EP0592948B1 - Procédé pour la commande autonome de position pour missiles guidés - Google Patents

Procédé pour la commande autonome de position pour missiles guidés Download PDF

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Publication number
EP0592948B1
EP0592948B1 EP93116241A EP93116241A EP0592948B1 EP 0592948 B1 EP0592948 B1 EP 0592948B1 EP 93116241 A EP93116241 A EP 93116241A EP 93116241 A EP93116241 A EP 93116241A EP 0592948 B1 EP0592948 B1 EP 0592948B1
Authority
EP
European Patent Office
Prior art keywords
missile
data
computer
onboard
guided
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.)
Expired - Lifetime
Application number
EP93116241A
Other languages
German (de)
English (en)
Other versions
EP0592948A1 (fr
Inventor
Wilfried Strentz
Günther Bittner
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.)
Airbus Defence and Space GmbH
Original Assignee
Daimler Benz Aerospace AG
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 Daimler Benz Aerospace AG filed Critical Daimler Benz Aerospace AG
Publication of EP0592948A1 publication Critical patent/EP0592948A1/fr
Application granted granted Critical
Publication of EP0592948B1 publication Critical patent/EP0592948B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/007—Preparatory measures taken before the launching of the guided missiles

Definitions

  • the invention relates to a method for autonomous position control of guided missiles which are launched from a carrier aircraft, wherein no data is transmitted to the guided missile from the carrier aircraft.
  • a weapon system is known from EP-A-0 547 637 in which a weapon is directed from a plane into a target. Both the aircraft and the weapon work with inertial navigation supported by satellite navigation (GPS). The weapon navigation data is entered by the carrier aircraft and then continued during the flight using GPS.
  • GPS satellite navigation
  • EP-A-0 368 738 shows a method for the sequence when starting an external load from a pylon of an airship with a computer, generator and an infrared light source located in the airship, which acts on a receiving device located on the external load.
  • the latter works together with a decoder and other electronic components in order to convert the received infrared pulses into programs for the takeoff and flight of the external load.
  • US-A-4 091 734 too, data is transmitted from a carrier aircraft to a weapon until it is dropped by means of infrared light rays, in which weapon these data are further processed for detonator information.
  • EP-A-0 432 902 relates to a rocket which launches even without a carrier aircraft and in whose memory the data for the entire flight are entered by a ground computer. The missile remains in a constant operating state due to further processing of the data.
  • EP-A-0 409 614 a rocket is launched from a pipe. Before the start there is an operator of one Computer via a line signals into a turning and rolling gyroscope of the missile, which are further processed into rudder deflections during the flight.
  • the invention has for its object to provide a method of the generic type, that is, to form an autonomous position control for guided missiles, which are started by a carrier aircraft which has no device for transmitting data to the guided missile.
  • the main advantage of the method according to the invention is to make an autonomous missile carried by a carrier aircraft independent of its carrier aircraft with regard to its launch and flight data. With the method it is therefore possible to launch guided missiles from a carrier aircraft, which as a result of its limited technical possibilities is not able to report data about the current position of the guided missile as well as about further flight and target data to the guided missile. Due to the method, these data are already entered on the ground in the computer of the guided missile, so that it can navigate from the ground using its inertial navigation and other navigation aids.
  • a pre-launch device is used, which inputs the data required for the navigation into the computer of the guided missile, which continuously calculates the change values from the inertial navigation and the further navigation aids. Even after a lengthy flight, the navigation device knows what position it is in without the need for further information from the aircraft.
  • the navigation device is also given the north direction via a compass coupled with the pre-takeoff device before takeoff. This value is also calculated using inertial navigation and the on-board computer until the end of the mission.
  • the compass can either belong to the missile or can also be part of the pre-launch device.
  • the on-board computer determines the horizontal position of the guided missile from the rest values of the accelerometers, i.e. from the components of gravitational acceleration. The guided missile does not have to be aligned horizontally for this purpose, since it is sufficient to save the starting position.
  • the autonomous flight guidance and self-guidance of the guided missile begins immediately after the data transfer from the pre-launch device. From this moment on, therefore, a constant and uninterrupted power supply to the inertial platform and the on-board computer must be ensured. This is done by an electric battery, which remains switched on from the time the initial data is transferred, and is also used as a backup battery to prevent data loss, even on longer flights, if the power supply is to be provided by the carrier aircraft's electrical system.
  • data for the following navigation aids can also be entered into the computer to fulfill the missile's mission: radar altimeter, Doppler speedometer, satellite navigation (GPS), laser range finder, infrared seeker head, engine control and security system.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Traffic Control Systems (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)

Claims (7)

  1. Procédé de commande autonome de la position de missiles qui sont lancés à partir d'un avion porteur, aucune donnée n'étant transmise au missile par l'avion porteur, caractérisé par les étapes suivantes:
    entrée de données concernant la position instantanée, aussi bien de données de vol que de données de cible, dans un calculateur embarqué à bord du missile, les données étant entrées lorsque le missile est au sol;
    décollage de l'avion porteur et transport du missile dans les airs;
    mise à jour en continu des données initiales introduites dans le calculateur par modification des valeurs par un système de navigation inertiel y compris par un ou plusieurs moyens auxiliaires de navigation embarques à bord du missile sans intervention de l'avion porteur, ces valeurs étant traitées en vue d'une conduite de vol autonome et d'un guidage autonome du missile;
    maintien d'une alimentation en courant électrique à bord du missile depuis l'instant de la prise en charge des données et maintien de cette alimentation pendant la durée de la mission.
  2. Procédé selon la revendication 1, caractérisé par le fait que les données initiales sont entrées dans le calculateur du missile à l'aide d'un appareil de préparation au tir.
  3. Procédé selon les revendications 1 et 2, caractérisé par le fait que le calculateur de bord mémorise la position initiale du missile par rapport au nord, cette position étant obtenue à partir des données électriques d'un compas orienté dans la direction longitudinale.
  4. Elément de connexion selon la revendication 3, caractérisé par le fait que l'on utilise un compas existant à bord du missile.
  5. Elément de connexion selon la revendication 3, caractérisé par le fait que l'on utilise un compas couplé à l'appareil de préparation au tir.
  6. Procédé selon les revendications 1 et 2, caractérisé par le fait qu'au sol le calculateur de bord détermine la position horizontale du missile à partir de valeurs de calcul d'accéléromètres.
  7. Procédé selon les revendications 1 et 2, caractérisé par le fait que dans le calculateur du missile peuvent être entrées en plus des données pour la navigation inertielle également des données pour les systèmes auxiliaires de navigation suivants: radar indicateur d'altitude, indicateur de vitesse à effet Doppler, système de navigation par satellites (GPS), télémètre à laser, tête chercheuse à infrarouges, commande de moteur et système de sécurité.
EP93116241A 1992-10-16 1993-10-07 Procédé pour la commande autonome de position pour missiles guidés Expired - Lifetime EP0592948B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4234878A DE4234878C2 (de) 1992-10-16 1992-10-16 Verfahren zur autonomen Lagesteuerung von Lenkflugkörpern
DE4234878 1992-10-16

Publications (2)

Publication Number Publication Date
EP0592948A1 EP0592948A1 (fr) 1994-04-20
EP0592948B1 true EP0592948B1 (fr) 1997-09-03

Family

ID=6470600

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93116241A Expired - Lifetime EP0592948B1 (fr) 1992-10-16 1993-10-07 Procédé pour la commande autonome de position pour missiles guidés

Country Status (3)

Country Link
US (1) US5397079A (fr)
EP (1) EP0592948B1 (fr)
DE (1) DE4234878C2 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5542334A (en) * 1994-11-15 1996-08-06 Hughes Aircraft Company Missile launch safety enhancement apparatus
DE19505527B4 (de) * 1995-02-18 2004-02-05 Diehl Stiftung & Co. Verfahren zur Ziel- oder Lageaufklärung
US6211816B1 (en) 1995-02-18 2001-04-03 Diehl Stiftung & Co. Process and apparatus for target or position reconnaissance
US5739787A (en) * 1995-04-20 1998-04-14 Burke; Edmund D. Vehicle based independent tracking system
WO1999061933A2 (fr) * 1998-04-16 1999-12-02 Raytheon Company Systeme de guidage gps aeroporte destine a mettre en echec une pluralite de brouilleurs
US6666123B1 (en) 2002-05-30 2003-12-23 Raytheon Company Method and apparatus for energy and data retention in a guided projectile
US7591225B1 (en) * 2005-10-27 2009-09-22 The United States Of America As Represented By The Secretary Of The Navy Fuze module
DE102008033429B4 (de) * 2008-07-16 2020-03-19 Diehl Defence Gmbh & Co. Kg Feststofftriebwerk
DE102008034618B4 (de) * 2008-07-25 2015-05-13 Mbda Deutschland Gmbh Verfahren zum Abkoppeln eines unbemannten Flugkörpers von einem Trägerluftfahrzeug
US8829401B1 (en) * 2011-06-16 2014-09-09 The Boeing Company Projectile and associated method for seeking a target identified by laser designation
US8513580B1 (en) * 2012-06-26 2013-08-20 The United States Of America As Represented By The Secretary Of The Navy Targeting augmentation for short-range munitions
JP6705686B2 (ja) * 2016-03-31 2020-06-03 株式会社クボタ 作業車
CN112817339B (zh) * 2019-11-15 2022-12-23 中国北方工业有限公司 一种复合制导飞行器指令融合算法

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4470562A (en) * 1965-10-22 1984-09-11 The United States Of America As Represented By The Secretary Of The Navy Polaris guidance system
US4091734A (en) * 1977-02-22 1978-05-30 The United States Of America As Represented By The Secretary Of The Navy Aircraft to weapon fuze communication link
DE3735629A1 (de) * 1987-10-21 1989-05-11 Messerschmitt Boelkow Blohm Anordnung zur automatischen azimut-uebertragung
FR2638922B1 (fr) * 1988-11-07 1994-04-29 Matra Procede et dispositif de programmation, par voie aerienne, d'une charge externe ou integree a partir d'un vehicule porteur
US5123610A (en) * 1989-07-21 1992-06-23 Hughes Aircraft Company Retrofit digital electronics unit for a tube-launched missile
US5048771A (en) * 1989-11-15 1991-09-17 Hughes Aircraft Company Method and apparatus for a reprogrammable program missile memory
US5260709A (en) * 1991-12-19 1993-11-09 Hughes Aircraft Company Autonomous precision weapon delivery using synthetic array radar

Also Published As

Publication number Publication date
DE4234878C2 (de) 1995-03-30
US5397079A (en) 1995-03-14
EP0592948A1 (fr) 1994-04-20
DE4234878A1 (de) 1994-04-21

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