Folding wing for a missile and a missile having at least one folding wing arranged thereon

Abstract

A folding wing for a missile comprises a wing root, an upper wing part foldably supported at the wing root around a swiveling axis, at least one first elastically pre-stressed force element and a latching device. The at least one first elastically pre-stressed force element is coupled with the wing root and the upper wing part and is designed for permanently urging the upper wing part into a working position relative to the wing root through introducing a torque. The latching device is designed for arresting the upper wing part on reaching the working position automatically.

Claims

1. A folding wing for a missile, comprising: a wing root connected to or integrated with a fuselage of the missile, the wing root comprising a resting surface; an upper wing part foldably supported at the wing root around a swiveling axis of a hinge, the hinge comprising a first hinge bushing integrated into the upper wing part, a second hinge bushing integrated into the wing root, and an axle element; the first hinge bushing comprising: a gliding side surface; a first base having a first axle borehole to receive the axle element, a first side from which the upper wing part extends, and a second side opposite the first side; a first protrusion extending from the second side of the first base; and a second protrusion extending from the second side of the first base, wherein the second protrusion extends further away from the first base in comparison to the first protrusion; the second hinge bushing comprising: a second base having an upper resting surface and a side end surface; a flange extending from the upper resting surface of the second base; and a second axle borehole arranged in the flange to receive the axle element; a first pre-stressed force element coupled with the wing root and the upper wing part to urge the upper wing part into a working unfolded position relative to the wing root through introducing a torque; and a second pre-stressed force element configured to axially urge the first hinge bushing and the second hinge bushing onto each other in an axial direction of the hinge; wherein, when the folding wing is in a folded state, the gliding side surface of the first hinge bushing touches the side end surface of the second hinge bushing, and the first hinge bushing does not touch the flange of the second hinge bushing; and wherein, when the folding wing is in the working unfolded position, the first hinge bushing touches the flange of the second hinge bushing, an end surface of the first protrusion of the first hinge bushing rests on the upper resting surface of the second hinge bushing to prevent swiveling back of the upper wing part, and an end surface of the second protrusion of the first hinge bushing rests on the resting surface of the wing root to prevent over-swiveling of the upper wing part beyond the working unfolded position.

2. The folding wing of claim 1, wherein the second pre-stressed force element comprises at least one elastic tensioning element.

3. The folding wing of claim 1, wherein the first force element is a leg spring.

4. A missile comprising a fuselage and the folding wing of claim 1 attached to the fuselage.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Further characteristics, advantages and potential applications of the present embodiment result from the following description of the exemplary embodiments and the figures. In this respect, all described and/or graphically illustrated characteristics also form the object of the embodiment individually and in arbitrary combination regardless of their composition in the individual claims or their references to other claims. Furthermore, identical or similar objects are identified by the same reference symbols in the figures.

(2) FIG. 1 shows an exemplary embodiment of a folding wing in an isometric view having a folded-away upper wing part.

(3) FIG. 2 shows the folding wing in an isometric view with the upper wing part in a working position.

(4) FIGS. 3a and 3b show an exemplary embodiment of a first, pre-stressed force element in two different illustrations.

DETAILED DESCRIPTION

(5) FIG. 1 shows a folding wing 2 having an upper wing part 4 and a wing root 6, wherein the upper wing part 4 is arranged in a swiveling manner at the wing root 6 through a hinge 8 creating a hinge axis 10. The hinge 8 comprises a first hinge component 12 integrated into the upper wing part having a number of first hinge bushings 14 as well as a second hinge component 16 integrated into the wing root having a number of second hinge bushings 18. For integration, the hinge components 12 and 16 may be realized as single parts with the upper wing part 4 or the wing root 16, respectively, or may be attached thereto.

(6) For clarification of an exemplary design, a first hinge bushing 14 and a second hinge bushing 18 are illustrated separately. The first hinge bushing 14 comprises a base 20, in which an axle borehole 22 is arranged. From a first side 24 of the base 20, a flange 26 extends for receiving the upper wing part 4, wherein this is slightly tapered relative to the base and arranged symmetrically thereto. At a second side 28 opposite the first side 24 a first protrusion 30 as well as a second protrusion 32 are arranged at one outer edge of the base each, wherein the second protrusion 32 clearly further extends away from the base 20 in comparison to the first protrusion 30. As is apparent in the overview of the whole folding wing 2, all second protrusions 32 of all first hinge bushings 14 create a surface-like stop. In the context of the above description, both protrusions 30 and 32 are to be considered as first form-fit means.

(7) A second hinge bushing 18 comprises a surface-like base 34 having an upper resting surface 35, wherein at an outer edge 36 a surface-like flange 38 having an axle borehole 40 is arranged eccentrically to the surface of the base 34 and extends therefrom substantially perpendicular thereto. The base 34 is connected to the wing root 6 through a surface opposite the resting surface 35 in planar fashion. The resting surface 35 is to be understood as a second form-fit means, which corresponds with the first form-fit means in form of the first protrusion 30.

(8) In the position, shown in FIG. 1, the hinge bushings 14 and 18 touch each other with gliding surfaces facing to each other, such that the first hinge bushing 14 touches an end surface 40 of a base 34 of a neighboring second hinge bushing 18.

(9) Two rotational springs 42, which are to be considered as first pre-stressed force element in context with the above description, are arranged between the upper wing part 4 and the wing root 6, are mechanically coupled with these and permanently exert a torque onto the upper wing part 4, such that it is urged into a working position, in which the upper wing part 4 is arranged perpendicular to the wing root 6, and creates a full, usable wing with it. An axle element 44 extends through all axle boreholes 22 and 40 of the hinge components 12 and 16.

(10) A second pre-stressed force element in form of a spring 40, which is connected to the axle element 44, which is furthermore mechanically coupled with the first hinge bushing 14 through a locking ring 48, urges the hinge bushing 14 to the neighboring second hinge bushing 18 along the hinge axis 10. Upon reaching the working position, this lead to an axial placement of the upper wing part 4 relative to the wing root 6, as shown in FIG. 2 in the following.

(11) FIG. 2 shows the folding wing 2 in the working position, in which the upper wing part 4 having the first hinge component 12 is displaced relative to the second hinge component 16 along the hinge line 10 compared to the illustration in FIG. 1. This is made possible by the first protrusion 30 of the first hinge bushing 14 being rotated so far around the hinge axis 10 through a torque acting upon the upper wing part 4 that they just do not touch the end surface 40 of the second hinge bushings 18. In result, the force permanently introduced by the spring 46 during the rotation process leads to shifting the first hinge bushings 14 along each base 34 of the second hinge bushings 18 along the hinge axis 10, until the first hinge bushings 14 snuggly touch the flanges 38. The first protrusions 30 then rest on the respective associated bases 34, preventing a swiveling-back of the upper wing part 4. Hence, the combination of a first protrusion 30, a base 34, and a spring 46 create a latching device, which reliably and mechanically simple conducts a latching of the upper wing part in the working position.

(12) The continuous connection of a plurality of second protrusions 32 leads to the creation of an elongate web, which flushly rests on the wing root 6 with an end surface 50 in the working position. As apparent from FIG. 1, each base 34 extends to an outer edge 52 of the wing root 6 not to a full extent, but in each case leaves free a resting surface 54, respectively. In the context of the above description, the resting surface is to be understood as a second form-fit means, which corresponds to the first form-fit means in form of the second protrusion 32. As shown in FIG. 2, the second protrusions 32 snuggly rest on the resting surface 54 and consequently cover the hinge 8 to prevent a through-flow. Additionally, a swiveling of the upper wing part 4 over the working position is prevented.

(13) For a further clarification, FIGS. 3a and 3b show an exemplary design of the rotational spring 42, which is also known as leg spring, in different views. The rotational spring 42 comprises two legs 56 and 58, which at both sides connect to a winding arrangement 60, which creates the torque. The winding arrangement 60 comprises a through-opening 62, through which a positioning at the axle element 44 may be accomplished. The legs 56 and 58 each are mechanically connected to the upper wing part 4 or the wing root 6, respectively, e.g. through insertion into a suitable bore hole in the upper wing part and the form-fit pressing to the wing root 6, as apparent from e. g. FIG. 2.

(14) In addition, it should be pointed out that comprising does not exclude other elements or steps, and a or an does not exclude a plural number. Furthermore, it should be pointed out that characteristics or steps which have been described with reference to one of the above exemplary embodiments may also be used in combination with other characteristics or steps of other exemplary embodiments described above. Reference characters in the claims are not to be interpreted as limitations.

(15) While at least one exemplary embodiment has been presented in the foregoing detailed description, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the embodiment in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment, it being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the embodiment as set forth in the appended claims and their legal equivalents.