EP3279605A1 - Procédé de lancement d'un missile guidé à partir d'une plate-forme volante - Google Patents

Procédé de lancement d'un missile guidé à partir d'une plate-forme volante Download PDF

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Publication number
EP3279605A1
EP3279605A1 EP17001259.5A EP17001259A EP3279605A1 EP 3279605 A1 EP3279605 A1 EP 3279605A1 EP 17001259 A EP17001259 A EP 17001259A EP 3279605 A1 EP3279605 A1 EP 3279605A1
Authority
EP
European Patent Office
Prior art keywords
rudder
blocking element
missile
blocking
hard
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
EP17001259.5A
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German (de)
English (en)
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EP3279605B1 (fr
Inventor
Bernd Lindenau
Ingo Weltin
Peter Gerd Fisch
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 Defence GmbH and Co KG
Original Assignee
Diehl Defence GmbH and Co KG
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Publication date
Application filed by Diehl Defence GmbH and Co KG filed Critical Diehl Defence GmbH and Co KG
Publication of EP3279605A1 publication Critical patent/EP3279605A1/fr
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Publication of EP3279605B1 publication Critical patent/EP3279605B1/fr
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft

Definitions

  • the invention relates to a method for dropping a missile from a platform, in which the missile is dropped from the flying platform and using at least one movable rudder controls a rolling motion about its longitudinal axis.
  • a method of the type mentioned in which according to the invention the rudder is blocked from being dropped by a mechanical blocking element, the rudder is partially unlocked in the course of a discharge process by a movement of the blocking element, so that the rudder is movable only over part of its rudder deflection range is and the blocking element after reaching a predetermined flight phase of the missile completely unlocks the rudder, so that it is movable over its entire rudder deflection range.
  • the invention is based on the consideration that prevail at the moment of dropping the missile complex aerodynamic conditions to the missile.
  • the flying platform is surrounded by air, so strong, especially under the pylon to which the missile hangs Cross winds can occur.
  • the configuration of this winch also depends on the current flying maneuver of the flying platform.
  • the guided missile includes guided wings, which are provided with movable rudders for influencing the attitude.
  • the rudders are connected to a drive so that a control unit can control the attitude of the missile by controlling the drive or drives.
  • a control error leads to the just discarded and, for example, not yet driven missile assumes a trajectory that brings him on a collision course with the abinneden platform. Impacting the missile on the platform can severely damage both units.
  • the missile receives no steering authority over the rudders when dropped until it reaches a safe distance from the platform. These can be blocked by a blocking element, so that the faulty control of a collision-causing maneuver is mechanically prevented.
  • the invention is based on the further consideration that the rudders can be controlled via a mixer in order to generate pitch, yaw and roll moments for the implementation of flight control specifications.
  • This has the respective flight commands as input and generates from this the rudder deflections to be produced.
  • It turns out from this the legality that for the pitching and yawing moments differential, ie not uniform or opposite deflections of the rudder are necessary.
  • only in the same direction deflections lead to a pure rolling motion.
  • significantly smaller rudder deflections are required for a pure rolling movement than for a similarly strong pitching or yawing maneuver.
  • its guided missile has greatly differing moments of inertia due to its typical shape. The moment of inertia about the roll axis is considerably smaller than the moment of inertia about the pitch and yaw axis.
  • a roll rate can be increased or decreased significantly less than rates around the other axes.
  • much smaller rudder deflections are necessary, as in an equally strong control of a pitch or yaw.
  • the rudders only slightly deflect to compensate for the aerodynamically caused rolling forces. If the rudders are limited to such a deflection, a bumping by rolling can be sufficiently counteracted and an undesired collision course to the platform can be effectively prevented by a faulty pitching maneuver of the guided missile when dropped.
  • the blocking element according to the invention allows the rudder to be partially unlocked, so that the rudder is movable only over a part of its rudder deflection. As a result, an undesired pitching motion can be effectively prevented.
  • the rudder After reaching the predetermined flight phase, for example, when reaching a predetermined distance of the missile to the platform, the rudder is fully released, so that the missile can be freely controlled to its predetermined destination to be controlled.
  • a simple mechanical measure both a collision due to incorrect control and because of a transverse flow-related rolling movement after being dropped off can be avoided.
  • the flying platform is, for example, an aircraft or a rotorcraft, under the wing of the missile hangs during a flight.
  • the missile has expediently four wings in the X position, wherein during a flight in particular two of the wings are directed obliquely downwards and two obliquely upwards.
  • the missile may include a propulsion engine including a rocket engine or an air-breathing engine, such as a turbine.
  • the drop may be a notching and down throwing the missile or starting at a ramp forward.
  • the discharge process expediently comprises the entire process associated with a discharge, such as a discharge preparation and the discharge itself, and in particular also a flight control phase due to the discharge in the immediate vicinity of the platform.
  • the ejection preparation can be initiated, for example, by an operator of the flying platform, who releases the missile for ejection. Controlling a rolling movement after ejection expediently also includes the countersteering against an externally applied rolling moment, so that the resultant is an at least substantially vanishing roll rate.
  • the mechanical blocking element blocks the rudder before the departure of the guided missile.
  • the rudder is thereby expediently at least substantially immobile, so fixed to the fuselage of the missile.
  • the rudder is movable over part of its rudder travel range.
  • the rudder deflection area expediently comprises the deflection area, which can be achieved by the steering control during a regular control operation of the guided missile.
  • the area is expediently limited to less than 30% of the total rudder deflection range, in particular to a maximum of 20%.
  • the missile If the missile has left the vicinity of the flying platform, it enters the predetermined flight phase, in which the rudder is completely unlocked.
  • the predetermined flight phase can begin when the missile has flown or fallen, for example, a minimum distance from the platform or a minimum time after the dropping or unlatching.
  • the blocking element is expediently connected to a drive which moves it along a predetermined path.
  • the movement of the blocking element is expediently controlled by a control unit which controls the drive.
  • all present in the same axial position of the missile rudder in an X-position so all four rudders, equipped with a blocking element according to the invention, so that a partial release according to the invention is made possible for all oars.
  • the partial release can be equally effective for all rudders, so that the currently possible rudder range for all Rudder of a group, so all rudders in the same axial position on the missile, is the same.
  • the blocking element engages in the rudder and is moved out of the rudder for unlocking.
  • the blocking element can be applied from the outside to the rudder, for example at a trailing edge of the rudder.
  • the blocking element may be removed radially inward, in the tangential direction, in the axial direction or in a combination of two or more directional components from the rudder. It is also possible that the blocking element is guided around the rear edge of the rudder and is removed for unlocking to the rear, ie in the axial direction of the missile from the trailing edge.
  • the blocking element is removed from the rudder, at least part of the blocking element moves away from the rudder, for example, the blocking element moves wholly or partly out of the rudder.
  • the blocking element engages in the rudder to block this in whole or in part, there is the possibility that it engages from radially inside, ie in the radial direction of the missile from the inside out.
  • To unlock the blocking element can now be moved out of the rudder at least predominantly in the radial direction inwards.
  • the blocking element it may also be advantageous for the blocking element to be moved out of the rudder at least predominantly in the axial direction for unlocking.
  • a further advantageous embodiment of the invention provides that a form-fitting backdrop of blocking element and rudder is stepped at least twice.
  • the step may be formed by a step in the blocking element and / or by a step in the rudder.
  • the blocking element is now expediently moved discretely from a blocking position into a partially unlocked position and from there into a release position. It is expedient if the blocking element remains stationary in the partially unlocked position until it is then moved, expediently, in the release position. In this way, a partial release, ie a release of a defined part of the entire rudder deflection range, can be defined.
  • a movement from one stage to the next expediently takes less than one third of the time in which the blocking element remains stationary in the partially unlocked position.
  • the movement of the blocking element of Position to position expediently happens so far, for example, each within less than 0.5 seconds.
  • the drive of the blocking element is designed so that it moves the blocking element only slowly from the blocking position on the partially unlocked position to the release position, for example, a total of a period of at least two seconds, in particular at least five seconds ,
  • the drive is expediently designed so that a faster unlocking movement is not possible. Too fast unlocking and thus the risk of a collision course is thus prevented.
  • the blocking element releases the rudder continuously by a removal from the rudder from the blocked position to the full position again.
  • the part of the rudder deflection range over which the rudder is movable thus becomes continuously larger over time, at least substantially linearly continuously larger.
  • the invention is also directed to a method for controlling a missile, in which a rudder of the missile is moved by a steering mechanism in a steering manner and the flight of the missile is thereby controlled.
  • the rudder is placed in a rudder hard position, in which the rudder is thus aligned in a maximum deflection, for example, abuts against a stop.
  • the rudder can now stay there.
  • a Ruderhartlage can be useful if the missile is to be braked hard or defined to crash should be, for example, a maneuver abort.
  • a flight of a guided missile it may happen that the flight of the missile should be stopped or slowed down considerably. For example, the missile should not leave a predetermined safety zone in a test shot. Or a signal connection between flying platform and guided missile breaks off or is disturbed, so that a misdirection of the missile is to be feared. Or the guided missile is placed on a wrong target and an attack should be stopped as soon as possible.
  • a maneuver termination can also be initiated by the control unit which controls the regular flight of the guided missile. However, it may happen that the control unit is defective, unreachable, or unable to act quickly enough, for example, when the missile is on a wrong destination and would take a while to "flag" it. It is therefore advantageous to have a system with which a flight termination can be achieved with simple means.
  • This object is achieved by a method for controlling a guided missile as described above, wherein according to the invention, the rudder is pressed by an additional blocking element to the control mechanism in the Ruderhartlage and / or held in the Ruderhartlage.
  • a regular control by the control unit may be overridden, so that the rudder remains in its Ruderhartlage.
  • a maneuver abort may also be obtained contrary to the commands of the regular control unit.
  • the blocking element can advantageously have a double function: It can unlock the rudder in the ejection process, whereby a partial unlocking is performed as an intermediate step, and it can bring the rudder into the rudder hard position and / or hold there.
  • all the details of the method for dropping a guided missile from a flying platform can also be combined with the method for controlling a guided missile and vice versa.
  • the blocking element moves by its movement into a hard-position position, the rudder in a Ruderhartlage. As a result, for example, a control operation of the regular control unit can be overridden and a reliable braking or crashes of the missile can be achieved.
  • the movement of the blocking element to its hard position is controlled by an algorithm which is in addition to a regular steering control algorithm of the guided missile.
  • the movement of the blocking element to its hard position may be triggered by a special signal, for example a signal cancellation from or to a higher-level control system, such as the flying platform.
  • the special signal can also be sent specifically to achieve a quick maneuver abort.
  • the blocking element passes through a backdrop during its movement into a hard position, by which the movement of the blocking element is converted into a rudder movement in the rudder hard position of the rudder.
  • the Ruderhartlage can be reliably achieved in this way on simple mechanical means.
  • a maneuver abort is expediently only after a certain flight of the missile. It is advantageous in that the blocking element is moved from its release position to its hard position and there holds the rudder in the Ruderhartlage. In this case, the blocking element when moving from the release position to the hard position can pass through the blocking position, which is thus between the release position and the hard position. It is also possible that the hard position of the blocking element is in relation to a release position against a blocking position. In this case, therefore, the release position would lie between a blocking position and a hard position.
  • the rudder is already worn out at the time of a maneuver crash.
  • a backdrop control of the rudder in its hard position is not possible.
  • the blocking element presses the rudder from the outside in the Ruderhartlage when moving into the hard position.
  • the invention is directed to a rudder position for a discharge missile comprising a static system for fixation in the missile and a static system movable rudder.
  • the static system according to the invention comprises a blocking element and a drive for moving the blocking element, wherein the blocking element and the rudder are arranged to each other, that the blocking element mechanically fixes the rudder and deemedtriegelt the rudder after moving the blocking element by the drive is and is movable only over part of its rudder range.
  • An ejection missile may in this case be a missile that is dropped by a flying platform, for example, down or at an independent start to the front.
  • FIG. 1 shows a guided missile 2, which hangs under a wing of a flying platform 4 during a flight of the flying platform 4.
  • the guided missile 2 is fastened with a coupling unit 6 to a pylon 8 of the flying platform 4 and can be dropped by loosening the coupling unit 6.
  • the guided missile 2 When the guided missile 2 is dropped, it falls down, starts its own engine 10 and, controlled by rudder 12, flies toward an aimed target.
  • the rudders 12 are attached to the steering wings 14 and can exert a rolling motion, a pitching motion and / or a yawing motion on the guided missile 2 by a corresponding movement.
  • the guided missile 2 can in another embodiment start forward by procuring its engine 10 feed and the coupling unit 6 is guided in a rail of the pylon 8 to the front, until the guided missile 2 leaves the pylon 8.
  • the engine 10 may be an air-breathing engine, for example in the form of a turbine, when dropped to the front, it is expediently a rocket engine.
  • FIG. 2 shows the guided missile 2 hanging on the pylon 8 of the flying platform 4 in a schematic representation of the front.
  • the guided missile 2 is not only flown from the front of air.
  • the in FIG. 2 are indicated by a plurality of straight dashed arrows. Due to air resistance in the Near the wing, these crosswinds decrease with increasing distance from the wing, as in FIG. 2 is indicated by the length of the straight arrows.
  • a rolling moment 18 is applied to the guided missile 2, the in FIG.
  • This roll moment 18 is produced in particular by the engagement of the transverse flow 16 on the guide wings 14, but also on the front wings 20 and on the fuselage 22 of the guided missile 2. As a result, the missile 2 is already prestressed on the pylon 8 during the flight.
  • the rolling moment 18 causes a rolling acceleration on the guided missile 2, which can lead to the missile 2 striking the pylon 8, in particular with a steering wing 14, in particular damaging a rudder 12 and thus an impairment of the maneuverability of the missile 2 threatens.
  • the guided missile 2 expediently carries out a steering movement with its rudders 12, which counteract the rolling moment 18, already during the ejection process before the ejection or notching from the pylon 8.
  • each rudder 12 is a blocking element 24 (FIG. FIG. 3 ), which blocks a strong steering deflection of the rudder 12.
  • FIG. 3 shows the blocking element 24 at the rudder 12 of the steering wing 14 of the guided missile 2.
  • the blocking element 24 indicated only schematically and shown only to a better understanding will in a bolt shape. There are many different shapes and positions of the blocking element 24 in question, some of which are exemplified in the following figures.
  • substantially identical components are numbered with the same reference numerals.
  • like components in different embodiments are designated by the same reference numerals and other reference characters, and may be identical to each other or with slight differences from each other, for example, in size, shape, position, and / or function.
  • the reference number alone without a Reference letters mentioned, the corresponding components of all embodiments are addressed.
  • a rudder system 26 of the guided missile 2 which has 12 actuators 30 and a control unit 28 for outputting control signals to actuators 30 of the rudder 12 in addition to the four guide vanes 14 with the associated rudders.
  • the control unit 28 comprises a mixer, not shown, which converts steering signals into rudder deflections and outputs corresponding control signals to the four actuators 30 of the four rudders 12.
  • a blocking element 24 with an associated drive 32 with which the blocking element 24 in the radial direction 34 inwardly or outwardly, as indicated by the double arrow, or in the axial direction 36 forward or backward, as by the two horizontal arrows in FIG. 3 is indicated, lets move.
  • the drive 32 is also controlled by the control unit 28 with the corresponding control signals.
  • the control unit 28 with the drive 32 and the blocking element 24 is part of a static system 38 which is fixed on or in the fuselage 22 of the guided missile 2.
  • the blocking element 24 and parts of the actuator 30 are movable relative to the body 22.
  • FIG. 4 shows an embodiment 24a of the blocking element 24, which engages around the rear edge 40 of the rudder 12 from the outside. Shown is a section through the rudder 12, wherein the viewing direction is directed in the radial direction to the guided missile 2.
  • the view is from the outside of the blocking element 24a, which is located as a sheet in the vicinity of the fuselage 22 and in the axial direction 36 of the fuselage 22 is movable. It engages around the rudder 12 bifurcated from behind, so that this - as in the left illustration FIG. 4 can be seen - is blocked in his rowing motion.
  • the left position of the blocking element 24a shows the blocking position in which the blocking element 24a is positioned during the flight and before the missile 2 is dropped off the platform 4.
  • a rudder movement of the rudder 12 is completely prevented, whereby the advantage is achieved that act during the flight on the rudder 12 acting aerodynamic forces on the blocking element 24a and the actuator 30 is mechanically protected.
  • the drive 32 moves the blocking element 24a axially to the rear in a Absch ein, in the middle representation of FIG. 4 is shown.
  • the rudder 12 is partially unlocked so that it is movable over part 42 of its entire rudder deflection area 44, for example 15%.
  • the mobility is stopped or limited by a stop of the rudder 12 on the blocking element 24a.
  • there is a certain controllability of the missile 2 which is limited to weak steering movements. A strong pitching upwards by a faulty control is not possible.
  • it is possible by a same direction rudder deflection of all four rudders 12 a rolling moment by the prevailing rolling moment 18 is compensated, so that the missile 2 can be dropped harmless.
  • the available part 42 of the entire rudder area is in size dependent on the position of the blocking element 24a.
  • the passable portion 42 comprises a maximum of 25% of the total rudder deflection range.
  • the blocking element 24 is moved to a discharge position, which releases a sufficient rudder deflection, in order to guarantee a collision-free discharge of the guided missile 2.
  • the blocking element 24 remains in this discharge position. If the guided missile 2 has reached a predetermined flight phase, for example a sufficient distance from the platform 4, the rudder 12 is completely released by a further movement of the blocking element 24, as is shown by way of example in the right-hand illustration of FIG FIG. 4 is shown.
  • the blocking element 24 is arranged so that the rudder 12 no longer touches the blocking element 24 in the case of a full rudder deflection on both sides.
  • Discharge position and release position are expediently approached discreetly. The blocking element 24 rests in the discharge position until the guided missile 2 has reached the predetermined flight phase.
  • the rudder deflection is released continuously.
  • This can be done by a continuous movement of the blocking element 24, which thereby releases a steadily growing part 42, as for example from the middle illustration FIG. 4 can be seen.
  • This method has the advantage that a slow drive 32 can be used, so that a high speed of movement of the blocking element 24 is prevented in this respect.
  • a complete release of the rudder 12 still too close to the missile 2 from the platform 4 is thereby reliably avoided even with a control error of the control unit 28 to the drive 32. As a result, a greater security against collision of the missile 2 to the platform 4 can be achieved.
  • the rudder 12 is shown in a sectional view, in which the cutting plane is aligned perpendicular to the tangential direction of the guided missile 2. You can see the axis of rotation 46 about which the rudder 12 is rotatable. From the hull 22 a blocking element 24b projects radially outwards and penetrates from the inside into a recess 48 of the rudder 12. In the left display off FIG. 5 the blocking element 24b is shown in its blocking position, in which a rudder deflection movement of the rudder 12 is completely blocked. In the middle illustration, the discharge position of the blocking element 24b is shown, in which only part of the rudder deflection region 44 is released.
  • FIG. 5 shows the blocking element 24b in its release position in which the rudder 12 is released over its entire rudder deflection area 44 or completely unlocked.
  • FIG. 6 The embodiment of FIG. 6 is similar to that FIG. 5 with the difference that the blocking element 24c is asymmetrical in shape so as to asymmetrically release the rudder 12 in the partially unlocked position with respect to the possible rudder portion 42.
  • the rudder 12 is in the partially unlocked position, which is shown in the middle figure, movable in one direction only.
  • the asymmetry of the blocking element 24c would be designed accordingly. In this way, the rolling moment 18 can be sufficiently counteracted without releasing the rudder 12 to a great extent.
  • FIGS. 7 to 9 three different form-fitting scenes 50a-c are shown, which are each formed by a recess of the rudder 12 and the blocking element 24d-f therein.
  • the form-fitting scenes 50a-c are each staggered twice to show the stepped principle. In the same way, more levels are possible.
  • FIG. 7 shows the partially unlocked position of the blocking element 24d. If the blocking element 24d extended slightly further, so it is in its blocking position in which the radially inner and thicker part of the blocking element 24d forms a blocking stage that blocks the rudder 12. The radially outer and thinner part of the blocking element 24d holds the rudder 12 in the partially blocked step in which it is partially unlocked.
  • both the blocking position and the partially unlocked position of the blocking element 24d can be set precisely even if the blocking element 24d is positioned less accurately, without this affecting the released part of the rudder deflection region.
  • the form-fitting gate 50b is formed by a step in the recess in the rudder 12.
  • the narrower part of the recess here forms the blocking stage, which blocks the rudder 12 in conjunction with the introduced blocking element 24e.
  • the wider in Ruderausschlagraum part of the recess forms together with the blocking element 24e, a partially unlocked area in which the rudder deflection of the rudder 12 is partially released.
  • FIG. 9 is similar to that FIG. 7 However, wherein the interlocking gate 50c, the rudder in a stepped manner releases only in one direction, so that an asymmetric Operaentriegelung of the rudder 12 is achieved.
  • the grading may be formed by the blocking element 24f or by a recess in the rudder 12 analogous to the example FIG. 8 ,
  • the rudder 12 is unlocked by the relevant blocking element 24b-f, for example, in the radial direction 34 moves out of the rudder 12.
  • the release position of the blocking element 24 g is achieved by its movement, which is substantially perpendicular to the radial direction 34.
  • the rudder 12 is perpendicular to the radial direction 34 cut just inside its radially inner End, so close to the hull 22. It can be seen that the fuselage 22 facing side of the rudder 12 is provided with a link 52a. This forms a recess into which engages the blocking element 24g.
  • FIG. 10 shows the blocking element 24g in three positions: one in FIG. 10 overhead blocking position, a middle inconveniencetriegelnden position and a in FIG. 10 shown below release position.
  • Dash-dotted line is the movement axis of the blocking element 24g, which runs in a straight line between these three positions. The movement axis runs, for example, in the axial direction of the guided missile 2 or, more generally, parallel to the fuselage 22 of the guided missile 2.
  • the gate 52 is designed to narrow the blocking position, so that the blocking element 24g when entering into the rudder 12 this blocked further and further.
  • the link 52 forms an inner channel 54, which is dimensioned so that the blocking element 24g in the channel located completely blocks the rudder 12.
  • the channel 54 widens, so that in the middle, partially unlocked position, the rudder 12 is movable over a part 42 of the entire rudder deflection area 44. In the release position, the rudder 12 can drive in both rudder deflection directions completely over the blocking element 24g, so that this, even if it still protrudes from the hull 22, the rudder 12 is no longer blocked but this is completely unlocked.
  • the channel 54 may end where the blocking element 24g assumes its blocking position. In the example off FIG. 10 However, the channel is still running. As a result, the rudder 12 can be pressed by a movement of the blocking member 24g in a Ruderhartlage, as in FIG. 11 is shown.
  • the blocking element 24g can be moved further beyond its blocking position. It moves through the channel 54 of the link 52.
  • the rudder 12 is forcibly deflected by the movement of the blocking element, for example in the axial direction of the missile 2, for example, in his Ruderhartlage, in FIG. 11 is shown.
  • the rudder 12 is again brought to its neutral starting position and only partially unlocked upon further movement of the blocking element 24g and then fully unlocked, as indicated by the three lower positions of the blocking element 24g in FIG. 11 is indicated.
  • the rudder 12 may be that it makes sense to bring the rudder 12 into its rudder hard position during the flight of the guided missile 2, for example in order to decelerate the guided missile 2 as quickly as possible or to bring it to a crash.
  • This can be achieved by the blocking element 24g passing through the channel 54 to its end or to the hard position of the blocking element 24g. In the embodiment of FIG. 11 However, it is visible that this only works when the blocking element 24g is within the gate 52. However, this does not have to be the case.
  • FIG. 12 This example is in FIG. 12 clarified.
  • the rudder 12 has a certain rudder deflection and is to be brought by the blocking element 24g in Ruderhartlage.
  • the rudder 12 could be brought into its neutral position, which in FIG. 10 is shown, and the blocking element can be moved to the hard position position, as in FIG. 11 is shown.
  • the rudder 12 should still be brought into Ruderhartlage. This is possible, as in the two representations of the FIGS. 12 and 13 is shown.
  • the blocking element 24g is moved in the direction of its blocking position, as in FIG FIG.
  • the rudder hard position of the rudder 12 is in this case already achieved when the blocking element 24 g is not yet in its blocking position, as in FIG. 13 is shown. Instead, an outer blocking position is reached in which the rudder 12 has reached its maximum deflection in one direction, ie its rudder hard position. This is in FIG. 13 shown, in which the blocking element 24g has taken its outer blocking position. Based on the shape of the gate 52, the rudder 12 can therefore be pressed regardless of its initial position from the blocking element 24g in its Ruderhartlage.
  • FIGS. 14 and 15 shows an alternative gate 52b, in which the blocking position of the blocking element 24g is opposite to a hard layer position, the FIG. 15 is shown.
  • FIG. 14 shows the blocking element 24g in a rear blocking position in which it is closest to the trailing edge 40. Further forwardly the blocking element 24g is shown in a partially unlocking position and further forward in its release position, in which the rudder 12, without abutting the blocking element 24g, can be moved across it over its full rudder deflection range. Further forward, the channel 54 connects, which leads to the hard position of the blocking element 24g.
  • FIG. 15 shows the blocking element 24g in five possible positions.
  • the uppermost position or from the point of view of the missile 2 foremost position shows the blocking element 24g in its hard position in the channel 54. If the rudder 12 is pressed by the blocking element 24g from the outside into its Ruderhartlage, so also drawn hard position of the blocking element 24g is slightly further back.
  • the further rear positions of the release position, the UNEtriegelnden position and the blocking position along the dash-dotted axis of movement are shown.
  • the embodiment of the FIGS. 14 and 15 has the advantage that the blocking element 24g can be driven a little faster in its hard position, since it does not have to go through the blocking position. As a result, the narrowing from the release position into the channel 54 can take place more quickly or the constriction from the release position to the point of the blocking position can be designed independently of the channel 54.
  • FIG. 16 shows an embodiment in which the basis of the blocking element 24a FIG. 4 it is shown that this too can push the rudder 12 into a rudder hard position. For this purpose, however, it is necessary that the rudder 12 is already in a relatively far moved out of the middle state. Some control of the rudder 12 by the control unit 28 is therefore still necessary.
  • the advantage with the blocking element 24a is mainly that the rudder 12 can be kept in its rudder-hard position, even if the control unit 28 or control of the rudder 12 subsequently fails.
  • FIG. 17 This is similar to the embodiment FIG. 5 in which a section is shown with a viewing direction from behind.
  • the front tip of the blocking element 24g is designed to be rounded in order to press the rudder 12 more smoothly from the outside into the rudder hard position, which in FIG. 17 is shown.
  • the rudder 12 is not of the. Side but viewed from behind, so that the rudder deflection corresponding to the double arrow.
  • the rudder is 12th provided with tangentially outwardly open recesses 58, along which the tip of the blocking member 24h moves along.
  • the blocking element 24h or the recesses 56, 58 should be relatively far forward, so near the rudder axis 46, in which the outer edge of the rudder 12 in hard position not far from the plane of symmetry of the rudder 12 in his Center position should be removed.
  • the blocking element 24h presses the rudder 12 in an extension in the direction of the blocking position in his Ruderhartlage.
  • the blocking element 24h moves beyond its blocking position.
  • a pressing of the rudder 12 in its rudder hard position is only possible if the blocking element 24h comes to rest laterally next to its recess 56, in which it is retracted in its blocking position.
  • the advantage lies in the fact that the blocking element 24h can hold the rudder 12 in its rudder hard position without the control unit 28 still being required for this purpose.
  • the blocking element 24g, 24h assumes a double function. It completely blocks the rudder 12 in its rudder deflection, for example during a flight. In addition, there is the rudder 12 in a UNEtriegelnden position partially and completely released in the release position. In addition, it can push the rudder 12 into its rudder hard position and hold it in this position.

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  • 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)
EP17001259.5A 2016-08-02 2017-07-24 Procédé de lancement d'un missile guidé à partir d'une plate-forme volante Active EP3279605B1 (fr)

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DE102016009384.6A DE102016009384B4 (de) 2016-08-02 2016-08-02 Verfahren zum Abwurf eines Lenkflugkörpers von einer fliegenden Plattform

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109703777A (zh) * 2018-10-26 2019-05-03 中国飞行试验研究院 一种用于电传运输类飞机飞行试验的舵面卡阻系统
EP3918267A4 (fr) * 2019-01-31 2022-09-07 Saab Ab Ensemble de commande de gouvernail pour missile

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2240954A (en) * 1990-02-13 1991-08-21 Normalair Garrett Lock means for missile control fins
WO2002010670A2 (fr) * 2000-08-02 2002-02-07 Raytheon Company Systeme de verrouillage d'ailette
DE102008034618A1 (de) * 2008-07-25 2010-02-04 Lfk-Lenkflugkörpersysteme Gmbh Verfahren zum Abkoppeln eines unbemannten Flugkörpers von einem Trägerluftfahrzeug
DE102012016093B3 (de) * 2012-08-14 2014-02-13 Mbda Deutschland Gmbh Verfahren zur Ermittlung von für einen Abwurf einer mit verstellbaren Rudern ausgestatteten Außenlast von einem Luftfahrzeug zulässigen Flugzuständen und Parametern einer Abgangsregelung für die Außenlast

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2452053A1 (de) * 1974-11-02 1976-05-06 Dornier Gmbh Einrichtung zum starten von raketengetriebenen flugkoerpern
DE3222378A1 (de) * 1982-06-15 1983-12-15 Dynamit Nobel Ag, 5210 Troisdorf Vorrichtung zur verringerung der empfindlichkeit leitwerksstabilisierter, in luft und/oder wasser sich bewegender gefechtskoerper gegen seitliche anstroemung
US5141175A (en) * 1991-03-22 1992-08-25 Harris Gordon L Air launched munition range extension system and method
FR2919269B1 (fr) * 2007-07-25 2010-01-01 Rafaut & Cie Dispositif de montage d'une drisse d'armement reliant une charge largable a un systeme d'emport fixe sous un aeronef.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2240954A (en) * 1990-02-13 1991-08-21 Normalair Garrett Lock means for missile control fins
WO2002010670A2 (fr) * 2000-08-02 2002-02-07 Raytheon Company Systeme de verrouillage d'ailette
DE102008034618A1 (de) * 2008-07-25 2010-02-04 Lfk-Lenkflugkörpersysteme Gmbh Verfahren zum Abkoppeln eines unbemannten Flugkörpers von einem Trägerluftfahrzeug
DE102012016093B3 (de) * 2012-08-14 2014-02-13 Mbda Deutschland Gmbh Verfahren zur Ermittlung von für einen Abwurf einer mit verstellbaren Rudern ausgestatteten Außenlast von einem Luftfahrzeug zulässigen Flugzuständen und Parametern einer Abgangsregelung für die Außenlast

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109703777A (zh) * 2018-10-26 2019-05-03 中国飞行试验研究院 一种用于电传运输类飞机飞行试验的舵面卡阻系统
CN109703777B (zh) * 2018-10-26 2022-04-19 中国飞行试验研究院 一种用于电传运输类飞机飞行试验的舵面卡阻系统
EP3918267A4 (fr) * 2019-01-31 2022-09-07 Saab Ab Ensemble de commande de gouvernail pour missile

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DE102016009384B4 (de) 2019-10-31
EP3279605B1 (fr) 2019-03-13

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