EP0226577A1 - Ogive. - Google Patents

Ogive.

Info

Publication number
EP0226577A1
EP0226577A1 EP85903286A EP85903286A EP0226577A1 EP 0226577 A1 EP0226577 A1 EP 0226577A1 EP 85903286 A EP85903286 A EP 85903286A EP 85903286 A EP85903286 A EP 85903286A EP 0226577 A1 EP0226577 A1 EP 0226577A1
Authority
EP
European Patent Office
Prior art keywords
antenna
warhead
housing
piston
warhead according
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
EP85903286A
Other languages
German (de)
English (en)
Other versions
EP0226577B1 (fr
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
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 filed Critical Licentia Patent Verwaltungs GmbH
Priority to AT85903286T priority Critical patent/ATE45623T1/de
Publication of EP0226577A1 publication Critical patent/EP0226577A1/fr
Application granted granted Critical
Publication of EP0226577B1 publication Critical patent/EP0226577B1/fr
Expired legal-status Critical Current

Links

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-OS 32 37 485. They are carried by a flying means of transport such as a missile, projectile or the like. transported over a target area and ejected there, in order to then autonomously record targets and combat recorded targets during a decelerated descent.
  • a flying means of transport such as a missile, projectile or the like. transported over a target area and ejected there, in order to then autonomously record targets and combat recorded targets during a decelerated descent.
  • Warheads of the type described above are exposed to extreme acceleration stresses, so that the antennas of the sensors, which are relatively sensitive to the effects of force, are usually accommodated in a protected manner within the warheads and are only unfolded in the flight phase of the warheads.
  • Such an antenna arrangement also proves to be necessary if a large number of battleballs have to be accommodated in a transport means in spatially tight packing.
  • the invention has for its object to provide a novel warhead in which such adjustment problems are completely 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 ⁇ different operating sites are manufactured.
  • Fig. 1 in a schematic three-dimensional representation with omission of all details not essential to the invention, a first embodiment of a warhead with the antenna folded;
  • Fig.la a section through the warhead according to Fig. 1
  • FIG. 2 the warhead according to FIG. 1 with the antenna in the operating position
  • FIG. 3 shows a second exemplary embodiment of a warhead with the antenna folded in
  • Fig. 7 is a rear view of the warhead of Fig. 6;
  • FIG. 8 is an enlarged view of details of the warhead after. Fig. 6;
  • FIG. 10 a rear view of the warhead shown in FIG. 9;
  • Figure 12 is an enlarged detail view of "used in the '.Aus enclosuresbeiford according to Figures 6 and 9 Gas pressure slider;..
  • Fig. 13 a further embodiment with a cable for unfolding the antenna
  • Fig. 14 a rear view of the warhead according to Fig. 13
  • Fig.15 in a further Asu Equipmentsbeispiel with antenna in the rest position, a section through the Ausklappmech mechanism;
  • FIG. 16 a section through the fold-out mechanism according to FIG. 15 with the antenna in the working position;
  • Fig. 17 Piston and cylinder of the folding mechanism according to Fig. 15, Fig. 16;
  • FIG. 21 shows a section through the fold-out mechanism according to FIG. 20 with the antenna in the working position
  • FIG. 22 a section through the fold-out mechanism according to FIG. 20, FIG. 21, showing locking means for the folded-out antenna.
  • a warhead 1 shows a schematic illustration, omitting all details that are not essential to the invention, of a first exemplary embodiment of a warhead 1, which comprises a payload part 11 arranged in a housing 10.
  • This payload part 11 can be activated by a sensor which responds to a target-characteristic signal which it receives via an antenna 13.
  • the antenna 13 is for reasons of space saving and to prevent damage during the
  • the fold-out antenna 13 itself, the means for unfolding the antenna and the means for further processing the target-characteristic radiation picked up by the antenna 13 are now in the form of an integral assembly which can be inserted into the warhead 1
  • the pre-adjusted assembly 12 is therefore only connected to the battle head 10 in the final assembly of the battle head in an uncomplicated manner, without the need for additional critical and expensive manufacturing adjustments.
  • 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 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.
  • 5 is a rear view of the warhead 1 with the antenna 13 swung out according to FIG. Fig. 4.
  • This fold-out mechanism must namely the antenna 13 from its protected position within the housing 10 of the warhead 1 (see FIG. 1, FIG. 3) in its working position outside the Spend 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 the focusing of the radiation received 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.
  • 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 it is 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 the propellant 103 can spread in the direction of the 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. Through this shoulder 108, the end piece 109 of the piston rod 107 rests at a predeterminable distance from the
  • FIGS. 6, 7 and 8. 6 shows, with omission of details not essential to the invention, in a schematic longitudinal sectional illustration, in which, however, only the essential components of the assembly 12 are shown in section, a warhead with a folding mechanism for the antenna 13, which according to the schematic drawing of FIGS. 1 and FIG. 2 is designed.
  • 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 must be at an angle of to reach its working position.
  • 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 which is 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. 6) on the gear 62 such that the teeth of the row of teeth 61 * mesh with the teeth of the gear 62.
  • the propellant 103 After ignition of the ignition element 101 of the gas pressure slide 60, the propellant 103 develops propellant gases which first penetrate into the damping chamber 109 through the nozzle plate 104 and then move the slidably mounted piston rod 107 in the longitudinal axial direction as it expands further.
  • the antenna 13 is in turn rotated about the axis 63 and in this way reaches its unfolded working position, in which it must be reliably locked because of the high * precision required for the antenna alignment.
  • the gear 62 carries on a part of its U fans a flat surface 64.
  • FIG. 7 shows a rear view of the warhead according to FIG. 6 and clearly shows tooth rack 62.
  • FIG. 8 shows an enlarged detail of the fold-out means according to the exemplary embodiment of the warhead according to FIG. 6 in the unfolded state of the antenna 13, in which case the end piece 61 de piston rod 107 designed as a toothed rack with its inclined surface 65 on the flat surface 64 of the gearwheel 62 rests and thereby locks the antenna 13.
  • FIGS. 9, 10 and 11 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 shows a rear view of the warhead according to FIG. 9.
  • FIG. 11 shows, as a view from the direction of the arrow 91, an enlarged detailed view of components of the fold-out 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 are rotatably mounted about axes 112 such that the peripheral surfaces of the rollers 111 lie in front of the fork ends.
  • another roller 11 is rotatably mounted about an axis.
  • the piston rod 107 After activation of the gas pressure slide 60, the piston rod 107 is first pushed out of the housing 100 of the gas pressure slide 60, which by means of the rollers 111 rotatably mounted in the arms of the fork 110, offset from the fulcrum, about the axis 63 on the back surface of the antenna 13 attacks. As a result of this forward movement of the piston rod 107, the antenna 13 is pivoted about the axis of rotation 63. 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 antenna 13 reaches the working position, engages in a bore 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 ignites, the piston rod 107 is retracted.
  • This modification of the Gas ⁇ press slider 60 to the skilled artisan readily possible, since it must arrange only suitable gas wells, to the gas passage to be designed so that the piston rod 107 is applied to i m slide sense.
  • the antenna 13 can, as already described, by. a spring-loaded bolt which engages in a correspondingly arranged bore can be locked.
  • the gas pressure slide 60 can also be operated 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.
  • FIGS. 15 to 19 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 surrounds the shaft 13a, which has a stepped diameter, with a hollow cylindrical projection 13d.
  • 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 at its end piece facing the pyrotechnic charge 153a.
  • the pressure piece 152 is form-fitting to the preferably square cross Cut equipped recess 12a adapted and therefore serves as an anti-rotation when the piston 150 slides within the recess 12a.
  • a spiral groove 150c is introduced into the outer circumferential surface of the piston 150, into which drivers 12c 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 deployment of the antenna is in this exemplary embodiment of the invention follows: After An ⁇ ignite the pyrotechnic propellant charge 153a is the m supplied with Gas ⁇ pressure it the piston 150 connected to pressure member 152 and pushes the piston 150 through the recess 12a in the direction of the Antenna reflector 13. Since the piston 150 is moved against rotation within the recess 12a and the catches 12c connected to the pinion 150b engage in the spiral groove 150c, a rotation of the drive pinion 150b takes place, or otherwise, depending on the movement of the piston 150 in other words, the translational movement of the piston 150 is converted into a rotational movement of the drive pinion 150b.
  • FIG. 16 shows the arrangement of the piston 150 in the housing 153 shown in longitudinal section
  • 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 embodiment differs from the embodiment according to FIG. 15, FIG. 16 essentially in that a rotational 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. In addition, the drive mechanism can be manufactured more cheaply.
  • a piston 150 is again provided as the drive means, which carries at least one spiral-shaped 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.
  • piston 150 extends through the antenna reflector 13, thread threads 190 located 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 at max.
  • the antenna reflector 13 bears a thread 190, the pitch of which runs in the same direction as the pitch of the spiral groove 150c in the piston 150, the antenna reflector 13 is held against it by the fixing thread 210a
  • This exemplary embodiment of the invention therefore requires a comparatively low outlay on mechanical parts and is characterized by a small space requirement in the rest position. At the same time, however, a cost-effective, precise manufacture is made possible and the play-free fixing of the antenna reflector 13 in its work.
  • 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 ° by translational movement of the piston 150 and is screwed on its rotating plane to the housing 153 and the housing 12a of the structural unit 12 by means of the fixing thread 210a.
  • 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, which is arranged at a radial distance from the piston 150 in the housing 12b and has a conical head 221a, which snaps into a form-fitting, truncated cone-shaped recess 220 in the antenna carrier 13 after it has worked is pivoted.
  • 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.
  • piston 150 and pressure piece 152 in housing 153 are 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 acted upon by gas pressure of the propellant charge 153a via the transfer duct 223 and thus snaps into the bore 220 of the antenna carrier 13, which has been pivoted in its working position by the movement of the piston 150.
  • a pyrotechnic propellant charge 222 is itself 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.
  • Arming the securing means of the payload part of the warhead can be used. 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerials With Secondary Devices (AREA)
  • Ceramic Products (AREA)
  • Details Of Aerials (AREA)

Abstract

Une ogive renfermant une partie pour le charge utile (11) et un capteur avec une antenne à charnière (13) pour activer la partie pour la charge utile (11) après réception d'un signal qui caractérise la cible. Pour en faciliter le montage malgré le haut niveau de précision requis pour l'orientation de l'antenne (13), les moyens pour l'ouverture de l'antenne et les moyens pour le traitement du signal de la cible, detecté par l'antenne (13), sont realisés sous la forme d'un ensemble en une seule pièce, pouvant être introduite dans l'ogive.
EP85903286A 1984-07-30 1985-07-12 Ogive Expired EP0226577B1 (fr)

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
DE19843428051 DE3428051A1 (de) 1984-07-30 1984-07-30 Wirkkoerpereinheit
DE3428051 1984-07-30

Publications (2)

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

Family

ID=6241922

Family Applications (1)

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

Country Status (11)

Country Link
EP (1) EP0226577B1 (fr)
JP (1) JPS62500042A (fr)
AU (1) AU4603085A (fr)
BR (1) BR8506845A (fr)
DE (2) DE3428051A1 (fr)
DK (1) DK145786D0 (fr)
GR (1) GR851820B (fr)
IL (1) IL75937A (fr)
NO (1) NO861288L (fr)
PT (1) PT80879B (fr)
WO (1) WO1986000980A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8730324B1 (en) 2010-12-15 2014-05-20 Skybox Imaging, Inc. Integrated antenna system for imaging microsatellites

Families Citing this family (10)

* 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
DE102020127361A1 (de) 2020-10-16 2022-04-21 Vega Grieshaber Kg Sensor mit einer verlagerbaren Antenne und Verfahren zum Betreiben eines Sensors

Family Cites Families (5)

* 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
DE3322927A1 (de) * 1983-06-25 1985-01-03 Rheinmetall GmbH, 4000 Düsseldorf Von einem lastengeschoss oder flugkoerper abwerfbarer geschosskopf

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO8600980A1 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8730324B1 (en) 2010-12-15 2014-05-20 Skybox Imaging, Inc. Integrated antenna system for imaging microsatellites
US8786703B1 (en) 2010-12-15 2014-07-22 Skybox Imaging, Inc. Integrated antenna system for imaging microsatellites
US9013577B2 (en) 2010-12-15 2015-04-21 Skybox Imaging, Inc. Integrated antenna system for imaging microsatellites

Also Published As

Publication number Publication date
BR8506845A (pt) 1986-09-23
IL75937A (en) 1991-06-10
DE3572393D1 (en) 1989-09-21
WO1986000980A1 (fr) 1986-02-13
EP0226577B1 (fr) 1989-08-16
AU4603085A (en) 1986-02-25
GR851820B (fr) 1985-11-26
DE3428051A1 (de) 1986-03-06
PT80879B (de) 1986-11-24
PT80879A (de) 1985-08-01
DK145786A (da) 1986-03-26
JPS62500042A (ja) 1987-01-08
NO861288L (no) 1986-06-19
DK145786D0 (da) 1986-03-26
IL75937A0 (en) 1985-12-31

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