EP1103779A1 - Procédé de correction d'une trajectoire ballistique liée à une cible - Google Patents

Procédé de correction d'une trajectoire ballistique liée à une cible Download PDF

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Publication number
EP1103779A1
EP1103779A1 EP00124171A EP00124171A EP1103779A1 EP 1103779 A1 EP1103779 A1 EP 1103779A1 EP 00124171 A EP00124171 A EP 00124171A EP 00124171 A EP00124171 A EP 00124171A EP 1103779 A1 EP1103779 A1 EP 1103779A1
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EP
European Patent Office
Prior art keywords
trajectory
target
projectile
real
expected
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
EP00124171A
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German (de)
English (en)
Other versions
EP1103779B1 (fr
Inventor
Karl Kautzsch
Jürgen Leininger
Jürgen Wittmann
Albrecht Reindler
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.)
Diehl BGT Defence GmbH and Co KG
Original Assignee
Diehl Munitionssysteme GmbH and Co KG
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Application filed by Diehl Munitionssysteme GmbH and Co KG filed Critical Diehl Munitionssysteme GmbH and Co KG
Publication of EP1103779A1 publication Critical patent/EP1103779A1/fr
Application granted granted Critical
Publication of EP1103779B1 publication Critical patent/EP1103779B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F41G7/346—Direction control systems for self-propelled missiles based on predetermined target position data using global navigation satellite systems, e.g. GPS, GALILEO, GLONASS

Definitions

  • the invention relates to a method according to the preamble of claim 1.
  • Such a method is known from WO 98/01719. It is based on a satellite navigation device on board the projectile the one currently flown Determine trajectory and from a comparison with a target-optimized Flight path when reaching a path point derived from the comparison aerodynamic Braking devices for the most accurate correction possible to release the subsequent trajectory. Problematic for practical implementation is, however, that the numerous external factors influencing a trajectory act on the trajectory even after the brake means have been triggered and therefore the corrected trajectory then not for the precise delivery of the mechanism of action leads in the projectile.
  • Reliability is also a problem with a ground-based process a communication link for the transmission of the brake release time or directly from the brake command from the fire control computer to the projectile, because, given its high speed, it is at times in one piece ionized, atmospheric envelope impairing a radio connection can.
  • the present invention is based on the object that is promising in itself, but still too for practical needs to further develop inaccurate methods of the generic type in such a way that a shortening of the trajectory due to an increase in aerodynamic Braking torque can achieve a much more precise target acquisition.
  • This The object is achieved in that the specified in the main claim essential process steps can be realized.
  • the solution according to the invention is therefore based on what is known per se the much larger longitudinal scatter of a ballistic compared to the transverse scatter or quasi-ballistic projectile by reducing the stopping point first moved behind the measured target position and then this path is abbreviated. But that relocation now takes place only so far that the transition trajectory the projectile after decelerating taking into account a current one Error budget leads theoretically to the target on the shortest trajectory; According to the invention, this given error budget is as long as possible along the Path curve up to the braking torque from a comparison with that for certain Error specifications theoretically predicted trajectory is determined.
  • the projectile can e.g. to an unpowered, from a mortar or storey from a howitzer, but also about an artillery missile with their initially quasi-ballistic to increase the range Trajectory acting rocket engine.
  • the real transition trajectory into which the projectile then from its initial trajectory using the aerodynamic Braking effect is swung in between the flattest or shortest (minimum) and the highest or longest (maximum) trajectory of the current Spreading fan and can in principle by braking into the shortest, i.e. into the trajectory leading straight to the destination.
  • the initialization point intended for the braking maneuver on board the projectile i.e. without to be dependent on a data connection to a ground station.
  • the projectile is again to be determined with a satellite reception device the actual initial trajectory.
  • Deviating from The braking maneuver does not become a generic state of the art triggered when a predetermined path point is reached, but according to the invention the initial trajectory is as long as possible compared with the theoretical launch curve for as many path points as possible.
  • the current disturbances are recorded parametrically. They are special Wind directions and strengths at different heights, but also about Failure budget of the launcher (known transverse and vertical direction inaccuracies of the gun) and influences depending on the environment Launch charge intensity. With such knowledge, you can be right precise statements about the interference effects using the usual external ballistic Predict approaches that are still active even after the brake is triggered the transitional trajectory flown subsequently to act on these to be expected Error effects in advance by correcting the braking time to compensate as much as possible.
  • the braking time is as possible late. So it is ultimately not defined depending on the start of the projectile, but depending on the remaining flight time until the theoretical reaching of Target. It is therefore determined backwards in time, in a way counter to the temporal movement along the path.
  • the projectile will be deployed as soon as possible after the start of the projectile information about the error budget that is already known arithmetic, i.e. currently ideal trajectory, as well as the resulting expected satellite contacts. This can be done very much from the projectile quickly to at least some of the navigation satellites above the horizon accessed and quickly reliable information on the actual (Real) trajectory curve, i.e. also about its deviation from that predicted by calculation can be obtained from the actual current error influences close.
  • the target point transmitted on board in the projectile can be determined. So that leaves the ideal initialization point for initiating the braking process, i.e. for entry into the transition trajectory determined by the new aerodynamic conditions from the real trajectory that is too far specified into the minimal, precise Trajectory depending on the remaining flight time to the target area accordingly predict exactly. Because, on the other hand, this is as late as possible Braking timing can be determined accurately, the satellite bearing for updating the knowledge of the real trajectory up to the immediate temporal Close to the activation point for the braking maneuver, i.e.
  • elevation 15 and propellant charge power i.e. the theoretical exit speed 16
  • the calculated exit trajectory 18 goes into a trajectory 20 after apogee that between a minimum trajectory 21 and a maximum trajectory 22 for a certain budget in the environment of the actually acquired Target 13 lies within a certain longitudinal scatter 23 of the possible ones Impact points in the target area.
  • a real trajectory 20 is for the actually existing braking system 26 and for certain interference influences an ideal initialization time in relation to the remaining flight time to the destination 13 24 assigned from which straight from the real trajectory 20 can swing around in such a transition trajectory 25 that this increasingly the minimal trajectory 21 nestles and in theory ultimately exactly leads to goal 13.
  • the means that for a fan of possible real trajectories 20 a consequence of ideal initialization points 24 can be represented as a trigger curve 28 which (as from the drawing) something compared to a family of curves of real trajectories 20 is pivoted, which is the total of the real trajectories 20 between minimum and maximum trajectory 21-22 intersects once.
  • the different Interfering influences (such as wind data 19) can be differentiated by a group inclined fan of trajectories 20 and / or by a crowd different Parameterize tripping curves 28.
  • the determination of the currently real trajectory 20 (and from this the determination the initialization point 24) is reached on board the projectile 17 even over the longest possible flight route in order to maximize the real impact many error influences on the trajectory 18 into the trajectory 20 to capture.
  • the orbit determination is carried out with the aid of satellites, i.e. via Receiving the position information from those currently recorded on board the projectile 17 Navigation satellites 27 based on their known orbital data, such as from satellite navigation using different systems of location satellites as such well known.
  • the spin-stabilized projectile 17 is preferably included a scanning of the projectile 17 rotating against the swirl on its outer surface surrounding antenna elements equipped to ensure interference-free To enable direct reception, i.e. disturbing ground reflections from the satellite radiation to hide, as explained in EP 0 840 393 A2.
  • the braking device 26 is activated and the previous real trajectory 20 with pivoting into the transition path 25 ins Leave goal 13 inside.
  • the minimum trajectory 21 - taking into account the error budget the weapon 12 and the expected external factors such as height-dependent Headwind 19 on a real trajectory 20 - through the previously explained Target position 13 relocated so that all real trajectories 20 to the maximum Trajectory 22 of this total error budget lie behind target position 13. Then the projectile 17 descends into the target area from the current, real one Trajectory 20 out to the minimal trajectory 21, that is to the target position 13 shortened by releasing an aerodynamic braking effect.

Landscapes

  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (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)
  • Radar Systems Or Details Thereof (AREA)
  • Vehicle Body Suspensions (AREA)
  • Electrophonic Musical Instruments (AREA)
  • Electrotherapy Devices (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
EP00124171A 1999-11-29 2000-11-08 Procédé de correction d'une trajectoire ballistique liée à une cible Expired - Lifetime EP1103779B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19957363 1999-11-29
DE19957363A DE19957363A1 (de) 1999-11-29 1999-11-29 Verfahren zur zielbezogenen Korrektur einer ballistischen Flugbahn

Publications (2)

Publication Number Publication Date
EP1103779A1 true EP1103779A1 (fr) 2001-05-30
EP1103779B1 EP1103779B1 (fr) 2004-02-04

Family

ID=7930696

Family Applications (1)

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EP00124171A Expired - Lifetime EP1103779B1 (fr) 1999-11-29 2000-11-08 Procédé de correction d'une trajectoire ballistique liée à une cible

Country Status (5)

Country Link
US (1) US6467721B1 (fr)
EP (1) EP1103779B1 (fr)
AT (1) ATE259053T1 (fr)
DE (2) DE19957363A1 (fr)
SG (1) SG93904A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005052474B3 (de) * 2005-11-03 2007-07-12 Junghans Feinwerktechnik Gmbh & Co. Kg Drallstbilisiertes Artillerieprojektil
WO2008118159A2 (fr) 2006-12-14 2008-10-02 Simmonds Precision Products, Inc. Commande de trajectoire de projectile gyro-stabilisatrice
CN104154818A (zh) * 2014-07-25 2014-11-19 北京机械设备研究所 一种无控弹射击角度确定方法
CN105589068A (zh) * 2015-12-08 2016-05-18 河海大学 基于三步数值积分的弹道外推方法
US20200049809A1 (en) * 2004-07-02 2020-02-13 Trackman A/S Method and an apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction
EP3961145A1 (fr) * 2020-08-31 2022-03-02 Simmonds Precision Products, Inc. Systèmes de correction de trajectoire de projectiles
CN118466556A (zh) * 2024-07-09 2024-08-09 四川汉科计算机信息技术有限公司 基于轨迹预判的瞄准点控制方法及系统、无人机、介质

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10129043A1 (de) 2001-06-15 2003-01-02 Diehl Munitionssysteme Gmbh Verfahren und Vorrichtungen zum Bestimmen des Auslösens einer Bremseinrichtung für die zielbezogene Korrektur der ballistischen Flugbahn eines Projektils
DE10227251B4 (de) * 2002-06-19 2004-05-27 Diehl Munitionssysteme Gmbh & Co. Kg Kombinations-Antenne für Artilleriemunition
DE10236157A1 (de) 2002-08-07 2004-02-26 Junghans Feinwerktechnik Gmbh & Co. Kg Programmierbarer Artilleriezünder
DE102004036003B4 (de) * 2004-07-23 2006-11-16 Diehl Bgt Defence Gmbh & Co. Kg Panzerhaubitze mit Programmiereinrichtung für Artilleriemunition mit Korrekturzünder
WO2006088687A1 (fr) * 2005-02-07 2006-08-24 Bae Systems Information And Electronic Systems Integration Inc. Munitions guidees optiquement
WO2006086528A2 (fr) * 2005-02-07 2006-08-17 Bae Systems Information And Electronic Systems Integration Inc. Commande de guidage balistique destinee a des munitions
WO2006086532A2 (fr) * 2005-02-07 2006-08-17 Bae Systems Information And Electronic Systems Commande aerodynamique triaxiale de munitions guidees
US7503521B2 (en) * 2005-02-07 2009-03-17 Bae Systems Information And Electronic Systems Integration Inc. Radiation homing tag
WO2007089243A2 (fr) * 2005-02-07 2007-08-09 Bae Systems Information And Electronic Systems Integration Inc. Procédé et système de commande de munition à guidage optique
US7350744B1 (en) * 2006-02-22 2008-04-01 Nira Schwartz System for changing warhead's trajectory to avoid interception
FR2909458B1 (fr) * 2006-12-01 2009-01-23 Thales Sa Procede d'estimation du site d'un projectile balistique.
US20110059421A1 (en) * 2008-06-25 2011-03-10 Honeywell International, Inc. Apparatus and method for automated feedback and dynamic correction of a weapon system
US8046203B2 (en) 2008-07-11 2011-10-25 Honeywell International Inc. Method and apparatus for analysis of errors, accuracy, and precision of guns and direct and indirect fire control mechanisms
US8729442B2 (en) * 2009-06-15 2014-05-20 Blue Origin, Llc Predicting and correcting trajectories
DE102010023449B4 (de) * 2010-06-11 2014-01-02 Diehl Bgt Defence Gmbh & Co. Kg Verfahren und Vorrichtung zum Steuern eines Lenkflugkörpers
US8510041B1 (en) 2011-05-02 2013-08-13 Google Inc. Automatic correction of trajectory data
CN113276116B (zh) * 2021-05-21 2022-01-18 武汉瀚迈科技有限公司 一种误差可控的机器人轨迹同步过渡方法

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US4655411A (en) * 1983-03-25 1987-04-07 Ab Bofors Means for reducing spread of shots in a weapon system
DE3608109A1 (de) 1986-03-12 1987-09-17 Diehl Gmbh & Co Bremseinrichtung fuer ein drallstabilisiertes projektil
EP0519315A1 (fr) * 1991-06-20 1992-12-23 DIEHL GMBH & CO. Dispositif pour mesurer le profil en hauteur d'un vent au sol
WO1998001719A1 (fr) 1996-07-05 1998-01-15 The Secretary Of State For Defence Moyen servant a augmenter la trainee d'un projectile
EP0840393A2 (fr) 1996-11-05 1998-05-06 DIEHL GMBH & CO. Système d'antenne pour la navigation d'un missile supporté par satellite
DE19718947A1 (de) * 1997-05-05 1998-11-12 Rheinmetall W & M Gmbh GPS-gestütztes Pilot-Geschoß und Verfahren zur Einweisung von Wirkgeschossen über einem definierten Einsatzbereich
DE19740888A1 (de) * 1997-09-17 1999-03-25 Rheinmetall W & M Gmbh Verfahren zum autonomen Lenken eines drallstabilisierten Artilleriegeschosses und autonom gelenktes Artilleriegeschoß zur Durchführung des Verfahrens

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US4566656A (en) * 1982-09-15 1986-01-28 General Dynamics Pomona Division Steering mechanism for an explosively fired projectile
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US5647558A (en) * 1995-02-14 1997-07-15 Bofors Ab Method and apparatus for radial thrust trajectory correction of a ballistic projectile
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DE19753752C1 (de) * 1997-12-04 1999-07-29 Eurocopter Deutschland Vorrichtung und Verfahren zur Bestimmung des Auftreffpunkts eines ballistischen Flugkörpers
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EP0138942B1 (fr) 1983-03-25 1988-06-22 Aktiebolaget Bofors Installation pour reduire la dispersion des projectiles dans un systeme d'armes
DE3608109A1 (de) 1986-03-12 1987-09-17 Diehl Gmbh & Co Bremseinrichtung fuer ein drallstabilisiertes projektil
US4726543A (en) * 1986-03-12 1988-02-23 Diehl Gmbh & Co. Braking arrangement for a spin-stabilized projectile
EP0519315A1 (fr) * 1991-06-20 1992-12-23 DIEHL GMBH & CO. Dispositif pour mesurer le profil en hauteur d'un vent au sol
DE4120367A1 (de) 1991-06-20 1992-12-24 Diehl Gmbh & Co Einrichtung zur messung des hoehenprofils eines bodenwindes
WO1998001719A1 (fr) 1996-07-05 1998-01-15 The Secretary Of State For Defence Moyen servant a augmenter la trainee d'un projectile
EP0840393A2 (fr) 1996-11-05 1998-05-06 DIEHL GMBH & CO. Système d'antenne pour la navigation d'un missile supporté par satellite
DE19718947A1 (de) * 1997-05-05 1998-11-12 Rheinmetall W & M Gmbh GPS-gestütztes Pilot-Geschoß und Verfahren zur Einweisung von Wirkgeschossen über einem definierten Einsatzbereich
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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200049809A1 (en) * 2004-07-02 2020-02-13 Trackman A/S Method and an apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction
US10690764B2 (en) * 2004-07-02 2020-06-23 Trackman A/S Method and an apparatus for determining a deviation between an actual direction of a launched projectile and a predetermined direction
EP1783451A3 (fr) * 2005-11-03 2007-08-29 Junghans Feinwerktechnik GmbH & Co.KG Projectile stabilisé par rotation
US7360490B2 (en) 2005-11-03 2008-04-22 Junghans Microtec Gmbh Spin-stabilized artillery projectile
DE102005052474B3 (de) * 2005-11-03 2007-07-12 Junghans Feinwerktechnik Gmbh & Co. Kg Drallstbilisiertes Artillerieprojektil
WO2008118159A2 (fr) 2006-12-14 2008-10-02 Simmonds Precision Products, Inc. Commande de trajectoire de projectile gyro-stabilisatrice
WO2008118159A3 (fr) * 2006-12-14 2008-12-11 Simmonds Precision Products Commande de trajectoire de projectile gyro-stabilisatrice
US7963442B2 (en) 2006-12-14 2011-06-21 Simmonds Precision Products, Inc. Spin stabilized projectile trajectory control
CN104154818A (zh) * 2014-07-25 2014-11-19 北京机械设备研究所 一种无控弹射击角度确定方法
CN104154818B (zh) * 2014-07-25 2016-01-20 北京机械设备研究所 一种无控弹射击角度确定方法
CN105589068B (zh) * 2015-12-08 2017-09-22 河海大学 基于三步数值积分的弹道外推方法
CN105589068A (zh) * 2015-12-08 2016-05-18 河海大学 基于三步数值积分的弹道外推方法
EP3961145A1 (fr) * 2020-08-31 2022-03-02 Simmonds Precision Products, Inc. Systèmes de correction de trajectoire de projectiles
CN118466556A (zh) * 2024-07-09 2024-08-09 四川汉科计算机信息技术有限公司 基于轨迹预判的瞄准点控制方法及系统、无人机、介质

Also Published As

Publication number Publication date
SG93904A1 (en) 2003-01-21
US6467721B1 (en) 2002-10-22
EP1103779B1 (fr) 2004-02-04
ATE259053T1 (de) 2004-02-15
DE19957363A1 (de) 2001-05-31
DE50005186D1 (de) 2004-03-11

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