CN218123646U

CN218123646U - Battery energy control device for stratospheric aircraft

Info

Publication number: CN218123646U
Application number: CN202123320389.2U
Authority: CN
Inventors: 赵宗哲; 颜湘武; 赵丽; 李鹏; 范云飞; 王晓明
Original assignee: Yuneng Electrical Co Ltd
Current assignee: Yuneng Electrical Co Ltd
Priority date: 2021-12-27
Filing date: 2021-12-27
Publication date: 2022-12-23
Anticipated expiration: 2031-12-27

Abstract

The utility model relates to a battery energy technical field especially relates to a stratosphere is battery energy controlling means for aircraft, including two fixed columns and battery controller, two lower extreme fixed mounting of fixed column have the base, the vertical circular recess one of having seted up in two upper ends of fixed column, the vertical rectangular channel two of having seted up of a circular recess lower extreme that two fixed columns were seted up, rectangular channel one has transversely been seted up in the middle of the rectangular channel two that two fixed columns were seted up. The utility model discloses a the arm-tie of front end is connected with the quick buckle of buckle to and the quick buckle of rear end buckle board and buckle is connected, has accomplished the efficiency of quick dismantlement, makes the staff can save time when dismantling, reduces the time cost, improves work efficiency, drives pull rod two through pull rod three, and pull rod two drives two arm-ties and two buckle boards again and removes, only needs to stimulate can dismantle fast once, simple structure, and the operation is quick, and the practicality is strong.

Description

Battery energy control device for stratospheric aircraft

Technical Field

The application relates to the technical field of battery energy, in particular to a battery energy control device for an stratospheric aircraft.

Background

A power control board is a device that provides current voltage to an electronic device, also known as a power controller, and provides control of the current required by all components in the power supply. The power of the power supply, and whether the current and the voltage are stable or not are directly influenced by the power control board.

As disclosed in the chinese patent: power supply controller, publication No.: CN210627129U is provided with a plurality of communication protocol interaction modules in the interior, and can be adapted to a plurality of intelligent electrical appliances, so that centralized management, remote control and monitoring of the intelligent electrical appliances are realized, the working conditions of the intelligent electrical appliances are mastered in real time, and the power utilization safety of the electrical appliances is ensured.

However, the existing power supply controller is very troublesome to disassemble, and the disassembly can be completed only by disassembling a plurality of screws, so that the time and the labor are consumed, and the working efficiency of maintainers is reduced.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a battery energy controlling means for stratospheric aircraft to solve the problem that proposes among the above-mentioned background art.

The embodiment of the application adopts the following technical scheme:

the battery energy control device for the stratospheric aircraft comprises a second fixing column and a battery controller, wherein a base is fixedly mounted at the lower end of the second fixing column, a second rectangular groove is vertically formed in the lower end of the second fixing column, a first rectangular groove is transversely formed in the middle of the second rectangular groove formed in the second fixing column, a second spring is fixedly mounted at the lower end of the second rectangular groove formed in the second fixing column, a first spring is fixedly mounted at one side end of the second rectangular groove formed in the second fixing column, and a pull plate is fixedly mounted at one side end of the first spring and slidably mounted in the first rectangular groove.

Preferably, the front end of the pulling plate is vertically provided with a first clamping groove in a penetrating mode, the side end of the pulling plate is fixedly provided with a second pulling rod, the first pulling rod is fixedly arranged on the circumferential surface of the second pulling rod and is located away from the pulling plate, a clamping plate is fixedly arranged on one side end of the pulling rod, and the clamping plate is vertically provided with a second clamping groove in a penetrating mode.

Preferably, the buckle plate is transversely provided with a third fixing column in a sliding manner, the upper end of the third fixing column is vertically penetrated and provided with a second circular groove, the lower end of the second circular groove provided in the third fixing column is vertically penetrated and provided with a fifth rectangular groove, the middle of the fifth rectangular groove provided in the third fixing column is transversely penetrated and provided with a fourth rectangular groove, and the four side ends of the fourth rectangular groove provided in the third fixing column are penetrated and provided with sliding grooves and are slidably mounted with the first pull rod.

Preferably, a spring four is fixedly mounted at four sides of the rectangular groove formed in the fixing column three and is fixedly mounted with the side end of the buckling plate, and a spring three is fixedly mounted at the lower end of the rectangular groove five formed in the fixing column three.

Preferably, a third pull rod is fixedly mounted in the middle of the second pull rod, and a fixed block is rotatably mounted in the third pull rod in a penetrating manner and fixedly mounted on the upper end of the base.

Preferably, the four corners of the lower end of the battery controller are fixedly provided with a first fixing column, the lower end of the first fixing column is fixedly provided with a buckle, the two buckles located at the front end are movably sleeved with the pull plate through a second rectangular groove formed in the second fixing column, and the two buckles located at the rear end are movably sleeved with the buckle plate through a fifth rectangular groove formed in the third fixing column.

The embodiment of the application adopts at least one technical scheme which can achieve the following beneficial effects:

firstly, this battery energy controlling means for stratospheric aircraft is connected through the arm-tie of front end and the quick buckle of buckle to and the quick buckle of rear end buckle board and buckle is connected, has accomplished the efficiency of quick dismantlement, makes the staff can save time when dismantling, reduces time cost, improves work efficiency.

Secondly, this battery energy controlling means for stratospheric aircraft drives pull rod two through pull rod three, and pull rod two drives two arm-tie and two buckle boards again and removes, only needs to stimulate can dismantle fast once, simple structure, and the operation is quick, and the practicality is strong.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:

fig. 1 is a schematic overall structure diagram of the present invention;

FIG. 2 is a schematic view of the base of the present invention;

FIG. 3 is a schematic structural view of a second pull rod of the present invention;

fig. 4 is a schematic structural view of the pulling plate of the present invention.

In the figure: 1. fixing a first column; 11. buckling; 13. fixing a second column; 14. a first rectangular groove; 15. a second rectangular groove; 16. a first spring; 17. a second spring; 18. a first clamping groove; 19. pulling a plate; 2. a second circular groove; 21. fixing a column III; 22. a rectangular groove IV; 23. a rectangular groove V; 24. a second clamping groove; 25. a third spring; 26. a buckle plate; 27. a fourth spring; 28. a first pull rod; 3. a second pull rod; 31. a third pull rod; 32. a fixed block; 33. a chute; 4. a battery controller; 41. a base.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail and completely with reference to the following specific embodiments of the present application and the accompanying drawings. It should be apparent that the described embodiments are only a few embodiments of the present application, and not all embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.

The technical solutions provided by the embodiments of the present application are described in detail below with reference to the accompanying drawings.

Referring to fig. 1-4, a battery energy control device for a stratospheric aircraft comprises a second fixed column 13 and a battery controller 4, wherein a base 41 is fixedly installed at the lower end of the second fixed column 13, a second rectangular groove 15 is vertically formed at the lower end of the second fixed column 13, a first rectangular groove 14 is transversely formed in the middle of the second rectangular groove 15 formed in the second fixed column 13, a second spring 17 is fixedly installed at the lower end of the second rectangular groove 15 formed in the second fixed column 13, a first spring 16 is fixedly installed at the side end of the first rectangular groove 14 formed in the second fixed column 13, a pull plate 19 is slidably installed in the first rectangular groove 14 and is positioned at the side end of the first spring 16, a first clamping groove 18 is vertically formed in the front end of the pull plate 19 in a penetrating manner, a second pull rod 3 is fixedly installed at the side end of the pull plate 19, a first pull rod 28 is fixedly installed on the circumferential surface of the second pull rod 3 and is positioned at the opposite end of the pull plate 19, and a clamping plate 26 is fixedly installed at the side end of the first pull plate 28, the buckling plate 26 is vertically provided with a second clamping groove 24 in a penetrating manner, the buckling plate 26 is transversely provided with a third fixing column 21 in a sliding manner, the upper end of the third fixing column 21 is vertically provided with a second circular groove 2 in a penetrating manner, the lower end of the second circular groove 2 arranged on the third fixing column 21 is vertically provided with a fifth rectangular groove 23, the middle of the fifth rectangular groove 23 arranged on the third fixing column 21 is transversely provided with a fourth rectangular groove 22, the side end of the fourth rectangular groove 22 arranged on the third fixing column 21 is provided with a sliding groove 33 in a penetrating manner and is slidably mounted with the first pull rod 28, the side end of the fourth rectangular groove 22 arranged on the third fixing column 21 is fixedly provided with a fourth spring 27 and is fixedly mounted with the buckling plate 26, the lower end of the fifth rectangular groove 23 arranged on the third fixing column 21 is fixedly provided with a third spring 25, the middle part of the second pull rod 3 is fixedly provided with a third pull rod 31, the third pull rod 31 is alternately rotatably provided with a fixing block 32 and is fixedly mounted with the upper end of the base 41, when a user needs to disassemble the battery energy control device, only pulling the third pull rod 31, the third pull rod 31 slides and translates in the fixed block 32, the third pull rod 31 drives the second pull rod 3 to move forward, the second pull rod 3 drives the pull plate 19 located at the front end and the first pull rod 28 located at the rear end to move forward, the pull plate 19 located at the front end moves transversely in the first rectangular groove 14 formed in the second fixed column 13, the buckle 11 connected by the buckle in the first clamping groove 18 formed in the pull plate 19 is sprung upwards under the elastic action of the second spring 17 located at the lower end of the second rectangular groove 15, the first pull rod 28 located at the rear end drives the buckle plate 26 to move forward, the buckle 11 connected by the buckle in the second clamping groove 24 formed in the buckle plate 26 is sprung upwards under the elastic action of the fifth rectangular groove 23 located at the lower end of the fifth rectangular groove 23, the first fixed column 1 is fixedly installed at the four corners of the lower end of the battery controller 4, the buckle 11 is fixedly installed at the lower end of the first fixed column 1, the two buckles 11 located at the front end are both sleeved with the pull plate 19 through the second rectangular groove 15 formed in the fifth movable groove 23 formed in the fixed column 13, and the movable sleeve joint 26 in the three buckles 21.

When the battery energy control device is used, two groups of fixing columns II 13 and internal structures of the fixing columns II 13 in the mechanism are provided, two groups of fixing columns III 21 and internal structures of the fixing columns III 21 in the mechanism are provided, when a user needs to disassemble the battery energy control device, only the pull rod III 31 needs to be pulled, the pull rod III 31 slides and translates in the fixing block 32, the pull rod III 31 drives the pull rod II 3 to move forwards, the pull rod II 3 drives the pull plate 19 located at the front end and the pull rod I28 located at the rear end to move forwards, the pull plate 19 located at the front end transversely moves in the rectangular groove I14 formed in the fixing column II 13, the buckle 11 connected in the clamping groove I18 formed in the pull plate 19 is upwards ejected under the elastic action of the spring II 17 located at the lower end of the rectangular groove II 15, the pull rod I28 located at the rear end drives the buckling plate 26 to move forwards, the buckle 11 connected in the clamping groove II 24 formed in the buckling plate 26 is upwards ejected under the elastic action of the rectangular groove V23 located at the lower end of the rectangular groove V23, and at the moment, and the battery energy control device is quickly disassembled. This mechanism is connected through the arm-tie 19 of front end and the quick buckle of buckle 11 to and the quick buckle of rear end buckle board 26 and buckle 11 is connected, the efficiency of quick dismantlement has been accomplished, make the staff can save time when dismantling, reduce the time cost, improve work efficiency, drive pull rod two 3 through pull rod three 31 simultaneously, pull rod two 3 drives two arm-ties 19 and two buckle boards 26 removal again, only need stimulate can dismantle fast once, moreover, the steam generator is simple in structure, the operation is quick, therefore, the clothes hanger is strong in practicability.

The above description is only an example of the present application and is not intended to limit the present application. Various modifications and changes may occur to those skilled in the art to which the present application pertains. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.

Claims

1. The utility model provides a battery energy controlling means for stratospheric aircraft, includes fixed column two (13) and battery controller (4), its characterized in that: the lower end of the second fixing column (13) is fixedly provided with a base (41), the lower end of the second fixing column (13) is vertically provided with a rectangular groove II (15), the middle of the rectangular groove II (15) formed in the second fixing column (13) is transversely provided with a rectangular groove I (14), the lower end of the rectangular groove II (15) formed in the second fixing column (13) is fixedly provided with a spring II (17), the side end of the rectangular groove I (14) formed in the second fixing column (13) is fixedly provided with a spring I (16), and a pulling plate (19) is located at the side end of the spring I (16) and is slidably arranged in the rectangular groove I (14).

2. The battery power control apparatus for an stratospheric aircraft as defined in claim 1, wherein: draw-in groove one (18) have been seted up in vertical running through of arm-tie (19) front end, arm-tie (19) side fixed mounting has two (3) of pull rod, is located two (3) circumference surfaces of pull rod and lie in arm-tie (19) fixed mounting has pull rod one (28) mutually, pull rod one (28) side fixed mounting has buckle board (26), buckle board (26) are vertical to be run through and have been seted up draw-in groove two (24).

3. The battery power control apparatus for an stratospheric aircraft as defined in claim 2, wherein: the clamping plate (26) is transversely provided with a third fixing column (21) in a sliding mode, the upper end of the third fixing column (21) is vertically penetrated and provided with a second circular groove (2), the lower end of the second circular groove (2) formed in the third fixing column (21) is vertically penetrated and provided with a fifth rectangular groove (23), the middle of the fifth rectangular groove (23) formed in the third fixing column (21) is transversely penetrated and provided with a fourth rectangular groove (22), the side end of the fourth rectangular groove (22) formed in the third fixing column (21) is penetrated and provided with a sliding groove (33) and is slidably installed with the first pull rod (28).

4. The battery power control apparatus for an stratospheric aircraft as defined in claim 3, wherein: a spring IV (27) is fixedly installed at the side end of a rectangular groove IV (22) formed in the fixing column III (21) and is fixedly installed with the side end of the buckle plate (26), and a spring III (25) is fixedly installed at the lower end of a rectangular groove V (23) formed in the fixing column III (21).

5. The battery power control apparatus for an stratospheric aircraft as recited in claim 2, wherein: and a third pull rod (31) is fixedly installed in the middle of the second pull rod (3), and a fixed block (32) is installed in the third pull rod (31) in a penetrating and rotating mode and is fixedly installed at the upper end of the base (41).

6. The battery power control apparatus for an stratospheric aircraft as recited in claim 1, wherein: the battery controller is characterized in that a first fixing column (1) is fixedly mounted at the four corners of the lower end of the battery controller (4), buckles (11) are fixedly mounted at the lower end of the first fixing column (1), the two buckles (11) located at the front end are movably sleeved with a pull plate (19) through a second rectangular groove (15) formed in a second fixing column (13), and the two buckles (11) located at the rear end are movably sleeved with a buckle plate (26) through a fifth rectangular groove (23) formed in a third fixing column (21).