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WO1999030105A1 - Procede et dispositif de correction de la trajectoire de projectiles aerodynamiques - Google Patents

Procede et dispositif de correction de la trajectoire de projectiles aerodynamiques Download PDF

Info

Publication number
WO1999030105A1
WO1999030105A1 PCT/SE1998/002047 SE9802047W WO9930105A1 WO 1999030105 A1 WO1999030105 A1 WO 1999030105A1 SE 9802047 W SE9802047 W SE 9802047W WO 9930105 A1 WO9930105 A1 WO 9930105A1
Authority
WO
WIPO (PCT)
Prior art keywords
projectile
trajectory
impulse
devices
correction
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.)
Ceased
Application number
PCT/SE1998/002047
Other languages
English (en)
Inventor
Kjell Albrektsson
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.)
Saab Bofors AB
BAE Systems Bofors AB
Original Assignee
Bofors Weapon Systems AB
Bofors AB
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 Bofors Weapon Systems AB, Bofors AB filed Critical Bofors Weapon Systems AB
Publication of WO1999030105A1 publication Critical patent/WO1999030105A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge

Definitions

  • the present invention relates to a method and a device for correcting the trajectory of a projectile travelling in a ballistic trajectory.
  • the impulse devices have so far consisted of small rocket motors with short burning times and with nozzles collected to form a unit distributed round the projectile periphery near the centre of gravity.
  • a proposal has already been made, however, to use the impulse device which has given the desired impulse force by ejecting heavy metal rods or suchlike from the projectile surface.
  • This type of impulse device must also give the desired impulse close to the projectile centre of gravity.
  • the projectile rotation position must be checked very carefully using a gyroscope or other device, at the same time as the projectile must have either a fully autonomous guidance function which determines the deviations from the planned ballistic trajectory and gives the necessary commands for activating the impulse device at the correct time, or have a receiver which can receive guidance commands from a ground station from where the necessary trajectory measurements and correction calculations have been carried out.
  • the total deviation between a calculated ballistic trajectory and the actual trajectory consists of the sum of a number of different error sources with different causes and sizes.
  • the sum of the longitudinal errors and the sum of the transverse errors are roughly the same size even if the relative size of the errors can vary from occasion to occasion. It is therefore necessary to be able to correct both error types to the same degree and, with the technology available up to this point, it has been necessary to ensure the availability of a sufficient number of powerful impulse devices in order to make these corrections.
  • impulse devices instead of using one impulse device which gives an active trajectory correction impulse close to the ⁇ centre of gravity of the projectile, that at least two impulse devices are used, one of which is located in front of the centre of gravity in the direction of flight, and one of which is located to the rear of the centre of gravity, and also that these devices are activated simultaneously, upon which the impulse devices selected, which can be of rocket or solid (projectile) type, are so adjusted regarding the distance to the projectile centre of gravity and also so directed, that they together give the projectile an impulse the effect of which is close to the centre of gravity, and thereby provides a new projectile trajectory without oscillation.
  • the impulse devices selected which can be of rocket or solid (projectile) type
  • Figure 1 shows a schematic longitudinal section through an artillery round
  • Figure 2 shows a cross-section along II: II in Figure 1
  • Figure 3 shows a schematic plan of a trajectory correction in accordance with the invention.
  • the artillery round shown in Figure 1 has a centre section 2 for active payload, for example submunitions, a front section 3 with gyro for control of the shell instantaneous roll angle receiver for correction orders and devices for carrying out the orders, while the rear section 4 has a location for a base-bleed device and is fitted with deployable fins 5.
  • the fins 5 are essential in this context as it is considerably easier to correct the projectile trajectory using impulse motors for a fin-stabilised ballistic projectile than for a roll-stabilised projectile.
  • a front and a rear group of impulse devices 6 and 7, are also included.
  • the figure also shows a separation charge 8 for the active payload in the projectile centre section 2.
  • the front section of the projectile has a removable ring-formed section 9. If this is removed, the projectile's ldrag is increased considerably and this has a retardation effect on the projectile resulting in a shortening of its ballistic trajectory.
  • Part 9 can also be replaced by deployable brake flaps of various designs
  • the impulse devices 6 and 7 include a number of radially directed impulse charges 10 together with a centrally located part 11 in which the ignition functions for the various impulse charges are expected to be located.
  • the radial positioning of the impulse charges provides space for a large number of small but sufficient impulse charges within a small projectile volume.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

L'invention concerne un procédé et un dispositif de correction de la trajectoire (16) d'un projectile (1, 13) qui se déplace dans une trajectoire balistique. Selon l'invention, on utilise des dispositifs d'impulsions (6, 7) pour apporter, si besoin, au projectile (1, 13) une correction transversale et ainsi lui conférer une nouvelle trajectoire (21). En revanche, la trajectoire du projectile est, si besoin, corrigée en longitude par un ralentissement actif du projectile, ce qui raccourcit sa trajectoire initiale légèrement plus longue. Selon un développement ultérieur de l'invention, plusieurs dispositifs d'impulsions (6, 7) coopérant placés de chaque côté du centre de gravité du projectile (1, 13) sont utilisés pour chaque correction transversale de la trajectoire.
PCT/SE1998/002047 1997-12-08 1998-11-13 Procede et dispositif de correction de la trajectoire de projectiles aerodynamiques Ceased WO1999030105A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE9704558A SE513646C2 (sv) 1997-12-08 1997-12-08 Sätt och artelleriprojektil r bankorrigering av aerodynamiska projektiler försedda med impulsmotorer
SE9704558-7 1997-12-08

Publications (1)

Publication Number Publication Date
WO1999030105A1 true WO1999030105A1 (fr) 1999-06-17

Family

ID=20409294

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE1998/002047 Ceased WO1999030105A1 (fr) 1997-12-08 1998-11-13 Procede et dispositif de correction de la trajectoire de projectiles aerodynamiques

Country Status (2)

Country Link
SE (1) SE513646C2 (fr)
WO (1) WO1999030105A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1267141A3 (fr) * 2001-06-15 2003-10-29 Diehl Munitionssysteme GmbH & Co. KG Méthode et dispositif pour l'activation d'un dispositif de freinage pour corriger le trajectoire ballistique d'un projectile vers une cible
US11231259B2 (en) * 2017-04-28 2022-01-25 Bae Systems Bofors Ab Projectile with selectable angle of attack

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4232738A1 (de) * 1992-09-30 1994-03-31 Rheinmetall Gmbh Vorrichtung zur Korrektur der Flugbahn von Überschallgeschossen

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4232738A1 (de) * 1992-09-30 1994-03-31 Rheinmetall Gmbh Vorrichtung zur Korrektur der Flugbahn von Überschallgeschossen

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1267141A3 (fr) * 2001-06-15 2003-10-29 Diehl Munitionssysteme GmbH & Co. KG Méthode et dispositif pour l'activation d'un dispositif de freinage pour corriger le trajectoire ballistique d'un projectile vers une cible
US11231259B2 (en) * 2017-04-28 2022-01-25 Bae Systems Bofors Ab Projectile with selectable angle of attack

Also Published As

Publication number Publication date
SE9704558D0 (sv) 1997-12-08
SE9704558L (sv) 1999-06-09
SE513646C2 (sv) 2000-10-16

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