A fixed-wing aircraft embedded rudder transmission structure

Abstract

The utility model relates to the field of aviation technology, concretely relates to a fixed wing aircraft embedded rudder engine transmission structure, including fuselage, fixedly connected on the main wing of fuselage, the aileron of rotary connection in one side of main wing and rudder engine, main wing and aileron are integrally connected through composite material flexible connecting structure, and rudder engine is embedded in the fuselage, and the output gear of rudder engine is transmission connection with aileron root, and the center axis of rudder engine output gear rotation coincides with the extension line of aileron rotation axis and is arranged, and through composite material, the integration lightweight is realized, and more through the creative space layout and function coupling of transmission system and integration structure, completely eliminate transmission gap, and realized the revolutionary assembly experience of " aligning and combining", thereby guaranteeing the extremely high control accuracy and reliability at the source.

Description

Technical Field

[0001] This utility model relates to the field of aviation technology, specifically to an embedded servo transmission structure for fixed-wing aircraft. Background Technology

[0002] Existing control surfaces for fixed-wing aircraft, such as the connection and drive technology between the wings and ailerons, have long relied on mechanical hinges and linkage mechanisms. This traditional approach suffers from three inherent bottlenecks: 1. Structural bottleneck: Independent hinges, bearings, carbon tubes and servo brackets result in a large number of parts, heavy weight, and complex assembly, and create aerodynamic defects and stress concentration points, affecting fatigue life.

[0003] 2. Transmission bottleneck: There is an unavoidable clearance between the connecting rod and the hinge, which leads to sluggish control surface response and reduced control precision, making it impossible to meet the control requirements of high-dynamic flight.

[0004] 3. Assembly bottleneck: The assembly process requires cumbersome adjustment and locking of the connecting rod length, which is time-consuming, labor-intensive, and heavily reliant on the operator's experience, making it difficult to ensure consistency.

[0005] Therefore, there is an urgent need to develop a specific structural solution that can efficiently and accurately integrate it with embedded servo drive transmission in order to achieve the comprehensive goals of high precision, high reliability and simplified assembly. Utility Model Content

[0006] The purpose of this invention is to provide an embedded servo transmission structure for fixed-wing aircraft. It achieves integrated lightweighting through composite materials, and further eliminates transmission gaps by creatively arranging and functionally coupling the transmission system with the integrated structure. It also achieves a revolutionary assembly experience of "alignment and engagement", thereby ensuring extremely high control precision and reliability from the source, thus solving the problems mentioned in the background art.

[0007] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: An embedded servo transmission structure for a fixed-wing aircraft includes a fuselage, a main wing fixedly connected to the fuselage, an aileron rotatably connected to one side of the main wing, and a servo. The main wing and the aileron are integrally connected by a flexible composite material connection structure. The servo is embedded in the fuselage. The output gear of the servo is connected to the root of the aileron, and the central axis of rotation of the servo output gear coincides with the extension line of the rotation axis of the aileron.

[0008] A further technical solution is to have an internal gear ring at the root of the aileron, located at the axis of rotation of the aileron, which meshes with the output gear; so that when the main wing is fixedly mounted on the fuselage, the output gear is placed inside the internal gear ring and meshes with the internal gear ring.

[0009] A further technical solution is to have a rudder arm at the root of the aileron, with an internal gear ring located at the end of the rudder arm that coincides with and is aligned with the axis of rotation of the aileron.

[0010] A further technical solution is that the composite flexible connection structure is made of high-performance fiber composite materials.

[0011] A further technical solution is to use aramid fibers as the high-performance composite material.

[0012] Compared with the prior art, the beneficial effects of this utility model are: 1. High structural strength and fatigue life: The wing and aileron are integrated through a continuous composite flexible connection structure, which avoids stress concentration at mechanical connection points, allowing the load to be efficiently and evenly transferred and distributed, thereby significantly improving the fatigue life and reliability of the structure.

[0013] 2. Significant weight reduction: By eliminating a large number of mechanical connecting parts such as hinges, bearings, and connecting rods, as well as separate servo brackets, the integrated structure achieves significant weight reduction, which is beneficial to improving the aircraft's endurance and maneuverability. At the same time, it also eliminates the failure modes such as loosening and wear that these parts may cause, and the system reliability is fundamentally improved.

[0014] 3. High control precision and hysteresis-free response: Since the servo output gear directly meshes with the internal gear ring set on the aileron, the mechanical backlash in the traditional hinge and linkage system is eliminated, forming a backlash-free transmission system and avoiding impact loads; the output angle of the servo and the deflection angle of the aileron have a strict linear relationship, achieving millisecond-level precise response.

[0015] 4. Simplified assembly process and high reliability: The assembly concept of "alignment equals connection" is implemented. During final assembly, simply align the wing with the integrated aileron to the fuselage, allowing the servo motor's output gear to naturally engage with the internal gear ring on the aileron, thus completing the transmission connection. This significantly simplifies assembly, reduces manual adjustments, lowers assembly errors, and improves overall consistency and reliability.

[0016] 5. Excellent durability and environmental adaptability: The flexible connection structure of composite materials is resistant to corrosion and high and low temperature changes, and its ability to adapt to harsh environments is far stronger than that of easily corroded and deformable metal mechanical parts. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the embedded servo transmission structure for a fixed-wing aircraft according to the present invention.

[0018] Figure 2 This is a schematic diagram showing the disassembled structure of an embedded servo transmission structure for a fixed-wing aircraft according to the present invention.

[0019] Figure 3 This is a schematic diagram of the composite flexible connecting section structure of this utility model.

[0020] Icons: 1-Fuselage, 2-Main Wing, 3-Aileron, 4-Servo, 5-Composite Flexible Connection Structure, 7-Internal Gear Ring, 8-Rudder Arm, 9-Connector A, 10-Connector B, 11-Connecting Section, 12-Embedded Section. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0022] All electrical components involved in this application are prior art. Those skilled in the art understand their connection methods. With the help of those skilled in the art, all electrical components in this application and their compatible power supplies can be connected by wires. According to the actual situation, a suitable controller can be selected to meet the control requirements. For specific connections and control sequences, please refer to the description below. The electrical connection between each electrical component is completed in the order of operation. The detailed connection methods are well known in the art. The following mainly introduces the working principle and process, and will not describe the electrical control.

[0023] Example 1 Reference Figure 1 , Figure 2 This utility model discloses an embedded servo transmission structure for a fixed-wing aircraft, comprising a fuselage 1, a main wing 2 fixedly connected to the fuselage 1, an aileron 3 rotatably connected to one side of the main wing 2, and a servo motor 4. The main wing 2 is mounted on the fuselage 1 by means of mounting holes and bolts and nuts, which is existing technology. Those skilled in the art can directly obtain the corresponding installation relationship and structure based on common knowledge, so it will not be described in detail here. The main wing 2 and the aileron 3 are integrally connected by a composite material flexible connection structure 5, so that the main wing 2 and the aileron 3 form a complete rigid-flexible composite structure without any independent mechanical hinges. The servo motor 4 is embedded in the fuselage 1, and the output gear of the servo motor 4 is connected to the root of the aileron 3 for transmission, and the central axis of rotation of the output gear of the servo motor 4 coincides with the extension line of the rotation axis of the aileron 3.

[0024] In this embodiment, the wing and aileron 3 are integrally connected by a composite flexible connection structure 5, forming a complete integral structural component without independent mechanical hinges. This avoids stress concentration at mechanical connection points, allowing the load to be efficiently and evenly transferred and distributed, thereby significantly improving the fatigue life and reliability of the structure. It eliminates a large number of mechanical connecting components such as hinges, bearings, and connecting rods, as well as a separate servo motor 4 bracket. Significant weight reduction is achieved through structural integration, which is beneficial to improving the aircraft's endurance and maneuverability.

[0025] Example 2 Based on Example 1, referring to Figure 1 , Figure 2 The root of the aileron 3 is provided with an internal gear ring 7 at the position of the axis of rotation of the aileron 3, which is matched with the output gear; so that when the main wing 2 is fixedly installed on the fuselage 1, the output gear is placed in the internal gear ring 7 and meshes with the internal gear ring 7.

[0026] In one preferred embodiment, the aileron 3 is provided with a rudder arm 8 at its root, and the internal gear ring 7 is located at the end of the rudder arm 8 that coincides with and is aligned with the axis of rotation of the aileron 3.

[0027] Specifically, during final assembly, the wing with integrated aileron 3 is simply connected to the fuselage 1, allowing the output gear of the servo motor 4 to naturally engage with the internal gear ring 7, thus completing the transmission connection. This significantly simplifies assembly, reduces manual adjustments, lowers assembly errors, and improves overall consistency and reliability, realizing the "alignment equals engagement" assembly concept. Simultaneously, because the output gear of the servo motor 4 directly meshes with the internal gear ring 7 mounted on the aileron 3, mechanical backlash in traditional hinge and linkage systems is eliminated, forming a backlash-free transmission system. The output angle of the servo motor 4 exhibits a strictly linear relationship with the deflection angle of the aileron 3, achieving millisecond-level precise response.

[0028] Example 3 Based on Example 1, the composite flexible connection structure 5 is made of high-performance fiber composite material, which is aramid fiber.

[0029] It should be noted that, referring to Figure 3The composite flexible connection structure includes connector A9, connector B10, and a connecting segment 11 between them. Connecting segment 11 is made of high-performance fiber material and is at least partially immersed in a non-fluid material that maintains its flexibility. The non-fluid material includes, but is not limited to, silicone rubber or sealant. The immersion length can be set according to the specific application, mainly the folding angle, which can be determined through calculation. Ideally, the area between connector A9 and connector B10 is the immersion area, thus eliminating any high-strength, non-bendable areas between them, thereby better ensuring the relative arbitrary flipping requirements of connector A9 and connector B10. To increase connection reliability, both ends of connecting segment 11 need to be connected to connector A9 and connector B10 respectively, i.e., an embedded segment 12 of a certain length needs to be provided. The length of the embedded segment 12 is not limited and can be determined based on practical experience and experiments. Then, curing is performed to form an integrated structure. This is existing technology, and those skilled in the art can directly obtain the corresponding installation relationship and structure based on common knowledge, so it will not be elaborated further here.

[0030] Specifically, composite flexible connection structures are corrosion-resistant, resistant to high and low temperature changes, and have a much stronger ability to adapt to harsh environments than easily corroded and deformable metal mechanical parts.

[0031] Although the present invention has been described herein with reference to several illustrative embodiments, it should be understood that many other modifications and implementations can be devised by those skilled in the art, which will fall within the scope and spirit of the principles disclosed herein. More specifically, various variations and modifications can be made to the components and / or layout of the subject matter combination within the scope of the disclosure, drawings, and claims. Besides variations and modifications to the components and / or layout, other uses will be apparent to those skilled in the art.

Claims

1. An embedded rudder actuator transmission structure of a fixed-wing aircraft, comprising a fuselage (1), a main wing (2) fixedly connected to the fuselage (1), an aileron (3) rotatably connected to one side of the main wing (2), and a rudder actuator (4), characterized in that: The main wing (2) and the aileron (3) are integrally connected by a composite material flexible connection structure (5). The servo motor (4) is embedded in the fuselage (1). The output gear of the servo motor (4) is connected to the root of the aileron (3) for transmission. The central axis of the rotation of the output gear of the servo motor (4) coincides with the extension line of the rotation axis of the aileron (3).

2. The fixed-wing aircraft flush rudder actuator transmission structure of claim 1, wherein: The root of the aileron (3) is provided with an internal gear ring (7) that meshes with the output gear at the position of the axis of rotation of the aileron (3); so that when the main wing (2) is fixedly installed on the fuselage (1), the output gear is placed in the internal gear ring (7) and meshes with the internal gear ring (7).

3. The fixed-wing aircraft flush rudder actuator transmission structure of claim 2, wherein: The aileron (3) has a rudder arm (8) at its root, and the internal gear ring (7) is located at the end of the rudder arm (8) that coincides with and is aligned with the axis of rotation of the aileron (3).

4. The fixed-wing aircraft recessed elevator actuator transmission structure of claim 1, wherein: The flexible connection structure of the composite material is made of high-performance fiber composite material.

5. The fixed-wing aircraft recessed elevator actuator transmission structure of claim 4, wherein: The high-performance fiber composite material is aramid fiber.

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