Aviation high-voltage direct-current power generation mechanism type variable output rectifying device

Abstract

The invention relates to the technical field of aviation generators, in particular to an aviation high-voltage direct-current power generation mechanism type variable output rectifying device which is composed of three sets of rectifier diodes, each set of rectifier diodes is formed by laminating two rectifier diodes, and after lamination, the rectifier diodes are fixed through screws and nuts. A wiring board is arranged between the two laminated rectifier diodes, a wiring lug and a positioning lug are arranged on the wiring board, the wiring lug is used for connecting three-phase alternating current, and a screw rod penetrates through the positioning lug and is used for circumferential positioning; the three groups of rectifier diodes are connected with the upper confluence plate and the lower confluence plate so as to output direct current outwards; an upper supporting plate and a lower supporting plate are respectively arranged on the outer sides of the upper confluence plate and the lower confluence plate, small holes are formed in the two confluence plates and the two supporting plates, and screw rods penetrate through the small holes and are matched with nuts, so that the overall fixation of the three groups of rectifier diodes is realized; by changing the shapes of the two confluence plates and the two supporting plates, the overall configuration of the whole output rectifying device can be changed.

Description

TECHNICAL FIELD

[0001] Embodiments of the present application relate to the technical field of aeronautical generator, in particular to a variable output rectifier device for aeronautical high-voltage direct current generator. BACKGROUND

[0002] Aeronautical high-voltage direct current generator is a power generation device specially designed for aerospace scenarios, which is used to generate high-voltage direct current. The aeronautical high-voltage direct current generator converts the three-phase or double three-phase (also known as six-phase) alternating current output by the main generator into direct current through the output rectifier, thereby providing power for the electrical equipment on the aircraft. The voltage of the high-voltage direct current generated by the aeronautical high-voltage direct current generator is generally 270V, and some can reach 540V.

[0003] Compared with traditional power supply systems, the aeronautical high-voltage direct current generator has the following advantages.

[0004] First, high power density. Under the same power, the power supply system based on the 270V aeronautical high-voltage direct current generator has smaller wire current. Higher voltage can reduce current under the same power, so thinner and lighter cables can be used, significantly reducing the weight of the aircraft and improving space utilization to some extent.

[0005] Second, power distribution simplification and efficiency improvement. The aeronautical high-voltage direct current generator integrates the rectifier device internally, so it can directly provide high-voltage direct current, eliminating the need for external rectifier devices in traditional power supply systems, reducing energy conversion losses, and reducing system complexity.

[0006] Third, strong compatibility. The aeronautical high-voltage direct current generator is more easily integrated with modern energy storage devices such as lithium batteries, high-power electrical equipment (such as electrically driven pumps and electric deicing systems), and future electric propulsion systems.

[0007] Fourth, high reliability. The aeronautical high-voltage direct current generator has good stability and anti-interference ability, and can work stably in complex aerospace environments, eliminating the need for constant speed transmission devices or variable frequency alternating current devices, reducing mechanical failure points, simplifying system structure, and facilitating redundancy design. In the case of small faults in some power modules, it can still work normally.

[0008] However, the inventors of the present application found that the rectifier device integrated in the aeronautical high-voltage direct current generator needs to stack six rectifier diodes on top of each other to form a rectifier, which requires a specific shape of mounting space and must be installed on the top of the aeronautical high-voltage direct current generator inside the housing, which severely restricts the overall size of the aeronautical high-voltage direct current generator. SUMMARY

[0009] In order to solve the above technical problems, the embodiment of the present application proposes an aviation high-voltage DC generator structure variable output rectifier device, the configuration and installation position of which can be flexibly adjusted according to the internal space of the aviation high-voltage DC generator, while meeting the miniaturization design, the conduction area after confluence is increased, and the reliability of the output rectifier device is improved, thereby improving the reliability of the aviation high-voltage DC generator.

[0010] In order to achieve the above-mentioned purpose, the embodiment of the present application proposes an aviation high-voltage DC generator structure variable output rectifier device, which is composed of three groups of rectifier diodes, each group of rectifier diodes is composed of a first rectifier diode and a second rectifier diode in series, and is fixed by a screw rod and a nut after being connected in series. A wiring board is arranged between the two rectifier diodes connected in series, and two lugs are arranged on the wiring board, which are respectively a wiring lug and a positioning lug. The wiring lug is used to connect a group of three-phase alternating current output by the generator, and the positioning lug is used to position the screw rod in the circumferential direction. The common polarity end of the three first rectifier diodes facing away from the wiring board is connected with a complete upper bus plate, and the common polarity end of the three second rectifier diodes facing away from the wiring board is connected with a complete lower bus plate, so as to output direct current and realize full-wave rectification. An upper support plate is arranged on the outer side of the upper bus plate, and a lower support plate is arranged on the outer side of the lower bus plate. Small holes are arranged at positions corresponding to the positioning lugs of the two bus plates and the two support plates, and the screw rod is arranged in the small holes and cooperates with the nuts on the outer sides of the two support plates to realize overall fixation of the three groups of rectifier diodes. By changing the shapes of the two bus plates and the two support plates, the overall configuration and size of the output rectifier device can be changed to adapt to the internal installation space of the aviation high-voltage DC generator.

[0011] In order to achieve the above-mentioned purpose, the embodiment of the present application further proposes an aviation high-voltage DC generator with single three-phase output, which is provided with an aviation high-voltage DC generator structure variable output rectifier device as described above.

[0012] In order to achieve the above-mentioned purpose, the embodiment of the present application further proposes an aviation high-voltage DC generator with double three-phase output, which is provided with two aviation high-voltage DC generator structure variable output rectifier devices as described above.

[0013] In order to achieve the above-mentioned purpose, the embodiment of the present application further proposes an aviation aircraft, which is provided with an aviation high-voltage DC generator with single three-phase output as described above, or an aviation high-voltage DC generator with double three-phase output as described above.

[0014] The application provides a variable output rectifier device for an aviation high-voltage direct-current generator, which comprises three groups of full-wave rectification diodes, two diodes in each group are stacked to realize variable distributed configuration, a wiring board is arranged between the two diodes in each group, the wiring board is provided with wiring lugs and positioning lugs, the wiring lugs are connected with three-phase alternating current output by the generator, and the positioning lugs are used for fixing and circumferential positioning, three groups of diodes output direct current through upper and lower bus bars, the upper and lower bus bars replace the connection mode of the switching bus bar in the traditional output rectifier device, the conductive area after bus connection is effectively increased, and some complex and high-cost connecting components are saved, the outer side of the upper bus bar is provided with an upper support plate, the outer side of the lower bus bar is provided with a lower support plate, small holes are formed in positions corresponding to the positioning lugs of the two bus bars and the two support plates, a screw rod is arranged in the small holes and matched with nuts on the outer sides of the two support plates, thereby realizing overall fixing of the three groups of diodes and ensuring the firmness and stability of the overall structure of the output rectifier device, and the shape of the two bus bars and the two support plates can be changed to change the overall configuration and size of the output rectifier device, so that the internal installation space of the aviation high-voltage direct-current generator can be flexibly adapted, and the design requirements of small size and light weight of the aviation high-voltage direct-current generator are well met.

[0015] Optionally, an insulating layer is arranged between the screw rod and the upper bus bar, the lower bus bar, the upper support plate and the lower support plate, between the upper bus bar and the upper support plate, and between the lower bus bar and the lower support plate, so as to realize electrical isolation.

[0016] Optionally, the insulating layer is made of a non-metallic material.

[0017] Optionally, the six diodes in the three groups are all ceramic insulating gold-sealed structures.

[0018] Optionally, the upper bus bar, the lower bus bar and the wiring board are made of metallic conductive materials.

[0019] Optionally, the upper support plate and the lower support plate are structural components.

[0020] Optionally, in the case that the aviation high-voltage direct-current generator is a double three-phase output aviation high-voltage direct-current generator, two output rectifier devices are required to be installed oppositely, and butt lugs are further arranged on the wiring boards of the two groups of diodes at the edges of the two output rectifier devices, a screw rod is arranged in the butt lugs and matched with nuts, so as to realize connection of the two output rectifier devices. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to make the technical solutions in the embodiments of the present application or the related art clearer, the accompanying drawings needed in the description of the embodiments of the present application or the related art will be briefly introduced. Obviously, the following drawings are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained without creative effort based on these drawings. The drawings described herein are only used to explain the present application and should not be used to limit the present application.

[0022] Figure 1 is a structural schematic diagram of an aviation high-voltage DC generator shape-variable output rectifier device provided in an embodiment of the present application; Figure 2 is a schematic diagram of the connection of two output rectifier devices provided in an embodiment of the present application. DETAILED DESCRIPTION

[0023] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the embodiments of the present application will be described in detail below with reference to the drawings. Those skilled in the art can understand that in the embodiments of the present application, many technical details are proposed in order to make the readers better understand. However, the technical solutions claimed by the present application can be implemented without these technical details and various changes and modifications based on the following embodiments. The following embodiments are classified for the convenience of description, and should not constitute any limitation on the specific implementation of the present application. The following embodiments can be combined and referenced with each other without contradiction.

[0024] In order to solve the technical problem that the traditional rectifier requiring a specific shape of installation space seriously restricts the overall size of the aviation high-voltage DC generator, an embodiment of the present application proposes an aviation high-voltage DC generator shape-variable output rectifier device. The implementation details of the aviation high-voltage DC generator shape-variable output rectifier device proposed in the embodiment will be described in detail below. The following content is only provided for the convenience of understanding and is not necessary for implementing the present solution.

[0025] The specific structure of the aviation high-voltage DC generator shape-variable output rectifier device proposed in the embodiment can be as shown in Figure 1 The aviation high-voltage DC generator shape-variable output rectifier device proposed in the embodiment is composed of three groups of rectifier diodes. Each group of rectifier diodes is composed of a first rectifier diode 11 and a second rectifier diode 12 stacked together. The two stacked rectifier diodes are fixed by a screw rod 41 and a nut 42. A wiring board 30 is arranged between the two stacked rectifier diodes. The wiring board 30 is provided with two lugs, namely a wiring lug 31 and a positioning lug 32. The wiring lug 31 is used to connect a group of three-phase alternating current output by the generator. The positioning lug 32 passes through the screw rod 41 and is used for circumferential positioning.

[0026] The common polarity ends of the three first rectifier diodes 11 facing away from the terminal block 30 are all connected to a complete upper bus bar 21 (i.e., the three first rectifier diodes 11 share one upper bus bar 21), and the common polarity ends of the three second rectifier diodes 12 facing away from the terminal block 30 are all connected to a complete lower bus bar 22 (i.e., the three second rectifier diodes 12 share one lower bus bar 22), so as to output direct current through the upper bus bar 21 and the lower bus bar 22, realizing full-wave rectification.

[0027] The outer side (the side facing away from the terminal block 30) of the upper bus bar 21 is provided with an upper support plate 51, and the outer side (the side facing away from the terminal block 30) of the lower bus bar 22 is provided with a lower support plate 52. Small holes are formed in positions corresponding to the positioning lugs 32 of the two bus bars and the two support plates, and a screw rod 41 is passed through the small holes and cooperates with a nut 42 on the outer side of the two support plates, so as to realize overall fixation of the three groups of rectifier diodes.

[0028] The shapes and sizes of the upper bus bar 21, the lower bus bar 22, the upper support plate 51 and the lower support plate 52 can all be adjusted based on actual needs. By changing the shapes of the two bus bars and the two support plates, the overall configuration and size of the entire output rectifier device can be changed, so as to flexibly adapt to the diversified internal installation space of the aviation high-voltage direct-current generator.

[0029] The components of the output rectifier device will be described in detail below.

[0030] The six rectifier diodes of the three groups of rectifier diodes of the output rectifier device all adopt a ceramic insulation gold-sealing structure. The ceramic insulation gold-sealing structure is composed of a ceramic insulator, a metal part, a lead wire and a sealing material. The ceramic insulation gold-sealing structure has good insulation performance, high mechanical strength, excellent heat dissipation performance, good sealing performance and flexible designability, and is very suitable for application in rectifier diodes.

[0031] The materials of the upper bus bar 21, the lower bus bar 22 and the terminal block 30 are all metal conductive materials, which can include but are not limited to copper, brass, silver, gold and aluminum.

[0032] The upper support plate 51 and the lower support plate 52 are both structural parts, and the materials of the structural parts that can be selected include but are not limited to steel structural parts and titanium alloy structural parts.

[0033] Insulating layers 60 are arranged between the screw rod 41 and the upper bus bar 21, the lower bus bar 22, the upper support plate 51 and the lower support plate 52, between the upper bus bar 21 and the upper support plate 51, and between the lower bus bar 22 and the lower support plate 52, for realizing electrical isolation.

[0034] The material of the insulation layer 60 is a non-metallic material, and the non-metallic material that can be selected includes but is not limited to polyvinyl chloride, polyethylene, cross-linked polyethylene, polytetrafluoroethylene, natural rubber, nitrile rubber, silicone rubber, and impregnated fiber products.

[0035] In one example, in the case of an aviation high-voltage DC generator with double three-phase output, two output rectifier devices are required to achieve full-wave rectification of two sets of three-phase alternating current. Figure 2 As shown in the figure, the two sets of rectifier diodes on the edge of the two output rectifier devices are provided with a butt lug 33, and the butt lug 33 is penetrated by a screw rod 41 and cooperates with the nuts 42 on the outer side of the two support plates to realize the connection of the two output rectifier devices. Figure 2 The two support plates in the figure protrude inward and are perforated, and are installed at the rear of the motor by screws. The two output rectifier devices are distributed in the circumferential direction, and the motor structure does not need to be provided with a special cavity, only the axial length of the motor needs to be appropriately lengthened.

[0036] In one example, the installation position of the output rectifier device includes but is not limited to the upper part inside the shell of the aviation high-voltage DC generator, and multiple output rectifier devices can be arranged in a ring structure around the rotating shaft of the aviation high-voltage DC generator and cooled by oil injection.

[0037] The aviation high-voltage DC generator structure variable output rectifier device provided in the embodiment has three groups of rectifier diodes, and the two rectifier diodes in the same group are stacked to achieve a variable distributed configuration. A wiring lug and a positioning lug are arranged on the wiring plate between the two diodes in the same group, the wiring lug realizes the connection of the rectifier diode and the three-phase alternating current output by the generator, and the positioning lug realizes the fixation and circumferential positioning. The three groups of rectifier diodes output direct current through the upper bus plate and the lower bus plate, realizing full-wave rectification. The upper bus plate is provided with an upper support plate on the outer side, and the lower bus plate is provided with a lower support plate on the outer side. Small holes are formed in the positions corresponding to the positioning lugs of the two bus plates and the two support plates, and a screw rod is penetrated in the small holes and cooperates with the nuts on the outer side of the two support plates to realize the overall fixation of the three groups of rectifier diodes, ensuring the firmness and stability of the overall structure of the output rectifier device. By changing the shapes of the two bus plates and the two support plates, the overall configuration and size of the output rectifier device can be changed, so as to flexibly adapt to the internal installation space of the aviation high-voltage DC generator, thereby meeting the design requirements of small size and light weight of the aviation high-voltage DC generator.

[0038] It is worth mentioning that the modules involved in the embodiments are logical units, which can be a physical unit, a part of a physical unit, or a combination of multiple physical units in actual application. In addition, in order to highlight the innovative part of the present application, the units not closely related to solving the technical problems proposed in the present application are not introduced in the embodiments, but this does not mean that there are no other units in the embodiments.

[0039] Another embodiment of the present application provides a single three-phase output aviation high-voltage DC generator, which is provided with an aviation high-voltage DC generator structure variable output rectifier device as described in the above output rectifier device embodiment.

[0040] Another embodiment of the present application provides a double three-phase output aviation high-voltage DC generator, which is provided with two aviation high-voltage DC generator structure variable output rectifier devices as described in the above output rectifier device embodiment.

[0041] Another embodiment of the present application provides an aviation aircraft, which is provided with a single three-phase output aviation high-voltage DC generator as described in the above single three-phase output aviation high-voltage DC generator embodiment, or a double three-phase output aviation high-voltage DC generator as described in the above double three-phase output aviation high-voltage DC generator embodiment.

[0042] Those skilled in the art can understand that each of the above embodiments is a specific embodiment for implementing the present application, and various changes can be made in form and details in actual application without departing from the spirit and scope of the present application. For those skilled in the art, without departing from the principles of the present application, a number of improvements and refinements can also be made, which are also considered within the protection scope of the present application.

Claims

1. An aircraft high voltage direct current generator system variable output rectifier device, characterized by, Each of the three groups of rectifier diodes is composed of a first rectifier diode (11) and a second rectifier diode (12) stacked together, and fixed by a screw rod (41) and a nut (42). A wiring board (30) is arranged between the two stacked rectifier diodes, and two lugs are arranged on the wiring board (30), namely a wiring lug (31) and a positioning lug (32). The wiring lug (31) is used to connect a group of three-phase alternating current output by the generator, and the positioning lug (32) is used to pass through the screw rod (41) for circumferential positioning. The common polarity end of the three first rectifier diodes (11) facing away from the wiring board (30) is connected to a complete upper bus plate (21), and the common polarity end of the three second rectifier diodes (12) facing away from the wiring board (30) is connected to a complete lower bus plate (22), so as to output direct current and realize full-wave rectification. An upper support plate (51) is arranged on the outer side of the upper bus plate (21), and a lower support plate (52) is arranged on the outer side of the lower bus plate (22). Small holes are arranged at positions corresponding to the positioning lug (32) of the two bus plates and the two support plates, and the screw rod (41) passes through the small holes and cooperates with the nuts (42) on the outer sides of the two support plates to realize overall fixation of the three groups of rectifier diodes. By changing the shapes of the two bus plates and the two support plates, the overall configuration and size of the output rectifier device can be changed to adapt to the internal installation space of the aviation high-voltage DC generator.

2. The output rectifier of claim 1, wherein the output rectifier is a high voltage DC generator for an aircraft. Insulating layers (60) are arranged between the screw rod (41) and the upper bus plate (21), the lower bus plate (22), the upper support plate (51) and the lower support plate (52), between the upper bus plate (21) and the upper support plate (51), and between the lower bus plate (22) and the lower support plate (52), for electrical isolation.

3. The variable output rectifier of claim 2, wherein the controller is configured to: determine a first output voltage of the first output rectifier; determine a second output voltage of the second output rectifier; and select the first output rectifier or the second output rectifier based on the first output voltage and the second output voltage. The insulating layer (60) is made of non-metallic material.

4. The variable output rectifier of claim 1, wherein the controller is configured to: The six rectifier diodes of the three groups of rectifier diodes are all ceramic insulating gold-sealed structures.

5. The variable output rectifier of claim 1, wherein the controller is configured to: determine a first output voltage of the first output; determine a second output voltage of the second output; and determine the first output voltage and the second output voltage are within a predetermined range of each other. The upper bus plate (21), the lower bus plate (22) and the wiring board (30) are all made of metallic conductive material.

6. The variable output rectifier of claim 1, wherein The upper support plate (51) and the lower support plate (52) are both structural parts.

7. The variable output rectifier of claim 1 to 6, wherein, In the case of a double three-phase output aviation high-voltage DC generator, two output rectifier devices need to be installed relatively, and a butt lug (33) is further arranged on the wiring board (30) of the two groups of rectifier diodes at the edges of the two output rectifier devices. The butt lug (33) passes through the screw rod (41) and cooperates with the nut (42) to realize connection of the two output rectifier devices.

8. An aviation high-voltage DC generator with single three-phase output, characterized in that An aviation high-voltage DC generator with a variable output rectifier device as claimed in any one of claims 1 to 6 is provided.

9. A dual three-phase output aeronautical high-voltage DC generator, characterized in that, Two aviation high-voltage DC generators with a variable output rectifier device as claimed in claim 7 are provided.

10. An aircraft, characterized in that An aviation high-voltage DC generator with a single three-phase output as claimed in claim 8 is provided, or an aviation high-voltage DC generator with a double three-phase output as claimed in claim 9 is provided.

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