EP1249680A1 - Ruderblatt-Lagereinrichtung für ein Geschoss - Google Patents
Ruderblatt-Lagereinrichtung für ein Geschoss Download PDFInfo
- Publication number
- EP1249680A1 EP1249680A1 EP02007872A EP02007872A EP1249680A1 EP 1249680 A1 EP1249680 A1 EP 1249680A1 EP 02007872 A EP02007872 A EP 02007872A EP 02007872 A EP02007872 A EP 02007872A EP 1249680 A1 EP1249680 A1 EP 1249680A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rudder blade
- bearing
- rudder
- foot
- 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.)
- Granted
Links
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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
Definitions
- the invention relates to a rudder blade storage device for a floor according to the preamble of claim 1.
- a rudder control device for a missile is included a pendulum-mounted servomotor known, the one via a spindle Driving nut drives a rudder shaft by means of a driving fork the rudder blade is rotatable.
- Servomotor and the rudder shaft mounted on a common support block, which in Missile is mountable.
- the rudder shaft has a receptacle in which the Rudder blade engages positively in the direction of adjustment. Between the rudder shaft and the driving fork is a positive connection in the direction of adjustment intended.
- rudder blade storage devices for projectiles which are bullets that can be fired by a propellant charge are sensitive against pollution caused by combustion residues, often unavoidable. Such pollution can affect the Functional safety influence.
- the invention is based on the object Rudder blade storage device for a floor of the type mentioned at the beginning create, eliminating sensitivity to pollution and thus excellent functional reliability, i.e. Ensuring fast and safely opening the rudders of a combustion chamber projectile which can be closed by propellant charge is guaranteed.
- the axial distance between the front surfaces of the two side parts of the bearing element of the rudder blade bearing device is larger than the axial thickness dimension of the rudder blade foot, and in that the Rudder blade axis between the two side parts secured against rotation axially limited movement and the rudder blade base with the rudder blade axis is positively connected such that the rudder blade foot in the opened Active position of the rudder blade against the front surface of one side part of the Bearing element forced and in the folded inactive position by the form-fitting connection spaced from this front surface and thus the Rudder blade foot axially limited with the rudder blade axis relative to the bearing element movable and the rudder blade consequently freely between the folded Inactive position and the opened active position adjustable, i.e.
- rudder blade bearing device consist in the high positional accuracy of the opened rudder blade, because in this Active position between the rudder blade and the bearing element no play is available in an inexpensive construction because the rudder blade bearing device according to the invention only from a few, simply trained parts with small Tolerance requirements exist, as well as in the reduced friction, so that after the respective rudder blade quickly and reliably after leaving the pipe mouth opened, i.e. is set to the opened, play-free active position.
- the space required for the rudder blade bearing device according to the invention low. Due to the low tolerance requirements of the parts of the Rudder blade storage device according to the invention, i.e. the tolerance requirements to the bearing element and the associated rudder blade is also advantageous a surface coating of said parts is unproblematic.
- FIG. 1 shows a rudder blade bearing device 10 for a propellant charge projectile that can be fired from a barrel.
- the rudder blade storage facility 10 has a rudder blade 12 with a rudder blade foot 14 and a bearing element 16 for the rudder blade 12 on.
- the bearing element 16 has a circular base part 18, from which a bearing journal 20 protrudes in the middle. This is about the journal 20 Rudder blade 12 adjustable for steering the projectile.
- the two side parts 22 and 24 are one-sided connected to each other in one piece. On the other side are the two side parts 22 and 24 separated from each other by a slot 26.
- the rudder blade 12 is about a pivot axis 28 with respect to the bearing element 16 between a folded inactive position (not shown) and a Opened active position shown in the drawing can be pivoted. In the retracted inactive position, the rudder blade 12 extends through the slot 26 therethrough.
- FIG. 1 and 2 illustrate that the side part 22 of the bearing element 16 with one assigned to the pivot axis 28 and deviating from the circular shape Recess 30 is formed.
- FIG. 3 illustrates the side part 24 of the Bearing element 16, which is associated with one of the pivot axis 28 circular blind hole 32 for a contact collar 34 of a rudder blade axis 36 for the Rudder blade 12 is formed.
- the rudder blade axis 36 is on the front with one of the circular shape deviating blind hole 38.
- FIG. 3 also illustrates a hole 40 in the side part 24 of the bearing element 16, which is provided for a locking element 42 of a resilient locking device 44 is. With the aid of the locking device 44, the rudder blade 12 is opened in the Active position locked with the bearing element 16.
- FIG. 4 illustrates all the individual parts of the rudder blade bearing device 10 in one spatial exploded view with the rudder blade 12 and the bearing element 16 and with the other individual parts, which are described in more detail below become.
- the rudder blade foot 14 of the rudder blade 12 is ring-shaped on one side Recess 46 formed, which to a central internal threaded bore 48th is provided concentrically.
- the annular recess 46 is for receiving a hinged spring element 50 is provided.
- the pop-up spring element 50 has at least one spring turn 52 and a first spring leg 54 and a second spring leg 56.
- the annular recess 46 in Rudder blade foot 14 serves to receive the at least one spring turn 52 Slot 58 in the rudder blade base 14 serves to receive and fix the first one Spring leg 54 of the opening spring element 50.
- the second spring leg 56 of the pop-up spring element 50 is in a (not shown) hole in the Bearing element 16 of the rudder blade bearing device 10 is fixed.
- the two have a spacing from one another Side parts 22 and 24 facing front surfaces 60 and 62 through which a receiving space 64 for the rudder blade foot 14 is limited.
- a receiving space 64 for the rudder blade foot 14 is limited.
- the rudder blade axis 36 has an external thread section 68 formed of the internal threaded bore 48 in the rudder blade 14 of the Rudder blade 12 is adapted.
- FIG. 5 also shows that the rudder blade axis 36 between the two Side parts 22 and 24 of the bearing element 16 by means of a Anti-rotation element 74 axially limited secured against rotation is provided movably.
- the positive connection between the rudder blade axis 36 and the Rudder blade base 14 can, for example, by metric threads 48, 68 Trapezoidal thread or through suitably shaped recesses and ridges - one or multi-course - be realized.
- the rudder blade base 14 is through the rudder blade axis 36 External thread section 68 of the rudder blade axis 36 and the internal threaded bore 48 of the rudder foot 14 positively connected such that the rudder foot 14 in the opened active position of the rudder blade 12 against the front surface 62 of the side part 24 or against a thrust ring element belonging to the side part 24 76 is forced. This is done by adjusting the Rudder blade axis 36 causes. As a result, in the unfolded active position high positional accuracy of the rudder blade 12 reached.
- the rudder blade 12 is adjusted in the opened active position of the Rudder blade 12 in such a way that the rudder blade 12 or its rudder blade foot 14 by rotating the rudder blade axis 36 against the thrust ring element 76 or against the front surface 62 of the side part 24 of the Bearing element 16 is forced.
- the Circular shape deviating, i.e. a regular hexagonal contour Blind hole 38 of the rudder blade axis 36 inserted a suitable tool and the Rudder blade axis 36 rotated until the rudder blade foot 14 against the thrust ring element 76 or the front surface 62 is forced.
- Anti-rotation element 74 fixed to the rudder blade axis 36.
- Hinged spring element 50 mechanically tensioned.
- the pop-up spring element 50 can relax again the rudder blade 12 from the folded inactive position to the opened To adjust active position.
- the Rudder blade foot 14 again against the thrust ring element 76 or the front surface 62 of the side part 24 of the bearing element 16 and thus the rudder blade 12 connected to the bearing element 16 in a form-fitting manner.
- the rudder blade axis 36 has two axially spaced cylindrical ones Bearing sections 80 and 82 formed on the bearing bores 84 and 86 in the Adjusted side parts 24 and 22 of the bearing element 16 with a sliding fit tolerance are. At one end, the rudder blade axis 36 is connected to the Contact collar 34 and with the blind hole 38 deviating from the circular shape educated. This is at the opposite second end of the rudder blade axis 36 Anti-rotation element 74 fixed. The anti-rotation element 74 is in the recess 30 of the shape adapted to the anti-rotation element 74 associated side part 22 of the bearing member 16 attached.
- a second thrust ring element 88 is provided in the bearing element 16. In the unfolded active position of the rudder blade 12 is between the rudder blade foot 14 and the last-mentioned second thrust ring element 88 has a gap 90 available.
- FIG. 6 illustrates the rudder blade in sections in a sectional illustration 12 with its rudder blade foot 14 and sections of the two side parts 22 and 24 of the bearing element 16 of the rudder blade device 10 and a training of resilient locking device 44 with which the rudder blade 12 in the unfolded Active position with respect to the bearing element 16 is fixed.
- the rudder blade foot 14 is formed with a blind hole 92 in which the pin-shaped locking element 42nd is provided axially movable. Between the locking element 42 and the bottom 94 of the blind hole 92, a locking spring element 96 is arranged, which in the folded inactive position of the rudder blade 12 is mechanically tensioned.
- the Side part 24 is formed with the hole 40 for the pin-like locking element 42.
- the rudder blade 12 When the rudder blade 12 is in the uncapped active position, it is in the form of a pin Locking element 42 with a stepped front section 98 reduced Cross section into the hole 40 to the rudder blade 12 in the unfolded Fix active position. This is achieved by relaxing the locking spring element 96 causes.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Support Of The Bearing (AREA)
Abstract
Description
- Figur 1
- eine perspektivische Darstellung der Ruderblatt-Lagereinrichtung,
- Figur 2
- eine Seitenansicht der Ruderblatt-Lagereinrichtung gemäß Figur 1 in Blickrichtung des Pfeiles II,
- Figur 3
- eine Seitenansicht der Ruderblatt-Lagereinrichtung gemäß Figur 1 von der anderen Seite, d.h. in Blickrichtung des Pfeiles III,
- Figur 4
- eine räumliche Explosionsdarstellung der Ruderblatt-Lagereinrichtung gemäß den Figuren 1, 2 und 3,
- Figur 5
- abschnittweise eine Schnittdarstellung der Ruderblatt-Lagereinrichtung gemäß den Figuren 1 bis 4, und
- Figur 6
- abschnittweise geschnitten die Ruderblatt-Lagereinrichtung zur Verdeutlichung der federnden Rasteinrichtung zur Fixierung des Ruderblattes in der aufgeklappten Aktivstellung in bezug auf das Lagerelement.
- 10
- Ruderblatt-Lagereinrichtung
- 12
- Ruderblatt (von 10)
- 14
- Ruderblattfuß (von 12)
- 16
- Lagerelement (von 10 für 14)
- 18
- Basisteil (von 16)
- 20
- Lagerzapfen (von 16)
- 22
- Seitenteil (von 16)
- 24
- Seitenteil (von 16)
- 26
- Schlitz (zwischen 24 und 26)
- 28
- Schwenkachse (in 16 für 12)
- 30
- Ausnehmung (in 22 für 74)
- 32
- Sackloch (in 24 für 34)
- 34
- Anlagebund (von 36)
- 36
- Ruderblattachse (in 16 für 12)
- 38
- Sackloch (in 36)
- 40
- Loch (in 24 für 42)
- 42
- Arretierelement (in 14)
- 44
- Rasteinrichtung (für 12)
- 46
- ringförmige Aussparung (in 14 für 50)
- 48
- Innengewindebohrung (in 14 für 36)
- 50
- Aufklapp-Federelement (für 12)
- 52
- Federwindung (von 509
- 54
- erster Federschenkel (von 50)
- 56
- zweiter Federschenkel (von 50)
- 58
- Schlitz (in 14 für 54)
- 60
- Frontfläche (von 22)
- 62
- Frontfläche (von 24)
- 64
- Aufnahmeraum (zwischen 60 und 62 für 14)
- 68
- Außengewindeabschnitt (von 36)
- 70
- axialer Abstand (zwischen 60 und 62)
- 72
- axiale Dickenabmessung (von 14)
- 74
- Verdrehsicherungselement (an 36)
- 76
- Anlauf-Ringelement (zwischen 14 und 62)
- 78
- Schraubelement (für 74)
- 80
- Lagerabschnitt (von 36 in 24)
- 82
- Lagerabschnitt (von 36 in 22)
- 84
- Lagerbohrung (in 24 für 80)
- 86
- Lagerbohrung (in 22 für 82)
- 88
- zweites Anlauf-Ringelement (zwischen 14 und 60)
- 90
- Spalt (zwischen 14 und 88)
- 92
- Sackloch (in 14 für 42)
- 94
- Grund (von 92)
- 96
- Arretier-Federelement (zwischen 42 und 94)
- 98
- Vorderabschnitt (von 42)
Claims (9)
- Ruderblatt-Lagereinrichtung für ein Geschoß, mit einem Ruderblatt (12) und mit einem für den Ruderblattfuß (14) des Ruderblattes (12) vorgesehenen Lagerelement (16), das zwei voneinander beabstandete Seitenteile (22 und 24) mit einander zugewandten Frontflächen (60 und 62) aufweist, durch die ein Aufnahmeraum (64) für den Ruderblattfuß (14) begrenzt ist, wobei sich zwischen den beiden Seitenteilen (22 und 24) durch den Aufnahmeraum (64) eine Ruderblattachse (36) für das zwischen einer eingeklappten Inaktivstellung und einer aufgeklappten Aktivstellung verstellbare Ruderblatt (12) hindurcherstreckt,
dadurch gekennzeichnet, daß der axiale Abstand (70) zwischen den Frontflächen (60 und 62) der beiden Seitenteile (22 und 24) größer ist als die axiale Dickenabmessung (72) des Ruderblattfußes (14), und daß die Ruderblattachse (36) zwischen den beiden Seitenteilen (22 und 24) gegen Verdrehung gesichert axial begrenzt beweglich angeordnet und der Ruderblattfuß (14) mit der Ruderblattachse (36) formschlüssig derartig verbunden ist, daß der Ruderblattfuß (14) in der aufgeklappten Aktivstellung des Ruderblattes (12) gegen die Frontfläche (62) des einen Seitenteiles (24) gezwängt und in der eingeklappten Inaktivstellung durch die formschlüssige Verbindung von dieser Frontfläche (62) beabstandet und somit der Ruderblattfuß (14) mit der Ruderblattachse (36) axial begrenzt beweglich und das Ruderblatt (12) frei von der eingeklappten Inaktivstellung in die aufgeklappte Aktivstellung verstellbar ist. - Ruderblatt-Lagereinrichtung nach Anspruch 1,
dadurch gekennzeichnet, daß die Ruderblattachse (36) mit einem Außengewindeabschnitt (68) und daß der Ruderblattfuß (14) mit einer an den Außengewindeabschnitt (68) angepaßten Innengewindebohrung (48) ausgebildet ist, die die formschlüssige Verbindung zwischen der Ruderblattachse (36) und dem Ruderblattfuß (14) bilden. - Ruderblatt-Lagereinrichtung nach Anspruch 1 oder 2,
dadurch gekennzeichnet, daß die Ruderblattachse (36) mit zwei axial voneinander beabstandeten zylindrischen Lagerabschnitten (80 und 82) und daß die beiden Seitenteile (22 und 24) des Lagerelementes (16) mit an die zugehörigen Lagerabschnitte (82 und 80) angepaßten Lagerbohrungen (86 und 84) ausgebildet sind. - Ruderblatt-Lagereinrichtung nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, daß die Lagerachse (36) an ihrem einen stirnseitigen Ende einen Anlagebund (34) und ein von der Kreisform abweichendes Sackloch (38) aufweist, und daß am gegenüberliegenden zweiten Ende der Ruderblattachse (36) ein Verdrehsicherungselement (74) befestigt ist, das in einer formmäßig angepaßten Ausnehmung (30) des Lagerelementes (16) vorgesehen ist. - Ruderblatt-Lagereinrichtung nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet, daß zwischen dem Ruderblattfuß (14) und den Frontflächen (60 und 62) der beiden Seitenteile (22 und 24) des Lagerelementes (16) jeweils ein dünnes Anlauf-Ringelement (88, 76) vorgesehen ist. - Ruderblatt-Lagereinrichtung nach einem der Ansprüche 1 bis 5,
dadurch gekennzeichnet, daß das Ruderblatt (12) mittels eines mechanisch gespannten Aufklapp-Federelementes (50) von der eingeklappten Inaktivstellung in die aufgeklappte Aktivstellung verstellbar ist, das zwischen dem Ruderblattfuß (14) und dem Lagerelement (16) festgelegt ist. - Ruderblatt-Lagereinrichtung nach Anspruch 6,
dadurch gekennzeichnet, daß das Aufklapp-Federelement (50) von einer Schraubenfeder mit mindestens einer Federwindung (52) und zwei Federschenkeln (54 und 56) gebildet ist, wobei die mindestens eine Federwindung (52) in einer im Ruderblattfuß (14) ausgebildeten ringförmigen Aussparung (46) angeordnet und der eine Federschenkel (54) in einem Schlitz (58) im Ruderblattfuß (14) und der zweite Federschenkel (56) in einem Loch im Lagerelement (16) festgelegt ist. - Ruderblatt-Lagereinrichtung nach einem der Ansprüche 1 bis 7,
dadurch gekennzeichnet, daß das Ruderblatt (12) in seiner aufgeklappten Aktivstellung mittels einer im Ruderblattfuß (14) vorgesehenen federnden Rasteinrichtung (44) am Lagerelement (16) festlegbar ist. - Lagerblatt-Lagereinrichtung nach Anspruch 8,
dadurch gekennzeichnet, daß der Ruderblattfuß (14) mit einem Sackloch (92) ausgebildet ist, in dem ein Arretierelement (42) und ein mechanisch vorgespanntes Arretier-Federelement (96), die die Rasteinrichtung (44) bilden, angeordnet sind, und daß eines der beiden Seitenteile (24) des Lagerelementes (16) mit einem Loch (40) ausgebildet ist, in das das Arretierelement (42) mit einem abgesetzten Vorderabschnitt (98) reduzierten Querschnitts mittels des Arretier-Federelementes (96) in der aufgeklappten Aktivstellung hineinsteht.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10118216A DE10118216A1 (de) | 2001-04-12 | 2001-04-12 | Ruderblatt-Lagereinrichtung für ein Geschoß |
DE10118216 | 2001-04-12 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1249680A1 true EP1249680A1 (de) | 2002-10-16 |
EP1249680B1 EP1249680B1 (de) | 2005-12-14 |
Family
ID=7681308
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02007872A Expired - Lifetime EP1249680B1 (de) | 2001-04-12 | 2002-04-09 | Ruderblatt-Lagereinrichtung für ein Geschoss |
Country Status (4)
Country | Link |
---|---|
US (1) | US6578792B2 (de) |
EP (1) | EP1249680B1 (de) |
DE (2) | DE10118216A1 (de) |
IL (1) | IL148156A0 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3032212A1 (de) * | 2014-12-11 | 2016-06-15 | MBDA Deutschland GmbH | Rudersystem |
US10006748B2 (en) | 2014-12-11 | 2018-06-26 | Mbda Deutschland Gmbh | Rudder system |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2446988C1 (ru) * | 2010-10-15 | 2012-04-10 | Открытое акционерное общество "Корпорация "Тактическое ракетное вооружение" | Складная рулевая поверхность летательного аппарата |
RU2549044C2 (ru) * | 2013-01-24 | 2015-04-20 | Открытое акционерное общество "Корпорация "Тактическое ракетное вооружение" | Складная рулевая поверхность авиационного средства поражения с пружинным механизмом раскладывания |
KR101356554B1 (ko) * | 2013-08-13 | 2014-01-29 | 국방과학연구소 | 유도탄의 날개 전개 및 접힘 구조 |
KR102552485B1 (ko) * | 2016-12-16 | 2023-07-06 | 현대자동차주식회사 | 연료전지 시스템 |
CN110230955A (zh) * | 2019-06-28 | 2019-09-13 | 浙江理工大学 | 潜入式折叠翼同步横向展开锁紧机构及其展开锁紧方法 |
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 |
CN115200419A (zh) * | 2022-07-29 | 2022-10-18 | 北京航天万润高科技有限公司 | 一种电动舵机 |
Citations (4)
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---|---|---|---|---|
US5048772A (en) * | 1990-01-26 | 1991-09-17 | Thomson-Brandt Armements | Device for roll attitude control of a fin-stabilized projectile |
DE4335785A1 (de) * | 1993-10-20 | 1995-04-27 | Diehl Gmbh & Co | Ruderstelleinrichtung |
US5685503A (en) * | 1994-06-28 | 1997-11-11 | Luchaire Defense As | Deployment device for the fin of a projectile |
US6202958B1 (en) * | 1998-06-19 | 2001-03-20 | Diehl Stiftung & Co. | Mounting arrangement for the pivotally openable rudder blades of a guided missile |
Family Cites Families (15)
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US3117520A (en) * | 1959-07-02 | 1964-01-14 | Martin Marietta Corp | Self-tightening attachment arrangement |
DE2227103A1 (de) * | 1972-06-03 | 1973-12-13 | Dynamit Nobel Ag | Klappleitwerk |
DE2342783C2 (de) * | 1973-08-24 | 1983-12-22 | Rheinmetall GmbH, 4000 Düsseldorf | Mit einem Leitwerk versehenes Geschoß |
GB1602338A (en) * | 1978-05-25 | 1981-11-11 | Bristol Aerojet Ltd | Rocket vehicles |
GB2150092B (en) * | 1983-11-25 | 1987-07-22 | British Aerospace | Deployment and actuation mechanisms |
DE3441534A1 (de) * | 1984-11-14 | 1986-05-15 | Diehl GmbH & Co, 8500 Nürnberg | Lageranordnung fuer das ruderblatt eines flugkoerpers |
DE3507677A1 (de) * | 1985-03-05 | 1986-09-11 | Diehl GmbH & Co, 8500 Nürnberg | Flugkoerper mit ueberkalibrigem leitwerk |
FR2655720A1 (fr) * | 1989-12-08 | 1991-06-14 | Thomson Brandt Armements | Aile galbee deployable pour engin volant. |
US5042749A (en) * | 1990-04-10 | 1991-08-27 | Sundstrand Corporation | Mechanism for limiting rotation of a rotatably mounted shaft |
DE4119613C2 (de) * | 1991-06-14 | 1997-03-27 | Diehl Gmbh & Co | Flugkörper mit ausklappbaren Leiteinrichtungen |
JPH063096A (ja) * | 1992-06-23 | 1994-01-11 | Mitsubishi Heavy Ind Ltd | 飛しょう体の展伸式操舵翼 |
IL107844A (en) * | 1993-12-02 | 1996-06-18 | Ministry Of Defence Armaments | Flying object control system |
DE19827278A1 (de) * | 1998-06-19 | 1999-12-23 | Diehl Stiftung & Co | Lenkbarer Flugkörper |
US6186443B1 (en) * | 1998-06-25 | 2001-02-13 | International Dynamics Corporation | Airborne vehicle having deployable wing and control surface |
DE19960738C1 (de) * | 1999-12-16 | 2001-08-23 | Lfk Gmbh | Ruderanbindung für Lenkflugkörper |
-
2001
- 2001-04-12 DE DE10118216A patent/DE10118216A1/de not_active Withdrawn
-
2002
- 2002-02-14 IL IL14815602A patent/IL148156A0/xx unknown
- 2002-04-04 US US10/116,532 patent/US6578792B2/en not_active Expired - Fee Related
- 2002-04-09 DE DE50205245T patent/DE50205245D1/de not_active Expired - Lifetime
- 2002-04-09 EP EP02007872A patent/EP1249680B1/de not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5048772A (en) * | 1990-01-26 | 1991-09-17 | Thomson-Brandt Armements | Device for roll attitude control of a fin-stabilized projectile |
DE4335785A1 (de) * | 1993-10-20 | 1995-04-27 | Diehl Gmbh & Co | Ruderstelleinrichtung |
US5685503A (en) * | 1994-06-28 | 1997-11-11 | Luchaire Defense As | Deployment device for the fin of a projectile |
US6202958B1 (en) * | 1998-06-19 | 2001-03-20 | Diehl Stiftung & Co. | Mounting arrangement for the pivotally openable rudder blades of a guided missile |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3032212A1 (de) * | 2014-12-11 | 2016-06-15 | MBDA Deutschland GmbH | Rudersystem |
US10006748B2 (en) | 2014-12-11 | 2018-06-26 | Mbda Deutschland Gmbh | Rudder system |
Also Published As
Publication number | Publication date |
---|---|
US6578792B2 (en) | 2003-06-17 |
DE10118216A1 (de) | 2002-10-17 |
DE50205245D1 (de) | 2006-01-19 |
IL148156A0 (en) | 2002-09-12 |
EP1249680B1 (de) | 2005-12-14 |
US20020148927A1 (en) | 2002-10-17 |
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