DE102021005973A1 - Projectile with fins that can be swung out without springs - Google Patents

Abstract

In a projectile section (2) as at least part of an intended projectile (6), with a projectile body (8) extending along a central longitudinal axis (10) of the projectile (6) which, when the projectile (6) is flying as intended, after it has been fired a Twist (16) about the central longitudinal axis (10), with at least one fin (18) which rotates about an axis of rotation (20) between a firing position (A) resting against the projectile body (8) and a flight position (A) protruding from the projectile body (8). F) is rotatably mounted on the projectile body (8), with the axis of rotation (20) running in the direction of the central longitudinal axis (10), with the flight of the projectile (6) generating a force (K) which causes a rotational movement (22) of the When the fin (18) moves from the firing position (A) to the flight position (F) about the axis of rotation (20), the force (K) is neither caused by the relaxation of a prestressed spring nor by an electrically or pneumatically or hydraulically or detonatively operated active drive element in the Projectile (6).A projectile (6) includes a projectile section (2).In one method of generating the force (K) at the projectile section (2), the force (K) is not generated by relaxation of a preloaded spring or by an electrically or pneumatically or hydraulically or detonatively operated active drive element in the projectile (6).

Description

The invention relates to projectiles that have at least one fin.

From the EP 3 032 213 B1 a folding wing system is known, comprising a wing root, a wing upper part rotatably mounted on the wing root, wherein the wing upper part can be moved between an unfolded and a folded position relative to the wing root. The folding wing system has a large number of elastic rotating elements or torsion springs. The torsion spring causes the rotary erection of the upper part of the wing. Folding wing systems are always used when a guided missile needs a wing to stabilize its flight, but at the same time is to be launched from a mostly cylindrical launch tube.

The object of the present invention is to provide an improved solution for swinging out a fin on a projectile.

The object is achieved by a bullet section according to patent claim 1. Preferred or advantageous embodiments of the invention and other categories of the invention result from the further claims, the following description and the attached figures.

The projectile section is at least part of a designated projectile, with “at least part” in the present sense meaning that the projectile section can also degenerate into the entire projectile. "Intended" means that the bullet section is designed to be or become part of a specific bullet or bullet type, i. H. a correspondingly completed floor has the floor section.

The projectile section or the projectile completed as intended contains a projectile body extending along a central longitudinal axis of the projectile. The projectile body can thus also be an entire projectile body of an entire projectile or also a part of such a projectile body which is assigned to the projectile section. So the bullet body is a whole bullet body or a part of it. The projectile body is in particular a mechanical base body, a supporting structure, a shell of a projectile, etc. The projectile body therefore does not include other components of the projectile, such as its payload, explosive charge, fuse, electronics, trajectory control, etc.

The invention assumes that the projectile is set up and also intended to be fired when it is used or during operation, for example from a barrel weapon. It is also set up or intended to fly as intended—in particular through the air—after such a launch. The invention is also based on the assumption that the projectile has a spin about its central longitudinal axis during this intended flight, ie, during its intended flight after it has been fired, it has a twist about the central longitudinal axis. In the present case, therefore, only projectiles spinning after being fired are considered.

Firing refers in particular to the exit of the projectile from a launching device, e.g. B. the tube of a gun. Spin means that the body of the bullet spins around the central longitudinal axis during flight.

The missile section includes at least one fin, which may also be a fin, stabilizer, wings, etc. of the missile. The fin is rotatably mounted on the projectile body about an axis of rotation. The fin can be rotated or pivoted between a firing position and a flight position. In the firing position, the fin lies against the projectile body; in the flight position, this protrudes from the projectile body or protrudes from this.

The projectile section contains, in particular, a plurality of fins, in particular six fins, which are distributed evenly over the circumference (relative to the central longitudinal axis) of the projectile section.

The axis of rotation runs in the direction of the central longitudinal axis. “In the direction” is to be understood in such a way that the axis of rotation in any case does not run transversely to the central longitudinal axis. In particular, the axis of rotation lies in a common plane with the central longitudinal axis, in particular it runs parallel to the central longitudinal axis.

During the flight of the projectile, a force is or is intended to be generated in the projectile, which causes a rotational movement of the fin from the firing position to the flight position about the axis of rotation. Strictly speaking, the force causes a torque for the fin around the axis of rotation. The rotary movement is therefore a folding out or swinging out of the fin away from the projectile body. The projectile section or the projectile is accordingly set up in such a way that the corresponding force is generated in the intended flight. The rotational movement therefore has a direction; this is always directed from the firing position A to the flight position F. this means not that the fin could not also move in the opposite direction around the axis of rotation, i.e. counter to the rotational movement.

The projectile section and also the entire completed projectile is set up in such a way that the force is not caused by relaxation of a prestressed spring or by an electrically or pneumatically or hydraulically or detonatively operated active drive element in the projectile. A “drive element” is to be understood in such a way that this is a physical device that is actually present specifically for the purpose of generating force, in particular as a component of the projectile.

By dispensing with a corresponding spring or other drive element, a particularly simple projectile section, and therefore projectile, arises which is therefore not susceptible to faults and is cost-effective.

In a preferred embodiment, the force is exclusively a centrifugal force acting on the fin and caused by the twist and the inherent mass of the fin. Alternatively or additionally, the force is an aerodynamic force acting on the fin, which is caused by the air flowing against or past the fin during the flight of the projectile. The corresponding aerodynamic force is therefore generated solely by the fact that the projectile flies through the air, so in particular this is not a device and is therefore not to be understood in the sense of a pneumatic drive element mentioned above. In particular, the force results as a mixed form of the above-mentioned variants: for example, initially there is only centrifugal force, which leads to the fin “lifting” from the firing position. Since the fin in the firing position, for example, still lies close to the body of the projectile or can even be sunk into it, no aerodynamic force is created here. Only when the fin has left the firing position does air flow against it in such a way that aerodynamic forces act on the fin at all. In particular, aerodynamic force only gradually adds to the centrifugal force during the rotary movement or even replaces the centrifugal force in the further course of the rotary movement up to the flight position.

The invention is based on the finding that these two forces can be used to cause the rotary movement of the fins and that an additional device for generating a force (spring, drive element) that causes or at least supports the rotary movement is therefore unnecessary. In particular, the fin is designed by means of a suitable shape to have correspondingly favorable aerodynamics in order to allow the relevant force to develop on the fin. The shape depends on the individual bullet and can e.g. B. can be found empirically or by simulation.

In a preferred embodiment, the rotational movement has a direction of rotation that is opposite to that of the twist. This further improves the generation of the aerodynamic force, since air is forced to a flat side of the fin pointing in the direction of twist, e.g. B. the underside flows.

In a preferred embodiment, the fin lies in a recess in the projectile body in the firing position. This makes it possible to create a projectile which, at least initially in its flight phase, has aerodynamic properties which correspond to those of a projectile without fins. A conflict with the generation of an aerodynamic force to generate the rotational movement is thus avoided. In particular, the recess is designed as a negative form of the fin, so that in the firing position it rests more or less tightly or without a gap in the recess. In this case in particular, centrifugal force alone is used to initially release the fin from its firing position.

In a preferred embodiment, the fin is shaped in such a way that, in the firing position, its outer surface or top surface pointing radially outward (relative to the central longitudinal axis) complements the circular-cylindrical peripheral surface of the projectile body. The latter is the surface of the projectile body or projectile that points radially outward and is not occupied or covered by the fins. This measure also leads to the above-mentioned initial aerodynamic properties of the projectile (as if it were designed without fins).

In a preferred embodiment, the fin has a thickness that decreases with increasing distance from the axis of rotation in a direction transverse to its outer surface or cover surface pointing radially outwards in the firing position. In other words, the fins taper in terms of their thickness, profile thickness perpendicular to their surface extension, starting from the axis of rotation towards their free end. The direction in which the “thickness” dimension is to be understood is in the firing position in particular the radial direction, in the flight position in particular the circumferential direction of the projectile, in each case based on the central longitudinal axis. This creates a fin that is particularly advantageous in terms of design and/or aerodynamics.

In a preferred embodiment, the fin has, in a plane transverse to the central longitudinal axis, a basic shape that follows or corresponds to the circumference of the projectile in the manner of a segment of a circle. This "following" is especially true in the launch position. The pie shape is in particular the shape of the outer surface of the fin in the firing position. A corresponding fin therefore takes up the basic circular shape of the projectile and thus fits geometrically particularly well into a corresponding projectile in the firing position.

In a preferred embodiment, part of the surface of the fin is designed as a stop surface. In the flight position, the stop surface comes into contact with the projectile body, i.e. it then rests against the projectile body and thereby limits the rotary movement of the fin in the flight position. In other words, the fin is prevented from rotating beyond the flight position. Advantageously, the surface of the fin itself is used as a stop; a separate or special structural part as a stop element in addition to the fin is therefore avoided.

In a preferred variant of this embodiment, the fin has only one wing section and one or more hinge sections protruding therefrom for receiving the axis of rotation. The stop surface is then arranged on the wing section. This results in a structurally particularly simple fin, which only has the actually aerodynamically effective fin in the form of the wing section and only additional hinge sections. The hinge sections can be designed in a particularly simple manner without regard to a corresponding stop function. The stop function is taken over by the wing section in a particularly simple manner.

In a preferred embodiment, the fin can be locked in relation to the projectile body in the flight position. A movement of the fin out of the flight position against the rotational movement is thus prevented.

In a preferred variant of this embodiment, the fin can be locked by a tongue and groove arrangement arranged on the axis of rotation. The tongue and groove arrangement can be locked in place by a locking movement in the form of a displacement of the fin relative to the projectile body in the flight position against the direction of flight along the axis of rotation. "Locking in" means that the tongue slides into the groove. Either the fin has the groove and the projectile body has the tongue, or the fin has the tongue and the projectile body has the groove. This enables a particularly simple and yet reliable locking of the fin in the flight position.

In a further preferred variant of this embodiment, the projectile section contains an elastic pressure element arranged on the axis of rotation and supported between the projectile body and the fin, in particular a compression spring, which is set up to support the latching movement counter to the direction of flight. The pressure element supports - in addition to the compressive force acting on the fin in the opposite direction to the direction of flight due to the air flowing onto the face of the fin in the direction of flight - the above-mentioned latching movement of the fin along the axis of rotation. The pressure element is thus supported with pressure directly on the fin and projectile body; the latching movement is accompanied by a particularly but only partial relaxation/expansion of the pressure element. In particular, the pressure element is therefore still prestressed even when the fin is in the locked position and therefore holds the fin in this position (in addition to the air flowing against it).

The locking or locking takes place in particular as follows: It takes place in a form-fitting manner by means of an axial displacement of the fins, which is supported or initiated by a pressure element/compression spring. The fin itself is used as a tongue (the tongue and groove connection) and moves into a groove in the base body (bullet body). The aerodynamic forces favor this displacement. No separate tongue and groove system is used at the foot of the connection, i.e. directly on the axis of rotation, but the fin or the wing section itself locks directly in the connection (groove), i.e. a corresponding part of the projectile body. The locking mechanism places only minimal demands on the installation space. Even a minimal displacement of the fin in the axial direction (entry of the tongue into the groove) prevents the fin from kicking back (around the axis of rotation against the rotational movement) and allows the forces and moments occurring on the fin to be transmitted to the projectile body. From practice it is known, for example, to lock the fins in the end position (flight position) by means of a wedge or pin, which disengages due to spring force, after opening the tail unit (folding out the fins into the flight position). In the present case, such a separate, blocking element that has to intervene in the fin structure is not used; instead, in particular the fin itself (its one-piece section forming a groove) is guided axially into a detent (integral one-piece section of the projectile body, which is designed as a groove) when it is erected.

This results in a mechanism for positive locking of the fins, in particular a coiled tail unit.

In a further preferred variant of this embodiment, the fin is mounted on the axis of rotation via at least two hinges. The compression spring is then arranged between two adjacent hinges and is supported with its ends on both hinges. In particular, the pressure element is designed as a spring element, in particular a helical spring. In particular, the spring element is mounted on the axis of rotation or penetrated by the axis of rotation. Corresponding hinges have two hinge sections: a first hinge section is—particularly an integral—part of the projectile body, and a second hinge section is a corresponding part of the fin. Both hinge sections are penetrated by the axis of rotation. This results in a particularly compact design of the rotating mechanism for the fin and the resulting hinge arrangement.

In a preferred embodiment, the projectile portion is a tailplane of the projectile. The advantages mentioned above thus also arise for the corresponding tail unit of the projectile. In particular, a so-called coil tail unit results, since the fins in the firing position comparatively wrap or wrap around the projectile body—starting from the pivot axis—in the manner of a coil with their free ends.

The object of the invention is also achieved by a projectile according to claim 14 with a projectile section according to the invention. The projectile and at least some of its possible embodiments and the respective advantages have already been explained in connection with the projectile section according to the invention.

The object of the invention is also achieved by a method according to claim 15, which serves to generate the above-mentioned force on the above-mentioned projectile section or projectile.

According to the method, the projectile with the projectile body is fired in such a way and/or is or is set up in such a way that, after being fired, it has a twist about the central longitudinal axis in flight. Furthermore, the force for the rotary movement of the fin around the axis of rotation is generated during the flight of the projectile. The force is not caused by the relaxation of a prestressed spring or by an electrically, pneumatically, hydraulically or detonatively operated active drive element in the projectile.

The method and at least some of its possible embodiments and the respective advantages have already been explained in connection with the projectile section or projectile according to the invention. In particular, the method has the preferred embodiments explained above in connection with the projectile section or projectile.

In particular, the force is generated exclusively as a centrifugal force acting on the fin, which is caused by the spin and the inherent mass of the fin, and/or as an aerodynamic force acting on the fin, which is caused by the flow of the projectile on the fin during flight air is caused.

The invention is based on the following findings, observations and considerations and also has the following embodiments. The embodiments are sometimes also referred to as “the invention” for the sake of simplicity. The embodiments can also contain parts or combinations of the above-mentioned embodiments or correspond to them and/or optionally also include embodiments that have not been mentioned before.

The invention is particularly suitable for locking a coiled tail a guided ammunition in the caliber range of about 75mm, z. B. 70 to 80 mm or 60 to 90 mm, z. B. 76mm.

According to one embodiment, in the case of a coiled tail unit, the fins are folded onto the projectile body during passage. After leaving the tube, the fins must be set up (rotary movement) and locked so that the flight stability of the projectile is given. For this purpose, the fins are rotatably connected to the projectile body, in particular to the rear structure of the projectile, via a bolt (axis of rotation). An elastic pressure element (compression spring) exerts a force against the direction of flight on the connection of the fins. The fins are guided through a cone into a recess (groove) in the bullet body (tail), which prevents it from folding back (from the flight position) and in the end position (flight position) represents a positive stop in both directions (in and against the rotational movement). The elastic pressure element (compression spring) and the aerodynamic forces prevent the fin from moving forward from this longitudinal position in the direction of flight (and the spring leaving the groove).

• 1 einen Geschossabschnitt eines Geschosses mit Finnen in Abschussposition in einer perspektivischen Ansicht,
• 2 den Geschossabschnitt aus 1 mit Finnen in unverriegelter Flugposition in einer perspektivischen Ansicht mit Teilschnitt,
• 3 das Detail III aus 2,
• 4 den Geschossabschnitt aus 2 mit Finnen in verriegelter Flugposition.

Further features, effects and advantages of the invention result from the following description of a preferred exemplary embodiment of the invention and the attached figures. Show, each in a schematic principle sketch:

• 1 a projectile section of a projectile with fins in firing position in a perspective view,
• 2 the bullet section 1 with fins in unlocked flight position in a perspective view with partial section,
• 3 detail III 2 ,
• 4 the bullet section 2 with fins in locked flight position.

1 shows a projectile section 2, here in the form of a tail unit 4, in the form of part of a projectile 6, here a guided ammunition, which in 1 is only indicated by dashed lines and is not shown further.

The projectile section 2 contains a projectile body 8, which is part of an entire projectile body of the projectile 6, not shown in detail, namely its tail section. The projectile body 8 is here a mechanically supporting projectile casing of the projectile 6. The projectile body 8 extends along a central longitudinal axis 10.

When the projectile 6 is deployed or in operation, it is fired or launched along its central longitudinal axis 10 with the aid of a barrel weapon (not shown) in a flight direction 12 (symbolized by an arrow). After leaving the barrel of the barrel weapon, the projectile 6 moves in flight in the direction of flight 12 through the surrounding air 14. The projectile 6 is fired or is set up in such a way that it spins 16 (represented by an arrow) around the central longitudinal axis 10 has, ie rotated in the direction of this arrow about the central longitudinal axis 10.

The floor section 2 or the floor 6 also contains six fins 18, of which in 1 only four pieces are visible. The fins 18 are distributed uniformly over the circumference of the projectile 6 in the circumferential direction about the central longitudinal axis 10 .

Each of the fins 18 is rotatably mounted on the projectile body 8 with the aid of an axis of rotation 20 and about this respective axis of rotation 20 in or against a direction of rotation, i.e. by means of a rotary movement 22 (directed in the direction of rotation, movement itself and its direction indicated by an arrow). The axes of rotation 20 are here bolts or plug-in pins and their course or longitudinal direction is indicated or extended by dash-dotted lines for clarification.

1 shows a first end position (beginning) of the possible rotational movement 22, namely a firing position A of the fins 18, the 2 until 4 the respective opposite end position (end) of the rotary movement 22, namely a respective flight position F of the fins 18.

In the firing position A, the fins 18 are in contact with the projectile body 8, in the flight position 11 they protrude from the projectile body 8 or protrude from it and therefore serve as tail units.

The axes of rotation 20 each run in the direction of the central longitudinal axis 10, here each parallel to the central longitudinal axis 10.

During the flight of the projectile 6, a force K (indicated by an arrow) is generated, which causes the rotational movement 22 of the fins 18 from the firing position A to the flight position F ( 2 until 4 ) about the axis of rotation 20 causes. Strictly speaking, the force K causes a torque about the axis of rotation 20.

In the present case, this force K is caused neither by the relaxation of a prestressed spring nor by an active drive element in the projectile 6 that is operated electrically, pneumatically, hydraulically or detonatively. In the present case, the force K consists exclusively of two components. The first component is a centrifugal force L (indicated by arrows), which acts on each of the fins 18 and is generated or caused by the spin 16 of the projectile 6 and thus all of the fins 18 about the central longitudinal axis 10 .

The second component is an aerodynamic force D (see 2 ), which also acts on the respective fin 18 and which is caused or generated by the air 14 which flows past the respective fin 18 or flows against it during the flight of the projectile 6 .

In the present case, the aerodynamic force D is also generated in particular by the fact that the direction of rotation of the rotary movement 22 is directed in the opposite direction to the direction of rotation of the twist 16 . This is because, shortly after the fins 18 are lifted off the firing position A, air 14 flows through a respective underside 24 of the fin 18 (see Fig 2 ) on, namely as soon as a corresponding gap has formed between the free end 26 and the projectile body 8 into which air 14 can flow.

It can be seen that the fin 18 is shaped such that in the firing position A The radially outward-pointing outer surface 30 supplements the circular-cylindrical peripheral surface 32 of the projectile body 8, continuing here with the same radius to the central longitudinal axis 10.

The fins 18 also have a basic shape in the manner of a circular section 38 (indicated by dashed lines) in a plane transverse to the central longitudinal axis 10 . This basic shape follows - which can be seen in particular in firing position A - the perimeter 36 of the projectile 6, which encloses the entire outer surface (with fins in firing position A) tightly. In other words, the cross section of the fins 18, here related to their outer surface 30, follows the perimeter 36 in the firing position A.

2 shows floor section 2 1 with the fins 18 in flight position F. In synopsis with 1 It can be seen that the fins 18 lie in the respective recesses 28 in the projectile body 8 in the firing position A and that the recesses 28 are designed as negative forms of the fins 18, i.e. the fins 18 lie essentially tightly in the space created by the recess 28 or .fill this space with almost no gaps.

In a respective transverse direction 34 to the outer surface 30, the fins also have a thickness H, which decreases with increasing distance from the axis of rotation 20. In other words, the fins taper in terms of their wall thickness/profile thickness, starting from the axis of rotation 20 towards the free end 26 thereof. In firing position A (see 1 ) corresponds to the transverse direction 34 so the radial direction with respect to the central longitudinal axis 10; in flight position F ( 2 until 4 ), on the other hand, the corresponding circumferential direction around the central longitudinal axis 10.

A part of the surface of the fins 18 , here the front side facing away from the free end 26 or towards the axis of rotation 20 , is designed as a stop surface 40 in each case. In the flight position F, the stop surface 40 rests against the projectile body 8, here its peripheral surface 32, and limits the rotational movement 22 so that it ends at the flight position F.

The fins 18 here consist exclusively of two parts, namely a wing section 42, albeit curved, but still fundamentally rectangular and two hinge sections 44 protruding from the wing section 42. The hinge sections 44 serve to accommodate the axis of rotation 20. The stop surface 40 is on the wing section 42 arranged.

In the flight position F, the fin 18 can be locked in relation to the projectile body 8 so that it is held in the flight position F and can no longer leave it in the direction of the firing position, ie counter to the rotary movement 22 .

2 and 3 shows the fin 18 in the flight position F, but in the unlocked state. 3 shows detail III 2 . 4 shows the locked state in flight position F.

The locking is effected by a locking movement 48 (represented by an arrow) in the form of a displacement of the fin 18 counter to the direction of flight 12 along the axis of rotation 20 relative to the projectile body 8. A tongue and groove arrangement 46 is used for locking. This is on the axis of rotation 20 arranged. To clarify this is in the 2 and 3 one of the fins 18 is shown in such a way that it is shown cut off in the area of its hinge sections 44 . In this case, the fin 18 has a tongue 50 , and the projectile body 8 has a groove 52 of the tongue and groove arrangement 46 .

An elastic pressure element 54, here a helical spring, is arranged on the axis of rotation 20. This is supported—axially compressively prestressed—between the projectile body 8 and the fin 18, in this case the hinge section 44 thereof. The pressure element 54 serves to initiate/support the latching movement 48. The latching movement 48 is, however, also brought about by the air 14 flowing against the fin 18 during flight. As soon as the fin 18 has reached sufficiently close to the flight position F in its rotational movement 22, the spring 50 slides into the groove 52 via cones 56 that are formed on in each case. The cones 56 therefore form a kind of insertion section for the tongue and groove arrangement 46. When the flight position F is fully reached, the tongue 50 can slide into the groove 52 with a precise fit and with a positive fit; the fin 18 is then locked in the flight position F.

4 shows the corresponding situation. Both the inflowing air 14 as well as compared to the 2 and 3 Partially relaxed but still axially prestressed pressure element 54 prevent the fin 18 or spring 50 from moving out of the groove 52 counter to the latching movement 48 .

The hinge sections 44 designed in one piece and integrally with the fin 18 together with hinge sections 58 also designed in one piece and integrally with the projectile body 8 form respective hinges 60 which enable the rotary movement 22 of the fin 18 about the axis of rotation 20 . In the present embodiment, there are two hinges 60 per fin 18 . The elastic pressure element 54 is arranged and supported between the two adjacent hinges 60 with its ends 62 on the two hinges 60 from. In the present case, one end 62 is supported on the hinge section 58 and the other end 62 on the hinge section 44 .

Reference List

2

floor section

4

tailplane

6

bullet

8th

body

10

central longitudinal axis

12

flight direction

14

Air

16

spin

18

fin

20

axis of rotation

22

rotary motion

24

bottom

26

free end

28

recess

30

outer surface (fin)

32

Circumferential Surface (Bullet Body)

34

transverse direction

36

perimeter

38

circle section

40

stop surface

42

wing section

44

Hinge Section (Fin)

46

tongue and groove arrangement

48

snap movement

50

Tongue (tongue and groove arrangement)

52

Groove (tongue and groove arrangement)

54

Pressure element, elastic

56

cone

58

Hinge Section (Bullet Body)

60

hinge

62

end (print element)

A

firing position

f

flight position

K

Power

L

centrifugal force

D

power (aerodynamic)

H

thickness

QUOTES INCLUDED IN DESCRIPTION

This list of documents cited by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent Literature Cited

• EP 3032213 B1 [0002]

Claims (15)

Projectile section (2) as at least part of an intended projectile (6), - with a projectile body (8) extending along a central longitudinal axis (10) of the projectile (6) and having a spin (16) about the central longitudinal axis (10) when the projectile (6) is in flight as intended after it has been fired, - with at least one fin (18) which is rotatably mounted on the projectile body (8) about an axis of rotation (20) between a firing position (A) resting against the projectile body (8) and a flight position (F) protruding from the projectile body (8), - the axis of rotation (20) running in the direction of the central longitudinal axis (10), - wherein during the flight of the projectile (6) a force (K) is generated, which causes a rotational movement (22) of the fin (18) from the firing position (A) to the flight position (F) about the axis of rotation (20), - Wherein the force (K) is caused neither by relaxation of a prestressed spring nor by an electrically or pneumatically or hydraulically or detonatively operated active drive element in the projectile (6). floor section (2) after claim 1 , characterized in that the force (K) exclusively on the fin (18) acting centrifugal force (L), which is caused by the twist (16) and the intrinsic mass of the fin (18), and / or at the The aerodynamic force (D) acting on the fin (18) is caused by the air (14) flowing against the fin (18) during flight of the projectile (6). Projectile section (2) according to one of the preceding claims, characterized in that the rotational movement (22) has a direction of rotation which is opposite to that of the spin (16). Projectile section (2) according to one of the preceding claims, characterized in that the fin (18) rests in a recess (28) in the projectile body (8) in the firing position (A). Projectile section (2) according to one of the preceding claims, characterized in that the fin (18) is shaped in such a way that in the firing position (A) its radially outward-pointing outer surface (30) overlaps the circular-cylindrical peripheral surface (32) of the projectile body ( 8) added. Projectile section (2) according to one of the preceding claims, characterized in that the fin (18) has a decreasing thickness (H) in a transverse direction (34) to the outer surface (30) with increasing distance from the axis of rotation (20). Projectile section (2) according to one of the preceding claims, characterized in that the fin (18) in a transverse plane to the central longitudinal axis (10) has a basic shape following the circumference (36) of the projectile (6) in the manner of a circular section (38). Projectile section (2) according to one of the preceding claims, characterized in that part of the surface of the fin (18) is designed as a stop surface (40) which in the flight position (F) comes to rest on the projectile body (8) and thereby the rotary movement (22) the fin is limited in the flight position (F). floor section (2) after claim 8 , characterized in that the fin (18) exclusively has a wing section (42) and one or more hinge sections (44) protruding therefrom for receiving the axis of rotation (20), and the stop surface (40) is arranged on the wing section (42). Projectile section (2) according to one of the preceding claims, characterized in that the fin (18) can be locked in relation to the projectile body (8) in the flight position (F). floor section (2) after claim 10 , characterized in that the fin (18) can be locked by a tongue and groove arrangement (46) arranged on the axis of rotation (20), which can be locked by a latching movement (48) in the form of a displacement of the fin (18) in the flying position ( F) can be latched against the direction of flight (12) relative to the projectile body (8) along the axis of rotation (20), the fin (18) having the groove (52) and the projectile body (8) having the tongue (50) or vice versa. floor section (2) after claim 11 , characterized in that it has an elastic pressure element (54) which is arranged on the axis of rotation (20) and is supported between the projectile body (8) and the fin (18) and which is set up to support the latching movement (48) counter to the direction of flight (12). floor section (2) after claim 12 , characterized in that the fin (18) is mounted on the axis of rotation (20) via at least two hinges (60) and the elastic pressure element (54) is arranged between two adjacent hinges (60) and has its axial ends (62 ) supported on both hinges (60). Projectile (6) having a projectile section (2) according to one of the preceding claims. Method for generating a force (K) on a projectile section (2) as at least part of a specific projectile (6), - with a projectile body (8) extending along a central longitudinal axis (10) of the projectile (6), which is fired and/or set up in such a way that, when the projectile (6) is flying as intended, it has a spin (16th ) around the central longitudinal axis (10), - with at least one fin (18) which is rotatably mounted on the projectile body (8) about an axis of rotation (20) between a firing position (A) resting against the projectile body (8) and a flight position (F) protruding from the projectile body (8), - the axis of rotation (20) running in the direction of the central longitudinal axis (10), - wherein during the flight of the projectile (6) the force (K) is generated, which causes a rotational movement (22) of the fin (18) from the firing position (A) to the flight position (F) about the axis of rotation (20), - Wherein the force (K) is caused neither by relaxation of a prestressed spring nor by an electrically or pneumatically or hydraulically or detonatively operated active drive element in the projectile (6).

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