EP1154223B1 - Drallstabilisiertes Projektil mit Bremseinrichtung - Google Patents
Drallstabilisiertes Projektil mit Bremseinrichtung Download PDFInfo
- Publication number
- EP1154223B1 EP1154223B1 EP01111503A EP01111503A EP1154223B1 EP 1154223 B1 EP1154223 B1 EP 1154223B1 EP 01111503 A EP01111503 A EP 01111503A EP 01111503 A EP01111503 A EP 01111503A EP 1154223 B1 EP1154223 B1 EP 1154223B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- projectile
- sectors
- respect
- operating position
- longitudinal axis
- 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
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
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
- F42B10/50—Brake flaps, e.g. inflatable
Definitions
- the invention relates to a spin stabilized projectile according to the preamble of the claim 1.
- the mounting plane is the parting plane between the mouth of the projectile body and the screwed into this mouth Detonators. So that the entire conical fuze body protrudes the plane of action of the shell segments forward, the shell segments So lie in the rear transverse plane of the there in the projectile body screwed detonator. This results in the smallest possible Ratio of outer diameter to inner diameter of issued Sheath segments and therefore only a moderate braking effect of exhibited shell segments.
- the desired braking effect is still further reduced by the fact that the conical fuze body long through the Level of the exposed shell segments protrudes forward through.
- the projectile according to US Pat. No. 5,762,291 A is not a generic one spin-stabilized projectile, but a non-generic Tailfin stabilized projectile. This is again in the assembly level between detonator and projectile body equipped with braking surfaces, which folded out by means of torsion spring in its operative position and against a backward stop of the flow to be counteracted.
- braking device In the braking device according to WO 98/01719 A1 is provided in the parting plane between projectile body and projectile-tip semicircular plates axially overlapping each other, azimuthally around the projectile longitudinal axis offset from each other. You can radially with respect to this longitudinal axis from its position of movement within the contour of the projectile in its axisymmetric operative position be pushed out, then due to increase in aerodynamic drag to shorten the ballistic trajectory.
- the present invention is the technical problem underlying, a projectile generic type with a simply activatable, uncontrolled (thus having two-point behavior) and yet very effective, functionally reliable equip aerodynamic braking device.
- this object is the characterizing part of the main claim essentially solved in that as an aerodynamic braking device approximately in the middle region the projectile tip a from the position of transfer, contrary to the flow, in a geometrically defined operative position swing-out annular sector-shaped Valve system is provided, which there in a circumferential groove on the wall the igniter housing is articulated.
- swing-out annular sector-shaped Valve system is provided, which there in a circumferential groove on the wall the igniter housing is articulated.
- the detonator is the complete tip for designed a disassembly, so easily replaceable on the body of the projectile supported.
- the conventional, imported ammunition even later be equipped with this braking device for trajectory control by simply the conventional projectile tip replaced with another with the brake elements becomes.
- flap-shaped brake elements When folded into the housing movement position wear the flap-shaped brake elements hardly radially on. They must therefore not be so wide that they e.g. At her Projection laterally over the outer surface of the igniter tip. That's why comparatively narrow flaps circumferentially offset from each other to unbalanced hinged mounted bolt-shaped pivot shafts.
- two each other adjacent flaps can be arranged spring supports over the entire circumference the top by mutual support a uniform running up to promote all valves.
- the braking effect can still be increased by the spaces between them be bridged between the disc sectors by flexible elements, such as through textile cutouts that arise when placing the flaps between the sectors span.
- the spanned by the spokes textile ring can then still by an unrequited circumferential edge to be enlarged, to the braking attack surface for the flow to optimize.
- a spin stabilized artillery projectile 11 consists essentially of a stretched hollow cylindrical body 12, in which a removable igniter 13 engages frontally. Of the Igniter 13 is thus part of the tip 14 of the projectile 11, whose contour is substantially is determined by their ballistic hood 15.
- the igniter 13 is detachably connected to the body 12 via a coaxial screw 16. He then protrudes through the dividing plane 17 between the tip 14 and body 12 of the Projectile 11 at least with a booster or transformer charge 18th together with securing device 19 into the front region of the body 12. Before that lies at about the division plane 17, e.g. satellite navigation based navigation unit 20 behind a battery 21 in the base of the projectile tip 14. Between this and the transmitter 22 in the front region of the igniter 13 is an ignition electronics 23rd arranged approximately in the axial center plane.
- each of the flap-shaped sectors 24 is for a tangentially oriented in the jacket area bolt 25 as a short bearing and Assigned pivot shaft.
- the bolts 25 lie in radial cuts 26, which are approximately in the central transverse plane of the tip 14 in the circumferential direction in the igniter housing 27 introduced are.
- the sequence of bolts 25 does not lie on a projectile axis 28 kozentrischen Circle, but radially asymmetric, namely with one end inside and radially offset with the other end to the outside of this circle, so that the Bolt 25 on either side in the circumferential direction is mounted radially in front of or behind it are.
- This pivoting from the direction of the secants in the mentioned imaginary Circle and thus with respect to the axis 28 unbalanced orientation of the bolt 25 makes it possible to perform their mutual bearings for all bolts 25 identical and thereby a symmetrical installation behavior of the individual in the circumferential direction each other to promote neighboring sectors 24.
- the relatively narrow sectors 24 are profiled curved around their longitudinal axes, in order to folded or moved state according to FIG. 1 / FIG. 2 the contours on the one hand inside of the housing 27 and on the other hand outside the rearward continuation of the here settled Ballistic hood 15 as well as possible.
- this transfer state can on the embraced brake flaps (ring sectors 24) one (in Fig. 2 dashed lines taken into account) retaining sleeve 29 may be turned up to be in the backward continuation the shortened hood 15 whose lateral surface contour to define, so the aerodynamic ensure smooth geometry and over the lateral surface of conventional Projectile tip 14 not to change.
- the brake device will remove this cuff 29 e.g.
- this gaping cutouts 32 (Fig. 3) can be between each two adjacent sectors 24 a flexible bridging 33 may be provided in the course of setting up the sectors 24th is spanned, as shown in Fig. 3 left considered.
- This bridging 33 of the sectored Brake ring can be made of textile fabric, which in the folded Condition of the sectors 24 is folded radially under this.
- the sectors 24 can then also be thinned to narrow radial spokes whose suspension on short Bolt 25 structurally less problematic than the hinged suspension of the wider sectors 24 is and in the issued state umbrella-like structurally defined stiffening then provide a total of textile annular disk-shaped braking device.
- the individual sectors 24 are at their radial extending longitudinal edges with welded or riveted triangular Bounded spring plates 34 equipped, preferably in the warped transport state the braking device under the sleeve 29 alternately over and under each other to come to rest. This is promoted when the spring plates 34 of a sector 24 in mutually offset planes connect to these, as shown in Fig. 5 can be seen.
- These Arrangement also promotes a rapidly revolving circulating unfolding of the sectors 24 to their functional positions, in which the adjacent, now relaxed in levels Spring plates 34 just overlap each other to the closed ring.
- a spin stabilized artillery projectile 11 can thus be easily with an axisymmetric aerodynamic braking device for shortening the ballistic trajectory retrofit, if equipped with the igniter 13, from the projectile body 12 easily removable tip 14 hinged at about half height with centrifugal force hinged out Sectors 24, which in their position in the conical Nestle shape of the lateral surface and in operative position to a gaping or closed issued radial ring are unfolded.
Description
- Fig. 1
- einen Artillerie-Zünder mit inaktiver Bremseinrichtung in Ansicht,
- Fig. 2
- den Zünder gemäß Fig. 1 in abgebrochener Achsial-Längsschnittdarstellung,
- Fig. 3
- den Zünder gemäß Fig. 1 bei aktivierter Bremseinrichtung in Ansicht,
- Fig. 4
- den Zünder gemäß Fig. 3 in abgebrochener Achsial-Längsschnittdarstellung und
- Fig. 5
- einen Zünder, dessen radial ausgestellte Bremseinrichtung eine in Anströmrichtung geschlossene metallische Ringscheibenstruktur aufweist.
Claims (9)
- Drallstabilisiertes Projektil (11) mit einer längs seiner Flugbahn aus einer Verbringungsstellung in die axialsymmetrische Wirkstellung radial aufstellbaren aerodynamischen Bremseinrichtung im Projektil-Frontbereich, in dem klappenförmige Ringscheiben-Sektoren (24) um Lagerstellen (Bolzen 25) aus einer Verbringungsstellung im Mantelflächenbereich der Projektil-Spitze (14) in eine Wirkstellung etwa quer zur Projektillängsachse (28) ausschwenkbar sind, dadurch gekennzeichnet, dass die Sektoren (24) etwa in der Mitten-Querschnittsebene der Spitze (14), weit vorne vor der Trennebene zum Projektil Körper (12) im verjüngten Bereich der Spitze (24), angelenkt sind, wo sie - unter Vermeidung eines Ausschwenkens gegen einen gehäusefesten Anschlag - frei und ungebremst in ihre Wirkstellung durchschwingen, die durch das Kräftegleichgewicht der an den Sektoren (24) angreifenden Zentrifugal- und Staudruckkräfte gegeben ist.
- Projektil nach Anspruch 1,
dadurch gekennzeichnet, daß die Sektoren (24) um Bolzen (25) in die Wirkstellung ausschwenkbar sind, welche in einem Gehäuse-Einschnitt (26) quer zur Längsachse (28) orientiert gelagert sind. - Projektil nach Anspruch 2,
dadurch gekennzeichnet, daß die Bolzen (25) jeweils derart aus einer sekanten Orientierung verschwenkt asymmetrisch gelagert sind, daß ein Ende eines Bolzens (25) einen größeren Abstand von der Längsachse (28) als das andere Ende aufweist, das vom in Umfangsrichtung sich anschließenden Bolzen (25) mit seinem den größeren Abstand aufweisenden Ende radial bezüglich der Projektil-Längsachse (28) hintergriffen ist. - Projektil nach einem der vorangehenden Ansprüche,
dadurch gekennzeichnet, daß die Sektoren (24) mit Schenkelbiegefedern um die Bolzen (25) herum aufgehängt sind, die den Sektoren (24) gegenüber gegen das Zünder-Gehäuse (27) radial abgestützt sind. - Projektil nach einem der vorangehenden Ansprüche,
dadurch gekennzeichnet, daß die Breite der in ihrer Verbringungsstellung einander überdeckenden Sektoren (24) in deren Wirkstellung einen mit Ausschnitten lückenden Ring etwa quer zur Projektil-Längsachse (28) erbringt. - Projektil nach dem vorangehenden Anspruch,
dadurch gekennzeichnet, daß die Lücken (32) von zwischen einander in Umfangsrichtung benachbarten Sektoren (24) eingespannten flexiblen Überbrückungen (33) überspannt sind. - Projektil nach dem vorangehenden Anspruch,
dadurch gekennzeichnet, daß die Sektoren (24) schmale Speichen sind. - Projektil nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet, daß die Sektoren (24) seitlich mit dreieckförmigen Federblechen (34) bestückt sind, die sich im Verbringungs-Zustand überlappen und im ausgeklappter Wirkstellung die Lücken (32) zwischen den Sektoren (24) zum geschlossenen Ring schließen. - Projektil nach dem vorangehenden Anspruch,
dadurch gekennzeichnet, daß die Federbleche (34) beiderseits eines Sektors (24) in gegeneinander versetzter projektil-axialer Position am Sektor (24) befestigt sind.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10023345A DE10023345C2 (de) | 2000-05-12 | 2000-05-12 | Drallstabilisiertes Projektil mit Bremseinrichtung |
DE10023345 | 2000-05-12 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1154223A2 EP1154223A2 (de) | 2001-11-14 |
EP1154223A3 EP1154223A3 (de) | 2001-11-28 |
EP1154223B1 true EP1154223B1 (de) | 2005-07-27 |
Family
ID=7641832
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01111503A Expired - Lifetime EP1154223B1 (de) | 2000-05-12 | 2001-05-11 | Drallstabilisiertes Projektil mit Bremseinrichtung |
Country Status (5)
Country | Link |
---|---|
US (1) | US6511016B2 (de) |
EP (1) | EP1154223B1 (de) |
KR (1) | KR20010104211A (de) |
DE (2) | DE10023345C2 (de) |
SG (1) | SG128407A1 (de) |
Families Citing this family (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
AUPR303501A0 (en) * | 2001-02-09 | 2001-03-08 | Kusic, Tom | Spiralling missile |
AUPR583001A0 (en) * | 2001-06-20 | 2001-07-12 | Kusic, Tom | Aircraft spiralling mechanism |
US7093791B2 (en) * | 2001-06-22 | 2006-08-22 | Tom Kusic | Aircraft spiralling mechanism—c |
US7637453B2 (en) * | 2001-06-22 | 2009-12-29 | Tom Kusic | Aircraft spiraling mechanism with jet assistance - A |
US7635104B1 (en) * | 2001-06-22 | 2009-12-22 | Tom Kusic | Aircraft spiraling mechanism with jet assistance—B |
US7165742B2 (en) * | 2001-06-22 | 2007-01-23 | Tom Kusic | Aircraft spiralling mechanism - B |
DE10143312C1 (de) * | 2001-09-04 | 2003-06-18 | Diehl Munitionssysteme Gmbh | Bremseinrichtung für ein bahnkorrigierbares drallstabilisiertes Artillerieprojektil |
US6860448B2 (en) * | 2001-09-05 | 2005-03-01 | Omnitek Partners, Llc | Deployable projectiles |
DE10236157A1 (de) | 2002-08-07 | 2004-02-26 | Junghans Feinwerktechnik Gmbh & Co. Kg | Programmierbarer Artilleriezünder |
WO2004031682A1 (de) * | 2002-09-13 | 2004-04-15 | Diehl Bgt Defence Gmbh & Co. Kg | Bremseinrichtung für ein bahnkorrigierbares drallstabilisiertes artillerieprojektil |
US7163176B1 (en) * | 2004-01-15 | 2007-01-16 | Raytheon Company | 2-D projectile trajectory correction system and method |
US7004424B1 (en) * | 2004-04-05 | 2006-02-28 | The United States Of America, As Represented By The Secretary Of The Army | Projectile flight altering apparatus |
DE102004036003B4 (de) * | 2004-07-23 | 2006-11-16 | Diehl Bgt Defence Gmbh & Co. Kg | Panzerhaubitze mit Programmiereinrichtung für Artilleriemunition mit Korrekturzünder |
US20060185931A1 (en) * | 2005-02-04 | 2006-08-24 | Kawar Maher S | Acoustic noise reduction apparatus for personal computers and electronics |
US7415931B2 (en) * | 2005-07-20 | 2008-08-26 | Textron Systems Corporation | Methods and apparatus for active deployment of a samara wing |
US7963442B2 (en) * | 2006-12-14 | 2011-06-21 | Simmonds Precision Products, Inc. | Spin stabilized projectile trajectory control |
US7642491B2 (en) * | 2007-03-19 | 2010-01-05 | Tom Kusic | Aircraft spiraling mechanism with jet assistance—D |
US8319163B2 (en) | 2008-07-09 | 2012-11-27 | Bae Systems Land & Armaments, L.P. | Roll isolation bearing |
WO2010023636A1 (en) * | 2008-08-28 | 2010-03-04 | Denel (Pty) Ltd | Projectile drag augmentation device |
US8438977B2 (en) * | 2008-12-25 | 2013-05-14 | Lockheed Martin Corporation | Projectile having deployable fin |
WO2010083517A1 (en) * | 2009-01-16 | 2010-07-22 | Bae Systems Land & Armaments L.P. | Munition and guidance navigation and control unit |
KR101043308B1 (ko) * | 2009-01-30 | 2011-06-22 | 국방과학연구소 | 시험용 포탄의 사거리 감소방법, 사거리 감소신관 및 이를 구비하는 시험용 포탄 |
JP4732546B1 (ja) * | 2010-11-22 | 2011-07-27 | 英世 村上 | 飛行装置 |
TR201901397T4 (tr) * | 2011-05-13 | 2019-02-21 | Leigh Aerosystems Corp | Karadan fırlatılan roket güdüm sistemi. |
US8816261B1 (en) * | 2011-06-29 | 2014-08-26 | Raytheon Company | Bang-bang control using tangentially mounted surfaces |
SE536255C2 (sv) | 2012-02-06 | 2013-07-23 | Bae Systems Bofors Ab | Bromspanel för ett tändrör eller en projektil |
US9021961B1 (en) * | 2012-03-20 | 2015-05-05 | The United States Of America As Represented By The Secretary Of The Army | Enhanced stability extended range (guidance adaptable) 40 mm projectile |
JP6103532B2 (ja) * | 2013-05-30 | 2017-03-29 | 株式会社Ihiエアロスペース | 飛翔体発射装置 |
US11371814B2 (en) | 2015-08-24 | 2022-06-28 | Leigh Aerosystems Corporation | Ground-projectile guidance system |
WO2017062563A1 (en) | 2015-10-08 | 2017-04-13 | Leigh Aerosystems Corporation | Ground-projectile system |
SE1800208A1 (sv) * | 2018-10-30 | 2020-05-01 | Bae Systems Bofors Ab | Bromsanordning, tändrör samt projektil |
CN111272025B (zh) * | 2020-01-23 | 2020-10-30 | 西安现代控制技术研究所 | 一种时序展开弹速控制装置 |
US11835319B2 (en) * | 2021-06-07 | 2023-12-05 | The Boeing Company | Guided projectile and countermeasure systems and methods for use therewith |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL2171C (de) | 1914-04-18 | |||
US3047259A (en) * | 1959-11-25 | 1962-07-31 | George J Tatnall | Speed brake retarding mechanism for an air-dropped store |
DE2856859A1 (de) * | 1978-12-30 | 1980-07-17 | Dynamit Nobel Ag | Uebungsflugkoerper mit drallstabilisierung |
DE3608109A1 (de) | 1986-03-12 | 1987-09-17 | Diehl Gmbh & Co | Bremseinrichtung fuer ein drallstabilisiertes projektil |
GB9614133D0 (en) * | 1996-07-05 | 1997-03-12 | Secr Defence | Means for increasing the drag on a munition |
US5762291A (en) | 1996-10-28 | 1998-06-09 | The United States Of America As Represented By The Secretary Of The Army | Drag control module for stabilized projectiles |
DE19861399B4 (de) | 1998-05-29 | 2009-04-30 | Rheinmetall Waffe Munition Gmbh | GPS-gestütztes Geschoss |
DE19845611A1 (de) * | 1998-07-27 | 2000-02-10 | Oerlikon Contraves Gmbh | Verfahren zur Flugbahnkorrektur von Flugkörpern |
-
2000
- 2000-05-12 DE DE10023345A patent/DE10023345C2/de not_active Revoked
-
2001
- 2001-03-28 SG SG200101949A patent/SG128407A1/en unknown
- 2001-04-18 KR KR1020010020810A patent/KR20010104211A/ko not_active Application Discontinuation
- 2001-05-10 US US09/853,107 patent/US6511016B2/en not_active Expired - Fee Related
- 2001-05-11 DE DE50106858T patent/DE50106858D1/de not_active Expired - Lifetime
- 2001-05-11 EP EP01111503A patent/EP1154223B1/de not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
US20010039898A1 (en) | 2001-11-15 |
DE10023345A1 (de) | 2001-11-22 |
EP1154223A3 (de) | 2001-11-28 |
EP1154223A2 (de) | 2001-11-14 |
DE50106858D1 (de) | 2005-09-01 |
SG128407A1 (en) | 2007-01-30 |
KR20010104211A (ko) | 2001-11-24 |
DE10023345C2 (de) | 2002-03-28 |
US6511016B2 (en) | 2003-01-28 |
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