Power system and aircraft

Abstract

The utility model relates to the technical field of motors, in particular to a power system and an aircraft. The power system is applied to an aircraft and comprises a stator assembly and a rotor assembly, the stator assembly generates a magnetic field to drive the rotor assembly to rotate, the power system further comprises a first main shaft and a second main shaft, the first main shaft comprises a first end and a second end which are opposite, the first end penetrates through the stator assembly, and the second end penetrates through the rotor assembly. And the second main shaft is fixed on the rotor assembly, is fixedly connected with the second end, and synchronously rotates relative to the stator assembly along with the first main shaft and the rotor assembly. The power system provided by the utility model adopts the sectional main shaft, and is convenient to disassemble and assemble.

Description

Technical Field

[0001] This utility model relates to the field of motor technology, and in particular to a power system and an aircraft. Background Technology

[0002] The primary function of an aircraft's propulsion system is to generate driving torque to rotate the propeller and achieve flight. In existing technology, the propulsion system includes a main shaft, a stator assembly, and a rotor assembly. The main shaft passes through the stator assembly and the rotor assembly and is fixed to the rotor assembly. Because the main shaft is relatively long and vertically mounted to the rotor and stator assemblies, the aircraft is disassembled for easier packaging and transportation. Disassembling the main shaft can cause the propulsion system to fall apart, affecting its dynamic balance and leading to excessive vibration. Utility Model Content

[0003] In order to solve the technical problem that disassembling the main shaft would cause the power system to fall apart, this utility model provides a power system and aircraft that are easy to disassemble.

[0004] The first aspect of this utility model provides a power system for an aircraft, including a stator assembly and a rotor assembly. The stator assembly generates a magnetic field to drive the rotor assembly to rotate. The system also includes a first main shaft and a second main shaft. The first main shaft has a first end and a second end opposite to each other. The first end passes through the stator assembly and is fixed to the rotor assembly. The second main shaft is fixedly connected to the second end and rotates synchronously with the first main shaft and the rotor assembly relative to the stator assembly.

[0005] In some embodiments, the rotor assembly includes a base, the base including a second body and a third tube, the third tube being disposed on the side of the second body away from the stator assembly, and the first end being fixed to the third tube by a first fastener.

[0006] In some embodiments, the first end is provided with a fixing groove, the third tube is provided with a first fixing hole, and the first fastener fixes the first end and the third tube through the fixing groove and the first fixing hole.

[0007] In some embodiments, the second spindle includes a third end and a fourth end disposed opposite to each other, the third end being fixedly connected to the second end by a second fastener, and the fourth end being used for fixed connection to a propeller.

[0008] In some embodiments, the third end is inserted into the receiving groove of the second end, the second end is provided with a second fixing hole, the third end is provided with a third fixing hole, and the second fastener fixes the second end and the third end through the second fixing hole and the third fixing hole.

[0009] In some embodiments, the sidewall of the second end has a notch that communicates with the receiving groove.

[0010] In some embodiments, the stator assembly includes a cover and a bracket. The cover includes a first body, a first tube, and a second tube. The first tube and the second tube are located on two opposite sides of the first body. The first tube includes an inner tube and an outer tube that are sleeved together. The inner tube communicates with the second tube. The first spindle is inserted into the second tube and the inner tube. The bracket is fixed to the outer wall of the outer tube.

[0011] In some embodiments, a bearing assembly is also included, through which the first spindle is connected to the stator assembly.

[0012] In some embodiments, the first spindle further includes a shaft connecting the first end and the second end, wherein the diameters of the first end, the shaft, and the second spindle are approximately equal, and the outer diameter of the second end is larger than that of the second spindle.

[0013] A second aspect of this utility model provides an aircraft, including a frame, a power system, and a propeller. The power system is fixed to the frame, and the propeller is fixed to the power system, driving the propeller to rotate.

[0014] Compared to existing technologies, the power system of the aircraft provided in this embodiment features a first main shaft that passes through the stator assembly and is fixed to the rotor assembly, while the second main shaft is fixed to the second end. By employing a segmented main shaft, when disassembling the aircraft, the second main shaft is removed, and the first main shaft ensures that the power system does not disintegrate and its balance is not affected. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the following description of the embodiments will be briefly introduced. The drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a three-dimensional structural diagram of a power system for an aircraft provided in the first embodiment of the present invention;

[0017] Figure 2 yes Figure 1 A three-dimensional exploded view of the power system shown.

[0018] Figure 3 yes Figure 1 A three-dimensional structural decomposition diagram of the power system shown from another angle;

[0019] Figure 4 yes Figure 1 A cross-sectional view of the power system shown.

[0020] Figure 5 yes Figure 1 The diagram shows the exploded three-dimensional structure of the first and second main axes. Detailed Implementation

[0021] The technical solutions in the embodiments of this utility model will be clearly and completely described below. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0022] Please refer to the following: Figure 1 and Figure 2 ,in, Figure 1 This is a three-dimensional structural diagram of a power system for an aircraft provided by an embodiment of the present invention. Figure 2 for Figure 1 The diagram shows an exploded three-dimensional structural view of a power system applied to an aircraft. This embodiment of the invention provides an aircraft comprising a frame, a power system 10, and a propeller 20. The power system 10 is fixed to the frame, and the propeller 20 is fixed to the power system 10. The power system 10 drives the propeller 20 to rotate.

[0023] The power system 10 includes a stator assembly 11, a rotor assembly 12, a first main shaft 14, and a second main shaft 16. The stator assembly 11 generates a magnetic field to drive the rotor assembly 12 to rotate. The first main shaft 14 passes through the stator assembly 11 and is fixed to the rotor assembly 12. The second main shaft 16 is fixed to the first main shaft 14. The propeller 20 is fixed to the second main shaft 16 and rotates synchronously with the second main shaft 16, the first main shaft 14, and the rotor assembly 12 relative to the stator assembly 11.

[0024] The stator assembly 11 includes a cover 111, a bracket 113, and multiple conductive coils 115. The bracket 113 is fixed to the cover 111, and the multiple conductive coils 115 are wound around the bracket 113 in a ring arrangement. The conductive coils 115 generate a magnetic field when energized. The cover 111 includes a first body 1111, a first tube 1113, and a second tube 1115. The first tube 1113 and the second tube 1115 are located at the centers of two opposite sides of the first body 1111 and are interconnected. The first tube 1113 is located on the side of the first body 1111 facing the rotor assembly 12, and the second tube 1115 is located on the side of the first body 1111 facing the second main shaft 16. The bracket 113 is preferably a magnetic conductor, specifically an iron core or silicon steel sheet.

[0025] Please refer to the following: Figure 3 and Figure 4 ,in, Figure 3 yes Figure 1 The diagram shows a three-dimensional exploded view of the power system from another angle. Figure 4 yes Figure 1 The diagram shows a cross-sectional view of the power system. The first tube body 1113 includes an inner tube 11131, an outer tube 11133, and a connecting wall 11135. The outer tube 11133 is sleeved on the inner tube 11131, and the connecting wall 11135 connects the outer tube 11133 and the inner tube 11131. The inner tube 11131 communicates with the second tube body 1115, and the first main shaft 14 is housed in the second tube body 1115 and the inner tube 11131. The bracket 113 is fixed to the outer wall of the outer tube 11133.

[0026] Please see again Figure 2 The rotor assembly 12 includes a rotor base 121 and magnets 123. The rotor base 121, together with the cover 111, forms a receiving space to receive the bracket 113 and the conductive coil 115. There are multiple magnets 123, which are wound around the radial surface of the rotor base 121 corresponding to the conductive coil 115.

[0027] The rotor base 121 includes a base 1211 and a side wall 1213. The side wall 1213 is connected to the edge of the base 1211 facing the first body 1111 and is spaced apart from the first body 1111. The magnet 123 is fixed to the inner surface of the side wall 1213. The base 1211 is provided with toothed protrusions 12111 corresponding to the magnet 123, and one magnet 123 is positioned and clamped between two adjacent toothed protrusions 12111.

[0028] Please see again Figure 3 and Figure 4The base 1211 includes a second body 12112 and a third tube 12113, wherein the third tube 12113 is located at the center of the second body 12112 on the side away from the stator assembly 11.

[0029] It is understandable that through holes may be provided on the first body 1111 and the base 1211 in order to dissipate heat and reduce the weight of the power system 10.

[0030] The first spindle 14 includes a first end 141, a shaft body 142, and a second end 143 connected in sequence. The first end 141 passes through the stator assembly 11, is inserted into the third tube 12113, and is fixed therein. The second end 143 is housed in the second tube 1115 and fixed to the second spindle 16.

[0031] The second main shaft 16 includes a third end 161 and a fourth end 163 disposed opposite to each other. The third end 161 is fixedly connected to the second end 143, and the fourth end 163 is fixedly connected to the propeller 20.

[0032] Please refer to the following: Figure 4 and Figure 5 , Figure 5 yes Figure 1 The diagram shows an exploded three-dimensional view of the first and second spindles. In this embodiment, the power system 10 further includes a first fastener 17. A fixing groove 1411 is provided on the first end 141, and a first fixing hole 121131 is provided on the third tube 12113 corresponding to the fixing groove 1411. The first fastener 17 fixes the first end 141 and the third tube 12113 through the fixing groove 1411 and the first fixing hole 121131.

[0033] In some embodiments, the first fastener is a screw, and the inner wall of the first fixing hole is provided with threads that cooperate with the first fastener for locking.

[0034] The power system 10 also includes a second fastener 18. The diameters of the first end 141, the shaft body 142, and the second spindle 16 are approximately equal. The outer diameter of the second end 143 is larger than that of the second spindle 16, and a receiving groove 1430 with an inner diameter approximately equal to that of the second spindle 16 is provided. The third end 161 of the second spindle 16 is inserted into the receiving groove 1430 of the second end 143. The second end 143 is provided with a second fixing hole 1431, and the third end 161 is provided with a third fixing hole 1611. The second fastener 18 fixes the second end 143 and the third end 161 through the second fixing hole 1431 and the third fixing hole 1611.

[0035] In some embodiments, the second fastener is a screw, and the inner wall of the second fixing hole is provided with threads that cooperate with and lock the second fastener.

[0036] In a further embodiment, a notch 1433 is formed on the side wall of the second end 143, communicating with the receiving groove 1430, to facilitate the installation of the second spindle 16. The second tube body 1115 is provided with a clearance through hole 11151 corresponding to the second fixing hole 1431 to facilitate the installation of the second fastener 18.

[0037] In some embodiments, the first and second spindles are tubular. There are two fixing slots, arranged opposite each other; there are two corresponding first fixing holes; and two corresponding first fasteners. There are two third fixing holes, arranged opposite each other; there are two corresponding second fixing holes; and one second fastener. There are two notches, arranged opposite each other.

[0038] The power system 10 further includes a bearing assembly 19, which is housed within the inner tube 11131 and fitted with the shaft body 142. The inner tube 11131 has a limiting step corresponding to the bearing assembly 19. The bearing assembly 19 includes a first bearing 191 and a second bearing 192. The first bearing 191 is sandwiched between the limiting step and the base 1211, and the second bearing 192 is sandwiched between the limiting step and the second end 143.

[0039] Compared to existing technologies, the power system 10 of the aircraft provided in this embodiment of the utility model has a first end 141 of the first main shaft 14 passing through the stator assembly 11 and fixed to the rotor assembly 12, and a second main shaft 16 fixed to the second end 143. By adopting a segmented main shaft, when disassembling the aircraft, the second main shaft 16 is disassembled, while the first main shaft 14 ensures that the power system 10 does not fall apart and does not affect the balance of the power system 10, facilitating disassembly and installation.

[0040] The above description is only a part of the embodiments of this utility model and does not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made based on the contents of the utility model specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. A power system for an aircraft, comprising a stator assembly and a rotor assembly, wherein the stator assembly generates a magnetic field to drive the rotor assembly to rotate, characterized in that, Also includes: The first main shaft includes a first end and a second end opposite to each other, the first end passing through the stator assembly and fixed to the rotor assembly; The second main shaft is fixedly connected to the second end and rotates synchronously with the first main shaft and the rotor assembly relative to the stator assembly.

2. The power system according to claim 1, characterized in that, The rotor assembly includes a base, the base includes a second body and a third tube, the third tube is located on the side of the second body away from the stator assembly, and the first end is fixed to the third tube by a first fastener.

3. The power system according to claim 2, characterized in that, The first end is provided with a fixing groove, and the third tube is provided with a first fixing hole. The first fastener fixes the first end and the third tube through the fixing groove and the first fixing hole.

4. The power system according to claim 1, characterized in that, The second spindle includes a third end and a fourth end that are disposed opposite to each other. The third end and the second end are fixedly connected by a second fastener, and the fourth end is used to be fixedly connected to the propeller.

5. The power system according to claim 4, characterized in that, The third end is inserted into the receiving groove of the second end. The second end is provided with a second fixing hole, and the third end is provided with a third fixing hole. The second fastener fixes the second end and the third end through the second fixing hole and the third fixing hole.

6. The power system according to claim 5, characterized in that, The side wall at the second end has a notch that communicates with the receiving groove.

7. The power system according to claim 1, characterized in that, The stator assembly includes a cover and a bracket. The cover includes a first body, a first tube, and a second tube. The first tube and the second tube are located on two opposite sides of the first body. The first tube includes an inner tube and an outer tube. The inner tube and the second tube communicate with each other. The first spindle is inserted into the second tube and the inner tube. The bracket is fixed to the outer wall of the outer tube.

8. The power system according to claim 1, characterized in that, It also includes a bearing assembly, through which the first spindle is connected to the stator assembly.

9. The power system according to claim 1, characterized in that, The first spindle also includes a shaft body connecting the first end and the second end. The diameters of the first end, the shaft body, and the second spindle are approximately equal, and the outer diameter of the second end is larger than that of the second spindle.

10. An aircraft comprising a frame, a power system, and a propeller, wherein the power system is fixed to the frame, the propeller is fixed to the power system, and the propeller is driven to rotate, characterized in that, The power system is any one of the power systems described in claims 1-9.

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