EP1054231A2 - Actuation system for an aerodynamic control surface of an air vehicle - Google Patents

Actuation system for an aerodynamic control surface of an air vehicle Download PDF

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Publication number
EP1054231A2
EP1054231A2 EP00110018A EP00110018A EP1054231A2 EP 1054231 A2 EP1054231 A2 EP 1054231A2 EP 00110018 A EP00110018 A EP 00110018A EP 00110018 A EP00110018 A EP 00110018A EP 1054231 A2 EP1054231 A2 EP 1054231A2
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EP
European Patent Office
Prior art keywords
actuating device
carrier housing
servomotors
missile
motor shaft
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
Application number
EP00110018A
Other languages
German (de)
French (fr)
Other versions
EP1054231B1 (en
EP1054231A3 (en
Inventor
Werner Dipl.-Ing. Schröppel
Josef Dipl.-Ing. Dommer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Diehl BGT Defence GmbH and Co KG
Original Assignee
Diehl Munitionssysteme GmbH and Co KG
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Publication of EP1054231A2 publication Critical patent/EP1054231A2/en
Publication of EP1054231A3 publication Critical patent/EP1054231A3/en
Application granted granted Critical
Publication of EP1054231B1 publication Critical patent/EP1054231B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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 an adjusting device for rudders of a missile, the rudders of servomotors over Adjustable thrust spindles and the servomotors in one arranged in the missile tail carrier housing are.
  • Such an actuator is in the DE 43 35 785 A1 described.
  • the servomotors are there provided with their own housings and on the carrier housing swinging. This structure demands one comparatively large installation space.
  • Another control device for rudder one Steerable projectile is in DE 34 41 533 C2 described.
  • a bearing arrangement for the swiveling rudder blade a steerable missile in particular a means Propellant gas pressure of the closable floor known from DE 34 41 534 A1.
  • the object of the invention is to provide an actuator type mentioned with a particularly compact structure to propose.
  • the above object is achieved in that the Stators of the motors directly in the carrier housing are arranged and that the push spindle in one Internal thread of the motor shaft engages.
  • the stators of the servomotors in the carrier housing are built in, there is no need for own Motor housing, which saves space and one Weight reduction means. Even in a cramped one Missile tail can use two actuators with parallel Axes can be installed side by side. So it's not necessary, the servomotors are staggered in the longitudinal direction Arrange rear, which would increase the overall length.
  • the an actuator is used to adjust a pair of oars.
  • the other servomotor is used to adjust the other Oars.
  • a small overall length is also possible because of the Engage thrust spindles in the internal thread of the motor shafts.
  • the compact design is with a weight reduction connected.
  • the extremely small and light Actuator is particularly suitable for a a propellant-projectile projectile (mortar projectile), has the rudder.
  • the carrier housing is like this designed, that it is arranged in the rear area, the Rear area of the projectile against radial forces, in particular gayak forces.
  • the carrier housing is like this designed, that it is arranged in the rear area, the Rear area of the projectile against radial forces, in particular gayak forces.
  • One is sufficient reduced wall thickness of the rear area, resulting in a Weight saving and an installation space with enlarged Inner diameter is allowed.
  • the inner ring and the outer ring support one the motor shaft bearing bearing at one Launch acceleration of the missile in the carrier housing from.
  • the carrier housing Disc is preferably one in the carrier housing Disc provided.
  • a projectile that can be fired with a propellant (Mortar level) carries a pair of oars in the rear area 1 Oars 2 and a pair of oars with oars 3.
  • Oars 2,3 can be folded out about axes A (see Fig. 4 with Fig. 1) and by means of an adjusting device around rudder axes B swiveling.
  • the actuating device has a carrier housing 4, which is used in the rear area 1.
  • the dimensionally stable carrier housing 4 supports the rear area 1 radially from the longitudinal axis F of the floor and thereby increases Radial pressure forces are created, so that the Wall thickness of the rear area 1 where it from Support housing 4 is supported to be smaller than usual can. This increases the usable space inside the Rear area 1.
  • the motors 5,6 are side by side (cf. Fig. 3,4). Their motor shafts run parallel to one another. Both motors 5,6 have the same structure and the same Way connected to the assigned pair of oars. in the For simplification, the following is just one engine and described its coupling to its rudder pair. For the same applies to other motors.
  • the motor is brushless and houseless. His stator 7 is inserted directly into the carrier housing 4, for example glued. Its rotor 8 sits on the Motor shaft 9.
  • the motor shaft 9 is at both ends by means of Carrier housing 4 roller bearings 10 used, for example angular contact ball bearings.
  • roller bearings 10 used, for example angular contact ball bearings.
  • the bearing there is a disk 11 in the rear-side roller bearing 10 intended.
  • the outer ring 12 of the Rolling bearing 10 on.
  • the Disc 11 a step 40 with regard to the rolling bearing 10 precisely defined game between inner ring 13 and Outer ring 12 on.
  • the inner ring 13 of the roller bearing 10 on the disc 11 on which the outer ring 12 stands.
  • the axial force acting on the roller bearing 10 limited so that the rolling bearing 10 does not destroy becomes.
  • the inner ring 13 of the deformed elastically by the launch acceleration Bearing back from the disc 11 so that the inner ring 13th free is.
  • the Motor shaft 9 has an internal thread 14 into which an axial Movable push spindle 15 secured against twisting engages with an external thread 16.
  • an engagement nut 18 with one attached to the axis B of the one oar pair Driving lever 19 is coupled.
  • the Adjustment position is by means of a counter screw 20 definable.
  • the specified actuating device is small and comparatively easy. Few moving parts are sufficient for a smooth-running gear train.
  • an arm 21 is attached to the an actuator 22 of a linear potentiometer 23 attacks.
  • the linear potentiometer 23 is connected to one in the room 24 arranged control electronics connected.
  • the Linear potentiometer 23 is in a recess 25 (cf. 3) the carrier housing 4 is arranged.
  • About the Linear potentiometer 23 becomes the actual position of the control electronics of the respective oar pair reported.
  • Linear potentiometers can also take other measures Detection of the actual position of the rudder may be provided.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

The control surface is displaced by servomotors via thrust spindles. The servomotors are arranged in a carrier housing in th missile. The stators (7) of the servomotors (5,6) are arranged directly on the carrier housing (4). The thrust spindles (15) eng with the internal thread of the motor shaft (9). The internal thread lies within a roller bearing of the motor shaft. The roller bearing (10) comprises an inner ring (13) and an outer ring (12) which rest in the carrier housing during the launching accelera of the missile.

Description

Die Erfindung betrifft eine Stelleinrichtung für Ruder eines Flugkörpers, wobei die Ruder von Stellmotoren über Schubspindeln verstellbar und die Stellmotoren in einem im Flugkörperheck angeordneten Trägergehäuse angeordnet sind.The invention relates to an adjusting device for rudders of a missile, the rudders of servomotors over Adjustable thrust spindles and the servomotors in one arranged in the missile tail carrier housing are.

Eine derartige Stelleinrichtung ist in der DE 43 35 785 A1 beschrieben. Dort sind die Stellmotoren mit eigenen Gehäusen versehen und am Trägergehäuse pendelnd gelagert. Dieser Aufbau beansprucht einen vergleichsweise großen Bauraum.Such an actuator is in the DE 43 35 785 A1 described. The servomotors are there provided with their own housings and on the carrier housing swinging. This structure demands one comparatively large installation space.

Eine weitere Stelleinrichtung für Steuerruder eines lenkbaren Geschosses ist in der DE 34 41 533 C2 beschrieben. Dort ist eine vorteilhafte Kopplungseinrichtung zwischen dem Steuerruder und einem Linear-Stellglied angegeben. Diese läßt sich mittels einer Justiereinrichtung voreinstellen.Another control device for rudder one Steerable projectile is in DE 34 41 533 C2 described. There is an advantageous one Coupling device between the rudder and a Linear actuator specified. This can be done using preset an adjustment device.

Eine Lageranordnung für das verschwenkbare Ruderblatt eines lenkbaren Flugkörpers, insbesondere eines mittels Treibladungs-Gasdruckes verschießbaren Geschosses, ist aus der DE 34 41 534 A1 bekannt.A bearing arrangement for the swiveling rudder blade a steerable missile, in particular a means Propellant gas pressure of the closable floor known from DE 34 41 534 A1.

Aufgabe der Erfindung ist es, eine Stelleinrichtung der eingangs genannten Art mit besonders kompaktem Aufbau vorzuschlagen. The object of the invention is to provide an actuator type mentioned with a particularly compact structure to propose.

Erfindungsgemäß ist obige Aufgabe dadurch gelöst, daß die Statoren der Motoren unmittelbar im Trägergehäuse angeordnet sind und daß die Schubspindel in ein Innengewinde der Motorwelle eingreift.According to the invention, the above object is achieved in that the Stators of the motors directly in the carrier housing are arranged and that the push spindle in one Internal thread of the motor shaft engages.

Da die Statoren der Stellmotoren in das Trägergehäuse selbst eingebaut sind, erübrigen sich eigene Motorengehäuse, was eine Platzersparnis und eine Gewichtsreduzierung bedeutet. Auch in ein beengtes Flugkörperheck können zwei Stellmotoren mit parallelen Achsen nebeneinander eingebaut werden. Es ist also nicht nötig, die Stellmotoren in Längsrichtung gestaffelt im Heck anzuordnen, was die Baulänge vergrößern würde. Der eine Stellmotor dient zur Verstellung eines Ruderpaares. Der andere Stellmotor dient der Verstellung des anderen Ruderpaares.As the stators of the servomotors in the carrier housing are built in, there is no need for own Motor housing, which saves space and one Weight reduction means. Even in a cramped one Missile tail can use two actuators with parallel Axes can be installed side by side. So it's not necessary, the servomotors are staggered in the longitudinal direction Arrange rear, which would increase the overall length. The an actuator is used to adjust a pair of oars. The other servomotor is used to adjust the other Oars.

Eine kleine Baulänge ist auch ermöglicht, weil die Schubspindeln in Innengewinde der Motorwellen eingreifen. Die kompakte Bauweise ist mit einer Gewichtsreduzierung verbunden. Die extrem klein bauende und leichte Stelleinrichtung eignet sich insbesondere für ein mit einer Treibladung verschießbares Geschoß (Mörsergeschoß), das Steuerruder aufweist.A small overall length is also possible because of the Engage thrust spindles in the internal thread of the motor shafts. The compact design is with a weight reduction connected. The extremely small and light Actuator is particularly suitable for a a propellant-projectile projectile (mortar projectile), has the rudder.

Eine kurze Baulänge der Stelleinrichtung wird dadurch unterstützt, dag das Innengewinde, in das die Schubspindel eingreift, innerhalb eines die Motorwelle lagernden Wälzlagers liegt.This results in a short overall length of the actuating device supports, dag the internal thread into which the Thrust spindle engages within a motor shaft bearing bearing is located.

In Ausgestaltung der Erfindung ist das Trägergehäuse so gestaltet, dag es im Heckbereich angeordnet, den Heckbereich des Geschosses gegen radiale Kräfte, insbesondere Gadruckkräfte, abstützt. Dadurch genügt eine verringerte Wandstärke des Heckbereichs, wodurch eine Gewichtsersparnis und ein Einbauraum mit vergrößertem Innendurchmesser ermöglicht ist. In an embodiment of the invention, the carrier housing is like this designed, that it is arranged in the rear area, the Rear area of the projectile against radial forces, in particular gadruck forces. One is sufficient reduced wall thickness of the rear area, resulting in a Weight saving and an installation space with enlarged Inner diameter is allowed.

Um die Stelleinrichtung besonders beschleunigungsfest zu machen, stützt sich der Innenring und der Außenring eines die Motorwelle lagernden Wälzlagers bei einer Abschußbeschleunigung des Flugkörpers im Trägergehäuse ab. Vorzugsweise ist hierfür im Trägergehäuse eine Scheibe vorgesehen.To make the actuating device particularly resistant to acceleration make, the inner ring and the outer ring support one the motor shaft bearing bearing at one Launch acceleration of the missile in the carrier housing from. For this there is preferably one in the carrier housing Disc provided.

Unempfindlich gegen Beschleunigungen ist die Stelleinrichtung auch dadurch, dag der Motor ein bürstenloser Motor ist.It is insensitive to accelerations Actuator also by dag the engine is brushless motor.

Weitere vorteilhafte Ausgestaltungen der Erfindung ergeben sich aus den Unteransprüchen und der folgenden Beschreibung eines Ausführungsbeispiels. In der Zeichnung zeigen:

  • Figur 1 eine Stelleinrichtung im Heck eines Geschosses im Längsschnitt,
  • Figur 2 eine schematische Darstellung des Getriebezugs der Stelleinrichtung,
  • Figur 3 einen Querschnitt der Stelleinrichtung und
  • Figur 4 einen weiteren Längsschnitt.
    • Further advantageous refinements of the invention result from the subclaims and the following description of an exemplary embodiment. The drawing shows:
  • 1 shows an adjusting device in the rear of a projectile in longitudinal section,
  • FIG. 2 shows a schematic illustration of the gear train of the actuating device,
  • Figure 3 shows a cross section of the actuator and
  • Figure 4 shows another longitudinal section.

    • Ein mittels einer Treibladung verschießbares Geschoß (Mörsergeschoß) trägt im Heckbereich 1 ein Ruderpaar mit Rudern 2 und ein Ruderpaar mit Rudern 3. Die Ruder 2,3 sind um Achsen A ausklappbar (vgl. Fig.4 mit Fig.1) und mittels einer Stelleinrichtung um Ruderachsen B schwenkbar.A projectile that can be fired with a propellant (Mortar level) carries a pair of oars in the rear area 1 Oars 2 and a pair of oars with oars 3. Oars 2,3 can be folded out about axes A (see Fig. 4 with Fig. 1) and by means of an adjusting device around rudder axes B swiveling.

    Die Stelleinrichtung weist ein Trägergehäuse 4 auf, welches in den Heckbereich 1 eingesetzt ist. Das formstabile Trägergehäuse 4 stützt den Heckbereich 1 radial zur Geschoßlängsachse F ab und nimmt dabei beim Abschuß entstehende radiale Druckkräfte auf, so daß die Wandstärke des Heckbereichs 1 dort, wo er vom Trägergehäuse 4 gestützt ist, kleiner als sonst sein kann. Dies vergrößert den nutzbaren Bauraum im Innern des Heckbereichs 1. In dem Trägergehäuse 4 sind ein Stellmotor 5 zur Verstellung des einen Ruderpaars und ein Stellmotor 6 zur Verstellung des anderen Ruderpaars vorgesehen. Die Motoren 5,6 liegen nebeneinander (vgl. Fig.3,4). Ihre Motorwellen verlaufen parallel zueinander. Beide Motoren 5,6 sind gleich aufgebaut und in gleicher Weise mit dem zugeordneten Ruderpaar verbunden. Im folgenden ist zur Vereinfachung nur der eine Motor und dessen Ankopplung an sein Ruderpaar beschrieben. Für den anderen Motor gilt entsprechendes.The actuating device has a carrier housing 4, which is used in the rear area 1. The dimensionally stable carrier housing 4 supports the rear area 1 radially from the longitudinal axis F of the floor and thereby increases Radial pressure forces are created, so that the Wall thickness of the rear area 1 where it from Support housing 4 is supported to be smaller than usual can. This increases the usable space inside the Rear area 1. In the carrier housing 4 are a Actuator 5 for adjusting the one oar pair and a Actuator 6 for adjusting the other rudder pair intended. The motors 5,6 are side by side (cf. Fig. 3,4). Their motor shafts run parallel to one another. Both motors 5,6 have the same structure and the same Way connected to the assigned pair of oars. in the For simplification, the following is just one engine and described its coupling to its rudder pair. For the the same applies to other motors.

    Der Motor ist bürstenlos und gehäuselos. Sein Stator 7 ist unmittelbar in das Trägergehäuse 4 eingesetzt, beispielsweise eingeklebt. Sein Rotor 8 sitzt auf der Motorwelle 9.The motor is brushless and houseless. His stator 7 is inserted directly into the carrier housing 4, for example glued. Its rotor 8 sits on the Motor shaft 9.

    Die Motorwelle 9 ist beidendig mittels in das Trägergehäuse 4 eingesetzten Wälzlagern 10, beispielsweise Schrägkugellagern, gelagert. Um zu verhindern, daß durch die bei der Abschußbeschleunigung auftretenden Axialkräfte das tragende Wälzlager zerstört wird, ist beim heckseitigen Wälzlager 10 eine Scheibe 11 vorgesehen. An dieser liegt der Außenring 12 des Wälzlagers 10 an. Im Bereich des Innenrings 13 weist die Scheibe 11 eine Stufe 40 mit im Hinblick auf das Wälzlager 10 genau definiertem Spiel zwischen Innenring 13 und Außenring 12 auf. Bei der Abschußbeschleunigung, vor Überschreiten der für das Wälzlager 10 zulässigen Axialkraft, setzt sich der Innenring 13 des Wälzlagers 10 auf die Scheibe 11, auf der der Außenring 12 aufsteht. Dadurch wird die auf das Wälzlager 10 wirkende Axialkraft derart begrenzt, daß das Wälzlager 10 nicht zerstört wird. Nach dem Abschuß löst sich der Innenring 13 des durch die Abschußbeschleunigung elastisch verformten Lagers wieder von der Scheibe 11, so daß der Innenring 13 frei ist.The motor shaft 9 is at both ends by means of Carrier housing 4 roller bearings 10 used, for example angular contact ball bearings. In order to prevent by accelerating the launch occurring axial forces destroyed the bearing there is a disk 11 in the rear-side roller bearing 10 intended. At this, the outer ring 12 of the Rolling bearing 10 on. In the area of the inner ring 13, the Disc 11 a step 40 with regard to the rolling bearing 10 precisely defined game between inner ring 13 and Outer ring 12 on. At the launch acceleration, before Exceeding the permissible for the rolling bearing 10 Axial force, the inner ring 13 of the roller bearing 10 on the disc 11 on which the outer ring 12 stands. As a result, the axial force acting on the roller bearing 10 limited so that the rolling bearing 10 does not destroy becomes. After the launch, the inner ring 13 of the deformed elastically by the launch acceleration Bearing back from the disc 11 so that the inner ring 13th free is.

    Innerhalb des heckseitigen Wälzlagers 10 weist die Motorwelle 9 ein Innengewinde 14 auf, in das eine axial bewegliche, gegen Verdrehen gesicherte Schubspindel 15 mit einem Außengewinde 16 greift. Durch den innerhalb des Wälzlagers 10 liegenden Gewindeeingriff ergibt sich eine kurze Baulänge. Am anderen Ende der Schubspindel 15 sitzt an einem Außengewinde 17 eine Eingriffsmutter 18, die mit einem an der Achse B des einen Ruderpaars befestigten Mitnahmehebel 19 gekoppelt ist. Durch Verdrehen der Eingriffsmutter 18 läßt sich die Stellung der Ruderachse B bezogen auf die Schubspindel 15 justieren. Die Justierstellung ist mittels einer Konterschraube 20 festlegbar.Within the rear roller bearing 10, the Motor shaft 9 has an internal thread 14 into which an axial Movable push spindle 15 secured against twisting engages with an external thread 16. Through the inside of the Rolling bearing 10 lying engagement results in a short overall length. Sitting at the other end of the push spindle 15 on an external thread 17, an engagement nut 18 with one attached to the axis B of the one oar pair Driving lever 19 is coupled. By twisting the Engagement nut 18, the position of the rudder axis Adjust B in relation to the push spindle 15. The Adjustment position is by means of a counter screw 20 definable.

    Die Umsetzung der Drehbewegung des Rotors 8 in die Schwenkbewegung der Ruderachse B geschieht folgendermaßen:Implementation of the rotary movement of the rotor 8 in the Swivel movement of the rudder axis B happens as follows:

    Durch rotatorische Bewegung r1 (vgl. Fig.2) der Motorwelle 9 wird über die Gewindepaarung 14,16 die Schubspindel 15 in Richtung t translatorisch bewegt. Dadurch wird über den Mitnahmehebel 19 die Ruderachse B rotatorisch r2 (vgl. Fig.2) bewegt. Die bei der Bewegungsumsetzung entstehenden radialen Reaktionskräfte werden von den Wälzlagern 10 aufgenommen. Es tritt dabei nur eine geringe Reibung auf, was den Wirkungsgrad des Getriebezugs erhöht. Das geringe Gewicht und das geringe Trägheitsmoment der beweglichen Teile ermöglicht eine hohe Dynamik (Bandbreite) der Bewegung. Der Getriebezug erlaubt eine hohe Übersetzung auf kleinstem Raum. Ein Kugelgewindetrieb zwischen der Motorwelle 9 und der Schubspindel 15 ist nicht erforderlich. Es genügt ein metrisches Gewinde.By rotary movement r1 (see Fig.2) the Motor shaft 9 is the thread pair 14.16 Thrust spindle 15 translationally moved in direction t. As a result, the rudder axis B rotatory r2 (see Fig. 2) moves. The at the Radial reaction forces arising from the movement are taken up by the roller bearings 10. It occurs just a little friction on what the efficiency of the Gear train increased. The light weight and the light Moment of inertia of the moving parts enables one high dynamics (bandwidth) of movement. The gear train allows a high translation in the smallest space. On Ball screw drive between the motor shaft 9 and the Thrust spindle 15 is not required. It is enough metric thread.

    Die angegebene Stelleinrichtung ist kleinbauend und vergleichsweise leicht. Wenige bewegliche Teile genügen für einen leichtgängigen Getriebezug.The specified actuating device is small and comparatively easy. Few moving parts are sufficient for a smooth-running gear train.

    An der Schubspindel 15 ist ein Arm 21 befestigt, der an einem Stellglied 22 eines Linearpotentiometers 23 angreift. Das Linearpotentiometer 23 ist an eine im Raum 24 angeordnete Regelelektronik angeschlossen. Das Linearpotentiometer 23 ist in einer Ausnehmung 25 (vgl. Fig.3) des Trägergehäuses 4 angeordnet. Über das Linearpotentiometer 23 wird der Regelelektronik die Ist-Lage des jeweiligen Ruderpaars gemeldet. Anstelle des Linearpotentiometers können auch andere Maßnahmen zur Erfassung der Ist-Stellung der Ruder vorgesehen sein.On the push spindle 15, an arm 21 is attached to the an actuator 22 of a linear potentiometer 23 attacks. The linear potentiometer 23 is connected to one in the room 24 arranged control electronics connected. The Linear potentiometer 23 is in a recess 25 (cf. 3) the carrier housing 4 is arranged. About the Linear potentiometer 23 becomes the actual position of the control electronics of the respective oar pair reported. Instead of Linear potentiometers can also take other measures Detection of the actual position of the rudder may be provided.

    Claims (10)

    Stelleinrichtung für Ruder eines Flugkörpers, wobei die Ruder von Stellmotoren über Schubspindeln verstellbar sind und die Stellmotoren in einem im Flugkörper angeordneten Trägergehäuse vorgesehen sind,
    dadurch gekennzeichnet,
    daß die Statoren(7) der Stellmotoren(5,6) unmittelbar im Trägergehäuse(4) angeordnet sind und daß die Schubspindel (15) in ein Innengewinde(14) der Motorwelle(9) eingreift.    Setting device for rudder of a missile, the rudders of servomotors being adjustable via thrust spindles and the servomotors being provided in a carrier housing arranged in the missile,
    characterized,
    that the stators (7) of the servomotors (5, 6) are arranged directly in the carrier housing (4) and that the thrust spindle (15) engages in an internal thread (14) of the motor shaft (9).         Stelleinrichtung nach Anspruch 1,
    dadurch gekennzeichnet,
    daß das Innengewinde(14), in das die Schubspindel(15) eingreift, innerhalb eines die Motorwelle(9) lagernden Wälzlagers(10) liegt.    Actuating device according to claim 1,
    characterized,
    that the internal thread (14), in which the thrust spindle (15) engages, lies within a roller bearing (10) supporting the motor shaft (9).         Stelleinrichtung nach Anspruch 1 oder 2,
    dadurch gekennzeichnet,
    daß ein die Motorwelle(9) lagerndes Wälzlager(10) einen Innenring(13) und einen Außenring(12) aufweist und daß der Innenring(13) und der Außenring(12) bei einer Abschußbeschleunigung des Flugkörpers sich im Trägergehäuse(4) abstützt.    Actuating device according to claim 1 or 2,
    characterized,
    that a roller bearing (10) supporting the motor shaft (9) has an inner ring (13) and an outer ring (12) and that the inner ring (13) and the outer ring (12) are supported in the carrier housing (4) when the missile accelerates.         Stelleinrichtung nach Anspruch 3,
    dadurch gekennzeichnet,
    daß eine Scheibe(11) im Trägergehäuse(4) angeordnet ist, an dem sich der Außenring(12) und bei einer Abschußbeschleunigung auch der Innenring(13) abstützt.    Actuating device according to claim 3,
    characterized,
    that a disc (11) is arranged in the carrier housing (4), on which the outer ring (12) and, when the launch is accelerated, also the inner ring (13) is supported.         Stelleinrichtung nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet,
    daß das Wälzlager(10) ein Schrägkugellager ist.    Actuating device according to one of the preceding claims,
    characterized,
    that the roller bearing (10) is an angular contact ball bearing.         Stelleinrichtung nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet,
    daß die Motorwellen(9) im Trägergehäuse(4) parallel zueinander und nebeneinander liegen.    Actuating device according to one of the preceding claims,
    characterized,
    that the motor shafts (9) in the carrier housing (4) are parallel to each other and next to each other.         Stelleinrichtung nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet,
    daß die Stellmotoren bürstenlose Motoren sind.    Actuating device according to one of the preceding claims,
    characterized,
    that the servomotors are brushless motors.         Stelleinrichtung nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet,
    daß das Trägergehäuse(4) den Heckbereich(1) des Flugkörpers gegen radiale Kräfte abstützt.    Actuating device according to one of the preceding claims,
    characterized,
    that the carrier housing (4) supports the tail area (1) of the missile against radial forces.         Stelleinrichtung nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet,
    daß die Lage der Ruder bezogen auf die Schubspindel(15) justierbar ist.    Actuating device according to one of the preceding claims,
    characterized,
    that the position of the rudder relative to the thrust spindle (15) is adjustable.         Stelleinrichtung nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet,
    daß ein Potentiometer(23) zur Rückmeldung der Ruderlage an eine Steuerelektronik vorgesehen ist und daß ein Stellglied(22) des Potentiometers(23) mit der Schubspindel(15) verbunden ist.    Actuating device according to one of the preceding claims,
    characterized,
    that a potentiometer (23) is provided for feedback of the rudder position to control electronics and that an actuator (22) of the potentiometer (23) is connected to the thrust spindle (15).
    EP00110018A 1999-05-18 2000-05-12 Actuation system for an aerodynamic control surface of an air vehicle Expired - Lifetime EP1054231B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    DE19922693A DE19922693A1 (en) 1999-05-18 1999-05-18 Control device for the rudder of a missile
    DE19922693 1999-05-18

    Publications (3)

    Publication Number Publication Date
    EP1054231A2 true EP1054231A2 (en) 2000-11-22
    EP1054231A3 EP1054231A3 (en) 2002-06-12
    EP1054231B1 EP1054231B1 (en) 2005-11-30

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    ID=7908347

    Family Applications (1)

    Application Number Title Priority Date Filing Date
    EP00110018A Expired - Lifetime EP1054231B1 (en) 1999-05-18 2000-05-12 Actuation system for an aerodynamic control surface of an air vehicle

    Country Status (3)

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    US (1) US6299101B1 (en)
    EP (1) EP1054231B1 (en)
    DE (2) DE19922693A1 (en)

    Cited By (1)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    WO2010005350A1 (en) * 2008-07-07 2010-01-14 Saab Ab Rudder machinery

    Families Citing this family (7)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US6446906B1 (en) * 2000-04-06 2002-09-10 Versatron, Inc. Fin and cover release system
    DE102005038856A1 (en) 2005-08-17 2007-02-22 Airbus Deutschland Gmbh Fastening system for attaching tail unit at fastening surface of airplane, has contact surfaces for attachment at tail unit and fastening surface, where contact surfaces comprise contact line and differentiating angle of specified degrees
    US8148670B2 (en) * 2008-08-26 2012-04-03 Woodward Hrt, Inc. Rotary actuator ball-detent locking mechanism
    US8324544B2 (en) 2010-06-02 2012-12-04 Woodward Hrt, Inc. Multi-stage fin deployment assembly
    US8624172B2 (en) * 2010-10-13 2014-01-07 Woodward Hrt, Inc. Shift lock assembly
    US9453531B2 (en) 2013-08-26 2016-09-27 Roller Bearing Company Of America, Inc. Integrated bearing assemblies for guided attack rockets
    US9605692B2 (en) 2014-10-01 2017-03-28 Woodward, Inc. Locking rotary actuator

    Citations (3)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    DE3441534A1 (en) 1984-11-14 1986-05-15 Diehl GmbH & Co, 8500 Nürnberg BEARING ARRANGEMENT FOR THE RUDDER BLADE OF AN AIRCRAFT
    DE3441533C2 (en) 1984-11-14 1989-07-20 Diehl Gmbh & Co, 8500 Nuernberg, De
    DE4335785A1 (en) 1993-10-20 1995-04-27 Diehl Gmbh & Co Control surface actuating device

    Family Cites Families (11)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US3154015A (en) * 1962-09-19 1964-10-27 Martin Marietta Corp Missile flight control system
    US4037806A (en) * 1964-09-16 1977-07-26 General Dynamics Corporation Control system for rolling missile with target seeker head
    US5393011A (en) * 1965-12-03 1995-02-28 Shorts Missile Systems Limited Control systems for moving bodies
    US4438893A (en) * 1973-08-10 1984-03-27 Sanders Associates, Inc. Prime power source and control for a guided projectile
    DE3613539C1 (en) * 1986-04-22 1997-05-28 Dornier Gmbh Actuator for aerodynamic control surfaces, especially on missiles
    DE3702733A1 (en) * 1987-01-30 1988-08-11 Diehl Gmbh & Co RUDDER CONTROL
    DE4135557C2 (en) * 1991-10-29 1999-05-06 Diehl Stiftung & Co Rudder control device
    US5528092A (en) * 1992-06-23 1996-06-18 Nippon Corporation Spindle motor
    DE4325218C2 (en) * 1993-07-28 1998-10-22 Diehl Stiftung & Co Artillery missile and method for increasing the performance of an artillery missile
    US5593109A (en) * 1995-01-10 1997-01-14 Lucas Western, Inc. Actuator system and method
    US6073880A (en) * 1998-05-18 2000-06-13 Versatron, Inc. Integrated missile fin deployment system

    Patent Citations (3)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    DE3441534A1 (en) 1984-11-14 1986-05-15 Diehl GmbH & Co, 8500 Nürnberg BEARING ARRANGEMENT FOR THE RUDDER BLADE OF AN AIRCRAFT
    DE3441533C2 (en) 1984-11-14 1989-07-20 Diehl Gmbh & Co, 8500 Nuernberg, De
    DE4335785A1 (en) 1993-10-20 1995-04-27 Diehl Gmbh & Co Control surface actuating device

    Cited By (1)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    WO2010005350A1 (en) * 2008-07-07 2010-01-14 Saab Ab Rudder machinery

    Also Published As

    Publication number Publication date
    DE19922693A1 (en) 2000-11-23
    DE50011724D1 (en) 2006-01-05
    US6299101B1 (en) 2001-10-09
    EP1054231B1 (en) 2005-11-30
    EP1054231A3 (en) 2002-06-12

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