EP0592948A1 - Procédé pour la commande autonome d'attitude pour missiles guidés - Google Patents

Procédé pour la commande autonome d'attitude pour missiles guidés Download PDF

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Publication number
EP0592948A1
EP0592948A1 EP93116241A EP93116241A EP0592948A1 EP 0592948 A1 EP0592948 A1 EP 0592948A1 EP 93116241 A EP93116241 A EP 93116241A EP 93116241 A EP93116241 A EP 93116241A EP 0592948 A1 EP0592948 A1 EP 0592948A1
Authority
EP
European Patent Office
Prior art keywords
data
guided missile
computer
missile
entered
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.)
Granted
Application number
EP93116241A
Other languages
German (de)
English (en)
Other versions
EP0592948B1 (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
Deutsche Aerospace AG
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 Deutsche Aerospace AG, Daimler Benz Aerospace AG filed Critical Deutsche 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

Links

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.
  • inertial platforms for their flight guidance and self-guidance, which are able to determine electrically processable values of changes in the roll, pitch and yaw angle in space.
  • the inertial platform generally also determines acceleration values in the three body axes, from which the on-board computer can use integration to determine changes in the airspeed.
  • the on-board computer receives no information about the absolute position in the room and about the three speed vectors.
  • Polaris rockets according to US Pat. No. 4,470,562 also contain such an inertial platform, but are only suitable for underwater launching.
  • the missile receives the missing information during the carrying flight from the carrier aircraft by means of data transmission via an electrical interface. Airplanes that are not equipped with such an interface could therefore not be used to launch guided missiles.
  • the invention has for its object to provide a method for autonomous position control of guided missiles so that the guided missile can also be launched from a carrier aircraft which has no facilities for transmitting data to the guided missile - that is, without the participation or help of aircraft.
  • the method according to the invention there is the possibility of launching 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. Because of the method, these data are already entered on the ground into the guided missile computer, so that it can navigate from the ground with the aid of its inertial navigation and other navigation aids.
  • a pre-launch device is used which inputs the data required for 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-take-off device before take-off. 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 should 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)
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 true EP0592948A1 (fr) 1994-04-20
EP0592948B1 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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0713074A1 (fr) * 1994-11-15 1996-05-22 Hughes Aircraft Company Dispositif pour l'amélioration de la sécurité des lancements de missile
CN107272672A (zh) * 2016-03-31 2017-10-20 株式会社久保田 作业车

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6211816B1 (en) 1995-02-18 2001-04-03 Diehl Stiftung & Co. Process and apparatus for target or position reconnaissance
DE19505527B4 (de) * 1995-02-18 2004-02-05 Diehl Stiftung & Co. Verfahren zur Ziel- oder Lageaufklärung
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
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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
EP0368738A1 (fr) * 1988-11-07 1990-05-16 Matra Defense Procédé et dispositif de programmation par voie aérienne, d'une charge externe ou intégrée à partir d'un véhicule porteur
EP0409614A2 (fr) * 1989-07-21 1991-01-23 Hughes Aircraft Company Ensemble électronique numérique pour missile lancé par tube
EP0432902A2 (fr) * 1989-11-15 1991-06-19 Hughes Aircraft Company Procédé et dispositif pour une mémoire de programme de missile reprogrammable
EP0547637A1 (fr) * 1991-12-19 1993-06-23 Hughes Aircraft Company Guidage d'arme de précision autonome utilisant un radar à ouverture synthétique

Family Cites Families (2)

* 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
DE3735629A1 (de) * 1987-10-21 1989-05-11 Messerschmitt Boelkow Blohm Anordnung zur automatischen azimut-uebertragung

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
EP0368738A1 (fr) * 1988-11-07 1990-05-16 Matra Defense Procédé et dispositif de programmation par voie aérienne, d'une charge externe ou intégrée à partir d'un véhicule porteur
EP0409614A2 (fr) * 1989-07-21 1991-01-23 Hughes Aircraft Company Ensemble électronique numérique pour missile lancé par tube
EP0432902A2 (fr) * 1989-11-15 1991-06-19 Hughes Aircraft Company Procédé et dispositif pour une mémoire de programme de missile reprogrammable
EP0547637A1 (fr) * 1991-12-19 1993-06-23 Hughes Aircraft Company Guidage d'arme de précision autonome utilisant un radar à ouverture synthétique

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0713074A1 (fr) * 1994-11-15 1996-05-22 Hughes Aircraft Company Dispositif pour l'amélioration de la sécurité des lancements de missile
CN107272672A (zh) * 2016-03-31 2017-10-20 株式会社久保田 作业车

Also Published As

Publication number Publication date
DE4234878C2 (de) 1995-03-30
EP0592948B1 (fr) 1997-09-03
US5397079A (en) 1995-03-14
DE4234878A1 (de) 1994-04-21

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