EP1154223A2 - Drallstabilisiertes Projektil mit Bremseinrichtung - Google Patents
Drallstabilisiertes Projektil mit Bremseinrichtung Download PDFInfo
- Publication number
- EP1154223A2 EP1154223A2 EP01111503A EP01111503A EP1154223A2 EP 1154223 A2 EP1154223 A2 EP 1154223A2 EP 01111503 A EP01111503 A EP 01111503A EP 01111503 A EP01111503 A EP 01111503A EP 1154223 A2 EP1154223 A2 EP 1154223A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- projectile
- sectors
- longitudinal axis
- projectile according
- tip
- 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
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 generic projectile is known from WO 98/01719 A1.
- the technical problem of the present invention lies in the knowledge of these circumstances based on a projectile of the generic type with an easily activated, uncontrolled (i.e. having two-point behavior) and yet very effective, functionally reliable equip aerodynamic braking device.
- this task is according to the characterizing part of the main claim essentially solved in that as an aerodynamic braking device approximately in the middle the projectile tip on from the transfer position, against the inflow, can be swung out into a geometrically defined operative position Flap system is provided, which there in a circumferential recess on the wall of the igniter housing is articulated. Because in the top of the large-caliber ones of interest here Ammunition for the tube artillery is housed the detonator, is the complete tip for designed for disassembly, that is, easily replaceable on the body of the projectile supported. As a result, the conventional, imported ammunition can also be retrofitted can be equipped with this braking device for influencing the trajectory by simply the conventional projectile tip is replaced by another with the brake elements becomes.
- the centrifugal force acts on the spin-stabilized Projectile swinging the flap-shaped swing out without braking Sectors of the braking device into a star-shaped, approximately radially oriented operative position, due to the equilibrium of forces of the centrifugal and dynamic pressure forces are given.
- the location as far as possible in front of the parting plane to the projectile body is also useful because there is practically no inside of the tip is required for detonator functions and because this area is also of no significance for the design for the overall rigidity of the projectile, that is, a weakening of the Ignition housing through radial recesses for mounting the swivel shafts for the brake flaps quite tolerated.
- the individual flap-shaped brake sectors not swung out against a stop fixed to the housing, because that is there - especially with possibly in the direction of flow acting flow - raise critical stability problems would.
- the brake elements can be opened through deposited between the brake elements and the housing of the projectile tip clamped leg springs are promoted.
- the flap-shaped brake elements carry hardly radial. Therefore, they must not be so wide that they e.g. At her Project the linkage laterally over the surface of the igniter tip. Therefore are comparative narrow flaps offset circumferentially against each other at asymmetrical mounted bolt-shaped swivel shafts. Under two each other Adjacent flaps can be arranged around the entire circumference the top, thanks to mutual support, a uniform set-up to promote all valves.
- the braking effect can be increased by the gaps be bridged between the ring disk sectors by flexible elements, for example through textile cut-outs, which arise when the flaps are set up between the sectors span.
- the textile ring that is braced by the spokes can then still be braced by an unsupported one circumferential edge are enlarged to the braking surface for the incoming flow to optimize.
- the essentially textile continuous structure of the braking device due to a mechanically more stable because it is metallically closed in the direction of flow Ring surface should be replaced, as yes by the width of the flap-shaped sectors alone cannot be reached without gaps, then these braking elements can be radial on themselves extending sector longitudinal edges equipped on both sides with triangular spring plates be the one another in the folded state of the sectors with elastic adjustment overlap alternately on the lateral surface curvature of the projectile tip and in stretched unfolded state, the free cutouts between the flaps just cover in pairs.
- a spin-stabilized artillery projectile 11 consists essentially of a straight one hollow cylindrical body 12, in which a removable detonator 13 engages frontally.
- the Detonator 13 is thus part of the tip 14 of the projectile 11, the contour of which is essentially is determined by their ballistic hood 15.
- the igniter 13 is detachably connected to the body 12 via a coaxial screw connection 16. It then protrudes through the parting plane 17 between the tip 14 and body 12 of the Projectile 11 with at least one ignition amplifier or transmitter charge 18 together with securing device 19 into the front area of the body 12. Before that lies approximately in the division level 17, e.g. Navigation unit based on satellite navigation 20 behind a battery 21 in the base of the projectile tip 14. Between this and the evaluation electronics 22 in the front area of the igniter 13 is an ignition electronics 23 arranged approximately in the axial center plane.
- flap-shaped elements of the braking device Washer sectors 24 to the front - that is, against the flow - under the action of centrifugal force Swing-out without any stops.
- Each of the flap-shaped sectors 24 is therefor a pin 25 oriented tangentially in the jacket area as a short bearing and Assigned swivel shaft.
- the bolts 25 lie in radial incisions 26, which are approximately in the center transverse plane of the tip 14 is introduced into the igniter housing 27 in the circumferential direction are. The beginning and end, i.e.
- the sequence of bolts 25 does not lie on one that is concentric with the longitudinal axis 28 of the project Circle, but radially asymmetrical, namely with one end inside and radially offset with the other end outside this circle, so that the Bolts 25 adjacent on both sides in the circumferential direction are mounted radially in front of or behind them are.
- This pivoting from the direction of the secants in the above-mentioned Circle and thus the asymmetrical orientation of the bolts with respect to the axis 28 25 makes it possible to carry out their bearings on both sides identically for all bolts 25 and thereby a symmetrical installation behavior of each other in the circumferential direction to promote neighboring sectors 24.
- the relatively narrow sectors 24 are profiled so as to be curved around their longitudinal axes folded or movement state according to Fig. 1 / Fig. 2 the contours on the one hand inside of the housing 27 and on the other hand outside of the rear continuation of the here deposited to adapt ballistic hood 15 as well as possible.
- this state of movement can over the hammered flaps (ring sectors 24) one (dashed lines in Fig. 2) considered) bracket sleeve 29 to be put on to continue in the rear the shortened hood 15 to define its lateral surface contour, that is, the aerodynamic ensure smooth geometry and compared to the surface of the conventional Projectile tip 14 not to be changed.
- this sleeve 29 is e.g.
- the sectors 24 can then can also be thinned to narrow radial spokes, the suspension of which on short Bolt 25 constructively less problematic than the folding suspension of the wider sectors 24 and is in the issued state an umbrella-like stiffening then bring the overall textile disk-shaped braking device.
- a swirl-stabilized artillery projectile 11 can therefore be simply with an axially symmetrical aerodynamic braking device to shorten the ballistic trajectory retrofit if the equipped with the igniter 13 from the projectile body 12 without any problems
- Removable tip 14 at about half height with articulated hinged under centrifugal force Sectors 24 is populated, which are in the conical in their transfer position Nest the shape of the outer surface and in the operative position to a gaping or closed issued radial ring are unfolded.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Braking Arrangements (AREA)
- Folding Of Thin Sheet-Like Materials, Special Discharging Devices, And Others (AREA)
Abstract
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 längs seiner Flugbahn aus einer Verbringungsstellung in die axialsymmetrische Wirkstellung radial aufstellbarer aerodynamischer Bremseinrichtung im Projektil-Frontbereich,
dadurch gekennzeichnet, daß seine Spitze (14) in etwa ihrer Mitten-Querschnittsebene mit Lagerstellen für klappenförmige Ringscheiben-Sektoren (24) ausgestattet ist, die aus einer Verbringungsstellung im Mantelflächenbereich der Spitze (14) in eine Wirkstellung etwa quer zur Projektillängsachse (28) ausschwenkbar sind. - 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 |
---|---|---|---|
DE10023345 | 2000-05-12 | ||
DE10023345A DE10023345C2 (de) | 2000-05-12 | 2000-05-12 | Drallstabilisiertes Projektil mit Bremseinrichtung |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1154223A2 true EP1154223A2 (de) | 2001-11-14 |
EP1154223A3 EP1154223A3 (de) | 2001-11-28 |
EP1154223B1 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) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2010023636A1 (en) * | 2008-08-28 | 2010-03-04 | Denel (Pty) Ltd | Projectile drag augmentation device |
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 |
US7165742B2 (en) * | 2001-06-22 | 2007-01-23 | Tom Kusic | Aircraft spiralling mechanism - B |
US7635104B1 (en) | 2001-06-22 | 2009-12-22 | Tom Kusic | Aircraft spiraling mechanism with jet assistance—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 |
AU2003283241A1 (en) * | 2002-09-13 | 2004-04-23 | Diehl Munitionssysteme Gmbh And Co. Kg | Braking device for a trajectory-correctable spin-stabilized artillery projectile |
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 |
WO2010039322A2 (en) * | 2008-07-09 | 2010-04-08 | Bae Systems Land & Armaments L.P. | Roll isolation bearing |
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 |
ES2709655T3 (es) | 2011-05-13 | 2019-04-17 | Leigh Aerosystems Corp | Sistema de guiado de proyectil terrestre |
US8816261B1 (en) * | 2011-06-29 | 2014-08-26 | Raytheon Company | Bang-bang control using tangentially mounted surfaces |
SE1230014A1 (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 |
US20190141969A1 (en) * | 2017-11-16 | 2019-05-16 | Verily Life Sciences Llc | Insect release devices |
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 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3608109A1 (de) | 1986-03-12 | 1987-09-17 | Diehl Gmbh & Co | Bremseinrichtung fuer ein drallstabilisiertes projektil |
WO1998001719A1 (en) | 1996-07-05 | 1998-01-15 | The Secretary Of State For Defence | Means for increasing the drag on a munition |
DE19845611A1 (de) | 1998-07-27 | 2000-02-10 | Oerlikon Contraves Gmbh | Verfahren zur Flugbahnkorrektur von Flugkörpern |
Family Cites Families (5)
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 |
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 |
-
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 EP EP01111503A patent/EP1154223B1/de not_active Expired - Lifetime
- 2001-05-11 DE DE50106858T patent/DE50106858D1/de not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3608109A1 (de) | 1986-03-12 | 1987-09-17 | Diehl Gmbh & Co | Bremseinrichtung fuer ein drallstabilisiertes projektil |
WO1998001719A1 (en) | 1996-07-05 | 1998-01-15 | The Secretary Of State For Defence | Means for increasing the drag on a munition |
DE19845611A1 (de) | 1998-07-27 | 2000-02-10 | Oerlikon Contraves Gmbh | Verfahren zur Flugbahnkorrektur von Flugkörpern |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2010023636A1 (en) * | 2008-08-28 | 2010-03-04 | Denel (Pty) Ltd | Projectile drag augmentation device |
Also Published As
Publication number | Publication date |
---|---|
DE10023345C2 (de) | 2002-03-28 |
DE10023345A1 (de) | 2001-11-22 |
EP1154223A3 (de) | 2001-11-28 |
EP1154223B1 (de) | 2005-07-27 |
KR20010104211A (ko) | 2001-11-24 |
DE50106858D1 (de) | 2005-09-01 |
SG128407A1 (en) | 2007-01-30 |
US6511016B2 (en) | 2003-01-28 |
US20010039898A1 (en) | 2001-11-15 |
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