EP0226577B1 - Gefechtskopf - Google Patents

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Publication number
EP0226577B1
EP0226577B1 EP85903286A EP85903286A EP0226577B1 EP 0226577 B1 EP0226577 B1 EP 0226577B1 EP 85903286 A EP85903286 A EP 85903286A EP 85903286 A EP85903286 A EP 85903286A EP 0226577 B1 EP0226577 B1 EP 0226577B1
Authority
EP
European Patent Office
Prior art keywords
warhead
reflector
fact
accordance
antenna
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
Application number
EP85903286A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0226577A1 (de
Inventor
Klaus Gersbach
Kaus Loske
Rainer Schmieg
Hans Egon Schepp
Klaus Dietmar Karius
Rolf Hellwig
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.)
Rheinmetall Industrie AG
Original Assignee
Licentia Patent Verwaltungs GmbH
Rheinmetall GmbH
Telefunken Systemtechnik 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 Licentia Patent Verwaltungs GmbH, Rheinmetall GmbH, Telefunken Systemtechnik AG filed Critical Licentia Patent Verwaltungs GmbH
Priority to AT85903286T priority Critical patent/ATE45623T1/de
Publication of EP0226577A1 publication Critical patent/EP0226577A1/de
Application granted granted Critical
Publication of EP0226577B1 publication Critical patent/EP0226577B1/de
Expired legal-status Critical Current

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/08—Means for collapsing antennas or parts thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/006—Mounting of sensors, antennas or target trackers on projectiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C1/00—Impact fuzes, i.e. fuzes actuated only by ammunition impact
    • F42C1/14—Impact fuzes, i.e. fuzes actuated only by ammunition impact operating at a predetermined distance from ground or target by means of a protruding member

Definitions

  • the invention relates to a warhead according to the preamble of claim 1.
  • Warheads of the generic type are known from DE-A-3 322 927.
  • a projectile is disclosed in which two reflectors are arranged diametrically, which can be folded radially over the cross section of the projectile.
  • the sensors are arranged in the reflector itself.
  • a disadvantage of this known arrangement is that the reflectors are very small per se and a complicated and space-consuming drive mechanism is required.
  • the device described is only manufactured in one piece with the carrier. A separate production of warhead or projectile head and the folding device with sensor and reflector is not disclosed.
  • DE-A-3 137 198 discloses a fold-out mechanical touch switch which activates an active charge when it hits a target. An indication of how such a sensor could be used to receive electromagnetic waves cannot be found in this laid-open publication.
  • the present invention has for its object to provide a fold-out device with reflector and sensor, which can be manufactured as an assembly separately from the warhead or projectile head, and which has a reflector as large as possible.
  • the warhead according to the invention thus has the advantage that adjustment problems are practically eliminated and time and cost-saving assembly of the warhead is still feasible even if the sensor unit on the one hand and the other components of the warhead on the other hand are manufactured in different operating sites.
  • the invention is explained in more detail below with reference to the drawing.
  • the fold-out antenna 13 itself, the means for unfolding the antenna and the means for further processing of the target-characteristic radiation picked up by the antenna 13 are designed as an integral assembly 12 which can be inserted into the warhead 1.
  • the Components of this assembly 12 are clearly highlighted by the hatching indicated in FIG. 1 a to FIG. 4. This measure makes it possible to completely separate the assembly 12 including the antenna 13 from the other components of the assembly. to produce the fencing head 1 and to adjust it precisely, which is of crucial importance for the functionality of the warhead 1, since in the frequency ranges in question in the microwave range or optical range of the electromagnetic spectrum, an extremely precise alignment of the fold-out antenna 13 with the receiving elements is necessary.
  • the pre-adjusted assembly 12 is therefore connected to the warhead 10 in an uncomplicated manner only, without critical adjustment measures which are more expensive to manufacture being additionally necessary.
  • the antenna 13 can be easily aligned in the proposed manner to fractions of a millimeter on the radiation-sensitive sensor components of the assembly 12.
  • FIG. 3, FIG. 4 and FIG. 5 A further embodiment variant of the warhead is explained with reference to FIG. 3, FIG. 4 and FIG. 5, in which the antenna 13 is pivotably mounted about an axis 63 which is inclined only by a small angle with respect to the longitudinal axis 2 of the warhead 1, so that it is in The rest position lies entirely within the housing 10 of the warhead 1 and, in the operating position, projects beyond the diameter of the housing 10 when pivoted.
  • FIG. 3 shows the antenna 13 of the assembly 12 pivoted into the housing 10 for protection, while FIG. 4 shows the antenna 13 swung out in the working position.
  • FIG. 5 is a rear view of the warhead 1 with the antenna 13 according to FIG. 4 swung out.
  • the combination of the fold-out antenna 13 and the means for unfolding the antenna and the means for further processing the radiation picked up by the antenna 13 to form the easily assembled pre-adjusted compact assembly 12 led to particular problems in the development of a sufficiently compact but operationally reliable under the most difficult conditions Folding mechanism for the antenna 13.
  • This folding mechanism has to move the antenna 13 from its protected position inside the housing 10 of the warhead 1 (see FIG. 1, FIG. 3) into its working position outside the housing 10 (see FIG. 2 and FIG. 4). and lock it there so securely that folding is prevented on the one hand and on the other hand the required precision of focusing the radiation picked up by the antenna 13 onto the radiation-sensitive sensor elements is guaranteed.
  • the fold-out means have to perform their function under the influence of strong acceleration forces, which arise due to the rotational movement of the warhead 1 about its longitudinal axis 2 or during the braking process during the descent.
  • FIG. 6, FIG. 7 and FIG. 8 show a first exemplary embodiment of the means for unfolding the antenna 13. These means comprise a gas pressure slide 60, the construction of which is first explained further with reference to FIG. 12.
  • the gas pressure slide 60 consists of a housing 100 with, for example, cylindrical inner bore 106 and a piston rod 107 slidably mounted in this inner bore 106 and a pyrotechnic device which develops propellant gases when ignited.
  • the pyrotechnic device comprises an ignition element 10, which can preferably be actuated by remote electrical ignition, a charge 102 and a propellant charge 103.
  • the aforementioned components of the pyrotechnic device are arranged on the bottom of the housing 100 and close it off on one side while moving in the direction of the piston rod 107 are delimited from the inner bore 106 by a nozzle plate 104.
  • the nozzle plate contains bores through which the propellant gases developed by propellant 103 can spread in the direction of inner bore 106.
  • This inner bore 106 is formed with a different diameter such that a shoulder 104 is formed, on which the end piece 109 of the piston rod 107 rests in the rest position of the piston rod.
  • the end piece 109 of the piston rod 107 rests at a predeterminable distance from the surface of the nozzle plate 104, so that a damping space 109 extends between the end face of the piston rod 107 and the surface of the nozzle plate 104.
  • FIG. 6, FIG. 7 and FIG. 8. 6 shows a warhead with a fold-out mechanism for the antenna 13, which is designed in accordance with the schematic drawing of FIG. 1 and FIG. 2, in a schematic longitudinal sectional illustration, in which, however, only the essential components of the assembly 12 are shown, while omitting details that are not essential to the invention.
  • the antenna 123 is mounted within the housing 10 on an axis 62 which is arranged perpendicularly with respect to the longitudinal axis 2 of the warhead and has to reach its working position by an angle of more than 180 ° from its rest position shown in FIG Housing 10 are folded out.
  • a gear 62 is also rotatably mounted about the axis 63 and connected to the antenna 13 in a rotationally fixed manner.
  • the piston rod 107 of the gas pressure slide 60 is designed on its end piece 61 lying outside the housing 100 as a toothed rack which has a row of teeth 61 '. The teeth of this row of teeth 61 'rest in the rest position of the antenna 13 (FIG.
  • the gear wheel 62 has a flat surface 64 on part of its circumference.
  • the piston rod 107 has an inclined surface 65 which can be displaced on the flat surface 64 by longitudinal displacement of the piston rod 107 during the unfolding of the antenna 13 of the gear 62 comes to rest. This safety measure reliably prevents the folded-out antenna 13 from folding back out of its working position into the rest position.
  • FIG. 7 shows a rear view of the warhead according to FIG. 6 and clearly shows the gear 62.
  • FIG. 8 shows an enlarged detailed illustration of the fold-out means according to the exemplary embodiment of the warhead according to FIG. 6 in the extended state of the antenna 13, in which the end piece 61 of the piston rod 107 designed as a rack rests with its inclined surface 65 on the flat surface 64 of the gear wheel 62 and thereby the Antenna 13 locked.
  • FIG. 9 shows a schematic representation of the antenna 13 shown in the rest position and the antenna 13 ′ shown in dashed lines in the working position.
  • FIG. 10 does not show a rear view of the warhead according to FIG. 9.
  • FIG. 11 shows, as a view from the direction of arrow 91, an enlarged detailed view of components of the folding mechanism of the antenna 13, 13 '.
  • the fold-out mechanism again comprises a gas pressure slide 60 with a piston rod 107.
  • the end piece of the piston rod 107 lying outside the housing 100 of the gas pressure slide 60 carries a fork 110, in the arms of which two rollers 111 around axes 112 are rotatably supported such that the peripheral surfaces of the rollers 111 lie in front of the fork ends.
  • another roller 113 is rotatably mounted about an axis.
  • the piston rod 107 is first pressed out of the housing 100 of the gas pressure slide 60, which acts on the back surface of the antenna 13 by means of the rollers 111 rotatably mounted in the arms of the fork 110, offset from the pivot point, about the axis 63.
  • the antenna 13 is pivoted about the axis of rotation 63 by this forward movement of the piston rod 107.
  • the pin 90 of the antenna 13 swings through the arms of the fork 110, so that the roller 113 arranged on the fork base comes to rest on the outer contour 91 of the pin 90 which is designed as a control surface.
  • a spring-loaded pin 114 is provided, which, when the working position of the antenna 13 is reached, engages in a hole arranged in the antenna holder near the axis of rotation 63 (FIG. 10).
  • a cable pulley 140 is connected in a rotationally fixed manner to the antenna 13 pivotably mounted about the axis 63.
  • a traction cable 141 is wound, one end piece of which is connected to a piston rod 107 which is mounted in a longitudinally displaceable manner in a gas pressure slide 60.
  • the gas pressure slide 60 is designed such that when the pyrotechnic propellant charge is ignited, the piston rod 107 is retracted.
  • This modification of the gas pressure slide 60 is readily possible for the person skilled in the art, since he only has to arrange gas bores in a suitable manner in order to design the gas guide in such a way that the piston rod 107 is acted on in the direction of insertion. By pushing in the piston rod 107, a pull is exerted on the pull cable 140.
  • This train in turn results in a rotary movement of the rope pulley 140 and the antenna 13 connected to it.
  • the antenna 13 can, as already described above, be locked by a spring-loaded bolt which engages in a correspondingly arranged bore.
  • the gas pressure slide 60 can also be actuated by a high-tension gas which is stored in a pressure vessel.
  • the reflection surface of the essentially circular antenna 13 is expediently designed as a segment of a paraboloid, the antenna 13 also containing the vertex of the paraboloid, which is in the extended state of the antenna in the vicinity of its axis of rotation.
  • FIG. 15 shows an enlarged view of a section through the fold-out mechanism with the antenna in the rest position.
  • a shaft 13a is screwed into the housing 12b of the assembly 12, about the axis A of which the antenna reflector 13 is rotatably mounted.
  • the antenna reflector 13a includes, with a hollow cylindrical projection 13d, the shaft 13a formed with a stepped diameter.
  • the outer jacket of the shoulder 13d carries a pinion 13b which meshes with a drive pinion 150b.
  • An essentially cylindrical piston 150 is slidably mounted in the recess 12a of the housing 153 and carries an essentially cuboidal pressure piece 152 on its end piece facing the pyrotechnic charge 153a.
  • the pressure piece 152 is form-fitting to the preferably square Adjusted cross-section recess 12a and therefore serves as a rotation lock when the piston 150 slides within the recess 12a.
  • a spiral groove 150c is made in the outer circumferential surface of the piston 150, into which drivers 12c, which are firmly connected to the drive pinion 150b, engage.
  • the spiral groove 150c extends over an angle of rotation of 180 ° with a transmission ratio of 1: 1 of the transmission consisting of the drive pinion 150b and the pinion 13b.
  • the spiral groove 150c ends in the rear area of the piston facing the pressure piece 152, 150 in a recess 151 running essentially parallel to the longitudinal axis of the piston 150, the height of which corresponds approximately to the height of the conical head portion 150a of the piston 150.
  • the antenna is unfolded as follows: after igniting the pyrotechnic propellant charge 153a, the pressure piece 152 connected to the piston 150 is subjected to gas pressure and presses the piston 150 through the recess 12a in the direction of the antenna reflector 13. Because the piston 150 is rotated within the recess 12a and the drivers 12c connected to the pinion 150b engage in the spiral groove 150c, a rotational movement of the drive pinion 150b takes place in accordance with the movement of the piston 150, or in other words, the translational movement of the piston 150 becomes a rotational movement of the drive pinion 150b. Since the pinion 13b meshes with the drive pinion 150b, rotation of the drive pinion 150b also causes the antenna reflector 13 to rotate about its axis of rotation A.
  • the conically widened recess 13c in the antenna carrier 13 comes to lie above the recess 12a when the antenna carrier 13 has stopped rotating, so that the piston 150 with its frustoconical head part 150a snaps into the conical extension of the recess 13c and in this way locks the antenna carrier 13 pivoted into the working position.
  • this working position has been reached, there is no further rotation of the antenna carrier 13, since the drivers 12c have now reached the straight-line region 151 of the spiral groove 150c and therefore no more torque is exerted on the drive pinion 150b.
  • This last described position of the antenna carrier 13 is shown in FIG. 16.
  • FIGS. 17 and 18 show the arrangement of the piston 150 in the housing 153 shown in longitudinal section, while FIG. 18 shows the piston 150 and housing 153 separately from one another.
  • FIGS. 19 to 22 A last exemplary embodiment of the invention is explained with reference to FIGS. 19 to 22.
  • This exemplary embodiment differs from the exemplary embodiment according to FIG. 15, FIG. 16 essentially in that a rotary movement of the antenna reflector is brought about without the interposition of a transmission consisting of drive pinion 150b and pinion 13b. By eliminating the gearbox, weight is saved.
  • a piston 150 is again provided as the drive means, which carries at least one spiral groove 150c in its outer jacket.
  • the piston 150 is in turn connected to a pressure piece 152 which can be acted upon by a pyrotechnic charge 153a.
  • the antenna reflector 13 is rotatably mounted on the housing 153 and connected to it by a thread 120a.
  • the piston 150 extends through the antenna reflector 13, with threads 190 attached there engaging in the spiral groove of the piston 150.
  • the pitch of the spiral groove arranged in the piston 150 and the thread 190 in the antenna reflector 13 are dimensioned such that, with maximum translational movement of the piston 150 after ignition of the propellant charge 153a, the antenna carrier 13 is rotated by 180 °.
  • the rotary movement of the antenna reflector 13 takes place on a rotating plane, the angle of attack of which corresponds to half the amount of the difference between the angle of attack of the antenna reflector 13 in the rest position and the angle of attack of the antenna reflector 13 in the working position.
  • the antenna reflector 13 Since the antenna reflector 13 has a thread 190, the slope of which runs in the same direction as the slope of the spiral groove 150c in the piston 1 50, the antenna reflector 13 is pulled by the locking thread 21 Oa against the rotating plane and clamped to it when it reaches its working position.
  • This exemplary embodiment of the invention therefore requires a comparatively low outlay on mechanical parts and is therefore characterized by a small space requirement in the rest position.
  • inexpensive, precise manufacture is made possible and the play-free fixation of the antenna reflector 13 in its working position.
  • This working position is shown in FIG. 21, while the rest position of the antenna carrier is indicated in FIG. 20.
  • the antenna reflector 13 In the working position according to FIG. 21, the antenna reflector 13 is pivoted outward by 180 ° due to the translational movement of the piston 150 and is screwed to the housing 153 and the housing 12a of the structural unit 12 on its rotational plane by means of the fixing thread 21a.
  • the antenna carrier 13 which has come into the working position can be further secured by additional securing means (FIG. 22).
  • securing means essentially consist of a cylinder 221, arranged at a radial distance from the piston 150 in the housing 12b, with a conical head 221a, which snaps into a shape-matched truncated cone-shaped recess 220 in the antenna carrier 13 after it has been pivoted into the working position.
  • the piston 221 is loaded by a compression spring, not shown in FIG. 22, which presses it into the recess 220.
  • the bottom of the piston 221 is connected via a transfer channel 223 to the interior of the housing 153, in which the piston 150 and the pressure piece 152 connected to it are slidably mounted.
  • the piston 150 and the pressure piece 152 in the housing 153 have been driven upward and the boundary surface of the pressure piece 152 facing the propellant charge 153a has passed the transfer duct 223, the bottom of the cylinder 221 is also gas-pressure-fed via the transfer duct 223 of the propellant charge 153a and thus engages in the bore 220 of the antenna carrier 13, which has been pivoted into its working position by the movement of the piston 150.
  • a pyrotechnic propellant charge 222 is also arranged in the bore receiving the piston 221, which may be ignited by the propellant charge 153a itself, either electrically or indirectly via a pyrotechnic delay chain.
  • the pyrotechnic delay chain can optionally also be arranged in the transfer hole 223.
  • reaching the locked position of the antenna carrier 13, characterized by the engagement of the piston 221 in the recess 220, can also be used to arm the securing means of the payload part of the warhead. This can be brought about, for example, in that the movement of the piston 221 actuates a switch (not shown in the drawing) which closes an electrical ignition circuit.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerials With Secondary Devices (AREA)
  • Details Of Aerials (AREA)
  • Ceramic Products (AREA)
EP85903286A 1984-07-30 1985-07-12 Gefechtskopf Expired EP0226577B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT85903286T ATE45623T1 (de) 1984-07-30 1985-07-12 Gefechtskopf.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3428051 1984-07-30
DE19843428051 DE3428051A1 (de) 1984-07-30 1984-07-30 Wirkkoerpereinheit

Publications (2)

Publication Number Publication Date
EP0226577A1 EP0226577A1 (de) 1987-07-01
EP0226577B1 true EP0226577B1 (de) 1989-08-16

Family

ID=6241922

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85903286A Expired EP0226577B1 (de) 1984-07-30 1985-07-12 Gefechtskopf

Country Status (11)

Country Link
EP (1) EP0226577B1 (enrdf_load_stackoverflow)
JP (1) JPS62500042A (enrdf_load_stackoverflow)
AU (1) AU4603085A (enrdf_load_stackoverflow)
BR (1) BR8506845A (enrdf_load_stackoverflow)
DE (2) DE3428051A1 (enrdf_load_stackoverflow)
DK (1) DK145786A (enrdf_load_stackoverflow)
GR (1) GR851820B (enrdf_load_stackoverflow)
IL (1) IL75937A (enrdf_load_stackoverflow)
NO (1) NO861288L (enrdf_load_stackoverflow)
PT (1) PT80879B (enrdf_load_stackoverflow)
WO (1) WO1986000980A1 (enrdf_load_stackoverflow)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3508453A1 (de) * 1985-03-09 1986-09-11 Rheinmetall GmbH, 4000 Düsseldorf Nutzlastgeschoss
SE452505B (sv) * 1986-03-27 1987-11-30 Bofors Ab Substridsdel med svengbart anordnad maldetektor
DE3700342A1 (de) * 1987-01-08 1988-07-28 Rheinmetall Gmbh Submunitionskoerper mit einer zielerfassungsvorrichtung
FI82324C (fi) * 1989-03-29 1991-02-11 Valtion Teknillinen Antennanordning.
DE4017353A1 (de) * 1990-05-30 1991-12-05 Rheinmetall Gmbh Flugkoerper mit einer zieldetektionseinrichtung
DE19507253C2 (de) * 1995-03-02 1999-11-18 Sel Alcatel Ag Fernschaltmodul
RU2137268C1 (ru) * 1998-04-17 1999-09-10 Козлов Алексей Николаевич Антенна для радиовысотомера баллистического летательного аппарата
RU2137267C1 (ru) * 1998-04-21 1999-09-10 Щербинин Игорь Владимирович Антенна для радиовысотомера баллистического летательного аппарата
RU2151454C1 (ru) * 1999-03-22 2000-06-20 Козлов Алексей Николаевич Антенна для радиовысотомера баллистического летательного аппарата
WO2012082957A1 (en) 2010-12-15 2012-06-21 Skybox Imaging, Inc. Ittegrated antenna system for imaging microsatellites
DE102020127361A1 (de) 2020-10-16 2022-04-21 Vega Grieshaber Kg Sensor mit einer verlagerbaren Antenne und Verfahren zum Betreiben eines Sensors

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3322927A1 (de) * 1983-06-25 1985-01-03 Rheinmetall GmbH, 4000 Düsseldorf Von einem lastengeschoss oder flugkoerper abwerfbarer geschosskopf

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB600555A (en) * 1943-08-18 1948-04-13 Vickers Armstrongs Ltd Improvements in or relating to aerial bombs
FR907737A (fr) * 1944-11-15 1946-03-20 Bombe à antenne provoquant l'explosion avant l'arrivée au sol
FR1285932A (fr) * 1960-12-26 1962-03-02 Nord Aviation Charge creuse
DE3137198C2 (de) * 1981-09-18 1984-10-11 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Zünder mit einschiebbarem Abstandshalter

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3322927A1 (de) * 1983-06-25 1985-01-03 Rheinmetall GmbH, 4000 Düsseldorf Von einem lastengeschoss oder flugkoerper abwerfbarer geschosskopf

Also Published As

Publication number Publication date
DE3428051A1 (de) 1986-03-06
DK145786D0 (da) 1986-03-26
BR8506845A (pt) 1986-09-23
IL75937A (en) 1991-06-10
DE3572393D1 (en) 1989-09-21
PT80879B (de) 1986-11-24
GR851820B (enrdf_load_stackoverflow) 1985-11-26
NO861288L (no) 1986-06-19
WO1986000980A1 (en) 1986-02-13
EP0226577A1 (de) 1987-07-01
DK145786A (da) 1986-03-26
PT80879A (de) 1985-08-01
JPS62500042A (ja) 1987-01-08
AU4603085A (en) 1986-02-25
IL75937A0 (en) 1985-12-31

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