EP0329524A1 - Vorrichtung zur Berechnung des Integrationsschrittes einer Granatenflugbahn - Google Patents

Vorrichtung zur Berechnung des Integrationsschrittes einer Granatenflugbahn Download PDF

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Publication number
EP0329524A1
EP0329524A1 EP89400336A EP89400336A EP0329524A1 EP 0329524 A1 EP0329524 A1 EP 0329524A1 EP 89400336 A EP89400336 A EP 89400336A EP 89400336 A EP89400336 A EP 89400336A EP 0329524 A1 EP0329524 A1 EP 0329524A1
Authority
EP
European Patent Office
Prior art keywords
integration step
trajectory
calculating
shell
values
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
EP89400336A
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English (en)
French (fr)
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EP0329524B1 (de
Inventor
Serge Braconne
Jean-Luc Estival
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.)
Thales SA
Original Assignee
Thomson CSF SA
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 Thomson CSF SA filed Critical Thomson CSF SA
Publication of EP0329524A1 publication Critical patent/EP0329524A1/de
Application granted granted Critical
Publication of EP0329524B1 publication Critical patent/EP0329524B1/de
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
    • F41G3/00—Aiming or laying means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F41G3/142—Indirect aiming means based on observation of a first shoot; using a simulated shoot

Definitions

  • the present invention relates to a method and a device for calculating the integration pitch of shell trajectories.
  • trajectory integration calculations are carried out, with successive corrections from firing conditions chosen initially, until the shell drop point is located within defined limits with respect to the target.
  • the subject of the present invention is a method for calculating such an optimized integration step, that is to say the maximum integration step compatible with the required precision, making it possible to save on the integration time of the trajectories. without losing on the precision of the integration calculation.
  • the method for calculating the integration pitch of shell trajectories essentially consists of: - in a preliminary stage: . to calculate, for different firing configurations, a so-called reference trajectory, with a given integration step, relatively small, said reference step, . to successively try, at different points of the different reference paths thus obtained, different values of the integration step, increasing from the reference step until the difference with the reference path is greater than a predetermined limit, said tolerable position error by integration step, in which case the integration step adopted, called limit integration step, is that corresponding to the last test carried out, .
  • the set of these variables constitutes a point P of the trajectory.
  • time limit noted h limit
  • This method is relatively costly in calculation time, but it does not have to be implemented in the field, in the calculation means associated with the firing battery; it will advantageously be implemented beforehand, with more efficient calculation means than those associated with the firing battery, the performance of which is obviously limited for reasons of bulk. Since this database cannot be exhaustive, it is necessary, if we want to effectively reduce the time taken to calculate trajectories in the field, using the calculation means associated with the firing battery, to determine a means quick calculation of the h lim value corresponding to any point P, from this database and according to the parameters existing at the point considered and the firing configuration considered.
  • explanatory variables that is, variables according to which the variable to be modeled h lim is expressed according to a certain function.
  • This geometrically amounts to carrying out a projection of the set of points representing h lim in the space of the different variables "x" of the set (T, X, ⁇ p ), on each plans (h lim , x), then to select those of these variables "x" having the strongest explanatory power.
  • Each of the eight zones thus defined corresponds to a set of coefficients b i 1, b i 2, b i 3, b i 4, b i 5 (1 ⁇ i ⁇ 8) used in the expression of the above model. These different cases will appear in FIG. 3 which will be described later.
  • FIG. 2b we graphically represented the model allowing to approximate h lim in a limited space for more clarity with the two explanatory variables ⁇ p and M ⁇ 2 and in this space we considered only the case M> M o (area "High Mach”).
  • This model is constituted by a succession of planes which each project, as represented on figure 2a, in each of the planes (h lim , ⁇ p ) and (h lim , M ⁇ 2) according to the line segments resulting from the modeling linear.
  • the values of the parameters which it is necessary to know at the point considered are the values of the parameters M, U X , U Y , U Z , A o , T e , P r , U o , W X , m.
  • the parameters U X , U Y , U Z designate the components of the absolute speed of the shell at the point considered; A o indicates the rise of the barrel.
  • This modeling of ⁇ p is obtained from a database ( ⁇ p , T) which can itself be obtained in the following way.
  • the method according to the invention makes it possible to significantly reduce the calculation times and to dispense with operators specialized in the calculation means associated with the firing battery; the architecture of these is simplified and their energy consumption reduced, which is fundamental for problems of portability and autonomy.
  • the method according to the invention makes it possible to reduce this number to around twenty.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)
EP19890400336 1988-02-17 1989-02-07 Vorrichtung zur Berechnung des Integrationsschrittes einer Granatenflugbahn Expired - Lifetime EP0329524B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8801857A FR2627302B1 (fr) 1988-02-17 1988-02-17 Procede et dispositif de calcul du pas d'integration de trajectoire d'obus
FR8801857 1988-02-17

Publications (2)

Publication Number Publication Date
EP0329524A1 true EP0329524A1 (de) 1989-08-23
EP0329524B1 EP0329524B1 (de) 1993-05-12

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19890400336 Expired - Lifetime EP0329524B1 (de) 1988-02-17 1989-02-07 Vorrichtung zur Berechnung des Integrationsschrittes einer Granatenflugbahn

Country Status (4)

Country Link
EP (1) EP0329524B1 (de)
DE (1) DE68906418T2 (de)
DK (1) DK66489A (de)
FR (1) FR2627302B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2294133A (en) * 1994-10-11 1996-04-17 Accuracy Int Ltd Ballistic calculator
US7815115B2 (en) 2005-05-17 2010-10-19 Krauss-Maffei Wegmann Gmbh & Co. Kg Method of determining a fire guidance solution

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006036257A1 (de) * 2006-08-03 2008-02-07 Rheinmetall Defence Electronics Gmbh Bestimmung der einzustellenden Ausrichtung einer ballistischen Waffe

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2459443A1 (fr) * 1979-06-15 1981-01-09 Thomson Brandt Procede et dispositif de determination des elements de tir d'un projectile
GB2094950A (en) * 1981-03-12 1982-09-22 Barr & Stroud Ltd Gun fire control systems
EP0065832A1 (de) * 1981-05-15 1982-12-01 The Marconi Company Limited Anordnung zum Richten eines Geschützes

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU860082A1 (ru) * 1979-10-03 1981-08-30 Таганрогский радиотехнический институт им. В.Д.Калмыкова Стохастический интегратор

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2459443A1 (fr) * 1979-06-15 1981-01-09 Thomson Brandt Procede et dispositif de determination des elements de tir d'un projectile
GB2094950A (en) * 1981-03-12 1982-09-22 Barr & Stroud Ltd Gun fire control systems
EP0065832A1 (de) * 1981-05-15 1982-12-01 The Marconi Company Limited Anordnung zum Richten eines Geschützes

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
AUTOMATISME, tome 16, no. 2, février 1971, pages 122-126, Equipement autonome de D.C.A.; L. PUN: "Application d'une méthode prédictive de Newton a un équipement autonome de D.C.A." *
SOVIET INVENTIONS ILLUSTRATED, section EL, semaine E25, 4 août 1982, classe T01, no. H4849 E/25, page 15, Derwent Publications Ltd, Londres, GB; & SU-A-860 082 (TAGANROG WIRELESS ENG.) 30-08-1981 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2294133A (en) * 1994-10-11 1996-04-17 Accuracy Int Ltd Ballistic calculator
GB2294133B (en) * 1994-10-11 1999-08-18 Accuracy Int Ltd Ballistic calculator
US7815115B2 (en) 2005-05-17 2010-10-19 Krauss-Maffei Wegmann Gmbh & Co. Kg Method of determining a fire guidance solution

Also Published As

Publication number Publication date
DK66489A (da) 1989-08-18
DE68906418D1 (de) 1993-06-17
EP0329524B1 (de) 1993-05-12
FR2627302B1 (fr) 1990-06-08
DE68906418T2 (de) 1993-09-09
DK66489D0 (da) 1989-02-13
FR2627302A1 (fr) 1989-08-18

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