Vertical take-off and landing aircraft motor fixing rod structure

Abstract

The utility model is suitable for the technical field of motor fixing rods, discloses a motor fixing rod structure of a vertical take-off and landing aircraft, and aims to solve the technical problems that in the prior art, the dismounting process is tedious, and a motor is separated due to abrasion of a motor mounting structure. Comprising a motor fixing rod, the motor fixing rod comprises a fixing rod main body and a long cover, a front long rib and a rear long rib are installed in the fixing rod main body, through the arrangement of a stabilizing component, after a front reinforcing rib is matched with a rear reinforcing rib, an abutting block is made to be unfolded outwards and abut against the inner wall of the front reinforcing rib by abutting against a sliding block rack, and then the front reinforcing rib and the rear reinforcing rib are fixed. The situation that a gap is generated when the rear reinforcing rib is matched with the front reinforcing rib, so that the front long rib shakes due to vibration of the motor in the operation process of the aircraft, the gap is greatly abraded, the transmission process of the motor is affected, and the risk that the aircraft falls due to the phenomenon that a motor gear is separated from a transmission gear in a severe case is avoided.

Description

Technical Field

[0001] This utility model relates to the technical field of motor mounting rods, and in particular to a motor mounting rod structure for vertical take-off and landing aircraft. Background Technology

[0002] Aircraft motor mounting rods are critical structural components used to securely mount motors to specific locations on an aircraft. They are typically made of high-strength materials, such as aluminum alloys or composite materials, to ensure they can withstand various forces and vibrations during flight. Their structural design must comprehensively consider the motor's weight, size, mounting angle, and compatibility with other aircraft systems. It must ensure stable motor mounting, facilitate installation and maintenance, and also meet the aerodynamic shape and spatial layout requirements of the aircraft. This is crucial for ensuring the normal operation of aircraft motors and flight safety.

[0003] Nowadays, most motor mounting rods directly connect the motor to the rod. When the motor is damaged and needs repair, the entire mounting rod needs to be disassembled before the motor can be disassembled and repaired, making the disassembly process cumbersome. Moreover, the motor is usually installed inside the mounting rod through the connecting structure at both ends of the rib. To facilitate installation, a small gap is left between the two structures, making interference fit installation difficult. Under the long-term vibration of the motor, this gap will wear down and widen, causing the motor to detach. Summary of the Invention

[0004] The purpose of this utility model is to overcome the shortcomings of the prior art and provide a motor fixing rod structure for vertical take-off and landing aircraft, which aims to solve the technical problems of cumbersome disassembly process and motor detachment caused by wear of the motor installation structure in the prior art.

[0005] To achieve the above objectives, this utility model proposes a motor mounting rod structure for a vertical take-off and landing aircraft, including a motor mounting rod. The motor mounting rod includes a mounting rod body and a long cover. A front long rib and a rear long rib are installed inside the mounting rod body. Several straight long ribs are provided on the front long rib. Front reinforcing ribs are fixed on both sides of the front long rib.

[0006] A rear reinforcing rib is fixed to one end face of the rear long rib. The rear reinforcing rib cooperates with the corresponding front reinforcing rib. A stabilizing member is provided inside the rear reinforcing rib.

[0007] The stabilizing member includes a slider rack and an abutment block that slide within the rear reinforcing rib, the abutment block being located on the outer periphery of the slider rack.

[0008] Preferably, at least three abutment blocks are provided, and the abutment blocks are located at the edge of the rear reinforcing rib. Each abutment block is internally threaded with a lead screw, and a lead screw gear is fixed on the lead screw. The end face of the slider rack meshes with all the lead screw gears.

[0009] Preferably, the slider rack moves axially and extends to the outside near the front reinforcing rib, while the other side of the slider rack is fixed to the inner wall of the rear reinforcing rib by a spring, and the abutment block moves radially.

[0010] Preferably, one side of the front reinforcing rib is open, and the rear reinforcing rib matches its opening, both being semi-circular in shape.

[0011] Preferably, a support rib is also fixedly installed on the rear long rib;

[0012] The support ribs include a first upper support rib, a first lower support rib, a second upper support rib, and a second lower support rib, wherein the first upper support rib and the second upper support rib are located above the rear long rib and have a through hole in the middle, and the first lower support rib and the second lower support rib are located below the rear long rib.

[0013] Preferably, the bottom of the front long rib is also fixed with a front fixing seat and a rear fixing seat.

[0014] Preferably, a right motor cover and a left motor cover are provided on both sides of the long cover. The long cover, the right motor cover and the left motor cover are installed on the main body of the fixing rod by screws to form a whole. All the outer walls of the ribs of the motor fixing rod are covered with skin.

[0015] Compared with the prior art, the beneficial effects of the vertical takeoff and landing aircraft motor fixing rod structure provided by this utility model are as follows:

[0016] 1. The straight rib motor mounting rod is divided into several areas, each with a motor installed in parallel to provide power output. When a motor in a single area is damaged, the motor in that area can be repaired or replaced directly, avoiding the need to disassemble the entire motor system and avoid the difficulties of repair and disassembly. At the same time, the multi-area setup allows the aircraft to continue operating after a single motor is damaged, reducing the risk of the aircraft crashing.

[0017] 2. By cooperating with the front and rear reinforcing ribs, the entire front long rib is located in the middle of the main body of the fixing rod, with space left at its bottom and around for heat dissipation, etc. Moreover, after the motor is installed on the entire front long rib, it can form a separate motor module. When the motor is disassembled and assembled as a whole, the module can be directly disassembled and assembled without disassembling other parts, making it convenient for maintenance and installation of accessories.

[0018] 3. By setting up stabilizing components, after the front and rear reinforcing ribs are engaged, the abutting block can be extended outward by abutting the inner wall of the front reinforcing rib through the abutting slider rack. This avoids gaps when the rear and front reinforcing ribs are engaged, which would cause the front long rib to shake due to motor vibration during aircraft operation, resulting in significant wear on this gap. This would affect the motor's transmission process, and in severe cases, the motor gears and transmission gears could disengage, thus posing a risk of the aircraft crashing.

[0019] The features and advantages of this utility model will be described in detail through embodiments and accompanying drawings. Attached Figure Description

[0020] Figure 1 This is a perspective view of an embodiment of the present utility model.

[0021] Figure 2 This is an exploded view of an embodiment of the present invention.

[0022] Figure 3 This is an internal view of an embodiment of the present utility model.

[0023] Figure 4 This is a view of the stable component of an embodiment of the present utility model.

[0024] Figure 5 This is a half-sectional view of the stabilizing component of an embodiment of this utility model.

[0025] in:

[0026] 10-Fixed rod body; 11-Long cover; 12-Right motor cover; 13-Left motor cover; 14-Skin; 20-Front long rib; 21-Front fixed seat; 22-Rear fixed seat; 23-Straight long rib; 24-Front reinforcing rib; 30-Rear long rib; 31-First upper support rib; 32-First lower support rib; 33-Second upper support rib; 34-Second lower support rib; 35-Rear reinforcing rib; 40-Slider rack and pinion; 41-Abutting block; 42-Lead screw; 43-Lead screw gear; 44-Spring. Detailed Implementation

[0027] 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. However, it should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit its scope. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of the present utility model.

[0028] In the description of this utility model, it should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to or indirectly connected to the other element.

[0029] In the description of this utility model, it should be noted that the terms "center," "length," "width," "thickness," "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, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of describing the invention and for simplifying the description, 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. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.

[0030] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0031] See Figure 1-5This utility model provides a motor mounting structure for a vertical takeoff and landing (VTOL) aircraft, including a motor mounting rod. The motor mounting rod includes a mounting rod body 10 and a long cover 11. A front long rib 20 and a rear long rib 30 are installed inside the mounting rod body 10. Several straight long ribs 23 are fixed to the front long rib 20 by welding or bonding, dividing the motor mounting rod interior into several areas. Each area is equipped with a motor, and the motors are connected in parallel to provide power output. When a motor in a single area fails, the motor in that area can be directly repaired and replaced, avoiding the need to disassemble the entire motor system and causing difficulties in repair and disassembly. Furthermore, the multi-area setup allows the aircraft to continue operating after a single motor fails, reducing the risk of the aircraft crashing. A front mounting base 21 and a rear mounting base 22 are also fixed to the bottom of the front long rib 20, extending to... The motor mounting rod and the front long rib 20 can be installed inside the aircraft together through the front mounting base 21 and the rear mounting base 22. The front long rib 20 is fixed with front reinforcing ribs 24 on both sides, and the rear long rib 30 is fixed with a rear reinforcing rib 35 on one end face. The rear reinforcing rib 35 cooperates with the corresponding front reinforcing rib 24. One side of the front reinforcing rib 24 is set with an opening, and the rear reinforcing rib 35 cooperates with its opening. Both are semi-circular. The rear reinforcing rib 35 is provided with a stabilizing component. Through the cooperation of the front reinforcing rib 24 and the rear reinforcing rib 35, the entire front long rib 20 is located in the middle of the mounting rod body 10. Space is left at its bottom and around for heat dissipation, etc. Moreover, after the motor is installed on the entire front long rib 20, it can form a separate motor module. When the motor is disassembled and assembled as a whole, the module can be directly disassembled and assembled without disassembling other parts, which makes it convenient for maintenance and installation of accessories.

[0032] The stabilizing components include a sliding rack 40 and abutment blocks 41 that slide within the rear reinforcing rib 35. At least three abutment blocks 41 are located on the outer periphery of the sliding rack 40 and are positioned at the edge of the rear reinforcing rib 35. A lead screw 42 is internally threaded onto each abutment block 41, and a lead screw gear 43 is fixed to the lead screw 42. The end face of the sliding rack 40 has racks corresponding to the lead screw gear 43, and the end face of the sliding rack 40 meshes with all the lead screw gears 43. The sliding rack 40 moves axially and extends outwards towards the side closest to the front reinforcing rib 24. On the other side, it is fixed to the inner wall of the rear reinforcing rib 35 by spring 44. The abutment block 41 moves radially. With the setting of the stabilizing component, after the front reinforcing rib 24 and the rear reinforcing rib 35 are engaged, the abutment block 41 can be extended outward by the abutment slider rack 40 and abut against the inner wall of the front reinforcing rib 24. This avoids the gap that occurs when the rear reinforcing rib 35 and the front reinforcing rib 24 are engaged. As a result, during the operation of the aircraft, the vibration of the motor will cause the front long rib 20 to shake, affecting the transmission process of the motor. In severe cases, the motor gear and the transmission gear may disengage, which may cause the aircraft to fall.

[0033] Support ribs are also fixedly installed on the rear long rib 30. The support ribs include a first upper support rib 31, a first lower support rib 32, a second upper support rib 33, and a second lower support rib 34. The first upper support rib 31 and the second upper support rib 33 are located above the rear long rib 30 and have through holes in the middle. The first lower support rib 32 and the second lower support rib 34 are located below the rear long rib 30. The support ribs can reduce the weight of the motor fixing rod and increase the stability of the rear long rib 30, making it easier for the front long rib 20 to be installed more stably in the fixing rod body 10.

[0034] The long cover 11 is also provided with a right motor cover 12 and a left motor cover 13 on both sides. The long cover 11, the right motor cover 12 and the left motor cover 13 are installed on the main body 10 of the fixing rod by screws to form a whole. All the outer walls of the ribs of the motor fixing rod are bonded with skin 14. The skin 14 can further stabilize all the ribs and increase their strength.

[0035] Working principle: In use, first press all the motors onto the front long rib 20, then place the front long rib 20 into the fixed rod body 10, and then make the front reinforcing rib 24 abut against the rear reinforcing rib 35 to complete the installation. Then fix the long cover 11, right motor cover 12 and left motor cover 13 with screws. During the process of the front reinforcing rib 24 abutting against the rear reinforcing rib 35, the front reinforcing rib 24 will abut against the slider rack 40, causing the slider rack 40 to compress the spring 44 inward and slide, thereby allowing the wire to pass through. The lever gear 43 drives the lead screw 42 to rotate, causing all the abutment blocks 41 to slide outward synchronously and unfold, so that the abutment blocks 41 abut against the inner wall of the front reinforcing rib 24, thereby greatly reducing the gap between the front reinforcing rib 24 and the rear reinforcing rib 35. Moreover, the tighter the rear reinforcing ribs 35 on both sides are pressed, the smaller the gap between the front reinforcing rib 24 and the rear reinforcing rib 35, and the more securely the front long rib 20 is installed. When removing the front long rib 20, the rear reinforcing rib 35 on the side away from the rear long rib 30 can be removed to complete the disassembly.

[0036] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions or improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A motor mounting rod structure for a vertical takeoff and landing aircraft, comprising a motor mounting rod, characterized in that: The motor fixing rod includes a fixing rod body (10) and a long cover (11). The fixing rod body (10) is equipped with a front long rib (20) and a rear long rib (30). The front long rib (20) is provided with a number of straight long ribs (23). Front reinforcing ribs (24) are fixed on both sides of the front long rib (20). A rear reinforcing rib (35) is fixed to one end face of the rear long rib (30). The rear reinforcing rib (35) cooperates with the corresponding front reinforcing rib (24). A stabilizing member is provided inside the rear reinforcing rib (35). The stabilizing member includes a slider rack (40) that slides within the rear reinforcing rib (35) and an abutment block (41) located on the outer periphery of the slider rack (40).

2. The vertical takeoff and landing aircraft motor mounting rod structure as described in claim 1, characterized in that: At least three abutment blocks (41) are provided. The abutment blocks (41) are located at the edge of the rear reinforcing rib (35). The abutment blocks (41) are internally threaded with lead screws (42). Lead screw gears (43) are also fixed on the lead screws (42). The end face of the slider rack (40) meshes with all the lead screw gears (43).

3. The vertical takeoff and landing aircraft motor mounting rod structure as described in claim 1, characterized in that: The slider rack (40) moves axially and extends to the outside near the front reinforcing rib (24). The other side of the slider rack (40) is fixed to the inner wall of the rear reinforcing rib (35) by a spring (44). The abutment block (41) moves radially.

4. The vertical takeoff and landing aircraft motor mounting rod structure as described in claim 1, characterized in that: The front reinforcing rib (24) has an opening on one side, and the rear reinforcing rib (35) matches its opening, both of which are semi-circular in shape.

5. The vertical takeoff and landing aircraft motor mounting rod structure as described in claim 1, characterized in that: A support rib is also fixedly installed on the rear long rib (30); The support ribs include a first upper support rib (31), a first lower support rib (32), a second upper support rib (33), and a second lower support rib (34), wherein the first upper support rib (31) and the second upper support rib (33) are located above the rear long rib (30) and have a through hole in the middle, and the first lower support rib (32) and the second lower support rib (34) are located below the rear long rib (30).

6. The vertical takeoff and landing aircraft motor mounting rod structure as described in claim 1, characterized in that: The bottom of the front long rib (20) is also fixed with a front fixing seat (21) and a rear fixing seat (22).

7. The vertical takeoff and landing aircraft motor mounting rod structure as described in claim 1, characterized in that: The long cover (11) is also provided with a right motor cover (12) and a left motor cover (13) on both sides. The long cover (11), the right motor cover (12) and the left motor cover (13) are installed on the main body (10) of the fixing rod by screws to form a whole. All the outer walls of the ribs of the motor fixing rod are covered with skin (14).

Images