EP3032212B1 - Systeme de gouvernail - Google Patents

Systeme de gouvernail Download PDF

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Publication number
EP3032212B1
EP3032212B1 EP15003425.4A EP15003425A EP3032212B1 EP 3032212 B1 EP3032212 B1 EP 3032212B1 EP 15003425 A EP15003425 A EP 15003425A EP 3032212 B1 EP3032212 B1 EP 3032212B1
Authority
EP
European Patent Office
Prior art keywords
rudder
leg
housing
foldable
locking device
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15003425.4A
Other languages
German (de)
English (en)
Other versions
EP3032212A1 (fr
Inventor
Jörg Lutzenberger
Bernd Käbitz
Robert Kroyer
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.)
MBDA Deutschland GmbH
Original Assignee
MBDA Deutschland 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
Priority claimed from DE102015004702.7A external-priority patent/DE102015004702A1/de
Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP3032212A1 publication Critical patent/EP3032212A1/fr
Application granted granted Critical
Publication of EP3032212B1 publication Critical patent/EP3032212B1/fr
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
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of 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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • the subject of this invention is the rowing system described below, in particular a self-locking folding powder, which has been realized with the objectives of robustness, reliability and minimization of the production costs. This is achieved by the use of as few components as possible, a functional and production-optimized design of the production parts and the use of standard components.
  • Flip-flop systems are known in the art.
  • rudder systems are according to the preamble of claim 1 of the US 6,092,264 A and the EP 1 249 680 A the latter being considered as the closest prior art.
  • These folding spray systems are commonly used in guided missiles launched from a launch tube. Once the missile has left the launch tube, the folding powder is unfolded to control the missile can. In the folded state, the missile has a nearly cylindrical shape, so that it can be stored in the launch tube.
  • the kinematics of known folding spray systems is very complicated and therefore expensive.
  • known Klapprudersysteme for each missile individually to develop, as they are not adaptable or scalable.
  • a rudder system having a foldable rudder part, a rudder housing and an elastic locking device.
  • the hinged rudder member is rotatably mounted on the rudder housing, wherein the foldable rudder member is movable from a retracted position to a deployed position. The movement between the folded position and the unfolded position takes place relative to the rudder housing.
  • the resilient locking device is held in a biased position by the foldable rudder member when the foldable rudder member is in the retracted position.
  • the elastic locking device can be transferred from the pretensioned position by relaxation into an at least partially relaxed position.
  • the elastic locking device in the at least partially relaxed position blocks a movement of the folding rudder part relative to the rudder housing.
  • the foldable rudder part in the unfolded position is completely surrounded by the rudder housing and the elastic locking device.
  • a first elastic element is provided, which is mounted on an axle.
  • the axle is connected to the rudder housing and stores in particular the folding rudder part.
  • a movement of the folding rudder part relative to the rudder housing takes place by rotation of the folding rudder part about the axis.
  • a spring force of the first elastic element urges the folding rudder part in the unfolded position.
  • the rudder system is seklappbar, so that an external force is required to hold the folding rudder part in the folded position.
  • the first elastic element is particularly advantageously a first leg spring.
  • the elastic locking device comprises a second elastic element, in particular a second leg spring.
  • the second elastic element in particular the second elastic leg spring, is advantageously oriented perpendicular to the first elastic element, in particular to the first leg spring.
  • each leg spring has a characteristic plane which runs parallel to the legs of the leg spring.
  • each leg spring has an axis of rotation which is perpendicular to the characteristic plane and about which the legs of the leg spring are rotatable. If two torsion springs are oriented perpendicular to one another, it is provided in particular that both the characteristic planes and the axes of rotation are oriented perpendicular to one another.
  • the elastic locking device comprises a movable first leg and an at least partially attached to the rudder housing second leg.
  • the first leg is in particular rotatable about the axis of rotation of the leg spring of the elastic locking device.
  • the second leg is held frictionally in particular between two cylinder pins. It is provided that the second leg rests against a wall of the rudder housing, so that the elastic locking device can be supported by the second leg on the rudder housing.
  • the foldable rudder part has a rudder foot mounted on the rudder housing and a rudder blade attached to the rudder foot. It is provided that the rudder rest in the unfolded position of the folding rudder part of the rudder housing and the movable leg, so that a movement of the rudder foot is blocked relative to the rudder housing.
  • the rudder housing itself blocks movement of the rudder foot, which is generated by the elastic spring force of the first elastic member, while the movable leg blocks movement of the rudder foot, which is oriented against the spring force of the first elastic member.
  • the elastic device is mounted on the retaining element via a retaining element. It is provided that the holding element parallel to the Rotary axis of the leg spring of the elastic locking device is oriented.
  • the first leg of the resilient locking device is rotatable about the support member for movement between the biased position and the at least partially relaxed position.
  • the rudder housing has a recess.
  • the recess is in particular a bag.
  • the first leg engages when it is in the at least partially relaxed position. In this way, an additional support of the first leg is provided, so that the first leg can effectively block a movement of the rudder foot of the folding rudder part relative to the rudder housing.
  • one end of the first leg which faces away from the holding element, engages in the recess, so that one end of the first leg is fixed by the holding element to the rudder housing, and the other end through the recess.
  • the recess has a tapering region and an end region.
  • the end region has parallel flanks. It is provided that the tapering serves to allow the first leg can easily engage in the recess. Thus, it is particularly avoided that the first leg engages past the recess and thus could not be transferred into the at least partially relaxed position.
  • the end region serves to guide the first leg into the at least partially relaxed position.
  • the first leg thus engages in the end region of the recess when the first leg is in the at least partially relaxed position.
  • an inner dimension of the end region which is defined in particular by a distance between the parallel flanks of the end region, corresponds to an outer dimension of the first leg.
  • the inner dimension and the outer dimension correspond to one another, if this maximum deviation of 5% exhibit.
  • the rudder foot has a bevel.
  • the chamfer is mounted on the rudder foot such that the first leg is pressed against the chamfer by the relaxation of the resilient locking device when the foldable rudder member is between the folded position and the deployed position.
  • an additional force is applied to the rudder foot and thus to the foldable rudder member, the additional force amplifying deployment of the foldable rudder member, i.e., movement to the deployed position.
  • a quick unfolding of the folding rudder part is ensured.
  • the rudder system advantageously also has an axle receptacle, via which the entire rudder system can be mounted on an actuator axle.
  • the rudder system does not penetrate the shell of the missile, whereby the rudder system is flexible on a variety of missiles or can be adapted to the missile.
  • the rudder foot also advantageously has a groove.
  • the first elastic element is advantageously a second leg spring, so that one leg of the second leg spring engages in the groove of the rudder foot, while the other leg rests against the rudder housing. Since the second leg spring is mounted in particular on the same axis on which the foldable rudder part is mounted, thus a simple and reliable power transmission between the second leg spring and hinged rudder part is possible.
  • the folding powder is characterized by the possibility of scaling and simple adaptation to other missiles, since the rudders are only applied externally to the rudder axis of the actuator system and do not interfere with the shell of the missile.
  • FIGS. 1 to 3 show various views of the rudder system 11 according to an embodiment of the invention.
  • the rudder system 11 is in FIG FIG. 1 and 3 unfolded, in FIG. 2 collapsed.
  • the rudder system 11 has a folding rudder part 18, which is rotatably mounted on a rudder housing 3 via an axle 4.
  • the folding rudder member 18 To the hinged rudder part 18 between the in FIG. 1 and 3 shown unfolded position and in FIG. 2 To move shown folded position, the folding rudder member 18 must be rotated about the axis 4 relative to the rudder housing 3.
  • the hinged rudder part 18 has a rudder blade 5 and a rudder foot 13.
  • the rudder foot is mounted on the axle 4 on the rudder housing 3, while the rudder blade 5 serves as an aerodynamic control surface. So that the movable rudder part 18 can be moved independently from the folded-in position into the unfolded position, the rudder system 11 has a first elastic element 1.
  • the first elastic element 1 is in particular a first leg spring 1.
  • a first leg of the first leg spring 1 is biased inserted into the groove 14 of the rudder foot 13, a second leg is supported on the rudder housing 3 from.
  • the spring body of the first leg spring 1 finds place in a recess of the rudder foot 13 and is centered by the axis 4, which also represents the articulated connection between hinged rudder member 18 and rudder housing 3. This is pressed after inserting the first leg spring 1 in the rudder housing 3.
  • the foldable rudder member 18 is thus independently in the unfolded position can be transferred.
  • the foldable rudder member 18 must be held by an external force to hold the folding rudder member 18 in the folded position.
  • a second leg spring 2 is used, of which a leg itself acts as a bolt.
  • the second leg spring 2 comprises a first leg 8 and a second leg 9.
  • the first leg 8 is movable and serves in particular as a bolt for reaching said lock.
  • the second leg 9 is preferably attached to a wall of the rudder housing 3. Furthermore, the second leg spring 2 has a spring body.
  • the spring body of the second leg spring 2 is characterized by a holding element 7, in particular by a pressed-in pin with collar (see. Fig. 5 ), or a screw, mounted on the rudder housing 3. On the spring body of the second leg spring 2 no force may be applied, since the second leg spring 2 must remain free.
  • the second leg 9 of the second leg spring 2 is supported on the housing wall of the rudder housing 3 and is held between two cylinder pins 6 pressed into the rudder housing 3, so that its position is fixed under prestressing.
  • the first leg 8 of the second leg spring 2 is supported in the folded state of the foldable rudder part 18 on the rudder foot 13.
  • the rudder foot 13 slides on the first leg 8 until it has sufficient space to reduce the pretension by rotation. In this way, the relaxation of the elastic locking device, whereby a rotation 100 of the first leg 8 is generated.
  • the case delivered torque additionally supports the unfolding of the hinged rudder part 18 when the first leg 8 under the rudder 13, in particular on a chamfer 21 of the rudder foot 13 engages.
  • a recess or pocket 10 which tapers in a tapering region 19 upwards and finally in a vertical region without edge slope, the end portion 20 passes. This serves to "catch" the first leg 8 of the second leg spring 2 and to guide it into the at least partially relaxed position.
  • first leg 8 In the vertical pitch-free region of the pocket flanks, ie in the end region 20, there is a geometric blocking of the first leg 8, ie, a force applied by the folding rudder member 18 on the acting as a cross bar first leg 8 force loads the first leg 8 at the two outer edges of the leg leg of the first leg 8 only to shear. Dodge of acting as a locking first leg 8 is excluded.
  • a second leg spring 2 is such that it maintains a balance of preload in the end position defined by the bag 10, i.e., in the partially relaxed position, to always ensure compliance with the situation.
  • the rudder housing 3 has an axle receptacle 12.
  • the axle receptacle 12 is used for connecting the rudder system 11 to an actuator, so that the rudder system 11 is movable by the actuator. It can be seen that the rudder system 11 can be attached to the actuator in a very simple manner. In particular, the rudder system 11 does not have to penetrate the outer shell of a missile.
  • FIG. 4 shows the axis 4 of the rudder system 11.
  • the axis 4 has a first region 22 and a second region 23. It is provided that the first portion 22 for supporting the first leg spring 1, that is, for supporting the first elastic member 1, serves, while the second portion 23 for supporting the rudder foot 13 of the folding rudder portion 18 is used.
  • FIG. 5 schematically shows the holding device 7 for connecting the second leg spring 2, that is, which is selected on the actuator system.
  • the axle 12 serves to tie the rudder housing 3 and thus the entire Rudder system 11 to an actuator.
  • the rudder housing 3 and thus the rudder system 11 is movable, whereby a flow of the rudder blade 5 is variable. This leads to a movement change of the missile.
  • elastic locking device 2 to the rudder housing 3.
  • the retaining element 7 is a retaining pin, wherein the retaining element can also be a screw.
  • FIG. 6 schematically shows the hinged rudder part 18.
  • the foldable rudder member 18 has, in addition to the rudder 13 a rudder blade 5, wherein the rudder blade 5 serves as an aerodynamic control surface.
  • a groove 14 is present, which serves to receive a leg of the first leg spring 1, that is, for receiving the first elastic element 1.
  • FIG. 7 shows a schematic view of the rudder housing.
  • FIG. 8 shows a sectional view through the rudder housing 3.
  • the rudder housing 3 has a recess or pocket 10, which has a tapering portion 19 and an end portion 20. The function of the tapering portion 19 and the end portion 20 has previously been described in detail.
  • the rudder housing 3 has a retaining element receptacle 17.
  • the holding element receptacle 17 can be a thread if the holding element 7 is a screw or can be a bore if the holding element 7 is a holding pin.
  • the rudder housing 3 also has two pin receivers 16, which are in particular holes.
  • the cylindrical pins 6 can be pressed into the pin receptacle 16.
  • the rudder housing 3 has an axle bearing receptacle 15, on which the axle 4 can be coupled to the rudder housing 3.
  • the axle 4 can be pressed into the axle bearing receptacle 15 of the rudder housing 3, so that the axle 4 is rotationally connected to the rudder housing 3.
  • the rudder housing 3 has an axle receptacle 12.
  • the axle receptacle 12 is in this embodiment, in particular a threaded hole, so that an actuator axis in the axle 12 is screwed.
  • the execution of the axle can also be performed as a simple bore when an adhesive connection for connecting the rudder

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Pivots And Pivotal Connections (AREA)
  • Toys (AREA)

Claims (9)

  1. Système de gouvernail (11) comprenant :
    - une partie de gouvernail (18) rabattable,
    - un boîtier de gouvernail (3) sur lequel la partie de gouvernail (18) rabattable est montée de manière rotative,
    - un premier élément élastique (1) qui est monté sur un axe (4) fixé sur le boîtier de gouvernail (3), une force élastique du premier élément élastique (1) forçant la partie de gouvernail (18) rabattable en la position dépliée,
    - un dispositif de verrouillage (2) élastique,
    - dans la partie de gouvernail (18) rabattable est déplaçable de manière relative par rapport au boîtier de gouvernail (3), d'une position rabattue en une position dépliée,
    - dans lequel le dispositif de verrouillage (2) élastique est maintenu par la partie de gouvernail (18) rabattable en une position précontrainte lorsque la partie de gouvernail (18) rabattable se trouve dans la position rabattue,
    - dans lequel le dispositif de verrouillage (2) élastique peut, par détente, passer de la position précontrainte en une position au moins en partie détendue lorsque la partie de gouvernail (18) rabattable se trouve en position dépliée, et
    - dans lequel le dispositif de verrouillage (2) élastique, en position au moins en partie détendue, bloque un mouvement de la partie de gouvernail (18) rabattable par rapport au boîtier de gouvernail (3), caractérisé en ce que
    - le dispositif de verrouillage (2) élastique comprend un deuxième élément élastique réalisé en tant qu'un ressort à branches, dans lequel le dispositif de verrouillage (2) élastique présente une première branche (8) déplaçable et une deuxième branche (9) fixée au moins en partie sur le boîtier de gouvernail (3).
  2. Système de gouvernail (11) selon la revendication 1, caractérisé en ce que la partie de gouvernail (18) rabattable est montée sur l'axe (4).
  3. Système de gouvernail (11) selon l'une quelconque des revendications précédentes, caractérisé en ce que le premier élément élastique (1) comprend un premier ressort à branches.
  4. Système de gouvernail (11) selon l'une quelconque des revendications précédentes, caractérisé en ce que la partie de gouvernail (18) rabattable présente un pied de gouvernail (13) monté sur le boîtier de gouvernail (3) et un safran (5) fixé sur le pied de gouvernail (13), dans lequel le pied de gouvernail (13), en position dépliée de la partie de gouvernail (13) rabattable, s'appuie contre le boîtier de gouvernail (3) et à la première branche (8) de manière à ce qu'un mouvement du pied de gouvernail (13) soit bloqué par rapport au boîtier de gouvernail (3).
  5. Système de gouvernail (11) selon l'une quelconque des revendications précédentes, caractérisé en ce que le dispositif de verrouillage (2) élastique est monté sur le boîtier de gouvernail (3) par l'intermédiaire d'un élément de maintien (7), dans lequel la première branche (8) est rotative autour de l'élément de maintien (7) pour le déplacement entre la position précontrainte et la position au moins en partie détendue.
  6. Système de gouvernail (11) selon l'une quelconque des revendications précédentes, caractérisé en ce que le boîtier de gouvernail (3) présente un évidement (10) dans lequel a prise la première branche (8) en position au moins en partie détendue.
  7. Système de gouvernail (11) selon la revendication 6, caractérisé en ce que l'évidement (10) présente une partie rétrécie (19) et une partie terminale (20), la partie terminale comprenant des flancs parallèles.
  8. Système de gouvernail (11) selon la revendication 7, caractérisé en ce que la première branche a prise dans la partie terminale (20) en position au moins en partie détendue, dans lequel une dimension intérieure de la partie terminale (20), notamment un écart entre les flancs parallèles, correspond à une dimension extérieure de la première branche (8).
  9. Système de gouvernail (11) selon l'une quelconque des revendications précédentes, caractérisé en ce que le pied de gouvernail (13) présente un chanfrein (21), dans lequel la première branche (8), en raison de la détente du dispositif de verrouillage (2) élastique, est pressée sur le chanfrein (21) lorsque la partie de gouvernail (18) rabattable se trouve entre la position rabattue et la position dépliée.
EP15003425.4A 2014-12-11 2015-12-02 Systeme de gouvernail Active EP3032212B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014018259 2014-12-11
DE102015004702.7A DE102015004702A1 (de) 2014-12-11 2015-04-09 Rudersystem

Publications (2)

Publication Number Publication Date
EP3032212A1 EP3032212A1 (fr) 2016-06-15
EP3032212B1 true EP3032212B1 (fr) 2017-07-26

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ID=54782394

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15003425.4A Active EP3032212B1 (fr) 2014-12-11 2015-12-02 Systeme de gouvernail

Country Status (1)

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EP (1) EP3032212B1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108180791A (zh) * 2018-01-09 2018-06-19 北京航空航天大学 分体式舵面舵轴结构和导弹
CN108408027A (zh) * 2018-03-21 2018-08-17 北京瑞极通达科技有限公司 一种舵面折叠旋转机构
CN110260727A (zh) * 2019-07-05 2019-09-20 贵州航天控制技术有限公司 一种小型舵面折叠机构组件

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2712679B1 (fr) * 1993-11-16 1996-02-09 Luchaire Defense Sa Dispositif de déploiement pour une ailette de stabilisation de projectile de type roquette.
KR0176320B1 (ko) * 1995-12-09 1999-04-01 배문한 유도탄 날개 전개 및 고정 장치
US6092264A (en) 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
DE10118216A1 (de) * 2001-04-12 2002-10-17 Diehl Munitionssysteme Gmbh Ruderblatt-Lagereinrichtung für ein Geschoß
US8278612B2 (en) * 2010-07-27 2012-10-02 Raytheon Company Aerodynamic fin lock for adjustable and deployable fin

Non-Patent Citations (1)

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Title
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