or defend against an enemy aircraft pursuing from the rear or a projectile from an enemy aircraft without changing the direction of the aircraft.

Description

AIRCRAFT REAR DEFENSE SYSTEM

The present invention relates to an aircraft rear defense system, and more particularly, to an aircraft rear defense system capable of detecting enemy aircraft pursuing from behind an aircraft or projectiles from enemy aircraft and attacking or defending against them.

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

As battlefields expand due to the development of combat technology, the ability to first discover and attack targets outside of enemy threats is becoming more important. However, looking at the air combat capabilities of current domestically produced fighter jets, it is difficult to meet such capabilities.

In this regard, Japanese Patent No. 2640905 discloses a rear-targeting anti-aircraft missile capable of shooting down aircraft at the rear. The above-mentioned prior art patent document discloses a rear-targeting anti-aircraft missile including a missile forward body, a control wing or fixed wing for performing a stable flight with respect to its own speed direction until the speed decreases after release, and a TVC device covered with a detachable dome at the tail of the missile for accelerating in the direction opposite to its own speed direction after confirmation of the speed decrease.

In this way, in the past, many prior literatures have been proposed regarding devices attached to aircraft to defend the rear, but there is a disadvantage in that missiles for rear defense always face rearward and cannot be used for forward attacks.

Japanese Patent No. 2640905

In order to overcome the above-mentioned shortcomings, the present invention aims to provide a rear defense system for an aircraft capable of detecting a rear enemy or a projectile from an enemy aircraft from a radar mounted on the rear of the aircraft and changing the direction of a missile mounted on the aircraft.

In order to achieve the above object, the present invention provides a rear defense system for an aircraft for shooting down an enemy aircraft pursuing from the rear or a projectile from an enemy aircraft, comprising: a rear detection radar mounted on the aircraft for detecting an enemy aircraft pursuing from the rear or a projectile from an enemy aircraft; a shooting down missile having a propellant at the rear of the body and configured to shoot down the enemy aircraft; and a rotator for changing the direction of the shooting down missile facing forward to be mounted rearward or facing rearward; characterized in that it is possible to preemptively attack or defend against an enemy aircraft pursuing from the rear or a projectile from an enemy aircraft without changing the direction of the aircraft.

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

Preferably, the rotator can change the direction of the interception missile to face rearward when the rear-looking radar detects an enemy.

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

Preferably, the rotator may include a rotating part having a pillar shape, one side of the pillar being vertically connected to the lower part of the aircraft and configured to be rotatable 180 degrees or 360 degrees; and a mounting part having a disc shape, the upper side of the disc being connected to one side of the rotating part and configured to be rotatable together with the rotating part, and the shooting-down missile being mounted on the lower side of the disc.

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

In addition, the present invention has an advantage in that it can attack backwards while the aircraft is facing forward, instead of attacking backwards by using a rotator.

Figure 1 shows an example of a rear defense missile loading of 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.
FIG. 3 shows an example of a rear detection radar according to an embodiment of the present invention mounted on the rear of an aircraft.
FIG. 4 shows a rotator equipped on 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 contents described in the attached drawings. However, the present invention is not limited or restricted by the exemplary embodiments. The same reference numerals presented in each drawing represent components that perform substantially the same function.

The purpose and effect of the present invention can be naturally understood or made clearer by the following description, and the purpose and effect of the present invention are not limited to the following description alone. In addition, when explaining the present invention, if it is judged that a detailed description of a known technology related to the present invention may unnecessarily obscure the gist of the present invention, the detailed description will be omitted.

Fig. 1 shows an example of rear defense of an aircraft rear defense system (10) according to an embodiment of the present invention. Referring to Fig. 1, the aircraft rear defense system (10) can shoot down an enemy aircraft pursuing from the rear or a projectile from an enemy aircraft. The aircraft rear defense system (10) can preemptively attack an enemy aircraft pursuing from the rear or a projectile from an enemy aircraft without changing the direction of the aircraft (1).

The aircraft rear defense system (10) can change the direction of a missile mounted forward to the rear of the aircraft (1) by using a directional mounting or rotator. The aircraft rear defense system (10) can reverse propulsion a missile toward an enemy aircraft chasing 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 aircraft chasing at close range in an air battle and improve the survivability of the aircraft (1).

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

The rear detection radar (100) is mounted on the aircraft (1) and can detect an enemy at the rear. The rear detection radar (100) is mounted on the aircraft (1) and can detect an approaching enemy or a projectile from an enemy. 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.

FIG. 3 shows an example in which a rear detection radar (100) according to an embodiment of the present invention is mounted on the rear of an aircraft (1). Referring to FIG. 3, the rear detection radar (100) can be mounted on the rear of the aircraft (1). The rear detection radar (100) is mounted on the rear of the aircraft (1) so that even when the aircraft (1) is facing forward, it can detect an enemy aircraft pursuing from behind or a projectile from an enemy aircraft. The rear detection radar (100) is mounted on the rear of the aircraft (1) so that it can intensively detect an enemy aircraft approaching from behind or a projectile from an enemy aircraft. 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) can 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. The rear detection radar (100) can apply beamforming technology.

The rear detection radar (100) can detect an enemy pursuing from the rear and transmit the corresponding information to the rotator (500). The rear detection radar (100) can provide information on whether an enemy exists at the rear, which serves as a reference for changing direction of the rotator (500).

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

The interception missile (300) can be directed toward the front of the aircraft (1) to intercept enemy aircraft, enemy forces, etc. that appear in front in normal times. The interception missile (300) can be directed toward the rear of the aircraft (1) by the pilot's operation of the rotator (500) to intercept enemy aircraft that appear in the rear. When the rear detection radar (100) detects an enemy, the interception missile (300) can be directed toward the rear of the aircraft (1) by automatically operating the rotator (500).

If the interception 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 the relative speed is small, making it difficult to intercept the enemy aircraft. If the interception missile (300) is launched toward the rear of the aircraft (1) to intercept an enemy aircraft in the rear, it moves in the opposite direction as the enemy aircraft, so the relative speed is large, making it easy to intercept the enemy aircraft. In other words, unlike missiles of general fighter aircraft that only attack forward, the interception missile (300) has an advantage in terms of relative speed by attacking backward while the aircraft (1) is facing forward.

The interception missile (300) may include missile control fins. The interception missile (300) may have its speed reduced during free fall by the missile control fins. The interception missile (300) may detect and intercept the enemy by calculating the position and direction of the enemy through radar. In other words, the interception missile (300) may be configured as a guided missile.

FIG. 4 shows a rotator (500) equipped on an aircraft (1) according to an embodiment of the present invention. Referring to FIG. 4, the rotator (500) can change the direction of a forward-facing missile (300) to be mounted or facing rearward. The rotator (500) can change the direction of a forward-facing missile (300) to the opposite direction, thereby creating a state in which an enemy pursuing from the rear can be attacked first. The rotator (500) can provide an advantage in terms of relative speed by allowing the missile (300) to be reverse-propelled in the opposite direction to the direction of the aircraft (1).

The rotator (500) may be installed at the bottom of the aircraft (1). The rotator (500) may be installed inside the aircraft (1). When the rotator (500) is installed inside the aircraft (1), it can change the direction of the shooting down missile (300) to the rear and then cause the shooting down missile (300) to fall freely. Here, the freely fallen shooting down missile (300) can intercept the enemy by the operation of the propellant coupled to the rear.

The rotator (500) can change the direction of the shooting missile (300) manually or automatically. The rotator (500) can change the direction of the shooting missile (300) by the pilot's operation. The rotator (500) can automatically change the direction of the shooting missile (300) depending on the presence of an enemy aircraft at the rear.

The rotator (500) can change the direction of the interception missile (300) to face rearward when the rear detection radar (100) detects an enemy. The rotator (500) can automatically change the direction of the interception missile (300) to face rearward without manual operation of the pilot when an enemy is detected at the rear. The rotator (500) can change the direction of the interception missile (300) to face forward when the rear detection radar (100) does not detect an enemy. That is, the rotator (500) can automatically change the direction of the interception missile (300) to face forward so that it can attack an enemy at the front when there is no enemy at the rear.

Fig. 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) may have a column shape, and one side of the column may be configured to be vertically connected to the lower part of the aircraft and rotate 180 degrees or 360 degrees. The rotating part (510) may be configured in a column shape to connect the aircraft (1) and the mounting part (520). The rotating part (510) may be configured in a cylindrical shape, but is not limited thereto, and may have any shape that is easy to design or manufacture.

The rotating part (510) can rotate 180 degrees when the shooting missile (300) is turned from the front to the rear. The rotating part (510) can rotate in the direction opposite to the original rotation or the rotation when the shooting missile (300) is turned from the rear to the front.

The mounting part (530) has a disc shape, and the upper surface of the disc is configured to be coupled to one surface of the rotating part so as to be able to rotate together with the rotating part (510), and the shooting missile can be mounted on the lower surface of the disc. The mounting part (530) can be configured so that the shooting missile (300) can be mounted and can be separated and launched in an emergency. The mounting part (530) can have a disc shape so as to be easily rotated according to the rotation of the rotating part (510), but is not limited thereto. The shape of the mounting part (530) can vary depending on the ease of design or manufacturing.

The mounting part (530) may include a binding module on which a shooting missile (300) is mounted on the lower surface. The binding module may release the binding of the shooting missile (300) when the missile is launched, thereby allowing it to fall freely.

Although the present invention has been described in detail through representative examples 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. Therefore, the scope of the rights of the present invention should not be limited to the described embodiments, but should be determined by all changes or modifications derived from the claims and equivalent concepts as well as the claims.

1 : Aircraft
10: Rear defense system of aircraft
100 : Rear detection radar
300: Shooting Missiles
500 : Rotator
510 : Rotating part
530 : Mounting part

Claims (5)

In an aircraft rear defense system for shooting down enemy aircraft pursuing from the rear or projectiles from enemy aircraft,
A rear-looking radar mounted on an aircraft to detect enemy aircraft or projectiles from enemy aircraft behind it;
A missile configured to shoot down enemy aircraft by having a propellant at the rear of the body; and
A rotator for changing the direction of the forward-facing missile to be mounted rearward or facing rearward;
The above rear detection radar,
It is mounted on the rear of the aircraft so that beamforming technology can be applied, and calculates the distance and angle to an object approaching the aircraft to provide information on the presence of an enemy at the rear to the rotator.
The above rotator,
Equipped inside the aircraft,
When the above rear detection radar detects an enemy, the direction of the above-mentioned shooting missile is changed to face rearward,
If the above rear detection radar does not detect an enemy, the direction of the above-mentioned interception missile is changed to face forward,
The above rotator,
A rotating part having a pillar shape, one side of the pillar being vertically connected to the lower part of the aircraft and configured to rotate 180 degrees or 360 degrees; and
It has a disc shape, and the upper surface of the disc is connected to one surface of the rotating part so that it can rotate together with the rotating part, and the lower surface of the disc includes a mounting part on which the shooting down missile is mounted;
The above mounting part,
Including a binding module on the lower surface of which the said shooting missile is mounted, so as to cause the shooting missile to fall freely when released;
An aircraft rear defense system characterized by being capable of preemptively attacking or defending against enemy aircraft or projectiles from enemy aircraft tracking from the rear without changing the direction of the aircraft.
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