EP0838656B1 - Lenkflugkörper mit Staustrahlantrieb - Google Patents
Lenkflugkörper mit Staustrahlantrieb Download PDFInfo
- Publication number
- EP0838656B1 EP0838656B1 EP97114018A EP97114018A EP0838656B1 EP 0838656 B1 EP0838656 B1 EP 0838656B1 EP 97114018 A EP97114018 A EP 97114018A EP 97114018 A EP97114018 A EP 97114018A EP 0838656 B1 EP0838656 B1 EP 0838656B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- guided missile
- control surfaces
- axis
- articulated
- swivel
- 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
- F42B10/60—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 guided missile with ramjet drive according to the preamble of claim 1.
- a rudder control device for a missile in which a motor-driven spindle with a thread on the latter seated anti-rotation nut moves axially.
- a firm helm or the shaft connected lever is pivotally connected to the nut.
- the motor - including spindle and nut - is movably mounted around a pendulum axis. Consequently this results in low-friction kinematics with pure swivel movements in all Joints. Slot guides, scenery stars etc. can thus be omitted. With strong However, accelerations transverse to the spindle axis will adversely affect the spindle Bending stressed.
- Missiles are also known, in which missiles are placed on the outside of the cell contour Air inlets primarily for flow-related reasons in the form of trailing shafts up to are extended to the missile tail. If not otherwise, these trailing shafts can used to install elements of the rudder drive.
- the object of the invention is to provide a guided missile with ramjet create, whose rudder control system is optimally integrated into the cell and also in extreme mechanical and thermal conditions the specified requirements, e.g. in terms of positioning accuracy and positioning speed, fully met.
- the four drive units with linear adjustment movement for the four rudders are locally concentrated arranged in pairs in the two trailing shafts, the double Offset - in the longitudinal and circumferential direction of the missile - additional spatial Brings advantages. Sufficiently large / powerful drives can therefore be used, which are not in the cell itself must be integrated.
- the linkage for the two lower oars each consisting of a coupling rod with two Joints - like the drive units - are also fully integrated in the trailing shafts.
- the rods for the two upper oars consist of two articulated ones Elements, namely a pivoted double lever and a coupling rod with spatially movable joints. They lead out of the trailing shafts and are up to towards the oars of spatial, i.w. adapted cylindrical cell contour.
- Preferred embodiments of the guided missile according to are in the dependent claims 2 to 8 marked the main claim.
- Fig. 1 shows a guided missile 1 with ramjet in perspective View looking obliquely from the left and from above.
- an orthogonal axis cross is shown, in which the Longitudinal axis with X, the transverse axis with Y and the vertical axis with Z are. In terms of flight mechanics, this would be the roll axis (X), the pitch axis (Y) and the yaw axis (Z).
- cell 2 of the guided missile 1 has a largely circular cylindrical shape, the diameter something varies locally.
- Fig. 2 shows i.w. the drive kinematics of the lower left oar 14 in the direction of view from its pivot axis R2.
- the lower right rudder 13 and that left upper rudder 11 with their common pivot axis R1 are - with Break lines to the outside areas - seen in side view, as well the horizontally arranged cell 2.
- the trailing shaft 8 is cut open graphically, so that its inside is visible.
- the drive unit 16 of the rudder 14 is in shape of a brushless DC electric motor with roller spindle drive 18.
- the drive unit 17 of the rudder 11 is relative to the unit 16 both in the longitudinal direction displaced and lies in the circumferential direction of the guided missile 1 closer to the rudder axis plane (R1, R2).
- the rudder 14 points - here vertically below its pivot axis R2 - a linkage pivot point A2.
- Between this and the nut 20 of the roller spindle drive 18 is one on train and pressure-resistant coupling rod 23 as a kinematic connecting link inserted.
- This has fork-like joint ends 24, 25, which the mother 20 and grasp the rudder lever and are articulated to it.
- There the hinge axes G1, G2 and the rudder pivot axis R2 are parallel here, joints with one degree of freedom, i.e. with swiveling by one Axis.
- Fig. 3 shows i.w. the drive kinematics of the upper left oar 11 in the direction of view its pivot axis R1.
- the lower left rudder 14 and the right upper rudders 12 with their common pivot axis R2 are - break lines too the radially outer areas - seen in side view, as well as the horizontally arranged cell 2.
- the latter is cut open in the upper image area shown, the flow channel of the engine in the wall Area can be seen.
- the reference number 3 points approximately in the area of downstream dust chamber end, reference numeral 5 in the area of the nozzle neck and the reference number 4 in the area of the thrust nozzle, more precisely said in their exit cross section.
- the outer Cell wall has a circumferential constriction in the area of the nozzle neck 5, in which at least parts of the rudder bearing and the rudder linkage are accommodated.
- the inside of the trailing shaft 8 is visible again shown, but from a direction different from FIG. 2 by 90 °.
- the drive unit 16 for the rudder 14 is visible again shown, but from a direction different from FIG. 2 by 90 °.
- the drive unit 17 follows further to the right at the same height of the rudder 11 - in view - with their roller spindle drive 19 inclusive his mother 21.
- the linkage pivot point of the rudder 11 is designated A1.
- the actuating force or actuating movement is transmitted by the mother 21 on the double lever 26 pivotable about a fixed axis and on via a coupling rod 29 articulated to the latter to the point A1. Because the rudder pivot axis R1 and the pivot axis of the double lever 26 are neither parallel nor intersect, the coupling rod 29 is with two spatially movable ball joints.
- the kinematic arrangement resembles a so-called Watts linkage, with geometric Adaptation (lengths, angles, axis positions) almost complete linearity between the entrance and exit movement.
- Fig. 4 shows in addition to Fig. 3 shows a cross section through the cell 2 in the Swivel axis plane (R1, R2) of rudder 11 to 14, the course of the cut partially follows the linkage of the upper left oar 11.
- the right one Trailing shaft 9 is thus cut in the R1-R2 level, the left trailing shaft 8 in a further lying level in the area of the double lever 26 and the mother 21.
- the rudder 11 is - like the rudder 12 - in one backlash-free bearing 15, here a four-point deep groove ball bearing to its Swivel axis rotatably guided. Its linkage point A1 coincides with the center M3 of the ball joint 30, which with the coupling rod 29 is connected.
- the double-lever ball joint has the in this view same center position M3 and is not visible. However, one sees in Cut the double lever 26, its pivot bearing 28 with pivot axis S and its lower, forked end 27.
- the latter encompasses the nut 21 of the roller spindle drive 19 and is articulated to it.
- the center of the mother 21 is designated here with M1.
- Hinge pins 22 are fastened to the nut 21, which should be rotatably mounted in sliding blocks, the latter in the two legs of the forked end 27 of the double lever 26 can be displaced to a limited extent should be led.
- the nut 21 is to be secured against rotation separately his. This scenery guide is necessary in order to with transition from linear movement to swivel movement - harmful Avoid coercive forces. In the given drawing scale is one However, rendering these details does not make sense due to the lack of recognizability. the The constructive implementation is already familiar to a person skilled in the art.
- the hinge axis given by the hinge pin 22 is designated G3.
- This and the pivot axis S of the double lever 26 are parallel to Avoid constraining forces and deformation in the fork area.
- the centers M1 to M3 lie on a line L, which is within or approximately on Edge of the material cross section of the double lever 26 runs. The so achieved Power flow only leads to minimal local torsional loads in the double lever 26, which increases the rigidity of the transmission kinematics.
- the boundary line B extending from the rudder 12 to the area of the rudder 14 reproduces the contour specified by the starting device to which the Missile outer contour - with the exception of Rudder 11 - a certain everywhere Keep a distance, from which the rudder linkage to the rudder 11 is affected.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Transmission Devices (AREA)
Description
- Fig. 1
- eine perspektivische Ansicht eines Lenkflugkörpers,
- Fig. 2
- eine seitliche Teilansicht eines Flugkörperhecks in Achsrichtung eines unteren Ruders mit Einblick in einen Nachlaufschacht,
- Fig. 3
- eine vergleichbare Teilansicht in Achsrichtung eines oberen Ruders,
- Fig. 4
- einen Querschnitt durch einen Flugkörper im Bereich der Ruder mit Blickrichtung von hinten.
Claims (8)
- Lenkflugkörper mit Staustrahlantrieb, insbesondere für militärische Einsätze, mit einem den Querschnitt seiner Zelle weitgehend bis vollständig ausfüllenden Triebwerk, mit zwei außenseitig auf die Zellenkontur aufgesetzten Lufteinläufen im unteren Zellenbereich, welche mit Nachlaufschächten bis zum Flugkörperheck verlängert sind, mit einer starren Flügelanordnung im mittleren bis vorderen Flugkörperbereich und mit einem Heckleitwerk aus vier radial, vorzugsweise in Form eines rechtwinkeligen Diagonalkreuzes angeordneten separat schwenkbaren Rudern, wobei die Schäfte der beiden unteren Ruder in das Innere der Nachlaufschächte führen und zu jedem Ruder eine Antriebseinheit mit linearer Stellbewegung vorhanden ist und jedes Ruder einen zu seiner Schwenkachse beabstandeten Gestängeanlenkpunkt aufweist, dadurch gekennzeichnet,a) daß in jedem der beiden Nachlaufschächte (8, 9) zwei der vier Antriebs-einheiten (16, 17) in Längs- und Umfangsrichtung des Lenkflugkörpers (1) zueinander versetzt mit längsorientierter Bewegungsrichtung angeordnet sind,b) daß die kinematische Verbindung von der Antriebseinheit (16) zum Gestängeanlenkpunkt (A2) jedes der beiden unteren Ruder (13, 14) eine Koppelstange (23) mit je einem Schwenk- oder Kugelgelenk an beiden Enden (Gelenkende 24, 25) bildet,c) und daß die kinematische Verbindung von der Antriebseinheit (17) zum Gestängegelenkpunkt (A1) jedes der beiden oberen Ruder (11, 12) einen um eine Achse (S) schwenkbaren Doppelhebel (26) und eine Koppelstange (29) mit je einem Kugelgelenk (30) an beiden Enden bilden.
- Lenkflugkörper nach Anspruch 1, dadurch gekennzeichnet, daß die Antriebseinheiten (16, 17) als elektromechanische Motor-Getriebe-Einheiten ausgeführt sind, vorzugsweise als bürstenlose Gleichstrommotoren mit Rollenspindeltrieben (18, 19).
- Lenkflugkörper nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die beiden Antriebseinheiten (16) für die unteren Ruder (13, 14) vor den beiden Antriebseinheiten (17) für die oberen Ruder (11, 12), d.h. in größerem Abstand vor der von den Ruderschwenkachsen (R1, R2) aufgespannten Ebene, angeordnet sind, und daß die Rudergestänge für die unteren Ruder (13, 14) (je eine Koppelstange 23) hinsichtlich ihrer Steifigkeit, d.h.hinsichtlich ihrer Kraft-Verformungs-Charakteristik, an die Rudergestänge für die oberen Ruder (11, 12) (je ein Doppelhebel 26 und eine Koppelstange 29) angepaßt sind.
- Lenkflugkörper nach einem oder mehreren der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Koppelstangen (23) für die unteren Ruder (13, 14) mit gabelkopfartigen Gelenkenden (24, 25) mit parallelen Gelenkachsen (G1, G2) versehen sind.
- Lenkflugkörper nach einem oder mehreren der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß jeder Doppelhebel (26) der Gestänge für die oberen Ruder (11, 12) jeweils mit einem gegabelten Ende (27) die Mutter (21) eines Rollenspindeltriebes (19) umgreift und an der Mutter (21) befestigte Gelenkzapfen (22) in langlochförmigen Kulissen mit Kulissensteinen aufnimmt, wobei die Mutter (21) selbst verdrehgesichert ist.
- Lenkflugkörper nach einem oder mehreren der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß bei jedem Doppelhebel (26) seine Schwenkachse (S) und die Gelenkachse (G3) durch die Mutter (21) des Rollenspindeltriebes (19), d.h. die Achse durch die Mitte der Gelenkzapfen (22), parallel stehen.
- Lenkflugkörper nach einem oder mehreren der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß bei jedem Doppelhebel (26) der Schnittpunkt (M1) der Gelenkachse (G3) durch die Mutter (21) des Rollenspindeltriebes (19) mit der Spindelachse des Rollenspindeltriebes (19), der radiale und axiale Mittelpunkt (M2) seines Schwenklagers (28) und der Mittelpunkt (M3) des koppelstangenseitigen Kugelgelenkes (30) auf einer Linie (L) liegen.
- Lenkflugkörper nach einem oder mehreren der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß zumindest der Großteil der Schwenk- und Gelenklager (15, 28, 30) der Rudergestänge und Ruder (11 bis 14) als Wälzlager ausgeführt sind.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19635847A DE19635847C2 (de) | 1996-09-04 | 1996-09-04 | Lenkflugkörper mit Staustrahlantrieb |
DE19635847 | 1996-09-04 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0838656A2 EP0838656A2 (de) | 1998-04-29 |
EP0838656A3 EP0838656A3 (de) | 2000-01-19 |
EP0838656B1 true EP0838656B1 (de) | 2002-02-13 |
Family
ID=7804584
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97114018A Expired - Lifetime EP0838656B1 (de) | 1996-09-04 | 1997-08-14 | Lenkflugkörper mit Staustrahlantrieb |
Country Status (3)
Country | Link |
---|---|
US (1) | US5904319A (de) |
EP (1) | EP0838656B1 (de) |
DE (2) | DE19635847C2 (de) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6250584B1 (en) | 1999-10-18 | 2001-06-26 | Hr Textron, Inc. | Missile fin locking mechanism |
DE19960738C1 (de) | 1999-12-16 | 2001-08-23 | Lfk Gmbh | Ruderanbindung für Lenkflugkörper |
DE10007120B4 (de) * | 2000-02-17 | 2007-04-12 | LFK Lenkflugkörpersysteme GmbH | Stromregelung permanenterregter Synchronmotoren für Lenkflugkörper mit elektromechanischem Ruderstellantrieb |
DE10149087B4 (de) * | 2000-10-07 | 2008-04-03 | Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh | Ruderblattansteuerung für Flugkörper |
SE521445C2 (sv) * | 2001-03-20 | 2003-11-04 | Bofors Defence Ab | Sätt att synkronisera fenutfällningen vid en fenstabiliserad artillerigranat samt en i enlighet därmed utformad artillerigranat |
US6948685B2 (en) | 2003-10-27 | 2005-09-27 | Hr Textron, Inc. | Locking device with solenoid release pin |
US7410120B2 (en) * | 2005-01-21 | 2008-08-12 | The Boeing Company | Control surface assemblies with torque tube base |
US7195197B2 (en) * | 2005-02-11 | 2007-03-27 | Hr Textron, Inc. | Techniques for controlling a fin with unlimited adjustment and no backlash |
IL167721A (en) * | 2005-03-29 | 2008-06-05 | Israel Aerospace Ind Ltd | Steering system and method for guided flying apparatus |
DE102009007731A1 (de) * | 2009-02-05 | 2010-08-19 | Lfk-Lenkflugkörpersysteme Gmbh | Flugabbruchvorrichtung für einen Flugkörper |
EP2556327B1 (de) | 2010-04-07 | 2016-06-08 | BAE Systems Information and Electronic Systems Integration Inc. | Flügelspaltdichtung |
US8530809B2 (en) | 2011-08-03 | 2013-09-10 | Raytheon Company | Ring gear control actuation system for air-breathing rocket motors |
DE102015005135A1 (de) | 2015-04-22 | 2016-10-27 | Diehl Bgt Defence Gmbh & Co. Kg | Flugkörperrudersystem |
US11340052B2 (en) | 2019-08-27 | 2022-05-24 | Bae Systems Information And Electronic Systems Integration Inc. | Wing deployment initiator and locking mechanism |
US11852211B2 (en) | 2020-09-10 | 2023-12-26 | Bae Systems Information And Electronic Systems Integration Inc. | Additively manufactured elliptical bifurcating torsion spring |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3154015A (en) * | 1962-09-19 | 1964-10-27 | Martin Marietta Corp | Missile flight control system |
US3373955A (en) * | 1964-05-25 | 1968-03-19 | Huska Paul | Pitch and yaw actuator assembly for vehicle guidance surfaces |
US5393011A (en) * | 1965-12-03 | 1995-02-28 | Shorts Missile Systems Limited | Control systems for moving bodies |
US4327885A (en) * | 1971-10-06 | 1982-05-04 | The United States Of America As Represented By The Secretary Of The Navy | Thrust augmented rocket |
US3901028A (en) * | 1972-09-13 | 1975-08-26 | Us Air Force | Ramjet with integrated rocket boost motor |
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 |
US4417441A (en) * | 1979-03-29 | 1983-11-29 | Messerschmitt-Bokow-Blohm Gesellschaft mit beschrankter Haftung | Ram jet engine |
US4369940A (en) * | 1979-12-17 | 1983-01-25 | Mcdonnell Douglas Corporation | Airbreathing propulsion system for supersonic vehicles |
US4560121A (en) * | 1983-05-17 | 1985-12-24 | The Garrett Corporation | Stabilization of automotive vehicle |
US4655420A (en) * | 1983-06-09 | 1987-04-07 | The United States Of America As Represented By The Secretary Of The Air Force | Low height fin control actuator |
DE3441534A1 (de) * | 1984-11-14 | 1986-05-15 | Diehl GmbH & Co, 8500 Nürnberg | Lageranordnung fuer das ruderblatt eines flugkoerpers |
DE3441533A1 (de) * | 1984-11-14 | 1986-05-15 | Diehl GmbH & Co, 8500 Nürnberg | Kopplungseinrichtung zwischen einem linear-stellglied und einem schwenkelement, insbesondere einem steuerruder |
FR2629136B1 (fr) * | 1985-09-17 | 1990-11-09 | Aerospatiale | Statoreacteur pourvu d'une pluralite de manches d'alimentation en air carbure et missile pourvu d'un tel statoreacteur |
FR2631387B1 (fr) * | 1988-05-10 | 1990-07-13 | Poudres & Explosifs Ste Nale | Propulseur sans tuyere de faible allongement |
JPH03199198A (ja) * | 1989-12-28 | 1991-08-30 | Shin Etsu Chem Co Ltd | ランタンガレート単結晶およびその製造方法 |
DE4135557C2 (de) * | 1991-10-29 | 1999-05-06 | Diehl Stiftung & Co | Ruderstelleinrichtung |
DE4325218C2 (de) * | 1993-07-28 | 1998-10-22 | Diehl Stiftung & Co | Artillerie-Rakete und Verfahren zur Leistungssteigerung einer Artillerie-Rakete |
US5505408A (en) * | 1993-10-19 | 1996-04-09 | Versatron Corporation | Differential yoke-aerofin thrust vector control system |
-
1996
- 1996-09-04 DE DE19635847A patent/DE19635847C2/de not_active Expired - Fee Related
-
1997
- 1997-08-14 DE DE59706370T patent/DE59706370D1/de not_active Expired - Lifetime
- 1997-08-14 EP EP97114018A patent/EP0838656B1/de not_active Expired - Lifetime
- 1997-08-28 US US08/919,982 patent/US5904319A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
EP0838656A3 (de) | 2000-01-19 |
DE59706370D1 (de) | 2002-03-21 |
EP0838656A2 (de) | 1998-04-29 |
DE19635847C2 (de) | 1998-07-16 |
US5904319A (en) | 1999-05-18 |
DE19635847A1 (de) | 1998-03-12 |
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