EP0090184A2 - Roquette d'exercice - Google Patents

Roquette d'exercice Download PDF

Info

Publication number
EP0090184A2
EP0090184A2 EP83101908A EP83101908A EP0090184A2 EP 0090184 A2 EP0090184 A2 EP 0090184A2 EP 83101908 A EP83101908 A EP 83101908A EP 83101908 A EP83101908 A EP 83101908A EP 0090184 A2 EP0090184 A2 EP 0090184A2
Authority
EP
European Patent Office
Prior art keywords
rocket
original
practice
tube
training
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.)
Withdrawn
Application number
EP83101908A
Other languages
German (de)
English (en)
Other versions
EP0090184A3 (fr
Inventor
Christoph Mathey
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.)
Huels Troisdorf AG
Dynamit Nobel AG
Original Assignee
Huels Troisdorf AG
Dynamit Nobel 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 Huels Troisdorf AG, Dynamit Nobel AG filed Critical Huels Troisdorf AG
Publication of EP0090184A2 publication Critical patent/EP0090184A2/fr
Publication of EP0090184A3 publication Critical patent/EP0090184A3/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B8/00—Practice or training ammunition
    • F42B8/12—Projectiles or missiles
    • F42B8/24—Rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/048—Means for imparting spin to the rocket before launching
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
    • F42B14/061—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile

Definitions

  • the invention relates to a practice rocket of the type specified in the preamble of claim 1.
  • This practice ammunition consists of the original rocket engine and a practice rocket head, which, depending on the type of screwed-on detonator, is disassembled on impact or while still in flight.
  • the object of the invention is to avoid these disadvantages, i.e. a training rocket of the type specified in the preamble of claim 1 in particular so that the effort required for it is relatively low and they can be used under field conditions on those shooting ranges that are primarily suitable for training with light infantry weapons in terms of their size.
  • Such firing ranges are usually not only near infantry barracks, but also near the locations of rocket launcher units.
  • the spacing elements located at a distance from one another are preferably arranged such that the center of gravity of the practice rocket lies between them.
  • the practice rocket according to the invention which is sub-caliber in comparison to the original rocket, is designed such that it represents a scale reduction of the original rocket with regard to its external ballistics. It is fired from the original rocket launcher, the trajectory is tracked with the original fire control radar and the correction values are determined by the original fire control computer. For this purpose, a computer program changed in the scale of the trajectory reduction is entered in the latter before the start of the exercise, which takes into account the trajectory that has been reduced in size compared to the original rocket.
  • Claim 2 used anyway the guide surfaces as spacers.
  • the spacer elements provided to compensate for the difference in diameter (caliber) between the original and the practice rocket can be designed to be repulsive in order to avoid any undesired change in the flow conditions.
  • the spacer elements can also be used for swirl transmission, e.g. are provided with guide devices which slide in the twist trains of the launcher tube and thus impart the desired rotation about their longitudinal axis to the practice rocket.
  • the spacer elements are supported on the inner wall of this "auxiliary" launcher tube.
  • the auxiliary launcher tube which is short in comparison to the original launcher tube, is preferably also provided with swirl trains in which the spacer elements engage.
  • the embodiment according to claim 6 has proven to be advantageous.
  • the outline of the auxiliary launcher tube in the area of the missile sleeve bearing is designed such that it corresponds to the original missile, in particular in the area of electrical contacting.
  • the outer diameter of the auxiliary launcher tube is approximately equal to the inner diameter of the original launcher tube, so that it can be used properly.
  • the practice rocket can be equipped with a rocket head that functions as the original warhead, e.g. simulated with regard to target point marking, discharge point marking, cutting point marking or marking of the trajectory.
  • a reflector in the missile head, which reflector reflects the radar signal emitted by the fire control radar in such a way that trajectory tracking and recording is possible.
  • the practice rocket can be packaged, transported, stored, etc. in the packaging of the original rocket, thereby reducing the logistical effort to a minimum.
  • Fig. 1 shows the original launcher tube 1 with the twisted twists 2 wound into the plane of the drawing and with the sub-caliber training rocket 3 used, shown in the view, the guiding surfaces 5 acting as spacer elements 4 and the two arranged in front of the center of gravity S. Round rods 6, which also act as spacer elements and engage the twist trains 2.
  • Fig. 1a shows a section along the line A-B in Fig.1, which shows the engagement of the tail surfaces 5 in the swirl cables 2.
  • Fig. 1b shows the engagement of the round rods 6 as a section along the line C-D in Fig. 1.
  • winding guide rails can be provided on the inner wall of the original launcher tube, as can an internally smooth launcher tube can be used.
  • the at least two spacer elements 4 are designed as detachable spacers 7, which are arranged here again such that the center of gravity S of the practice rocket 3 lies between the guide surfaces 5 and the spacers 7.
  • Fig. 2a shows a cross section corresponding to that of the win rarely section line EF in Fig. 2.
  • the four spacers 7 engage with their guide pins 8 in the twist trains 2.
  • FIG. 3a shows the detail X from FIG. 2 on an enlarged scale.
  • the spacer 7 is locked until it is fired by means of the spring-loaded ball 9.
  • the practice rocket 3 is accelerated according to arrow A, so that the ball 9 remains and thus releases the retaining bolt 10 of the spacer 7.
  • the spacer 7, supported by the rotation of the practice rocket 3, is thrown off.
  • 3b shows, as an enlarged detail Y from FIG. 2a, an analog variant in which the unlocking takes place due to the rotational movement of the practice rocket 3, corresponding to the arrow B in the launcher tube 1.
  • the practice rocket 3 is inserted into the tube 11, which acts here as an "auxiliary" launcher tube with twist pulls 12, which in turn is inserted into the original launcher tube 1 and held by means of the lock 13.
  • the tube 11 is closed at the rear by means of the cover 14 which can be ejected during firing and by means of the foam cover 15.
  • the electrical contact 16 is formed due to the compatible design of the launcher sleeve bearing 17 as in the original rocket.
  • FIG. 4a shows the view corresponding to the arrow Z in FIG. 4, while FIG. 4b shows the cross section along the line G-H in FIG. 4.
  • the reference numbers have the same meaning as previously explained.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP83101908A 1982-03-25 1983-02-26 Roquette d'exercice Withdrawn EP0090184A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3211011 1982-03-25
DE19823211011 DE3211011A1 (de) 1982-03-25 1982-03-25 Uebungsrakete

Publications (2)

Publication Number Publication Date
EP0090184A2 true EP0090184A2 (fr) 1983-10-05
EP0090184A3 EP0090184A3 (fr) 1983-11-30

Family

ID=6159295

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83101908A Withdrawn EP0090184A3 (fr) 1982-03-25 1983-02-26 Roquette d'exercice

Country Status (2)

Country Link
EP (1) EP0090184A3 (fr)
DE (1) DE3211011A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3414911A1 (de) * 1984-04-19 1985-10-24 Dynamit Nobel Ag, 5210 Troisdorf Flugkoerper, insbesondere ballistische rakete

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19508008A1 (de) * 1995-03-07 1996-09-12 Wegmann & Co Gmbh Abschußvorrichtung für selbstangetriebene Flugkörper, insbesondere Artillerieraketen

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR95452E (fr) * 1954-10-22 1971-01-15 Soc Tech De Rech Ind Perfectionnements aux projectiles a réaction.
US3038382A (en) * 1958-09-26 1962-06-12 William R Noyes Bore riders for launching of projectiles
US2966827A (en) * 1959-01-27 1961-01-03 Leo M Harvey Rocket launcher
US3112671A (en) * 1961-11-17 1963-12-03 James V Dunham Rocket trainer
US3487780A (en) * 1967-03-07 1970-01-06 Edvard Troen Rockets for subcaliber training system for anti-tank weapon
FR1529742A (fr) * 1967-04-27 1968-06-21 Perfectionnements aux tubes et projectiles de mortiers
GB1323593A (en) * 1969-07-12 1973-07-18 Messerschmitt Boelkow Blohm Launcher for missiles
DE2159941C3 (de) * 1971-12-03 1980-07-17 Dynamit Nobel Ag, 5210 Troisdorf Elektrische Kontakteinrichtung für eine Rakete

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3414911A1 (de) * 1984-04-19 1985-10-24 Dynamit Nobel Ag, 5210 Troisdorf Flugkoerper, insbesondere ballistische rakete

Also Published As

Publication number Publication date
DE3211011A1 (de) 1983-09-29
EP0090184A3 (fr) 1983-11-30

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PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

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Effective date: 19840413

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Effective date: 19870218

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Inventor name: MATHEY, CHRISTOPH