WO2022196597A1 - Guided missile hard-kill system - Google Patents

Guided missile hard-kill system 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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Prior art keywords
aircraft
kill system
hard
hard kill
function
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PCT/JP2022/011152
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French (fr)
Japanese (ja)
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和男 吉原
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合同会社Ｉｐマネジメント
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    • 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.

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  • 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

[Problem] Flares are used as means for jamming guided missiles that employ infrared rays in terminal guidance; however, in the case of infrared sensors having simultaneous multi-target processing capabilities, there is a possibility that an actual target (aircraft) will be tracked if a flare is not deployed before the infrared sensor initiates target tracking. Additionally, chaff is used as a means for jamming guided missiles that employ radar guidance in terminal guidance; however, a large amount of chaff is required to deceive a guided missile. There is also a possibility that, even if deception succeeds once, the target will be re-acquired. [Solution] Provided is a guided missile hard-kill system in which a hard-kill system that fires a net or a projectile over a broad range is mounted in an aircraft, the guided missile hard-kill system predicting the movement of a guided missile and the trajectory after the hard-kill system has split off from the aircraft, and controlling the movement of the aircraft such that the hard-kill system that has split off from the aircraft collides with the guided missile, thereby physically deactivating the guided missile.

Description

誘導飛翔体ハードキルシステムGuided projectile hard kill system
本発明は、航空機の撃墜を目的とした誘導飛翔体を物理的に無力化するためのものである。 The present invention is for physically neutralizing a guided projectile intended to shoot down an aircraft.
軍用機を誘導ミサイルから保護するため、軍用機から発射されたデコイに誘導ミサイルを引き付ける技術が提供（下記特許文献１）されている。 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).
特表２０１６ー５２９４６２Special table 2016-529462
赤外線を終末誘導に採用している誘導飛翔体に対してはフレアが妨害手段として用いられるが、同時多目標処理能力を有する赤外線センサーの場合、赤外線センサーが目標の追尾を開始する前にフレアを展開しなければ、本物の目標（航空機）が追尾される可能性がある。 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.
レーダー誘導を終末誘導に採用している誘導飛翔体に対してはチャフが妨害手段として用いられるが、誘導飛翔体を欺瞞するには、大量のチャフが必要となる。
また、一度欺瞞に成功しても、再度捕捉される可能性がある。 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.
このため、網や弾体を広範囲に射出するハードキルシステムを航空機に搭載、ハードキルシステムが航空機から切り離された後の軌道と誘導飛翔体の機動を予測し、航空機から切り離されたハードキルシステムと誘導飛翔体が衝突するよう航空機の機動を制御する事で、誘導飛翔体を物理的に無力化する誘導飛翔体ハードキルシステムを提供する。 For this reason, the aircraft is equipped with a hard kill system that shoots nets and projectiles over a wide range. To provide a guided flying object hard kill system for physically incapacitating a guided flying object by controlling the maneuvering of an aircraft so that the guided flying object collides with a flying object.
本発明の誘導飛翔体ハードキルシステムは、網もしくは弾体を射出する機能を備え、前記ハードキルシステムを航空機から切り離す機能を備える。 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.
好適には、前記ハードキルシステムが航空機から切り離される際の航空機の速度、加速度ベクトル、ハードキルシステムの姿勢から、航空機から切り離された後のハードキルシステムの軌道を算出する予測機能を備える。 Preferably, 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.
より好適には、航空機と誘導飛翔体の位置及び機動から、誘導飛翔体の機動を予測する予測機能を備え、予測機能により算出されたハードキルシステムの軌道に基づき、誘導飛翔体とハードキルシステムが衝突する航空機の機動、並びにハードキルシステムの切り離しタイミングを算出する機能を備える。 More preferably, 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.
より好適には、ハードキルシステムは姿勢制御のための姿勢制御翼と通信機能を備え、通信機能により航空機と通信を行い、予測機能が算出した航空機から切り離されたハードキルシステムの軌道、並びに誘導飛翔体の機動に基づき、姿勢制御翼の角度を調整する機能を備える。 More preferably, 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.
より好適には、前記予測機能により算出された航空機の機動、並びにハードキルシステムの切り離しタイミングを、音声もしくは映像で操縦士に伝達する伝達機能を備える。 More preferably, 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.
より好適には、前記予測機能により算出された航空機の機動、並びにハードキルシステムの切り離しタイミングに基づき、航空機を自動操縦する自動操縦機能を備える。 More preferably, 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.
本発明に係る誘導飛翔体ハードキルシステムによれば、フレアやチャフ等の妨害手段で欺瞞出来なかった誘導飛翔体を物理的に無力化するのに好適である。 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.
本発明の実施例に係る誘導飛翔体ハードキルシステムを説明するための概略図Schematic diagram for explaining a guided projectile hard kill system according to an embodiment of the present invention.
以下、本発明に係る誘導飛翔体ハードキルシステムについて、実施例にて図面を用いて説明する。
実施例では、有人の航空機を例に説明しているが、無人航空機にも適用可能である。
＜実施例＞ Hereinafter, a guided projectile hard kill system according to the present invention will be described in an embodiment with reference to the drawings.
In the embodiment, a manned aircraft is described as an example, but the application is also applicable to an unmanned aircraft.
<Example>
図１は、誘導飛翔体ハードキルシステムを説明する概略図である。
誘導飛翔体ハードキルシステム１は、ハードキルシステム２、航空機３、近接信管４、射出機能５，姿勢制御翼６、通信機能７、予測機能８、レーダー９、伝達機能１０、自動操縦機能１１から構成される。 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.
誘導飛翔体ハードキルシステム１は、近接信管４を備え、射出機能５により網や弾体を射出するハードキルシステム２と、ハードキルシステム２を搭載可能な航空機３により構成され、航空機３からハードキルシステム２を切り離す機能を備える。 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.
航空機３は予測機能８を備え、ハードキルシステム２が航空機３から切り離された際の、航空機３の速度、加速度ベクトル、ハードキルシステム２の姿勢、姿勢制御翼６の角度等からハードキルシステム２の軌道を予測する。
姿勢制御翼６は、姿勢制御を行うためにハードキルシステム２に備えられた翼である。 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.
航空機３は、レーダー９が捉えた誘導飛翔体１２の位置と機動、航空機３の機動から、予測機能８により誘導飛翔体１２の機動を算出、航空機３から切り離されたハードキルシステム２を誘導飛翔体１２に衝突させるための航空機３の機動と、ハードキルシステム２を航空機３から切り離すタイミングを算出する。 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 .
ハードキルシステム２は通信機能７により、航空機３と通信を行い、予測機能８が算出した誘導飛翔体１２の機動、並びにハードキルシステム２の軌道に基づき、姿勢制御翼６の角度を調整する。 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 .
予測機能８は航空機３からハードキルシステム２が切り離された後も、ハードキルシステム２と誘導飛翔体１２が衝突する航空機３の機動を算出し続ける。 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 .
ハードキルシステム２は航空機３から切り離された後も、通信機能７により航空機３と通信を行い、予測機能８が算出した誘導飛翔体１２の機動に基づき、誘導飛翔体１２とハードキルシステム２が衝突するよう、姿勢制御翼６の角度を調整する。 Even after being 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.
航空機の構造上、ハードキルシステム２は航空機３の底部に装着される事になる。
このため、ハードキルシステム２を誘導飛翔体１２に十分に接近させるには、ハードキルシステム２の姿勢制御翼６により揚力を発生させる、ハードキルシステム２を切り離し後に航空機３をダイブする事で誘導飛翔体１２がハードキルシステム２に接近するよう誘導する、ハードキルシステム２を切り離す直前に航空機３を急上昇させる等のオペレーションが必要になる。 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.
姿勢制御翼６は、ハードキルシステム２の減速に用いてもかまわない。 The attitude control wings 6 may be used for deceleration of the hard kill system 2.
予測機能８により算出された航空機３の機動は、伝達機能１０により音声もしくは映像によって操縦士に伝達される。
また、航空機４は、予測機能８により算出された航空機３の機動に基づき、自動操縦機能１１により、自動操縦される事が望ましい。 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 .
予測機能８により算出されたハードキルシステム２の切り離しタイミングは、伝達機能１０により音声もしくは映像によって操縦士に伝達される。
また、ハードキルシステム２は、予測機能８により算出されたハードキルシステム２の切り離しタイミングに基づき、自動操縦機能１１により、自動的に切り離される事が望ましい。 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 .
本発明は、フレアやチャフ等の妨害手段で欺瞞出来なかった誘導飛翔体を、物理的に無力化するのに好適である。 INDUSTRIAL APPLICABILITY The present invention is suitable for physically neutralizing guided projectiles that could not be deceived by interference means such as flares and chaffs.
１　　誘導飛翔体ハードキルシステム
２　　ハードキルシステム
３　　航空機
４　　近接信管
５　　射出機能
６　　姿勢制御翼
７　　通信機能
８　　予測機能
９　　レーダー
１０　伝達機能
１１　自動操縦機能
１２　誘導飛翔体 1 guided missile hard kill system 2 hard kill system 3 aircraft 4 proximity fuse 5 ejection function 6 attitude control wing 7 communication function 8 prediction function 9 radar 10 transmission function 11 autopilot function 12 guided missile

Claims (6)

  1. 網もしくは弾体を射出するハードキルシステムを、
    航空機に搭載する機能を備え、
    前記ハードキルシステムを航空機から切り離す
    機能を備える事を特徴とする誘導飛翔体ハードキルシステム。     A hard kill system that shoots nets or bullets,
    Equipped with functions to be mounted on aircraft,
    A guided projectile hard kill system characterized by having a function of separating the hard kill system from an aircraft.
  2. 前記ハードキルシステムが航空機から切り離される際の航空機の速度、加速度ベクトル、ハードキルシステムの姿勢から、
    航空機から切り離した後のハードキルシステムの軌道を算出する
    機能を備える事を特徴とする請求項１に記載の誘導飛翔体ハードキルシステム。     From the velocity of the aircraft, the acceleration vector, the attitude of the hard kill system when the hard kill system is disconnected from the aircraft,
    2. The guided projectile hard kill system according to claim 1, further comprising a function of calculating the trajectory of the hard kill system after separation from the aircraft.
  3. 航空機と誘導飛翔体の位置及び機動から、誘導飛翔体の機動を予測する予測機能を備え、
    前記予測機能により算出されたハードキルシステムの軌道に基づき、
    誘導飛翔体とハードキルシステムが衝突する航空機の機動、
    並びにハードキルシステムの切り離しタイミングを算出する
    機能を備える事を特徴とする請求項１に記載の誘導飛翔体ハードキルシステム。     Equipped with a prediction function that predicts the maneuver of the guided missile from the position and maneuver of the aircraft and the guided missile,
    Based on the trajectory of the hard kill system calculated by the prediction function,
    Aircraft maneuvers where guided projectiles and hard kill systems collide,
    2. The guided projectile hard kill system according to claim 1, further comprising a function of calculating the disconnection timing of the hard kill system.
  4. ハードキルシステムは姿勢制御のための姿勢制御翼と通信機能を備え、
    通信機能により航空機と通信を行い、
    予測機能が算出した航空機から切り離されたハードキルシステムの軌道、
    並びに誘導飛翔体の機動に基づき、姿勢制御翼の角度を調整する
    機能を備える事を特徴とする請求項１に記載の誘導飛翔体ハードキルシステム。     The hard kill system has attitude control wings and communication functions for attitude control,
    The communication function communicates with the aircraft,
    the trajectory of the hardkill system disconnected from the aircraft calculated by the predictor;
    2. The guided missile hard kill system according to claim 1, further comprising a function of adjusting the angle of the attitude control wing based on the maneuver of the guided missile.
  5. 前記予測機能により算出された航空機の機動、
    並びにハードキルシステムの切り離しタイミングを、
    音声もしくは映像で操縦士に伝達する
    機能を備える事を特徴とする請求項１に記載の誘導飛翔体ハードキルシステム。     Aircraft maneuvers calculated by the prediction function;
    And the timing of disconnecting the hard kill system,
    2. The guided missile hard kill system according to claim 1, further comprising a function of transmitting voice or video to the pilot.
  6. 前記予測機能により算出された航空機の機動、
    並びにハードキルシステムの切り離しタイミングに基づき、
    航空機を自動操縦する
    機能を備える事を特徴とする請求項１に記載の誘導飛翔体ハードキルシステム。     Aircraft maneuvers calculated by the prediction function;
    And based on the release timing of the hard kill system,
    2. The guided missile hard kill system of claim 1, further comprising a function of autopiloting an aircraft.
PCT/JP2022/011152 2021-03-14 2022-03-12 Guided missile hard-kill system WO2022196597A1 (en)

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Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014159941A (en) * 2012-07-13 2014-09-04 Boeing Co Projectile-deployed countermeasure system and method
JP2016529462A (en) * 2013-07-10 2016-09-23 セレックス・イーエス・リミテッドＳｅｌｅｘ ＥＳ Ｌｔｄ decoy

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014159941A (en) * 2012-07-13 2014-09-04 Boeing Co Projectile-deployed countermeasure system and method
JP2016529462A (en) * 2013-07-10 2016-09-23 セレックス・イーエス・リミテッドＳｅｌｅｘ ＥＳ Ｌｔｄ decoy

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