EP0679860A2 - Dispositif de signalisation, en particulier roquette de signalisation - Google Patents

Dispositif de signalisation, en particulier roquette de signalisation Download PDF

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Publication number
EP0679860A2
EP0679860A2 EP95106002A EP95106002A EP0679860A2 EP 0679860 A2 EP0679860 A2 EP 0679860A2 EP 95106002 A EP95106002 A EP 95106002A EP 95106002 A EP95106002 A EP 95106002A EP 0679860 A2 EP0679860 A2 EP 0679860A2
Authority
EP
European Patent Office
Prior art keywords
cover
outer tube
signal
constriction
rocket
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
EP95106002A
Other languages
German (de)
English (en)
Other versions
EP0679860B1 (fr
EP0679860A3 (fr
Inventor
Arthur Zahn
Eckart Foehn
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.)
Comet GmbH Pyrotechnik Apparatebau
Original Assignee
Comet GmbH Pyrotechnik Apparatebau
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 Comet GmbH Pyrotechnik Apparatebau filed Critical Comet GmbH Pyrotechnik Apparatebau
Publication of EP0679860A2 publication Critical patent/EP0679860A2/fr
Publication of EP0679860A3 publication Critical patent/EP0679860A3/fr
Application granted granted Critical
Publication of EP0679860B1 publication Critical patent/EP0679860B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F42B4/00—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes
    • F42B4/06—Aerial display rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B7/00—Shotgun ammunition
    • F42B7/02—Cartridges, i.e. cases with propellant charge and missile
    • F42B7/12—Cartridge top closures, i.e. for the missile side

Definitions

  • the invention relates to a signaling means, in particular a signaling rocket, according to the preamble of claims 1, 2 and 6.
  • Pyrotechnic signaling devices are used primarily in aviation and seafaring to make third parties aware of acute emergencies and impending dangerous situations.
  • signal rockets which are usually fired by hand
  • signal cartridges which can be fired from a suitable signal gun
  • Such signaling means are also used as pyrotechnic lighting means for airport apron lighting or for lighting during search and rescue operations at night.
  • the signal is fired from an outer tube in which the signal is housed.
  • the signal occurs after the Ignition out of the outer tube, namely through a front side of the outer tube provided with a detachable closure, which is thereby removed from the signal.
  • the invention relates to a practical design of the closure on the upper end face of the outer tube, which essentially has to meet two requirements.
  • the breech is intended to withstand mechanical stresses on the signal rocket, in particular a fall on the upper end face, without the unignited signal being able to slip out of the outer tube.
  • the signal should be able to emerge from the face of the outer tube with as little resistance as possible, that is to say the closure can be easily blasted off.
  • the present invention seeks to provide a signaling device that has a reliable and functional closure that ensures simple manufacture.
  • the signaling device has the features of claim 1.
  • the one-piece design of the outer tube and cover simplifies the manufacture of the signaling means. In particular, the assembly of the previously separate cover is no longer necessary.
  • the signaling device has the features of claim 2.
  • the constriction causes force on the cover opposite to the direction of the rocket launch, e.g. in the case of a fall on the closed end of the signal rocket, that the cover is deformed in a targeted manner only in the elastic range. A loosening of the cover from the outer tube and an associated slipping out of the signal from the outer tube is prevented.
  • the signaling device has the features of claim 6.
  • the predetermined breaking point assigned to the cover ensures that the signal emerges with the lowest possible resistance when the signal rocket is fired.
  • the breech can be easily detached or blasted off the cover, thereby reducing the recoil when the signaling means is fired.
  • FIG. 1 shows a signaling device designed as a parachute signaling rocket 10.
  • An elongated cylindrical outer tube 11 of the parachute signal rocket 10 has two opposite end faces 12, 13.
  • the lower end face 13 has an opening 14.
  • the opening 14 is closed by a bottom 15 which is detachably connected to the outer tube 11 and which is a manually operated one Trigger 16 is assigned to the ignition.
  • Trigger 16 Seen in the direction of the rocket launch (arrow 17), there is a propellant charge 18 above the floor 15 and a signal above it, namely a star set 19, with a parachute 20 folded over it .
  • the propellant charge 18 and the star set 19 are still assigned in the manner known per se, firings, delay sets and intermediate sets, which are not described in more detail here.
  • a closure 22 consists of a cover 23 which is integrally connected to a wall 24 of the outer tube 11 (Fig. 3).
  • the cover 23 consists of two sections, namely a lower, cylindrical section 25 and an upper, conical section 26.
  • the lower section 25 is dimensioned such that a predetermined breaking point 28 is formed in a transition region 27 between cover 23 and wall 24.
  • the predetermined breaking point 28 is thinner than the thickness of the wall 24, and in fact so thin that when the parachute rocket 10 is fired, the closure 22 can be easily released or blasted off.
  • the predetermined breaking point 28 is made thick enough that in the event of the parachute missile 10 falling on the breech 22, the cover 23 cannot become detached from the wall 24.
  • a closure 29 consists of a cover 30, the cover 30 having a lower, cylindrical section 31 and an upper, conical section 32 (FIG. 4).
  • the cover 30 is formed in one piece with a wall 33 of the outer tube 11.
  • a constriction 34 is assigned to the cover 30 in the lower, cylindrical section 31.
  • the constriction 34 is designed as a circumferential groove which extends from the outside of a wall 35 of the lower section 31.
  • the depth of the constriction 34 is several times greater than the thickness of the wall 33 of the outer tube 11.
  • the depth of the constriction 34 is preferably about three times the thickness of the wall 33.
  • the width of the constriction 34 is dimensioned such that when a force is applied opposite to the direction of the rocket launch, the deformation of the cover 30 always remains in the elastic range. Furthermore, the constriction 34 is arranged at a short distance from a bottom wall 36 of the cover 30. This creates a predetermined breaking point 38 in a transition region 37 between cover 30 and wall 33. The predetermined breaking point 38 or the distance of the constriction 34 from the bottom wall 36 is less than the thickness of the wall 33, in such a way that when the parachute signal rocket 10 is fired, the closure 29 can be easily blown off.
  • the closure 39 consists of a cover 40 which is connected to a wall 41 of the outer tube.
  • the cover 40 also consists of a lower, cylindrical section 42 and an upper, conical section 43.
  • a peripheral region 44 of the lower section 42 of the cover 40 is assigned a circumferential notch 45 adjacent to the wall 41 of the outer tube.
  • the circumferential notch 45 starts from a bottom wall 46 of the cover 40.
  • the notch 45 is V-shaped in cross section, one leg of the notch 45 being formed by the wall 41.
  • the notch 45 is accordingly arranged in the transition region 47 between the cover 40 and the wall 41.
  • the depth of the notch 45 is dimensioned such that a defined predetermined breaking point 48 is created in the transition region 47.
  • the notch has an opening angle of 10 ° - 50 °, preferably 30 °.
  • the opening angle of 30 ° has proven to be particularly favorable from the point of view of a recoil-free detachment of the closure 39.
  • the closure 21 consists of a cover 49 which is formed in one piece with a wall 50 of the outer tube 11.
  • the cover 49 consists of a lower, cylindrical section 51 and an upper, conical section 52.
  • a constriction 53 and a notch 54 are assigned to the lower section 51.
  • the constriction 53 is formed as a circumferential groove starting from a wall 55 of the cover 49.
  • the constriction 53 is designed and dimensioned analogously to the constriction 34 in FIG. 4.
  • the notch 54 is assigned to an edge region 57 thereof. The formation and dimensioning of the notch 54 takes place analogously to the notch 45 of FIG. 5 with the formation of an interface 58.
  • FIG. 7 shows the mode of operation of the breech 21 designed according to the invention as shown in FIG. 6, when a force is applied opposite to the direction (arrow 17) of the rocket launch (for example by a fall of the parachute signal missile 10 on the breech 21).
  • the cover 49 With such a force, the cover 49 is deformed such that it is downward, ie in the direction of the force, yields.
  • the deformation of the cover 49 is limited by the width of the constriction 53.
  • the constriction 53 is compressed in the region of the wall 50 of the outer tube 11 in such a way that sections of opposing walls 59, 60 of the constriction 53 lie on one another. Outside the area of the wall 50, the constriction 53 forms a cavity 61.
  • constriction 53 deliberately deforms an annular ring of the cover 49 that is delimited by the wall 50 and the end of the groove.
  • the depth of the constriction 53 or groove determines the width of the circular ring. In connection with the width of the constriction 53, the depth thereof ensures that the deformation of the cover 49 or the circular ring is limited and always remains in the elastic range, so that the predetermined breaking point 58 does not break.
  • FIGS. 8 and 9 show a preferred embodiment of a closure 62 from the point of view of production technology.
  • the closure 62 consists of a cover 63 which is formed in one piece with a wall 64 of the outer tube.
  • the cover 63 consists of a lower, cylindrical section 65 and an upper, conical section 66.
  • the lower section 65 is assigned a constriction 67 and a notch 68.
  • the constriction 67 is designed in a special way. Starting from a wall 69 of the cover 63, the constriction 67 is designed as a circumferential groove.
  • the depth of the constriction 67 is a multiple, in particular a double, greater than the thickness of the wall 64 of the outer tube.
  • the width of the constriction is made thicker than in the exemplary embodiment according to FIG. 6 for reasons of production technology, so that the constriction 67 maintains its functionality for limiting the deformation of the cover 63, webs 70 are assigned to the same.
  • the webs 70 are offset from one another over the circumference of the constriction 67 by an angle of approximately 90 °.
  • the webs 70 limit the opposite direction of the force Missile launching the deformation of the cover 63 and keep it always in the elastic range.
  • the invention discussed above can also be used with other signaling means, for example signal cartridges.
  • the signal is not fired from an outer tube, but from a cartridge case.
  • the design of a closure of the cartridge case can be analogous to the exemplary embodiments according to FIGS. 3-9.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Casings For Electric Apparatus (AREA)
  • Train Traffic Observation, Control, And Security (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)
  • Telephone Function (AREA)
EP95106002A 1994-04-28 1995-04-21 Dispositif de signalisation, en particulier roquette de signalisation Expired - Lifetime EP0679860B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE9407053U DE9407053U1 (de) 1994-04-28 1994-04-28 Signalmittel, insbesondere Signalrakete
DE9407053U 1994-04-28

Publications (3)

Publication Number Publication Date
EP0679860A2 true EP0679860A2 (fr) 1995-11-02
EP0679860A3 EP0679860A3 (fr) 1997-01-08
EP0679860B1 EP0679860B1 (fr) 2000-03-15

Family

ID=6907960

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95106002A Expired - Lifetime EP0679860B1 (fr) 1994-04-28 1995-04-21 Dispositif de signalisation, en particulier roquette de signalisation

Country Status (2)

Country Link
EP (1) EP0679860B1 (fr)
DE (2) DE9407053U1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1255089A3 (fr) * 2001-05-01 2003-06-25 Gregory P. Shelton Fusée pyrotechnique munie d'un dispositif pour retarder la descente dans l'air après son allumage
EP3623741A1 (fr) 2018-09-12 2020-03-18 Rheinmetall Waffe Munition GmbH Unité de tir pour munition

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103183132B (zh) * 2011-12-29 2015-09-09 任明琪 弹射用动力源单元体和航母燃气蒸汽弹射器及弹射方法

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2032357A (en) * 1932-10-06 1936-03-03 Max W Fischer Pyrotechnic unit
GB461253A (en) * 1935-08-12 1937-02-12 Horace Ainley Roberts Improvements in or relating to shot gun cartridges
US2918003A (en) * 1957-04-29 1959-12-22 Mine Safety Appliances Co Deep water cartridge
US3127837A (en) * 1961-04-27 1964-04-07 Driaire Inc Shot shell construction
DE1280096B (de) * 1964-10-24 1968-10-10 Nico Pyrotechnik Leucht- oder Signalstern
US3782285A (en) * 1972-09-14 1974-01-01 Us Navy Flare cartridge
DE2543935A1 (de) * 1975-10-02 1977-04-07 Dynamit Nobel Ag Schrotpatrone
DE7600548U1 (de) * 1976-01-10 1976-07-15 Comet Gmbh Pyrotechnik-Apparatebau, 2850 Bremerhaven Raketenkoerper
DE7737498U1 (de) * 1977-12-09 1978-09-28 Pyrotechnische Fabrik F. Feistel Kg, 6719 Goellheim Vorrichtung zum abschiessen von pyrotechnischen signalen o.dgl.
FR2469691B1 (fr) * 1979-11-09 1985-11-15 Lacroix E Tous Artifices Munition lance-leurres electromagnetiques a chargement simplifie
DE3707062A1 (de) * 1987-01-29 1988-08-25 Comet Pyrotech Signalmittel, insbesondere signalrakete oder -patrone
DE3902381A1 (de) * 1988-01-28 1989-08-10 Comet Pyrotech Feuerwerksrakete
DE9001399U1 (de) * 1990-02-07 1990-04-12 Haisch + Straub GmbH, 7332 Eislingen Spitzkappe für Feuerwerksraketen

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1255089A3 (fr) * 2001-05-01 2003-06-25 Gregory P. Shelton Fusée pyrotechnique munie d'un dispositif pour retarder la descente dans l'air après son allumage
EP3623741A1 (fr) 2018-09-12 2020-03-18 Rheinmetall Waffe Munition GmbH Unité de tir pour munition

Also Published As

Publication number Publication date
EP0679860B1 (fr) 2000-03-15
DE59507978D1 (de) 2000-04-20
DE9407053U1 (de) 1994-07-28
EP0679860A3 (fr) 1997-01-08

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