JPH03225200A - Guiding system for obtaining simultaneous impact - Google Patents

Guiding system for obtaining simultaneous impact

Info

Publication number
JPH03225200A
JPH03225200A JP2156590A JP2156590A JPH03225200A JP H03225200 A JPH03225200 A JP H03225200A JP 2156590 A JP2156590 A JP 2156590A JP 2156590 A JP2156590 A JP 2156590A JP H03225200 A JPH03225200 A JP H03225200A
Authority
JP
Japan
Prior art keywords
missiles
launching
simultaneous
order
routes
Prior art date
Legal status (The legal status 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 status listed.)
Pending
Application number
JP2156590A
Other languages
Japanese (ja)
Inventor
Hiroyuki Takeuchi
博幸 竹内
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to JP2156590A priority Critical patent/JPH03225200A/en
Publication of JPH03225200A publication Critical patent/JPH03225200A/en
Pending legal-status Critical Current

Links

Landscapes

  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

PURPOSE:To permit the simultaneous arrival of missiles at a target by a method wherein routes and launching times, which are necessary for impacting simultaneously a plurality of missiles, launched out of same or a plurality of launchers, against the single target, are considered and determined while the missiles are guided based on the determined routes and launching times. CONSTITUTION:When the simultaneous impact order of missiles is commanded, a simultaneous launching order interpreting program in a simultaneous launching order interpreter recognizes the order and transmits launching data to a flight route regulator, controlled by a flight route regulating program. The flight route regulator operates the flight routes of respective missiles based on the data in the launching data and transmits them to respective missiles. According to this method, respective missiles impact the single target simultaneously and, therefore, the remaining factor as well as the incendiary effect of the missiles can be increased.

Description

【発明の詳細な説明】 [産業上の利用分野] 本発明は、発射前にその経路を指定する誘導方式の飛し
ょう体を単一標的に同時に着弾させるシステムに関する
DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to a system for simultaneously impacting a single target with a guided projectile whose path is specified before launch.

[従来の技術] 従来の方式では、同一発射機から発射される飛しよう体
は発射間隔により同時弾着させることは原理的に困難で
ある。
[Prior Art] In the conventional method, it is theoretically difficult to land projectiles fired from the same launcher at the same time due to the firing interval.

[発明が解決しようとする課題] 従来の技術では、同一の発射機から発射された発射時刻
の異なる飛しょう体は単一標的には別々に弾着するため
残存率が低下し、また填実効果も低くなる可能性がある
[Problems to be Solved by the Invention] In the conventional technology, projectiles fired from the same launcher at different launch times impact a single target separately, resulting in a reduced survival rate and It may also be less effective.

本発明はこのような問題を解決することを目的とするも
のである。
The present invention aims to solve such problems.

[課題を解決するための手段] 本発明によるシステムは、射撃を統制する装置が、射撃
に先立ち発射する飛しょう体の飛しょう経路を個々に調
整し、できるだけ異なる方向から同一標的に同時に弾着
するように誘導するものである。
[Means for Solving the Problems] In the system according to the present invention, a shooting control device individually adjusts the flight path of the projectiles to be fired prior to shooting, so that the projectiles hit the same target from as different directions as possible at the same time. It is intended to induce people to do so.

[作 用] 本発明では、飛しょう経路は発射間隔に応じて同時に標
的に到着するように予め経路が決定され、したがって異
なる距離を経ることにより同時に標的に到達することが
可能になる。
[Function] In the present invention, the flight paths are determined in advance so as to arrive at the target at the same time according to the firing interval, and therefore it becomes possible to reach the target at the same time by passing different distances.

[実施例] 実施例で説明する。本発明による同時弾着誘導方式は、
同時発射命令を解釈するプログラムおよび、飛しょう経
路調整プログラムを実行することによって構成される。
[Example] This will be explained using an example. The simultaneous impact guidance method according to the present invention is as follows:
It is constructed by executing a program that interprets simultaneous launch commands and a flight path adjustment program.

第2図はそのフロー図で同時弾着命令が下されると、同
時発射命令解釈子において同時発射命令解釈プログラム
が命令を認識し、発射諸元を飛しょう経路調整プログラ
ムで制御される飛しょう経路調整子に送る。飛しよう経
路調整子では、発射諸元のデータを基にして、それぞれ
の飛しょう体の飛しよう経路を計算し、それを飛しょう
体に伝達する。
Figure 2 shows the flowchart. When a simultaneous firing command is issued, the simultaneous firing command interpreter recognizes the command, and the simultaneous firing command interpreter recognizes the command and determines the firing specifications. Send to route coordinator. The flight path adjuster calculates the flight path of each projectile based on launch specification data and transmits it to the projectile.

同時弾着技術を用いれば、各飛しょう体が単一標的に同
時に弾着するため、飛しよう体の残存率および飛しょう
体の填実効果を高めることができる。
Using simultaneous landing technology, each projectile hits a single target at the same time, increasing the survival rate of the projectile and the impact of the projectile.

[発明の効果コ 本発明により、同時に、複数の飛しよう体を単一標的に
弾着させることができ、対空火器を持つ目標艦船および
地上目標に対しても充分な残存率と填実効果とを得られ
る。
[Effects of the Invention] The present invention allows multiple flying objects to hit a single target at the same time, and achieves sufficient survivability and coverage effect against target ships with anti-aircraft weapons and ground targets. You can get .

【図面の簡単な説明】[Brief explanation of drawings]

第1図は本発明を適用した地対艦ミサイルシステムの例
を示す。 第2図は同時弾着方式の発射命令から発射までをフロー
図で表す。
FIG. 1 shows an example of a surface-to-ship missile system to which the present invention is applied. FIG. 2 is a flow diagram showing the process from firing command to firing in the simultaneous landing method.

Claims (1)

【特許請求の範囲】[Claims] 同一または複数の発射機から発射された複数の飛しよう
体を単一標的に同時に弾着させるために必要な経路を発
射時刻を考慮して決定し、それに基いて飛しょう体を誘
導することを特徴とする同時弾着誘導方式。
Determines the path required for multiple flying objects fired from the same or multiple launchers to hit a single target simultaneously, taking into account the launch time, and guides the flying objects based on this. Features simultaneous bullet guidance method.
JP2156590A 1990-01-31 1990-01-31 Guiding system for obtaining simultaneous impact Pending JPH03225200A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2156590A JPH03225200A (en) 1990-01-31 1990-01-31 Guiding system for obtaining simultaneous impact

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2156590A JPH03225200A (en) 1990-01-31 1990-01-31 Guiding system for obtaining simultaneous impact

Publications (1)

Publication Number Publication Date
JPH03225200A true JPH03225200A (en) 1991-10-04

Family

ID=12058546

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2156590A Pending JPH03225200A (en) 1990-01-31 1990-01-31 Guiding system for obtaining simultaneous impact

Country Status (1)

Country Link
JP (1) JPH03225200A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2024143122A (en) * 2023-03-30 2024-10-11 三菱電機株式会社 Guidance device

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2024143122A (en) * 2023-03-30 2024-10-11 三菱電機株式会社 Guidance device

Similar Documents

Publication Publication Date Title
US4307650A (en) Weapons system for the ballistic and guided attack on multiple targets, especially by an aircraft
EP0138942B1 (en) Means for reducing spread of shots in a weapon system
RU2151370C1 (en) Method for destruction of moving target by guided projectile with active guidance system and pre-acceleration engine
US4198015A (en) Ideal trajectory shaping for anti-armor missiles via time optimal controller autopilot
CN116360489B (en) A collaborative mid-range guidance law design method based on forming guidance law
JP7543400B2 (en) How to optimize the burst point
US3534653A (en) Controlled dispersion missile dispenser
CN101554923A (en) Airplane missile defense system
GB2073382A (en) Method of compensation for target location changes when firing ballistic missiles
RU2213926C1 (en) Method for missile guidance
RU2651362C1 (en) Method of striking a distant multiple target
JPH03225200A (en) Guiding system for obtaining simultaneous impact
RU2017103622A (en) WINGED ROCKET AND METHOD OF ITS BATTLE USE
US3538809A (en) Process for attacking a ground target from an airplane
KR102697942B1 (en) Apparatus and systems for launching to reduce launch shock
RU2165585C1 (en) Method for flight control of guided vehicle and guided vehicle
RU2723783C1 (en) Method of cruise missile homing
RU2213318C1 (en) Method of aiming of guided rocket
RU2836926C1 (en) Method of using uav and system for implementing method
RU2845727C1 (en) Network-centric air defense and counter-battery combat system
US20030224332A1 (en) Computerized battle-control system/game (BCS)
RU2808847C1 (en) Method of attacking enemy targets with anti-tank guided missiles perpendicular to longitudinal axis of helicopter
RU2799000C1 (en) Firing method of ground fire means
US2966316A (en) Missile
RU25931U1 (en) WINGED ROCKET