Foldable rotor system for high subsonic velocity tilt rotor aircraft

Abstract

The embodiment of the invention discloses a foldable rotor system for a high subsonic velocity tilt rotor aircraft, relates to the technical field of high-speed vertical take-off and landing aircrafts, and can reduce air resistance while realizing the functions of rotation, pitch change and folding. The foldable rotor mainly works in an unfolding mode and a folding mode, has rotational degrees of freedom in three directions, and can achieve the functions of rotation, pitch change and folding. When the high subsonic velocity tilt-rotor aircraft vertically takes off, lands and flies in a rotor wing mode, the rotor wings of the high subsonic velocity tilt-rotor aircraft are unfolded and are similar to a rotor wing system of a tilt-rotor aircraft; when the high subsonic velocity tilt rotor aircraft flies in a jet mode, the engine is switched into a turbofan mode, meanwhile, the rotors are folded backwards to reduce resistance, and high-speed cruise is achieved. Therefore, air resistance can be reduced while the functions of rotating, pitch changing and folding are achieved.

Description

Technical Field

[0001] The invention relates to the technical field of high-speed vertical take-off and landing aircraft, and in particular to a foldable rotor system for a high-subsonic tilt-rotor aircraft. Background Art

[0002] The common foldable rotor and its mechanism can realize rotation, variable pitch control and blade folding by relying on the internal transmission mechanism, and is suitable for the rotor system of high subsonic tilt-rotor aircraft. High subsonic tilt-rotor aircraft has two flight modes: rotor mode and jet mode. When the rotor is deployed, similar to a conventional propeller, the rotor provides the aircraft with forward flight thrust by rotating, and the blades can be controlled by variable pitch at the same time; when the engine is switched to turbofan mode, the rotor is adjusted to the feathering state, relying on resistance to stop and fold backward to achieve high-speed cruising.

[0003] However, how to further optimize the foldable rotor used in high subsonic tilt-rotor aircraft so that it can achieve the functions of rotation, pitch change and folding while reducing air resistance has become a topic that needs to be studied. Summary of the invention

[0004] An embodiment of the present invention provides a foldable rotor system for a high subsonic tiltrotor aircraft, which can realize the functions of rotation, pitch change and folding while also reducing air resistance.

[0005] To achieve the above object, the embodiments of the present invention adopt the following technical solutions:

[0006] A foldable rotor system for a high subsonic tiltrotor aircraft, comprising: a nacelle fairing (1), a nacelle fixed part (2), a blade (3), a rotor fairing rotating part (4) and a rotor fairing fixed part (5); the opening end of the nacelle fairing (1) is installed close to the opening end of the nacelle fixed part (2), and the nacelle fixed part (2) is fixedly connected to the wing of the high subsonic tiltrotor aircraft; the internal cavity of the nacelle fairing (1) and the internal cavity of the nacelle fixed part (2) together form a chamber for enclosing an internal system, and the internal system comprises: a main shaft (6), a turntable (7 ), a rotor bracket (8), a crank rod I (9), a crank rod II (10), a pitch rocker arm (11) and a universal joint (12); the central axis of the nacelle fairing (1) coincides with the main shaft (6), and the inner wall of the nacelle fairing (1) is fixed to the front end of the main shaft (6) so that the main shaft (6) can drive the nacelle fairing (1) to rotate around the central axis; the blades (3) are respectively connected to the rotor bracket (8) and the crank rod I (9); the inner side of the rotor fairing rotating part (4) is respectively hinged to the blades (3) and the rotor bracket (8); the rotor fairing fixed part (5) is fixedly installed on the outer surface of the nacelle fairing (1).

[0007] The main shaft (6) is connected to the rotor bracket (8), the turntable (7) is sleeved on the main shaft (6), and the turntable (7) is connected to the pitch rocker arm (11) through a ball joint; one end of the rotor bracket (8) is connected to the blade (3), and the other end is connected to the main shaft (6).

[0008] The two ends of the bent rod I (9) are respectively hinged to the blade (3) and the bent rod II (10); one end of the bent rod II (10) is hinged to the bent rod I (9), and the other end is hinged to the rotor bracket (8) at the turning point; the end of the bent rod II (10) is connected to one end of the pitch rocker arm (11) through a universal joint (12).

[0009] The other end of the variable pitch rocker arm (11) is connected to the rotating disk (7) through a ball joint; and the universal joint (12) is respectively connected to the crankshaft II (10) and the variable pitch rocker arm (11).

[0010] The blade (3), the rotating part of the rotor fairing (4), the fixed part of the rotor fairing (5), the rotor bracket (8), the crankshaft I (9), the crankshaft II (10), the variable pitch rocker arm (11) and the universal joint (12) form a set of component assemblies, and a total of three sets of component assemblies are respectively arranged at 0°, 120° and 240° around the central axis of the main shaft (6).

[0011] The foldable rotor system for a high subsonic tiltrotor aircraft provided in an embodiment of the present invention comprises: a nacelle fairing (1), a nacelle fixed part (2), a blade (3), a rotor fairing rotating part (4), a rotor fairing fixed part (5), a main shaft (6), a turntable (7), a rotor bracket (8), a crankshaft 1 (9), a crankshaft 2 (10), a variable pitch rocker arm (11), and a universal joint (12). The foldable rotor is mainly unfolded ( Figure 1 ) and fold( Figure 2 ) two modes, with three degrees of rotational freedom, can realize the functions of rotation, pitch change and folding. When the high subsonic tilt-rotor aircraft takes off and lands vertically and flies in the rotor mode, its rotor is like Figure 1 Deployed, similar to the rotor system of a tiltrotor aircraft; when a high subsonic tiltrotor aircraft flies in jet mode, the engine switches to turbofan mode and the rotor folds back to reduce drag, such as Figure 2 , achieving high-speed cruising. Thus, while realizing the functions of rotation, pitch change and folding, it can also reduce air resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0013] Figure 1 A schematic diagram of the overall structure provided by an embodiment of the present invention;

[0014] Figure 2 A schematic diagram of the folding of the overall structure provided by an embodiment of the present invention;

[0015] Figure 3 to Figure 8 A partial schematic diagram of a specific structure provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0016] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention will be described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be interpreted as limiting the present invention. It can be understood by those skilled in the art that, unless specifically stated, the singular forms "one", "one", "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present invention refers to the presence of the features, integers, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or their groups. It should be understood that when we say that an element is "connected" or "coupled" to another element, it can be directly connected or coupled to other elements, or there may also be intermediate elements. In addition, the "connection" or "coupling" used here may include wireless connection or coupling. The term "and / or" used herein includes any unit and all combinations of one or more associated listed items. It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as generally understood by those of ordinary skill in the art to which the present invention belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have meanings consistent with the meanings in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as herein.

[0017] An embodiment of the present invention provides a foldable rotor system for a high subsonic tiltrotor aircraft, characterized in that it comprises: a nacelle fairing (1), a nacelle fixed part (2), a blade (3), a rotor fairing rotating part (4) and a rotor fairing fixed part (5); wherein the nacelle fairing (1) can rotate around its central axis to wrap the internal system and structure to reduce aerodynamic resistance; the nacelle fixed part (2) is also used to wrap the internal system and structure, the nacelle fixed part (2) is connected to the wing of the high subsonic tiltrotor aircraft, and this part does not rotate around its axis;

[0018] The opening end of the nacelle fairing (1) is installed close to the opening end of the nacelle fixed part (2), and the nacelle fixed part (2) is fixedly connected to the wing of the high subsonic tilt-rotor aircraft;

[0019] The internal cavity of the nacelle fairing (1) and the internal cavity of the nacelle fixed part (2) together form a chamber for enclosing an internal system, wherein the internal system includes: a main shaft (6), a rotating disk (7), a rotor bracket (8), a crank arm I (9), a crank arm II (10), a pitch rocker arm (11) and a universal joint (12);

[0020] The central axis of the nacelle fairing (1) coincides with the main shaft (6), and the inner wall of the nacelle fairing (1) is fixed to the front end of the main shaft (6) so that the main shaft (6) can drive the nacelle fairing (1) to rotate around the central axis;

[0021] The blade (3) is connected to the rotor bracket (8) and the bent rod I (9) respectively; the blade (3) is connected to the rotor bracket (8) and the bent rod I (9) at the same time, and has a large negative twist angle in order to adapt to a high subsonic tilt-rotor aircraft, and a part is cut off at the root to avoid interference with the bent rod I (9) when folding;

[0022] The inner side of the rotating part (4) of the rotor fairing is respectively hinged to the blade (3) and the rotor bracket (8), moves with the blade during pitch control, and wraps the internal mechanism when the blade (3) is folded to reduce aerodynamic resistance;

[0023] The rotor fairing fixed part (5) is fixedly mounted on the outer surface of the nacelle fairing (1), rotates along with the nacelle fairing (1), and plays a role in wrapping the internal structure and reducing aerodynamic resistance after the blades (3) are folded.

[0024] The main shaft (6) is connected to the rotor bracket (8), thereby driving the rotor to rotate. The turntable (7) is sleeved on the main shaft (6). The turntable (7) is connected to the pitch rocker arm (11) through a ball joint. When the rotor is subjected to pitch control and folding, it can be moved and rotated along the central axis of the main shaft (6) for corresponding adjustment. One end of the rotor bracket (8) is connected to the blade (3), and the other end is connected to the main shaft (6). The rotor bracket (8) can rotate around the main shaft (6), thereby driving the blade (3) to achieve pitch control. At the same time, the middle part is hinged to the crankshaft II (10), such as Figure 4 and Figure 5 As shown;

[0025] The two ends of the crank rod I (9) are respectively hinged to the blade (3) and the crank rod II (10). The function of the crank rod I (9) is to directly drive the blade (3) to fold and provide a lateral torque to the blade (3) during pitch control. One end of the crank rod II (10) is hinged to the crank rod I (9), and the other end is hinged to the rotor bracket (8) at the turning point. The end of the crank rod II (10) is connected to one end of the pitch rocker arm (11) through a universal joint (12). Figure 4 shown.

[0026] The other end of the pitch rocker arm (11) is connected to the turntable (7) through a ball joint; the universal joint (12) is respectively connected to the crankshaft II (10) and the pitch rocker arm (11), and serves as an important connecting part to provide rotational freedom during pitch control and folding. The blade (3), the rotating part of the rotor fairing (4), the fixed part of the rotor fairing (5), the rotor bracket (8), the crankshaft I (9), the crankshaft II (10), the pitch rocker arm (11) and the universal joint (12) constitute a set of components. A total of three sets of components are arranged at 0°, 120° and 240° around the central axis of the main shaft (6), respectively. Figure 3 shown.

[0027] This embodiment is applicable to the rotor system of a high-subsonic tilt-rotor aircraft. The high-subsonic tilt-rotor aircraft is a new type of aircraft for future sea operations, with two flight modes: rotor mode and jet mode. When the high-subsonic tilt-rotor aircraft takes off and lands vertically and flies in the rotor mode, its rotor is as follows: Figure 1 Deployed, similar to the rotor system of a tiltrotor aircraft; when a high subsonic tiltrotor aircraft flies in jet mode, the engine switches to turbofan mode and the rotor folds back to reduce drag, such as Figure 2 , achieving high-speed cruising.

[0028] In practical applications, the working states of the foldable rotor system include: rotor deployment and rotation state, rotor pitch control state and rotor folding state. Figure 1 ) and fold( Figure 2) two modes of operation, with three degrees of rotational freedom, and can realize the functions of rotation, pitch change and folding. The main working states of the present invention and the switching process between them are as follows:

[0029] 1. Rotor deployment and rotation:

[0030] In this state, the blades (3) are fully extended. Figure 1 and Figure 3 As shown. The nacelle fairing (1), the blade (3), the rotating part of the rotor fairing (4), the fixed part of the rotor fairing (5), the main shaft (6), the turntable (7), the rotor bracket (8), the crankshaft I (9), the crankshaft II (10), the variable pitch rocker arm (11), and the universal joint (12) can rotate together around the central axis of the main shaft (6). At this time, the blade (3), the rotor bracket (8), the crankshaft I (9), the crankshaft II (10), the variable pitch rocker arm (11), and the universal joint (12) do not move relative to each other.

[0031] 2. Rotor pitch control:

[0032] When the rotor is deployed, the rotor bracket (8) rotates around its rotation axis, and the turntable (7) rotates and translates relatively along the central axis of the main shaft (6), thereby driving the pitch rocker arm (11) to move together through the ball joint. Since the pitch rocker arm (11) is connected to the crankshaft II (10) through the universal joint (12), the hinge between the rotor bracket (8) and the crankshaft II (10) is locked at this time, so that the crankshaft II (10) can only rotate relatively around the rotation axis direction of the rotor bracket (8), thereby driving the crankshaft I (9), the blades (3) and the rotor fairing rotating part (4) to rotate around the rotation axis of the rotor bracket (8) together, and the rotation angle can be 0 to 90 degrees, while the blades (3), the rotor fairing rotating part (4), the rotor bracket (8), the crankshaft I (9) and the crankshaft II (10) do not move relative to each other. In this way, the rotor pitch control can be realized by mutual adjustment of the various components, such as Figure 6 and Figure 7 It should be noted that the rotor pitch control can be performed while the rotor is rotating, and the two movements do not interfere with each other.

[0033] 3. Rotor folded state:

[0034] On the basis of the rotor deployment state, or when the rotor is adjusted to the feathering state through the pitch control, the rotor stops rotating, the rotor bracket (8) is locked, the turntable (7) does not rotate relative to the main shaft, but translates along its central axis, thereby promoting the movement of the pitch rocker arm (11), driving the universal joint (12) to rotate in a direction perpendicular to the plane of the blade (3), further driving the crankshaft II (10) to rotate around the hinge between it and the rotor bracket (8), and finally driving the crankshaft I (9) to drive the blade (3) to fold backward around the hinge between the blade (3) and the rotor bracket (8), and the folding angle is 0 to 90 degrees, as shown in Figures (2) and (8).

[0035] Each embodiment in this specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the device embodiment, since it is basically similar to the method embodiment, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiment. The above is only a specific implementation method of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or replacements that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A foldable rotor system for a high subsonic tilt-rotor aircraft, characterized in that: include: A nacelle fairing (1), a nacelle fixed portion (2), a blade (3), a rotor fairing rotating portion (4) and a rotor fairing fixed portion (5); The opening end of the nacelle fairing (1) is installed close to the opening end of the nacelle fixed part (2), and the nacelle fixed part (2) is fixedly connected to the wing of the high subsonic tilt-rotor aircraft; The internal cavity of the nacelle fairing (1) and the internal cavity of the nacelle fixed part (2) together form a chamber for enclosing an internal system, wherein the internal system includes: a main shaft (6), a rotating disk (7), a rotor bracket (8), a crank arm I (9), a crank arm II (10), a pitch rocker arm (11) and a universal joint (12); The central axis of the nacelle fairing (1) coincides with the main shaft (6), and the inner wall of the nacelle fairing (1) is fixed to the front end of the main shaft (6) so that the main shaft (6) can drive the nacelle fairing (1) to rotate around the central axis; The blades (3) are connected to the rotor bracket (8) and the crankshaft I (9) respectively; The inner side of the rotating part (4) of the rotor fairing is hinged to the blade (3) and the rotor bracket (8) respectively; The rotor fairing fixing part (5) is fixedly mounted on the outer surface of the nacelle fairing (1).

2. The foldable rotor system for a high subsonic tilt-rotor aircraft according to claim 1, characterized in that: The main shaft (6) is connected to the rotor bracket (8), the turntable (7) is sleeved on the main shaft (6), and the turntable (7) is connected to the pitch rocker arm (11) through a ball joint; One end of the rotor bracket (8) is connected to the blade (3), and the other end is connected to the main shaft (6).

3. The foldable rotor system for a high subsonic tilt-rotor aircraft according to claim 2, characterized in that: The two ends of the curved rod I (9) are respectively hinged to the blade (3) and the curved rod II (10); One end of the bent rod II (10) is hinged to the bent rod I (9), and the other end is hinged to the rotor bracket (8) at the turning point. The end of the bent rod II (10) is connected to one end of the pitch rocker arm (11) through a universal joint (12).

4. The foldable rotor system for a high subsonic tilt-rotor aircraft according to claim 3, characterized in that: The other end of the variable pitch rocker arm (11) is connected to the rotating disk (7) through a ball joint; The universal joint (12) is respectively connected to the crankshaft II (10) and the variable pitch rocker arm (11).

5. The foldable rotor system for a high subsonic tilt-rotor aircraft according to claim 4, characterized in that: The blade (3), the rotating part of the rotor fairing (4), the fixed part of the rotor fairing (5), the rotor bracket (8), the crankshaft I (9), the crankshaft II (10), the variable pitch rocker arm (11) and the universal joint (12) form a set of component assemblies, and a total of three sets of component assemblies are respectively arranged at 0°, 120° and 240° around the central axis of the main shaft (6).

6. The foldable rotor system for a high subsonic tiltrotor aircraft according to any one of claims 1 to 5, characterized in that: The working states of the foldable rotor system include: rotor deployment and rotation state, rotor pitch control state and rotor folding state.

7. The foldable rotor system for a high subsonic tiltrotor aircraft according to claim 6, characterized in that: In the rotor deployment and rotation state, the blades (3) are fully deployed, and the nacelle fairing (1), the blades (3), the rotor fairing rotating part (4), the rotor fairing fixed part (5), the main shaft (6), the turntable (7), the rotor bracket (8), the crankshaft I (9), the crankshaft II (10), the pitch rocker arm (11) and the universal joint (12) rotate together around the central axis of the main shaft (6); However, there is no relative movement between the blade (3), the rotor bracket (8), the crankshaft I (9), the crankshaft II (10), the variable pitch rocker arm (11) and the universal joint (12).

8. The foldable rotor system for a high subsonic tilt-rotor aircraft according to claim 6, characterized in that: During the rotor pitch control, the rotor bracket (8) rotates around the main shaft (6), and the turntable (7) rotates and translates relatively along the central axis of the main shaft (6), thereby driving the pitch rocker arm (11) to move together through the ball joint; since the pitch rocker arm (11) is connected to the crankshaft II (10) through the universal joint (12), the hinge between the rotor bracket (8) and the crankshaft II (10) is locked at this time, so that the crankshaft II (10) only rotates relatively around the rotation axis direction of the rotor bracket (8), thereby driving the crankshaft I (9), the blades (3) and the rotor fairing rotating part (4) to rotate together around the rotation axis of the rotor bracket (8), wherein the rotation angle is 0 to 90 degrees, and the blades (3), the rotor fairing rotating part (4), the rotor bracket (8), the crankshaft I (9) and the crankshaft II (10) do not move relative to each other.

9. The foldable rotor system for a high subsonic tilt-rotor aircraft according to claim 6, characterized in that: In the rotor folding state, the rotor stops rotating and the rotor bracket (8) is locked; The turntable (7) does not rotate relative to the main shaft, but translates along the central axis of the turntable (7), thereby driving the movement of the variable pitch rocker arm (11); The universal joint (12) is driven to rotate in a direction perpendicular to the plane of the blade (3), thereby driving the crank rod II (10) to rotate around the hinge between the crank rod II (10) and the rotor bracket (8), and finally driving the crank rod I (9) to drive the blade (3) to fold backward around the hinge between the blade (3) and the rotor bracket (8), with the folding angle being 0 to 90 degrees.

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