EP1953494A1 - Vorrichtung zur Lenkung einer Munition mit ausklappbaren Steuerflächen - Google Patents

Vorrichtung zur Lenkung einer Munition mit ausklappbaren Steuerflächen Download PDF

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Publication number
EP1953494A1
EP1953494A1 EP08290062A EP08290062A EP1953494A1 EP 1953494 A1 EP1953494 A1 EP 1953494A1 EP 08290062 A EP08290062 A EP 08290062A EP 08290062 A EP08290062 A EP 08290062A EP 1953494 A1 EP1953494 A1 EP 1953494A1
Authority
EP
European Patent Office
Prior art keywords
gear
pinion
munition
ammunition
support
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
EP08290062A
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English (en)
French (fr)
Other versions
EP1953494B1 (de
Inventor
Cécile Grognet-Quenecan
René Dodu
Geoffroy Deschatre
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.)
Nexter Munitions SA
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Nexter Munitions SA
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 Nexter Munitions SA filed Critical Nexter Munitions SA
Publication of EP1953494A1 publication Critical patent/EP1953494A1/de
Application granted granted Critical
Publication of EP1953494B1 publication Critical patent/EP1953494B1/de
Active legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

  • the technical field of the invention is that of ammunition control devices comprising control surfaces.
  • control surfaces that deploy on trajectory after the firing of the ammunition, control surfaces whose pivot control allows to control the trajectory of the ammunition.
  • Licences FR-2864613 and FR-2846080 thus describe known devices associating a mechanism of deployment of control surfaces and a drive mechanism thereof.
  • control surfaces arranged behind the ammunition body or control surfaces disposed at the front of the munition body ("duck" control surfaces).
  • the purpose of the invention is to propose a control device having a minimal bulk, both at the level of governes itself at the level of the drive mechanism of these control surfaces.
  • the subject of the invention is a device for driving an ammunition, or a submunition, comprising integral control surfaces of a body of the munition and each pivoted by a geared motor, a device characterized in that the control surfaces are formed of elastic sheets foldable by winding around a rear part of the body of the munition and likely to take place to adopt a substantially radial position relative to the body of the ammunition, each surface comprising a support carrying the sheets forming the steering plane, support which is articulated relative to the body of the ammunition at a pivot disposed in front of the steering plane, the support also carrying a rear rack meshing with a pinion driven by the gear reduction motorcycle.
  • the support may comprise a rear tongue which will be held radially by an abutment surface secured to the body of the munition, the tongue sliding on the abutment surface during the pivoting of the rudder.
  • the rack will be advantageously conical.
  • the pinion driving the rack may include a conical portion cooperating with the rack and a cylindrical portion cooperating with a gear driven by the gear motor
  • the cylindrical portion can cooperate via a gear inverter with the gear driven by the gear motor.
  • the figure 1 shows a cargo shell 1 having a body 2 closed by a base 3.
  • the body 2 carries at its front part a rocket 4 and at its rear part a belt 5 sealing the propellant when fired in a weapon.
  • the shell 1 contains a submunition 6 which is equipped with a control device according to the invention (not visible in this figure).
  • the submunition is released on the trajectory by the shell 1 by means of a gas generating composition which is initiated by the rocket 4.
  • the pressure of the gases that are generated inside the shell 1 in the vicinity of the rocket 4 push the submunition 6 backwards. This one then pushes the base 3 whose connection is sheared.
  • the pellet is ejected and the submunition also.
  • FIG. 1 shows a cylinder 7 which ensures, on the one hand, the maintenance of the control surfaces of the sub ammunition 6 and secondly the braking in rotation of the latter.
  • the figure 3 shows the separate submunition of the cylinder 7. It can be seen that the cylinder 7 carries radial wings 8 which, when deployed at the exit of the body of the shell 1, provide rotational braking of the submunition.
  • the cylinder 7 releases in turn the sub-munition 6 itself.
  • the separation between the latter and the cylinder 7 is ensured by means of a gas generating composition (not shown) which is initiated by a safety device and firing at the end of a time period counted from the first expulsion (expulsion cylinder + under ammunition).
  • a plate 10 which is interposed between the submunition 6 and the bottom of the cylinder 7. It is intended to provide a rotational connection of these two elements during firing and braking in rotation. It constitutes the thrust plate of the submunition during this second expulsion.
  • control surfaces 9 integral with the body of the sub-munition 6 are formed of elastic sheets foldable by winding around a rear portion 12 of the body of the submunition 6.
  • the figure 2a shows in a simplified way the control surfaces 9 in their folded position.
  • the figure 2b shows these same control surfaces in their deployed position.
  • Each rudder is formed by the assembly of two thin steel sheets which are welded along their edges and which form once assembled a plane of rudder. This steering plane is delimited by the leading edge BA and the trailing edge BF (see figure 4 ).
  • the space between the sheets is hollow.
  • the sheets are also both fixed to a support 11 which is integral with the body of the sub-munition 6.
  • control surfaces 9 In this deployed position the control surfaces 9 have a substantially radial orientation relative to the body of the ammunition 6.
  • control surfaces are held radially in their folded position by the cylinder 7.
  • the ejection of the cylinder 7 allows the control surfaces to be deployed ( figure 3 ).
  • each rudder 9 is fixed to a support 11 by two welded flanges 13. These flanges are introduced into holes pierced on the sheets and they allow the deformation and the bringing together of the two sheets during the folding and unfolding movements.
  • the support 11 is articulated relative to the body of the submunition 6 at a pivot 14 which is disposed in front of the steering plane 9.
  • the support 11 also carries a rear rack 15 which meshes with a pinion 16 , driven by a steering gear motorcycle.
  • the gear motor is not visible on the figure 5 but it is coaxial with a gear 18 which drives the pinion 16, either directly or by means of a reversing pinion 17.
  • the device according to the invention comprises four geared motors, each driving a rudder 9. These geared motors have their axes parallel to the axis of the submunition.
  • the device has two stages of knuckles 26a and 26b superimposed axially.
  • Two geared motors 25a each have a short shaft carrying a gear 18 which directly drives a pinion 16. These gears and gears form the first stage 26a.
  • Two other geared motors 25b are provided with a long shaft which carries a gear 18 which drives another pinion 16 via a reversing pinion 17. These gears and pinions form the second stage 26b.
  • the first stage 26a thus consists of two identical sets each comprising a gear 18 mounted on a short motor shaft and which drives a pinion 16.
  • the pinions and gears of this first stage are shown in broken lines on the figure 6b .
  • the second stage 26b consists of two identical assemblies each comprising a gear 18 mounted on a long motor shaft and which drives a pinion 16 via a reversing pinion 17.
  • the components of this second stage are represented in solid lines on the figure 6b .
  • This two-stage distribution of the gears makes it easy to accommodate the geared motors while ensuring control surfaces are driven using a compact and robust mechanism.
  • the submunition body 6 has at its rear portion 12 a countersunk housing 19 (see figure 5 ) which is delimited by two intersecting planes 20 which converge in the direction of the pivot 14.
  • This housing 19 is extended by two lateral recesses 21 which allow the passage of the rack 15 during the pivoting of the rudder (see also figure 4 ).
  • the pivoting of the support 11 takes place in a plane (which is materialized by the bottom of the milled housing 19. Given the flatness of this movement while the pinions 16 are fixed and axes parallel to the axis of the sub 6, the rack 15 has a conical profile and cooperates with a conical portion 16a of the pinion 16.
  • the pinion 16 further comprises a cylindrical portion 16b which cooperates with the gear 18 (or with the inverter pinion 17).
  • each support comprises a rear tongue 22.
  • This tongue forms a friction pad which is held radially by an abutment surface 23 secured to the body of the submunition 6 ( figure 4 ).
  • This abutment surface 23 is an insert on a bottom 24 secured to the submunition and which closes the housing of the different gears.
  • each support 11 slides on the abutment surface 23 which also ensures its mechanical retention.
  • the device according to the invention has a certain number of advantages.
  • each rudder 9 is relatively wide, the mechanical drive means can be housed very behind the sub-munition thus releasing a significant volume for the payload.
  • each rudder 9 is made possible by the articulation of each rudder 9 at a pivot 14 located in front of the leading edge (BA) of the rudder while the rotation drive is provided by a motor that meshes with a rack next to the trailing edge (BF) of the rudder.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)
  • Catching Or Destruction (AREA)
  • Sowing (AREA)
  • Toys (AREA)
  • Accommodation For Nursing Or Treatment Tables (AREA)
  • Manipulator (AREA)
EP08290062A 2007-01-31 2008-01-23 Vorrichtung zur Lenkung einer Munition mit ausklappbaren Steuerflächen Active EP1953494B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0700659A FR2911954B1 (fr) 2007-01-31 2007-01-31 Dispositif de pilotage d'une munition a gouvernes deployables

Publications (2)

Publication Number Publication Date
EP1953494A1 true EP1953494A1 (de) 2008-08-06
EP1953494B1 EP1953494B1 (de) 2010-05-26

Family

ID=38521363

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08290062A Active EP1953494B1 (de) 2007-01-31 2008-01-23 Vorrichtung zur Lenkung einer Munition mit ausklappbaren Steuerflächen

Country Status (5)

Country Link
EP (1) EP1953494B1 (de)
AT (1) ATE469333T1 (de)
DE (1) DE602008001317D1 (de)
ES (1) ES2346721T3 (de)
FR (1) FR2911954B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2322896A1 (de) * 2009-11-13 2011-05-18 BAE SYSTEMS plc Kragen für Munition
WO2011058359A1 (en) * 2009-11-13 2011-05-19 Bae Systems Plc Guidance device
EP2423637A3 (de) * 2010-08-25 2015-07-08 BAE Systems Rokar International Ltd. System und Verfahren zum Lenken einer Granate während des Fluges

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112093032B (zh) * 2020-11-05 2021-02-09 成都云鼎智控科技有限公司 无人飞行器飞行控制系统及涵道风扇安装与电传接口模块
CN112093033B (zh) * 2020-11-05 2021-02-09 成都云鼎智控科技有限公司 无人飞行器飞行控制系统
CN112027064B (zh) * 2020-11-06 2021-07-30 成都云鼎智控科技有限公司 无人飞行器飞行控制系统及舵机定位模块
CN112141349B (zh) * 2020-11-27 2021-02-26 成都云鼎智控科技有限公司 无人飞行器发动机的控制系统

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4296895A (en) * 1979-01-15 1981-10-27 General Dynamics Corporation Fin erection mechanism
FR2623898A1 (fr) 1987-11-26 1989-06-02 France Etat Armement Dispositif de deploiement d'une ailette de projectile
EP0333681A1 (de) 1988-03-16 1989-09-20 Aktiebolaget Bofors Entrollbare Flächen oder Flossen für Lenkwaffen oder andere Geschosse
DE4025515A1 (de) 1990-08-11 1992-02-13 Messerschmitt Boelkow Blohm Tragfluegel fuer aus einem rohr startende flugkoerper
US5630564A (en) * 1993-10-19 1997-05-20 Versatron Corporation Differential yoke-aerofin thrust vector control system
EP0905473A1 (de) 1997-09-24 1999-03-31 Giat Industries Grosskalibriges und weitreichendes Artilleriegeschoss
FR2846080A1 (fr) 2002-10-17 2004-04-23 Giat Ind Sa Dispositif de deploiement et d'entrainement de gouvernes de projectile
FR2864613A1 (fr) 2003-12-31 2005-07-01 Giat Ind Sa Dispositif de deploiement et d'entrainement de gouvernes d'un projectile
EP1855076A1 (de) * 2006-05-12 2007-11-14 LFK-Lenkflugkörpersysteme GmbH Wickelflügeln eines Flugkörpers

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4296895A (en) * 1979-01-15 1981-10-27 General Dynamics Corporation Fin erection mechanism
FR2623898A1 (fr) 1987-11-26 1989-06-02 France Etat Armement Dispositif de deploiement d'une ailette de projectile
EP0333681A1 (de) 1988-03-16 1989-09-20 Aktiebolaget Bofors Entrollbare Flächen oder Flossen für Lenkwaffen oder andere Geschosse
DE4025515A1 (de) 1990-08-11 1992-02-13 Messerschmitt Boelkow Blohm Tragfluegel fuer aus einem rohr startende flugkoerper
US5630564A (en) * 1993-10-19 1997-05-20 Versatron Corporation Differential yoke-aerofin thrust vector control system
EP0905473A1 (de) 1997-09-24 1999-03-31 Giat Industries Grosskalibriges und weitreichendes Artilleriegeschoss
FR2846080A1 (fr) 2002-10-17 2004-04-23 Giat Ind Sa Dispositif de deploiement et d'entrainement de gouvernes de projectile
FR2864613A1 (fr) 2003-12-31 2005-07-01 Giat Ind Sa Dispositif de deploiement et d'entrainement de gouvernes d'un projectile
EP1855076A1 (de) * 2006-05-12 2007-11-14 LFK-Lenkflugkörpersysteme GmbH Wickelflügeln eines Flugkörpers

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2322896A1 (de) * 2009-11-13 2011-05-18 BAE SYSTEMS plc Kragen für Munition
WO2011058359A1 (en) * 2009-11-13 2011-05-19 Bae Systems Plc Guidance device
GB2487334A (en) * 2009-11-13 2012-07-18 Bae Systems Plc Guidance device
US8674277B2 (en) 2009-11-13 2014-03-18 Bae Systems Plc Guidance device
GB2487334B (en) * 2009-11-13 2015-02-11 Bae Systems Plc Guidance device
EP2423637A3 (de) * 2010-08-25 2015-07-08 BAE Systems Rokar International Ltd. System und Verfahren zum Lenken einer Granate während des Fluges
US9945649B2 (en) 2010-08-25 2018-04-17 Bae Systems Rokar International Ltd. System and method for guiding a cannon shell in flight
US11009322B2 (en) 2010-08-25 2021-05-18 Bae Systems Rokar International Ltd. System and method for guiding a cannon shell in flight

Also Published As

Publication number Publication date
ATE469333T1 (de) 2010-06-15
DE602008001317D1 (de) 2010-07-08
ES2346721T3 (es) 2010-10-19
EP1953494B1 (de) 2010-05-26
FR2911954A1 (fr) 2008-08-01
FR2911954B1 (fr) 2009-04-24

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