EP3279605B1 - Method for ejection of a guided missile from a flying platform - Google Patents
Method for ejection of a guided missile from a flying platform Download PDFInfo
- Publication number
- EP3279605B1 EP3279605B1 EP17001259.5A EP17001259A EP3279605B1 EP 3279605 B1 EP3279605 B1 EP 3279605B1 EP 17001259 A EP17001259 A EP 17001259A EP 3279605 B1 EP3279605 B1 EP 3279605B1
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- European Patent Office
- Prior art keywords
- rudder
- blocking element
- hard
- missile
- blocking
- 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.)
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- 230000000903 blocking effect Effects 0.000 claims description 210
- 238000005096 rolling process Methods 0.000 claims description 21
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- 230000008901 benefit Effects 0.000 description 6
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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 for decoupling an unmanned, aerodynamically unstable missile from a carrier aircraft is described. So that the missile does not collide with the carrier aircraft after uncoupling from aerodynamic forces acting on it, the following is proposed: After sensing a successful separation of missile and carrier aircraft, a missile flight control device is activated so that automatic control of the missile by the flight control device and the aircraft Control of the missile under the control of changes in flight state, which are caused by a ruling between missile and carrier aircraft wind field, is possible.
- a missile is known whose control surfaces or rudder can be locked by locking means.
- the locking means is configured such that it engages in a recess in the control surface for locking a control surface and allows a limited rash of the control surface before its complete withdrawal from the recess and thus the release of the control surface.
- 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 takes 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 "understand". 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.
- 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 system for a launch missile according to the features of claim 14, which comprises 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 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 where 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 pronouncedtriegelten 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 brought back to its neutral position and first 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.
- 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.
- 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 viewed from the side but from behind, so that the rudder deflection corresponds 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 and 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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Description
Die Erfindung betrifft ein Verfahren zum Abwurf eines Lenkflugkörpers von einer Plattform, bei dem der Lenkflugkörper von der fliegenden Plattform abgeworfen wird und mithilfe zumindest eines beweglichen Ruders eine Rollbewegung um seine Längsachse steuert.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.
Beim Abwurf eines Lenkflugkörpers von einer fliegenden Plattform, wie einem Hubschrauber oder einem Flugzeug, besteht die Gefahr, dass der Lenkflugkörper beim Abwurf durch unkontrollierte Bewegungen mit der Plattform kollidiert und diese beschädigt.When dropping a missile from a flying platform, such as a helicopter or an aircraft, there is a risk that the missile collides with the ejection by uncontrolled movements of the platform and this damage.
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Es ist daher eine Aufgabe der vorliegenden Erfindung, ein sicheres Verfahren zum Abwerfen eines Lenkflugkörpers anzugeben.It is therefore an object of the present invention to provide a safe method for launching a missile.
Diese Aufgabe wird durch ein Verfahren der eingangs genannten Art gelöst, bei der erfindungsgemäß das Ruder vor Abwurf von einem mechanischen Blockierelement blockiert ist, das Ruder im Verlauf eines Abwurfprozesses durch eine Bewegung des Blockierelements teilentriegelt wird, sodass das Ruder nur über einen Teil seines Ruderausschlagbereichs beweglich ist und das Blockierelement nach Erreichen einer vorgegebenen Flugphase des Lenkflugkörpers das Ruder vollständig entriegelt, sodass es über seinen gesamten Ruderausschlagsbereich beweglich ist.This object is achieved by 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.
Die Erfindung geht von der Überlegung aus, dass im Moment des Abwurfs des Lenkflugkörpers komplexe aerodynamische Verhältnisse um den Lenkflugkörper herrschen. Während des Tragflugs wird die fliegende Plattform von Luft umströmt, sodass insbesondere unter dem Pylon, an dem der Lenkflugkörper hängt, starke Seitenwinde auftreten können. Die Konfiguration dieser Winde ist auch abhängig vom momentanen Flugmanöver der fliegenden Plattform.The invention is based on the consideration that prevail at the moment of dropping the missile complex aerodynamic conditions to the missile. During the flight, 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.
Der Lenkflugkörper umfasst Lenkflügel, die mit beweglichen Rudern zur Beeinflussung der Fluglage versehen sind. Die Ruder sind mit einem Antrieb verbunden, sodass eine Steuereinheit durch Steuerung des oder der Antriebe die Fluglage des Lenkflugkörpers steuern kann. Gerade bei den komplexen aerodynamischen Verhältnissen beim Abwurf kann es vorkommen, dass ein Steuerungsfehler dazu führt, dass der gerade abgeworfene und beispielsweise noch nicht angetriebene Lenkflugkörper eine Flugbahn einnimmt, die ihn auf Kollisionskurs mit der abwerfenden Plattform bringt. Durch ein Anstoßen des Lenkflugkörpers an die Plattform können beide Einheiten ernsthaft beschädigt werden.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. Especially with the complex aerodynamic conditions when dropping it may happen that a control error leads to the just discarded and, for example, not yet driven missile takes a trajectory that brings him on a collision course with the abwerfenden platform. Impacting the missile on the platform can severely damage both units.
Eine Lösung dieses Problems besteht darin, dass der Lenkflugkörper bei Abwurf bis zum Erreichen einer sicheren Entfernung von der Plattform keine Lenkautorität über die Ruder erhält. Diese können durch ein Blockierelement blockiert werden, sodass das fehlerhafte Steuern von einem kollisionsbegründenden Flugmanöver mechanisch unterbunden wird.One solution to this problem is that 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.
Hierbei besteht jedoch das Problem, dass der derart passivierte Lenkflugkörper direkt nach Abwurf dennoch an der beweglichen Plattform anstoßen kann. Dies liegt darin begründet, dass die Umströmung eines den Lenkflugkörper tragenden Flügels der fliegenden Plattform eine unter dem Flügel befindliche Querströmung bewirken kann, die auf den Lenkflugkörper wirkt. Eine solche Querströmung kann durch den Pylon derart gestört werden, dass sich ein Strömungsfeld ausbildet, welches den Lenkflugkörper unsymmetrisch anströmt. Hierdurch wird ein Rollmoment auf den Lenkflugkörper ausgeübt, durch das der Lenkflugkörper in seiner noch an der Plattform befestigten Position mit einem Drehmoment vorgespannt ist. Direkt nach dem Ausklinken kann nun die strömungsbedingte Rollrate derart zunehmen, dass ein Flügel beziehungsweise Ruder des Lenkflugkörpers an den Pylon anschlägt. Der Lenkflugkörper kann beschädigt werden und gegebenenfalls nicht mehr manövrierfähig sein.Here, however, there is the problem that the thus passivated missile can still abut directly on the movable platform after dropping. This is due to the fact that the flow around a wing carrying the missile of the flying platform can cause a cross flow located under the wing, which acts on the missile. Such a transverse flow can be disturbed by the pylon in such a way that a flow field is formed which flows asymmetrically against the guided missile. As a result, a rolling moment is exerted on the missile, by which the missile is biased in its still attached to the platform position with a torque. Immediately after unlatching, the flow-related roll rate can increase in such a way that a wing or rudder of the guided missile strikes against the pylon. The guided missile may be damaged and may no longer be manoeuvrable.
Der Erfindung geht von der weiteren Überlegung aus, dass die Ruder über einen Mischer angesteuert werden können, um Nick-, Gier- und Rollmomente zur Umsetzung von Flugregelungsvorgaben zu erzeugen. Diese hat die jeweiligen Flugkommandos als Eingang und erzeugt daraus die herzustellenden Ruder-Auslenkungen. Es ergibt sich daraus die Gesetzmäßigkeit, dass für die Nick- und Giermomente differenzielle, also nicht einheitliche beziehungsweise gegenläufige Auslenkungen der Ruder notwendig sind. Demgegenüber führen ausschließlich gleichsinnige Auslenkungen zu einer reinen Rollbewegung. Daraus resultiert, dass für eine reine Rollbewegung erheblich kleinere Ruderauslenkungen notwendig sind, als für ein ähnlich starkes Nick- oder Giermanöver. Zudem hat sein Lenkflugkörper aufgrund seiner typischen Form stark differierende Trägheitsmomente. Das Trägheitsmoment um die Rollachse ist erheblich kleiner als die Trägheitsmomente um die Nick- und Gierachse.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. In contrast, only in the same direction deflections lead to a pure rolling motion. As a result, significantly smaller rudder deflections are required for a pure rolling movement than for a similarly strong pitching or yawing maneuver. In addition, 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.
Daraus resultiert, dass eine Rollrate mit erheblich kleineren Momenten auf- oder abgebaut werden können als Raten um die anderen Achsen. Um ein Rollen des Lenkflugkörpers zu steuern, sind daher erheblich kleinere Ruderauslenkungen notwendig, als bei einer gleich starken Steuerung einer Nick- oder Gierbewegung. Bei einem Abwurf reicht es daher aus, wenn die Ruder zur Kompensation der aerodynamisch bewirkten Rollkräfte nur leicht auslenken. Werden die Ruder auf eine solche Auslenkung begrenzt, so kann einem Anstoßen durch ein Rollen ausreichend entgegengewirkt werden und ein unerwünschter Kollisionskurs zur Plattform durch ein fehlerhaftes Nickmanöver des Lenkflugkörpers bei Abwurf wirksam verhindert werden.As a result, a roll rate can be increased or decreased significantly less than rates around the other axes. In order to control a rolling of the missile, therefore, much smaller rudder deflections are necessary, as in an equally strong control of a pitch or yaw. When dropped, it is therefore sufficient if 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.
Durch das erfindungsgemäße Blockierelement kann das Ruder teilentriegelt werden, sodass das Ruder nur über einen Teil seines Ruderausschlags beweglich ist. Hierdurch kann eine unerwünschte Nickbewegung wirksam unterbunden werden. Nach Erreichen der vorgegebenen Flugphase, beispielsweise bei Erreichen eines vorgegebenen Abstands des Lenkflugkörpers zur Plattform, wird das Ruder vollständig freigegeben, sodass der Lenkflugkörper frei steuerbar auf sein vorgegebenes Ziel zu gesteuert werden kann. Durch eine einfache mechanische Maßnahme kann hierdurch sowohl eine Kollision wegen Fehlsteuerung als auch wegen einer querströmungsbedingten Rollbewegung nach Abwurf vermieden werden.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. 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. As a result of 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.
Die fliegende Plattform ist beispielsweise ein Flugzeug oder ein Drehflügler, unter dessen Flügel der Lenkflugkörper während eines Tragflugs hängt. Der Lenkflugkörper weist zweckmäßigerweise vier Flügel in X-Stellung auf, wobei während eines Tragflugs insbesondere zwei der Flügel schräg nach unten und zwei schräg nach oben gerichtet sind.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.
Der Lenkflugkörper kann einen Antriebsmotor aufweisen, der ein Raketentriebwerk oder ein Luft atmender Motor, wie beispielsweise eine Turbine, umfasst. Der Abwurf kann ein Ausklinken und nach unten Abwerfen des Lenkflugkörpers sein oder ein Starten an einer Rampe nach vorne. Der Abwurfprozess umfasst zweckmäßigerweise den gesamten mit einem Abwurf verbundenen Prozess, wie eine Abwurfvorbereitung und den Abwurf an sich, und insbesondere auch eine durch den Abwurf bedingte Flugsteuerungsphase in unmittelbarer Nähe zur Plattform. Die Abwurfvorbereitung kann beispielsweise durch einen Bediener der fliegenden Plattform eingeleitet werden, der den Lenkflugkörper zum Abwurf freigibt. Das Steuern einer Rollbewegung nach Abwurf umfasst zweckmäßigerweise auch das Gegensteuern gegen ein von außen aufgebrachtes Rollmoment, sodass die Resultierende eine zumindest im Wesentlichen verschwindende Rollrate ist.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.
Das mechanische Blockierelement blockiert das Ruder vor dem Abflug des Lenkflugkörpers. Das Ruder ist hierdurch zweckmäßigerweise zumindest im Wesentlichen unbeweglich, also zum Rumpf des Lenkflugkörpers fixiert. Bei der Teilentriegelung ist das Ruder über einen Teil seines Ruderausschlagsbereichs beweglich. Der Ruderausschlagsbereich umfasst zweckmäßigerweise den Ausschlagsbereich, der bei einem regulären Steuerbetrieb des Lenkflugkörpers durch die Lenksteuerung erreicht werden kann. Bei der Teilentriegelung ist der Bereich zweckmäßigerweise auf weniger als 30% des gesamten Ruderausschlagsbereichs begrenzt, insbesondere auf maximal 20%.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. During partial unlocking, 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. In the case of partial unlocking, the area is expediently limited to less than 30% of the total rudder deflection range, in particular to a maximum of 20%.
Hat der Lenkflugkörper den Nahbereich zur fliegenden Plattform verlassen, so tritt er in die vorgegebene Flugphase ein, in der das Ruder vollständig entriegelt wird. Die vorgegebene Flugphase kann beginnen, wenn der Lenkflugkörper beispielsweise einen Mindestabstand von der Plattform oder eine Mindestzeit nach dem Abwurf beziehungsweise Ausklinken geflogen beziehungsweise gefallen ist.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.
Generell ist das Blockierelement zweckmäßigerweise mit einem Antrieb verbunden, der es entlang einer vorgegebenen Bahn bewegt. Die Bewegung des Blockierelements wird zweckmäßigerweise von einer Steuereinheit gesteuert, die den Antriebt steuert.In general, 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.
Zweckmäßigerweise sind alle in gleicher axialer Position des Lenkflugkörpers vorhandenen Ruder, bei einer X-Stellung also alle vier Ruder, mit einem erfindungsgemäßen Blockierelement ausgestattet, sodass bei allen Rudern eine erfindungsgemäße Teilfreigabe ermöglicht ist. Die Teilfreigabe kann für alle Ruder gleichwirkend sein, sodass der momentan mögliche Ruderausschlagsbereich für alle Ruder einer Gruppe, also alle Ruder in gleicher axialer Position am Lenkflugkörper, gleich ist.Conveniently, 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.
In einer vorteilhaften Ausführungsform der Erfindung greift das Blockierelement in das Ruder ein und wird zum Entriegeln aus dem Ruder herausbewegt. Anstelle oder zusätzlich zu einem Eingreifen kann das Blockierelement von außen an das Ruder angelegt werden, beispielsweise an einer Hinterkante des Ruders. Zum teilweisen oder vollständigen Entriegeln kann das Blockierelement nach radial innen, in Tangentialrichtung, in Axialrichtung oder in einer Kombination von zwei oder mehr Richtungskomponenten vom Ruder entfernt werden. Ebenfalls ist es möglich, dass das Blockierelement um die Hinterkante des Ruders herumgeführt ist und zur Entriegelung nach hinten, also in Axialrichtung des Lenkflugkörpers von der Hinterkante entfernt wird. Bei einem Entfernen des Blockierelements vom Ruder entfernt sich zumindest ein Teil des Blockierelements vom Ruder, das Blockierelement fährt beispielsweise ganz oder teilweise aus dem Ruder heraus.In an advantageous embodiment of the invention, the blocking element engages in the rudder and is moved out of the rudder for unlocking. Instead of or in addition to an intervention, the blocking element can be applied from the outside to the rudder, for example at a trailing edge of the rudder. For partial or complete unlocking, 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. When 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.
Wenn das Blockierelement in das Ruder eingreift, um dieses ganz oder teilweise zu blockieren, besteht die Möglichkeit, dass es von radial innen eingreift, also in Radialrichtung des Lenkflugkörpers von innen nach außen. Zum Entriegeln kann das Blockierelement nun zumindest überwiegend in Radialrichtung nach innen aus dem Ruder herausbewegt werden. Je nach Anwendung kann es auch vorteilhaft sein, dass das Blockierelement zum Entriegeln zumindest überwiegend in Axialrichtung aus dem Ruder herausbewegt wird.If 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. Depending on the application, 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.
Eine weitere vorteilhafte Ausführungsform der Erfindung sieht vor, dass eine Formschlusskulisse von Blockierelement und Ruder zueinander zumindest zweifach gestuft ist. Die Stufe kann durch eine Stufe im Blockierelement und/oder durch eine Stufe im Ruder gebildet sein. Das Blockierelement wird nun zweckmäßigerweise diskret von einer Blockierstellung in eine teilentriegelte Stellung bewegt und von dort in eine Freigabestellung. Hierbei ist es zweckmäßig, wenn das Blockierelement in der teilentriegelten Stellung ruhend verharrt bis es dann, zweckmäßigerweise sprunghaft, in die Freigabestellung bewegt wird. Hierdurch kann definiert eine Teilfreigabe, also eine Freigabe eines definierten Teils des gesamten Ruderausschlagsbereichs, erfolgen. Eine Bewegung von einer Stufe zur nächsten dauert hierbei zweckmäßigerweise weniger als ein Drittel der Zeit, in der das Blockierelement in der teilentriegelten Stellung ruhend verharrt. Die Bewegung des Blockierelements von Stellung zu Stellung geschieht insofern zweckmäßigerweise schnell, beispielsweise jeweils innerhalb von weniger als 0,5 Sekunden.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.
Bei einer schnellen Bewegung des Blockierelements besteht die Möglichkeit, dass das Blockierelement durch eine Fehlsteuerung zu schnell in seine Freigabestellung bewegt wird. Das Ruder ist vollständig entriegelt und Fehlsteuerungen, beispielsweise auf einen Kollisionskurs mit der abwerfenden Plattform, sind möglich. Um dies zu vermeiden, ist es vorteilhaft, wenn der Antrieb des Blockierelements so ausgeführt ist, dass er das Blockierelement nur langsam von der blockierenden Stellung über die teilentriegelte Stellung zur Freigabestellung bewegt, beispielsweise insgesamt über einen Zeitraum von mindestens zwei Sekunden, insbesondere zumindest fünf Sekunden. Der Antrieb ist jeweils zweckmäßigerweise so konstruiert, dass eine schnellere Entriegelungsbewegung nicht möglich ist. Eine zu schnelle Entriegelung und damit die Gefahr eines Kollisionskurses wird somit unterbunden.In a rapid movement of the blocking element, there is the possibility that the blocking element is moved by a faulty control too quickly in its release position. The rudder is fully unlocked and mismanagement, for example on a collision course with the launching platform, is possible. To avoid this, it is advantageous if 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.
Insbesondere bei einer kontinuierlichen Bewegung des Blockierelements ist es von Vorteil, wenn das Blockierelement das Ruder durch ein Entfernen vom Ruder kontinuierlich von der blockierten Stellung zur vollständigen Stellung wieder freigibt. Der Teil des Ruderausschlagsbereichs, über den das Ruder beweglich ist, wird somit über die Zeit kontinuierlich größer, zumindest im Wesentlichen linear kontinuierlich größer. Um dies zu erreichen, ist zweckmäßigerweise eine kontinuierliche Formschlusskulisse von Blockierelement und Ruder zueinander vorhanden.In particular, in a continuous movement of the blocking element, it is advantageous if 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. To achieve this, it is expedient to provide a continuous form-fitting backdrop of blocking element and rudder to one another.
Im Tragflug und im Moment des Abwurfs wird der Lenkflugkörper in der Regel asymmetrisch von der Seite angeströmt, sodass auf ihn ein Rollmoment wirkt. Auch wenn dieses Rollmoment abhängig sein kann von einem momentan von der fliegenden Plattform geflogenen Flugmanöver, also in seiner Größe variabel ist, wird es im Regelfall nur in eine Richtung gerichtet sein. Es ist daher in vielen Fällen bei einem Abwurf ausreichend, dem Rollmoment nur in eine Richtung entgegenzuwirken. Um dies zu erreichen ist es vorteilhaft, wenn das Ruder in der teilentriegelten Stellung asymmetrisch freigegeben ist, sodass der maximale freigegebene Ruderausschlag in eine Richtung größer ist als in die andere Richtung. Richtungsbezogen kann der Ruderausschlag ausgehend von einer Mittenstellung betrachtet werden.In the wing flight and the moment of the ejection of the missile is usually flowed asymmetrically from the side, so acting on him a roll moment. Even if this rolling moment can be dependent on a flight maneuver currently being flown by the flying platform, ie is variable in its size, it will as a rule only be directed in one direction. It is therefore sufficient in many cases in a drop, counteract the rolling moment in one direction only. To achieve this, it is advantageous if the rudder is released asymmetrically in the partially unlocked position, so that the maximum released rudder deflection in one direction is greater than in the other direction. Directional, the rudder deflection can be viewed from a center position.
Die Erfindung ist außerdem gerichtet auf ein Verfahren zum Steuern eines Lenkflugkörpers, bei dem ein Ruder des Lenkflugkörpers durch eine Steuermechanik lenkend bewegt wird und der Flug des Lenkflugkörpers hierdurch gesteuert wird.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.
Zweckmäßigerweise wird das Ruder in eine Ruderhartlage gebracht, in der das Ruder also in einer maximalen Auslenkung ausgerichtet ist, beispielsweise an einem Anschlag anliegt. Dort kann das Ruder nun verharren. Eine Ruderhartlage kann dann sinnvoll sein, wenn der Lenkflugkörper stark abgebremst werden soll oder definiert zum Absturz gebracht werden soll, beispielsweise bei einem Manöverabbruch.Conveniently, 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.
Bei einem Flug eines Lenkflugkörpers kann es vorkommen, dass der Flug des Lenkflugkörpers abgebrochen oder stark abgebremst werden soll. Beispielsweise soll der Lenkflugkörper bei einem Testschuss nicht eine vorgegebene Sicherheitszone verlassen. Oder eine Signalverbindung zwischen fliegender Plattform und Lenkflugkörper bricht ab oder ist gestört, sodass eine Fehlleitung des Lenkflugkörpers zu befürchten ist. Oder der Lenkflugkörper ist auf ein falsches Ziel aufgeschaltet und ein Angriff soll schnellstmöglich abgebrochen werden. Im Prinzip kann ein solcher Manöverabbruch auch von der Steuereinheit eingeleitet werden, die den regulären Flug des Lenkflugkörpers steuert. Es kann jedoch vorkommen, dass die Steuereinheit defekt, nicht erreichbar oder nicht schnell genug handlungsfähig ist, beispielsweise wenn der Lenkflugkörper auf ein falsches Ziel aufgeschaltet ist und eine Weile brauchen würde, um dies zu "verstehen". Es ist daher vorteilhaft, ein System zur Verfügung zu haben, mit dem ein Flugabbruch mit einfachen Mitteln erreicht werden kann.During 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. In principle, such 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 "understand". It is therefore advantageous to have a system with which a flight termination can be achieved with simple means.
Diese Aufgabe wird durch ein Verfahren zum Steuern eines Lenkflugkörpers wie oben beschrieben gelöst, bei dem erfindungsgemäß das Ruder durch ein zur Steuermechanik zusätzliches Blockierelement in die Ruderhartlage gedrückt und/oder in der Ruderhartlage gehalten wird. Hierdurch kann eine reguläre Steuerung durch die Steuereinheit unter Umständen übersteuert werden, sodass das Ruder in seiner Ruderhartlage verbleibt. Je nach Kräftewirksamkeit und Steueralgorithmen kann zudem ein Manöverabbruch auch entgegen den Kommandos der regulären Steuereinheit erwirkt werden.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. As a result, a regular control by the control unit may be overridden, so that the rudder remains in its Ruderhartlage. Depending on the force effectiveness and control algorithms, a maneuver abort may also be obtained contrary to the commands of the regular control unit.
Das Blockierelement kann vorteilhafterweise eine Doppelfunktion innehaben: Es kann das Ruder im Abwurfprozess entriegeln, wobei eine Teilentriegelung als Zwischenschritt durchlaufen wird, und es kann das Ruder in die Ruderhartlage bringen und/oder dort halten. Insofern können vorteilhafterweise sämtliche Details des Verfahrens zum Abwurf eines Lenkflugkörpers von einer fliegenden Plattform auch mit dem Verfahren zum Steuern eines Lenkflugkörpers kombiniert werden und vice versa.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. In this respect, advantageously, 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.
In einer vorteilhaften Ausführungsform der Erfindung bewegt das Blockierelement durch seine Bewegung in eine Hartlagenposition das Ruder in eine Ruderhartlage hinein. Hierdurch kann beispielsweise ein Steuerungsvorgang der regulären Steuereinheit übersteuert werden und ein zuverlässiges Abbremsen oder Abstürzen des Lenkflugkörpers erreicht werden. Vorteilhafterweise wird die Bewegung des Blockierelements in seine Hartlagenposition mit einem Algorithmus gesteuert, der zusätzlich zu einem Algorithmus zur regulären Lenksteuerung des Lenkflugkörpers vorhanden ist. Die Bewegung des Blockierelements in seine Hartlagenposition kann durch ein Sondersignal getriggert werden, beispielsweise ein Signalabbruch von oder zu einem übergeordneten Steuersystem, wie der fliegenden Plattform. Das Sondersignal kann jedoch auch gezielt gesendet werden, um einen schnellen Manöverabbruch zu erreichen.In an advantageous embodiment of the invention, 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. Advantageously, 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. However, the special signal can also be sent specifically to achieve a quick maneuver abort.
Weiter ist es vorteilhaft, wenn das Blockierelement bei seiner Bewegung in eine Hartlagenposition eine Kulisse durchläuft, durch die die Bewegung des Blockierelements in eine Ruderbewegung in die Ruderhartlage des Ruders umgesetzt wird. Die Ruderhartlage kann auf diese Weise auf einfachen mechanischen Mitteln zuverlässig erreicht werden.Further, it is advantageous if 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.
Ein Manöverabbruch erfolgt zweckmäßigerweise erst nach einem gewissen Eigenflug des Lenkflugkörpers. Es ist insofern vorteilhaft, wenn das Blockierelement von seiner Freigabestellung in seine Hartlagenposition bewegt wird und dort das Ruder in der Ruderhartlage hält. Hierbei kann das Blockierelement beim Bewegen von der Freigabestellung in die Hartlagenposition die Blockierstellung durchlaufen, die also zwischen der Freigabestellung und der Hartlagenposition liegt. Ebenfalls ist es möglich, dass die Hartlagenposition des Blockierelements in Bezug auf eine Freigabestellung entgegen einer Blockierstellung liegt. Hierbei würde also die Freigabestellung zwischen einer Blockierstellung und einer Hartlagenposition liegen.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.
Es kann sein, dass das Ruder zum Zeitpunkt eines Manöverabbruchs bereits weit ausgeschlagen ist. Gegebenenfalls ist dann eine Kulissensteuerung des Ruders in seine Hartlagenposition nicht möglich. Insofern ist es ebenfalls vorteilhaft, wenn das Blockierelement beim Bewegen in die Hartlagenposition das Ruder von außen in die Ruderhartlage drückt.It may be that the rudder is already worn out at the time of a maneuver crash. Optionally, then a backdrop control of the rudder in its hard position is not possible. In this respect, it is also advantageous if the blocking element presses the rudder from the outside in the Ruderhartlage when moving into the hard position.
Weiter ist die Erfindung gerichtet auf ein Rudersystem für einen Abwurf-Lenkflugkörper gemäß den Merkmalen von Patentanspruch 14, welches ein statisches System zur Fixierung im Lenkflugkörper und ein zum statischen System bewegliches Ruder umfasst.Further, the invention is directed to a rudder system for a launch missile according to the features of
Es wird vorgeschlagen, dass das statische System erfindungsgemäß ein Blockierelement und einen Antrieb zum Bewegen des Blockierelements aufweist, wobei das Blockierelement und das Ruder so zueinander angeordnet sind, dass das Blockierelement das Ruder mechanisch fixiert und das Ruder nach einem Bewegen des Blockierelements durch den Antrieb teilentriegelt ist und nur über einen Teil seines Ruderausschlagsbereichs beweglich ist.It is proposed that 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 teilentriegelt the rudder after moving the blocking element by the drive is and is movable only over part of its rudder range.
Zweckmäßig ist es, wenn das Ruder nach einer weiteren Bewegung des Blockierelements vollständig entriegelt ist, sodass es über seinen gesamten Ruderausschlagsbereich beweglich ist. Ein Abwurf-Lenkflugkörper kann hierbei ein Lenkflugkörper sein, der von einer fliegenden Plattform abgeworfen wird, beispielsweise nach unten oder bei einem selbständigen Start nach vorne.It is expedient if the rudder is completely unlocked after a further movement of the blocking element, so that it is movable over its entire rudder deflection 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.
Die bisher gegebene Beschreibung vorteilhafter Ausgestaltungen der Erfindung enthält zahlreiche Merkmale, die teilweise in einigen abhängigen Ansprüchen zu mehreren zusammengefasst wiedergegeben sind. Die Merkmale können jedoch zweckmäßigerweise auch einzeln betrachtet und zu sinnvollen weiteren Kombinationen zusammengefasst werden, insbesondere bei Rückbezügen von Ansprüchen, sodass ein einzelnes Merkmal eines abhängigen Anspruchs mit einem einzelnen, mehreren oder allen Merkmalen eines anderen abhängigen Anspruchs kombinierbar ist. Außerdem sind diese Merkmale jeweils einzeln und in beliebiger geeigneter Kombination sowohl mit den erfindungsgemäßen Verfahren als auch mit der erfindungsgemäßen Vorrichtung gemäß den unabhängigen Ansprüchen kombinierbar. So sind Verfahrensmerkmale auch als Eigenschaften der entsprechenden Vorrichtungseinheit gegenständlich formuliert zu sehen und funktionale Vorrichtungsmerkmale auch als entsprechende Verfahrensmerkmale.The description given herein of advantageous embodiments of the invention includes numerous features, some of which are set forth in several of the appended claims. However, the features may conveniently be considered individually and grouped together into meaningful further combinations, in particular when reclaiming claims so that a single feature of a dependent claim can be combined with a single, several or all features of another dependent claim. In addition, these features can be combined individually and in any suitable combination both with the inventive method and with the device according to the invention according to the independent claims. Thus, process features can also be formulated formally as properties of the corresponding device unit and functional device features also as corresponding process features.
Die oben beschriebenen Eigenschaften, Merkmale und Vorteile dieser Erfindung sowie die Art und Weise, wie diese erreicht werden, werden klarer und deutlicher verständlich in Zusammenhang mit der folgenden Beschreibung der Ausführungsbeispiele, die im Zusammenhang mit den Zeichnungen näher erläutert werden. Die Ausführungsbeispiele dienen der Erläuterung der Erfindung und beschränken die Erfindung nicht auf die darin angegebene Kombination von Merkmalen, auch nicht in Bezug auf funktionale Merkmale. Außerdem können dazu geeignete Merkmale eines jeden Ausführungsbeispiels auch explizit isoliert betrachtet, aus einem Ausführungsbeispiel entfernt, in ein anderes Ausführungsbeispiel zu dessen Ergänzung eingebracht und/oder mit einem beliebigen der Ansprüche kombiniert werden.The above-described characteristics, features, and advantages of this invention, as well as the manner in which they are achieved, will become clearer and more clearly understood in connection with the following description of the embodiments, which will be described in detail in conjunction with the drawings. The embodiments serve to illustrate the invention and do not limit the invention to the combination of features specified therein, not even in Reference to functional characteristics. In addition, suitable features of each embodiment may also be explicitly considered isolated, removed from one embodiment, incorporated into another embodiment to complement it, and / or combined with any of the claims.
Es zeigen:
- FIG 1
- einen Lenkflugkörper unter einem Flügel einer fliegenden Plattform,
- FIG 2
- den Lenkflugkörper in einer schematischen Ansicht von vorne,
- FIG 3
- einen Flügel des Lenkflugkörpers mit einem Ruder,
- FIG 4
- die Hinterkante eines Ruders mit einem dahinter und um die Ruderkante angeordneten Blockierelement,
- FIG 5
- ein schematisch angedeutetes Ruder mit einem von radial innen in das Ruder eingreifenden Blockierelement,
- FIG 6
- ein hinsichtlich der ermöglichten Ruderausschläge asymmetrisches Blockierelement,
- FIG 7
- ein gestuftes Blockierelement,
- FIG 8
- ein Blockierelement in einer gestuften Ausnehmung eines Ruders,
- FIG 9
- ein asymmetrisch einseitig gestuftes Blockierelement,
- FIG 10
- die Hinterkante eines Ruders eines Lenkflugkörpers mit einer Kulisse, in die ein Blockierelement von radial innen eingreift,
- FIG 11
- das Ruder in einer Ruderhartlage, durch die es vom Blockierelement in der Kulisse gedrückt wird,
- FIG 12
- das Ruder mit einem Ruderausschlag, der es vom Blockierelement weg bewegt,
- FIG 13
- das Ruder, das vom außerhalb des Ruders abgeordneten Blockierelement in seiner Ruderhartlage gedrückt wird,
- FIG 14
- ein Ruder mit einer Kulisse, in der eine Hartlagenposition eines Blockierelements gegenüber einer Blockierstellung des Blockierelements liegt,
- FIG 15
- das Ruder in seiner Hartlagenposition,
- FIG 16
- ein Ruder, das von einem Blockierelement wie aus
FIG 4 von außen in eine Ruderhartlage gedrückt wird, und - FIG 17
- ein Ruder, das von einem Blockierelement ähnlich zu
FIG 5 von außen in eine Ruderhartlage gedrückt wird.
- FIG. 1
- a guided missile under a wing of a flying platform,
- FIG. 2
- the guided missile in a schematic view from the front,
- FIG. 3
- a wing of the guided missile with a rudder,
- FIG. 4
- the trailing edge of a rudder with a blocking element behind and around the rudder edge,
- FIG. 5
- a schematically indicated rudder with a radially inwardly engaging in the rudder blocking element,
- FIG. 6
- an asymmetrical blocking element with regard to the permitted rudder deflections,
- FIG. 7
- a stepped blocking element,
- FIG. 8
- a blocking element in a stepped recess of a rudder,
- FIG. 9
- an asymmetrically one-sided stepped blocking element,
- FIG. 10
- the trailing edge of a rudder of a guided missile with a gate into which a blocking element engages from radially inside,
- FIG. 11
- the rudder in a rudder hard position, by which it is pressed by the blocking element in the scenery,
- FIG. 12
- the rudder with a rudder stroke that moves it away from the blocking element,
- FIG. 13
- the rudder, which is pressed in its rudder hard position by the blocking element which is separated from outside the rudder,
- FIG. 14
- a rudder with a link in which a hard-ply position of a blocking element lies opposite a blocking position of the blocking element,
- FIG. 15
- the rudder in its hard position,
- FIG. 16
- a rudder that looks like a blocking element
FIG. 4 pressed from the outside in a Ruderhartlage, and - FIG. 17
- a rudder similar to that of a blocking element
FIG. 5 pressed from the outside in a Ruderhartlage.
Bei einem Abwurf des Lenkflugkörpers 2 von der fliegenden Plattform 4 bewirkt das Rollmoment 18 eine Rollbeschleunigung auf den Lenkflugkörper 2, die dazu führen kann, dass der Lenkflugkörper 2 am Pylon 8 anschlägt, insbesondere mit einem Lenkflügel 14, wobei insbesondere eine Beschädigung eines Ruders 12 und damit eine Beeinträchtigung der Manövrierfähigkeit des Lenkflugkörpers 2 droht. Um einer solchen Beschädigung entgegenzuwirken, vollführt der Lenkflugkörper 2 zweckmäßigerweise bereits während des Abwurfprozesses vor dem Abwurf beziehungsweise Ausklinken aus dem Pylon 8 eine Lenkbewegung mit seinen Rudern 12, die dem Rollmoment 18 entgegenwirken.In a drop of the
Ist eine Steuerung der Ruderstellungen des Lenkflugkörpers 2 bei Abwurf durch irgendeinen Vorgang beeinträchtigt, so würde ein fehlerhaft aufgebrachtes Nickmoment auf den Lenkflugkörper 2 nach oben zu dessen Kollision mit der Plattform 4 führen. Um einer solchen Fehlsteuerung entgegenzuwirken, ist jedem Ruder 12 ein Blockierelement 24 (
In den Ausführungsbeispielen sind im Wesentlichen gleichbleibende Bauteile mit den gleichen Bezugszeichen beziffert. Zum einfacheren Verständnis sind außerdem gleiche Bauteile in verschiedenen Ausführungsbeispielen mit den gleichen Bezugsziffern und anderen Bezugsbuchstaben bezeichnet, wobei sie identisch zueinander oder mit geringfügigen Unterschieden zueinander sein können, zum Beispiel in Abmessung, Form, Position und/oder Funktion. Wird die Bezugsziffer alleine ohne einen Bezugsbuchstaben erwähnt, so sind die entsprechenden Bauteile aller Ausführungsbeispiele angesprochen.In the exemplary embodiments, substantially identical components are numbered with the same reference numerals. For ease of understanding, moreover, 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.
In
Vor, während oder nach dem Abwurf, also dem Ausklinken des Lenkflugkörpers vom Pylon 8, zweckmäßigerweise während eines Abwurfprozesses und insbesondere noch vor Abwurf, bewegt der Antrieb 32 das Blockierelement 24a axial nach hinten in eine Abwurfstellung, die in der mittleren Darstellung von
Bei der mittleren Darstellung aus
Zur Steuerung der Stellungen des Blockierelements 24 bestehen generell verschiedene Möglichkeiten.To control the positions of the blocking
In einer ersten Möglichkeit wird das Blockierelement 24 in eine Abwurfstellung bewegt, die einen ausreichenden Ruderausschlag freigibt, um einen kollisionsfreien Abwurf des Lenkflugkörpers 2 zu garantieren. Während des Abwurfs und einer hernach folgenden Abwurfphase verbleibt das Blockierelement 24 in dieser Abwurfstellung. Hat der Lenkflugkörper 2 eine vorgegebene Flugphase erreicht, beispielsweise einen ausreichenden Abstand von der Plattform 4, so wird durch eine weitere Bewegung des Blockierelements 24 das Ruder 12 vollständig freigegeben, wie beispielhaft in der rechten Abbildung von
Eine weitere Möglichkeit besteht darin, dass der Ruderausschlag kontinuierlich freigegeben wird. Während des Abwurfprozesses des Lenkflugkörpers wächst insofern der Teil 42 kontinuierlich an. Dies kann durch eine kontinuierliche Bewegung des Blockierelements 24 geschehen, das hierdurch einen stetig wachsenden Teil 42 freigibt, wie beispielhaft aus der mittleren Darstellung aus
Bei dem in
Das Ausführungsbeispiel aus
Bei den Ausführungsbeispielen der
Bei dem Ausführungsbeispiel aus
Bei dem Ausführungsbeispiel aus
Das Ausführungsbeispiel aus
Bei den Ausführungsbeispielen der
Die Kulisse 52 ist zur Blockierstellung hin verengend ausgeführt, sodass das Blockierelement 24g beim Hineinführen in das Ruder 12 dieses immer weiter blockiert. Die Kulisse 52 bildet einen inneren Kanal 54, der in seinen Abmessungen so ausgeführt ist, dass das Blockierelement 24g im Kanal befindlich das Ruder 12 vollständig blockiert. Nach hinten hin, also in Richtung zur Hinterkante 40 des Ruders 12, weitet sich der Kanal 54 auf, sodass in der mittleren, teilentriegelten Stellung das Ruder 12 über einen Teil 42 des gesamten Ruderausschlagsbereichs 44 beweglich ist. In der Freigabestellung kann das Ruder 12 in beide Ruderausschlagsrichtungen vollständig über das Blockierelement 24g hinweg fahren, sodass dieses, auch wenn es noch aus dem Rumpf 22 herausragt, das Ruder 12 nicht mehr blockiert sondern dieses vollständig entriegelt ist.The gate 52 is designed to narrow the blocking position, so that the blocking
Vom Prinzip her kann der Kanal 54 dort enden, wo das Blockierelement 24g seine Blockierstellung einnimmt. Bei dem Beispiel aus
Bei dem in
Es kann sein, dass es sinnvoll ist, das Ruder 12 während des Flugs des Lenkflugkörpers 2 in seine Ruderhartlage zu bringen, beispielsweise um den Lenkflugkörper 2 schnellstmöglich abzubremsen oder ihn zum Absturz zu bringen. Dies kann erreicht werden, indem das Blockierelement 24g den Kanal 54 bis zu dessen Ende beziehungsweise bis zur Hartlagenposition des Blockierelements 24g durchfährt. Bei dem Ausführungsbeispiel aus
Dieses Beispiel ist in
Das Ausführungsbeispiel aus den
Ähnlich ist es bei dem Ausführungsbeispiel aus
Anhand der Ruderbreite und des Ruderausschlags ist ersichtlich, dass das Blockierelement 24h beziehungsweise die Ausnehmungen 56, 58 relativ weit vorne, also nahe der Ruderdrehachse 46 liegen sollten, in der die Außenkante des Ruders 12 in Hartlagenstellung nicht weit von der Symmetrieebene des Ruders 12 in seiner Mittenstellung entfernt sein sollte. Auch hier drückt das Blockierelement 24h das Ruder 12 bei einem Ausfahren in Richtung zur Blockierstellung in seine Ruderhartlage. Bei dem in
Bei den Ausführungsbeispielen der
- 22
- LenkflugkörperMissile
- 44
- Plattformplatform
- 66
- KoppeleiriheitKoppeleiriheit
- 88th
- Pylonpylon
- 1010
- Triebwerkengine
- 1212
- Ruderrudder
- 1414
- Lenkflügelsteering wings
- 1616
- Querströmungcrossflow
- 1818
- Rollmomentroll moment
- 2020
- Flügelwing
- 2222
- Rumpfhull
- 24a-h24a-h
- Blockierelementblocking element
- 2626
- Rudersystemrudder system
- 2828
- Steuereinheitcontrol unit
- 3030
- Aktuatoractuator
- 3232
- Antriebdrive
- 3434
- Radialrichtungradial direction
- 3636
- Axialrichtungaxially
- 3838
- statisches Systemstatic system
- 4040
- Hinterkantetrailing edge
- 4242
- Teilpart
- 4444
- RuderausschlagsbereichRudder area
- 4646
- Drehachseaxis of rotation
- 4848
- Ausnehmungrecess
- 50a-c50a-c
- FormschlusskulisseForm-fitting backdrop
- 52a-b52a-b
- Kulissescenery
- 5454
- Kanalchannel
- 5656
- Ausnehmungrecess
- 5858
- Ausnehmungrecess
Claims (14)
- Method for ejecting a guided missile (2) from a flying platform (4), in which the guided missile (2) is ejected from the flying platform (4) and executes a rolling movement about its longitudinal axis by means of at least one movable rudder (12),
characterized
in that the rudder (12) is blocked by a mechanical blocking element (24) prior to ejection, the rudder (12) is partially unlocked by a movement of the blocking element (24) in the course of an ejection process, with the result that the rudder (12) is movable only over a part (42) of its rudder deflection range (44), and, after reaching a predetermined flight phase of the guided missile (2), the blocking element (24) completely unlocks the rudder (12), with the result that it is movable over its entire rudder deflection range (44). - Method according to Claim 1,
characterized
in that the blocking element (24b-h) engages in the rudder (12) and is moved out of the rudder (12) for unlocking. - Method according to Claim 1 or 2,
characterized
in that the blocking element (24g) engages from radially inward in the radial direction (34) outwardly into the rudder (12) and is moved out of the rudder (12) at least predominantly in the axial direction (36) for unlocking. - Method according to one of the preceding claims,
characterized
in that a form-fitting slotted link (50) between blocking element (24d-f) and rudder (12) is at least doubly stepped, with the result that the blocking element (24d-f) holds the rudder (12) in the blocked state with a blocking step, is then moved into the partially unlocked position and holds the rudder (12) partially unlocked there with a partial-blocking step, remains there in a stationary manner and is then moved into a release position and thereby completely unlocks the rudder (12). - Method according to one of Claims 1 to 3,
characterized
in that the blocking element (24a-c, 24g-h) further releases the rudder (12) by moving away from the rudder (12) continuously from the blocked position to the completely unlocked position. - Method according to one of the preceding claims,
characterized
in that the rudder (12) is released asymmetrically in the partially unlocked position, with the result that the maximum released rudder deflection is greater in one direction than in the other direction. - Method according to one of the preceding claims,
characterized
in that the rudder (12) is moved in a guided manner by a rudder system (26) and the flight of the guided missile (2) after ejection is thereby controlled and the rudder (12) is then brought into a hard rudder position in which the rudder (12) is at a maximum deflection, and remains there, wherein the rudder (12) is held in the hard rudder position by the blocking element (24) which is additional to the rudder system (26). - Method according to one of the preceding claims,
characterized
in that the blocking element (24), by its movement into a hard position, moves the rudder (12) into a hard rudder position. - Method according to one of the preceding claims,
characterized
in that, during its movement into a hard position, the blocking element (24g) runs through a slotted link (52) by means of which the movement of the blocking element is converted into a rudder movement into the hard rudder position of the rudder (12). - Method according to one of the preceding claims,
characterized
in that the blocking element (24) is moved from its release position into its hard position and holds the rudder (12) there in the hard rudder position. - Method according to Claim 10,
characterized
in that, during movement from the release position into the hard position, the blocking element (24g) runs through the blocking position. - Method according to Claim 10,
characterized
in that the hard position of the blocking element (24g) relative to a release position lies counter to a blocking position. - Method according to one of the preceding claims,
characterized
in that, during movement into the hard position, the blocking element (24) presses the rudder (12) from outside into the hard rudder position. - Rudder system (26) for an ejection guided missile (2) having a static system (38) for fixing in the guided missile (2) and having a rudder (12) which is movable with respect to the static system (38), wherein the static system (38) has a blocking element (24) and a drive (32) for moving the blocking element (24) and a control unit (28) for controlling the drive (32), wherein the blocking element (24) and the rudder (12) are arranged with respect to one another in such a way that the blocking element (24) mechanically fixes the rudder (12), and the rudder (12) is partially unlocked after a movement of the blocking element (24) by the drive (32) and is movable only over a part (42) of its rudder deflection range (44) and, after a further movement of the blocking element (24), is completely unlocked, with the result that it is movable over its entire rudder deflection range (44),
characterized
in that the control unit (28) is designed in such a way that it controls the drive (32) such that the rudder (12) is partially unlocked in the course of an ejection process of the ejection guided missile (2) and is completely unlocked only after reaching a predetermined flight phase of the ejection guided missile (2).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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DE102016009384.6A DE102016009384B4 (en) | 2016-08-02 | 2016-08-02 | Method for dropping a guided missile from a flying platform |
Publications (2)
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EP3279605A1 EP3279605A1 (en) | 2018-02-07 |
EP3279605B1 true EP3279605B1 (en) | 2019-03-13 |
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EP17001259.5A Active EP3279605B1 (en) | 2016-08-02 | 2017-07-24 | Method for ejection of a guided missile from a flying platform |
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EP (1) | EP3279605B1 (en) |
DE (1) | DE102016009384B4 (en) |
Families Citing this family (2)
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CN109703777B (en) * | 2018-10-26 | 2022-04-19 | ä¸å›½é£žè¡Œè¯•éªŒç ”究院 | Control surface blocking system for fly test of telex transport type airplane |
US11293729B2 (en) * | 2019-01-31 | 2022-04-05 | Saab Ab | Rudder control assembly for a missile |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2452053A1 (en) * | 1974-11-02 | 1976-05-06 | Dornier Gmbh | DEVICE FOR LAUNCHING ROCKET-PROPELLED AIRCRAFT |
DE3222378A1 (en) * | 1982-06-15 | 1983-12-15 | Dynamit Nobel Ag, 5210 Troisdorf | Device for reducing the sensitivity to lateral onflow of tail-stabilised combat bodies moving in air and/or water |
GB9003260D0 (en) * | 1990-02-13 | 1990-11-21 | Normalair Garrett Ltd | Lock means for missile control fins |
US5141175A (en) * | 1991-03-22 | 1992-08-25 | Harris Gordon L | Air launched munition range extension system and method |
US6450444B1 (en) * | 2000-08-02 | 2002-09-17 | Raytheon Company | Fin lock system |
FR2919269B1 (en) * | 2007-07-25 | 2010-01-01 | Rafaut & Cie | DEVICE FOR MOUNTING AN ARMING HALF CONNECTING A LARGEABLE LOAD TO A FIXED EMPLOYMENT SYSTEM UNDER AN AIRCRAFT. |
DE102008034618B4 (en) * | 2008-07-25 | 2015-05-13 | Mbda Deutschland Gmbh | A method of uncoupling an unmanned missile from a carrier aircraft |
DE102012016093B3 (en) * | 2012-08-14 | 2014-02-13 | Mbda Deutschland Gmbh | Method for determining flight conditions and parameters of exit arrangement allowed for dropping external load from aircraft, involves executing test flights with different flight conditions and determining flight condition data |
-
2016
- 2016-08-02 DE DE102016009384.6A patent/DE102016009384B4/en active Active
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2017
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DE102016009384A1 (en) | 2018-02-08 |
EP3279605A1 (en) | 2018-02-07 |
DE102016009384B4 (en) | 2019-10-31 |
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