阅读说明：本技术 旋翼航空器的降落装置 (Landing device for rotorcraft ) 是由 秋叶公三郎 村田岩 于 2018-04-06 设计创作，主要内容包括：实施方式的旋翼航空器的降落装置为了在更良好的条件下能够使旋翼航空器着陆时的充分的能量吸收和避免机体与地面的接触并存而具有2根滑行管和横管,所述横管用于连结所述2根滑行管并安装于旋翼航空器的机体,其中由复合材料构成所述横管的至少一部分。另外,实施方式的旋翼航空器具备上述降落装置,能够在更良好的条件下使着陆时的充分的能量吸收和避免机体与地面的接触并存。(The landing device for a rotorcraft according to the embodiment includes 2 glide pipes and a cross pipe for connecting the 2 glide pipes and attaching the cross pipe to the airframe of the rotorcraft so as to enable sufficient energy absorption when the rotorcraft lands and avoid contact between the airframe and the ground under better conditions, wherein at least a part of the cross pipe is made of a composite material. In addition, the rotorcraft according to the embodiment includes the landing device described above, and can achieve both sufficient energy absorption during landing and avoidance of contact between the body and the ground under better conditions.)

1. A landing gear for a rotorcraft, comprising:

2 sliding pipes; and

a cross tube for connecting the 2 glide tubes and for attaching to the fuselage of the rotorcraft,

wherein at least a portion of the cross tube is constructed from a composite material.

2. A landing gear for a rotorcraft according to claim 1, wherein,

and forming the whole transverse tube by the composite material.

3. A landing gear for a rotorcraft according to claim 1, wherein,

the central portion of the cross tube is constructed of the composite material while the end portions of the cross tube are constructed of metal.

4. A landing gear for a rotorcraft according to claim 1 or claim 3, wherein,

the transverse tube is formed from a non-bent part and a bent part, the non-bent part being formed from the composite material and the bent part being formed from metal.

5. A landing gear for a rotorcraft according to any one of claims 1 to 4, wherein,

the cross tube has a characteristic that rigidity changes nonlinearly with respect to a change in displacement.

6. A rotary wing aircraft landing gear according to claim 5,

the characteristic is a characteristic represented by a curve that is convex downward in a coordinate system in which the horizontal axis represents the displacement and the vertical axis represents the rigidity.

7. A landing gear for a rotorcraft according to any one of claims 1 to 6, wherein,

the proportion of fibers that reinforce the composite material of the cross pipe in the direction perpendicular to the longitudinal direction of the cross pipe is made greater among fibers that reinforce the upper and lower sides of the composite material of the cross pipe than among fibers that reinforce the composite material on the front and rear sides of the cross pipe in the direction perpendicular to the longitudinal direction of the cross pipe.

8. A landing gear for a rotorcraft according to any one of claims 1 to 7, wherein,

the ratio of fibers that reinforce the transverse tube in a direction perpendicular to the longitudinal direction of the transverse tube is maximized among fibers that reinforce either the upper side or the lower side of the composite material that forms the transverse tube, and the ratio of fibers that reinforce the transverse tube in the longitudinal direction of the transverse tube is maximized among fibers that reinforce the remainder of the composite material.

9. A rotorcraft comprising:

a descending device according to any one of claims 1 to 8.

10. A method of landing a rotorcraft, wherein,

the 2-piece sliding pipe for connecting the landing device of the rotorcraft is made of a composite material and is mounted on at least a part of a horizontal pipe of the airframe of the rotorcraft, thereby ensuring the absorption amount of energy when the rotorcraft lands and avoiding the airframe of the rotorcraft from contacting the ground.

11. A method of landing a rotorcraft according to claim 10, wherein,

by adjusting the orientation of the fibres constituting the composite material, the absorption of energy is ensured while avoiding contact of the body with the ground.

Technical Field

Embodiments of the present invention relate to a device for landing a rotorcraft, and a method for landing a rotorcraft.

Background

Conventionally, gliders are known as landing apparatuses for rotorcraft (see, for example, patent document 1, patent document 2, and patent document 3). The skid is a landing device using a skid-like (そり -like) sliding material. When a rotorcraft lands, energy is absorbed by the deformation of the runners.

Disclosure of Invention

Technical problem to be solved by the invention

In order to sufficiently ensure the amount of energy absorbed when a rotorcraft lands, the runners need to be deformed greatly. On the other hand, when the runner is excessively deformed, the body may come into contact with the ground. Therefore, in the design of the runner, it is important to have sufficient energy absorption and to avoid the coexistence of the body in contact with the ground.

Therefore, an object of the present invention is to enable sufficient energy absorption when a rotorcraft lands and to avoid contact between the airframe and the ground under better conditions.

Means for solving the problems

A landing device for a rotorcraft according to an embodiment of the present invention includes 2 glide pipes and a cross pipe attached to a body of the rotorcraft to connect the 2 glide pipes, and at least a part of the cross pipe is made of a composite material.

The rotorcraft according to the embodiment of the present invention includes the landing device described above.

In the method for landing a rotorcraft according to the embodiment of the present invention, the 2 glide pipes for connecting the landing devices of the rotorcraft are made of a composite material and attached to at least a part of the horizontal pipe of the airframe of the rotorcraft, thereby preventing the airframe of the rotorcraft from coming into contact with the ground while ensuring the amount of energy absorbed when the rotorcraft lands.

Drawings

Fig. 1 is a side view of a rotorcraft equipped with runners as a landing gear according to a first embodiment of the present invention.

Fig. 2 is a perspective view showing the structure of a runner mounted to the rotorcraft shown in fig. 1.

Fig. 3 is a sectional view showing a structural example of the cross tube shown in fig. 1 and 2.

Fig. 4 is a view showing how the cross tube shown in fig. 1 to 3 deforms.

Fig. 5 is a graph showing an example of mechanical characteristics imparted to the cross tube shown in fig. 1 to 3.

Fig. 6 is a cross-sectional view showing another configuration example of the cross tube shown in fig. 1 and 2.

Fig. 7 is a partially enlarged cross-sectional view showing an example of a case where a part of 2 plate-like composite materials having different fiber orientation angles are formed by a common fiber-reinforced layer.

Fig. 8 is a front view showing the structure of a runner as a landing gear according to a second embodiment of the present invention.

Fig. 9 is a front view showing the structure of a runner as a landing gear according to a third embodiment of the present invention.

Detailed description of the preferred embodiments

A device for landing a rotorcraft, and a method for landing a rotorcraft according to embodiments of the present invention will be described with reference to the drawings.

(first embodiment)

(Structure and function)

Fig. 1 is a side view of a rotorcraft including runners as a landing gear according to a first embodiment of the present invention, and fig. 2 is a perspective view showing a structure of runners attached to the rotorcraft shown in fig. 1.

As shown in fig. 1, the rotorcraft 1 is configured by attaching a runner 4 as a landing device to a body 3 provided with a rotor 2. As shown in fig. 1 and 2, the typical runner 4 is composed of 2 runner pipes 10 in a skid shape and 2 bent cross pipes 11 for attaching the runner pipes 10 to the machine body 3.

Each of the glide pipes 10 is a glide material arranged parallel to a longitudinal axis X that is one of the reference axes of the rotorcraft 1. On the other hand, each cross tube 11 is a support member for being attached to the lower portion of the machine body 3 in a state where 2 gliding tubes 10 are connected. Therefore, the longitudinal direction of each cross tube 11 is curved on a plane approximately perpendicular to the longitudinal axis X of the rotorcraft 1. One horizontal tube 11 is disposed on the front side, and the other horizontal tube 11 is disposed on the rear side. Furthermore, the deformation of the cross tubes 11 also acts to absorb energy during landing of the rotorcraft 1.

Each cross tube 11 is made of a composite material reinforced with a fiber-reinforced resin. Examples of the composite material include Glass Fiber Reinforced Plastics (GFRP) Reinforced with Glass Fiber resin, Carbon Fiber Reinforced Plastics (CFRP) Reinforced with Carbon Fiber resin, and Nomex (registered trademark) Reinforced with paper resin.

The conventional slide pipe and horizontal pipe are made of metal. Compared with metal, the composite material has higher specific rigidity. Therefore, the weight reduction can be achieved by forming the cross tube 11, which is made of a composite material and which serves to absorb energy at least when the rotorcraft 1 is landing. Of course, the glide tube 10 may also be constructed of a composite material.

When cross tube 11 is constructed from a composite material, anisotropy can be imparted to the mechanical properties of cross tube 11. That is, the composite material has anisotropic properties while changing mechanical properties depending on the stacking direction of the fibers. Therefore, the rigidity against bending of the cross tube 11 in the vertical direction is reduced by the anisotropy of the composite material, while the rigidity against stretching of the cross tube 11 in the longitudinal direction can be increased. That is, the cross tube 11 having a weak bending and a strong stretching can be designed and manufactured.

Fig. 3 is a cross-sectional view showing a structural example of the cross tube 11 shown in fig. 1 and 2.

As illustrated in fig. 3, the cross tube 11 can be produced by combining 2 bent plate-shaped composite material pieces 20A, 20B, and the composite material pieces 20A, 20B can be bonded to each other by, for example, an adhesive or a fastener. Alternatively, the composite material sheets 20A, 20B may be integrally molded (Co-curing). When the composite material sheets 20A and 20B are integrally molded, as will be described later, a part of the composite material sheets 20A and 20B can be formed of a common fiber-reinforced layer.

The cross section of each composite material sheet 20A, 20B is formed in an arc shape. Therefore, when 2 pieces of composite material sheets 20A, 20B are combined, the cross tube 11 is formed into a cylindrical shape. Since the cross tube 11 is curved in the longitudinal direction, the composite material sheets 20A and 20B are also curved in the longitudinal direction.

The first composite material sheet 20A may be made of a plate-shaped composite material covering the range of about 3/4 on the upper surface side of the cross tube 11. On the other hand, the second composite material sheet 20B may be made of a plate-like composite material covering the range of about 1/4 on the lower surface side of the cross tube 11. Further, the orientation angle of the fibers constituting the first composite sheet 20A and the orientation angle of the fibers constituting the second composite sheet 20B can be determined to be different from each other.

This can impart anisotropy to the rigidity of the horizontal tube 11. The composite material having the fiber longitudinal direction in the longitudinal direction of the cross tube 11 has high flexural rigidity and tensile rigidity in the longitudinal direction of the cross tube 11. On the other hand, the composite material having the fiber longitudinal direction as the circumferential direction perpendicular to the longitudinal direction of the cross tube 11 has low flexural rigidity and tensile rigidity in the longitudinal direction of the cross tube 11.

Therefore, the proportion of the fibers reinforcing in the direction perpendicular to the longitudinal direction of the cross tube 11 among the fibers reinforcing the second composite material sheet 20B on the lower side of the cross tube 11 can be set to the maximum. On the other hand, the proportion of the fibers reinforcing in the longitudinal direction of the transverse tube 11 among the fibers reinforcing the first composite material sheet 20A covering the remaining portion constituted by the front side, the upper side, and the rear side of the transverse tube 11 may be set to the maximum.

In this way, the slider 4 can be made with relatively low rigidity only on the lower side of the cross pipe 11 and relatively high rigidity including other portions on the front side, the upper side, and the rear side.

A typical structural component of an aircraft is made by combining composite materials with fibers oriented at angles of 0 degrees, 45 degrees, and 90 degrees. Therefore, the first composite material sheet 20A and the second composite material sheet 20B constituting the horizontal tube 11 can be produced by combining the composite materials having the fiber orientation angles of 0 degrees, 45 degrees, and 90 degrees.

Further, if the cross section of the horizontal tube 11 is circular, the fibers having an orientation angle of 90 degrees with respect to the circumferential direction perpendicular to the longitudinal direction of the horizontal tube 11 as the longitudinal direction are formed in an arc shape in the cross section of the horizontal tube 11. On the other hand, fibers having an orientation angle of 0 degrees with the longitudinal direction of the cross tube 11 being the longitudinal direction are dotted in the cross section of the cross tube 11.

In the cross tube 11, it is important to impart the lowest possible rigidity in each direction. Therefore, for example, the orientation of the fibers may be determined so that the composite material having the fiber orientation angle of 0 degrees and the composite material having the fiber orientation angle of 90 degrees are included at least 10% in both the first composite material sheet 20A and the second composite material sheet 20B.

As a practical example, the first composite material pieces 20A covering the front side, the upper side, and the rear side of the cross tube 11 may be 0-degree-rich composite materials in which the proportion of composite materials having a fiber orientation angle of 0 degrees is 50%, the proportion of composite materials having a fiber orientation angle of 45 degrees is 40%, and the proportion of composite materials having a fiber orientation angle of 90 degrees is 10%. On the other hand, the second composite material sheet 20B covering the lower side of the cross tube 11 may be a 90-degree-rich composite material in which the proportion of the composite material having a fiber orientation angle of 0 degrees is 10%, the proportion of the composite material having a fiber orientation angle of 45 degrees is 40%, and the proportion of the composite material having a fiber orientation angle of 90 degrees is 50%.

If the second composite material sheet 20B covering only the lower side of the cross tube 11 is made of a composite material rich in 90 degrees and the first composite material sheets 20A covering the front, upper, and rear sides of the cross tube 11 are made of a composite material rich in 0 degrees, the cross tube 11 is easily bent and deformed only the lower side of the cross tube 11 and is hardly bent and deformed on the front, upper, and rear sides of the cross tube 11.

The main effective stiffness for the bending stiffness of the cross tube 11 is the upper and lower stiffness. On the other hand, the rigidity in the axial direction of the cross tube 11 is effective as the rigidity over the entire circumference. Therefore, in the case of the above-described composite material laminated structure, the bending rigidity and the axial rigidity can be made different in the entire cross tube 11 as compared with the case of the uniformly laminated structure over the entire circumference. That is, the slider 4 having relatively low bending rigidity of the horizontal tube 11 and relatively high axial rigidity can be manufactured.

Fig. 4 is a view showing a modification of the horizontal tube 11 shown in fig. 1 to 3.

When the rotorcraft 1 lands, a load in the up-down direction acts on the cross tube 11 before deformation, which has a curved shape shown by a solid line in fig. 4. Therefore, as shown by the broken line in fig. 4, the horizontal tube 11 undergoes a bending deformation substantially vertically downward.

When the bending deformation of the cross tube 11 becomes large, a load in a substantially horizontal direction acts on the cross tube 11. As a result, friction is generated between the slide pipe 10 and the ground 30. When the friction between the slide tube 10 and the ground 30 exceeds the maximum static friction, the cross tube 11 is deformed in a manner to expand in the horizontal direction as shown by the chain line in fig. 4.

Therefore, in addition to the bending load, a tensile load acts on the slide pipe 10. That is, a bending load is applied at an initial stage of deformation of the cross tube 11, and then a tensile load is applied.

Therefore, as shown in fig. 3, the rigidity of the lower side of the horizontal pipe 11 is reduced, while the rigidity of the other portions can be set to be large. Accordingly, when the rotorcraft 1 lands and a bending load in the vertical direction acts on the cross tube 11, the lower side of the cross tube 11 is easily deformed, and thus energy can be sufficiently absorbed. Further, when the deformation of the lateral tube 11 becomes large and a tensile load acts on the lateral tube 11, the increase in the deformation can be suppressed by providing rigidity to the front side, the upper side, and the rear side of the lateral tube 11. As a result, the contact between the body 3 of the rotorcraft 1 and the ground 30 can be reliably avoided.

Fig. 5 is a graph showing an example of mechanical characteristics imparted to the cross tube 11 shown in fig. 1 to 3.

In fig. 5, the horizontal axis represents the displacement of the cross tube 11 and the vertical axis represents the rigidity of the cross tube 11. As shown in fig. 3, if the rigidity of the lower side of the horizontal tube 11 is reduced and the rigidity of the other portions is set to be large, the horizontal tube 11 having the characteristic that the rigidity changes nonlinearly with the change in displacement can be manufactured as shown in fig. 5. More specifically, the horizontal tube 11 can be given mechanical characteristics represented by a downward convex curve in a coordinate system in which the horizontal axis shown in fig. 5 is a displacement and the vertical axis is a rigidity.

If the transverse tube 11 is given a nonlinear characteristic in which the greater the deformation, the greater the rigidity, the amount of energy absorbed when the rotorcraft 1 lands can be ensured, and contact between the airframe 3 of the rotorcraft 1 and the ground 30 can be avoided. Moreover, the balance of the amount of energy absorbed when rotorcraft 1 lands and the effect of avoiding contact between airframe 3 of rotorcraft 1 and ground 30 can be optimized by adjusting the orientation of the fibers that make up the composite material.

In addition, even if the second composite material sheet 20B made of the composite material rich in 90 degrees covering the range of 1/4 and the first composite material sheet 20A made of the composite material rich in 0 degrees covering the range of 3/4 are inverted in the vertical direction, the same effect can be obtained. That is, even if the slider 4 is manufactured so that only the upper side of the cross pipe 11 has relatively low rigidity and the other portions including the front side, the lower side, and the rear side have relatively high rigidity, the same effect can be obtained.

That is, if the ratio of the fibers reinforcing in the direction perpendicular to the longitudinal direction of the cross tube 11 among the fibers reinforcing either the upper side or the lower side of the composite material constituting the cross tube 11 is maximized, and the ratio of the fibers reinforcing in the longitudinal direction of the cross tube 11 among the fibers reinforcing the remaining portion of the composite material is maximized, the rigidity that increases nonlinearly with the increase in displacement can be imparted to the cross tube 11. As a result, the following effects can be obtained: the amount of energy absorbed when rotorcraft 1 lands can be ensured while avoiding contact of body 3 of rotorcraft 1 with ground 30.

Fig. 6 is a cross-sectional view showing another configuration example of the cross tube 11 shown in fig. 1 and 2.

As shown in fig. 6, the cross tube 11 may be formed of 4 composite material sheets 20C, 20D, 20E, and 20F on the front side, the rear side, and the upper and lower sides. That is, the horizontal tube 11 may be divided into 4 pieces.

In this case, the composite material sheets 20C and 20D disposed on the front and rear sides of the cross tube 11 may be made of a 0-degree-rich composite material, as in the case of the first composite material sheet 20A shown in fig. 3. On the other hand, the composite material pieces 20E, 20F disposed on the upper and lower sides of the cross tube 11 may be made of a composite material rich by 90 degrees.

However, in the example of the four-piece division shown in fig. 6, the range of the composite material having a 90-degree-rich fiber orientation angle is increased as compared with the example of the two-piece division shown in fig. 3, and therefore, the proportion of the composite material having a fiber orientation angle of 90 degrees may be decreased. Specifically, the composite material sheets 20E and 20F disposed on the upper and lower sides of the cross tube 11 may be made of the composite material having the fiber orientation angle of 0 degrees in the same ratio as the composite material having the fiber orientation angle of 90 degrees, while the composite material sheets 20C and 20D disposed on the front and rear sides of the cross tube 11 may be made of the composite material having a rich fiber orientation angle of 0 degrees.

That is, if the proportion of the composite materials having the fiber orientation angles of 90 degrees contained in the composite material sheets 20E, 20F disposed on the upper and lower sides of the cross tube 11 is greater than the proportion of the composite materials having the fiber orientation angles of 90 degrees contained in the composite material sheets 20C, 20D disposed on the front and rear sides of the cross tube 11, the cross tube 11 can be imparted with the targeted anisotropy. In other words, if the proportion of the fibers that reinforce the transverse tube 11 in the direction perpendicular to the longitudinal direction of the transverse tube 11 among the fibers that reinforce the upper and lower sides of the composite material that constitutes the transverse tube 11 is greater than the proportion of the fibers that reinforce the transverse tube 11 in the direction perpendicular to the longitudinal direction of the transverse tube 11 among the fibers that reinforce the front and rear sides of the composite material, it is possible to impart rigidity to the transverse tube 11 that increases nonlinearly with an increase in displacement.

In addition to the above exceptions, the proportion of the composite material having a fiber orientation angle of 90 degrees may be changed stepwise to 3 stages or more instead of 2 stages. That is, the horizontal tube 11 may be divided into regions thinner than the 4 regions on the front side, the rear side, the upper side, and the lower side, and the fiber orientation may be adjusted. Further, it is not necessarily possible to impart anisotropy to the horizontal tube 11 using a composite material in which the orientation angle of the fibers is 0 degree or a composite material in which the orientation angle of the fibers is 90 degrees. Specifically, by adjusting the proportion of the composite material in which the orientation angle of the fibers is 45 degrees or the proportion of the composite material in which the orientation angle of the fibers is 60 degrees, it is possible to design and manufacture the horizontal tube 11 in which the rigidity changes nonlinearly depending on the displacement.

The specific fiber orientation can be determined by simulation or experiment to obtain the desired nonlinear change in stiffness.

The hollow cross tube 11 made of the composite material can be produced by any method. Typical examples of Molding methods for composite materials include a method in which a sheet-like prepreg obtained by impregnating fibers with an uncured thermosetting Resin is laminated, the laminate of the prepreg is shaped in conformity with the shape of the composite material, and then heat-cured by an autoclave apparatus, and an RTM (Resin Transfer Molding) method.

The RTM method is a method of molding a composite material in which sheet-like fibers are laminated to form a shape, and then a thermosetting resin is impregnated and cured by heating. The RTM method is a method of impregnating a fiber with a Resin by vacuum pressure, and is called VaRTM (vacuum assisted Resin Transfer Molding). Further, the cross pipe 11 may be manufactured by a hybrid molding method in which a prepreg lamination method and an RTM method are used in combination.

The cross tube 11 is hollow. Therefore, for example, the transverse tube 11 can be integrally molded by a method in which a prepreg or a fiber is laminated on a water-soluble core, a composite material is molded by heat curing of a resin impregnated in the fiber, and then the core is removed. In this case, as shown in fig. 3, if the horizontal tube 11 is divided into two pieces, the horizontal tube 11 can be produced by laminating at least 2 kinds of prepregs or fibers having different reinforcement directions. Therefore, the manufacturing labor can be reduced.

Another example of the manufacturing method is a method in which the composite material sheets that form the bends of the cross tube 11 are each thermoformed and then assembled. In this case, as shown in fig. 6, if the cross tube 11 is formed by 4 composite material sheets 20C, 20D, 20E, and 20F on the front side, the rear side, the upper side, and the lower side, the composite material sheets 20C, 20D, 20E, and 20F may be respectively heat-molded using a molding die having a surface curved in a convex shape. The horizontal tube 11 can be produced by assembling the thermoformed composite material sheets 20C, 20D, 20E, and 20F. Therefore, as shown in fig. 6, if the horizontal tube 11 is divided into 4 pieces, the manufacturing using the molding die becomes easy.

On the other hand, as shown in fig. 3, in the case where the cross tube 11 is formed by 2 composite material sheets 20A, 20B, the first composite material sheet 20A covering the front, upper and rear sides may be heat-molded using a water-soluble core or a flexible bag (ブラダバッグ), and the second composite material sheet 20B forming the lower side of the cross tube 11 may be heat-molded using a molding die having a surface curved in a convex shape. Then, the cross tube 11 can be manufactured by assembling the first composite material pieces 20A and the second composite material pieces 20B after molding. In this case, since 2 composite material sheets 20A and 20B are to be assembled, the assembly work is easier than the case of dividing the horizontal tube 11 into 4 pieces.

Of course, the first composite material sheet 20A covering the front, upper, and rear sides may be further divided into 2 composite material sheets, and the molding die may be removed from the composite material sheets. In this case, the cross tube 11 shown in fig. 3 can be produced by heating and curing 3 composite material sheets using a molding die and assembling the heated and cured composite material sheets.

The joining of the composite material sheets to each other when the cross tube 11 is assembled and manufactured without integral molding may be performed using an adhesive or a metal part.

When the cross tube 11 is fabricated by assembly, the cross tube 11 can be divided in the longitudinal direction. In this case, if the cross tube 11 is divided into lengths enough to allow the core to be pulled out, a composite material sheet having a circular cross section can be integrally molded.

When the cross tube 11 is integrally molded in the circumferential direction, such as when the cross tube 11 is divided in the longitudinal direction or when the cross tube 11 is molded using a water-soluble core, even if the cross tube is a composite material having a plurality of arc shapes with different fiber orientation angles, a part of the fiber reinforcement layers can be shared as described above.

Fig. 7 is a partially enlarged cross-sectional view showing an example in which a part of 2 plate-like composite materials having different fiber orientation angles are formed by a common fiber-reinforced layer.

As shown in fig. 7, when 1 plate-shaped composite material 42 is produced at the end of 2 plate-shaped composite material sheets 41A and 41B having mutually different orientation angles of the connecting fibers, a part of the fiber-reinforced layers can be made common. That is, the 2 composite material sheets 41A and 41B can be configured only by the specific layer and the fiber-reinforced layer having the different fiber length directions.

In the example shown in fig. 7, the longitudinal direction of the fibers of only one composite material sheet 41A of 1 layer is 0 degrees, whereas the longitudinal direction of the fibers of the other composite material sheet 41B is 90 degrees. Of the other layers, the composite material sheets 41A and 41B are both formed of a common fiber-reinforced layer in which the longitudinal direction of the fibers is 0 degree, 45 degrees, and 90 degrees.

The rotorcraft 1 described above is an aircraft in which the cross tubes 11 are made of a composite material, and the cross tubes 11 constitute skids 4 as landing gears. The slider 4 described above is configured to impart rigidity, which changes non-linearly according to displacement, to the cross pipe 11 by utilizing anisotropy of the composite material.

(Effect)

Therefore, according to the rotorcraft 1 to which the runners 4 are attached, it is possible to achieve weight reduction as compared with a rotorcraft to which a conventional metal runner is attached. Further, by imparting rigidity to cross tube 11 that changes non-linearly according to displacement, sufficient energy absorption during landing of rotorcraft 1 and avoidance of contact between airframe 3 and ground 30 can be achieved more reliably.

(second embodiment)

Fig. 8 is a front view showing the structure of a runner as a landing gear according to a second embodiment of the present invention.

The skid 4A of the second embodiment shown in fig. 8 is different from the skid 4 of the first embodiment in that the entire cross tube 11 is not made of a composite material, but a point at which a part of the cross tube 11 is made of a composite material. Since other structures and functions of the runner 4A of the second embodiment are not substantially different from those of the runner 4 of the first embodiment, only the runner 4A is illustrated, and the same structures or corresponding structures are denoted by the same reference numerals and description thereof is omitted.

As shown in fig. 8, the central portion 11A of the cross tube 11, which has a small amount of bending, is made of a composite material, while the both end portions 11B of the cross tube 11 may be made of metal. In this way, since the amount of bending of the tubular composite material is small, the bladder or the core can be easily pulled out when the tubular composite material is manufactured. As a result, the horizontal tube 11 can be easily manufactured. That is, it becomes easy to integrally mold the cross pipe 11 in the circumferential direction. In addition, the central portion 11A made of a composite material and the both end portions 11B made of a metal may be joined by an adhesive or a fastener.

Thus, if at least a portion of cross tube 11 is made of a composite material, it is possible to provide cross tube 11 with a reduced weight and a rigidity that changes non-linearly. Furthermore, if the transverse tube 11 is given a rigidity that varies non-linearly, sufficient energy absorption during landing of the rotorcraft 1 and avoidance of contact between the airframe 3 and the ground can be further reliably combined.

(third embodiment)

Fig. 9 is a front view showing the structure of a runner as a landing gear according to a third embodiment of the present invention.

In the runner 4B of the third embodiment shown in fig. 9, the transverse tube 11 is constituted by the non-bent portion 11C and the bent portion 11D which are not bent, the non-bent portion 11C is constituted by a composite material, and on the other hand, the point at which the bent portion 11D is constituted by a metal is different from the runner 4A of the second embodiment. Since other structures and functions of the runner 4B of the third embodiment are not substantially different from those of the runner 4A of the second embodiment, only the runner 4B is illustrated, and the same structures or corresponding structures are denoted by the same reference numerals and description thereof is omitted.

As shown in fig. 9, the cross tube 11 can be constituted by the non-bent portions 11C and the bent portions 11D. That is, the center portion and both end portions of the horizontal tube 11 can be constituted by the non-bent portions 11C, and the center and both non-bent portions 11C can be connected by the bent portions 11D.

In this case, the core can be easily pulled out by the non-bent portion 11C. Therefore, the non-bent portion 11C can be easily produced by integrally molding the composite material in which the orientation angle of the fibers is not necessarily constant. As a result, the advantages of the composite material can be effectively utilized. That is, the bent portion 11D which is difficult to be made of a composite material can be easily made of a metal, and the non-bent portion 11C which is easy to be made of a composite material can be made of a composite material to reduce the weight and impart rigidity which changes nonlinearly, so-called characteristics of a composite material can be exhibited.

The non-bent portion 11C made of a composite material and the bent portion 11D made of a metal can be connected by an adhesive or a fastener.

(other embodiments)

While specific embodiments have been described above, the embodiments described above are merely examples and do not limit the scope of the invention. The novel methods and apparatus described herein can be embodied in various other forms. In the method and apparatus described herein, various omissions, substitutions, and changes can be made without departing from the spirit of the invention. The scope and the spirit of the invention include the scope and the equivalents of the appended claims, and include such various embodiments and modifications.