US3839963A - Proximity fuse for missiles - Google Patents
Proximity fuse for missiles Download PDFInfo
- Publication number
- US3839963A US3839963A US00349124A US34912473A US3839963A US 3839963 A US3839963 A US 3839963A US 00349124 A US00349124 A US 00349124A US 34912473 A US34912473 A US 34912473A US 3839963 A US3839963 A US 3839963A
- Authority
- US
- United States
- Prior art keywords
- detonator
- striker
- fuse
- weight
- cap
- 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.)
- Expired - Lifetime
Links
Images
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
- F42C13/00—Proximity fuzes; Fuzes for remote detonation
- F42C13/02—Proximity fuzes; Fuzes for remote detonation operated by intensity of light or similar radiation
-
- 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
- F42C19/00—Details of fuzes
- F42C19/06—Electric contact parts specially adapted for use with electric fuzes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C9/00—Time fuzes; Combined time and percussion or pressure-actuated fuzes; Fuzes for timed self-destruction of ammunition
- F42C9/14—Double fuzes; Multiple fuzes
- F42C9/148—Proximity fuzes in combination with other fuzes
Definitions
- ABSTRACT A compact fuse designed to be armed after cessation of acceleration and provided with a plurality of safety means; a cap adapted to be set in an inoperative position by a rotation of 90 with reference to the fuse body, a cover for the cap adapted to collapse towards the striker and to prevent its releasing operation in case of a premature impact, a detonator-carrier adapted to be shifted laterally out of registry with the striker, a weight controlled by inertia and controlling operation of the striker and an arming weight releasing through inertia in striker.
- the present invention has for its object preventing premature ignition of a fuse and ensuring fuse ignition upon a missile reachinga point at a predetermined distance from the objective or from grounder upon impact therewith. Fuses of this type are already known which are generally extremely complex both electrically and mechanically and which are not wholly reliable for all conditions of use.
- the invention removes these drawbacks by means of a fuse for missiles, of the type considered, which is mechanically and electrically very simple while it is perfectly reliable.
- the invention comprises a fuse including a cap rotatable with reference to the fuse body and terminating with a conical point forming a deformable radome, the deformable radome protecting the detecting aerial and being rigid with the electronic system forming a compact unit which is slidable after the manner of a striker piston.
- the fuse also employs a mechanism including a detonator-carrier adapted to slide transversely within the body under the action of a spring or of centrifugal force, if required, said detonator-carrier being held normally aside by the end of the rod of an axial striker the front end of which forms a cylindrical tailpiece round which is slidingly fitted a striker weight urged forwardly by a spring and locked in its inoperative position by a first ball engaging a first groove in the tail-piece.
- a mechanism including a detonator-carrier adapted to slide transversely within the body under the action of a spring or of centrifugal force, if required, said detonator-carrier being held normally aside by the end of the rod of an axial striker the front end of which forms a cylindrical tailpiece round which is slidingly fitted a striker weight urged forwardly by a spring and locked in its inoperative position by a first ball engaging a first groove in the tail-piece.
- Said first ball is itself held in position by a second ball or the like part adapted to move transversely and locked by an arming weight adapted to move within the cap in parallelism with the striker and to be urged forwardly by a further spring while it includes an extension towards the rear constituted by a rod passing through the spring.
- the striker weight includes further locking means constituted, for instance, by a circlips adapted to be locked within a further groove of the tail-piece after the said weight has traveled sufficiently'towards the rear upon starting of the missile and after the arming weight has itself receded through inertia and has thus released the balls.
- the striker weight is returned forwardly under the action of its spring, the front end of the striker tail-piece engages the striker piston and, simultaneously, its rear tip releases the detonator-carrier permitting its transverse movement which sets the detonator in front of said tip and closes at the end of its travel the general switch controlling the electronic circuitry.
- the mechanism includes furthermore an electric primer arranged in parallelism within the striker and communicating through ports formed within the cap and the body with the main detonator when the latter is moved into an axial position.
- the electric primer is connected with the electronic detecting means through a delaying condenser. The whole arrangement is such that after a rotation, through say 90, of the cap with reference to the fuse body, the port connecting the electric primer in the cap registers no longer with the corresponding port inthe fuse body whereby the first series of firing means.
- FIG. 1 is an axial cross-sectional view of a missile proximity fuse formed in accordance with this invention.
- FIG. 2 is an axial cross-section, at right angles with that of FIG. 1, through line IIII of FIG. 4.
- FIG. 3 shows on a larger scale a detail of the central portion of FIG. 1.
- FIG. 4 is a transverse cross-section through line IV-IV of FIG. 1.
- FIG. 5 is a cross-section through line V-V of FIG. 1.
- the fuse illustrated includes a body 1 and a cap 2 revolvably carried by said body 1 over which it is held by an expansible ring 3 held by a screw 4 (FIG. 2) both inside a groove in the cap and a groove in the extension 5 of the body inside the cap.
- the body 1 includes a rear threaded section 6 so that it may be screwed as usual into the nose of a missile.
- the cap 2 is provided with a'cover 7 of a plastic perme able for hyperfrequency waves and acting as a radome while being sufficiently deformable. Inside said cover 7 is housed the aerial 8 of the hyperfrequency system forming a proximity radar system.
- the system including the aerial 8, the hyperfrequency circuit 9 and the electronic detecting circuit 10 is carried as a compact unit within a metal socket 11 by means of a molded piece of plastic, the whole arrangement being fitted inside a bore located to the front of the cap 2, so as to slide axially.
- the fuse will operate under direct impact against the target, the deformation of the cover 7 allowing said sliding arrangement to operate as a striker piston while it is urged forwards when inoperative by a spring 12a.
- the actual mechanical part of the fuse includes a central metal block 13 bored axially at 14, a tubular striker weight 15 slidably mounted in said bore 14 and being permanently urged forwardly by a spring 16.
- a tubular striker weight 15 slidably mounted in said bore 14 and being permanently urged forwardly by a spring 16.
- the cylindrical tailpiece 17 of a striker may slide in its turn, the cylindrical tailpiece 17 of a striker 18, ending to the rear with a pointed end and slidingly engaging the center of a disc 20 rigid with the block 13 rigidly secured in its turn to the cap 2 by means of a screw 21 (FIGS. 1 and 4).
- the same block-13 is provided with a further bore 22 parallel with the central bore 14 (FIG. 1) and wherein an arming weight 23 slides, which arming weight is urged forwardly by a spring 24.
- the arming weight 23 extends rearwardly, so as to form the rear tail-piece 25 of a smaller diameter passing through the spring 24 and slidingly engaging a port 26 in the disc 20.
- the weight 23 locks a ball 27 housed inside a transverse bore 28 in the block 13 and acting on a further ball 29 housed in a bore 30 in the weight 15 associated with the striker, said ball 29 engaging anannular groove 31 in the tail-piece 17 of the striker.
- the weight 15 on the striker is provided with a milled portion 30a which allows the ball 27 to enter slightly within said weight, so as to prevent its rotation.
- the transverse bore 28 opens into the longitudinal bore 22 through a preferably hammered or crimped clearance port as shown in FIG. 3, so as to prevent the ball 27 dropping into said bore 22.
- the tail-end 17 of the striker is provided with a further sharp-edged annular groove 32 adapted to cooperate with a circlips 32a engaging a groove and slot in the weight of the striker, so as to ensure the interlocking of the parts 15 and 17.
- a further disc 33 against which the arming weight 23 normally abuts.
- a parallelepipedic housing 35 the rear opening of which is closed by a disc 36 while a transversely shiftable substantially parallelepipedic detonator-carrier 37 is slidingly carried inside said housing.
- a bore provided in said detonator-carrier is engaged by the detonator 38 the front end of which registers with a port 39 in the carrier 37 while a further smaller bore 40 in said carrier in parallelism with the first-mentioned bore is adapted to house the rear tip 19 of the striker when the detonator-carrier 37 is in its outermost position illustrated in FIGS. 1 and 2.
- the return spring may be replaced by an eccentric weight the centrifugal force acting on which urges the detonator-carrier in the direction of said arrow 43.
- the block 34 and also the body 1 are provided with a longitudinal bore 44 affording a passage towards the rear for the rear tail-piece 25 of the arming weight 23.
- a port 45 extends through the disc 36.
- a tube 46 filled with an explosive acting as a relay for the explosive in the detonator 38 when the latter faces the striker, said relay acting then on the booster charge 47 enclosed in the cup-shaped member 48 screwed over the rear end of the body 1.
- the central block 13 is laterally milled at 49 (FIGS. 2 and 4), so as to house a block 50 of plastic in which are embedded a number of electric parts including an electric primer 51 with its feeding wires.
- the flame produced by said primer 51 is transmitted through the sloping bore 52in the disc and a further sloping bore 53 in the auxiliary block 34, to the detonator 38 through the port 39 when the latter registers with the fuse axis as described below.
- a condenser 54 feeding the electric primer 51 into which it is discharged upon detection by the circuit l0.
- the rear extension 55 of the plastic block 50 passes through the fuse body as provided by suitable openings, which allows the cap 2 to turn by one quarter of revolution with reference to the body 1, said extension 55 serving thus as an abutment for such a rotation.
- the rear end of the extension 55 carries two connectors 56 adapted to engage corresponding parts in a further block of plastic 57 in which are embedded the supply batteries 58, said block 57 being revolvable around the explosive-filled tube 46.
- the extension 55 of the block 50 is provided furthermore with a transverse port 59 inside which lie two elastic conductive blades 60 adapted to be short-circuited upon insertion between them of a shaped member 61 having an annular retaining groove.
- the shaped member 61 is fitted in the detonator-carrier 37 with the interposition of an insulating sleeve 62.
- the two conductive blades are inserted in a circuit section passing through one of the connectors while the other connector ensures direct feeding.
- it is essential to electrically connect the parts embedded or carried in the plastic block 12 with those carried by the plastic block 50 and its extension 55. This can be obtained by yielding wires which are not illustrated without this leading to any difficulty since the two blocks 12 and 50 do not revolve with reference to each other and, furthermore, move towards each other only upon impact, that is at a moment when the electric connections are no longer necessary.
- the electric connections between the blocks 55 and 57 are rigid by reason of the above'disclosed possibility of rotation of the block 57, so as to avoid the drawbacks arising from the use of a connection through yielding wires.
- the fuse is adjustable for operation as illustrated, that is the cap 2 is angularly set on the body 1 in a manner such that the oblique bores 52 and 53 register and that the port 26 registers also with the bore 44.
- the acceleration to which the fuse is subjected produces through inertia the recoil of the arming weight 23 which, after a sufficient travel, releases the ball 27 which, in its turn, releases the ball 29.
- the striker weight 15 returns forwardly under the action of the spring 16 and carries along with it the actual striker 18.
- the battery 58 feeds then the circuit of the radar and of the detector and loads the condenser 54 which, after a delay of say 5 to 6 seconds, is ready to operate.
- the missile continues its flight until the radar detects the presence of a target or the proximity of ground.
- the electronic system causes the discharge of the condenser 54 into the primer 51, which leads to the firing of the detonator 38 and consequently to the explosion of the missile. This corresponds to normal operation.
- the safety at the muzzle is ensured by the fact that throughout the duration of the acceleration and even after collapse of the arming weight 23 and after the striker weight 15 has receded, the spring 16 remains compressed, so that said striker weight 15 cannot bring the tail-piece 17 into contact with the electronic block 12. If the missile meets an obstacle during its acceleration, the block 12 is pushed inwardly and the tail-piece 17 of the striker can no longer travel far enough for releas ing the detonator-carrier 37 when the acceleration has come to end, which as precedingly breaks both the electric circuit and the two 'pyrotechnical sequential parts.
- the cap 2 must be turned round its axis through say 90 with reference to the body 1, so as to be set in a safety position. Under such conditions and in addition to all the above described safeties, said rotation causes the rear tail-piece 25 of the arming weight and the bore 26 in the disc to be out of registry with the bore' 44 in the block 34, which positively locks the mechanical part of the fuse and the corresponding safety means.
- the sloping bores 52 and 53 are out of registry, which produces a gap in the pyrotechnical chain of sequential parts adjacent the electric primer 51 while the electric circuit is broken by the locking of the detonator carrier in its inoperative position, the port 39 and the detonator 38 being also out of registry with the bore 53 and the tube 46.
- Absolute safety is thus obtained through a plurality of means, so that nothing whatever can lead to an explosion during transportation or dropping through a parachute.
- the fuse according to the invention has thus reached a high degree of reliability and safety while it is comparatively simple, sturdy and of a reduced bulk.
- a proximity fuse for missiles including a body adapted to be fitted on the nose of a missile and a cap revolvably carried by the body and provided with a cover forming a radome permeable to hyperfrequency radiation, said fuse being characterized by the fact that the radome is inade of a deformable material and encloses a detecting aerial rigidly mounted on an electronic section adapted to slide inside the cap so as to form a striking plunger, said section including detecting means, the fuse including a detonator-carrier and detonator adapted to slide transversely in the body, first means for applying a transverse force on said detonator-carrier, switch means responsive to said detonatorcarrier, said detonator-carrier being normally held in an inoperative position by the rear tip of the rod of an axial striker having a fronttail-piece, a striker weight slidable on said tail-piece and urged forwardly by a spring and locked when inoperative by a first ball engaging
- the switch means includes two elastic conductive blades having an interval therebetween, a conductive member provided with an annular retaining groove mounted on the detonator-carrier in alignment with said interval whereby transverse movement of said detonatorthe cap with reference to the body, the rearward extension of the first block ending with connecting plugs engaging a second block of plastic molded over the battery, a rear booster and a tube containing an explosive forming a pyrotechnic relay between the detonator and the rear booster, the second block surrounding said tube and mounted for rotation thereabout.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Air Bags (AREA)
- Nozzles (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Radar Systems Or Details Thereof (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR7212527A FR2180159A5 (ko) | 1972-04-10 | 1972-04-10 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3839963A true US3839963A (en) | 1974-10-08 |
Family
ID=9096601
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US00349124A Expired - Lifetime US3839963A (en) | 1972-04-10 | 1973-04-09 | Proximity fuse for missiles |
Country Status (9)
Country | Link |
---|---|
US (1) | US3839963A (ko) |
JP (1) | JPS4948200A (ko) |
DE (1) | DE2318039A1 (ko) |
FR (1) | FR2180159A5 (ko) |
GB (1) | GB1371480A (ko) |
IL (1) | IL41998A (ko) |
IT (1) | IT983756B (ko) |
NL (1) | NL7304993A (ko) |
NO (1) | NO135446C (ko) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3977329A (en) * | 1974-10-25 | 1976-08-31 | Motorola, Inc. | Shock-acceleration activated function selector |
US4451960A (en) * | 1979-03-15 | 1984-06-05 | Molitor Industries, Inc. | Method of producing multiple coil, multiple tube heat exchanger |
US4930419A (en) * | 1989-05-23 | 1990-06-05 | Serby Victor M | Ordnance fuze power source |
US20090151585A1 (en) * | 2007-12-15 | 2009-06-18 | Junghans Microtec Gmbh | Safety and Arming Unit for a Fuze of a Projectile |
WO2009104112A3 (en) * | 2008-02-21 | 2009-12-23 | Rafael Advanced Defense Systems Ltd. | Guided weapon with in-flight-switchable multiple fuze modes |
US20100058946A1 (en) * | 2008-09-08 | 2010-03-11 | Geswender Chris E | Smart fuze guidance system with replaceable fuze module |
US10845175B2 (en) | 2017-08-17 | 2020-11-24 | Luis Eduardo Tobón Trujillo | Electromechanical contact fuse for multipurpose aircraft ammunition |
US10935357B2 (en) | 2018-04-25 | 2021-03-02 | Bae Systems Information And Electronic Systems Integration Inc. | Proximity fuse having an E-field sensor |
DE102021123375A1 (de) | 2021-09-09 | 2023-03-09 | Rwm Schweiz Ag | Zündvorrichtung für eine Munition, insbesondere eine Mittelkalibermunition und zugehöriges Verfahren zum Zünden oder zur Selbstzerlegung einer Munition, insbesondere einer Mittelkalibermunition |
DE102022106883A1 (de) | 2022-03-23 | 2023-09-28 | Rheinmetall Air Defence Ag | Sicherungseinheit für einen Zünder, Verwendung der Sicherungseinheit und Verfahren zur Aktivierung eines Zünders mit dieser Sicherungseinheit |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3418759A1 (de) * | 1984-05-19 | 1985-11-21 | Diehl GmbH & Co, 8500 Nürnberg | Zuendsicherungseinrichtung |
EP0758737A1 (de) * | 1995-08-16 | 1997-02-19 | Schweizerische Eidgenossenschaft vertreten durch die Eidg. Munitionsfabrik Thun der Gruppe für Rüstungsdienste | Verfahren und Vorrichtung zum Sichern und zum Schärfen eines Zündsatzes und/oder eines mechanisch gezündeten Munitionskörpers |
DE19926754C2 (de) * | 1999-06-11 | 2001-08-23 | Buck Neue Technologien Gmbh | Sicherheitseinrichtung für Munition mit einer elektrochemischen Zelle als Energiequelle |
RU2767809C1 (ru) * | 2021-07-30 | 2022-03-22 | Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" (Госкорпорация "Росатом") | Предохранительно-исполнительный механизм взрывателя |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2870713A (en) * | 1955-06-09 | 1959-01-27 | Saloranta Arvo Ensio | Fuse for shells |
US2900911A (en) * | 1943-11-30 | 1959-08-25 | Louis D Statham | Fuze |
US2951444A (en) * | 1958-09-12 | 1960-09-06 | Jr Clayton E Hunt | Fuze arming and safety mechanism |
US3151558A (en) * | 1960-08-08 | 1964-10-06 | Lunati Charles Joseph | Percussion fuze with inertia type arming means |
-
1972
- 1972-04-10 FR FR7212527A patent/FR2180159A5/fr not_active Expired
-
1973
- 1973-04-09 US US00349124A patent/US3839963A/en not_active Expired - Lifetime
- 1973-04-09 NO NO1444/73A patent/NO135446C/no unknown
- 1973-04-10 IT IT22823/73A patent/IT983756B/it active
- 1973-04-10 DE DE2318039A patent/DE2318039A1/de active Pending
- 1973-04-10 IL IL41998A patent/IL41998A/en unknown
- 1973-04-10 NL NL7304993A patent/NL7304993A/xx unknown
- 1973-04-10 GB GB1722473A patent/GB1371480A/en not_active Expired
- 1973-04-10 JP JP48040781A patent/JPS4948200A/ja active Pending
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2900911A (en) * | 1943-11-30 | 1959-08-25 | Louis D Statham | Fuze |
US2870713A (en) * | 1955-06-09 | 1959-01-27 | Saloranta Arvo Ensio | Fuse for shells |
US2951444A (en) * | 1958-09-12 | 1960-09-06 | Jr Clayton E Hunt | Fuze arming and safety mechanism |
US3151558A (en) * | 1960-08-08 | 1964-10-06 | Lunati Charles Joseph | Percussion fuze with inertia type arming means |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3977329A (en) * | 1974-10-25 | 1976-08-31 | Motorola, Inc. | Shock-acceleration activated function selector |
US4451960A (en) * | 1979-03-15 | 1984-06-05 | Molitor Industries, Inc. | Method of producing multiple coil, multiple tube heat exchanger |
US4930419A (en) * | 1989-05-23 | 1990-06-05 | Serby Victor M | Ordnance fuze power source |
US7980179B2 (en) * | 2007-12-15 | 2011-07-19 | Junghans Microtec Gmbh | Safety and arming unit for a fuze of a projectile |
US20090151585A1 (en) * | 2007-12-15 | 2009-06-18 | Junghans Microtec Gmbh | Safety and Arming Unit for a Fuze of a Projectile |
WO2009104112A3 (en) * | 2008-02-21 | 2009-12-23 | Rafael Advanced Defense Systems Ltd. | Guided weapon with in-flight-switchable multiple fuze modes |
US20110041720A1 (en) * | 2008-02-21 | 2011-02-24 | Rafael Advanced Defense Systems Ltd. | Guided weapon with in-flight-switchable multiple fuze modes |
US8689692B2 (en) | 2008-02-21 | 2014-04-08 | Rafael Advanced Defense Systems Ltd. | Guided weapon with in-flight-switchable multiple fuze modes |
US7819061B2 (en) * | 2008-09-08 | 2010-10-26 | Raytheon Company | Smart fuze guidance system with replaceable fuze module |
US20100058946A1 (en) * | 2008-09-08 | 2010-03-11 | Geswender Chris E | Smart fuze guidance system with replaceable fuze module |
US10845175B2 (en) | 2017-08-17 | 2020-11-24 | Luis Eduardo Tobón Trujillo | Electromechanical contact fuse for multipurpose aircraft ammunition |
US10935357B2 (en) | 2018-04-25 | 2021-03-02 | Bae Systems Information And Electronic Systems Integration Inc. | Proximity fuse having an E-field sensor |
DE102021123375A1 (de) | 2021-09-09 | 2023-03-09 | Rwm Schweiz Ag | Zündvorrichtung für eine Munition, insbesondere eine Mittelkalibermunition und zugehöriges Verfahren zum Zünden oder zur Selbstzerlegung einer Munition, insbesondere einer Mittelkalibermunition |
WO2023036879A1 (de) | 2021-09-09 | 2023-03-16 | Rwm Schweiz Ag | Zündvorrichtung für eine munition, insbesondere eine mittelkalibermunition und zugehöriges verfahren zum zünden oder zur selbstzerlegung einer munition, insbesondere einer mittelkalibermunition |
DE102022106883A1 (de) | 2022-03-23 | 2023-09-28 | Rheinmetall Air Defence Ag | Sicherungseinheit für einen Zünder, Verwendung der Sicherungseinheit und Verfahren zur Aktivierung eines Zünders mit dieser Sicherungseinheit |
WO2023180278A1 (de) | 2022-03-23 | 2023-09-28 | Rheinmetall Air Defence Ag | Sicherungseinheit für einen zünder, verwendung der sicherungseinheit und verfahren zur aktivierung eines zünders mit dieser sicherungseinheit |
Also Published As
Publication number | Publication date |
---|---|
IL41998A (en) | 1976-09-30 |
NO135446C (ko) | 1977-04-05 |
DE2318039A1 (de) | 1973-10-31 |
IT983756B (it) | 1974-11-11 |
NO135446B (ko) | 1976-12-27 |
GB1371480A (en) | 1974-10-23 |
JPS4948200A (ko) | 1974-05-10 |
IL41998A0 (en) | 1973-06-29 |
NL7304993A (ko) | 1973-10-12 |
FR2180159A5 (ko) | 1973-11-23 |
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