SE460738B - BEFORE MISSILES AND OTHER PROJECTILES INTENDED FOR FALLABLE WINGS - Google Patents

Description

4eQ vase Several different constructions of retractable wings are previously known. A type is folded along a joint parallel to the longitudinal direction of the projectile.

These wings can be straight or curved around the projectile. The latter type is usually referred to as wrap-around wings. Such folded "straight" wings take up a large volume even in the retracted position, nor can they be made as long as one would normally wish.

Wrap-around wings can be made long, but since they usually retain a helical extension relative to the projectile's cross-section even after precipitation, they provide a strong connection between the steering around the three space axes, which makes the steering control system considerably more difficult to steer. Another disadvantage of the wrap-around wings is that so far they have as a rule had to be made of simple plates, which is why they have not been able to be given a desirable aerodynamic profile with wing cross-sectional conditions due to flight or steering considerations.

It is also previously known to produce open double-walled wrap-around wings consisting of two plates which support each other along a common outer edge extending parallel to the projectile. In these wing constructions, the projectile circulating air thus has free access to the space between the plates. An example of such a construction is described in more detail in the German patent specification DE 36 18956. Aerodynamically, this is not a particularly satisfactory construction even if the composite wing itself becomes more stable than the simple sheet metal wing.

Another wing construction that is used relatively often is the one where the wings are recessed in a slot in the fuselage. However, this type of wing seriously encroaches on the space inside the projectile and in some cases it cannot be used because it would impede a desirable design of the action part. In addition, this type of wing often forces special designs on the projectile that one would not otherwise have chosen.

The invention now relates to a wing which consists of two cupped plates which abut against each other and by eg welding or gluing are joined together along all the edge sides along which they are not directly or indirectly attached to the projectile body. With this construction, a space is thus formed between the plates and this gives a rigid wing despite the fact that the plates' own thickness is relatively small. The design also makes it possible to give the wing an aerodynamically adapted cross-sectional profile.

One of the preconditions for such a profile-shaped wing to be able to adapt to the wrap-around technique and in the retracted position lie tightly bent around the projectile body is that the material in the wing is sufficiently elastic to firstly allow a compression of the cupped plates into a tight cohesive sheet metal package, secondly, a deflection of this sheet metal package around the projectile body. Despite the at least partially fairly large plate elongation imposed on it, the wing must then, as soon as it is released, regain its original shape and have a sufficient rigidity of its own to be able to withstand the lifting and steering forces necessary for its function.

We have now surprisingly found that certain titanium alloys and certain glass- and carbon-fiber-reinforced plastic materials as well as certain high-quality spring steels have such properties that it is possible to produce wings of the type defined in the following claims.

Characteristic of the wing according to the invention is thus, in addition to the construction outlined above, two cupped interconnected plates, which enables a desired aerodynamic design and wing surface even with very long wings, that the precipitation force necessary for precipitating the wing is essentially derived from the stresses and strains that are forced into the goods as the wing folds into place. The locking function required for retaining the wing in the retracted position will not be discussed in more detail in this context as it is not included in the invention, but it may consist of a locking sleeve which is thrown as the projectile leaves the barrel or launch tube.

As can be seen indirectly from the above, this type of wing is completely frame-free and, due to its intrinsic rigidity, completely dependent on the shape and material of the included cupped plates. 46D 738 According to a detailed design of the invention, there are many advantages in designing the cupped plates with at least some central parts where the plates are substantially completely flat and run parallel to each other. With this design, the advantage is gained that these parts of the plates are first pressed tightly against each other during the folding in and preferably by means of cooperating lugs and openings in the opposing plates, which during compression engage with each other, are locked against relative lateral displacements before the wing is bent towards the projectile body. This prevents creases and distortions in the plates which, even if in the unfolded position they are completely uniform due to their different distance from the outer surface of the projectile body in the retracted position, will always be subjected to slightly different elongation during bending towards said outer surface.

In its simplest form, the Wing according to the invention is a straight double-sided wing which is tangentially attached to the projectile body. Since such wings in the retracted position can be rolled up perpendicular to the projectile body, each wing half can be given a length which corresponds to a maximum of half the circumference of the projectile, i.e. from one side of the attachment to the other side of the same attachment.

A second variant of the invention gives radially projecting wings, but then it is usually most suitable to give the wing, or in fact the wing half, a rotatable attachment which makes it possible to lower the wing to an at least tangential orientation relative to the projectile body before the wing is folded or rather bent. in along the outer surface of the projectile body.

In connection with the figures, two different types of rotatable wings according to the invention are described.

In the first alternative, a rotatable bearing for the wing is used in the form of a bearing shaft separately locked in the fully extended position provided with an axially arranged substantially axially centered rectangular bottom groove along one long side of which one of the cupped plates is attached along its inner edge side while the other 5. 460 738 of the cupped plates along its inner edge side is provided with a locking strip which can engage in a corresponding groove in the other opposite inner edge side of the bottom groove. In addition, there is a locking member in the form of a bent leaf spring which can snap in between the plates when the wing is fully extended and the cupped plates have regained their original shape. The function of this locking means is to prevent the plates from being compressed by the wing load during the flight of the projectile.

In the second variant of a folding radial wing, each cupped plate is provided with a substantially semicircular bearing pin at its free inner edge side facing the projectile at each outer corner.

When the cupped plates are completely compressed, these semicircular bearing pins in pairs each form a complete bearing pin around which the wing can be folded in to an at least tangential position relative to the projectile body.

The basic form of storage of these composite bearing pins in the projectile body is oval. The wing then folds in along one edge of the oval bearing, but in the fully extended position the plates crack apart and the semicircular bearing pins rest against opposite edges of the oval bearings.

This basic model for rotatable wing storage can then be supplemented with the same type of barrier edge along the lower edge of one plate which is found in the previously discussed wing type. The same also applies to the locking member between the plates.

The invention has been defined in the following claims and will now be described somewhat further in connection with the exemplary embodiments shown in the accompanying figures.

Of these, Figure 1 shows a projectile with extended superimposed wings in oblique projection.

Figure 2 A cross-section through the projectile according to Fig. 1. 460 738 in Figure 3 A partial section of the wing attachment according to Figs. 1-2.

Figure 4 A projectile with four radial wings.

Figure 5 A cross section through a projectile with four radial wings.

Figure 6 A detail of the wing attachment according to figure 5.

Figure 7-9 A wing in different projections.

Figure 10-ll Details of the wing attachment.

Figure 12-13 Cross section and detail section of an alternative wing attachment.

The projectile P shown in Figures 1-3 is provided with a superimposed retractable wing V and guide fins or rudder F. The guide fins F may be of a different construction and shall not be discussed in more detail in this context.

The wing V is formed by two cupped plates 1 and 2 which are bent into the common length and profile cross-sections shown in Figures 2-3.

The plates 1 and 2 are joined together along their periphery with the joints 3 which can be constituted by welding, glue or solder joints, but they can also be designed in another way. The main thing is that the joints offer a non-sliding connection between the plates and can absorb shear stresses. When recessed, the plates 1 and 2 are first pressed tightly against each other so that they become flat, after which they are wrapped around the projectile body K in the manner indicated by dashed lines V1 in Figure 2. As indicated in this figure, the wing tips are partially turned over. The elongation to which plates 1 and 2 are subjected as they wrap around the projectile body consists of two components; partly the elongation which the compression and the extraction of the cups' cupped shape give rise to, and partly the one which the winding around the projectile gives rise to. The latter elongation is determined by the double thickness of the plate and the diameter of the projectile, while the former is determined by the thickness of the plate and its radius of curvature in the pre-bent state. The elastic limit of the plate must be sufficient to accommodate the combination of these strains. This places very high demands on the material in the plates but at the same time gives wings which without special mechanics will fold out as soon as a locking function ceases to lock the wing in its recessed position.

As already mentioned, the material in the wing must have a very high elastic limit and high strength. Examples of suitable such materials are high-strength titanium alloys, spring steel and certain fiber-reinforced plastic materials. However, other materials could also be considered. The material to be chosen may be decided on a case-by-case basis, even if titanium for the day is probably the closest option.

Two different alternative wing attachments are indicated in Figure 1-3.

In the first alternative according to Fig. 2 (Fig. 1 is common), the lower wing plate 2 is provided with guide beads or pins 5 and 6 which fit recesses 7 and 8 in the projectile body and thereby fix the wing against rotation while the wing is held in place by a flexible but non-stretchable strap 4 which is stretched over the upper surface of the wing and attached to the projectile body. The belt 4 can thus be folded together at the same time as the wing parts 1 and 2 are pressed together as a preparation for the folding in of the wings.

According to the second variant shown in Fig. 3, the wing has been fixed against rotation by attaching the lower wing plate 2 to the projectile body with screws 9 and 10 with washers 11 and 12. In order for the screws 9 and 10 to be mounted and for the plates 1 and 2 it must be possible to squeeze it completely, there are two openings 13 and 14 in the upper wing plate 1. In this attachment it is not always necessary to supplement with the flexible band 4, although this may sometimes be necessary in view of the aerodynamic forces. affecting the wing.

V55 many projectiles want the same steerability in both the tipping direction and the turning direction. In such cases, you want four radially aligned wings instead of two. Figure 4 shows such a project.

In the following, two different possible variants of retractable radially aligned wings will be discussed. Of the figures in question, Figures 4-11 relate to the first variant and Figures 12 and 13 to the second variant.

All these radial wings must be made retractable against the projectile body about rotatable bearings arranged axially in the longitudinal direction of the projectile. The two variants of "radial" wings described below differ in the design of these rotatable bearings, while several other detailed solutions are common.

In the first variant of the projectile according to Figs. 4-11, the wing 15 consists of two cupped plates 16 and 17 which are joined together along their common edges with the joint 18 while the fourth edge of each plate is free and provided with fastening details 19 and 20, respectively. may, as in the previous case according to Figs. 1-3, be a solder, glue or welding joint.

When recessed, the plates 16 and 17 are first pressed tightly against each other, after which the wing is folded down towards the projectile body K around an axially directed rotatable bearing, after which the wing from a substantially tangential position relative to the projectile body K is wound around it. Even in this case, the wings have been shown solely to give a sense of proportion. This is facilitated by the formation of a sharp longitudinal notch in the projecting body at each wing attachment (see, for example, Fig. S). The recessed positions of the wings are shown by the dashed lines VIII in Figs. 5 and 6.

When the wings are thus wound around the projectile, as already mentioned, large tensile and compressive forces arise in the plates which are taken up in the joints 3 and 18 between the plates in the form of shear stresses. In the case of the wing according to Figs. 1-3, there was no free plate edge that could be deformed. 9,460,738.

In the current radial wing constructions which require rotatable bearings along the periphery of the projectile body, there are no joints between the plates along the bearings. This part of the wings could therefore be deformed if the fastening details 19-20 along the inner end edge of the respective plate are not made sufficiently rigid. To reduce the stresses on the attachment details, several different measures are shown of several that can be taken.

Such a measure may be to apply a flat surface 21 along the projecting body in immediate connection with the rotatable attachment of the wing so that the Wing when it is wrapped around the projectile body does not need to be further deformed (stretched) in immediate connection to the axis of rotation and the free end edges of the plates.

The second measure is to provide the plates with fixing means cooperating in the compressed state, for example in the form of plugs 22 on one plate and openings 23 adapted thereto in the other plate. The fixing means can be designed in a large number of ways and they could also, for example, consist of folds in the plates. By means of the fixing means, the plates are forced to follow each other as they are wrapped around the projectile body.

The fixing means and the "straight" part of the projectile periphery are solutions which may be relevant for all types of radial wings. However, the rotatable attachment can be of different construction.

In the variant shown in Figs. 5-11, the fastening part 19 consists of a rod with a substantially semicircular cross-section which is attached to the inner free end or the edge side of the flat or straight part 24 of the plate 16. It is namely the case that the compression of the wings the constituent plates and their rotation around the projectile body are always facilitated if the plates included in the wings have a central or flat portion arranged centrally between the edge joints at the height of the wing attachment to the projectile body. The ends of the rod 19 are extended past the "straight" part of the plate with substantially semicircular bearing pins 30, 31. The fastening member 20 also consists of a rod formed as two end-placed semicircular bearing pins 32, 33 and one along the plate. 17 flat part 25 attached barrier strip 26 with rectangular cross section. With the plates in the compressed state, round composite bearing pins are thus obtained at the respective end edges of the flat plate portions.

The part of the projectile which holds the wings is designed as a first ring 27 (Fig. 10) and two holding rings 28 (29) (Fig. 11) placed on either side thereof, the latter two being provided with pairs of opposite oval holes 34 and 35 for the bearing pins 30- 32 and 31-33, respectively. During assembly, the wings are mounted to the ring 27, after which the retaining rings 28, 29 are mounted so that the projecting bearing pins 30, 31, 32, 33 of the fastening details will slide into the oval holes 34 and 35 in the retaining rings 28 and 29, respectively. the wings in the extended position are shown in Fig. S. In this position the bearing pins 30-33 abut against the outer edges of the respective oval bearing holes 34 and 35, respectively. In the extended position the wing is held in place partly by the ends of the bearing pins 30-33 in the openings 28-29 of the fact that the semicircular part of the fastening part 19 abuts against the inside of a corresponding semicircular groove 36 in the ring 27 adapted thereto, at the same time as the fastening part 20 with its locking strip 26 fits into a locking groove 37 adapted thereto which is also mounted in the ring 27. The groove 36 and the locking groove 37 are arranged opposite each other in a recess or bottom groove 38 in the periphery of the ring 27. The grooves run axially relative to the main direction of the projectile. At the bottom of the recess 38 is arranged a curved leaf spring 39 which is originally compressed against the bottom of the recess but as soon as the wing is fully extended will snap in between the plates 15 and 16 and make it impossible for them to be compressed by the air forces. The width of the leaf spring 39 corresponds to the inner space between the flat parts of the plates 15 and 16. The leaf spring 39 also prevents the fastening details 19 and 20 from sliding out of their respective recesses in the ring 27.

The wing is kept recessed with a device (not shown). As in the case of a single wing, the device can consist of an outer sleeve which is removed ... 11 11 460 758 when the wing is to be folded out or the wings are kept recessed by the launch tube.

Figure 6 shows in broken lines how the fastening details lie in the openings 34 and 35 as long as the wing is recessed. The fastening details and the wing-forming plates are thus in the fixed position relatively centrally in order to burst out towards the opposite edges of the oval holes 34, 35 after the deposition. The figure also shows that the locking strip 26 is slightly inside, i.e. closer to the projectile axis than the fastening part 19.

Figures 12 and 13 show an alternative to the rotatable bearing of the wing according to Figures 5-11. However, the main principle is the same.

The difference is that in this case the wing is attached to a rotatable shaft 40. This shaft is provided with an axially aligned rectangular bottom groove 47. One plate of the wing here referred to as 41 is joined with its flat or straight part to one longitudinal edge of the shaft groove along the joint 43. The second plate here referred to as 42 has a fitting 44 with a locking edge 45 which, when the wing is folded out, engages in a corresponding recess 46 in the opposite longitudinal edge of the groove in the groove 47 in the shaft 40. In order not to compress the wing by the air forces on the recess a bulging leaf spring 48 which in the manner previously described can snap in between the plates in the wing as soon as it has reached a fully extended position. The leaf spring 48 effectively prevents compression between the wing plates.

Since the wings' plates in this construction in the unfolded position are both locked in the same rotatable shaft, does this have to be locked against rotation? This has been arranged so that the shaft 40 is displaceable in its longitudinal direction by a spring (not shown). With the wing in the fully extended position, this spring pulls the shaft to a position where some recesses 51 lock the shaft against further rotation.

For all alternatives, it is assumed that the wings' striving to assume their original form takes care of the precipitation. One way to increase the safety of the deposition at "radial" wings is that the projectile's guide fins 50 can set the projectile in rotation in the direction that gives a lifting force that wants to swing out the wings. 12

Claims (13)

0375 460 738 L fa PATENTKRAV 1. Foldable wing (V, 15) or fins intended for missiles and other projectiles which from a first recessed (V1) and towards the projectile body (K) bent and initially blocked position at the end of the blocking function is foldable to a second position where it generates for the projectile (P) desired lifting force and / or steering torque and wherein the forces required for the deposition of the wing or fin to its second position derive from the stresses contained in the material in the wing or fin due to the deformation to which the material is subjected during its bending. towards the projectile body is characterized in that the wing or fin in the extended position consists of two plates (1, 2, 16, 17) which are cupped apart from each other and which are immovably joined together (3, 18) along all the edge sides which are not directly or indirectly attached to the projectile body and the cupping of which is so chosen that together they give the wing or fin its cross-section due to aerodynamic considerations. Wing (V, 15) or fin according to claim 1, characterized in that from its attachment to the projecting body (K) and out to its outer end it is completely frame-free and only stiffened by the plates (1, 2, 16). , 17) cupping and the rigidity of the material. Wing or fin (V, 15) according to claim 2 - characterized in that it consists of two plates welded to each other along the edges (3) or otherwise firmly connected to each other by cupped plates (1, 2) which in the unfolded condition extends equally far on both sides of the projecting body (K) against the periphery of which one plate (2) abuts and is attached alternatively supported while the other plate (1) 13. 460 738 away from the the outer surface facing the first plate is supported by a support member (4) defined in the direction away from the projectile body (K) which is freely movable towards the projectile body (K) together with the plates (1, 2) as these are compressed and rolled around the projectile body (K) . Wing or fin according to claim 2 or 3, characterized in that the direct attachment to the projectile body is made along a part of the profile cross-section of the wing or fin where the two same-shaped cupped plates (2, 3, 16, 17) in the unfolded position are substantially flat (2, 5, 26) and run parallel to each other. Wing or fin according to claim 4, characterized in that it is rotatably mounted along its end edge facing the projectile body in a bearing (19, 20, 34, 25, 40) rotatably extending in the longitudinal direction of the projectile body at least a quarter of a turn around which The wing or fin is rotatable against the projectile body (K) provided that the two wing or fin forming cupped plates (2, 3, 16, 17) are previously pressed together into a tight and flat abutment against each other and one (16) of the two wings or the fin-forming cupped plates (2, 3, 16, 17) at their end face facing the bearing are attached (24, 43) to the bearing (19, 40) along the outside of their flat portion (24) while the other cupped plate ( 17) along the outside of its parallel end edge along its flat part (25) is provided with a bearing running parallel edge (26, 45) which with the wing or fin in the extended position engages in a therefore adapted projectile body connected parallel to the bearing ring n extending recesses (37, 46). Wing or fin according to claim 5, characterized in that its bearing consists of a first and a second pair of substantially semicircular at the outside of the edge of the flat parts (24, 25) of the two cupped plates fastened with their semicircular sides facing outwardly spaced guide pins (30-32) which 14. 460 738 are paired (31, 32 and 30, 33) mounted in oval bearings (34, 35) attached to the projectile body. Wing or fin according to claim 6, characterized in that along the flat part of one of the cupped plates runs between its guide pins a guide edge (19) with the same cross section as and made in one piece with the guide pins of the plate and for which there is a projectile-connected semicircular groove (36) while between the guide pins of the second plate runs a locking edge (26) with a rectangular cross-section for which there is a locking groove (37) connected to the projectile body in which the locking edge (26) can snap in when the wing or fin is completely unfolded. Wing or fin according to claim 5, characterized in that the bearing consists of a rotatable shaft (40) provided with a longitudinally axially centered groove (47) of rectangular cross-section along the central part of the shaft, the first of the cupped plates (41) at its flat part is attached to the rotatable shaft (10) against one longitudinal edge of the latch (47) along its end edge, while the other of the cupped plates with a locking edge (44) arranged along this edge is arranged to engage in a unfolded position in a adapted recess (46) in the opposite longitudinal edge of the groove (47). Wing or fin according to claim 8, characterized in that the shaft (40) constituting the bearing is axially displaceable by means of a separate spring from a first position, intended to be occupied as long as the wing or fin is fully or partially recessed to a second position. which it can only assume when it has been rotated to the position corresponding to the fully extended wing or fin and where the shaft is locked by means of engagement in means (51) connected to the projectile body against each continued rotation thereof, whereby the wing or fin locks in the extended position. Wing or fin according to any one of claims 5-9, characterized in that a movable locking member (39, 48) is arranged in the projectile body in the immediate vicinity of the attachment of the wing or fin therein and said locking member 15. 460 7ss fl by means of spring force or is otherwise movable from a first retracted position which it occupies as long as the wing or fin is fully retracted to a second position which it can assume only when it is fully extended and the locking means (39, 48) is inserted between the two cupped the plates (16, 17, 41, 42) and there extending from the inside of one plate to the inside of the opposite plate. 11. ll. Wing or fin according to one of Claims 1 to 10, characterized in that the cupped plates (15, 16) connected to one another along the edge sides along their wide sides have opposite guide lugs (27) and recesses (23), respectively, which when the plates are pressed poems close to each other engage with each other and when they bend around the projectile body, the plates force an equal elongation in each part of the wing or fin. Wing or fin according to any one of claims 1-11, characterized in that it is made of a titanium alloy, a spring steel or a reinforced plastic material. Wing or fin according to one of the preceding claims, characterized in that it is designed to be foldable down from a first fully unfolded position to a second recessed position where the compressed plates closely abut against a plane located in immediate inclination to its rotatable storage. part (21) of the projectile body, which flat part gradually turns into a curved shape characteristic of the projectile body and along which the wing or fin rotating around the body begins. OPA / Fkb 1988-12-14