CN210778725U

CN210778725U - Special nanometer capacitance battery structure of large aircraft

Info

Publication number: CN210778725U
Application number: CN201921538095.7U
Authority: CN
Inventors: 崔建中
Original assignee: Yinghongnami Corp
Current assignee: Yinghongnami Corp
Priority date: 2019-09-17
Filing date: 2019-09-17
Publication date: 2020-06-16
Anticipated expiration: 2029-09-17

Abstract

A special nanometer capacitor battery structure for a large aircraft comprises an installation sleeve, a battery body, an upper cover shell and a lower cover body which are detachably connected, wherein openings are formed in two sides of the installation sleeve, clamping blocks are arranged on the side wall of the installation sleeve, and the battery body is arranged in the installation sleeve; upper cover casing and lower cover casing are the mirror image setting, upper cover casing and lower cover casing bottom are equipped with the louvre, the louvre both ends are equipped with the fixing base, be equipped with the heat dissipation copper sheet between the fixing base, be equipped with the joint seat on the lateral wall of upper cover casing and lower cover casing, be equipped with the fly leaf in the joint seat, the fly leaf bottom is equipped with the spring, the bayonet socket has all been seted up on the both ends lateral wall of upper cover casing, the both ends lateral wall top of lower cover casing is equipped with the buckle, place in the lower cover casing through the installation cover that will be equipped with battery body, and in the joint seat with joint piece embedding, dock upper cover casing and lower cover casing again, make joint piece and joint seat realize flexonics, prevent that the battery from leading to the damage of battery because of the vibration of aircraft.

Description

Special nanometer capacitance battery structure of large aircraft

Technical Field

The utility model belongs to the technical field of the electric capacity battery, concretely relates to special nanometer electric capacity battery structure of large aircraft.

Background

Generally, a large unmanned aerial vehicle mostly provides energy through a battery during flying, the battery power of the large unmanned aerial vehicle is relatively large, and after a long-time flying task, the battery can generate a large amount of heat when discharging at high power, so that the battery can generate heat and scald, the aging of the battery is accelerated, the service life of the battery is shortened, and the battery can be caused to be ignited and exploded when the battery is serious. The battery of current large aircraft does not accomplish fine processing in the aspect of the heat dissipation, can't play good cooling effect, and because the long-time high power of battery discharges, the battery power consumption speed is very fast, consequently often need better multiunit battery in a flight task, current aircraft battery structure is complicated relatively, can consume the plenty of time when the installation with dismantle the battery, and because the gesture and the direction change of aircraft flight can lead to the inside emergence vibration of aircraft, adopt rigid connection mostly between current aircraft battery and the battery installation shell, can lead to the deformation damage of the battery of aircraft after long-time the use.

SUMMERY OF THE UTILITY MODEL

To the above problem, the utility model discloses a special nanometer electric capacity battery structure of large aircraft.

The specific technical scheme is as follows:

a special nanometer capacitor battery structure for a large aircraft comprises an installation sleeve, battery bodies, an upper cover shell and a lower cover body, wherein the upper cover shell and the lower cover body are detachably connected, the installation sleeve is of a hollow structure, openings are formed in two sides of the installation sleeve, the peripheral side walls of the installation sleeve are arranged in a hollow manner, two clamping blocks are symmetrically arranged on the side walls of the two sides of the installation sleeve, the clamping blocks are longitudinally arranged at two ends of the side wall of the installation sleeve, the cross sections of the clamping blocks are of a T-shaped structure, rubber cushions are arranged on the inner wall of the installation sleeve, the two battery bodies are arranged in the installation sleeve, and the battery bodies are detachably connected with the installation sleeve; the upper cover shell and the lower cover shell are arranged in a mirror image manner, a plurality of heat dissipation holes are arranged on the side walls of the bottom ends of the upper cover shell and the lower cover shell, fixing seats are symmetrically arranged at the two ends of the heat dissipation holes, a heat dissipation copper sheet is arranged between the fixing seats, two clamping seats are symmetrically arranged on the side walls of the two sides of the upper cover shell and the lower cover shell, the clamping seats are matched with the clamping block sizes on the mounting sleeve, a movable plate is horizontally arranged in the clamping seats, a spring is connected to the bottom end of the movable plate, the bottom end of the spring is fixedly connected with the inner wall of the bottom end of the connecting seat, mounting ports for placing the two ends of a battery are arranged on the side walls of the two ends of the upper cover shell, the clamping ports are positioned at the two sides of the mounting ports, and, the buckle is located the both sides of installing port are placed in the lower cover casing through the installation cover that will be equipped with battery body to in the joint piece embedding joint seat on the lower cover casing on will installing the cover, dock upper cover casing and lower cover casing again, and carry out the lock through buckle and bayonet socket, realize the upper cover casing and lower cover casing fixed.

Furthermore, the side walls of the two sides of the upper cover shell and the lower cover shell are provided with heat dissipation ports.

Furthermore, the horizontal position of the bottom end of the clamping seat is higher than that of the top end of the heat dissipation copper sheet.

Furthermore, the radiating copper sheets are uniformly arranged on two sides of each radiating hole.

Furthermore, the thickness dimension of the side walls at the two ends of the upper cover shell is smaller than that of the side walls at the two sides of the lower cover shell.

Furthermore, the number of the heat dissipation copper sheets is 5.

The utility model has the advantages that:

(1) the utility model discloses an installation cover is fixed battery body, place the installation cover in the lower cover casing again, and with the joint piece embedding joint seat, it is fixed to dock upper cover casing and lower cover casing again, realize the upper cover casing and the lower cover casing is fixed to the installation cover, and fly leaf in the joint seat passes through the spring and is connected with the joint seat, make the upper and lower both ends and the joint seat realization flexonics of joint piece, prevent that the aircraft from when flying, the battery leads to the damage of battery because of the vibration of aircraft.

(2) The utility model discloses set up a plurality of heat dissipation copper sheets in the louvre both sides of upper cover casing and lower cover casing, and the heat dissipation copper sheet is located battery body's upper and lower both ends, can effectively absorb the battery and produce the heat, prevents that the battery from leading to the ageing of battery because of overheated to promote the life of battery.

Drawings

Fig. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a perspective view of the upper cover case of the present invention.

Fig. 3 is a top view of the middle and lower cover casing according to the present invention.

Fig. 4 is a front view of the clamping seat of the present invention.

Description of the reference numerals

The battery cover comprises an installation sleeve 1, a clamping block 11, a rubber soft pad 12, a battery body 2, an upper cover shell 3, a heat dissipation hole 31, a fixed seat 32, a heat dissipation copper sheet 33, a clamping seat 34, a movable plate 341, a spring 342, a buckle 35, a heat dissipation port 36, an installation port 37, a lower cover shell 4 and a bayonet 41.

Detailed Description

For making the technical scheme of the utility model clear more clearly and definitely, it is right to combine the drawing below the utility model discloses further describe, any is right the utility model discloses technical scheme's technical characteristic carries out the scheme that equivalent replacement and conventional reasoning reachs and all falls into the utility model discloses protection scope. The utility model discloses in the fixed connection who mentions, fixed setting is the general connected mode among the mechanical field, and welding, bolt and nut are connected and the screw connection is all can.

In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for convenience of description of the present invention and for simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the number of the heat dissipation copper sheets is 5.

The working principle is as follows:

embedding the battery body into the mounting sleeve, placing the mounting sleeve into the lower cover shell, embedding the clamping block into the clamping seat, butting and fixing the upper cover shell and the lower cover shell, supporting two ends of the clamping block against the movable plate in the clamping seat at the moment, and connecting the movable plate with the clamping seat through the spring, thereby realizing flexible connection of the clamping block and the clamping seat.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A special nanometer capacitor battery structure for a large aircraft is characterized by comprising an installation sleeve, a battery body, an upper cover shell and a lower cover body, wherein the upper cover shell and the lower cover body are detachably connected; the upper cover shell and the lower cover shell are arranged in a mirror image manner, a plurality of heat dissipation holes are arranged on the side walls of the bottom ends of the upper cover shell and the lower cover shell, fixing seats are symmetrically arranged at the two ends of the heat dissipation holes, a heat dissipation copper sheet is arranged between the fixing seats, two clamping seats are symmetrically arranged on the side walls of the two sides of the upper cover shell and the lower cover shell, the clamping seats are matched with the clamping block sizes on the mounting sleeve, a movable plate is horizontally arranged in the clamping seats, a spring is connected to the bottom end of the movable plate, the bottom end of the spring is fixedly connected with the inner wall of the bottom end of the connecting seat, mounting ports for placing the two ends of a battery are arranged on the side walls of the two ends of the upper cover shell, the clamping ports are positioned at the two sides of the mounting ports, and, the buckle is located the both sides of installing port are placed in the lower cover casing through the installation cover that will be equipped with battery body to in the joint piece embedding joint seat on the lower cover casing on will installing the cover, dock upper cover casing and lower cover casing again, and carry out the lock through buckle and bayonet socket, realize the upper cover casing and lower cover casing fixed.

2. The special nano-capacitor battery structure for the large aircraft according to claim 1, wherein the upper cover shell and the lower cover shell are provided with heat dissipation ports on two side walls.

3. The special nanocapacitive battery structure for large aircraft according to claim 1, wherein a horizontal position of a bottom end of said clamping seat is higher than a horizontal position of a top end of said heat dissipating copper sheet.

4. The special nanocapacitive battery structure for large aircraft according to claim 1, wherein said heat dissipating copper sheets are uniformly arranged on both sides of each heat dissipating hole.

5. The special nanocapacitive battery structure for the large aircraft as recited in claim 1, wherein the thickness dimension of the side walls at the two ends of the upper cover shell is smaller than the thickness dimension of the side walls at the two sides of the lower cover shell.

6. The special nanocapacitive battery structure for large aircraft according to claim 1, wherein the number of said heat dissipating copper sheets is 5.