EP1103779B1 - 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
EP1103779B1
EP1103779B1 EP00124171A EP00124171A EP1103779B1 EP 1103779 B1 EP1103779 B1 EP 1103779B1 EP 00124171 A EP00124171 A EP 00124171A EP 00124171 A EP00124171 A EP 00124171A EP 1103779 B1 EP1103779 B1 EP 1103779B1
Authority
EP
European Patent Office
Prior art keywords
trajectory
projectile
target
actual
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.)
Expired - Lifetime
Application number
EP00124171A
Other languages
German (de)
English (en)
Other versions
EP1103779A1 (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
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 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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Classifications

    • 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.
  • the problem with a ground-based method is also the reliability a communication link for the transmission of the brake release time or directly from the brake control unit from the fire control computer to the projectile, In any case, given its high speed, this is partly in one ionized, a radio link affecting atmospheric envelope fly can.
  • the present invention is based on the object the in itself promising, but for the interests of the practice still too inaccurate methods of the generic type to the effect that over a trajectory shortening due to increase of the aerodynamic Braking torque can achieve a much more precise target acquisition.
  • the object is achieved in that the specified in the main claim essential process steps are realized.
  • the solution according to the invention is based on how known per se the much larger longitudinal spread of a ballistic compared to the transverse scattering or quasi-ballistically spent projectile thereby reducing the breakpoint first moved behind the measured target position and then this track is abbreviated. But this transfer is now only so far that the transition trajectory the projectile after its deceleration considering a current one Fault budget on theoretically shortest trajectory leads straight to the finish; according to the invention, this given fault budget as long as possible along the Trajectory up to the braking torque from a comparison with that for certain Error specifications theoretically predicted trajectory.
  • the projectile may be e.g. to a powerless, from a mortar or from a howitzer spent missile, but also about an artillery rocket with its initially to increase the range along quasi-ballistic Trajectory acting rocket motor.
  • the real crossing trajectory in the the projectile then from its initial trajectory by means of the aerodynamic Braking effect is pivoted, lies between the shallowest or shortest (minimum) and the highest or longest (maximum) trajectory of the current Streuf kauers and can in principle by braking in the shortest, so in the straight leading to the trajectory trajectory
  • the initialization point determined autonomously for the braking maneuver on board the projectile, ie without to be dependent on a data connection to a ground station.
  • the projectile is again with a satellite receiving device for determining equipped the actual initial trajectory.
  • Deviating from generic form of the art is the braking maneuver but not already triggered upon reaching a predetermined path point, but according to the invention becomes the initial trajectory over as long a period as possible for as many train points as possible compared with the theoretical launcher curve.
  • the current disturbances are detected parametrically. They are in particular Wind directions and strengths in different heights, but also about the Fault budget of the firing device (known transverse and height inaccuracies of the gun) and influences different depending on the environment Intensity of the firing charge.
  • the braking time is as possible late. So in the end it is not defined depending on the start of the projectile, but depending on the remaining flight time until the theoretical achievement of the Objective. He is therefore determined in time backwards, in a sense opposite to temporal movement along the track.
  • the projectile will be used as soon as possible after the start of the projectile an information about the currently known error budget mathematical, that is currently given ideal trajectory, as well as about the herefrom expected satellite contacts. This can be very good from aboard the projectile fast on at least some of the navigation satellites above the horizon accessed and quickly provide reliable information about the actual (real) trajectory, that is also about their deviation from the calculated to be derived from it on the actual current error influences close.
  • the satellite bearing can be updated the knowledge about the real trajectory until the immediate temporal Near the activation point for the braking maneuver, so long accordingly even beyond the apogee, which leads to another Improvement of the determination of the externally influenced real trajectory as far as possible close approach to the goal and thus to knowledge about the disturbing influences leads to close to the finish.
  • elevation 15 and propellant charge power i.e., theoretical exit velocity 16
  • These calculated departure trajectory 18 goes into a trajectory 20 after apogee over between a minimum trajectory 21 and a maximum trajectory 22 for a particular fault budget in the environment of the actual to be acquired Target 13 is, so within a certain longitudinal spread 23 of the possible Impact points in the target area.
  • a real trajectory 20 is for the actual existing braking system 26 and for certain disturbances a with respect to the remaining flight time to the destination 13 ideal initialization time 24, from which the actual trajectory 20 is straight turn into such a transition trajectory 25 that these are increasingly the minimal trajectory 21 snuggles and in theory ultimately accurate into goal 13 leads.
  • This initialization point 24 is the earlier on the real Trajectory 20, the farther they go without the braking corrective intervention at the target area level would be off the target 13, the higher the trajectory 20 so runs.
  • the different Disturbances can be differentiated by a crowd inclined fan of trajectories 20 and / or by a crowd differently parameterize the tripping curves 28.
  • the determination of the actual real trajectory 20 takes place on board the projectile 17 even over as long a flight as possible, in order to maximize the real impact many errors on the trajectory 18 into the trajectory 20 into with too to capture.
  • the path determination is carried out satellite-based, so over Reception of the position information of currently on board the projectile 17 detected Navigation satellites 27 based on their known orbit data, such as from satellite navigation by means of different systems of positioning satellites as such well known.
  • the spin-stabilized projectile 17 is preferably with a rotating against the swirl scanning of the projectile 17 on its lateral surface surrounding antenna elements to ensure a trouble-free Direct reception to allow, so disturbing ground reflections of the satellite emission hide as further 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 into Leave target 13 inside.
  • the minimum trajectory is 21 - taking into account the fault budget the weapon 12 and the expected external factors such as height-dependent Headwind 19 on a real trajectory 20 - through the previously enlightened Target position 13 passes through, so that all real trajectories 20 to the maximum Trajectory 22 of this total error budget are behind the target position 13. Then the descent of the projectile 17 into the target area from the current, real Trajectory 20 out to the minimum trajectory 21 out, so the target position 13 out 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)
  • Electrophonic Musical Instruments (AREA)
  • Electrotherapy Devices (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Vehicle Body Suspensions (AREA)

Claims (4)

  1. Procédé pour corriger, en fonction d'un déport probable de la cible, la trajectoire, mesurée à bord par satellite, d'un projectile lancé de manière balistique ou quasi-balistique, en augmentant son coefficient de résistance aérodynamique, pour passer de la trajectoire initiale à une trajectoire de transition plus raide par rapport à la cible, caractérisé en ce qu'on tient compte au moyen de capteurs et/ ou à partir de la trajectoire mesurée, par comparaison à une trajectoire déterminée par le calcul, de facteurs externes perturbant l'allure de la trajectoire, dans une détermination de prédiction de la trajectoire de vol réelle imminente au-delà de la cible, et en ce que pour la trajectoire de vol réelle à laquelle il faut s'attendre en conséquence, en tenant compte de ces influences, on détermine un instant d'initialisation situé aussi près que possible devant la cible, pour accroítre le coefficient de résistance à l'entrée dans une trajectoire de transition, pour le passage dans la trajectoire de vol minimale correspondant précisément à la cible.
  2. Procédé selon la revendication 1, caractérisé en ce que pour un éventail prédit, dépendant des erreurs, de trajectoires de vol réelles entre la trajectoire de vol minimale dans la cible et une trajectoire de vol maximale derrière la cible, la courbe de déclenchement d'une succession de points d'initialisation est mémorisée dans le projectile, et, à partir de la navigation courante par satellite, l'intersection imminente de la courbe de déclenchement avec la trajectoire de vol réelle mesurée, est déterminée pour le déclenchement du dispositif de freinage.
  3. Procédé selon la revendication 1 ou 2, caractérisé en ce que des ensembles de courbes dépendant des perturbations sont mémorisées dans le projectile pour des trajectoires de vol réelles et/ou pour des courbes de déclenchement.
  4. Procédé selon la revendication 1, 2 ou 3, caractérisé en ce qu'au lancement dans la trajectoire de vol réelle probable, des positions initiales sont prédéfinies pour le projectile, selon les contacts probables avec des satellites de navigation pour la mesure de la trajectoire.
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 EP1103779A1 (fr) 2001-05-30
EP1103779B1 true EP1103779B1 (fr) 2004-02-04

Family

ID=7930696

Family Applications (1)

Application Number Title Priority Date Filing Date
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 (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1783451A2 (fr) 2005-11-03 2007-05-09 Junghans Feinwerktechnik GmbH & Co.KG Projectile stabilisé par rotation

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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
EP1763683B1 (fr) * 2004-07-02 2016-04-06 Trackman A/S Procede et appareillage de determination d'un ecart entre une direction reelle d'un projectile lance et une direction predeterminee
DE102004036003B4 (de) * 2004-07-23 2006-11-16 Diehl Bgt Defence Gmbh & Co. Kg Panzerhaubitze mit Programmiereinrichtung für Artilleriemunition mit Korrekturzünder
WO2006086527A1 (fr) * 2005-02-07 2006-08-17 Bae Systems Information And Electronic Systems Integration Inc. Etiquette de retour de rayonnement
WO2006086532A2 (fr) * 2005-02-07 2006-08-17 Bae Systems Information And Electronic Systems Commande aerodynamique triaxiale de munitions guidees
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
US7834300B2 (en) * 2005-02-07 2010-11-16 Bae Systems Information And Electronic Systems Integration Inc. Ballistic guidance control for munitions
US7533849B2 (en) * 2005-02-07 2009-05-19 Bae Systems Information And Electronic Systems Integration Inc. Optically guided munition
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.
US7963442B2 (en) 2006-12-14 2011-06-21 Simmonds Precision Products, Inc. Spin stabilized projectile trajectory control
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
WO2010148023A1 (fr) * 2009-06-15 2010-12-23 Blue Origin, Llc Prédiction et correction de trajectoires
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
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
EP3961145A1 (fr) * 2020-08-31 2022-03-02 Simmonds Precision Products, Inc. Systèmes de correction de trajectoire de projectiles
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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Publication number Priority date Publication date Assignee Title
EP1783451A2 (fr) 2005-11-03 2007-05-09 Junghans Feinwerktechnik GmbH & Co.KG Projectile stabilisé par rotation

Also Published As

Publication number Publication date
DE19957363A1 (de) 2001-05-31
US6467721B1 (en) 2002-10-22
EP1103779A1 (fr) 2001-05-30
ATE259053T1 (de) 2004-02-15
DE50005186D1 (de) 2004-03-11
SG93904A1 (en) 2003-01-21

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