Improved motor isolation structure for electric vertical take-off and landing aircraft

Abstract

Provided is an electric vertical take-off and landing aircraft with an improved motor vibration isolation structure, comprising a plurality of propeller structures, the propeller structure comprising a motor, a base, a vibration isolator, and a blade, the motor being connected to the blade, the vibration isolator being circular and made of manganese copper alloy, the vibration isolator being arranged between the motor and the base, and a plurality of hollow grooves being formed on the side of the vibration isolator close to the base.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft design, and in particular to an electric vertical take-off and landing aircraft with improved motor vibration isolation structure. BACKGROUND

[0002] The design and development of electric vertical take-off and landing aircraft (eVTOL) has attracted widespread attention from aerospace companies, the automotive industry, the transportation industry, governments, the military, and academia. The potential future applications of electric vertical take-off and landing aircraft include urban passenger transport, regional passenger transport, cargo transport, personal aircraft, and emergency medical services. With the development of electric vertical take-off and landing aircraft technology and the use of high-power electric motors, the vibration problem of the propellers and motors of the power system of such aircraft when rotating at high speed and high load is becoming increasingly prominent. Excessive vibration can cause problems such as structural damage, fatigue failure, abnormal operation or failure of on-board equipment, and discomfort for personnel.

[0003] One of the characteristics of electric vertical take-off and landing aircraft is the ability to complete vertical take-off, which can be achieved using a distributed lift system or a lift / thrust system that combines lift and thrust. The power level required by electric vertical take-off and landing aircraft is usually much higher than that of ground vehicles with the same number of seats. Regardless of the aircraft configuration, the power system of electric vertical take-off and landing aircraft will work in a high-speed and high-torque state for a long time, and the power system will have a large vibration excitation on the entire aircraft, which will have a certain negative impact on the aircraft structure, system equipment, and personnel comfort.

[0004] Existing technical solutions mainly have two ways to reduce vibration: reducing the vibration amplitude of the power system itself and reducing vibration transmission. The power system of an aircraft is usually composed of power batteries, motor controllers, power motors, and propellers. The unbalanced force of the propeller rotor, the aerodynamic unbalanced force of the propeller, and the unbalanced force of the motor rotor constitute the main excitation source of the vibration of the power system.

[0005] The vibration reduction method for reducing the vibration amplitude of the power system itself is mainly achieved by reducing the main excitation source. For example, the propeller can be finely designed and manufactured, and dynamic balance compensation can be performed before use to minimize the unbalance of the propeller rotor. The accuracy of the propeller surface can be improved to reduce the aerodynamic unbalanced force caused by the rotation of the propeller. The design, manufacture and assembly of the motor can be refined to reduce the unbalance of the motor rotor itself. Through the above measures, the strength of the vibration source can be reduced as much as possible at the front end. However, this vibration reduction method through high-precision design, manufacture and installation will greatly increase the cost and technical difficulty, and with the increase of power and speed, the vibration is more intense. The current high-power motor still has unacceptable vibration even after implementing the above measures. Therefore, measures need to be taken to reduce the vibration transmission.

[0006] The existing measures for reducing the vibration transmission of the power system usually use rubber vibration isolators. However, due to the low strength of the rubber vibration isolator itself, the size and weight of the rubber vibration isolator that can meet the load requirement are relatively large, which makes it difficult to install, and the environmental adaptability is poor, so the use range is greatly limited. There is no very ideal solution for the vibration isolation of the current high-power motor. SUMMARY

[0007] The present application is made in view of the above state of the art. The purpose of the present application is to provide an improved motor vibration isolation structure for an electric vertical take-off and landing aircraft, which uses a manganese-copper alloy vibration isolator, has a compact structure and a light weight motor vibration isolation structure, and can effectively reduce the vibration transmitted from the motor to the aircraft fuselage.

[0008] The embodiments of the present application provide an improved motor vibration isolation structure for an electric vertical take-off and landing aircraft, which includes a plurality of propeller structures, the propeller structure including a motor, a base, a vibration isolator, a blade,

[0009] The motor is connected to the blade,

[0010] The vibration isolator is a circular ring and is made of manganese-copper alloy,

[0011] The vibration isolator is arranged between the motor and the base,

[0012] A plurality of hollow grooves are formed on the side of the vibration isolator close to the base.

[0013] In at least one possible embodiment, the electric vertical take-off and landing aircraft includes a plurality of motor arms, and the base is connected to the motor arms.

[0014] In at least one possible embodiment, the motor includes a flange connected to the vibration isolator,

[0015] The base is formed with a mounting surface connected to the vibration isolator.

[0016] In at least one possible implementation, one or more threading grooves are further formed on the side of the vibration isolator close to the base,

[0017] The mounting surface is formed with a bottom groove,

[0018] The threading grooves and the bottom groove are used for passing electrical lines.

[0019] In at least one possible implementation, the width of the hollow groove in the circumferential direction of the vibration isolator gradually increases from the radially inner side to the radially outer side of the vibration isolator.

[0020] In at least one possible implementation, a plurality of bolt holes are further formed on the vibration isolator,

[0021] A bolt hole is formed between every two adjacent hollow grooves.

[0022] In at least one possible implementation, the base is formed with a plurality of mounting holes,

[0023] The base further includes a plurality of bolts,

[0024] The bolts are connected to the motor through the mounting holes and the bolt holes.

[0025] In at least one possible implementation, the wall surface of the hollow groove is formed with an inner chamfer, and the edge of the wall surface of the hollow groove is formed with an outer chamfer to reduce stress concentration.

[0026] In at least one possible implementation, the inner chamfer and the outer chamfer are both round chamfers.

[0027] In at least one possible implementation, the outer diameter of the vibration isolator is 130 mm, the inner diameter is 60 mm, and the thickness is 10 mm. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 Structure diagram of an electric vertical take-off and landing aircraft according to an embodiment of the present application.

[0029] Figure 2 Structure diagram of a propeller according to an embodiment of the present application.

[0030] Figure 3 Bottom structure diagram of a propeller according to an embodiment of the present application.

[0031] Figure 4 Exploded structure diagram of a motor vibration isolation structure according to an embodiment of the present application.

[0032] Figure 5 This is a structural schematic diagram of a vibration isolator according to one embodiment of this application.

[0033] Figure 6 This is a schematic diagram of the structure of a base according to one embodiment of this application.

[0034] Explanation of reference numerals in the attached figures

[0035] 101 fuselage propeller

[0036] 102 Tail propeller

[0037] 200 motor arms

[0038] 110 motor

[0039] 111 Flange

[0040] 120 base

[0041] 121 bolt

[0042] 122 gasket

[0043] 123 Mounting Surface

[0044] 1231 Bottom groove

[0045] 1232 Mounting Hole

[0046] 130 Vibration Isolator

[0047] 131 Bolt hole

[0048] 132 Hollowed-out groove

[0049] 133 Threading channel

[0050] 134 Inner chamfer

[0051] 135° outer chamfer

[0052] 140 blades Detailed Implementation

[0053] Exemplary embodiments of this application are described below with reference to the accompanying drawings. It should be understood that these specific descriptions are for teaching those skilled in the art how to implement this application only, and are not intended to exhaustively describe all possible methods of this application, nor to limit the scope of this application.

[0054] This application provides an electric vertical takeoff and landing (EVA) aircraft (hereinafter sometimes simply referred to as an aircraft) with an improved motor vibration isolation structure. For example... Figure 1 As shown, the electric vertical takeoff and landing aircraft can be a compound wing type, which may include multiple fuselage propellers 101 (exemplary). Figure 1The aircraft comprises eight fuselage propellers 101, which can be mounted on the aircraft's motor arms 200. For example... Figure 2 As shown, the fuselage propeller 101 may include a motor 110, a base 120, a vibration isolator 130, and blades 140. The base 120 and the vibration isolator 130 can form a motor vibration isolation structure, reducing the vibration transmitted to the fuselage by the motor 110 and its connected blades 140. It is understood that the electric vertical takeoff and landing aircraft of this application is not limited to compound wing aircraft; for example, it can also be a multi-rotor aircraft. For aircraft including a tail propeller, for example... Figure 1 The aircraft includes two tail propellers 102, and a similar motor vibration isolation structure can also be installed at the tail propellers 102.

[0055] Specifically, such as Figure 2 , Figure 4 , Figure 6 As shown, a vibration isolator 130 can be disposed between the motor 110 and the base 120. The motor 110 has a flange 111 at its contact point with the vibration isolator 130. It is understood that the flange 111 may have multiple bolt holes for structural connection. The motor 110 can be connected to the propeller blade 140. The base 120 can be connected to the aircraft's motor arm 200. The base 120 may have a mounting surface 123 that contacts the vibration isolator 130. The mounting surface 123 may have one or more bottom grooves 1231 (exemplarily two in the figure) and multiple mounting holes 1232. The bottom grooves 1231 are recessed from the mounting surface 123 in a direction away from the vibration isolator 130.

[0056] Furthermore, such as Figure 5 , Figure 6 As shown, the vibration isolator 130 can be annular (including approximately annular). The inner hole of the vibration isolator 130 allows the structure of the motor 110 to pass through or partially pass through. The side of the vibration isolator 130 near the motor 110 can be flat and can contact the flange 111. The side of the vibration isolator 130 near the base 120 can form a plurality of radially extending perforated slots 132 and one or more radially extending wire passage slots 133. The plurality of perforated slots 132 can be used to reduce structural weight and enhance vibration isolation effect. The one or more wire passage slots 133 can cooperate with the bottom groove 1231 on the mounting surface 123 of the base 120 for the passage of electrical wires.

[0057] Preferably, the width of the hollow groove 132 and the wire-threading groove 133 in the circumferential direction of the vibration isolator 130 can gradually increase from the radial inner side to the radial outer side in the radial direction of the vibration isolator 130. It can be understood that the width of the wire-threading groove 133 can be smaller than the width of the hollow groove 132.

[0058] It can be understood that the hollow groove 132 and the threading groove 133 are only distinguished by whether the grooves are used to pass through the electrical lines in actual use. In fact, the threading groove 133 can also have the effect of reducing the structural weight and enhancing the damping effect. At the same time, the hollow groove 132 can also be used to pass through the electrical lines. And in actual use, it is not necessary that each threading groove 133 has an electrical line passing through it.

[0059] As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. Figure 5 As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. Figure 5 As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111.

[0060] As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. Figure 3 As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. Figure 4 As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. Figure 4 As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111.

[0061] As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111.

[0062] As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111. As shown in FIG. 1, the hollow groove 132 and the threading groove 133 are arranged on the flange 111 of the motor 110. The hollow groove 132 is an axial through hole, and the threading groove 133 is a groove with a width smaller than the diameter of the electrical line. The hollow groove 132 and the threading groove 133 can be arranged alternately on the flange 111. In other words, the hollow groove 132 and the threading groove 133 are arranged alternately on the flange 111.

[0063] Preferably, the hollow groove 132 of the vibration isolator 130 is formed with an inner chamfer 134 on the wall surface (two sides of the groove) of the wire slot 133, so that the wall surface of the hollow groove 132 and the wire slot 133 has a certain curvature. The edge of the wall surface of the hollow groove 132 (the edge of the intersection of the hollow groove 132 and the wire slot 133 on the surface of the vibration isolator 130 facing the base 120) can also be formed with an outer chamfer 135. The inner chamfer 134 and the outer chamfer 135 can avoid stress concentration during use, and improve the fatigue resistance and durability of the vibration isolator 130.

[0064] Preferably, the inner chamfer 134 and the outer chamfer 135 are round chamfers. It can be understood that, under the condition of the structure permitting, the size of the inner chamfer 134 can be as large as possible to weaken the stress concentration phenomenon.

[0065] The vibrations generated by the propeller and the motor of the aircraft are mainly medium-high frequency vibrations in three directions in space, so the vibration isolator 130 needs to have a certain material thickness in the axial and radial directions. Preferably, the size of the vibration isolator 130 can be: an outer diameter of 130 mm, an inner diameter of 60 mm, and a thickness of 10 mm. It can be understood that the above is an exemplary preferred size of the vibration isolator 130, and does not limit the specific size of the vibration isolator 130.

[0066] Through relevant experiments, it is verified that, when the aircraft is in a hovering state, the vibration peak of the aircraft is reduced by 35% after the above motor vibration isolation structure is set. Experiments show that the motor vibration isolation structure effectively reduces vibration and in turn effectively reduces structural strain.

[0067] The following briefly describes some beneficial effects of the above embodiments of the application.

[0068] (1) The motor vibration isolation structure of the electric vertical take-off and landing aircraft provided by the embodiments of the application uses a manganese copper alloy material for the vibration isolator used in the improved motor vibration isolation structure, and the vibration isolator can withstand larger loads and pressures during the operation of the aircraft, while having excellent vibration isolation effect.

[0069] (2) The electric vertical take-off and landing aircraft provided by the embodiments of the application has a small size and compact structure of the vibration isolation structure, which can meet the relatively strict installation space requirements of the high-power motor used in the aircraft.

[0070] (3) The vibration isolator of the electric vertical take-off and landing aircraft provided by the embodiments of the application uses a manganese copper alloy material, which has more excellent environmental adaptability and durability than traditional rubber vibration isolators, and is more suitable for motor vibration isolation of the aircraft.

[0071] It can be understood that, in the present application, the number of components or members is not particularly limited, and the number can be one or more, and the plurality herein refers to two or more. For the case where the number of components or members is specifically described as, for example, two, three, four, etc. in the drawings and / or the description, the specific number is generally exemplary and not limiting, and it can be understood as a plurality, i.e. two or more, but this does not mean that the present application excludes the case of one.

[0072] It should be understood that the above embodiments are only exemplary and are not intended to limit the present application. Those skilled in the art can make various modifications and changes to the above embodiments under the teaching of the present application without departing from the scope of the present application.

Claims

1. An improved electric vertical take-off and landing aircraft with motor isolation structure for carrying goods and / or personnel, comprising a plurality of propeller structures, characterized in that, the propeller structure comprises a motor (110), a base (120), an isolator (130), a blade (140), the electric vertical take-off and landing aircraft comprises a plurality of motor arms (200), the base (120) is connected to the motor arm (200), the motor (110) is connected to the blade (140), the isolator (130) is circular and made of manganese copper alloy, the isolator (130) is arranged between the motor (110) and the base (120), the base (120) and the isolator (130) form a motor isolation structure for reducing the vibration transmitted from the motor (110) and the blade (140) connected thereto to the fuselage of the electric vertical take-off and landing aircraft, a plurality of hollow grooves (132) are formed on one side of the isolator (130) close to the base (120) to reduce the structure weight and enhance the isolation effect, the width of the hollow groove (132) in the circumferential direction of the isolator (130) gradually increases from the radial inner side to the radial outer side of the isolator (130).

2. The improved electric vertical take-off and landing aircraft with motor isolation structure according to claim 1, characterized in that, the motor (110) comprises a flange (111) connected to the isolator (130), the base (120) is formed with a mounting surface (123) connected to the isolator (130).

3. The improved electric vertical take-off and landing aircraft with motor isolation structure according to claim 2, characterized in that, one or more threading grooves (133) are also formed on one side of the isolator (130) close to the base (120), the mounting surface (123) is formed with a bottom groove (1231), the threading groove (133) and the bottom groove (1231) are used for passing electrical lines.

4. The improved electric vertical take-off and landing aircraft with motor isolation structure according to claim 1, characterized in that, a plurality of bolt holes (131) are also formed on the isolator (130), one bolt hole (131) is formed between every two adjacent hollow grooves (132).

5. The improved electric vertical take-off and landing aircraft of claim 4, wherein, the base (120) is formed with a plurality of mounting holes (1232), the base (120) further comprises a plurality of bolts (121), the bolts (121) are connected to the motor (110) through the mounting holes (1232) and the bolt holes (131).

6. The electric vertical take-off and landing vehicle with improved motor vibration isolation structure according to claim 1, characterized in that, the wall surface of the hollow groove (132) is formed with an inner chamfer (134), and the edge of the wall surface of the hollow groove (132) is formed with an outer chamfer (135) to reduce stress concentration.

7. The improved electric vertical take-off and landing aircraft of claim 6, wherein, the inner chamfer (134) and the outer chamfer (135) are both round chamfers.

8. The electric vertical take-off and landing vehicle with improved motor vibration isolation structure according to claim 1, characterized in that, the outer diameter of the isolator (130) is 130 mm, the inner diameter is 60 mm, and the thickness is 10 mm.

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