Rotorcraft

Abstract

The invention relates to: a body (2); a rotor (3) positioned to extend outwardly from the body (2) and to rotate about its axis; at least one blade (4) extending outwardly from the rotor (2) and providing lift and / or thrust to the body (2) by its movement; at least one external blade (401) positioned in the blade (4) and providing lift and / or thrust to the body (2); at least one mechanism (5) enabling the external blade (401) to switch from a first, retracted position, in which the external blade is located almost entirely in the blade (4), to a second position, in which the external blade extends outwardly from the blade (4), by linear movement under the influence of centrifugal force generated during the movement of the rotor (2).

Description

TECHNICAL FIELD

[0001] The present invention relates to a blade folding system used in rotary wing aircraft such as helicopters. BACKGROUND

[0002] Rotary wing aircraft are capable of performing their flight operations by means of structures known as rotors and having blades on them that affect the flow. In terms of the aircraft, the larger size of the blades means that the blades will have higher thrust. However, since the blades occupy a large volume, the storage, parking and transportation of the helicopter presents a problem. In this regard, systems for folding the blades have been developed, but they are not automated. At present, the blades are folded by removing the screws at the points where the blade roots are connected to the rotor and bringing the blades to a single direction. This situation is very laborious in the field and causes time loss. In this regard, folding the blades by the field personnel can be strategically disadvantageous in terms of the operation and safety of the operating personnel.

[0003] The US patent document US3773433A included in the state of the art describes a blade coupled to the rotor that can be elongated and shortened under the effect of centrifugal force. It includes a stop element that interacts with the blade. Thus, the blade movement caused by the centrifugal force is limited in undesirable cases. In addition, according to the described patent document, elastic elements are provided in at least one blade section, thereby enabling the blade section to perform an elongation and shortening movement by centrifugal force. SUMMARY

[0004] With the rotary wing aircraft developed with the present invention, an effective and reliable solution is provided to the problem of the occupying volume of the blades when the rotary wing aircraft such as the helicopter is not in operation.

[0005] Another object of the present invention is to provide a practical and economic solution for folding the blades.

[0006] Another object of the present invention is to improve the folding of the blades in terms of aerodynamics.

[0007] A rotorcraft implemented for the purpose of the present invention comprises: a body; a rotor located inside the body and rotating at a user-determined speed; at least one blade positioned to be connected to the rotor so that the rotorcraft is able to perform flight operations with the thrust and lift generated by the rotorcraft itself by means of the movement of the rotor; at least one external blade provided in the blade, positioned in a closed first position inside the blade when the rotorcraft is not actively operated, and the at least one external blade is moved outwards from inside the blade and opened by the centrifugal force generated on the blade by the movement of the rotor and thus the movement of the blade, thereby being brought to a second position; and a mechanism enabling the external blade to be moved, providing mechanical transmission between the external blade and the blade, and enabling automatic switching from the first position to the second position and / or from the second position to the first position.

[0008] Due to the telescopic movement occurring between the external blade and the blade causing geometric incompatibility, the rotorcraft of the present invention comprises a transition device having a shape that surrounds the external blade and the blade, thus providing a transition between the blade and the external blade with aerodynamic transition surface smoothness, and acting as a stopper for the movement of the external blade inside the blade.

[0009] In one embodiment of the present invention, the rotorcraft comprises a transition device having a well-matched profile cross-section at one end with the blade and a well-matched profile cross-section at the other end with the external blade.

[0010] In one embodiment of the present invention, the rotorcraft has an at least partially interference-fitted connection between the transition device and the external blade when the moving external blade is in the second position. Thus, the rotorcraft comprises a transition device enabling high efficient structural performance.

[0011] In one embodiment of the present invention, the rotorcraft comprises a transition device coupled to the blade by means of an interference-fitted connection. Thus, it contributes to the structural performance.

[0012] In one embodiment of the present invention, the rotorcraft comprises a transition device having a form that thins and narrows from the section of the transition device that encloses the blade to the section thereof that encloses the external blade.

[0013] In one embodiment of the present invention, the rotorcraft comprises a transition device having at least one vibration-damping surface therein, thereby minimizing the vibrations caused by the movement of the external blade when switching from the first position to the second position.

[0014] In one embodiment of the invention, the rotorcraft comprises a transition device which itself has a protrusion which acts as a stop and prevents the outer blade from coming off the blade completely when it is in the second position.

[0015] In one embodiment of the invention, the rotorcraft comprises a transition device which has a double curvature form, making it possible to achieve good aerodynamic performance during flight of the rotorcraft.

[0016] In one embodiment of the invention, the rotorcraft comprises a transition device which has a more rigid material (such as metal) which is different from the material of the blade and the outer blade and which minimizes vibrations.

[0017] In one embodiment of the invention, the rotorcraft comprises at least one slide which allows the outer blade to move from the first position to the second position and / or from the second position to the first position, at least one cord which is connected to the outer blade, at least one winding bearing on which the cord is wound, a shaft around which the winding bearing is allowed to rotate, and a mechanism which has at least one elastic element connected to the shaft, thereby providing a resistance to the centrifugal force generated by the movement of the blade and the outer blade. Thereby, when the centrifugal force generated by the rotation of the rotor and the blade exceeds the potential force of the elastic element, the cord is allowed to rotate on the winding bearing, thereby enabling the outer blade to move from the first position to the second position. When the rotation of the rotor and the blade stops, the force of the elastic element exceeds the reduced centrifugal force, enabling the cord to be wound on the winding bearing in the opposite direction towards the elastic element, thereby allowing the outer blade to reach the first position from the second position in the blade.

[0018] In one embodiment of the invention, the rotorcraft comprises a mechanism which has an elastic element of the helical spring type.

[0019] In one embodiment of the invention, the rotorcraft comprises a transition device which has a length which is 1 / 6 of the length of the outer blade, and a blade which has a length which is 1.80 to 1.85 times the length of the outer blade. Thereby, the telescopic movement between the blade and the outer blade and the aerodynamic performance protection effect of the transition device on the outer blade and the blade are ensured at an optimum level.

[0020] In one embodiment of the invention, the rotorcraft comprises a polymeric transition device made of resin impregnated fabric. BRIEF DESCRIPTION OF DRAWINGS

[0021] A rotorcraft implemented in order to achieve the purpose of the invention is shown in the drawings, in which:

[0022] Figure 1 It is a 3D diagram of a rotorcraft.

[0023] Figure 2 This is a three-dimensional view of the blade in the first position.

[0024] Figure 3 This is a three-dimensional view of the blade in the second position.

[0025] Figure 4 This is a three-dimensional view of the mechanism and the outer blades in the second position.

[0026] Figure 5 This is a three-dimensional view of the mechanism and the outer blades in the first position.

[0027] Figure 6 It is a three-dimensional diagram of the mechanism inside the blades.

[0028] The components shown in the figure are individually assigned reference numerals, and the corresponding terms for these numerals are listed below.

[0029] 1. Rotorcraft

[0030] 2.Ontology

[0031] 3. Rotor

[0032] 4. Leaves

[0033] 401. External blades

[0034] 5. Institution

[0035] 501. Sliding component

[0036] 502. Rope

[0037] 503. Coil bearing

[0038] 504. Shaft

[0039] 505. Elastic element

[0040] 6. Transition device

[0041] 7. Protrusion Detailed Implementation

[0042] The rotorcraft 1 comprises a body 2, a rotor 3 rotating around its axis and positioned to extend outwardly from the body 2, at least one blade 4 extending outwardly from the rotor 3 and providing lift and / or thrust to the body 2 by its movement, at least one external blade 401 positioned in the blade 4 and providing lift and / or thrust to the body 2, at least one mechanism 5 enabling the external blade 401 to switch from a retracted first position, in which the external blade is located almost entirely in the blade 4, to a second position, in which the external blade extends outwardly from the blade 4, by linear movement under the influence of centrifugal force generated during the movement of the rotor 3. Figure 1 , Figure 2 , Figure 3 )

[0043] The rotorcraft 1 of the invention comprises a transition device 6 located on the blade 4, at least a part of which circumferentially grips the blade 4 and at least a part of which cooperates with the outer peripheral shape of the external blade 401, the transition device having a shape that surrounds the external blade and the blade, thus providing a transition between the blade 4 and the external blade 401 with aerodynamic transition surface smoothness, and the transition device being configured to prevent the external blade 401 from completely detaching from the blade 4. Figure 2 , Figure 3 )

[0044] The blade 4 of the rotorcraft 1 is capable of rotating by means of the rotor 3 extending outwardly from the body 2. Thus, the blade 4 provides sufficient lift and thrust to the rotorcraft 1 and performs flight maneuvers. The blade 4 comprises an external blade 401 that moves to the second position ready for flight, such that the blade comes out of the retracted first position by the centrifugal force generated by the rotation of the blade 4 around the rotor 3. By means of the mechanism 5, the external blade 401 can telescopically enter and exit the blade 4 depending on the centrifugal force. In this way, the external blade 401 does not occupy space when the rotorcraft 1 is not in operation. An effective and efficient system for adjusting the length of the external blade 401 is provided. Figure 2 , Figure 3 )

[0045] The telescopic movement capability between the blade 4 and the external blade 401 can be achieved by the dimensional difference of the external blade 401 and the blade 4. The transition device 6 is provided on the blade 4, thus effectively reducing the generated aerodynamic disadvantages such as air resistance, and at the same time limiting the maximum distance that the external blade 401 will come out of the blade 4. The transition device 6 provides a safe telescopic system while effectively ensuring the flow performance of the telescopic blade 4. The transition device 6 acts as a compensation for the aerodynamic surface between the blade 4 and the external blade 401, thus providing an effective, safe and efficient use for the telescopic system.

[0046] ( Figure 2, Figure 3 )

[0047] In an embodiment of the application, the rotorcraft 1 comprises a transition device 6 having a profile cross-section at one end that is nearly identical to the profile cross-section of the blade 4 and a profile cross-section at the other end that is nearly identical to the profile cross-section of the outer blade 401. Thereby, an effective aerodynamic surface profile is provided for the rotorcraft 1. Figure 2 、 Figure 3 )

[0048] In an embodiment of the application, the rotorcraft 1 comprises a transition device 6 having a connection structure that is at least partially interference-fitted between itself 6 and the outer blade 401 when the outer blade 401 is in the second position, thereby providing effective structural properties.

[0049] In an embodiment of the application, the rotorcraft 1 comprises a transition device 6 that is coupled to the blade 4 by means of an interference fit, thereby facilitating structural properties.

[0050] In an embodiment of the application, the rotorcraft 1 comprises a transition device 6 having a form that is thinned and narrowed from a portion surrounding the blade 4 towards a portion surrounding the outer blade 401. Figure 2 、 Figure 3 )

[0051] In an embodiment of the application, the rotorcraft 1 comprises a transition device 6 having at least one vibration-damping surface therein, thereby damping vibrations caused by the movement of the outer blade 401 when switching from the first position to the second position. Figure 4 )

[0052] In an embodiment of the application, the rotorcraft 1 comprises a transition device 6 having a protrusion 7 therein, thereby preventing the outer blade 401 in the second position from disengaging from the blade 4. Figure 4 )

[0053] In an embodiment of the application, the rotorcraft 1 comprises a transition device 6 having a double curvature form, thereby facilitating aerodynamic surface properties.

[0054] In an embodiment of the application, the rotorcraft 1 comprises a transition device 6 having a more rigid material than the material of the blade 4 and the outer blade 401, thereby allowing vibrations to be reduced.

[0055] In one embodiment of the application, the rotorcraft 1 comprises at least one slide 501 allowing the outer blade 401 to move by sliding from a first position to a second position and / or from a second position to a first position, at least one cord 502 connected to the outer blade 401, at least one winding bearing 503 on which the cord 502 winds, a shaft 504 allowing the winding bearing 503 to rotate around its axis, and a mechanism 5 having at least one elastic element 505 connected to said shaft 504, thereby providing a resistance to the centrifugal force generated by the movement of the blade 4 and of the outer blade 401. Figure 5 )

[0056] In one embodiment of the application, the rotorcraft 1 comprises a mechanism 5 having an elastic element 505 of the helical spring type.

[0057] In one embodiment of the application, the rotorcraft 1 comprises a transition device 6 having a length of 1 / 6 of the length of the outer blade 401 and a blade 4 having a length of 1.80 to 1.85 times the length of the outer blade 401. This ensures a safe and efficient fit between the blade 4, the outer blade 401 and the transition device 6.

[0058] In one embodiment of the application, the rotorcraft 1 comprises a polymeric transition device 6 made of a fabric impregnated with a resin.

Claims

1. A rotorcraft (1) comprising: a body (2); a rotor (3) rotating about its axis and positioned to extend from inside said body (2) outwardly; at least one blade (4) extending outwardly from said rotor (3) and providing lift and / or thrust to said body (2) by its own movement; at least one outer blade (401) positioned in said blade (4) and providing lift and / or thrust to said body (2); at least one mechanism (5) enabling said outer blade (401) to switch from a first position in which it is located almost entirely in said blade (4) to a second position in which it extends outwardly from said blade (4) by means of linear movement under the influence of centrifugal force generated during the movement of said rotor (3), characterized in that said rotor aircraft comprises a transition device (6), said transition device being disposed on said blade (4), at least a portion of said transition device circumferentially gripping said blade (4) and at least a portion of said transition device cooperating with the outer peripheral shape of said outer blade (401), the profile cross-section of one end of said transition device being almost identical to the profile cross-section of said blade (4) and the profile cross-section of the other end being almost identical to the profile cross-section of said outer blade (401), said transition device being configured to prevent said outer blade (401) from completely detaching from said blade (4), and said transition device having a shape that surrounds said outer blade and said blade, thus providing a transition between said blade (4) and said outer blade (401) with aerodynamic transition surface smoothness, and said transition device acting as a stop for the movement of said outer blade within said blade.

2. The rotorcraft (1) as claimed in claim 1, characterized in that said transition device (6) having a connection structure with at least partial interference fit between said transition device (6) and said outer blade (401) when said outer blade (401) is in said second position, thus providing efficient structural performance.

3. The rotorcraft (1) as claimed in claim 1, characterized in that said transition device (6) being connected to said blade (4) in the form of an interference fit, thus contributing to structural performance.

4. The rotorcraft (1) as claimed in claim 1, characterized in that said transition device (6) having a form that thins and narrows from the portion surrounding said blade (4) to the portion surrounding said outer blade (401).

5. The rotorcraft (1) according to any one of claims 1 to 4, characterized in that said transition device (6) having at least one vibration-damping surface therein, thus damping the vibrations caused by the movement of said outer blade (401) when said outer blade switches from said first position to said second position.

6. The rotorcraft (1) according to any one of claims 1 to 4, characterized in that said transition device (6) having a protrusion (7) therein, thus preventing said outer blade (401) in said second position from detaching from said blade (4).

7. The rotorcraft (1) according to any one of claims 1 to 4, characterized in that said transition device (6) having a double curvature form, thus contributing to aerodynamic surface performance.

8. The rotorcraft (1) according to any one of claims 1 to 4, characterized in that said transition device (6) having a more rigid material than the materials of said blade (4) and said outer blade (401), thus enabling vibrations to be reduced.

9. The rotorcraft (1) according to any one of claims 1 to 4, characterized in that Further comprising: At least one sliding element (501) allowing said external blade (401) to move by sliding from said first position to said second position and / or from said second position to said first position; at least one cord (502) connected to said external blade (401); at least one winding bearing (503) on which said cord (502) is wound; a shaft (504) allowing said winding bearing (503) to rotate around an axis of said shaft; and a mechanism (5) having at least one elastic element (505) connected to said shaft (504) so as to provide a resistance to the centrifugal force generated by the movement of said blade (4) and said external blade (401).

10. The rotorcraft (1) as claimed in claim 9, characterized in that Said elastic element (505) of said mechanism (5) is of the helical spring type.

11. The rotorcraft (1) according to any one of claims 1 to 4, characterized in that The length of said transition device (6) is 1 / 6 of the length of said external blade (401) and the length of said blade (4) is 1.80 to 1.85 times the length of said external blade (401).

12. The rotorcraft (1) according to any one of claims 1 to 4, characterized in that Said transition device (6) is polymeric and made of resin-impregnated fabric.

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