CN214852473U

CN214852473U - Water cooling structure of spaceflight generator controller

Info

Publication number: CN214852473U
Application number: CN202121147918.0U
Authority: CN
Inventors: 张文学; 孟嘉磊; 刘志立
Original assignee: Beijing Dianqing Technology Co ltd
Current assignee: Beijing Dianqing Technology Co ltd
Priority date: 2021-05-26
Filing date: 2021-05-26
Publication date: 2021-11-23
Anticipated expiration: 2031-05-26

Abstract

The utility model discloses a space flight plays generator controller water-cooling structure, including the controller casing, be equipped with the direct current passageway on the bottom a week lateral wall in the controller casing, be equipped with the partial pressure district on the one end lateral wall in the controller casing, the partial pressure internal fixation has the guide plate, equidistant a plurality of division boards that are fixed with on the a week lateral wall of partial pressure district, be fixed with a plurality of first radiating fin and second radiating fin between the division board, be connected with import pipe and outlet pipe on one side inner wall of controller casing. The utility model discloses not only can guarantee that water-cooling structure is inside to have abundant radiating effect, the partial pressure pipeline pressure loss scope widen moreover, provides bigger pressure loss, has realized that cooling structure plays generator control ware external pressure balance, the effect of inside partial pressure.

Description

Water cooling structure of spaceflight generator controller

Technical Field

The utility model relates to a play generator control ware technical field, especially relate to a spaceflight plays generator control ware water-cooling structure.

Background

In the working process of the aviation motor, the possibility of damaging the internal structure can be caused by the fact that the water pressure of the aerospace cooling structure is too high when the aviation motor enters the controller, and therefore a cooling liquid inlet of the generator controller and an internal design pressure dividing structure are arranged.

Theories and traditional partial pressure propose series partial pressure and installation relief pressure valve, although the velocity of flow of series partial pressure is even among these two kinds of partial pressure modes, the heat extraction is even, but radiating effect is not strong, within the limited 30% of pressure loss, it is higher to hardly reach, to aerospace's cooling structure, it is more difficult to require that the pressure loss to reach about 90% realization, the mode of import installation relief pressure valve, because the installation requirement, too far away with the export distance, and to the scope volume that pressure is big can restrict, for this reason, we have proposed a space plays generator controller water-cooling structure and have solved above-mentioned problem.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the defects existing in the prior art and providing a water cooling structure of a spaceflight generator controller.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model provides a space flight generator controller water-cooling structure, includes the controller casing, be equipped with the direct current passageway on bottom a week lateral wall in the controller casing, be equipped with the partial pressure district on the one end lateral wall in the controller casing, the partial pressure internal fixation has the guide plate, equidistant a plurality of division boards that are fixed with on a week lateral wall of partial pressure district, be fixed with a plurality of first radiating fin and second radiating fin between the division board, be connected with import pipe and outlet pipe on one side inner wall of controller casing, the one side of import pipe and outlet pipe all is connected with direct current passageway connecting pipe and curved flow passageway connecting pipe, the one end of direct current passageway connecting pipe is connected on the direct current passageway, the one end of curved flow passageway connecting pipe runs through the lateral wall of controller casing and extends to in the partial pressure district.

Preferably, a plurality of interfaces are connected to one side of the controller housing.

Preferably, the second heat dissipation fins are distributed at one end of the partition plate.

Preferably, the number of the first heat dissipation fins is 100 and 160, and the number of the second heat dissipation fins is 15-20.

Preferably, the first heat dissipation fin and the second heat dissipation fin are made of alloy materials.

Preferably, a plurality of mounting holes are formed in the side wall of the controller shell at equal intervals.

Compared with the prior art, the utility model discloses has following benefit:

1. the whole area achieves a sufficient heat dissipation effect through the pressure division structure of the bent pipe type pipeline and the heat dissipation fins, which is mainly used as the pressure division area;

2. through the structure of newly-increased direct current passageway and the parallelly connected water course partial pressure of return bend structure, for the water-cooling structure pressure loss range is wide to provide bigger pressure loss, become the unanimous cooling structure of import and outlet pressure.

To sum up, the utility model discloses have and to guarantee that water-cooling structure is inside to have abundant radiating effect, the partial pressure pipeline pressure loss scope widen moreover provides bigger pressure loss, has realized that cooling structure plays generator control ware external pressure balance, the effect of inside partial pressure.

Drawings

Fig. 1 is a schematic structural diagram of a water cooling structure of a space starter generator controller according to the present invention;

FIG. 2 is a schematic view of an inlet pipe structure of a water cooling structure of a spaceflight generator controller provided by the utility model;

fig. 3 is the utility model provides an outlet pipe schematic structure of space crane generator controller water-cooling structure.

In the figure: the device comprises an inlet pipe 1, an outlet pipe 2, a direct current channel 3, a separation plate 4, a first radiating fin 5, a connector 6, a guide plate 7, a through hole 8, a controller shell 9, a second radiating fin 10, a direct current channel connecting pipe 11 and a bent current channel connecting pipe 12.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

Referring to fig. 1-3, a space starter controller water-cooling structure comprises a controller shell 9, a direct current channel 3 is arranged on the bottom of the controller shell 9 on the side wall of the periphery, a pressure division area is arranged on the side wall of one end of the controller shell 9, a guide plate 7 is fixed in the pressure division area, the guide plate 7 divides the water flow in the pressure division area, a plurality of partition plates 4 are fixed on the side wall of the periphery of the pressure division area at equal intervals, and the partition plates 4 divide the pressure division area into a curved flow channel of a curved path structure, so that the large-pressure-difference pressure division in the controller is realized.

The utility model discloses in, be fixed with a plurality of first radiating fin 5 and second radiating fin 10 between division board 4, two kinds of radiating fin equidistant distribution are in the partial pressure district, radiating effect has been increased, be connected with import pipe 1 and outlet pipe 2 on one side inner wall of controller casing 9, one side of import pipe 1 and outlet pipe 2 is connected on direct current channel 3, one side of controller casing 9 is fixed with a plurality of interfaces 6, be fixed with a plurality of first radiating fin 5 and second radiating fin 10 between division board 4, two kinds of radiating fin equidistant distribution are in the partial pressure district, radiating effect has been increased.

The utility model discloses in, be connected with import pipe 1 and outlet pipe 2 on one side inner wall of controller casing 9, import pipe 1 and outlet pipe 2's one side all is connected with direct current channel connecting pipe 11 and curved flow channel connecting pipe 12, direct current channel connecting pipe 11's one end is connected on direct current channel 3, the one end of curved flow channel connecting pipe 12 runs through controller casing 9's lateral wall and extends to in the partial pressure area, direct current channel 3 becomes parallel water course partial pressure system with the partial pressure area, return bend partial pressure area is with aviation cooling system's pipeline pressure PN20, the partial pressure becomes PN2, and with its pressure loss control to 90%, bigger pressure loss has been realized.

The utility model discloses in, second fin 10 distributes in the one end of division board 4, first radiating fin 5's quantity is 100 and gives 160, second radiating fin 10's quantity is 15-20, these radiating fin make rivers can obtain abundant radiating effect when the partial pressure, can design according to the pressure loss scope, first radiating fin 5 and second radiating fin 10 are made by alloy material, equidistant a plurality of mounting holes 8 that are equipped with on the a week lateral wall of controller casing 9, through a plurality of mounting holes 8 with the steady fixing in the controller of partial pressure district and DC channel 3.

The utility model discloses in, under machine controller's control, rivers get into in the equipment through import pipe 1, rivers get into direct current channel 3 through direct current channel connecting pipe 11 on the import pipe 1, rivers get into the partial pressure district through curved flow channel connecting pipe 12 on the import pipe 1, direct current channel 3 and partial pressure district become parallel structure, equidistant a plurality of division boards 4 of distributing in the partial pressure district, first radiating fin 5 and second radiating fin 10, guarantee that cooling system plays generator control ware inside and outside pressure balance, and abundant heat dissipation, final rivers are followed direct current channel connecting pipe 11 on the outlet pipe 2 through direct current channel 3 and are drawn out, rivers are drawn out through curved flow channel connecting pipe 12 on the outlet pipe 2, it is the same to keep generator control structure water course pressure, simultaneously fully dispel the heat.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a space crane generator controller water-cooling structure, includes controller casing (9), its characterized in that: a direct current channel (3) is arranged on the side wall of the bottom and the periphery in the controller shell (9), a partial pressure area is arranged on the side wall of one end in the controller shell (9), a guide plate (7) is fixed in the partial pressure area, a plurality of partition plates (4) are fixed on the side wall of the circumference of the partial pressure zone at equal intervals, a plurality of first radiating fins (5) and second radiating fins (10) are fixed between the partition plates (4), an inlet pipe (1) and an outlet pipe (2) are connected on the inner wall of one side of the controller shell (9), one side of the inlet pipe (1) and one side of the outlet pipe (2) are both connected with a direct current channel connecting pipe (11) and a bent current channel connecting pipe (12), one end of the direct current channel connecting pipe (11) is connected to the direct current channel (3), one end of the bent flow channel connecting pipe (12) penetrates through the side wall of the controller shell (9) and extends into the partial pressure area.

2. The aerospace starter generator controller water-cooling structure of claim 1, wherein: one side of the controller shell (9) is connected with a plurality of interfaces (6).

3. The aerospace starter generator controller water-cooling structure of claim 1, wherein: the second radiating fins (10) are distributed at one end of the partition plate (4).

4. The aerospace starter generator controller water-cooling structure of claim 1, wherein: the number of the first heat dissipation fins (5) is 100 and 160, and the number of the second heat dissipation fins (10) is 15-20.

5. The aerospace starter generator controller water-cooling structure of claim 1, wherein: the first radiating fins (5) and the second radiating fins (10) are both made of alloy materials.

6. The aerospace starter generator controller water-cooling structure of claim 1, wherein: a plurality of mounting holes (8) are formed in the side wall of the periphery of the controller shell (9) at equal intervals.