Rotary wing air vehicle

Abstract

A rotary wing aircraft has a body (2), a rotor (3) positioned so as to extend outward from within the body (2) and to rotate about its axis, at least one blade (4) extending outward from the rotor (2) and providing lift and/or thrust force to the body (2) by its movement, at least one outer blade (401) positioned in the blade (4) and providing lift and/or thrust force to the body (2), and at least one mechanism (5) enabling the outer blade (401) to switch from a retracted first position in which the it is almost entirely located in the blade (4) to a second position in which it extends outward from the blade (4) by moving linearly under the influence of the centrifugal force generated during the movement of the rotor (2).

Claims

1. A rotary wing air vehicle (1) comprising: a body (2); a rotor (3) having an axis, the rotor (3) rotating about axis thereof and coupled to the body (2); at least one blade (4) extending outward from the rotor (3) and providing lift and/or thrust force to the body (2) by movement of the blade (4); at least one outer blade (401) positioned in the blade (4) and providing lift and/or thrust force to the body (2); a mechanism (5) enabling the outer blade (401) to switch from a retracted first position in which the outer blade is located in the blade (4) to a second position in which it extends outward from the blade (4) by moving linearly under the influence of the centrifugal force generated during the movement of the rotor (3); and a transition apparatus (6) which is provided on the blade (4), at least a part of which circumferentially grips the blade (4) and at least a part of which is form-fitting with the circumference of the outer blade (401), which has one end with a profile cross-section that is the same as that of the blade (4) and which has another end with a profile cross-section that is the same as that of the outer blade (401), which is configured to prevent the outer blade (401) from completely coming out of the blade (4), and which provides a transition with an aerodynamic transitional surface smoothness between the blade (4) and the outer blade (401) as a result of having a form that surrounds both the outer blade and the blade, and functions as a stopper for the movement of the outer blade within the blade.

2. The rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) has at least a partially interference fit connection structure (F) with the outer blade (401) when the outer blade (401) is in the second position, thereby providing an efficient structural performance.

3. The rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) is connected to the blade (4) in an interference fit form, thereby contributing to the structural performance.

4. The rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) has a form that becomes thinner and narrower from a part thereof surrounding the blade (4) to a part thereof surrounding the outer blade (401).

5. The rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) has at least one dampening surface therein, thereby dampening the vibration resulting from the movement of the outer blade (401) while it switches from the first position to the second position.

6. The rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) has a protrusion (7) therein, preventing the outer blade (401) from going out of the blade (4) in the second position.

7. A rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) has a double curvature form, thereby contributing to the aerodynamic surface performance.

8. The rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) has a more rigid material that is different from the material of the blade (4) and outer blade (401), thereby enabling the vibration to be reduced.

9. The rotary wing air vehicle (1) as claimed in claim 1, comprising: at least one slide (501) allowing the outer blade (401) to move by sliding from the first position to the second position and/or from the second position to the first position, at least one rope (502) connected to the outer blade (401), at least one winding bearing (503) on which the rope (502) is wound, and a shaft (504) having an axis, the shaft (504) allowing the winding bearing (503) to rotate around the axis of the shaft (504), and wherein the mechanism (5) has at least one elastic element (505) to which the shaft (504) is connected for providing resistance against the centrifugal force generated by the movement of the blade (4) and the outer blade (401).

10. The rotary wing air vehicle (1) as claimed in claim 9, wherein the elastic element (505) of the mechanism (5) is of a helical spring type.

11. The rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) has a length of th of the length of outer blade (401) and the blade (4) has a length that is 1.80 to 1.85 times the length of the outer blade (401).

12. The rotary wing air vehicle (1) as claimed in claim 1, wherein the transition apparatus (6) is polymeric and manufactured from a resin-impregnated fabric.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) In an embodiment of the invention, the rotary wing air vehicle comprises a polymeric transition apparatus made of a resin-impregnated fabric.

(2) The rotary wing air vehicle realized to achieve the object of the invention is shown in the attached figures, wherein from these figures;

(3) FIG. 1 is a perspective view of the rotary wing air vehicle.

(4) FIG. 2 is a perspective view of the blade in the first position.

(5) FIG. 3 is a perspective view of the blade in the second position.

(6) FIG. 4 is a perspective view of the mechanism and the outer blade in the second position.

(7) FIG. 5 is a perspective view of the mechanism and the outer blade in the first position.

(8) FIG. 6 is a perspective view of the mechanism in the inner blade.

DETAILED DESCRIPTION

(9) The parts illustrated in figures are individually assigned a reference numeral and the corresponding terms of these numbers are listed below. 1. Rotary wing air vehicle 2. Body 3. Rotor 4. Blade 401. Outer blade 5. Mechanism 501. Slide 502. Rope 503. Winding bearing 504. Shaft 505. Elastic element 6. Transition apparatus 7. Protrusion

(10) The rotary wing air vehicle (1) comprises a body (2), a rotor (3) rotating about its axis and positioned so as to extend outward from within the body (2), at least one blade (4) extending outward from the rotor (2) and providing lift and/or thrust to the body (2) by its movement, at least one outer blade (401) positioned in the blade (4) and providing lift and/or thrust to the body (2), at least one mechanism (5) enabling the outer blade (401) to switch from a retracted first position in which the it is almost entirely located in the blade (4) to a second position in which it extends outward from the blade (4) by moving linearly under the influence of the centrifugal force generated during the movement of the rotor (2). (FIG. 1, FIG. 2, FIG. 3)

(11) The rotary wing air vehicle (1) of the invention comprises a transition apparatus (6) on the blade (4), at least a part of which circumferentially grips the blade (4) and at least a part of which is form-fitting with the circumference of the outer blade (401), thereby preventing the outer blade (401) from completely coming out of the blade (4). (FIG. 2, FIG. 3)

(12) The blade (4) of the rotary wing air vehicle (1) can be rotated by means of the rotor (3) extending outward from within the body (2). Therefore, the blade (4) provides sufficient lift and thrust to the rotary wing air vehicle (1) and performs the flight action. The blade (4) comprises an outer blade (401), which moves to a second position ready for flight so that the blade comes out of a retracted first position by the centrifugal force generated by the rotation of the blade (4) around the rotor (3). By means of a mechanism (5), the outer blade (401) may telescopically go in and out of the blade (4) according to the centrifugal force. Thus, the outer blade (401) does not occupy space when the rotary wing air vehicle (1) is not in operation. An effective and efficient system for adjusting the length of the outer blade (401) is provided. (FIG. 2, FIG. 3)

(13) The telescopic moving capability between the blade (4) and the outer blade (401) can be achieved by the dimensional difference between the outer blade (401) and the blade (4). A transition apparatus (6) is provided on the blade (4), effectively reducing the resulting aerodynamic disadvantages such as air drag and at the same time limiting the maximum distance that the outer blade (401) will come out of the blade (4). The transition apparatus (6) provides a safe telescopic system while effectively ensuring the flow performance of the telescopic blade (4). The transition apparatus (6) acts as a complement to the aerodynamic surface between the blade (4) and the outer blade (401), thus providing an effective, safe and efficient use for the telescopic system. (FIG. 2, FIG. 3)

(14) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a transition apparatus (6) having one end with a profile cross-section that is almost the same as that of the blade (4) and another end with a profile cross-section that is almost the same as that of the outer blade (401). Thus, an efficient aerodynamic surface profile is provided for the rotary wing air vehicle (1). (FIG. 2, FIG. 3)

(15) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a transition apparatus (6) having at least a partially interference fit connection structure (F) between itself (6) and the outer blade (401) when the outer blade (401) is in the second position, thereby providing an effective structural performance.

(16) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a transition apparatus (6) that is connected to the blade (4) by means of an interference fit coupling, thereby contributing to the structural performance.

(17) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a transition apparatus (6) having at least one dampening surface (D) therein, thereby dampening the vibration resulting from the movement of the outer blade (401) when switching from the first position to the second position. (FIG. 3, FIG. 4)

(18) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a transition apparatus (6) having a protrusion (7) therein, preventing the outer blade (401) in the second position from coming out of the blade (4). (FIG. 4)

(19) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a transition apparatus (6) having a double curvature form, thereby contributing to the aerodynamic surface performance.

(20) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a transition apparatus (6) having a more rigid material that is different from the material of the blade (4) and outer blade (401), thereby allowing the vibration to be reduced.

(21) In an embodiment of the invention, the rotary wing air vehicle (1) comprises at least one slide (501) allowing the outer blade (401) to move by sliding from the first position to the second position and/or from the second position to the first position, at least one rope (502) connected to the outer blade (401), at least one winding bearing (503) on which the rope (502) is wound, a shaft (504) allowing the winding bearing (503) to rotate around its axis, and a mechanism (5) with at least one elastic element (505) to which the shaft (504) is connected, providing resistance against the centrifugal force generated by the movement of the blade (4) and the outer blade (401). (FIG. 5) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a mechanism (5) having a helical spring-type elastic element (505).

(22) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a transition apparatus (6) with a length of th of the length of the outer blade (401) and a blade (4) having a length that is 1.80 to 1.85 times the length of the outer blade (401). This ensures a safe and efficient fit between the blade (4), outer blade (401) and transition apparatus (6).

(23) In an embodiment of the invention, the rotary wing air vehicle (1) comprises a polymeric transition apparatus (6) manufactured from a resin-impregnated fabric.