JPH1114299A - Wing for airframe - Google Patents

Abstract

PROBLEM TO BE SOLVED: To ensure light weight, heat resistance and strength by forming a profile of a front edge by a crossbeam member, forming a recess opened on both side surfaces, and charging a heat resistant charging member in the recess. SOLUTION: A wing front edge 10 has a crossbeam member 11 for forming a profile of a front edge part as a basic frame. And, a plurality of rectangular recesses 12 are formed at the member 11 to arrange on both surfaces S1 , S2 in an extending direction of the wing. That is, the recesses 12 formed on one surface side are isolated via ribs 13 in its arranging direction. And, the recesses 12 formed on both side surfaces S1 , S2 are isolated by partition members 14 as a partition part. And, light weight heat resistant charging member (e.g. resin material) 20 is charged in the recess 12 of the member 1 formed in this manner. Thus, light weight, heat resistance and strength can be sufficiently ensured, and its manufacture is easily done at a low cost.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a wing provided on a flying object such as a rocket, and more particularly, to a wing for a flying object characterized by a structure of a leading edge portion.

[0002]

2. Description of the Related Art As shown in FIG. 1, for example, a flying object 1 such as a rocket has a fuselage portion 2, a propulsion device 3 arranged at the rear end of the fuselage portion 2 to generate a propulsive force, and an outer periphery of the propulsion device 3. It is constituted by a tail 4 and the like provided in a cross shape on the surface of the fuselage 2 in the vicinity.

The tail wing 4 serves as a stable wing in flight.
Alternatively, it functions as a steering wing for controlling the flight direction, and has heat resistance capable of withstanding aerodynamic heating during flight, and also withstands a pressure difference and the like generated on both surfaces of the tail wing 4 particularly when functioning as a steering wing. The required strength and rigidity are required. In particular, at the leading edge 5 of the tail 4, the effect of aerodynamic heating is great, and in some cases, it may reach up to nearly 2000 ° C. As described above, when heated to a high temperature, the Young's modulus of the member forming the outer skin of the blade decreases, and the required rigidity cannot be obtained.

Accordingly, in the conventional leading edge portion 5 of the blade, as shown in FIG. 2, relatively thick outer plates 8a and 8b forming both surfaces of the blade with respect to the leading edge end member 6 and the spar member 7 are provided. 8b, 9
a, 9b were joined by welding Lw or the like, and a structure in which a reinforcing member or the like was filled in the internal space was adopted.

[0005]

However, in the above-mentioned conventional leading edge structure, since the outer plates 8, 9 are directly subjected to aerodynamic heating, a thicker outer plate is used to secure rigidity and the like. Wing weight was increased. In other words, when a thick outer plate is not used, sufficient rigidity or the like cannot be obtained.

Further, each of the members 6, 7,
In order to combine the parts 8 and 9, it has been difficult to secure sufficient manufacturing accuracy due to deformation after welding or accumulation of welding errors.

SUMMARY OF THE INVENTION In view of the above-mentioned problems of the prior art, it is an object of the present invention to provide a flying object wing which is lightweight, has sufficient heat resistance, strength, etc., can be easily manufactured, and can be manufactured at low cost. It is in.

[0008]

According to a first aspect of the present invention, a flying object wing is formed so as to form at least a contour of a leading edge and to be open at a surface on each side of the leading edge. A girder member forming a concave portion to be formed and a partition portion for separating and separating the concave portion positioned on the surface on each side;
And a heat-resistant filling member filled in the concave portion.

The wing for a flying object according to a second aspect of the present invention has a configuration in which the side wall of the concave portion is formed in a tapered shape that widens from the surface of the wing toward the inside.

The wing for a flying object according to a third aspect of the present invention is configured such that the partition portion extends in a flat plate shape at a position substantially at the center from the surface on each side of the wing.

The flying object wing according to a fourth aspect of the present invention is configured such that the filling member is made of a resin material.

The flying object wing according to claim 5 of the present invention has a configuration in which a through hole is provided in the partition.

[0013]

According to the flying object wing according to the first aspect of the present invention, the spar member forms at least the contour of the front edge portion and also forms the concave portion which is open on both side surfaces, and the heat resistant portion is formed in the concave portion. Since the surface of the wing is formed by filling the filling member of the above, it is possible to suppress the invasion of heat by aerodynamic heating or a decrease in rigidity or the like due to aerodynamic heating in the portion of the filling member. In the part of the member, the rib in the thickness direction of the blade is sufficiently thick, that is, a rib having a sufficient height can be formed, so that the heat entering the spar member while securing sufficient mechanical strength and rigidity is ensured. Can be diffused.

Therefore, the weight of the entire leading edge of the blade can be reduced while ensuring heat resistance against aerodynamic heating, strength, rigidity, and the like.

[0015] Further, since a partition portion for separating and separating the two concave portions is provided between the concave portion formed on one surface side of the wing and the concave portion formed on the other surface side, both surfaces of the wing are provided. Even if there is a pressure difference between them, the pressure difference does not cause the filling member provided in the recess to fall off, and the filling member can be reliably held in the recess.

[0016] Further, the beam forming member having the concave portion and the partition portion can be easily formed by subjecting the member having the contour shape of the blade leading edge portion to machining or the like from both sides serving as the surface of the blade. it can. Therefore, it is possible to achieve an improvement in manufacturability, a reduction in manufacturing cost, and the like, as compared with a structure in which the inside is lightened.

According to the wing for a flying object according to the second aspect of the present invention, since the opening of the concave portion is formed to be narrower than the bottom, the wing vibration and the like are provided in addition to the above effects. Also, the filling member can be made more difficult to come off, and the filling member can be held more firmly in the concave portion.

According to the wing for a flying object according to the third aspect of the present invention, since the partition portion has a flat plate shape and is located symmetrically from both surfaces of the wing, uniformity in terms of mechanical strength, rigidity, etc. is obtained. In addition, the holding force for holding the filling member in the recess can be made uniform on each surface side of the blade.

According to the wing for a flying object according to the fourth aspect of the present invention, since a resin material is used as the heat-resistant filling member, it is possible not only to achieve a reduction in weight, but also to achieve an interior of the wing by aerodynamic heating. Intrusion can be prevented as much as possible, whereby the influence of the heat on the girder member can be suppressed as much as possible.

Further, by using a resin material which is cured after being filled in the concave portion, the productivity can be further improved.

According to the wing for a flying object according to the fifth aspect of the present invention, by providing a through hole in the partition portion and removing the thickness,
The weight of the entire wing can be reduced while maintaining the original function of the partition.

[0022]

Embodiments of the present invention will be described below with reference to the accompanying drawings.

FIG. 3 is a partial external perspective view showing an embodiment of a leading edge of a flying object wing according to the present invention. As shown in FIG. 3, the wing leading edge portion 10 has a spar member 11 forming a contour of the leading edge portion as a basic frame, and this spar member 11 has a plurality of surfaces S ₁ and S _{2 on} both sides. The rectangular recesses 12 are formed so as to be arranged in the direction in which the wings extend. That is, each recess 12 formed on one surface side is separated via the rib 13 in the arrangement direction,
In addition, the concave portions 12 formed on each of the surfaces S ₁ and S ₂ on both sides.
Are separated by a partition plate 14 as a partition portion.

A pair of connecting ribs 15 for connecting to the main body of the blade are formed on the rear end side of the front edge portion 10 so as to protrude rearward and extend in the extending direction of the blade. Further, the pair of connecting ribs 15 are provided with a plurality of holes 15a for inserting a connecting reamer bolt or the like.

Each part constituting the beam member 11 is integrally formed by subjecting a titanium alloy, a C / C material (carbon fiber reinforced carbon material) or the like capable of withstanding aerodynamic heating to machining or molding. ing. Further, as long as the mechanical strength and the like are satisfied, it is also possible to integrally mold the sintered material such as ceramics.

Then, the girder member 1 formed as described above
The lightweight and heat-resistant filling member 20 is embedded in the one recess 12. FIG. 3 shows a state in which the filling member 20 is buried in some of the recesses 12.

FIG. 4 is a plan view showing the root side of the leading edge of the flying object wing according to the present invention. As shown in FIG. 4, the concave portion 12 is formed over substantially the entire region on both sides of the front edge portion. As the beam member 11, weight reduction is achieved while satisfying required mechanical strength, rigidity, and the like. It is finished in a frame structure that can be done.

Also, a hole 15 provided in the coupling rib 15 is provided.
All of a are formed so as to be located on the extension of the rib 13 except for those located near the base end 11a and the tip 11b (see FIG. 7).

With the above construction, the leading edge 10 is inserted into the hole 15a by a fastening means such as a reamer bolt and the wing body 3
0 (see FIG. 8), it is possible to increase the mechanical strength, the rigidity, and the like in a state where it is attached.

Next, the shape of the concave portion 12 will be described with reference to FIGS. FIG. 5 is an enlarged sectional view taken along the line AA in FIG. 4, and FIG. 6 is an enlarged sectional view taken along the line BB in FIG.

As shown in FIGS. 5 and 6, concave portions 12 formed on the surfaces S ₁ and S ₂ on both sides of the spar member 11 forming the skeleton of the leading edge of the blade are provided with a partition plate located substantially at the center. 14 that define the recesses 12
2a is a partition plate 14 such that the recessed space has a tapered shape diverging from the surfaces S ₁ and S ₂ toward the inside.
Is inclined by a predetermined angle θ with respect to a direction perpendicular to.

The inclination angle θ is preferably large in order to prevent the filling member 20 from dropping off. However, in consideration of processing conditions when the concave portion 12 is formed by machining from the outside, the inclination angle θ is taken into consideration.
In addition, the setting is made in consideration of whether to use a material having high flexibility (cured after insertion) or a material having low flexibility such as a sintered material as the filling member 20 to be inserted. Is done.

A partition plate 14 for separating and separating the concave portions 12 formed on the surfaces S ₁ and S ₂ on both sides is formed on both surfaces S ₁ and S _2.
1, substantially equal distance from S _2, i.e., are formed so as to extend in the center line of the line symmetry.

As described above, by being positioned substantially at the center, not only the center of gravity can be brought closer to the center, but also stresses caused by aerodynamic heating or pressure load received from both surfaces S ₁ and S ₂ , etc. , Ie,
Local stress concentration and the like can be suppressed.

Further, since the partition plate 14 is covered from both sides by the filling member 20, it is not directly affected by heat due to aerodynamic heating unlike the conventional outer plate. Therefore, the plate thickness can be reduced as much as possible within a range that satisfies the required mechanical strength, rigidity, and the like, whereby the weight of the entire blade can be reduced.

[0036] Incidentally, inherent features of the partition plate 14, because at the point of preventing the falling off of the filling member 20 embedded in the concave portion 12 is not necessarily provided in the central portion, any surface S ₁ or it is also possible to provide a position offset to the S ₂ side.

Further, in the above-mentioned spar member 11, as shown in FIG. 6, a plurality of ribs 13 extending in the front-rear direction of the blade (in FIG. 6, the direction perpendicular to the plane of the paper) are provided.
These ribs 13 are formed as a integral thick extending from one surface S ₁ of the wing to the other surface S _2.

That is, since a sufficient thickness is secured in the direction in which the heat enters due to the aerodynamic heating, the heat that has entered the spar member 11 can be efficiently diffused, and a local rise in temperature can be suppressed. Further, since the section modulus of the rib 13 is set to be large, sufficient mechanical strength and rigidity against bending and the like can be secured.

Next, the filling member 20 embedded in the concave portion 12 of the beam member 11 will be described.

As shown in FIGS. 3, 4, and 6, the filling member 20 is buried in the concave portion 12 of the spar member 11,
It forms most of the wing surfaces S ₁ and S ₂ , and serves to block heat generated by aerodynamic heating from being transmitted to the inside of the wing.

Therefore, the material used for the filling member 20 must be not only lightweight but also high in heat resistance. This high heat-resistant material generally has a very low thermal conductivity, so even if the vicinity of the surface that comes into contact with air is heated to a high temperature by aerodynamic heating, no heat is transmitted to the inside, and the girder member 11 is reduced by that much. The design conditions for heat can be relaxed, that is, the thickness can be reduced.

As a specific material, it is possible to use a heat-resistant resin material such as a phenolic resin or a silicone resin, or a sintered material such as ceramics.

As a method of providing the filling member 20 in the concave portion 12, when a resin material is used as the material, the concave portion 12 is filled with a resin material in a fluid state or a flexible molded state, and then cured to a predetermined level. On the other hand, when a sintered material such as ceramics is used as the material, a tile-shaped material is embedded in the recess 12 using a heat-resistant adhesive and fixed. It can be done by doing. When the latter tile-shaped filling member is used, in order to facilitate the embedding work, the inclination angle θ of the side wall 12a defining the concave portion 12, or the gap between the tile-shaped filling member and the side wall 12a, etc. It is necessary to determine the molding size and the like of the tile-shaped filling member in consideration of the above.

Here, as shown in FIGS. 3, 4, and 6, the above-mentioned filling member 20 forms the surface of the wing (front edge) only in the opening area of the concave portion 12, and Area, the surface of the spar member 11 is exposed, and the wing (leading edge)
It forms the entire contour.

As described above, by exposing a part of the spar member 11 to be a part of the wing surface, the surface of the filling member 20 can be made to follow the exposed surface of the spar member 11. Thereby, the flatness and smoothness of the wing (leading edge) surface can be ensured.

However, as long as the above-mentioned flatness, smoothness, etc. are sufficiently ensured, the entire surface of the beam member 11 can be coated in a thin layer with the same heat-resistant material as the filling member 20. FIG. 7 is a plan view showing the tip side of the leading edge of the flying object wing according to the present invention. In the embodiment of the wing leading edge shown in FIG.
The same configuration as the embodiment shown in FIGS. 4 to 6 except that a plurality of through holes 14a are formed in the partition plate 14 that partitions the concave portion 12 formed in each of the surfaces S ₁ and S ₂ on both sides. It has become.

With the above structure, the weight of the girder member 11 and the weight of the entire wing can be reduced without significantly lowering the mechanical strength while maintaining the function of preventing the filling member 20 from falling off. be able to.

Next, the front edge 10 constructed as described above is used.
The method of connecting the wing to the wing body 30 will be described.

FIG. 8 is a partial cross-sectional view showing a state where the leading edge portion 10 is connected to the wing body 30. As an assembling procedure, as shown in FIG. 8, first, the front edge of the wing body 30 is inserted between a pair of connecting ribs 15 provided at the rear end of the front edge 10.

Subsequently, the hole 1 provided in the connecting rib 15
5a is aligned with the reamer hole 31 provided in the wing body 30, and the reamer bolt 40 and the reamer nut 41 are inserted into the hole 15a.
And it is inserted into the reamer hole 31 and both are fastened.

Thereafter, a heat-resistant material 50 is applied or stuck so as to cover the heads of the reamer bolt 40 and the reamer nut 41, respectively.

The heat-resistant material 50 is provided on both surfaces of the wing body 30.
A heat insulating cork 32 and the like are provided so as to be flush with each other.

As described above, the leading edge portion 10 and the wing body 3
This completes the assembly with zero and can be finished to the final wing.

Here, in order to increase the smoothness of the blade surface and reduce the air resistance, the entire surface can be painted using a heat-resistant paint.

The embodiments described above are merely examples of the present invention, and the present invention is not limited thereto. For example, the shape of the spar member 11 is not limited to those shown in FIGS. 3 to 7. Can be made circular or polygonal, and various types of ribs 13 and through holes 14a can be used.

The filling member 20 provided in the concave portion 12
Is not limited to the above-mentioned materials and shapes as long as the heat resistance and the heat insulating property against aerodynamic heating, which are the original functions, are ensured.

[Brief description of the drawings]

FIG. 1 shows the appearance of a conventional flying object, in which FIG. 1 (a) is a side view and FIG. 1 (b) is a plan view.

FIG. 2 is an external perspective view showing a part of a leading edge of a conventional flying object wing.

FIG. 3 is an external perspective view showing a part of a leading edge of a flying object wing according to the present invention.

FIG. 4 is a plan view showing a root side of a leading edge of the flying object wing according to the present invention.

FIG. 5 is an enlarged cross-sectional view taken along the line AA in FIG.

FIG. 6 is an enlarged sectional view taken along a line BB in FIG. 4;

FIG. 7 is a plan view showing another embodiment of the leading edge of the flying object wing according to the present invention.

FIG. 8 is a cross-sectional view showing a state in which the leading edge of the wing for a flying object according to the present invention and the wing main body are combined.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Flying object 4 Tail 5 Front edge 10 Front edge 11 Beam member 12 Concave part 12a Side wall 13 Rib 14 Partition plate (partition part) 14a Through hole 15 Coupling rib 15a hole 20 Filling member 30 Wing body

Claims (5)

[Claims] At least a contour of a leading edge is formed and separated by separating a recess positioned to open on a surface on each side of the leading edge and the recess positioned on a surface on each side. A girder member forming a partition portion to be formed;
And a heat-resistant filling member filled in the concave portion. 2. The flying object wing according to claim 1, wherein a side wall of the concave portion is formed in a tapered shape that widens from the surface of the wing toward the inside. 3. The wing for a flying object according to claim 1, wherein the partition portion extends in a plate shape at a position substantially at the center from the surface on each side of the wing. 4. The flying object wing according to claim 1, wherein the filling member is made of a resin material. 5. The flying object wing according to claim 1, wherein a through hole is provided in the partition portion.