CN218431195U - Unmanned manned aircraft battery installation mechanism - Google Patents

Abstract

The utility model belongs to the technical field of batteries, and in particular relates to a battery installation mechanism for an unmanned manned aircraft, comprising a base, a support frame detachably mounted on the base with openings on the side walls and top, and fixed on the base. The base and the limiter located inside the support frame, and the carbon fiber cloth fixed between the support frame and the limiter and can cover the opening of the side wall of the support frame, the battery installation mechanism can be easily installed by setting the base Fixed on the aircraft, it is easy to build the installation foundation of carbon fiber cloth by setting the support frame, and the detachable installation method facilitates the assembly of the support frame, and it is convenient to reduce the support frame by opening openings on the side wall and top of the support frame. The weight of the body reduces the weight of the entire aircraft and also helps to improve the overall flight time of the aircraft. In addition, by setting the limiter, it is convenient to fix the carbon fiber cloth inside the support frame and cover the opening of the side wall.

Description

An unmanned manned aircraft battery installation mechanism

technical field

The utility model belongs to the technical field of batteries, in particular to a battery installation mechanism for an unmanned manned aircraft.

Background technique

Lithium-ion batteries have the characteristics of high energy density and long service life, and are widely used in electric aircraft. The reactants in the electrochemical reaction of lithium-ion batteries are negative and positive electrodes, and the electrolyte provides a conductive medium for lithium ions to move between the electrodes. When electrons flow through the external circuit during discharging or charging respectively, electric energy flows out or flows into the battery; electric aircraft has high requirements on weight, and the weight affects the overall battery life. In order to reduce the weight of the aircraft, the current battery uses A lower density aluminum plate, but thicker and less effective at dissipating heat, and heavier.

The Chinese patent discloses a soft-packed battery pack, which includes a box body, a base, a fixed L plate, a heat conducting plate, a heat sink, and a battery module set; the battery module set includes an insulator and a battery module; the battery The module includes two ABS insulating splints, 15 heat-dissipating aluminum plates, 14 soft-packed single batteries and battery connectors; The axial direction of the body battery is vertical, the radiator is arranged on the outside of the battery module group and parallel to the axial direction of the single battery, guide rail grooves are arranged in the middle and both sides of the radiator along the axial direction, the The heat conduction plate is connected to the radiator by being inserted into the guide rail groove, but the battery installation structure is mainly fixed and installed with an aluminum plate, and the heavy weight will affect the overall battery life of the aircraft, and the overall heat dissipation effect is poor.

Utility model content

The purpose of this utility model is to provide a battery installation mechanism for unmanned manned aircraft, which aims to solve the problem that the existing battery installation structure mainly uses aluminum plates for fixing and installation. less effective problem.

The utility model is achieved in this way. A battery installation mechanism for an unmanned manned aircraft includes: a base, a support frame that is detachably installed on the base and has openings on the side wall and the top, and is fixed on the base. The base, the limit piece located inside the support frame, and the carbon fiber cloth fixed between the support frame and the limit piece and can cover the opening of the side wall of the support frame.

A battery installation mechanism for an unmanned manned aircraft of the utility model, by setting a base, it is convenient to fix the battery installation mechanism on the aircraft; It is convenient to assemble the supporting frame. Opening openings on the side walls and top of the supporting frame can reduce the weight of the supporting frame. While reducing the weight of the entire aircraft, it is also beneficial to improve the overall flight time of the aircraft. In addition, through Setting the limiter facilitates the fixed installation of carbon fiber cloth inside the support frame, and covers the opening of the side wall, thereby forming an isolated space for battery installation. Due to the lighter weight of carbon fiber cloth and faster heat dissipation, it further improves the performance of the aircraft. Excellent endurance effect and heat dissipation effect, which can meet the needs of aircraft battery installation.

Preferably, the supporting frame includes four corner pieces fixed on the top of the base and arranged in parallel, and two splicing pieces detachably connected between two adjacent corner pieces through a splicing assembly, the Cushioning components are padded between the carbon fiber cloth and the corner pieces.

Preferably, the corner piece includes a vertical portion and corner portions arranged symmetrically at both ends of the vertical portion, and each of the corner portions is connected with two splicing pieces perpendicular to each other through a splicing assembly, and the splicing One end of the piece away from the corner portion is connected to the corner portion of another adjacent corner piece, and the two corner pieces and the two splicing pieces connected between the two adjacent corner pieces form the side wall opening.

Preferably, the splicing assembly includes: one end is fixedly connected to the splicing piece and the other end is provided with a notch on the top; one end is fixed on one side of the corner and the other end can abut against the notch The fixing part and the splicing unit detachably connected between the fixing part and the supporting part.

Preferably, a counterbore opposite to the notch is opened at the bottom of the fixing member, an engaging groove opposite to the counterbore is recessed inwardly at the notch of the support member, and a recess is provided on one side of the fixing member There is a guide hole, and the splicing unit is slidably installed on the fixing part and can be engaged with the supporting part.

Preferably, the splicing unit includes: a clamping piece that is slidably installed inside the counterbore and can extend into the engaging groove, one end is connected to the clamping piece and the other end abuts against the counterbore The inner elastic member, one end of which is fixedly connected to the clamping member and slides through the inside of the guide hole, and the sliding member which is arranged on the outside of the fixing member and is fixedly connected to the end of the sliding member away from the clamping member. Adjustment parts.

Preferably, the stoppers are vertically fixed on the top of the base and there are a plurality of them, each of the stoppers is arranged on the inner side of one of the corner pieces and connected to the corner piece. The lengths are equal, and the carbon fiber cloth is fixedly wound around the outside of the limiting member.

Preferably, the buffer assembly includes: a buffer layer arranged on the outside of the carbon fiber cloth and a plurality of shock absorbers fixed inside the buffer layer at intervals, the buffer layer is fixedly attached to the inner wall of the corner piece and The side wall opening may be covered.

Preferably, a plurality of cooling holes are spaced inside the corner piece and the splicing piece.

Preferably, the carbon fiber angle of the carbon fiber cloth is set at -45 degrees to 90 degrees.

Compared with the prior art, the beneficial effects of the utility model are: it is convenient to fix the battery installation mechanism on the aircraft by setting the base; Assembling the support frame, by opening openings on the side wall and top of the support frame, it is easy to reduce the weight of the support frame, while reducing the weight of the entire aircraft, it is also conducive to improving the overall flight time of the aircraft. In addition, by setting the limit The position piece facilitates the fixed installation of the carbon fiber cloth inside the support frame and covers the opening of the side wall, thereby forming an isolated space for battery installation. In actual operation, the carbon fiber cloth can be directly attached to the outside of the cell On the surface, because the carbon fiber cloth is lighter in weight and dissipates heat faster, it further improves the endurance effect of the aircraft and the heat dissipation effect of the battery, which can meet the needs of aircraft batteries.

Description of drawings

Fig. 1 is the front structural view of a battery installation mechanism of an unmanned manned aircraft provided by the utility model;

Fig. 2 is the sectional view of A-A direction in Fig. 1;

Fig. 3 is the sectional view of B-B direction in Fig. 2;

Fig. 4 is a perspective view of a corner piece of an unmanned manned aircraft battery installation mechanism provided by the utility model;

Fig. 5 is a partial enlarged view of place C in Fig. 2;

Fig. 6 is a partial structural sectional view at C in Fig. 2;

FIG. 7 is a partially enlarged view at D in FIG. 3 .

In the drawings: 1 base, 2 supporting frame, 21 corner piece, 211 vertical part, 212 corner part, 22 splicing piece, 3 limiting piece, 4 carbon fiber cloth, 5 splicing assembly, 51 supporting piece, 52 fixing piece . hole.

Detailed ways

In order to make the purpose, technical solution and advantages of the utility model clearer, the utility model will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model, and are not intended to limit the utility model.

The specific implementation of the utility model is described in detail below in conjunction with specific embodiments.

Example 1

As shown in Figures 1-6, it is a structural diagram of a battery installation mechanism for an unmanned manned aircraft provided by the utility model, including: a base 1, which is detachably installed on the base 1 and has side walls and tops A support frame 2 with an opening, a stopper 3 fixed on the base 1 and located inside the support frame 2, and a support frame fixed between the support frame 2 and the stopper 3 and capable of covering the support frame A carbon fiber cloth 4 with openings on the side wall of the body 2.

In practical application of this embodiment, it is convenient to fix the battery installation mechanism on the aircraft by setting the base 1, and it is convenient to build the installation foundation of the carbon fiber cloth 4 by setting the support frame 2, and the detachable installation method is convenient for supporting the frame. 2, by opening openings on the side walls and top of the support frame 2, it is convenient to reduce the weight of the support frame 2, and it also helps to improve the overall flight time of the aircraft while reducing the weight of the entire aircraft. The position piece 3 facilitates the fixed installation of the carbon fiber cloth 4 inside the support frame 2, and covers the opening of the side wall, thereby forming an isolated space for battery installation. In actual installation, the carbon fiber cloth 4 can be directly attached to the battery. The outer surface of the core, because the carbon fiber cloth 4 is lighter in weight and dissipates heat faster, which further improves the endurance effect of the aircraft and the heat dissipation effect of the battery, which can meet the needs of aircraft batteries.

Specifically, the support frame 2 includes four corner pieces 21 fixed on the top of the base 1 and arranged in parallel, and a detachable connection between two adjacent corner pieces 21 through a splicing assembly 5 . Two splicing pieces 22, the buffer assembly 6 is filled between the carbon fiber cloth 4 and the corner pieces 21, by setting four corner pieces 21 and detachably installed splicing between two adjacent corner pieces 21 Part 22 is convenient to form a frame for battery installation, so that carbon fiber cloth 4 is fixed inside, and the battery installed in the support frame 2 is conveniently protected by setting buffer assembly 6, so as to avoid affecting the battery of the aircraft due to vibration during flight.

Further, the corner piece 21 includes a vertical portion 211 and corner portions 212 symmetrically arranged at both ends of the vertical portion 211, and each of the corner portions 212 is connected with two mutually perpendicular A splicing piece 22, one end of the splicing piece 22 away from the corner portion 212 is connected to the corner portion 212 of another adjacent corner piece 21, and the two corner pieces 21 are connected between two adjacent corner pieces 21 The two splices 22 form the side wall opening.

It can be known that by setting the vertical part 211 and the corner part 212, it is convenient to use the corner piece 21 to vertically install two splicing pieces 22 at the first and last ends respectively, and then use the splicing piece 22 to fix the adjacent corner piece 21 Connected, using the splicing component 5 for connection facilitates the detachable installation of the entire support frame 2, saves manpower and facilitates subsequent disassembly and maintenance.

Furthermore, the splicing assembly 5 includes: one end of which is fixedly connected to the splicing piece 22 and the other end of which is provided with a notch at the top; one end is fixed on one side of the corner 212 and the other end can be connected to The fixed part 52 with the gap and the splicing unit 7 detachably connected between the fixed part 52 and the support part 51 facilitate the detachable connection of the corner piece 21 and the spliced part 22 by setting the splicing assembly 5 , by recessing a notch on the top of the support member 51, it is convenient to abut the fixing member 52 on the notch, and then use the splicing unit 7 to realize the detachable installation of the support member 51 and the fixing member 52.

In one case of this embodiment, the bottom of the fixing member 52 is provided with a counterbore 53 opposite to the notch, and the notch of the support member 51 is recessed inwardly to provide a snapping hole 53 opposite to the counterbore 53 . The slot 54 is recessed with a guide hole 55 on one side of the fixing member 52 , and the splicing unit 7 is slidably installed on the fixing member 52 and can be engaged with the supporting member 51 .

In another case of this embodiment, the splicing unit 7 includes: a clamping piece 71 that is slidably installed inside the counterbore 53 and can extend into the inside of the engaging groove 54; 71 and the other end abuts against the elastic member 72 inside the counterbore 53; 52 outside and fixedly connected to the adjustment piece 74 at the end of the sliding piece 73 away from the clamping piece 71 .

It should be noted that the installation of the splicing unit 7 is facilitated by setting the counterbore 53 and the engaging groove 54, and by slidingly installing the clamping member 71 inside the counterbore 53, it is convenient to use the adjusting member 74 to drive the sliding member 73 along the Move up and down with the guide hole 55, and then drive the clamping member 71 to compress the elastic member 72, so that the clamping member 71 extends into the engaging groove 54 inside the support member 51, and the clamping member 71 is in contact with the engaging groove 54 to fix the fixing member 52 and the support member 51 , and the adjusting member 74 is arranged outside the fixing member 52 to facilitate manual adjustment.

In an example of the present utility model, the device adopts the combination of the supporting frame 2 and the limiting member 3 to realize the fixing of the carbon fiber cloth 4, thereby forming a closed battery installation space. In actual operation, the supporting frame 2 In addition to being set as the four corner pieces 21 and the splicing piece 22 of the device, other installation frames can also be used, and its shape can be other cubes besides a cube. The shape and installation method of this embodiment are not limited. In actual operation, the carbon fiber cloth 4 can be wound on the limiter 3 and fixed with the support frame 2 by bolts or screws, and can also be fixed by gluing, which is not discussed in this embodiment. Make specific limits.

Exemplarily, the splicing piece 22 can be a splicing rod or a connecting plate, and the material of the splicing piece 22 and the corner piece 21 can be a plate made of carbon fiber, and the support piece 51 can be a receiving plate or a receiving block, The fixing part 52 can be a fixing plate or a fixing block arranged in cooperation with the receiving plate, so that the splicing unit 7 can be used for splicing and installation, and its material can also be a carbon fiber plate; the clamping part 71 can be a trapezoidal block or a cylinder The elastic member 72 can be a spring or a compression spring, so that the snap-in member 71 can be abutted against the inside of the snap-in slot by using elasticity; block or slide bar, thereby driving the clip 71 to move up and down under the drive of the adjustment member 74; the adjustment member 74 can be an adjustment handle or an adjustment block, and of course it can also be other driving equipment such as an electric cylinder, etc., in this embodiment No specific limitation is made here.

Example 2

As shown in Figure 2, Figure 3 and Figure 7, on the basis of Embodiment 1, the limiter 3 includes a plurality of limiter 3 vertically fixed on the top of the base 1, each limiter The pieces 3 are arranged on the inside of one of the corner pieces 21 and have the same length as the corner piece 21 , and the carbon fiber cloth 4 is fixedly wound around the outside of the limiting piece 3 .

In the actual application of this embodiment, the installation of the auxiliary carbon fiber cloth 4 is facilitated by setting the limiting member 3, and by fixing the carbon fiber cloth 4 around the outer side of the limiting member 3, it is convenient to cooperate with the supporting frame 2 to realize its fixing. Furthermore, the battery to be installed can be isolated from the outside world. The installation of carbon fiber not only reduces the weight of the entire device, but also improves the heat dissipation effect of the device and improves the flight time of the aircraft.

Specifically, the buffer assembly 6 includes: a buffer layer 61 arranged on the outside of the carbon fiber cloth 4 and a plurality of shock absorbers 62 fixed at intervals inside the buffer layer 61, the buffer layer 61 and the The inner wall of the corner piece 21 is fixedly fitted and can cover the opening of the side wall.

It can be known that by setting the buffer assembly 6, it is convenient to protect the cells of the battery to be installed, avoiding the impact of the vibration generated during the flight on the battery, and the use of the shock absorber 62 is also convenient to improve the stability of the device.

Exemplarily, the limiting member 3 can be a limiting rod or a limiting plate, and its shape can be cylindrical, so that the carbon fiber cloth 4 is wrapped on the limiting member 3; the buffer assembly 6 can be fixed with bolts or screws Of course, it can also be glued between the limiter 3 and the support frame 2; the buffer layer 61 can be shock-absorbing cotton or soft plastic, and the shock-absorbing member 62 can be fixed at intervals inside the shock-absorbing cotton A special spring or a compression spring can offset the force when the cell contacts it, thus ensuring the stable power supply of the battery.

Example 3

As shown in FIGS. 1-4 , on the basis of Embodiment 1 and Embodiment 2, a plurality of cooling holes 8 are spaced apart inside the corner piece 21 and the splicing piece 22 .

Specifically, by opening the heat dissipation holes 8 inside the corner pieces 21 and the splicing pieces 22, it is convenient to further reduce the weight of the entire splicing frame, and the setting of the heat dissipation holes 8 is also convenient for improving the heat dissipation efficiency of the device and improving battery life. ability.

Further, the carbon fiber angle of the carbon fiber cloth 4 is set at -45° to 90°.

It can be known that in actual operation, the angle of the carbon fiber cloth 4 can be selected according to the needs, it can be -45 degrees, 0 degrees, 45 degrees or 90 degrees, or other angles, so as to adapt to different batteries The heat dissipation requirement is not specifically limited in this embodiment.

It should be noted that by further optimizing the selection of materials, the use of carbon fiber can further improve the functions of heat conduction and heat dissipation and weight reduction. Since the selected materials have the characteristics of high thermal conductivity, it can play a very good role in weight reduction and battery life of electric aircraft. Effect.

In actual operation, the four corner pieces 21 and the four splicing pieces 22 connected between the four corner pieces 21 form the top opening, which can further reduce the quality of the whole device; the top opening of the support frame 2 The cover is provided with a conductive plate, so as to supply power to the battery inside the supporting frame body 2. Specifically, it can be a PCB board, and the inside of the conductive plate is equipped with a plurality of conductive holes that can be connected to the battery. Of course, it can also be other The top cover is used in conjunction with the device to realize the installation and power supply of the aircraft battery, which is not specifically limited in this embodiment.

The above-mentioned embodiment of the utility model provides a battery installation mechanism for an unmanned manned aircraft. By setting the base 1, it is convenient to fix the battery installation mechanism on the aircraft, and by setting the support frame 2, it is convenient to set up the installation of the carbon fiber cloth 4. foundation, and the detachable installation method facilitates the assembly of the support frame 2, and openings are provided on the side walls and top of the support frame 2, which facilitates the reduction of the weight of the support frame 2 and reduces the weight of the entire aircraft. It is conducive to improving the overall flight time of the aircraft. In addition, by setting the limiter 3, it is convenient to fix the carbon fiber cloth 4 inside the support frame 2, and cover the opening of the side wall, thereby forming an isolated space for battery installation. During actual installation, the carbon fiber cloth 4 can be directly attached to the outer surface of the battery cell. Since the carbon fiber cloth 4 is lighter in weight and dissipates heat faster, it further improves the endurance effect of the aircraft and the heat dissipation effect of the battery, and can meet the needs of aircraft batteries. .

The above descriptions are only preferred embodiments of the present utility model, and are not intended to limit the present utility model. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present utility model shall be included in this utility model. within the scope of protection of utility models.

Claims (10)

1. An unmanned manned aircraft battery installation mechanism is characterized in that it comprises: a base (1), a support frame (2) that is detachably mounted on the base (1) and that the sidewall and the top are all provided with openings ), a limit piece (3) fixed on the base (1) and inside the support frame (2) and fixed between the support frame (2) and the limit piece (3) and The carbon fiber cloth (4) that can cover the opening of the side wall of the support frame body (2). 2. A battery installation mechanism for unmanned manned aircraft according to claim 1, characterized in that, the supporting frame (2) includes four parallel-arranged fixed on the top of the base (1). Corner pieces (21) and two splicing pieces (22) that are detachably connected between adjacent two corner pieces (21) by splicing components (5), the carbon fiber cloth (4) and the corner pieces ( 21) are filled with cushioning components (6). 3. A kind of unmanned manned aircraft battery installation mechanism according to claim 2, is characterized in that, described corner piece (21) comprises vertical part (211) and is symmetrically arranged on described vertical part ( 211) the corners (212) at both ends, and each of the corners (212) is connected with two mutually perpendicular splicing pieces (22) through the splicing assembly (5), and the splicing pieces (22) are far away from the corner One end of the part (212) is connected with the corner part (212) of another adjacent corner piece (21), and the two corner pieces (21) and the two adjacent corner pieces (21) connected between A splice (22) forms the side wall opening. 4. A battery installation mechanism for unmanned manned aircraft according to claim 3, characterized in that, the splicing assembly (5) comprises: one end is fixedly connected to the splicing piece (22) and the other end is topped A supporting piece (51) with a notch recessed, one end fixed on one side of the corner portion (212) and a fixing piece (52) whose other end can abut against the notch, and a fixing piece (52) detachably connected to the fixing piece (52) ) and the splicing unit (7) between the support (51). 5. A battery installation mechanism for unmanned manned aircraft according to claim 4, characterized in that, the bottom of the fixing member (52) is provided with a counterbore (53) opposite to the notch, and the support The notch of the piece (51) is recessed inwardly with an engaging groove (54) opposite to the counterbore (53), and a guide hole (55) is recessed on one side of the fixing piece (52), and the splicing The unit (7) is slidably installed on the fixing piece (52) and can be engaged with the supporting piece (51). 6. A battery installation mechanism for unmanned manned aircraft according to claim 5, characterized in that the splicing unit (7) includes: slidingly installed inside the counterbore (53) and can extend into the The clamping piece (71) of the engaging groove (54), one end of the elastic piece (72) connected to the clamping piece (71) and the other end abutting against the inner wall of the counterbore (53), one end connected to the The clamping piece (71) is fixedly connected and slides through the sliding piece (73) inside the guide hole (55), and the sliding piece (73) is arranged on the outside of the fixing piece (52) and is away from the sliding piece (73) from the card. An adjustment piece (74) that is fixedly connected to one end of the connector (71). 7. A battery installation mechanism for an unmanned manned aircraft according to claim 2, characterized in that, the stopper (3) is vertically fixed on the top of the base (1) and there are several in number, Each of the stoppers (3) is arranged on the inner side of one of the corner pieces (21) and is equal to the length of the corner piece (21), and the carbon fiber cloth (4) is fixedly wound around the The outer side of the limiting member (3). 8. A battery installation mechanism for unmanned manned aircraft according to claim 2, characterized in that, the buffer assembly (6) comprises: a buffer layer (61) arranged on the outside of the carbon fiber cloth (4) And a plurality of shock-absorbing pieces (62) fixed at intervals inside the buffer layer (61), the buffer layer (61) is fixedly attached to the inner wall of the corner piece (21) and can cover the opening of the side wall . 9. A kind of unmanned manned aircraft battery installation mechanism according to claim 2, is characterized in that, the inside of described corner piece (21) and splicing piece (22) are all separated with a plurality of cooling holes ( 8). 10. A battery installation mechanism for unmanned manned aircraft according to any one of claims 1-9, characterized in that, the carbon fiber angle of the carbon fiber cloth (4) is set to -45 degrees to 90 degrees.

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