EP1108972A2 - Device for mounting a steering fin on a missile - Google Patents
Device for mounting a steering fin on a missile Download PDFInfo
- Publication number
- EP1108972A2 EP1108972A2 EP00126530A EP00126530A EP1108972A2 EP 1108972 A2 EP1108972 A2 EP 1108972A2 EP 00126530 A EP00126530 A EP 00126530A EP 00126530 A EP00126530 A EP 00126530A EP 1108972 A2 EP1108972 A2 EP 1108972A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- rudder
- missile
- shaft
- bearing
- recess
- 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
- 239000000919 ceramic Substances 0.000 claims description 3
- 238000005452 bending Methods 0.000 description 3
- 239000000428 dust Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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
- F42B10/60—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 device for rudder connection for Guided missile, with the rudder blade in one on the missile cell attached interface fitting mounted on a rudder shaft and by means of a Rudder drive lever is pivotable.
- the guided missiles are for medium Range mainly carried on the fuselage in a partially submerged arrangement, to reduce the air resistance and the radar signature cheaply influence.
- the shape of the aircraft interface is due to the currently introduced air-to-air guided missile of the type AMRAAM and was also specified for example with the prototypes of the Eurofighter EF 2000 in this form realized.
- For the rudders and wings of the AMRAAM are in the Airplane fuselage slot-shaped recesses with a width of 41 mm specified
- Fig. 1 shows the environment for the subject of the invention.
- the fuselage or the wings of the aircraft - is a recess with a fixed predetermined width of 41 mm available, which is for the inclusion of the Airplane-facing rudder blade R of a ready-to-use missile FK (AMRAAM) serves. With this space must be a compatible missile get along.
- AMRAAM Airplane-facing rudder blade R of a ready-to-use missile FK
- Fig. 2 shows the construction principle of the AMRAAM-compatible Rudder support for a ramjet-powered missile after Invention.
- 2a shows the proposed solution with a view to the Rudder axis W in the direction of the missile FK.
- 2b shows a section through the arrangement and the bending load curve BL through the Main elements interface fitting B and rudder shaft W.
- the interface fitting B for fastening to the thin-walled Dust separation chamber of the FK missile cell has an outer diameter B2 which on the one hand ensures compatibility and freedom of movement and on the other hand through the conical recess B3 in the cross-sectional profile to the bending stress that occurs due to the one acting on the rudder Air force Fq is caused is adjusted.
- the Rudder shaft W in ceramic needle bearings L.
- the cross-sectional profile of the rudder shaft W is due to the choice of the bearing diameter d1 (22 mm) and d2 (12 mm) also the load curve on the Rudder shaft W adapted.
- the rudder shaft W takes a slot-like shape Recess W4 the rudder R, which is the cylindrical part of the Interface fitting B2 encloses to the root as shown in Fig. 2c.
- the rudder drive lever H is form-fitting on the inside of the fitting the rudder shaft W connected.
- the rudder drive lever H is, as in the initially mentioned document explained by an electromechanical Actuating system actuated.
- the formation of the rudder interface W4 i.e. the connection between the rudder R and rudder shaft W, enables easy manufacture and quick
- the rudder blade can be fitted using standard tools Battle conditions.
- the rudder interface is also close to the pressure point of the rudder blade, therefore there are small root bending moments at the clamping point Furthermore, the sealing of the missile to the outside in the area of Missile interface fitting B and the rudder drive lever H simple and done perfectly, since the position of the relative movement at the outer end of the Interface fitting is.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Sliding-Contact Bearings (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Erfindung betrifft eine Vorrichtung zur Ruderanbindung für Lenkflugkörper, wobei das Ruderblatt in einem an der Flugkörperzelle befestigten Interface-Beschlag auf einer Ruderwelle gelagert und mittels eines Ruderantriebshebels schwenkbar ist.The invention relates to a device for rudder connection for Guided missile, with the rudder blade in one on the missile cell attached interface fitting mounted on a rudder shaft and by means of a Rudder drive lever is pivotable.
Eine derartige Vorrichtung ist aus der DE 196 35 847 C2 bekannt.Such a device is known from DE 196 35 847 C2.
Bei modernen Kampfflugzeugen werden die Lenkflugkörper für mittlere Reichweite überwiegend am Rumpf in teilversenkter Anordnung mitgeführt, um den Luftwiderstand zu reduzieren und die Radarsignatur günstig zu beeinflussen.In modern combat aircraft, the guided missiles are for medium Range mainly carried on the fuselage in a partially submerged arrangement, to reduce the air resistance and the radar signature cheaply influence.
Die Form des Flugzeuginterfaces ist durch den derzeit eingeführten Luft-Luft-Lenkflugkörper vom Typ AMRAAM vorgegeben und wurde auch beispielsweise bei den Prototypen des Eurofighter EF 2000 in dieser Form realisiert. Für die Ruder und Flügel der AMRAAM sind dabei im Flugzeugrumpf schlitzförmige Ausnehmungen mit 41 mm Breite vorgegebenThe shape of the aircraft interface is due to the currently introduced air-to-air guided missile of the type AMRAAM and was also specified for example with the prototypes of the Eurofighter EF 2000 in this form realized. For the rudders and wings of the AMRAAM are in the Airplane fuselage slot-shaped recesses with a width of 41 mm specified
Bei staustrahlgetriebenen AMRAAM Nachfolgeflugkörpern muß die Ruderlagerung außerhalb des Flugkörperrumpfes erfolgen, weil der Innenraum fast vollständig von der Staubrennkammer ausgefüllt wird. Dies führt im allgemeinen zu voluminösen Lagerungsprinzipien außerhalb der Flugkörper-Struktur, die daher nicht mit dem von AMRAAM vorgegebenen Flugzeuginterface kompatibel bleiben können.In the case of ramjet-driven AMRAAM follow-on missiles, the Oars are placed outside the fuselage because of the Interior is almost completely filled by the dust separation chamber. This generally leads to voluminous storage principles outside of the Missile structure, therefore, not with that specified by AMRAAM Airplane interface can remain compatible.
Dabei genügt es nämlich nicht, den Flugkörper berührungsfrei in die vorgegebenen 41 mm breiten Ausnehmungen des Flugzeugrumpfes einzubringen, es muß auch eine geforderte Mindest-Freigängigkeit von mehreren Millimetern an allen Stellen eingehalten werden.It is not enough for the missile to touch the predetermined 41 mm wide recesses of the fuselage to bring in, there must also be a required minimum clearance of several millimeters at all points.
Die Forderung nach austauschbaren staustrahlgetriebenen Flugkörpern am gleichen Flugzeuginterface ist dadurch bei herkömmlichen Lösungen in Frage gestellt. The demand for interchangeable ram-jet missiles on The same aircraft interface is therefore in question with conventional solutions posed.
Es ist das Ziel der Erfindung, eine Vorrichtung der eingangs genannten Gattung zu schaffen, die sowohl die erforderlichen räumlichen Bedingungen erfüllt als auch für die bei den auftretenden Marschgeschwindigkeiten von Mach 4 auftretenden mechanischen und thermischen Belastungen geeignet ist.It is the object of the invention to provide a device of the type mentioned Genus to create both the necessary spatial conditions fulfilled as well as for the marching speeds of Mach 4 occurring mechanical and thermal loads is suitable.
Diese Aufgabe wird durch die im kennzeichnenden Teil von Anspruch 1 genannten Merkmale gelöst. Weitere vorteilhafte Weiterbildungen und Einzelheiten der Erfindung ergeben sich aus den Unteransprüchen und der Zeichnung, in der ein Ausführungsbeispiel beschrieben wird. Es zeigen
- Fig. 1
- schematisch die erfindungsgemäße Anordnung in ihrem Umfeld,
- Fig. 2a und 2b
- Aufsicht und Teil-Schnitt durch die erfindungsgemäße Anordnung,
- Fig. 2c
- einen weiteren Teil-Schnitt durch die erfindungsgemäße Anordnung.
- Fig. 1
- schematically the arrangement according to the invention in its environment,
- 2a and 2b
- Top view and partial section through the arrangement according to the invention,
- Fig. 2c
- another partial section through the arrangement according to the invention.
Fig. 1 zeigt das Umfeld für den Gegenstand der Erfindung. In der Außenkontur des Flugkörperträgers F - im vorliegenden Fall der Rumpf bzw. die Tragflächen des Flugzeuges - ist eine Ausnehmung mit einer fest vorgegebenen Breite von 41 mm vorhanden, die für die Aufnahme des dem Flugzeug zugewandten Ruderblattes R eines einsatzbereiten Flugkörpers FK (AMRAAM) dient. Mit diesem Raum muß ein kompatibler Flugkörper auskommen.Fig. 1 shows the environment for the subject of the invention. In the Outer contour of the missile carrier F - in the present case the fuselage or the wings of the aircraft - is a recess with a fixed predetermined width of 41 mm available, which is for the inclusion of the Airplane-facing rudder blade R of a ready-to-use missile FK (AMRAAM) serves. With this space must be a compatible missile get along.
Fig. 2 zeigt das Konstruktionsprinzip der AMRAAM-kompatiblen Ruderlagerung für einen staustrahlgetriebenen Flugkörper nach der Erfindung. Fig. 2a zeigt dabei die vorgeschlagene Lösung mit Blick auf die Ruderachse W in Richtung des Flugkörpers FK. Fig. 2b zeigt einen Schnitt durch die Anordnung sowie den Biegelastverlauf BL durch die Hauptelemente Interface-Beschlag B und Ruderwelle W.Fig. 2 shows the construction principle of the AMRAAM-compatible Rudder support for a ramjet-powered missile after Invention. 2a shows the proposed solution with a view to the Rudder axis W in the direction of the missile FK. 2b shows a section through the arrangement and the bending load curve BL through the Main elements interface fitting B and rudder shaft W.
Der Interface-Beschlag B zur Befestigung an der dünnwandigen Staubrennkammer der Flugkörperzelle FK besitzt einen Außendurchmesser B2 der einerseits die Kompatibilität und Freigängigkeit sicherstellt und andererseits durch die kegelförmige Ausnehmung B3 im Querschnittsverlauf an die auftretende Biegebelastung, die durch die am Ruder angreifende Luftkraft Fq verursacht wird, angepaßt ist.The interface fitting B for fastening to the thin-walled Dust separation chamber of the FK missile cell has an outer diameter B2 which on the one hand ensures compatibility and freedom of movement and on the other hand through the conical recess B3 in the cross-sectional profile to the bending stress that occurs due to the one acting on the rudder Air force Fq is caused is adjusted.
Innerhalb der kegelförmigen Ausnehmung B3 des Beschlages wird die Ruderwelle W in Keramik-Nadellagern L aufgenommen. Der Querschnittsverlauf der Ruderwelle W ist durch Wahl der Lagerdurchmesser d1 (22 mm) und d2 (12 mm) ebenfalls dem Belastungsverlauf an der Ruderwelle W angepaßt. Die Ruderwelle W nimmt in einer schlitzförmigen Ausnehmung W4 das Ruder R auf, welches den zylindrischen Teil des Interface-Beschlages B2 wie in Fig. 2c dargestellt bis zur Wurzel umschließt.Within the conical recess B3 of the fitting, the Rudder shaft W in ceramic needle bearings L. The The cross-sectional profile of the rudder shaft W is due to the choice of the bearing diameter d1 (22 mm) and d2 (12 mm) also the load curve on the Rudder shaft W adapted. The rudder shaft W takes a slot-like shape Recess W4 the rudder R, which is the cylindrical part of the Interface fitting B2 encloses to the root as shown in Fig. 2c.
An der Beschlaginnenseite ist der Ruderantriebshebel H formschlüssig mit der Ruderwelle W verbunden. Der Ruderantriebshebel H wird, wie in der eingangs erwähnten Druckschrift erläutert, von einem elektromechanischen Stellsystem betätigt.The rudder drive lever H is form-fitting on the inside of the fitting the rudder shaft W connected. The rudder drive lever H is, as in the initially mentioned document explained by an electromechanical Actuating system actuated.
Die beschriebene Anordnung vereinigt mehrere Vorteile:
Die in der Marschflugphase des Flugkörpers aufgrund von aerodynamischer Aufheizung bei Geschwindigkeiten bis Mach 4 auftretende hohe thermische Belastung führt zu einer homogenen Aufheizung der Hauptkomponenten und ermöglicht daher eine kostengünstige und klassische Anordnung von Hochtemperatur-Keramiknadeln als Lagerelemente.The in the cruise phase of the missile due to aerodynamic Heating at speeds up to Mach 4 occurs high thermal Stress leads to a homogeneous heating of the main components and therefore enables an inexpensive and classic arrangement of High-temperature ceramic needles as bearing elements.
Die Ausbildung des Ruderinterface W4, also der Verbindung zwischen Ruder R und Ruderwelle W, ermöglicht eine einfache Herstellung und die schnelle Montierbarkeit des Ruderblattes mit Standardwerkzeug unter Gefechtsbedingungen.The formation of the rudder interface W4, i.e. the connection between the rudder R and rudder shaft W, enables easy manufacture and quick The rudder blade can be fitted using standard tools Battle conditions.
Das Ruderinterface liegt ferner nahe am Druckpunkt des Ruderblattes, daher ergeben sich an der Einspannstelle kleine Wurzelbiegemomente Ferner kann die Abdichtung des Flugkörpers nach außen im Bereich des Flugkörper-Interfacebeschlages B und des Ruderantriebshebels H einfach und perfekt erfolgen, da die Stelle der Relativbewegung am äußeren Ende des Interfacebeschlages liegt.The rudder interface is also close to the pressure point of the rudder blade, therefore there are small root bending moments at the clamping point Furthermore, the sealing of the missile to the outside in the area of Missile interface fitting B and the rudder drive lever H simple and done perfectly, since the position of the relative movement at the outer end of the Interface fitting is.
Claims (5)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19960738 | 1999-12-16 | ||
DE19960738A DE19960738C1 (en) | 1999-12-16 | 1999-12-16 | Rudder connection for guided missiles |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1108972A2 true EP1108972A2 (en) | 2001-06-20 |
EP1108972A3 EP1108972A3 (en) | 2003-11-19 |
EP1108972B1 EP1108972B1 (en) | 2007-03-21 |
Family
ID=7932920
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00126530A Expired - Lifetime EP1108972B1 (en) | 1999-12-16 | 2000-12-11 | Device for mounting a steering fin on a missile |
Country Status (5)
Country | Link |
---|---|
US (1) | US6398156B2 (en) |
EP (1) | EP1108972B1 (en) |
JP (1) | JP4560206B2 (en) |
DE (2) | DE19960738C1 (en) |
ES (1) | ES2280172T3 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016022183A1 (en) * | 2014-08-05 | 2016-02-11 | Raytheon Company | Air vehicle with control system mechanical coupler |
CN115031587A (en) * | 2022-05-30 | 2022-09-09 | 洛阳安怀达智能科技有限公司 | Aircraft rudder face locking mechanism |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10118216A1 (en) * | 2001-04-12 | 2002-10-17 | Diehl Munitionssysteme Gmbh | Rudder blade storage device for one floor |
US6474594B1 (en) * | 2001-05-11 | 2002-11-05 | Raytheon Company | Output shaft assembly for a missile control actuation unit |
EP3708482B1 (en) * | 2019-03-13 | 2023-06-07 | Becker Marine Systems GmbH | Rudder for watercraft with a bearing clearance measuring device, method for measuring bearing clearance in a rudder and a bearing clearance measuring device for a rudder |
CN113154955B (en) * | 2020-12-28 | 2022-12-27 | 航天科工火箭技术有限公司 | System and method for accurately controlling debris falling area of rocket separation body with stable spinning |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19635847C2 (en) | 1996-09-04 | 1998-07-16 | Daimler Benz Aerospace Ag | Guided missile with ramjet drive |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3223034A (en) * | 1964-05-06 | 1965-12-14 | Atlantic Res Corp | Rocket fin assembly |
SE331242B (en) * | 1969-05-14 | 1970-12-14 | Bofors Ab | |
DE2227103A1 (en) * | 1972-06-03 | 1973-12-13 | Dynamit Nobel Ag | FOLDING TAIL |
DE2227104C2 (en) * | 1972-06-03 | 1982-07-15 | Dynamit Nobel Ag, 5210 Troisdorf | Projectile or missile with a hinged tail unit |
US4327886A (en) * | 1972-11-30 | 1982-05-04 | The United States Of America As Represented By The Secretary Of The Navy | Integral rocket ramjet missile |
DE2264338A1 (en) * | 1972-12-30 | 1974-07-04 | Dynamit Nobel Ag | FOLD-OUT TAIL, ESPECIALLY FOR MISSILE |
US4568041A (en) * | 1984-03-19 | 1986-02-04 | The United States Of America As Represented By The Secretary Of The Navy | Fin attachment |
DE3441534A1 (en) * | 1984-11-14 | 1986-05-15 | Diehl GmbH & Co, 8500 Nürnberg | BEARING ARRANGEMENT FOR THE RUDDER BLADE OF AN AIRCRAFT |
JPH0424499A (en) * | 1990-05-17 | 1992-01-28 | Mitsubishi Heavy Ind Ltd | Missile |
DE4135557C2 (en) * | 1991-10-29 | 1999-05-06 | Diehl Stiftung & Co | Rudder control device |
JPH08210799A (en) * | 1995-02-02 | 1996-08-20 | Mitsubishi Heavy Ind Ltd | Direction and posture controlling device for airframe |
DE19827278A1 (en) * | 1998-06-19 | 1999-12-23 | Diehl Stiftung & Co | Steerable missile can be launched by thrust of propellant gas charge |
DE19827277B4 (en) * | 1998-06-19 | 2006-08-10 | Diehl Stiftung & Co.Kg | Bearing arrangement for the pivotable rudder blades of a steerable missile |
-
1999
- 1999-12-16 DE DE19960738A patent/DE19960738C1/en not_active Expired - Fee Related
-
2000
- 2000-12-11 ES ES00126530T patent/ES2280172T3/en not_active Expired - Lifetime
- 2000-12-11 EP EP00126530A patent/EP1108972B1/en not_active Expired - Lifetime
- 2000-12-11 DE DE50014181T patent/DE50014181D1/en not_active Expired - Lifetime
- 2000-12-12 US US09/735,163 patent/US6398156B2/en not_active Expired - Lifetime
- 2000-12-18 JP JP2000384410A patent/JP4560206B2/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19635847C2 (en) | 1996-09-04 | 1998-07-16 | Daimler Benz Aerospace Ag | Guided missile with ramjet drive |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016022183A1 (en) * | 2014-08-05 | 2016-02-11 | Raytheon Company | Air vehicle with control system mechanical coupler |
US9546853B2 (en) | 2014-08-05 | 2017-01-17 | Raytheon Company | Air vehicle with control system mechanical coupler |
CN115031587A (en) * | 2022-05-30 | 2022-09-09 | 洛阳安怀达智能科技有限公司 | Aircraft rudder face locking mechanism |
Also Published As
Publication number | Publication date |
---|---|
JP4560206B2 (en) | 2010-10-13 |
DE19960738C1 (en) | 2001-08-23 |
EP1108972B1 (en) | 2007-03-21 |
DE50014181D1 (en) | 2007-05-03 |
ES2280172T3 (en) | 2007-09-16 |
US20010030259A1 (en) | 2001-10-18 |
EP1108972A3 (en) | 2003-11-19 |
US6398156B2 (en) | 2002-06-04 |
JP2001174197A (en) | 2001-06-29 |
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