DE3222378A1 - Device for reducing the sensitivity to lateral onflow of tail-stabilised combat bodies moving in air and/or water - Google Patents

Abstract

The device for reducing the sensitivity to lateral onflow of tail-stabilised combat bodies moving in air and/or water, in which the combat body is equipped with a nose cone having at least one destabilising fin which acts as an additional tail surface and which can be swung out of the contour of the nose cone at a predetermined first moment and swung in again or discarded at a predetermined second moment. The attached nose cone can additionally serve for influencing the range.

Description

Device for reducing sensitivity

Bitwork stabilized war body moving in air and / or water against lateral flow The invention relates to a device of the im Preamble of claim 1 specified type.

For stabilizing missiles moving in the air, in particular Missiles, but also, for example, flare missiles and projectiles, and those moving in water War bodies are known to tail units. The stabilizing effect of a tail unit comes about that the tail unit when rotating the missile from the flight direction a backward turning moment is generated, which acts until the missile is turned back in the direction of flight.

This turning back, the disturbance eliminating moment around the missile's center of gravity comes about because the wing behind the center of gravity of the missile, i.e. in its Rear area is attached and as a result of the deflection acts as a wing from the direction of flight. Is the buoyancy, i.e. the stability large, the disturbance is eliminated quickly; if it is small, compensation takes place the disturbance only slowly. If the tail unit lift is insufficient, the Deviation from the flight direction until the missile "erupts" after a certain time and the missile longitudinal axis is rotated by 90 ° to the direction of flight.

If the longitudinal stability is high, there will be a momentary deviation from the flight direction quickly eliminated, however, disadvantageously, for example, also with wind on the ground, i.e. here in the case of wind components that do not act in the direction of flight. This should be done using the example of Seen in the direction of flight, from the left acting crosswind are made clear. This Wind causes the missile no longer axially, but under a (usually small) angle from the left with the resulting velocity. Due to the above-described mode of operation of the tail unit, the missile now turned into the wind until the crosswind component has become zero. But this means a deviation from the firing direction. Only weak stabilization therefore the sensitivity to cross winds is reduced.

For aerodynamic reasons, the effectiveness of wings increases Subsonic flow increases with increasing airspeed, but supersonic away. In the case of unguided supersonic missiles, the tail unit must therefore at least be as follows be large that it is still sufficient for stabilization at maximum speed, What with the known contributions without delayed opening a high sensitivity to wind from the ground has the consequence. In the case of projectiles, this means that their sensitivity to crosswinds increases with decreasing supersonic speed, since according to the standing their stability increases and only decreases again in the subsonic range.

The same applies to devices or war bodies that are move in water and stabilize in an analogous way due to their tail unit lateral water currents react.

For simplicity, it is used below instead of the more general The term "war body" only uses the term "missile" without that a limitation is intended.

The invention is based on the object of the above-mentioned missiles Way of reducing the sensitivity to side currents.

According to the invention, this object is achieved by means of an additional device solved, which is designed according to the characterizing part of claim 1. Through this For example, the surface wind sensitivity of rockets is reduced without the tail unit of the missile has to be changed somewhat.

This is achieved by one or more additional tail surfaces, which fold out of the ogive and thereby the effect of the Beck tail unit more or less compensate for being positioned in front of the missile's center of gravity (Destabilizing fins). Analogous to a tail that unfolds too late the destabilization surfaces collapsed or discarded after a certain period of time to ensure the full stability of the missile again. If the Missile rotates to compensate for thrust vector errors of the engine, must the destabilization fins like the tail unit have an angle of incidence so a damping of the rotation is avoided. A suitably twisted destabilization fin can have the same effect as a flat, adjusted fin Task of deploying the destabilization fins during or shortly after the start of zOBo missiles and retracting or dropping them after a certain flight time are different physical switching quantities applicable. In the configurations described later At the start it is the acceleration and the throwing off of the distillation fins a moment caused by the aerodynamic drag. This is everyone One of the many possibilities. To initiate the two switching processes are individually or as a combination zOBo the acceleration force the centrifugal force, the aerodynamic Drag, aerodynamic lift and dynamic pressure can be used, i.e. all of them physical quantities that change during the missile's thrust phase Also pyrotechnic, mechanical, electromechanical and electrical timers, which are independent of the mentioned physical quantities, can be the switching processes initiate. For example, a timer can control both the switching operations for the at least initiate a destabilization surface as well as other functions of the head of the Initiate missile. This can be used, for example, for bullets, in which the destabilization device not when fired, but only to one later in function with a correspondingly reduced supersonic speed is set.

In an expedient embodiment of the invention, the training is according to Claim 2 provided so that it is possible in an advantageous manner at a given Missiles can still be retrofitted to increase the range by otherwise unchanged missile a corresponding correspondingly slimmer ogives are attached will. This allows all pre-existing missiles and associated facilities can be included in the improvement without any changes.

Also reducing the range of an existing missile is possible if the ogive is properly attached to the flow. A reduced minimum range can be used to expand the usable flight range be beneficial.

A missile of limited length is used e.g.

provided with a slim ogive before take-off, making the aerodynamic Resistance to a less lean is reduced and the range increases.

Of course, this measure is not the same in all cases effective, especially since the extension of the ogive also increases the take-off mass means. Without defining limits, it can generally be said that these Method is particularly effective with missiles with a great influence of the aerodynamic Resistance to the range (supersonic numbers, unfavorable aerodynamic Shape; large flight distance compared to the caliber; short thrust time with long free flight time).

The attached ogive slightly reduces the stability of the missile, what is the case with powered missiles with poor stability in the event of flame failure (more critical Case) must be taken into account.

The ogive to be retrofitted, also in an advantageous manner there is still enough space to install the destabilization device on the original log of the missile, e.g. by means of transversely arranged spring rods 1 which snap into the keyway of the original log. That poses a particularly Partial, easy and quick to do The ogive is expediently supported for centering and Torque absorption around the transverse axis at two points arranged axially one behind the other away. It is preferably made of plastic and e.g. by welding or glue with longitudinal and transverse reinforcements. The ogive according to the invention can be modified in the factory to the original Ogive, for example, can be attached or glued on before loading the launch pad Nerferrohr9 rail, canister) are placed on the missile or located is already on the launch pad and engages when the missile takes off.

With rotating plug bodies, there is basically only one application Destabilization fioses possible9 although here, too, preferably several, in particular four, are provided. The fins are given preference by an under before the start The device under spring pressure is locked in the folded state. After the start they are unlocked at a specified first time and can be folded out released that z, B. the axial acceleration of a missile has a locking body moves against the force of the aforementioned spring backwards, so that this except Engages the front free ends of the fins.

After a given flash time, do a given second At this point, the fins are thrown off or folded. This removal from the Functional position can be restored by utilizing the aerodynamic resistance or the other possibilities mentioned above. Unfolding and dropping even with rolling plug bodies can be supported by the fact that the center of gravity of the fins placed as far outwards as possible will. For example, you can do this Fins made of plastic with lead or other heavier inserts in the appropriate distance from their pivot point.

In order to achieve a separation of the fins as evenly as possible, the arrangement according to claim 3 can be provided. About the jump in stability, if necessary To reduce the size of the destabilization fins after they have gone out of function, orders can according to claims 4 to 6 are provided. The arrangement according to claim 7, according to which the ogive can be wholly or partially rotatable about the longitudinal axis of the missile is, finally offers the possibility of using the centrifugal forces as a switching variable increase and / or evenly distribute the eddies of the destabilizing fins.

The invention is shown in the drawing in various embodiments Sections shown schematically and will be explained in more detail below with reference to these. 1 shows an attached ogive with destabilization fins and FIG. 2 up to 9 different variants of this, some in a cutout.

Fig. 1, in particular its section A-B, shows part of the original Missile 1 with Ogive 2, on which a slim Ogive 3 is placed. To guarantee The Ogive 3 is provided with supports 4 and 6 for dimensional stability and strength. If necessary, additional supports can be provided, also in the area of the Axis 9. The reinforcements attached there are then not circular disc but rather in the shape of a quarter circle to the function of the destabilization fins 16 to ensure.

The at least one egg locking into the keyway 19 of the Ogive 2 Rod-shaped locking spring 5 is used to axially lock the ogive 3 (see also section C-D).

The centering is ensured by the component 6.

Due to their arrangement to one another, the supports 4 and 6 can also Bending moments are transferred from the slim ogive 3 to the missile 1.

The ogive 3 with the destabilization fins 16 folded in (right Page in section A-B of Fig. 1) is before loading the launcher tube on the missile set so that it engages with the spring bars 5, or it is already located beforehand in a suitable place in the launcher tube and locks when the tubes are loaded or when Launch the missile automatically one.

The destabilization fins 16 are thereby through the bearings 8 and the locking body 14 standing under the pressure of the switching spring 15 over the bevel 20 held in their retracted starting position.

The locking body slips due to the launch acceleration of the rocket 14 against the force of the switching spring 15 to the rear, so that the bevels on the front ends of the fins 16 are released and the fins 16 by the axial Acceleration force (provided the distance between the fins' center of gravity and the axis 9 is greater than the distance of the bearing 8 from this) and / or by centrifugal force open due to rotation (left side in section A-B of Fig. 1).

The destabilization fins 16 transmit the aerodynamic lift onto the ogive 3 through the side supports 7 (see in particular section E-F). This can be large, as shown in Fig. 1, section A-B9 (quality Support1 but subject to comparatively strong friction) or over a small area (e.g. washers on bearing 8 between 16 and 7), which means increased bending moments the destabilization fins 16 causes.

Another rearward rotation of the destabilization fins 16 will occur initially prevented by the retaining ring 10, the by a shear bolt 11 with the Axis 9 is connected. As a result of increasing with the speed of the missile Aerodynamic resistance press the destabilization fins 6 forward dßn retaining ring 10 until the bolt 11 shears off, so that the destabilization surfaces -16 continue to turn around the bearing 8 to the rear and after the stop at the end of the Slot in ogive 3 (position 21) and separate from the missile As a result - as intended - the tail unit effectiveness is fully restored.

When the aerodynamic drag of the destabilization fins 16 as a switching variable is not sufficient (e.g. because the shear bolt is then too small or because the shearing force is too difficult to reproduce), additional Resistance surfaces are attached to the free ends of the fins 16. Farther it is possible to design the fins 16 so that they are at an arrow angle (Angle between the leading edge of the fin and the axis) is less than 90 ° locked towards the front so that the center of gravity of the fins lies in front of the pivot point 8. Due to the centrifugal forces, which then attack the fins 16 in a rolling missile, becomes a generated additional moment to increase the shear force. -This still came from it be reinforced so that the center of gravity of the fin is moved outwards (e.g. lead insert in plastic fin).

In the case of the unlocking device described, it can by Material tolerances, environmental influences and construction inaccuracies occur that the destabilization fins 16 differ from missile to missile Solve times.

It must be examined in each individual case whether this is problematic. If this is the case, a more reproducible unlocking of the destabilization fiows must be achieved 16 are provided.

Fig. 2 shows in its sections G-H and I-J a fiction, contemporary Configuration, in lher a lifting spring 18 in connection with the sleeve 17 the Task of the shear bolt 11 according to FIG. 1 assumes the rest of the structure that according to Fig. 1.

In the configurations of FIGS. 3 to 6, the end locking device adjustable to ensure good reproducibility.

In axis 9 to Big. 3 a circumferential groove 22 is incorporated, in which a ball 24 engages, which is pressed by the spring 25. Through the Screw 26 on retaining ring 23, the pressing force of spring 25 is adjustable. In the Design according to FIG. 4, the adjusting device is housed in the axis 9. Of the Groove 22 in Fig. 3 corresponds here to the circumferential phase 32, at which the through the Spring 29 loaded ball 28 is applied. The spring force is provided by means of the screw 30 adjustable, the retaining ring 27 with its bore 31 on the axis 9 is displaceable with corresponding upward pressure forces of the fins 16.

Fig. 5 shows a configuration that adjusts particularly precisely and also ensures that the destabilization surfaces 16 are released synchronously.

The retaining ring 33 is provided with a longitudinal groove 34 on the underside of the retaining ring 35 to a segment-shaped take 36 is expanded, like Section K-L shows. The pin 37 is inserted into the axis 9. The leg compression spring 38 sits centrally and pretensioned around the axis 9. The spring leg 39 is inserted into the bore 40 of the retaining ring 33; the spring leg 41 lies in the longitudinal slot 42 of the axis 9, and thus both ends of the leg pressure are lower in the circumferential direction set.

The screw ring 44 is screwed onto the thread 43 of the axle 9, Via which the contact pressure of the leg compression spring 38 can be adjusted.

The Üestabilisierungsfinnen 16 press, due to their aerodynamic Resistance, the retaining ring 33 forward until the pin 37 and the segment-shaped Recess 36 are in the same position. The one installed in the tensioned state Leg compression spring 38 now rotates retaining ring 33 by 450 to the left (viewing direction on section K-L; see rotating arrow). The radial grooves 45 are in the retaining ring 33 at the end of this turning process over the destabilization fins 16, which are thus free and detach from the missile.

Fig. 6 shows the position of the Entriegelungsbausk tion briefly after reaching the release torque (retaining ring 33 in end position).

The described devices to reduce the aerodynamic Stability of a missile at the beginning of the flight phase or possibly for example in the case of a projectile even during the flight phase, if its stability is undesirable becomes high, as in the case of the delayed opening of the tail unit after the destabilization fins have been thrown off 16 a "jump in stability". The one with regard to the ground wind or side flow dependency however, optimal stability changes with the speed of the flight body continuously, which means that by a delayed opening tail or one of the devices shown in FIGS. 1 to 6 of the missiles in the initial flight phase is initially under- and then over-stabilized.

If necessary - what happens when developing from flight path simulations Taking into account the additional cost results - can approach the optimal Stability course as a function of the speed according to the invention The following measures can be improved: There are two or more destabilization devices 1 to 6 arranged one behind the other and have different "switching points". The comparatively large jump in stability is then made up of two or more small ones replaced.

The unlocking takes place in two or, if necessary, several stages in front of you by z0B. 7, two retaining rings 10 with shear bolts 11 are provided are. The arrow angle (angle e.g. between the leading edge of the fin and the radial direction) increases after each stage, reducing the destabilizing effect will. If the individual fins 16 with a different length of support rest on the retaining ring 10, it is possible to additionally throw off the fins in stages.

A "" steady swept wing effect "alone can also be used for this to make the change in stability more slowly. According to FIG. 8, this can thereby be achieved be achieved that the 16 needed to unlock the destabilization fins Angle of rotation about the bearing 8 is increased, e.g.

in that the retaining ring 10 with shear bolt 11 in comparison to Fig. 1 must be moved further forward on axis 9. At the indicated in Fig. 1 Place will take place its another axially displaceable retaining ring 47 attached, which is supported on 10 by a spring 46 guided through 9. First with a large arrow angle of the destabilization stream, the spring is fully compressed, so that the bolt 11 is sheared off. Accordingly, the in Fig. 2 to 6 modify the arrangements shown.

In rare cases in which the destabilization fins generate buoyancy the resulting eddies have an unfavorable effect on the effectiveness of the tail unit in the tail area, the device according to the invention can be arranged freely rotatable about the axis 9, by, for example, grooving instead of the two keys in the variant shown in Fig. 1 19 in the original ogive 2 a circumferential annular groove is provided as a bearing point.

Finally, FIG. 9 shows a variant in which the fins 16 are not thrown off, but to the rear after the function has been fulfilled fold into the contour of the attached ogive. In the left half there is one on display Fin 16 is shown, which finally acts on the retaining ring 47 as the force increases so far against the force of the spring 46, which is located on the collar 48 with locking pin 49 firmly supported, pushes upwards that it is with the edge at its inner end at the Ring 47 can slide and close by its rearward pressure force Lich locked in the folded position shown in the right half of FIG will.

The advantage achieved by the invention is in particular that a missile that is already available in large numbers, new range requirements can be adjusted, while reducing the side flow sensitivity. By optionally locking the missile with and without a device, the missile can also to the Needs (cluster weapons or point targets, range) adjusted at short notice will.

Claims (7)

Claims: 1. Device for reducing the sensitivity Stabilized war body moving in air and / or water against lateral flow, that is not indicated that the War body (1) is provided with an ogive (3), which is at least one as an additional Has the stabilizing fin (16) acting on the tail surface, leading to a predetermined first point in time from the contour of the ogive (3) can be folded out and at a specified time second point in time can be folded in again or ejected. 2. Apparatus according to claim 1, characterized in that the ogive (3) with the at least one destabilization fissure (16) on the already existing one Ogive (3) of the war body (1) can be placed. 3. Device according to claim 1 or 2, with several destabilization fins, characterized in that the movement of the destabilization fins (16) over a common mechanical switching element (33) is kinematically coupled. 4. Device according to one of claims 1 to 3, characterized in that that several destabilization devices with different operating times are arranged one behind the other. 5. Device according to one of claims 1 to 3, characterized in that that the angle between the leading edge of the destabilization fin (16) and the longitudinal axis (9) of the war body (1) can be enlarged during the operating time. 6. Device according to one of claims 1 to 5, characterized in that that the destabilization fins (16) can be folded in or ejected in a staggered manner are. 7. Device according to one of claims 1 to 6, characterized in that that it is rotatably mounted about the longitudinal axis (9) of the war body (1).