EP0499907B1 - Projectile comportant des ailettes déployables - Google Patents

Projectile comportant des ailettes déployables Download PDF

Info

Publication number
EP0499907B1
EP0499907B1 EP92102112A EP92102112A EP0499907B1 EP 0499907 B1 EP0499907 B1 EP 0499907B1 EP 92102112 A EP92102112 A EP 92102112A EP 92102112 A EP92102112 A EP 92102112A EP 0499907 B1 EP0499907 B1 EP 0499907B1
Authority
EP
European Patent Office
Prior art keywords
projectile
rudder plates
rudder
projectile according
segments
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP92102112A
Other languages
German (de)
English (en)
Other versions
EP0499907A3 (en
EP0499907A2 (fr
Inventor
Rüdiger Dipl.-Ing.(FH) Hornfeck
Klaus Dipl.-Ing.(FH) Bär
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.)
Diehl Stiftung and Co KG
Original Assignee
Diehl GmbH and Co
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 Diehl GmbH and Co filed Critical Diehl GmbH and Co
Publication of EP0499907A2 publication Critical patent/EP0499907A2/fr
Publication of EP0499907A3 publication Critical patent/EP0499907A3/de
Application granted granted Critical
Publication of EP0499907B1 publication Critical patent/EP0499907B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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

Definitions

  • the invention relates to a projectile with a fold-out tail unit according to the preamble of claim 1.
  • the generic device is known from DE-C-37 21 512. It is a missile launched from a launch device in which the rudder blades are unfolded from longitudinal slots in its structure.
  • the arrangement of the folded rudder blades within the structure guarantees a certain level of protection for the rudder blades.
  • Another case is when the projectile is to be fired from a cartridge with a propellant charge and the rudder blades are arranged at the end of the projectile, in particular behind the sealing ring projectile / cartridge. Since the rudder blades are more or less exposed here, they are fully exposed to the effects of the high-energy propellant gases during the launch. This can damage the edges and surfaces of the rudder blades, which are aerodynamically optimized, which could then lead to an unstable flight of the projectile when unfolded.
  • the invention is therefore based on the object of providing a device of the generic type in which the aerodynamic stabilizing surfaces (rudder blades) are protected from internal ballistic stress, such as powder gas pressure, temperature, etc., during the passage of the barrel.
  • the rudder blades folded in during storage and transport and in particular during the passage of the weapon barrel are fully protected.
  • the rudder protection is thrown out automatically by the twist of the projectile and the rudder blades can be unfolded.
  • FR-A-2 339 834 a large sub-caliber with stabilizing wings is described, the stabilizing wings being enveloped by a hollow body. However, the hollow body is stripped by the air resistance. No swirl forces are required for stripping.
  • the protective device is in operative connection with the securing device of the rudder blades, so that it is ensured that the release (unlocking) of the rudder blades does not take place too early (for example within the weapon barrel), since this leads to mechanical deformations of the rudder blades ( inside the protective device), which could lead to the rudder blades unfolding unevenly. It is therefore provided that the safety device only releases the rudder blades after the protective device has been thrown away.
  • the securing device as the engagement element, has a retaining star biased via a torsion element, the biased position of which is maintained by the engagement of lugs attached to the protective device, the holder being designed such that after the protective device is flung away the pretensioning of the retaining star is released, causing the same to twist out of engagement with the rudder blades.
  • rudder protection including the rudder retaining and unlocking device.
  • the timed functions protection of the rudder blades, removal of the rudder protection as well as opening (setting up) the rudder blades are achieved purely mechanically (without additional auxiliary devices), in comparison to the prior art, instead of a sliding unlocking, a simple twist unlocking is used which does not require any additional space.
  • the protective device is advantageously formed from a plurality of segments which enclose the folded rudder blades.
  • the spaces between the segments are additionally covered so that the rudder blades are protected from all sides against the internal ballistic loads. These covers also hold the segments together.
  • the rudder blade spaces between the individual segments are formed in that on one end face of the segments (the end face facing away from the axis of rotation of the rudder blades) they each have an edge perpendicular to each longitudinal wall. These edges face each other and thus enclose a recess.
  • the other end of the segments is each provided with a circular base plate.
  • the individual segments can be held together by a central disk in the area of their edges.
  • the holding elements are attached to the protective device in a simple manner either in a form-fitting manner or by means of an adhesive connection.
  • the rudder guard is attached to the projectile floor in a non-rotatable manner in a further embodiment of the invention. This is achieved by attaching a protruding attachment to the base plates of the respective segments, each of which again fits into a corresponding groove machined on the projectile base intervenes. When the rudder protection segments are thrown away, they are partially guided radially in this groove.
  • a slotted cylinder element which is integrated with the projectile base and is attached centrally, is provided.
  • the engaging element (retaining star) of the securing device for locking the folded rudder blades is attached at the same time.
  • the retaining star can engage either in the front groove or in the longitudinal groove of the rudder blades.
  • a torsion bar is used in a simple manner as a torsion element.
  • the rudder blades are brought into the radially spread position by swirl forces, it is advantageous if the rudder blades have their folding axes in the front part (seen in the direction of flight).
  • a particularly effective development of the invention is given in that a spring-loaded cam is provided on the projectile bottom.
  • the preload of the cam disc is released, the cam disc rotating in such a way that the rudder blades are prevented from folding back.
  • the spring force and the slope of the cam can also be designed so that this mechanism supports the installation process of the rudder blades.
  • a projectile 1 is arranged in a cartridge 2.
  • the projectile 1 has aerodynamic stabilizing surfaces (rudder blades 3) at the end of the projectile, which are folded during storage and transport as well as during firing, ie during the barrel of the gun barrel.
  • the rudder blade bracket 3 in this collapsed position serves a securing device 4 which engages in all rudder blades 3 at the same time.
  • a protective device 5 In order to protect the rudder blades 3 from the internal ballistic load (powder gas pressure, temperature etc.) during projectile passage through the weapon barrel, these are surrounded by a protective device 5.
  • the rudder blades 3 are articulated on the front of the projectile (as seen in the direction of flight) (see folding axles 6).
  • the protective device 5 consists of several segments 8 (in the exemplary embodiment four approximately rectangular in cross section), which are supported on the cylinder element 7 in the installed state and - seen in the overall cross section - have the shape of a cross with four perpendicular to one another Form cavities 9. In the folded state, the rudder blades 3 have completely disappeared in the cavities and are therefore protected.
  • the securing device 4 has, as an engagement element, a retaining star 10 attached to the cylinder element 7, which is prestressed via a torsion bar 11.
  • the prestressed position is maintained by the engagement of a nose 12 attached to the individual protective segments 8 (in the area of the provided holding star 10).
  • the holding star 10 engages in the folded rudder blades 3 (see FIG. 1).
  • This can be done in two ways: on the one hand, the engagement groove on the end faces (groove 13a, see FIG. 4) and on the other hand on the long sides (groove 13b, see FIG. 5) of the rudder blades 3.
  • the retaining star 10 has forward-facing (in the direction of flight) rectangular engagement webs.
  • the retaining star 10 in the second case has radially outwardly directed trapezoidal engagement webs.
  • the engagement grooves 13a and 13b are of course also formed in accordance with the shape of the engagement webs.
  • the protective device 5 After the projectile 1 has emerged from the launch tube, the protective device 5 is thrown away due to the swirl. Since the lugs 12 on the protective segments 8 are no longer in engagement with the retaining star 10, the pretensioning of the retaining star 10 is released, as a result of which the same is disengaged twisted with the rudder blades 3. After this unlocking, the rudder blades 3 (also due to the folding axes 6 in the front part) are transferred into the radially extended functional position (also by swirl forces) (cf. FIGS. 4 and 5).
  • a cam disk 14 which is under spring tension is attached to the projectile base. This is under tension when the rudder blades 3 are folded. When the rudder blades 3 are folded out, the pretension is released and the cam disk 14 is rotated such that the rudder blades 3 can no longer be folded in. It is of course also conceivable to design the spring force and the slope of the cam disc in such a way that the rudder blades 3 are also supported during the turning process.
  • FIG. 7 shows an enlarged representation of the entire protective device 5. From this it can be seen that the end faces of the protective segments 8 facing away from the projectile floor have an edge 8b perpendicular to each longitudinal wall. The edges 8b of the individual protective segments 8 are directed towards one another and thus close a recess (a cavity 9). As already mentioned, this serves to receive the folded rudder blades 3. So that the rudder blades 3 are now protected from all sides against the ballistic stresses, the cavities 9 are closed with covers 15.
  • the other end faces of the protective segments 8, on the other hand, are each provided with a circular base plate 8a, which of course runs in the opposite direction to the edges 8b.
  • the protective segments 8 are held together (in the area of their edges 8b) by a central disk 16.
  • the covers 15 also serve as holding elements. Both holding elements 15 and 16 are connected to the protective device 5 in a form-fitting manner or by an adhesive connection.
  • the protective segments 8 are secured against rotation on the projectile floor. This is achieved in each case by an attachment 17 on the respective base plates 8a of the rudder protection segments 8 (cf. FIGS. 8 and 9).
  • the lugs 17 each engage in a corresponding counterpart 18 (see FIG. 6) on the projectile bottom.
  • the rudder protection segments 8 are thrown away, they are partially guided radially in the grooves 18.

Claims (12)

  1. Projectile (1) avec empennage déployable, dont les ailettes de gouverne (3) sont maintenues à l'état rabattu par un dispositif de sécurité (4) s'engageant dans les ailettes de gouverne et le déploiement par rabattement des ailettes de gouverne, pour passer en position de fonctionnement, s'effectuant après sortie du projectile hors du tube d'éjection, caractérisé en ce que les ailettes de gouverne (3) sont recouvertes par un dispositif de protection (5), qui subit une éjection centrifuge du fait de la rotation, après que le projectile (1) ait quitté le tube.
  2. Projectile selon la revendication 1, caractérisé en ce que le dispositif de sécurité (4) présente, à titre d'élément d'engagement, une étoile de maintien (10), précontrainte par un élément de torsion (11) et dont la position précontrainte est conservée par un engagement d'ergots (12) montés sur le dispositif de protection (5), la fixation étant conçue de manière que, après éjection du dispositif de protection (5), la précontrainte de l'étoile de maintien (10) soit relâchée et que, de ce fait, celle-ci tourne hors de prise sur les ailettes de gouverne (3).
  3. Projectile selon la revendication 1, caractérisé en ce que le dispositif de protection (5) est constitué de segments (8) reliés ensemble par des recouvrements (15).
  4. Projectile selon la revendication 3, caractérisé en ce que les segments (8) présentent, sur une première face frontale, une plaque de fond (8a) en forme de secteur de cercle et, sur l'autre face frontale, une bordure (8b) perpendiculaire par rapport à sa paroi longitudinale, les bordures (8b) dirigées les unes vers les autres enclosant chacune un évidement (9), dans lequel les différentes ailettes de gouverne (3) sont logées - à l'état rabattu.
  5. Projectile selon la revendication 4, caractérisé en ce que les segments (8) sont maintenus dans la zone des bornes (8b) par un disque central (16).
  6. Projectile selon la revendication 4, caractérisé en ce que, sur chacune des plaques de fond (a) des segments (8) respectifs, est monté un appendice (17) en saillie, qui s'engage à son tour chaque fois dans une rainure (18) correspondante, usinée sur le fond de projectile.
  7. Projectile selon la revendication 3 et/ou 5, caractérisé en ce que les recouvrements (15) et/ou le disque (16) sont fixés sur le dispositif de protection (5), soit avec ajustement de forme soit au moyen d'une liaison par collage.
  8. Projectile selon la revendication 2, caractérisé en ce que sur le fond de projectile est prévu au centre un élément cylindrique (7) fendu, pour recevoir les ailettes de gouverne (3) rabattues, élément cylindrique sur lequel est montée l'étoile de maintien (10) s'engageant dans les ailettes de gouverne (3), par l'intermédiaire d'une barre de torsion (11) servant d'élément de torsion.
  9. Projectile selon la revendication 8, caractérisé en ce que l'étoile de maintien (10) s'engage soit dans des rainures de coté frontal (13a), soit dans des rainures de coté longitudinal (13b) des ailettes de gouverne (3).
  10. Projectile selon la revendication 1, caractérisé en ce que les ailettes de gouverne (3) sont maintenues sur le fond de projectile avec des axes de rabattement (6) situés dans la partie avant - lorsque l'on observe dans la direction du vol - et en ce qu'elles passent de la position libérée à la position radialement écartée sur l'effet des forces de rotation.
  11. Projectile selon la revendication 10, caractérisé en ce que, lors du processus de déploiement par rabattement, un disque de came (14), qui empêche toute rétraction par rabattement des ailettes de gouverne (3) et est monté sur le fond de projectile et placé sous contrainte d'un ressort entre en rotation.
  12. Projectile selon la revendication 11, caractérisé en ce que la force élastique et le pas du disque de came (14) sont tel qu'il apporte une assistance au déploiement des ailettes de gouverne (3).
EP92102112A 1991-02-20 1992-02-08 Projectile comportant des ailettes déployables Expired - Lifetime EP0499907B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4105142A DE4105142A1 (de) 1991-02-20 1991-02-20 Projektil mit ausklappbarem leitwerk
DE4105142 1991-02-20

Publications (3)

Publication Number Publication Date
EP0499907A2 EP0499907A2 (fr) 1992-08-26
EP0499907A3 EP0499907A3 (en) 1993-03-31
EP0499907B1 true EP0499907B1 (fr) 1996-01-31

Family

ID=6425398

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92102112A Expired - Lifetime EP0499907B1 (fr) 1991-02-20 1992-02-08 Projectile comportant des ailettes déployables

Country Status (2)

Country Link
EP (1) EP0499907B1 (fr)
DE (2) DE4105142A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7089866B2 (en) 2001-04-12 2006-08-15 Olympic Technologies Limited Small arms projectile

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2797946B1 (fr) 1999-08-31 2002-10-04 Aerospatiale Matra Missiles Dispositif de montage d'un appendice rigide sur un engin apte a etre lance depuis le tube, et engin correspondant
DE102007002948B4 (de) 2007-01-19 2009-04-02 Diehl Bgt Defence Gmbh & Co. Kg Vorrichtung zur Tragflächenentfaltung
CN107933887B (zh) * 2017-10-23 2023-10-20 四川大学 一种舵片展开机构
FR3094475B1 (fr) * 2019-03-27 2022-08-12 Nexter Munitions Capotage et projectile comportant un tel capotage
CN111220032B (zh) * 2019-11-18 2022-05-27 中国空空导弹研究院 一种小型折叠舵面的四通道联动解锁机构
CN114485287B (zh) * 2021-12-30 2023-11-07 北京动力机械研究所 一种折叠舵自锁承力结构
CN114963884A (zh) * 2022-03-01 2022-08-30 宁波天擎航天科技有限公司 一种靶弹舵片气动可控展开机构及安装有该机构的靶弹
CN115014132A (zh) * 2022-03-01 2022-09-06 宁波天擎航天科技有限公司 一种靶弹舵片可控展开机构及安装有该机构的靶弹

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE565999A (fr) * 1953-02-06
FR1191519A (fr) * 1958-02-13 1959-10-20 Hotchkiss Brandt Empennage déployant pour projectile d'artillerie
FR1405380A (fr) * 1964-05-28 1965-07-09 Soc Tech De Rech Ind Perfectionnements aux empennages déployants pour projectiles
FR1490554A (fr) * 1966-05-03 1967-08-04 Ruggieri Ets Perfectionnement aux empennages déployants de roquettes
DE2603756A1 (de) * 1976-01-31 1977-08-04 Rheinmetall Gmbh Unterkalibergeschoss mit stabilisierungsfluegeln
DE2623582C2 (de) * 1976-05-26 1985-06-13 Rheinmetall GmbH, 4000 Düsseldorf Raketengeschoß mit Ausklappleitwerk und Treibspiegel
IL66624A (en) * 1982-02-10 1986-04-29 Gen Dynamics Corp Wing housing and cover release assembly for self-erecting wing of a structure such as missile
DE3432614A1 (de) * 1984-09-05 1986-03-13 Rheinmetall GmbH, 4000 Düsseldorf Flugkoerper
US4691880A (en) * 1985-11-14 1987-09-08 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
DE3608109A1 (de) * 1986-03-12 1987-09-17 Diehl Gmbh & Co Bremseinrichtung fuer ein drallstabilisiertes projektil
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7089866B2 (en) 2001-04-12 2006-08-15 Olympic Technologies Limited Small arms projectile

Also Published As

Publication number Publication date
EP0499907A3 (en) 1993-03-31
DE59205195D1 (de) 1996-03-14
EP0499907A2 (fr) 1992-08-26
DE4105142A1 (de) 1992-08-27

Similar Documents

Publication Publication Date Title
DE2342783C2 (de) Mit einem Leitwerk versehenes Geschoß
EP0114602B1 (fr) Missile
EP0499907B1 (fr) Projectile comportant des ailettes déployables
DE69909719T2 (de) Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses
DE1168804B (de) Flugkoerperhinterteil mit mehreren Stabilisierungsflossen
EP1628112A1 (fr) Disposition d'ailettes
DE3615264C2 (fr)
DE60005239T2 (de) Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses
DE10205043C5 (de) Aus einem Rohr zu verschließender Flugkörper mit überkalibrigem Leitwerk
EP0185852A1 (fr) Missile sans pilote
DE3615263A1 (de) Niederhaltevorrichtung an raumflugkoerpern
DE1147514B (de) Leitwerkflosse fuer Geschosse und Raketen
DE2009988A1 (de) Zünder mit Zeitverzögerung
DE1703501A1 (de) Aufschlagzuender mit kippbarem Rotor fuer Drallgeschosse
DE3116175A1 (de) Nichttoedliches wuchtgeschoss
EP0411245B1 (fr) Dispositif d'allumage d'une sous-munition
DE2649643A1 (de) Raketengetriebener flugkoerper mit entfaltbaren stabilisierungsflaechen
DE2400947C3 (de) Sicherungs- und Entsicherungsvorrichtung für GeschoDzünder
EP0184617B1 (fr) Dispositif d'arrêt pour empennage déployable
DE713285C (de) Mit Aufschlagzuender versehene Bombe zum Abwurf im Tiefangriff aus einem Flugzeug
DE2139071C3 (de) Geschoß mit Bremsflügeln
DE1950638C3 (de) Flugkörper mit entfaltbaren Stabilisierungsflächen
DE102021005973A1 (de) Geschoss mit federlos ausschwenkbaren Finnen
EP0157112A1 (fr) Projectile avec ailettes de stabilisation
DE2637461C2 (de) Leitwerk für einen Flugkörper

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE GB IT NL

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): DE GB IT NL

17P Request for examination filed

Effective date: 19930319

17Q First examination report despatched

Effective date: 19940719

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB IT NL

REF Corresponds to:

Ref document number: 59205195

Country of ref document: DE

Date of ref document: 19960314

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19960227

ITF It: translation for a ep patent filed

Owner name: STUDIO JAUMANN

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
NLT1 Nl: modifications of names registered in virtue of documents presented to the patent office pursuant to art. 16 a, paragraph 1

Owner name: DIEHL STIFTUNG & CO.

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20040205

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 20040226

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20040428

Year of fee payment: 13

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050208

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050208

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050901

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050901

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20050206

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 20050901