Unmanned aerial vehicle engine component fixing support
Patent Information
- Application Number
- CN202522675763.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-17
- Publication Date
- 2026-10-27
- Estimated Expiration
- 2035-12-17
AI Technical Summary
通过对现有无人机发动机安装方式的分析，我们发现当前普遍存在以下技术不足：首先，在结构方面，现有技术通常将无人机发动机直接安装在结构较为单一的独立支撑架上，这种支撑架多为平面或简单框架式结构，缺乏针对纵向（即沿发动机推力方向）和侧向载荷的强化设计，导致整体纵向支撑刚度不足、抗变形能力较弱，发动机安装后，在高速运转及无人机机动飞行产生的复杂应力下，支撑结构的稳定性和可靠性有待提升；
本实用新型通过强化支撑结构：该支架采用了创新的支板组件设计，其核心是一个L形直角托架，用于承托发动机主体；在此基础上，关键性地增加了倾斜布置的支撑筋板，L形直角托架与倾斜筋板共同构建了一个三角稳定支撑结构，三角形在力学上具有天然的稳定性，此设计能高效地将发动机工作时产生的纵向力和振动载荷分散传递至支架主体，显著增强了沿推力方向的支撑刚性和整体抗扭、抗弯强度，从而为发动机提供了更为稳固、可靠的安装基础；
Smart Images
Figure CN224899143U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a mounting bracket for UAV engine components. Background Technology
[0002] The installation of engines during the aircraft installation process has particularly high requirements. As the core component of the aircraft, the different installation methods of the engine have a great impact on the flight of the aircraft. The weight of the engine accounts for a large proportion of the aircraft, and the stability of the engine installation is crucial. Analysis of existing UAV engine installation methods reveals the following common technical shortcomings: First, in terms of structure, existing technologies typically mount UAV engines directly onto relatively simple independent support frames. These support frames are mostly planar or simple frame structures, lacking reinforcement designs for longitudinal (i.e., along the engine thrust direction) and lateral loads. This results in insufficient overall longitudinal support stiffness and weak resistance to deformation. After engine installation, the stability and reliability of the support structure need to be improved under the complex stresses generated by high-speed operation and UAV maneuvering. Secondly, in terms of cushioning and protection, existing solutions mostly use two exposed rubber blocks as vibration damping elements. Although this provides some cushioning, this "exposed" design has obvious drawbacks: when the drone is performing missions outdoors, the rubber blocks are directly exposed to the natural environment and are affected by external factors such as rain, snow, direct ultraviolet radiation (sun exposure), and sand and dust abrasion. This will accelerate the aging, hardening, and even cracking of the rubber material, leading to a rapid decline in cushioning performance, thereby shortening the service life of key vibration damping components, which may in turn affect the smoothness of engine operation and the reliability of the entire power system. Utility Model Content
[0003] The purpose of this utility model is to provide a mounting bracket for unmanned aerial vehicle (UAV) engine components to solve the problems mentioned in the background art.
[0004] To achieve the above objectives, this utility model provides the following technical solution: a mounting bracket for drone engine components, including a main support board, on the surface of which are fixed at least four support mounting columns, and on the surface of which are bolted, a support plate assembly that can stably support the drone engine, the support plate assembly being divided into a drone engine mounting structure and a support assembly structure, and a hidden buffer mounting structure being provided on the inner side of the support mounting columns.
[0005] Preferably, the UAV engine mounting structure includes an L-shaped right-angle bracket fixed to the surface of the supporting mounting column, and an inclined support rib is fixed to the lower end of the L-shaped right-angle bracket. The L-shaped right-angle bracket and the inclined support rib are combined to form a triangular stable support structure, and the upper end of the L-shaped right-angle bracket is provided with at least four mounting holes.
[0006] Preferably, the support assembly structure includes an annular protrusion disposed on the side of the L-shaped right-angle bracket, the annular protrusion being slidably sleeved on the surface of the support mounting column, and a first buffer pad being filled inside the annular protrusion, which supports the surface of the support mounting column.
[0007] Preferably, the concealed buffer installation structure includes a hexagonal groove formed inside the supporting installation column, through which a nut and a second buffer pad are slidably filled. The threaded end of the bolt passes through the L-shaped right-angle bracket, the first buffer pad, the supporting installation column, and the second buffer pad in sequence through the through hole, and the threaded end is screwed with a nut and locked.
[0008] Preferably, the second buffer pad adopts a hexagonal ring block structure, and the second buffer pad slides into the inner side of the support mounting column through a hexagonal groove.
[0009] Preferably, at least one support block is fixed to the outer surface of the support mounting column, and the surface of the support block is fixed to the main support component.
[0010] Preferably, the main support component can be designed as a square plate structure with multiple mounting holes on the plate surface for installation on the drone.
[0011] Compared with the prior art, the beneficial effects of this utility model are: This utility model strengthens the support structure: the bracket adopts an innovative support plate assembly design, the core of which is an L-shaped right-angle bracket used to support the engine body; on this basis, key additions are inclined support ribs. The L-shaped right-angle bracket and the inclined ribs together construct a triangular stable support structure. Triangles have natural stability in mechanics. This design can efficiently distribute and transfer the longitudinal force and vibration load generated during engine operation to the bracket body, significantly enhancing the support rigidity along the thrust direction and the overall torsional and bending strength, thereby providing a more stable and reliable installation foundation for the engine; Concealed buffer protection structure: We have improved the installation method of the buffer components, and designed all the vibration damping elements inside the concealed structure. Specifically: the first buffer pad is embedded and protected in the inner groove of the annular protrusion, and the second buffer pad is encapsulated in the inner cavity of the support mounting column. When fixed, it is locked by bolts and nuts hidden in the inner cavity. The core advantage of this design is that the first and second buffer pads are completely concealed after installation and are no longer directly exposed to the external environment. They are effectively wrapped and protected by the metal or composite material support structure, which fundamentally avoids direct erosion and damage from external factors such as rain, snow, ultraviolet rays, and sand. While ensuring a firm installation and excellent vibration reduction effect, it greatly extends the service life of the buffer pads and improves the durability and maintenance-free nature of the entire engine mount in harsh environments. In summary, this utility model, through the organic combination of a triangular stable support structure and a concealed buffer protection structure, significantly improves the strength and stability of the UAV engine mounting support while effectively solving the problem of the buffer element being susceptible to environmental aging, thus achieving a dual optimization of structural strength and durability. Attached Figure Description
[0012] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a side view of the overall structure of this utility model; Figure 3 This is a partial cross-sectional view of the overall structure of this utility model; Figure 4 This is a partial cross-sectional view of the support and mounting column of this utility model. Figure 5 This is a partial structural diagram of the second buffer pad of this utility model.
[0013] In the diagram: 1. Main support component; 2. Support mounting column component; 3. L-shaped right-angle bracket; 4. Inclined support rib; 5. Mounting hole; 6. Annular boss component; 7. Bolt; 70. Hexagonal groove; 8. Nut; 9. Second buffer pad; 10. First buffer pad; 20. Support block. Detailed Implementation
[0014] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0015] Please see Figure 1-5This utility model provides a technical solution: a fixed bracket for drone engine components, including a main support component 1, with at least four support mounting columns 2 fixed on the surface of the main support component 1, and a support plate assembly that can stably support the drone engine installed on the surface of the support mounting columns 2 by bolts 7. The support plate assembly is divided into a drone engine mounting structure and a support assembly structure, and a hidden buffer mounting structure is provided on the inner side of the support mounting columns 2. When installing the drone engine, it is mounted on the drone engine mounting structure using the existing fastening structure. Specifically, The UAV engine mounting structure includes an L-shaped right-angle bracket 3 fixed to the surface of the supporting mounting column 2, and an inclined support rib 4 fixed to the lower end of the L-shaped right-angle bracket 3. The L-shaped right-angle bracket 3 and the inclined support rib 4 combine to form a triangular stable support structure. Triangles have inherent mechanical stability, and this design efficiently distributes and transfers the longitudinal force and vibration load generated during engine operation to the main body of the bracket, significantly enhancing the support rigidity along the thrust direction and the overall torsional and bending strength, thus providing a more stable and reliable mounting foundation for the engine. The upper end of the L-shaped right-angle bracket 3 is provided with at least four mounting holes 5. When installing the UAV engine, it can be supported on the upper surface of the L-shaped right-angle bracket 3, and the UAV engine can be installed along the mounting holes 5 using fasteners. During installation, the right-angle structure of the L-shaped right-angle bracket 3 and the inclined support rib 4 enhance the longitudinal support force. Furthermore, when the drone floats up and down rapidly during flight, the vibration generated by the collision between the engine and the airflow can be supported by the triangular stable support structure, thereby improving the support strength; and a triangular cavity is formed between the L-shaped right-angle bracket 3 and the inclined support rib plate 4, so that the airflow can pass through the triangular cavity during flight without causing excessive resistance. When the L-shaped right-angle bracket 3 is installed with the main support component 1, it is stably installed through the support assembly structure. Specifically, The supporting assembly structure includes an annular protrusion 6 provided on the side of the L-shaped right-angle bracket 3. During installation, the annular protrusion 6 is slidably sleeved on the surface of the supporting mounting column 2, and the inner side of the annular protrusion 6 is filled with a first buffer pad 10. At this time, the first buffer pad 10 can be supported on the surface of the supporting mounting column 2. Then install it using bolt 7 and the concealed buffer mounting structure; Specifically, The concealed buffer installation structure includes a hexagonal groove 70 formed inside the support mounting column 2. A nut 8 and a second buffer pad 9 are slidably installed through the hexagonal groove 70. During installation, the threaded end of the bolt 7 is passed through the through hole sequentially through the L-shaped right-angle bracket 3, the first buffer pad 10, the support mounting column 2, and the second buffer pad 9. At this time, the threaded end of the bolt 7 is screwed onto the nut 8 and locked. The pressing end of the bolt 7 is pressed against the surface of the L-shaped right-angle bracket 3 for fixation. The installation is stable. Furthermore, the nut 8 is preset inside the hexagonal groove 70 and does not need to be removed. Furthermore, the first buffer pad 10 is supported on the outside of the support mounting column 2, and the second buffer pad 9 is supported on the inside of the support mounting column 2. After being supported on both sides, the vibration generated by the engine during operation can be offset by the first buffer pad 10 and the second buffer pad 9. Moreover, the first buffer pad 10 is hidden inside the annular protrusion 6, and the second buffer pad 9 is hidden inside the hexagonal groove 70 of the support mounting column 2. They are not exposed to the outside and will not be directly corroded by rain, snow and sun exposure, thus extending their service life. Furthermore, the second buffer pad 9 and the first buffer pad 10 can be made of EPDM rubber material, whose main chain is composed of saturated carbon-carbon single bonds. Unlike unsaturated diene rubber, it has extremely strong resistance to ozone, ultraviolet rays, sunlight and extreme weather conditions, high temperature, low temperature, rain and snow. The second buffer pad 9 adopts a hexagonal ring block structure. The second buffer pad 9 is slid into the inner side of the support mounting column 2 through the hexagonal groove 70. At least one support block 20 is fixed to the outer surface of the support mounting column 2, and the surface of the support block 20 is fixed to the main support plate 1. The support block 20 can be welded to the support mounting column 2 and the main support plate 1, and multiple support blocks 20 can be circumferentially distributed and fixed on the surface of the support mounting column 2, which can improve the support strength between the support mounting column 2 and the main support plate 1. The main support component 1 can be designed as a square plate structure with multiple mounting holes on the plate surface. Through these mounting holes, the main support component 1 can be installed with the drone using fasteners.
[0016] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. A mounting bracket for a drone engine component, comprising a supporting main board (1), characterized in that: The surface of the main support component (1) is fixed with no less than four support mounting columns (2). The surface of the support mounting columns (2) is fitted with a support plate assembly that can stably support the UAV engine by bolts (7). The support plate assembly is divided into a UAV engine mounting structure and a support assembly structure. The inner side of the support mounting columns (2) is provided with a hidden buffer mounting structure.
2. The mounting bracket for a UAV engine component according to claim 1, characterized in that: The UAV engine mounting structure includes an L-shaped right-angle bracket (3) fixed on the surface of the support mounting column (2), and an inclined support rib plate (4) is fixed at the lower end of the L-shaped right-angle bracket (3). The L-shaped right-angle bracket (3) and the inclined support rib plate (4) are combined to form a triangular stable support structure, and at least four mounting holes (5) are provided at the upper end of the L-shaped right-angle bracket (3).
3. The mounting bracket for unmanned aerial vehicle engine components according to claim 2, characterized in that: The support assembly structure includes an annular protrusion (6) disposed on the side of the L-shaped right-angle bracket (3). The annular protrusion (6) is slidably sleeved on the surface of the support mounting column (2), and the inner side of the annular protrusion (6) is filled with a first buffer pad (10), which supports the surface of the support mounting column (2) through the first buffer pad (10).
4. A mounting bracket for unmanned aerial vehicle engine components according to claim 3, characterized in that: The concealed buffer installation structure includes a hexagonal groove (70) opened on the inner side of the support installation column (2). A nut (8) and a second buffer pad (9) are slidably filled through the hexagonal groove (70). The threaded end of the bolt (7) passes through the through hole in sequence through the L-shaped right-angle bracket (3), the first buffer pad (10), the support installation column (2), and the second buffer pad (9), and the threaded end is screwed with the nut (8) and locked.
5. A mounting bracket for unmanned aerial vehicle engine components according to claim 4, characterized in that: The second buffer pad (9) adopts a hexagonal ring block structure, and the second buffer pad (9) slides into the inner side of the support mounting column (2) through the hexagonal groove (70).
6. A mounting bracket for unmanned aerial vehicle engine components according to claim 1, characterized in that: At least one support block (20) is fixed to the outer surface of the support mounting column (2), and the surface of the support block (20) is fixed to the main support column (1).
7. A mounting bracket for unmanned aerial vehicle engine components according to claim 1, characterized in that: The main support component (1) can be designed as a square plate structure with multiple mounting holes on the plate surface for installation on the UAV.