EVTOL aircraft thrust unit arrangement and installation structure

Abstract

The utility model discloses an eVTOL aircraft thrust unit arrangement and installation structure, which comprises a thrust unit, the thrust unit is installed on an empennage framework, the empennage framework comprises a horizontal tail end rib and a vertical tail root rib, the horizontal tail end rib and the vertical tail root rib are oppositely distributed, the front end part of the horizontal tail end rib and the front end part of the vertical tail root rib are connected with a butt joint ring, and the butt joint ring is connected with the thrust unit. A front beam connecting piece is connected to the middle of the butt joint ring, a motor mounting seat is connected to the rear end of the butt joint ring, a horizontal tail front beam and a horizontal tail rear beam are mounted on the horizontal tail end rib, a vertical tail front beam and a vertical tail rear beam are mounted on the vertical tail root rib, and the horizontal tail end rib, the vertical tail root rib, the motor mounting seat, the front beam connecting piece and the butt joint ring form a box-shaped frame structure. The connecting position of the thrust unit and the motor mounting base is located on the rear beam of the empennage, and the thrust unit and the empennage have an overlapping area, so that the thrust unit is arranged in the front, and the gravity center of the whole machine is arranged in the front due to the fact that the thrust unit is heavy, the tail force arm is long and the thrust unit is arranged in the front.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to an arrangement and installation structure of an eVTOL aircraft thrust unit. Background Art

[0002] The development of eVTOL (Electric Vertical Takeoff and Landing) electric vertical takeoff and landing aircraft has attracted widespread attention from aerospace companies, the automotive industry, the transportation industry, the government, the military and academia. The potential future applications of eVTOL involve a variety of scenarios such as urban passenger transport, regional passenger transport, freight, personal aircraft, and emergency medical services. The American Vertical Flight Association believes that eVTOL technology is one of the most important technological changes in the aviation industry since the birth of helicopters 75 years ago, and may be more revolutionary than the emergence of turbine engines. According to the "World Electric Vertical Takeoff and Landing (eVTOL) Aircraft Directory" published online by the association, there are currently more than 260 projects engaged in eVTOL development around the world. The use of electric propulsion systems instead of internal combustion engine power has gained many advantages and unique qualities. The most prominent advantages are energy saving and environmental protection, high efficiency and low energy consumption, while achieving near zero emissions, low noise and vibration levels, and good ride comfort. It is a truly environmentally friendly aircraft. In addition, it also has the characteristics of safety and reliability, simple structure, easy operation and use, good maintainability / low cost, and good economy. There are also many advantages in design: the overall layout is flexible, and both optimal layout and unconventional / innovative layout can be adopted; aircraft with extraordinary performance can be designed to meet special purpose requirements, etc.

[0003] When an eVTOL aircraft is flying in the sky, it needs to meet the requirement that the center of gravity is a certain distance in front of the aerodynamic center of the whole aircraft in order to achieve stability in level flight. The thrust unit includes motors, propellers, etc., and weighs more than 40kg. In this example, the weight of the two thrust units is greater than 80kg. Because it is arranged at the tail, it is far away from the aerodynamic center of the whole aircraft, and the lever arm is long, which will cause the center of gravity of the whole aircraft to move backward, and have an adverse effect on the arrangement of other equipment and personnel. In order to ensure that the center of gravity is in a reasonable position, the passengers and seats can be arranged forward when designing the fuselage, but during flight, it may face the state of empty flight, so the center of gravity will move backward. If the position requirements of the center of gravity and the aerodynamic center cannot be met, if necessary, counterweights can be added to the nose position, but this will complicate the operating procedures. Utility Model Content

[0004] The purpose of the utility model is to provide an eVTOL aircraft thrust unit arrangement and installation structure to solve the problems mentioned in the background technology. To achieve the above purpose, the utility model provides the following technical solutions: an eVTOL aircraft thrust unit arrangement and installation structure, including a thrust unit, the thrust unit is installed on a tail frame, the tail frame includes a horizontal tail end rib and a vertical tail root rib, the horizontal tail end rib and the vertical tail root rib are relatively distributed, the front end of the horizontal tail end rib and the vertical tail root rib are connected with a docking ring, the middle is connected with a front beam connector, and the rear end is connected to a motor mounting seat, the horizontal tail end rib is installed with a horizontal tail front beam and a horizontal tail rear beam, the vertical tail root rib is installed with a vertical tail front beam and a vertical tail rear beam, and the horizontal tail end rib, the vertical tail root rib, the motor mounting seat, the front beam connector, and the docking ring form a box-type frame structure.

[0005] Preferably, the thrust unit comprises a motor, and the motor is provided with heat dissipation fins along the direction of airflow.

[0006] Preferably, the motor mounting seat is an annular structure as a whole, and a motor mounting hole is opened along the circumference of the motor mounting seat as a whole. A thickened area is designed around the motor mounting hole, and a reinforcing rib is provided in the middle of the thickened area. The motor is installed on the motor mounting seat by bolts matching the motor mounting hole.

[0007] Preferably, a certain gap is left between the motor cooling fins and the surrounding structure.

[0008] Preferably, the horizontal tail rear beam, the horizontal tail front beam, the vertical tail rear beam, and the vertical tail front beam are made of carbon fiber composite materials.

[0009] The technical effects and advantages of the utility model: the structure is conducive to the center of gravity of the whole machine: the position where the thrust unit is connected to the motor mounting seat is at the rear beam of the tail wing, and there is an overlapping area with the tail wing, so that the thrust unit is arranged relatively forward. Considering that the weight of the thrust unit is heavy and the tail arm is long, the forward arrangement is conducive to the arrangement of the center of gravity of the whole machine;

[0010] Good heat dissipation effect: The heat dissipation fins of the motor are directly exposed to the air, using the aircraft airflow to dissipate heat from the motor, with a large heat dissipation area, high heat dissipation speed, and good heat dissipation effect. At the same time, the direction of the heat dissipation fins follows the direction of the airflow, effectively reducing aerodynamic resistance;

[0011] Good structural strength: The motor mounting seat of the thrust unit is directly connected to the rear beams of the horizontal tail and vertical tail, and then the horizontal tail end rib, vertical tail root rib, and front beam connector form a box-shaped structure, which has good structural effects and high strength in bearing torque, thrust, vibration, etc.

[0012] Light weight: air-cooled motors are used. Compared with liquid-cooled motors, the liquid cooling system can be eliminated, thus reducing the weight of the thrust unit.

[0013] Small aerodynamic resistance: The direction of the heat sink fins is along the direction of the airflow, the windward area is small, and the pressure difference resistance is small. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is an axonometric drawing of the utility model;

[0015] Figure 2 It is an axonometric diagram of the connection between the tail wing frame and the motor of the utility model;

[0016] Figure 3 It is an axonometric view of the motor mounting seat of the utility model;

[0017] Figure 4 This is a circumferential cross-sectional view of the motor of the utility model;

[0018] Figure 5 This is a cross-sectional view of the connection position between the motor and the motor seat of the utility model;

[0019] Figure 6 It is an axonometric drawing of the utility model in the whole machine.

[0020] In the figure, 1. thrust unit arrangement and installation structure; 11. thrust unit; 111. motor; 1111. cooling fin; 12. tail; 121. horizontal tail rear beam; 122. horizontal tail front beam; 123. horizontal tail end rib; 124. motor mounting seat; 1241. reinforcing rib; 1242. motor mounting hole; 1243. thickening area; 125. vertical tail rear beam; 126. vertical tail front beam; 127. vertical tail root rib; 128. front beam connector; 129. docking ring; 13. bolts; 2. eVTOL aircraft. DETAILED DESCRIPTION

[0021] In order to make the technical means for realizing the utility model, creative features, objectives and effects easy to understand, the utility model is further explained below in conjunction with specific diagrams. In the description of the utility model, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, an integral connection or a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two components.

[0022] Example

[0023] like Figure 6 As shown, the thrust unit arrangement and mounting structure 1 is located at the tail of the eVTOL aircraft 2. The thrust is generated by the thrust unit to propel the eVTOL aircraft 2 to fly. In this example, there are two thrust units. When one fails, the other can satisfy the eVTOL aircraft 2 to continue flying at the minimum flight speed, thereby improving the safety of the eVTOL aircraft 2.

[0024] like Figure 1 As shown, the thrust unit 11 is installed at the fusion position of the tail 12, the horizontal tail and the vertical tail. The thrust unit 11 and the tail 12 have a partial overlapping area, so that the thrust unit 11 is arranged more forward, effectively reducing the moment arm of the thrust unit 11 relative to the center of gravity, facilitating the design and arrangement of other equipment and personnel of the eVTOL aircraft 2, and improving the diversity and flexibility of the arrangement of the eVTOL aircraft 2.

[0025] like Figure 2 As shown, the thrust unit 11 includes a motor 111, which is mounted on a tail frame. The tail frame includes a horizontal tail rear beam 121, a horizontal tail front beam 122, a horizontal tail end rib 123, a motor mounting seat 124, a vertical tail rear beam 125, a vertical tail front beam 126, a vertical tail root rib 127, a front beam connector 128 and a docking ring 129; the horizontal tail end rib 123 and the vertical tail root rib 127 are relatively distributed, and the front ends of the horizontal tail end rib 123 and the vertical tail root rib 127 are connected to a pair of The connecting ring 129 is connected with a front beam connector 128 in the middle, and the rear end is connected to the motor mounting seat 124. The horizontal tail end rib 123 is equipped with a horizontal tail front beam 122 and a horizontal tail rear beam 121, and the vertical tail root rib 127 is equipped with a vertical tail front beam 126 and a vertical tail rear beam 125, wherein the horizontal tail rear beam 121, the horizontal tail front beam 122, the vertical tail rear beam 125, and the vertical tail front beam 126 are the main load-bearing components of the tail structure, and are made of carbon fiber composite materials to effectively reduce the weight of the structure. The horizontal tail end rib 123, the motor mounting seat 124, the vertical tail root rib 127, the docking ring 129, and the front beam connector 128 are aluminum alloy machined parts, the preferred material is 2024, and the preferred heat treatment state is T351. Connecting ribs are designed on the parts at the positions where they need to be connected with other parts for easy connection. The horizontal tail end rib 123, the vertical tail root rib 127, the motor mounting seat 124, the front beam connector 128, and the docking ring 129 together form a box-type frame structure. In addition to transmitting the load of the horizontal tail and the vertical tail, it also bears the thrust of the thrust unit 11 and the torque of the motor 111, and has high strength and safety. The motor 111 is designed with heat dissipation fins 1111 in the direction of the airflow. When the eVTOL aircraft 2 flies forward, the motor 111 is cooled by the relative airflow to meet the heat dissipation requirements of the motor 111. The heat dissipation fins 1111 of the motor 111 are completely exposed to the air, and their inner diameter is greater than or equal to the size of the corresponding position on the tail 12 with the motor 111, so as to ensure that as many fins as possible are exposed to the air.

[0026] like Figure 3 and Figure 5As shown, the motor mounting seat 124 is designed with reinforcing ribs 1241, motor mounting holes 1242, and thickened areas 1243; the motor mounting seat 124 is an annular structure as a whole, and the motor mounting seat 124 is provided with motor mounting holes 1242 along the circumference as a whole, the motor mounting holes 1242 are connected to the motor 111 with bolts 13, and a thickened area 1243 is designed around the motor mounting holes 1242 to reduce the stress level around the motor mounting holes 1242 and ensure the connection strength and safety, and reinforcing ribs 1241 are designed at positions close to the motor mounting holes 1242, and the reinforcing ribs 1241 are located in the middle of the thickened area 1243 to improve the stiffness of this area, to ensure that it is less deformed when subjected to the torque and thrust of the thrust unit 11, to ensure that the thrust line of the thrust unit 11 is not deviated, and to ensure the flight quality of the eVTOL aircraft 2.

[0027] like Figure 4 As shown, a certain gap is left between the motor cooling fins 1111 and the surrounding structures. On the one hand, it ensures that the airflow on the motor cooling fins 1111 is not disturbed by the surrounding structures, maintains a high flow rate, and improves the heat dissipation efficiency. On the other hand, it ensures that when the motor 11 is running, due to the action of force, the tail wing deforms together with the motor 11, and does not interfere with the surrounding structure, causing damage to the motor 11 or structural damage, thereby ensuring safety. The gap in this example is 12.7mm.

[0028] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An eVTOL aircraft thrust unit arrangement and installation structure, comprising a thrust unit, characterized in that: The thrust unit is installed on the tail frame, and the tail frame includes a horizontal tail end rib and a vertical tail root rib, the horizontal tail end rib and the vertical tail root rib are relatively distributed, the front ends of the horizontal tail end rib and the vertical tail root rib are connected with a docking ring, the middle part is connected with a front beam connecting piece, and the rear end is connected with a motor mounting seat, the horizontal tail end rib is installed with a horizontal tail front beam and a horizontal tail rear beam, and the vertical tail root rib is installed with a vertical tail front beam and a vertical tail rear beam, and the horizontal tail end rib, the vertical tail root rib, the motor mounting seat, the front beam connecting piece, and the docking ring form a box-type frame structure.

2. The eVTOL aircraft thrust unit arrangement and installation structure according to claim 1, characterized in that: The thrust unit comprises a motor, and the motor is provided with heat dissipation fins along the airflow direction.

3. The eVTOL aircraft thrust unit arrangement and installation structure according to claim 2, characterized in that: The motor mounting seat is an annular structure as a whole, and a motor mounting hole is opened along the circumference of the motor mounting seat as a whole. A thickened area is designed around the motor mounting hole, and a reinforcing rib is provided in the middle of the thickened area. The motor is installed on the motor mounting seat by bolts matching the motor mounting hole.

4. The eVTOL aircraft thrust unit arrangement and installation structure according to claim 2, characterized in that: A certain gap is left between the motor heat dissipation fins and the surrounding structure.

5. The eVTOL aircraft thrust unit arrangement and installation structure according to claim 1, characterized in that: The horizontal tail rear beam, the horizontal tail front beam, the vertical tail rear beam, and the vertical tail front beam are made of carbon fiber composite materials.

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