Variable total pitch propeller hub of multi-tilt rotorcraft

Abstract

The invention discloses a variable total pitch propeller hub of a multi-tilt rotorcraft, and relates to the technical field of propeller hubs, the variable total pitch propeller hub comprises a shell, a total pitch control rod, a central part and a plurality of rotor mounting assemblies, the central part is located in the shell, one end of the total pitch control rod is connected with the central part, the other end of the total pitch control rod is used for being connected with a steering engine, and the rotor mounting assemblies are located in the shell. The central part is provided with a first variable-pitch control matching part, the rotor wing mounting assembly is rotationally connected with the shell, the rotor wing mounting assembly is provided with a second variable-pitch control matching part matched with the first variable-pitch control matching part, and the total-pitch control rod drives the central part to linearly move. And the rotor wing mounting assembly can be driven to rotate. According to the variable total pitch propeller hub of the multi-tilt rotorcraft, driving can be achieved only through one steering engine, the structure is simple, and the weight efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of rotor hub technology, and in particular to a variable collective pitch rotor hub for a multi-tilt rotor. Background Technology

[0002] Conventional tiltrotor aircraft have a rotor system similar to that of helicopters, capable of controlling both collective pitch and cyclic pitch. For this type of rotor hub, each rotor requires three servos to achieve full control functionality.

[0003] For multi-tilt rotorcraft, such as quad tiltrotors, each rotor system requires three servos in a traditional hub configuration, while a quad tiltrotor configuration requires twelve servos, plus surface servos. This makes the system extremely complex and inefficient in terms of weight.

[0004] For this multi-tilt rotor configuration, a smaller rotor pitch is required in hover mode, while a larger pitch angle is needed in forward flight mode (large axial flow). However, cyclic pitch control is not essential for multi-rotor aircraft, as the flight control system can adjust fuselage attitude through other means. Therefore, collective pitch control is necessary for multi-tilt rotor aircraft. Summary of the Invention

[0005] The purpose of this invention is to provide a variable collective pitch rotor hub for a multi-tilt rotorcraft that can be driven by only one servo motor, with a simple structure and improved weight efficiency.

[0006] To achieve the above objectives, the present invention provides the following solution: This invention provides a variable collective pitch rotor hub for a multi-tilt rotorcraft, comprising: a housing, a collective pitch control stick, a central component, and several rotor mounting assemblies. The central component is located within the housing. One end of the collective pitch control stick is connected to the central component, and the other end is used to connect to a servo motor. The central component is provided with a first variable pitch control mating part. The rotor mounting assemblies are rotatably connected to the housing, and each rotor mounting assembly is provided with a second variable pitch control mating part that mates with the first variable pitch control mating part. The collective pitch control stick drives the central component to move linearly and can drive the rotor mounting assemblies to rotate.

[0007] In some specific solutions, the first pitch control mating part is a groove, and the second pitch control mating part is a protrusion. The protrusion is located in the groove and is slidably connected to the groove.

[0008] In some specific designs, a limiting part is sleeved on the outer side of the second pitch control mating part, the limiting part is rotatably connected to the second pitch control mating part, and the limiting part is slidably connected to the first pitch control mating part.

[0009] In some specific embodiments, the extension of the rotation axis of the rotor mounting assembly can intersect the axis of the collective pitch control stick.

[0010] In some specific designs, a limiting structure is also included, which is located in the housing and is slidably connected to the central component along the axial direction of the collective pitch control lever.

[0011] In some specific embodiments, the rotor mounting assembly includes a blade root shaft, a blade, and a bushing. The blade is located inside the blade root shaft, and the blade and the blade form a mounting space at the rotor root. The bushing is located outside the blade root shaft and can limit the end of the blade.

[0012] In some specific designs, the central component is slidably connected to the housing.

[0013] In some specific designs, a first bearing is provided between the collective pitch control lever and the central component.

[0014] In some specific designs, a second bearing is provided between the rotor mounting assembly and the housing.

[0015] In some specific embodiments, the housing includes an upper shell and a lower shell, which are detachably connected.

[0016] The present invention achieves the following technical effects compared to the prior art: This invention uses a collective pitch control stick to move the central component, which in turn drives the synchronous movement of each rotor assembly, achieving synchronized adjustment of the aerodynamic angle of each blade. This meets the control requirements of tiltrotor aircraft for different collective pitch angles during hovering and forward flight phases. Addressing the variable collective pitch requirements of tiltrotor aircraft, this invention requires only one servo motor for control, reducing the operational complexity of the flight control system, decreasing the number of components, and lowering the overall weight of the rotor system, thus solving the problem of low weight efficiency in traditional solutions. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the variable collective pitch rotor hub of a multi-tilt rotorcraft in some embodiments of the present invention; Figure 2 This is a schematic diagram of the variable collective pitch rotor hub of a multi-tilt rotorcraft in some embodiments of the present invention (with the upper shell removed). Figure 3 This is a top view of the variable collective pitch rotor hub of a multi-tilt rotorcraft according to some embodiments of the present invention (with the upper shell removed). Figure 4 This is a schematic diagram of a rotor mounting assembly in some embodiments of the present invention; Figure 5 This is a side view of a rotor mounting assembly according to some embodiments of the present invention; Figure 6 for Figure 5 AA section view; Figure 7 This is a cross-sectional view of the limiting portion in some embodiments of the present invention; Figure 8 This is a schematic diagram of the collective pitch control lever, central component, and limiting structure in some embodiments of the present invention; Figure 9 This is a top view of the collective pitch control lever, central component, and limiting structure in some embodiments of the present invention; Figure 10 for Figure 9 BB cross-sectional view; In the diagram: 100 - Variable collective pitch rotor hub of a multi-tilt rotorcraft; 1 - Shell; 2 - Collective pitch control stick; 3 - Central component; 4 - Rotor mounting assembly; 5 - First variable pitch control mating part; 6 - Second variable pitch control mating part; 7 - Limiting part; 8 - Limiting structure; 9 - Blade root shaft; 10 - Sheet; 11 - Bushing; 12 - First bearing; 13 - Second bearing. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] The purpose of this invention is to provide a variable collective pitch rotor hub for a multi-tilt rotorcraft that can be driven by only one servo motor, with a simple structure and improved weight efficiency.

[0021] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0022] like Figures 1 to 10As shown, this embodiment provides a variable collective pitch rotor hub 100 for a multi-tilt rotorcraft, including: a housing 1, a collective pitch control stick 2, a central component 3, and several rotor mounting assemblies 4. The central component 3 is located within the housing 1. One end of the collective pitch control stick 2 is connected to the central component 3, and the other end is used to connect to a servo motor. The central component 3 is provided with a first variable pitch control mating part 5. The rotor mounting assemblies 4 are rotatably connected to the housing 1 and are provided with a second variable pitch control mating part 6 that mates with the first variable pitch control mating part 5. The collective pitch control stick 2 drives the central component 3 to move linearly, and can simultaneously drive each rotor mounting assembly 4 to rotate. After the variable collective pitch rotor hub 100 of this embodiment is installed, only the collective pitch control stick 2 is exposed. Connecting a servo motor allows for collective pitch control. This embodiment can drive the collective pitch control stick 2 through a single servo motor, thereby driving the rotor mounting assemblies 4 to rotate, achieving a change in the aerodynamic angle of attack of the rotor blades, and improving the weight efficiency of the rotor system.

[0023] In some specific embodiments, the first pitch control mating part 5 is a groove, and the extension direction of each groove is located on the same horizontal plane. The second pitch control mating part 6 is a protrusion located in the groove and slidably connected to the groove. The second pitch control mating part 6 is disposed at the end of the rotor mounting assembly 4, forming a control point and saving space.

[0024] In some specific embodiments, a limiting part 7 is sleeved on the outer side of the second pitch control mating part 6. The limiting part 7 is made of Teflon and is rotatably connected to the second pitch control mating part 6, and slidably connected to the first pitch control mating part 5. The limiting part 7 has a hexahedral shape, while the first pitch control mating part 5 has a rectangular cross-section. The shapes of the limiting part 7 and the first pitch control mating part 5 are matched, and the interior of the limiting part 7 is cylindrical, enabling relative rotation with the second pitch control mating part 6. When the collective pitch control lever 2 drives the central component 3 to move linearly along the axial direction of the collective pitch control lever 2, the second pitch control mating part 6 slides along the first pitch control mating part 5, realizing the rotation of the rotor mounting assembly 4 around its axis and changing the aerodynamic angle of attack of the blades.

[0025] In some specific embodiments, the extension line of the rotation axis of the rotor mounting assembly 4 intersects the axis of the collective pitch control stick 2, that is, the extension line of the rotation axis of the rotor mounting assembly 4 passes through the center of rotation. Therefore, the rotor mounting assembly 4 is not offset, and the centrifugal force generated by high-speed rotation only exerts a pulling force in the direction of the blade root. The operating conditions of the rotor hub and the second bearing 13 are good and stable. If there is an offset, the huge centrifugal force generated by high-speed rotation will cause a huge bending moment on the blade root.

[0026] In some embodiments, the central component 3 is slidably connected to the housing 1. This embodiment also includes a limiting structure 8 located within the housing 1. The limiting structure 8 is preferably a limiting rod, the axis of which is parallel to the axis of the collective pitch control lever 2. Several limiting rods are present, and the limiting structure 8 and the central component 3 are slidably connected along the axial direction of the collective pitch control lever 2. The limiting structure 8 ensures that during pitch control, the central component 3 can only move along the axial direction of the collective pitch control lever 2, thereby ensuring that the rotor mounting assembly 4 can only rotate around its axis, thus stabilizing the system.

[0027] In some specific embodiments, the rotor mounting assembly 4 includes a blade root shaft 9, a bearing plate 10, and a bushing 11. A second pitch control mating part 6 is fixedly disposed at one end of the blade root shaft 9 facing the central member 3. The bearing plate 10 is located inside the blade root shaft 9, forming a mounting space at the rotor root. The bushing 11 is located outside the blade root shaft 9 and can limit the end of the bearing plate 10. A protrusion is provided at the rotor root, located within the mounting space formed by the blade root shaft 9 and the bearing plate 10. The bearing plate 10 can abut against the protrusion, restricting its radial movement. Then, through a threaded connection between the bushing 11 and the outer ring of the blade root shaft 9, the bushing 11 can axially tighten the bearing plate 10, thereby completing the rotor mounting.

[0028] In some specific embodiments, a first bearing 12 is provided between the collective pitch control stick 2 and the central component 3. There are two sets of first bearings 12, and the collective pitch control stick 2 and the central component 3 are rotatably connected. In this embodiment, the central component 3 rotates together with the rotor system, and the first bearing 12 ensures that the collective pitch control stick 2 can only be moved and operated vertically, and does not rotate with the rotor system.

[0029] In some specific embodiments, a second bearing 13 is provided between the rotor mounting assembly 4 and the housing 1, and there are two sets of the second bearing 13.

[0030] In some embodiments, the housing 1 includes an upper housing and a lower housing, which are detachably connected by bolts. The housing 1 in this embodiment also has mounting bolt holes, allowing the entire device to be mounted on a power motor.

[0031] In this embodiment, the collective pitch control stick 2 moves up and down, causing the central component 3 to move up and down. The second pitch control mating part 6 slides along the first pitch control mating part 5, causing the rotor mounting assembly 4 to rotate around its axis, thus changing the aerodynamic angle of the blades. The limiting structure 8 in this embodiment restricts the central component 3's degrees of freedom except for vertical movement (i.e., along the axis of the collective pitch control stick 2). This embodiment reduces the control degrees of freedom of the flight control system, resulting in better overall robustness. The central component 3 keeps all control points on the same plane, ensuring that the pitch angle of each blade is consistent, and the collective pitch control stick 2 only changes the collective pitch.

[0032] This embodiment addresses the variable collective pitch requirements of multi-tilt rotorcraft, requiring only one servo motor for operation. The rotor mounting assembly 4 in this embodiment is highly versatile, with no special requirements for the rotor blades; installation is completed simply by pressing it with tiles 10. This embodiment integrates and seals the collective pitch control stick 2, the central component 3, and several rotor mounting assemblies 4 together through a housing 1, minimizing environmental impact on the structure.

[0033] In the description of this invention, it should be understood that the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0034] In the description of this invention, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0035] If this invention discloses or relates to components or structural parts that are fixedly connected to each other, then, unless otherwise stated, a fixed connection can be understood as: a detachable fixed connection (e.g., using bolts or screws) or a non-detachable fixed connection (e.g., riveting, welding). Of course, a fixed connection can also be replaced by an integral structure (e.g., manufactured in one piece using a casting process) (except where it is obviously impossible to use an integral molding process).

[0036] In addition, unless otherwise stated, the terms used in any of the technical solutions disclosed in this invention to indicate positional relationships or shapes include states or shapes that are similar to, close to, or approximate with those states or shapes.

[0037] Any component provided by this invention can be assembled from multiple individual components or can be a single component manufactured by a one-piece molding process.

[0038] It should be noted that the structures, proportions, sizes, etc., depicted in the accompanying drawings of this specification are only used to complement the content disclosed in the specification, so as to enable those skilled in the art to understand and read them, and are not intended to limit the conditions under which the present invention can be implemented. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size, without affecting the effects and objectives that the present invention can produce, should still fall within the scope of the technical content disclosed in the present invention.

[0039] It should also be noted that in the embodiments of this application, the same reference numerals are used to denote the same component or the same part.

[0040] Any adaptive changes made according to actual needs are within the scope of protection of this invention.

[0041] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A variable collective pitch rotor hub for a multi-tilt rotorcraft, characterized in that: include: The system comprises a housing, a collective pitch control stick, a central component, and several rotor mounting assemblies. The central component is located within the housing. One end of the collective pitch control stick is connected to the central component, and the other end is used to connect to a servo motor. The central component is provided with a first variable pitch control engagement part. The rotor mounting assemblies are rotatably connected to the housing and are provided with a second variable pitch control engagement part that engages with the first variable pitch control engagement part. The collective pitch control stick drives the central component to move linearly and can drive the rotor mounting assemblies to rotate.

2. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 1, characterized in that: The first pitch control engagement part is a groove, and the second pitch control engagement part is a protrusion. The protrusion is located in the groove and is slidably connected to the groove.

3. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 2, characterized in that: A limiting part is sleeved on the outer side of the second pitch control mating part. The limiting part is rotatably connected to the second pitch control mating part and slidably connected to the first pitch control mating part.

4. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 1, characterized in that: The extension of the rotation axis of the rotor mounting assembly can intersect the axis of the collective pitch control stick.

5. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 1, characterized in that: It also includes a limiting structure located in the housing, the limiting structure being slidably connected to the central component along the axial direction of the collective pitch control lever.

6. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 1, characterized in that: The rotor mounting assembly includes a blade root shaft, a tile, and a bushing. The tile is located inside the blade root shaft, and the blade root shaft and the tile form a mounting space at the rotor root. The bushing is located outside the blade root shaft and can limit the end of the tile.

7. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 1, characterized in that: The central component is slidably connected to the housing.

8. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 1, characterized in that: A first bearing is provided between the collective pitch control lever and the central component.

9. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 1, characterized in that: A second bearing is provided between the rotor mounting assembly and the housing.

10. The variable collective pitch rotor hub of the multi-tilt rotorcraft according to claim 1, characterized in that: The housing includes an upper shell and a lower shell, which are detachably connected.

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