EP2153162B1 - Pyrotechnische kette zur zündung einer hauptantriebsladung für eine rakete - Google Patents

Pyrotechnische kette zur zündung einer hauptantriebsladung für eine rakete Download PDF

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Publication number
EP2153162B1
EP2153162B1 EP08805914A EP08805914A EP2153162B1 EP 2153162 B1 EP2153162 B1 EP 2153162B1 EP 08805914 A EP08805914 A EP 08805914A EP 08805914 A EP08805914 A EP 08805914A EP 2153162 B1 EP2153162 B1 EP 2153162B1
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EP
European Patent Office
Prior art keywords
arming
charge
retarder
locking member
active position
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.)
Active
Application number
EP08805914A
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English (en)
French (fr)
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EP2153162A2 (de
Inventor
Philippe Biz
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.)
Safran Ceramics SA
Original Assignee
SNECMA Propulsion Solide SA
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Publication of EP2153162A2 publication Critical patent/EP2153162A2/de
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Publication of EP2153162B1 publication Critical patent/EP2153162B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
    • F42C15/184—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a slidable carrier
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/34—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by a blocking-member in the pyrotechnic or explosive train between primer and main charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/36—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein arming is effected by combustion or fusion of an element; Arming methods using temperature gradients

Definitions

  • the invention relates to a pyrotechnic chain for igniting a main engine load of a missile after ejection thereof from a launch tube or carrier, as described for example in the document DE 4 127 023 A .
  • the ignition of the main propulsive charge of a missile occur if the missile has received sufficient acceleration at launch, preferably in value and duration, and after the missile has traveled a sufficient distance.
  • a known solution for this purpose is to use a pyrotechnic ignition system which comprises an arming device capable of entering the "armed” state under the effect of the acceleration imparted during the ejection of the missile, a pyrotechnic delay defining a duration between ejection and ignition of the main charge, and a safety device with microbeads interposed between the main charge and a relay charge ignited at the end of combustion of the pyrotechnic delay.
  • the microbead security device comprises a bed of microbeads which flow through openings disengaged by the arrival of the arming device in the "armed” state, thus, in case of non-passage to the "armed” state.
  • the microbeads could not flow or flow completely and form a screen preventing the ignition of the load Although the ignition is applied to the main load despite ignition of the relay charge after combustion of the pyrotechnic delay, such a solution is implemented by the applicant for the "Mistral" tactical missile propulsion systems.
  • the object of the invention is to propose a solution with improved reliability, especially in the long term, to the problem of the ignition safety of the main propulsive charge of missiles after ejection.
  • locking in "armed” mode occurs after a time defined by the combustion of a first delay (arming delay) and is not dependent on the flow of a bed of microbeads.
  • Longer-term reliability can then be obtained because the behavior for a long life of a pyrotechnic composition is well controllable and characterizable.
  • the screen device may be a bed of balls that can flow through a closed opening when the cocking device is in the rest position and disengaged when the cocking device is in the active position.
  • the beads preferably microbeads, have no delay function. They fulfill a security function.
  • the balls In the case where the second relay load is carried by a moving part released during the ignition of the first relay load, the balls also provide a damping function to stop a sudden arrival of the second relay load in the position of ignition of the main charge.
  • the pyrotechnic chain shown on the figure 1 comprises a cylinder 10 in the rear part of which is housed a pyrotechnic arresting support 20 and in the front part of which is housed a part 30 carrying a pyrotechnic trajectory delay.
  • the terms "back” and “front” are used herein with reference to the direction of propagation of the combustion along the pyrotechnic chain.
  • the carrier 20 has a sleeve-shaped sealingly engaged within the cylinder 10. Inside the sleeve 20 there is fixed a pyrotechnic delay arming 22 comprising a pyrotechnic composition to block 22 housed in a casing 22 b.
  • the arming delay is immobilized by a ring 23 screwed into the sleeve 20 and acting on a gland 24 and a seal 25 at the rear of the arming delay.
  • an initiating charge or squib 26 At the rear of the arm delay 22 is arranged an initiating charge or squib 26, a passage 27 communicating the housing of the squib 26 with the block of pyrotechnic composition 22 is through the ring 23, the stuffing tow 24 and the envelope 22 b .
  • the pin 26 (shown only on the figure 1 ) Is mounted in a holder 26 screwed into a ring 28 itself is screwed on the rear wall of cylinder 10.
  • a pyrotechnic relay charge 29 At the front of the pyrotechnic composition block 22 a is fixed a pyrotechnic relay charge 29.
  • the support 20 is immobilized axially in the cylinder 10 by a pin 11 forming a locking member.
  • a split ring 12 prestressed circumferentially is housed in an annular groove formed in the outer surface of the support 20.
  • an annular housing 20b is formed by a portion of the support 20 of reduced diameter in the vicinity of the front end 20c of this support.
  • the support piece 30 of the pyrotechnic trajectory delay has a hollow piston shape in which is housed a block of pyrotechnic composition 32 forming the trajectory delay.
  • the block housing 32 in the part 30 is delimited by a rear side wall 30 has a through passage 31.
  • a pyrotechnic charge relay 34 At the front of the trajectory delay 32 is disposed a pyrotechnic charge relay 34.
  • the piece 30 is immobilized axially in the cylinder 10 by a pin 13 forming a locking member.
  • a prestressed compression spring 35 is housed between the part 30 and the sleeve 20, the spring 35 supported at its ends to the wall 30 and has an internal shoulder 20a of the sleeve 20.
  • the spring 35 provides a holding pins 11 , 13 in their locking position despite possible vibrations when the ignition system is in the non-active state.
  • An arming device in the form of a ring 40 is engaged on the cylinder 10 from its front end. At its rear end portion 40 has the cocking ring 40 is engaged on the outer surface of the cylinder 10.
  • the rear end portion 40a of the arming ring 40 abuts against an outer shoulder 10a of the cylinder 10 and is locked in this position by a ball 14 forming a locking member.
  • the ball 14 is housed in a bore formed in the wall of the cylinder 10 being retained on the inside by the front end portion 20c of the sleeve 20 engaged in the cylinder 10.
  • the ball 14 protrudes outside the cylinder 10 in a housing 41 formed by a portion of the arming ring 40 having an inner diameter greater than that of the rear end portion 40 a. In the position of the figure 1 , the ball 14 projects at the rear axial end of the housing 41.
  • Another ball 16 is housed in a hole in the wall of the cylinder 10. In the position of the figure 1 , the ball 16 projects internally into a housing 36 formed by a part of the part 30 of reduced outside diameter, while, on the outside, the ball 16 is blocked by a portion 40b of the ringing ring engaged without play on the cylinder 10.
  • the pyrotechnic chain is provided with a bottom 50 in the form of a ring screwed on the front end of the cylinder 10.
  • An envelope 51 containing a pyrotechnic charge relay 52 is supported in the front part of the cylinder 10 and immobilized by the rear face of a shoulder 50 in the bottom 50.
  • the cover 51 opens to the front to communicate through a passage 53 with a load (not shown) forming the ignition charge of the main propellant charge missile.
  • a gland 54 compresses a gasket 55 against the front face of the shoulder 50 a.
  • the casing 51 is provided with a bottom whose central portion 51 has a reduced thickness forms a lid.
  • a spring 42 not prestressed or weakly prestressed in compression is housed between the bottom 50 and an outer shoulder 43 of the cocking ring.
  • a bed of balls 60 is disposed between the bottom of the casing 51, on the rear side, and the front of the piece 30 and the trajectory retardation 32.
  • the bed of balls 60 is contained in the cylinder 10.
  • This one has openings 18 distributed at its periphery, in the vicinity of the bottom of the casing 51.
  • the openings 18 are closed off on the outside by the front end portion 40 c of the cocking ring which is engaged without play on the cylinder 10.
  • the ring arming 40 has openings 44 disposed at its periphery in the same manner as the openings 18. In the position of the figure 1 , the openings 44 are closed on the inside by the cylinder 10.
  • the cylinder 10 and the cocking ring 45 are immobilized with respect to each other in rotation in order to avoid misalignment of the openings 18 and 44. This effect, a pin 45 is engaged and immobilized in a radial orifice of the cylinder and projects into a slot 46 formed longitudinally in the rear part of the cocking ring 40.
  • the balls 60 are for example ceramic or glass microbeads whose diameter is typically 100 to 500 microns, for example about 200 microns.
  • the pyrotechnic chain is closed at its periphery by a case 62, for example metal, which connects the bottom 50 to the cylinder 10.
  • Seals such as 21, 47, 56, 57 seal between the cylinder 10 and the support 20, between the case 62 and the cocking ring 40 and between the case 62 and the bottom 50.
  • the operation of the pyrotechnic chain is as follows.
  • the pin 26 is lit when the missile is ejected. As known per se, this ignition can be achieved by power supply by means of contacts provided on a tube or launching support.
  • the generated pressure acting on the sleeve 20 causes the break of the pin 11, the displacement of the sleeve 20 from its position of rest, against the elastic force exerted by the spring 35, and the ignition of the load 22 has the pyrotechnic arresting delay 22.
  • the prestressed rod 12 is housed in a housing 19 formed in the inner wall of the cylinder 11, blocking the sleeve 20 in the active position.
  • the ball 14 is erased in the housing 20b formed at the rear of the front end portion 20c of the sleeve 20.
  • the acceleration imparted to the missile causes a forward movement of the cock ring 40, the locking ball 14 being erased.
  • the spring 42 is compressed.
  • the arming ring 40 is in an advanced position sufficient so that the ball 16 ceases to be blocked by the portion 40 b of the arming ring and is opposite a portion 40 d of the cocking ring 40 of inner diameter greater than that of the portion 40 b and progressively connecting thereto.
  • the openings 44 are then facing the openings 18 and the flow of the balls 60 can begin. It will be noted that the openings 44 are preferably of a size substantially greater than that of the openings 18. It is then in the position illustrated on FIG. figure 2 , arming authorization position.
  • the spring 42 is calibrated to oppose the arrival in the arming clearance position with release of the ball 16 if the initial acceleration of the missile is less than a predetermined minimum value.
  • the relay charge 29 When the combustion of the charge 22 has the pyrotechnic arming delay 22 is complete, the relay charge 29 is turned on. The generated pressure acting on the piston member 30 causes the pin 13 to break, releasing the piece 30 while at the same time the pyrotechnic path delay 32 is turned on. Under the action of the spring 35 and the gases produced by the relay charge 29, the piece 30 is moved forwards from its retracted position and the part of the piece 30 located at the rear of the housing 36 comes to block the ball 16 in a locking position ( figure 3 ). In this position, by pressing on the part 40 d of the cocking ring, the ball 16 acts as a non-return vis-à-vis the cocking ring 40, which can slightly go back when the acceleration launching stops producing its effects ( figure 4 ). The cocking ring 40 is then in the active position and the flow of the balls 60 continues. The active position of the arming ring corresponding to the "armed" mode.
  • the forward movement of the part 30 continues as the flow of balls 60 until arrival of the booster charge 34 in contact with the cap 51a when all the balls 60 have passed, while the combustion of the trajectory retardation 32 continues.
  • the balls 60 provide a damping function to avoid abrupt contact with the lid 51 a .
  • the position reached is that of the figure 4 .
  • the duration of combustion of the pyrotechnic trajectory delay 32 is chosen to ensure that the ignition of the main charge takes place at a point on the trajectory of the missile located at a sufficient distance from the launching location.
  • the relay charge 34 is on and ignites the relay charge 52 to cause the ignition of the main propellant charge, as shown in FIG. figure 5 .
  • the ignition safety is ensured as follows.
  • the ball 16 is returned to the housing 36 and blocked by the portion 40 b of the arming ring 40 as in the rest position.
  • There is no movement of the part 30 and the distance between the booster charge 34 and the lid 51a is such that the combustion gases generated by the booster charge 34 will disperse and can ensure the breakage of the cap 51a, the remaining microbeads 60 optionally in the cylinder providing additional security.
  • the ignition relay charge of the main engine of the missile is not initiated.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Woven Fabrics (AREA)
  • Portable Nailing Machines And Staplers (AREA)

Claims (5)

  1. Pyrotechnische Kette zum Zünden einer Haupttreibladung eines Flugkörpers nach dessen Ausstoßen, umfassend:
    - eine Schärfungsvorrichtung (40), die zwischen einer Ruhestellung, oder "nicht scharfen" Position, und einer aktiven Stellung, oder "scharfen" Position, als Reaktion auf das Ausstoßen des Flugkörpers beweglich ist,
    - ein erstes Verriegelungsorgan (14) zum Verriegeln der Schärfungsvorrichtung in der Ruhestellung,
    - ein zweites Verriegelungsorgan (16) zum Verriegeln der Schärfungsvorrichtung in der aktiven Stellung,
    - eine pyrotechnische Schärfungsverzögerung (22),
    - einen Zünder (26), der angeordnet ist, um bei Ausstoßen des Flugkörpers gezündet zu werden und das Zünden der Schärfungsverzögerung (22) sowie die Freigabe des ersten Verrieglungsorgans (14) zu bewirken, um den Übergang der Schärfungsvorrichtung in die aktive Stellung zuzulassen,
    - eine von der Schärfungsverzögerung (22) getrennte pyrotechnische Flugbahnverzögerung (32),
    - eine erste Verstärkungsladung (29), die angeordnet ist, um am Ende des Abbrennens der Schärfungsverzögerung (22) gezündet zu werden und das Zünden der Flugbahnverzögerung (32) sowie die Betätigung des zweiten Verriegelungsorgans (16) zu bewirken, um die Schärfungsvorrichtung (40) in der aktiven Stellung zu verriegeln, wenn sie sich in dieser Stellung befindet, sowie
    - eine zweite Verstärkungsladung (34), die angeordnet ist, um am Ende des Abbrennens der Flugbahnverzögerung (32) gezündet zu werden und das Zünden der Hauptladung zu bewirken, wenn die Schärfungsvorrichtung (40) sich in der aktiven Stellung befindet.
  2. Pyrotechnische Kette nach Anspruch 1, dadurch gekennzeichnet, daß sie ferner umfaßt:
    - ein bewegliches Teil (30), das die Flugbahnverzögerung (32) und die zweite Verstärkungsladung (34) trägt, wobei das bewegliche Teil zwischen einer eingefahrenen Position, in der die zweite Verstärkungsladung sich nicht in der Position zum Zünden der Hauptladung befindet, und einer ausgefahrenen Position, in der die zweite Verstärkungsladung sich in der Position zum Zünden der Hauptladung befindet, verschiebbar ist, und
    - ein drittes Organ zum Verriegeln (13) des beweglichen Teils in der eingefahrenen Position, wobei das dritte Verriegelungsorgan angeordnet ist, um als Reaktion auf das Zünden der ersten Verstärkungsladung (26) freigegeben zu werden.
  3. Pyrotechnische Kette nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß sie ferner umfaßt:
    - eine einen Schutzschild bildende Vorrichtung (60), die zwischen der zweiten Verstärkungsladung (34) und der Hauptladung angeordnet ist, und
    - Mittel (18, 44) zum schrittweisen Entfernen der einen Schutzbild bildenden Vorrichtung, wenn sich die Schärfungsvorrichtung (40) in der aktiven Stellung befindet.
  4. Pyrotechnische Kette nach Anspruch 3, dadurch gekennzeichnet, daß die einen Schutzschild bildende Vorrichtung ein Bett aus Kugeln (60) umfaßt, die durch Öffnungen (18, 44), welche verschlossen sind, wenn die Schärfungsvorrichtung (40) sich in der Ruhestellung befindet, und freigegeben sind, wenn die Schärfungsvorrichtung sich in der aktiven Stellung befindet, abrollen können.
  5. Pyrotechnische Kette nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß sie ferner umfaßt:
    - einen Träger (20) für die Schärfungsverzögerung, der zwischen einer Ruhestellung und einer aktiven Stellung beweglich ist,
    - ein viertes Verriegelungsorgan (11) zum Verriegeln des Trägers der Schärfungsverzögerung in der Ruhestellung und
    - ein fünftes Verriegelungsorgan (12) zum Verriegeln des Trägers der Schärfungsverzögerung , wenn er in die aktive Stellung gelangt ist,
    - wobei das Zünden des Zünders (26) die Freigabe des vierten Verriegelungsorgans sowie das Bewegen des Trägers der Schärfungsverzögerung in Richtung seiner aktiven Stellung bewirkt, in der er die Freigabe des ersten Verriegelungsorgans (14) bewirkt, um zuzulassen, daß die Schärfungsvorrichtung (40) in die aktive Stellung gelangt.
EP08805914A 2007-06-07 2008-06-03 Pyrotechnische kette zur zündung einer hauptantriebsladung für eine rakete Active EP2153162B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0755562A FR2917159B1 (fr) 2007-06-07 2007-06-07 Chaine pyrotechnique d'allumage d'une charge principale de propulsion d'un missile.
PCT/FR2008/050971 WO2009001000A2 (fr) 2007-06-07 2008-06-03 Chaine pyrotechnique d'allumage d'une charge principale de propulsion d'un missile

Publications (2)

Publication Number Publication Date
EP2153162A2 EP2153162A2 (de) 2010-02-17
EP2153162B1 true EP2153162B1 (de) 2010-12-08

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Application Number Title Priority Date Filing Date
EP08805914A Active EP2153162B1 (de) 2007-06-07 2008-06-03 Pyrotechnische kette zur zündung einer hauptantriebsladung für eine rakete

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EP (1) EP2153162B1 (de)
AT (1) ATE491133T1 (de)
DE (1) DE602008003925D1 (de)
FR (1) FR2917159B1 (de)
WO (1) WO2009001000A2 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU197618U1 (ru) * 2019-12-11 2020-05-18 Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" (Госкорпорация "Росатом") Средство задействования

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH353285A (fr) * 1960-05-20 1961-03-31 Energa Dispositif de sécurité à temps, notamment pour fusée de prjectile
CH617262A5 (de) * 1977-12-02 1980-05-14 Sarmac Sa
DE3743536A1 (de) * 1987-12-22 1989-07-06 Diehl Gmbh & Co Zuender bei einem traegergeschoss
DE4127023C2 (de) * 1991-08-16 1999-09-23 Rheinmetall W & M Gmbh Treibladungsanzünder mit einem durch eine Feder vorgespannten Schlagbolzen

Also Published As

Publication number Publication date
DE602008003925D1 (de) 2011-01-20
WO2009001000A2 (fr) 2008-12-31
EP2153162A2 (de) 2010-02-17
FR2917159A1 (fr) 2008-12-12
FR2917159B1 (fr) 2009-09-04
WO2009001000A3 (fr) 2009-04-16
ATE491133T1 (de) 2010-12-15

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