WO2022196597A1 - Système de destruction de missile guidé - Google Patents

Système de destruction de missile guidé Download PDF

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Publication number
WO2022196597A1
WO2022196597A1 PCT/JP2022/011152 JP2022011152W WO2022196597A1 WO 2022196597 A1 WO2022196597 A1 WO 2022196597A1 JP 2022011152 W JP2022011152 W JP 2022011152W WO 2022196597 A1 WO2022196597 A1 WO 2022196597A1
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WO
WIPO (PCT)
Prior art keywords
aircraft
kill system
hard
hard kill
function
Prior art date
Application number
PCT/JP2022/011152
Other languages
English (en)
Japanese (ja)
Inventor
和男 吉原
Original Assignee
合同会社Ｉｐマネジメント
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 合同会社Ｉｐマネジメント filed Critical 合同会社Ｉｐマネジメント
Publication of WO2022196597A1 publication Critical patent/WO2022196597A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means
    • B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
    • B64C13/18—Initiating means actuated automatically, e.g. responsive to gust detectors using automatic pilot
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
    • B64D7/08—Arrangements of rocket launchers or releasing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft

Definitions

  • the present invention is for physically neutralizing a guided projectile intended to shoot down an aircraft.
  • Patent Document 1 In order to protect military aircraft from guided missiles, a technique has been provided to attract guided missiles to decoys launched from military aircraft (Patent Document 1 below).
  • Flares are used as a means of jamming guided missiles that use infrared for terminal guidance, but in the case of infrared sensors with simultaneous multi-target processing capability, flares are used before the infrared sensors start tracking the target. Without deployment, a real target (aircraft) may be tracked.
  • Chaff is used as a means of jamming guided missiles that use radar guidance for terminal guidance, but a large amount of chaff is required to deceive guided missiles. Also, even if you succeed in deceiving once, you may be caught again.
  • the aircraft is equipped with a hard kill system that shoots nets and projectiles over a wide range.
  • a hard kill system that shoots nets and projectiles over a wide range.
  • the guided projectile hard kill system of the present invention has the function of launching nets or projectiles, and the function of decoupling the hard kill system from the aircraft.
  • a prediction function is provided for calculating the trajectory of the hard kill system after it is separated from the aircraft from the velocity of the aircraft, the acceleration vector, and the attitude of the hard kill system when the hard kill system is separated from the aircraft.
  • the guided missile and the hard kill system are provided with a prediction function that predicts the maneuver of the guided missile from the positions and maneuvers of the aircraft and the guided missile, and based on the trajectory of the hard kill system calculated by the prediction function. has a function to calculate the maneuvering of the colliding aircraft and the release timing of the hard kill system.
  • the hard kill system has an attitude control wing for attitude control and a communication function, communicates with the aircraft by the communication function, and the trajectory of the hard kill system separated from the aircraft calculated by the prediction function and guidance It has a function to adjust the angle of the attitude control wing based on the maneuver of the flying object.
  • it has a transmission function for transmitting the maneuver of the aircraft calculated by the prediction function and the disconnection timing of the hard kill system to the pilot by voice or video.
  • an autopilot function is provided for autopiloting the aircraft based on the maneuvers of the aircraft calculated by the prediction function and the release timing of the hard kill system.
  • the guided projectile hard kill system according to the present invention is suitable for physically neutralizing guided projectiles that could not be deceived by interference means such as flares and chaffs.
  • FIG. 1 is a schematic diagram illustrating a guided projectile hard kill system.
  • the guided missile hard kill system 1 includes a hard kill system 2, an aircraft 3, a proximity fuse 4, an ejection function 5, an attitude control wing 6, a communication function 7, a prediction function 8, a radar 9, a transmission function 10, and an autopilot function 11. Configured.
  • the guided missile hard kill system 1 is composed of a hard kill system 2 equipped with a proximity fuse 4 and ejecting nets and projectiles using an ejection function 5, and an aircraft 3 on which the hard kill system 2 can be mounted. It has a function to disconnect the kill system 2.
  • the aircraft 3 has a prediction function 8, and when the hard kill system 2 is separated from the aircraft 3, the speed of the aircraft 3, the acceleration vector, the attitude of the hard kill system 2, the angle of the attitude control wings 6, etc. are used to predict the hard kill system 2. predict the trajectory of The attitude control wing 6 is a wing provided in the hard kill system 2 for attitude control.
  • the aircraft 3 calculates the movement of the guided projectile 12 by the prediction function 8 from the position and movement of the guided projectile 12 captured by the radar 9 and the maneuver of the aircraft 3, and guides the hard kill system 2 separated from the aircraft 3 into flight. Calculating the maneuvers of the aircraft 3 to impact the body 12 and the timing of decoupling the hard kill system 2 from the aircraft 3 .
  • the hard kill system 2 communicates with the aircraft 3 through the communication function 7 and adjusts the angle of the attitude control wings 6 based on the maneuver of the guided missile 12 calculated by the prediction function 8 and the trajectory of the hard kill system 2 .
  • the prediction function 8 continues to calculate maneuvers of the aircraft 3 in which the hard kill system 2 and the guided projectile 12 collide even after the hard kill system 2 is separated from the aircraft 3 .
  • the hard kill system 2 communicates with the aircraft 3 using the communication function 7, and based on the maneuvers of the guided missile 12 calculated by the prediction function 8, the guided missile 12 and the hard kill system 2
  • the angle of the attitude control wing 6 is adjusted so as to collide.
  • the hard kill system 2 Due to the structure of the aircraft, the hard kill system 2 will be mounted on the bottom of the aircraft 3 . For this reason, in order to bring the hard kill system 2 sufficiently close to the guided missile 12, lift is generated by the attitude control wings 6 of the hard kill system 2. After disconnecting the hard kill system 2, the aircraft 3 is guided by diving. Operations such as guiding the flying object 12 to approach the hard kill system 2 and making the aircraft 3 rise sharply just before the hard kill system 2 is released are required.
  • the attitude control wings 6 may be used for deceleration of the hard kill system 2.
  • the maneuver of the aircraft 3 calculated by the prediction function 8 is transmitted to the pilot by voice or video by the transmission function 10 . Also, it is desirable that the aircraft 4 is automatically piloted by the autopilot function 11 based on the maneuvers of the aircraft 3 calculated by the prediction function 8 .
  • the disconnection timing of the hard kill system 2 calculated by the prediction function 8 is transmitted to the pilot by voice or video by the transmission function 10 . Further, it is desirable that the hard kill system 2 is automatically disconnected by the autopilot function 11 based on the disconnection timing of the hard kill system 2 calculated by the prediction function 8 .
  • the present invention is suitable for physically neutralizing guided projectiles that could not be deceived by interference means such as flares and chaffs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

Le problème décrit par la présente invention est d'utiliser des fusées éclairantes en tant que moyens de brouillage de missiles guidés qui utilisent des rayons infrarouges dans un guidage terminal; cependant, dans le cas de capteurs infrarouges ayant des capacités de traitement multi-cibles simultanées, il existe une possibilité qu'une cible réelle (aéronef) sera suivie si une fusée éclairante n'est pas déployée avant que le capteur infrarouge déclenche un suivi de cible. De plus, les paillettes sont utilisées comme moyen de brouillage de missiles guidés qui utilisent un guidage radar dans un guidage terminal; cependant, une grande quantité de paillettes est nécessaire pour leurrer un missile guidé. Il existe également une possibilité que, même si le leurre réussit une fois, la cible sera acquise à nouveau. La solution selon l'invention porte sur un système de destruction de missile guidé dans lequel un système de destruction qui tire un filet ou un projectile sur une large plage est monté dans un aéronef, le système de destruction de missile guidé prédisant le mouvement d'un missile guidé et la trajectoire après que le système de destruction a été séparé de l'aéronef, et commandant le mouvement de l'aéronef de telle sorte que le système de destruction qui a été séparé de l'aéronef entre en collision avec le missile guidé, désactivant ainsi physiquement le missile guidé.
PCT/JP2022/011152 2021-03-14 2022-03-12 Système de destruction de missile guidé WO2022196597A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2021-040882 2021-03-14
JP2021040882 2021-03-14

Publications (1)

Publication Number Publication Date
WO2022196597A1 true WO2022196597A1 (fr) 2022-09-22

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ID=83320354

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2022/011152 WO2022196597A1 (fr) 2021-03-14 2022-03-12 Système de destruction de missile guidé

Country Status (1)

Country Link
WO (1) WO2022196597A1 (fr)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014159941A (ja) * 2012-07-13 2014-09-04 Boeing Co 発射物が展開される対抗手段システムおよび方法
JP2016529462A (ja) * 2013-07-10 2016-09-23 セレックス・イーエス・リミテッドＳｅｌｅｘ ＥＳ Ｌｔｄ デコイ

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014159941A (ja) * 2012-07-13 2014-09-04 Boeing Co 発射物が展開される対抗手段システムおよび方法
JP2016529462A (ja) * 2013-07-10 2016-09-23 セレックス・イーエス・リミテッドＳｅｌｅｘ ＥＳ Ｌｔｄ デコイ

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