Motor system for aircraft hydraulic electric pump

Abstract

The motor system for the aircraft hydraulic electric pump is suitable for driving the hydraulic electric pump and comprises a support, a control box and a brushless direct-current motor, the control box and the brushless direct-current motor are installed on the support, the input end of the brushless direct-current motor is connected with the input end of the hydraulic electric pump, and the control box is electrically connected with the brushless direct-current motor through a cable. The brushless direct-current motor comprises a stator assembly, three-phase winding is carried out on the stator assembly in a parallel concentration mode, wires of the three-phase winding can shorten the size of the end portion of the stator winding in a direct leading-out mode, the brushless direct-current motor can adapt to large current supply, and the driving efficiency of the hydraulic electric pump of the airplane is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of drive structures, and in particular relates to a motor system for an aircraft hydraulic electric pump. Background Art

[0002] The secondary energy system of an aircraft is an energy system for aircraft control and manipulation, and its energy is mainly provided by the primary energy, namely the engine. Traditional secondary energy mainly consists of hydraulic energy, air pressure energy, electrical energy and mechanical energy. Each secondary energy includes independent energy production, conversion, control, protection, distribution, transmission and application, each forming a complex and complete system, making the aircraft interior design more complex, the structure bloated, the installation space tight, and the detection and maintenance inconvenient. In addition, hydraulic and air pressure leakage problems frequently occur, resulting in a high aircraft failure rate and poor reliability, which reduces performance. Summary of the invention

[0003] In view of this, the motor system for an aircraft hydraulic electric pump provided by the present invention can realize the function of converting electrical energy into mechanical energy and providing driving power to the hydraulic pump. It has an electromagnetic compatibility filter to effectively filter out interference signals in the frequency band exceeding the standard. It is the first low-voltage and high-current motor system in China and abroad that meets the requirements of DO160G.

[0004] A motor system for an aircraft hydraulic electric pump can be used to drive the hydraulic electric pump, comprising a bracket, a control box and a brushless DC motor mounted on the bracket, wherein the input end of the brushless DC motor is connected to the input end of the hydraulic electric pump, the control box and the brushless DC motor are electrically connected via a cable, and the brushless DC motor comprises a stator assembly, wherein the stator assembly is three-phase wound in a parallel centralized manner, and the wires of the three-phase winding are directly led out so as to shorten the size of the stator winding end and adapt to the supply of large current.

[0005] Beneficial Effects

[0006] The stator assembly is three-phase wound in parallel and concentrated mode. The three-phase winding wires are directly led out to shorten the size of the stator winding end, which not only improves the integration of the motor, but also can adapt to the supply of large currents and efficiently convert electrical energy into mechanical energy, providing driving power for the hydraulic pump. It has an electromagnetic compatibility filter to effectively filter out interference signals in the out-of-standard frequency band. It is the first low-voltage and high-current motor system in China and abroad that meets the requirements of DO160G. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0008] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0009] Figure 2 is a front cross-sectional view of the brushless DC motor structure of the present invention;

[0010] Figure 3 This is a cross-sectional view of the brushless DC motor structure test of the present invention

[0011] Figure 4 Schematic diagram of the control box of the present invention

[0012] Figure 5 is a schematic diagram of the arrangement of stator slots of the present invention, wherein:

[0013] 1. Support; 2. Control box; 3. Cable assembly; 4. Brushless DC motor; 5. Shell; 6. Box; 7. Filter assembly; 8. Support capacitor; 9. Control board; 10. Drive board; 11. Protective cover; 12. Front cover; 13. Front bearing; 14. Stator slot; 15. Rotor assembly; 16. Filter; 17. Rear cover; 18. Rear bearing; 19. Rotary transformer; 20. Fan; 21. Cover; 22. Terminal. DETAILED DESCRIPTION

[0014] The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.

[0015] The following describes the embodiments of the present disclosure through specific examples, and those skilled in the art can easily understand other advantages and effects of the present disclosure from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all of the embodiments. The present disclosure can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present disclosure. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present disclosure.

[0016] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present disclosure, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0017] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present disclosure, and only show the components related to the present disclosure rather than being drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout type may also be more complicated.

[0018] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, one skilled in the art will appreciate that aspects may be practiced without these specific details.

[0019] like Figures 1 to 5 The motor system for an aircraft hydraulic electric pump is used for driving the hydraulic electric pump, comprising a bracket, a control box 2 and a brushless DC motor 4 mounted on the bracket, wherein the input end of the brushless DC motor 4 is connected to the input end of the hydraulic electric pump, the control box 2 and the brushless DC motor 4 are electrically connected via a cable, and the brushless DC motor 4 comprises a stator assembly, wherein the stator assembly is three-phase wound in parallel and concentrated manner, and the wires of the three-phase winding are directly led out to shorten the size of the stator winding end, and can adapt to the supply of large current, meeting the requirements of DO160G for low voltage and large current.

[0020] As a specific implementation method provided in this case, the stator assembly includes a stator core, which is mounted on the inner annular surface of the housing 5, and a terminal 22 is arranged on the outer annular surface of the housing 5. Radial heat dissipation ribs are arranged at intervals on the outer circumferential surface of the housing 5 to increase the heat dissipation area, wherein:

[0021] The stator core is provided with stator slots at intervals in the circumferential direction, such as Figure 5As shown, the stator winding is wound in the stator slot in a parallel and concentrated manner to form a three-phase winding. The stator slot is a through slot and is concentrically arranged along the axial direction of the stator core. The lead-out wire of the three-phase winding is welded to the terminal 22 through a busbar. The busbar, for example, adopts a T2 pure copper busbar with a cross-sectional size of 20×3 to reduce the current density and reduce the cable transmission loss. The size of the stator slots is the same and they are concentric stator slots, that is, the distance from the center of the stator core to each stator slot is the same. For a winding current of nearly 300A at a low voltage DC28V, a distributed integer slot electronic winding is generally used in the traditional way. The size of the stator winding end is large, resulting in a large motor volume and weight, and the internal space utilization rate is low, the integration is low, and the integration of aviation airborne equipment is seriously affected, and the maintenance and modification costs are high. The stator winding is wound in the stator slot in a parallel and concentrated manner to form a three-phase winding, which can meet the large current transmission and reduce the motor volume, reduce the motor weight, and improve the internal space utilization of the motor.

[0022] Furthermore, the stator assembly also includes a stator end piece, the stator end face is installed on the axial end face of the stator core, and is used for insulation between the end of the three-phase winding and the stator core. The stator end face is made of epoxy glass cloth laminate, the sub-winding adopts QY-1 / 220 enameled wire, and the impregnating paint is polyester modified silicone impregnating paint; the shell is ZL101 cast aluminum alloy, the heat treatment measure is T5, the surface treatment measure is sulfuric acid anodizing, and the exposed surface is sprayed with QH-15 primer and QFS-15 topcoat in turn for protection. The sub-core is made of stator punchings stacked and welded, and the stator punching material is 35WW360 cold-rolled electrical steel strip.

[0023] The housing 5 further includes a front end cover 12 and a rear end cover 17. The front end cover 12 is arranged adjacent to the hydraulic electric pump. The inner end surfaces of the front end cover 12 and the rear end cover 17 are respectively provided with a front bearing 13 and a rear bearing 18. The bearings and the rear bearing 18 are used for assembling the main shaft. One end of the main shaft extends out of the front end cover 12 and is connected to the input end of the hydraulic electric pump. The other end of the main shaft extends out of the rear end cover 17 and leaves an extended section. The extended section is installed with a fan 20. The fan 20 cools the motor. Specifically,

[0024] The fan 20 is covered by a casing 6, which is connected to the housing 5, and the terminal 22 is arranged on the top surface of the casing 6, and a protective cover 11 is arranged on the side surface of the casing 6 in the width direction for insulating the terminal 22, and the casing 6 is provided with a cover plate 21;

[0025] A filter 16 is provided on the rear end cover 17 to filter impurities in the air;

[0026] A rotor assembly 15 is mounted on the main shaft, and the rotor assembly 15 can rotate in the stator core;

[0027] A rotary transformer 19 is installed on the main shaft and adjacent to the fan 20 . The rotary transformer 19 is in communication connection with the control box 2 for feeding back the polarity position of the rotor assembly 15 .

[0028] The fan 20 is used for ventilation and cooling of the motor. The material is ZL101 cast aluminum alloy and is heat-treated. The surface treatment measure is sulfuric acid anodizing. The exposed surface is sprayed with QH-15 primer and QFS-15 topcoat in sequence.

[0029] As a specific implementation method provided in this case, the control box 2 is provided with an electrically connected filter component 7 and a capacitor, and the terminal 22 is electrically connected to the filter component 7 and the capacitor in sequence through a cable, which is used for filtering, lightning protection, reducing signal transmission delay, and commutation power supply of the drive circuit. Specifically, the control box 2 is provided with a control board 9 and a drive board 10, and the control board 9 and the drive board 10 are electrically connected to the capacitor respectively, wherein,

[0030] The control board 9 is used for logic judgment of external input control signals and input of spindle speed signals;

[0031] The drive board 10 is used for orderly switching on and off of the three-phase windings, and controls the brushless DC motor to convert electrical energy into mechanical energy and output power to the hydraulic pump.

[0032] The working principle of the present invention is: when the aircraft hydraulic electric pump motor system is working, the DC 28V DC power supply passes through the built-in filter component 7 of the control box 2 and supplies power to the drive board 10 and the control board 9. The control board 9 calculates the motor control instruction (PWM) according to the control signal instruction of the control box 2 and the feedback signal of the rotary transformer 19. The drive board 10 receives the control instruction and outputs a three-phase voltage to the brushless DC motor 4 to drive the brushless DC motor 4 to work. At the same time, the control board 9 outputs the speed signal of the brushless DC motor 4 by calculating the signal of the rotary transformer 19. Specifically,

[0033] Start the motor manually, and keep the rated speed at 5150r / min at a DC voltage of 25V. The motor rotates clockwise when facing the direction of the motor drive shaft.

[0034] Start the motor manually, and keep the rated speed at 5150r / min at a DC voltage of 28V. The motor rotates clockwise when facing the direction of the motor drive shaft.

[0035] Start the motor manually, and keep the rated speed at 5150r / min at a DC voltage of 30.8V. The motor rotates clockwise when facing the direction of the motor drive shaft.

[0036] When the motor is started manually, the input voltage increases to 40V / DC, the output speed decreases, and the motor stops for overvoltage protection. When the motor is started manually, the input voltage drops to 20V / DC, the output speed decreases, and the motor stops for undervoltage protection.

[0037] The above is only a specific implementation of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present disclosure should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. A motor system for an aircraft hydraulic electric pump, which can be used to drive the hydraulic electric pump, characterized in that: It includes a bracket, a control box and a brushless DC motor installed on the bracket, the input end of the brushless DC motor is connected to the input end of the hydraulic electric pump, the control box is electrically connected to the brushless DC motor through a cable, and the brushless DC motor includes a stator assembly, the stator assembly is three-phase wound in parallel and concentrated manner, the wires of the three-phase winding are directly led out to shorten the size of the stator winding end and can adapt to the supply of large current.

2. The motor system for an aircraft hydraulic electric pump according to claim 1, characterized in that: The stator assembly includes a stator core, which is mounted on the inner ring surface of the housing, and a terminal is arranged on the outer ring surface of the housing, wherein: The stator core is provided with stator slots at intervals in the circumferential direction. The stator winding is wound in the stator slots in a parallel and concentrated manner to form a three-phase winding. The lead wires of the three-phase winding are welded to the terminal through a busbar.

3. The motor system for an aircraft hydraulic electric pump according to claim 2, characterized in that: The stator assembly also includes a stator end piece, the stator end face is mounted on the end face of the stator core, and is used for insulation between the end of the three-phase winding and the stator core, and the stator end face is made of epoxy glass cloth laminate; The stator winding adopts QY-1 / 220 enameled wire, and the impregnating varnish is polyester modified silicone impregnating varnish.

4. The motor system for an aircraft hydraulic electric pump according to claim 3, characterized in that: The shell material is ZL101 cast aluminum alloy, the heat treatment measure is T5, the surface treatment measure is sulfuric acid anodizing, and the exposed surface is sprayed with QH-15 primer and QFS-15 topcoat in sequence for protection; The stator core is formed by laminating and welding stator punching sheets, and the material of the stator punching sheets is 35WW360 cold-rolled electrical steel strip.

5. The motor system for an aircraft hydraulic electric pump according to claim 4, characterized in that: The shell includes a front end cover and a rear end cover, the front end cover is arranged adjacent to the hydraulic electric pump, the inner end surfaces of the front end cover and the rear end cover are respectively provided with a front bearing and a rear bearing, the bearings and the rear bearing are used for the assembly of the main shaft, and one end of the main shaft extends out of the front end cover and is connected to the input end of the hydraulic electric pump, and the other end of the main shaft extends out of the rear end cover and leaves an extended section, and the extended section is equipped with a fan.

6. The motor system for an aircraft hydraulic electric pump according to claim 5, characterized in that: The fan is installed in a box body, one end of the box body has a hole and is connected to the housing, the terminal is arranged on the top surface of the box body, and a protective cover is arranged on the side surface of the box body in the width direction for insulating and protecting the terminal; The rear end cover is provided with a filter screen for filtering impurities in the air; A rotor assembly is mounted on the main shaft, and the rotor assembly can rotate in the stator core; A rotary transformer is installed on the main shaft and adjacent to the fan. The rotary transformer is communicatively connected with the control box and is used to feed back the polarity position of the rotor assembly.

7. The motor system for an aircraft hydraulic electric pump according to claim 6, characterized in that: The fan is used for ventilation and cooling of the motor. The material is ZL101 cast aluminum alloy and is heat-treated. The surface treatment measure is sulfuric acid anodizing. The exposed surface is sprayed with QH-15 primer and QFS-15 topcoat in sequence.

8. The motor system for an aircraft hydraulic electric pump according to claim 6, characterized in that: The control box is provided with an electrically connected filter component and a capacitor, and the terminal is electrically connected to the filter component and the capacitor in sequence through a cable, and is used for filtering, lightning protection, reducing signal transmission delay, and commutation power supply of the drive circuit.

9. The motor system for an aircraft hydraulic electric pump according to claim 7, characterized in that: The control box is provided with a control board and a drive board, and the control board and the drive board are electrically connected to the capacitor respectively, wherein: The control board is used for logic judgment of external input control signals and input of spindle speed signals; The driving board is used for orderly switching on and off of the three-phase windings.

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