Battery pack constant pressure shell structure for unmanned aerial vehicle and battery module

Abstract

The application discloses a kind of battery pack constant voltage shell structure and battery module for unmanned aerial vehicle, the battery pack constant voltage shell structure includes fixed shell and movable shell, the inside of the fixed shell is opened with battery compartment, and an opening is communicated with the battery compartment, the annular side wall of battery compartment is around the opening, and annular sealing air bag is further sleeved on the outside of the annular side wall;The inside of the movable shell is opened with the butt joint compartment that is communicated with the butt joint of the battery compartment, and the butt joint is arranged with annular butt joint slot around the butt joint, and multiple groups of sealing rings are arranged in the slot of the annular butt joint slot along vertical direction on both sides;The fixed shell is inserted in the inside of annular butt joint slot by the annular side wall and is completed with the movable shell Butt joint, and after butt joint is completed, the outside of the annular butt joint slot inserted with the annular side wall is sealed by the annular sealing air bag inflation.

Description

Technical Field

[0001] This invention relates to the field of battery technology, and more specifically, to a constant-pressure housing structure and battery module for a battery pack used in drones. Background Technology

[0002] Drones, especially special drones that perform high-altitude, long-endurance missions, face severe environmental challenges in their onboard battery systems. The core issue lies in the huge pressure difference and temperature changes between high altitudes and the ground. When a drone climbs from the ground (high-pressure environment) to high altitudes (low-pressure environment), the internal air pressure of the battery pack is relatively high, which creates an outward pressure difference, causing the casing to bulge, deform, or even rupture (i.e., the risk of bulging). Conversely, when the drone descends, negative pressure may be created, drawing in external moisture, leading to circuit corrosion, insulation degradation, and short-circuit hazards.

[0003] Existing battery pack sealing solutions are mostly static seals, such as O-rings and silicone gaskets. This type of sealing cannot adapt to drastic pressure differential environments, and the seals are prone to failure under continuous pressure cycles. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a solution that can dynamically adapt to changes in the flight environment and intelligently maintain stable internal pressure of the battery pack, thereby significantly improving the reliability and safety of the drone battery system.

[0005] To achieve the above objectives, the present invention provides the following technical solution: In one aspect, the present invention provides a constant-pressure battery pack housing structure for a drone. In this technical solution, the constant-pressure battery pack housing structure for a drone includes a fixed housing and a movable housing mounted on the drone. The fixed housing has a battery compartment for mounting the battery pack and an opening communicating with the battery compartment. An annular sidewall surrounds the opening of the battery compartment, and an annular sealing airbag is fitted outside the annular sidewall. The movable housing is used to close the opening. The movable housing has a docking compartment for docking with the battery compartment and a docking interface communicating with the docking compartment. An annular docking slot is provided around the docking interface, and multiple sets of sealing rings are arranged vertically on both sides of the annular docking slot. The fixed housing is inserted into the annular docking slot through the annular sidewall to dock with the movable housing. After docking, the annular sealing airbag is inflated to seal the outside of the annular docking slot through which the annular sidewall is inserted.

[0006] Furthermore, in the technical solution of the present invention, the interior of the fixed housing is further provided with a gas cavity filled with dry nitrogen gas. The gas cavity is connected to the internal space of the annular sealing airbag. The gas cavity is provided with a motor push rod. The motor push rod is used to: push and compress the internal space of the gas cavity, so that more dry nitrogen gas enters the airbag of the annular sealing airbag, thereby increasing the internal air pressure of the annular sealing airbag; and retract and release the internal space of the gas cavity, so that part of the gas in the airbag of the annular sealing airbag flows back into the gas cavity, thereby decreasing the internal air pressure of the annular sealing airbag.

[0007] Furthermore, in the technical solution of this invention, the internal air pressure of the annular sealing airbag is adjusted in real time according to the flight altitude of the UAV, specifically including: calculating according to the international standard atmospheric model, within the troposphere, ,in, The altitude is expressed as flight altitude. The air pressure at that location Expressed as standard atmospheric pressure at sea level. Expressed as sea level standard temperature, Expressed as the rate of temperature lapse, This represents the altitude at which the drone is flying. Expressed as gravitational acceleration, Expressed as the gas constant of dry air; the internal target air pressure of the annular sealing airbag is calculated in real time. ,in, This represents the target internal air pressure of the annular sealing airbag, calculated in real time. To set the pressure difference, that is, the pressure difference between the inside and outside of the annular sealing airbag; based on the calculated target internal pressure of the annular sealing airbag. The advancing or retracting distance of the motor push rod is adjusted in real time, and the relationship between the advancing or retracting distance of the motor push rod and the internal air pressure of the annular sealing airbag is as follows: ,in, This refers to the internal air pressure of the annular sealing airbag. This represents the initial internal air pressure of the annular sealing airbag. Expressed as pressure sensitivity coefficient, This is expressed as the advancing or retracting distance of the motor push rod.

[0008] Furthermore, in the technical solution of the present invention, the interior of the movable housing is further provided with a solution cavity communicating with the annular docking slot. The solution cavity is filled with insulating liquid and is located below the annular docking slot. A sliding switch is provided at the communication point between the solution cavity and the annular docking slot. A sliding push rod is provided inside the solution cavity. The sliding push rod is used to: push and squeeze the internal space of the solution cavity, so that the insulating liquid in the solution cavity enters the lower part of the annular docking slot, further filling and sealing the gap between the inserted annular sidewall and the annular docking slot with insulating liquid; and retract to release the internal space of the solution cavity, so that the insulating liquid in the lower part of the annular docking slot flows back into the interior of the solution cavity.

[0009] Furthermore, in the technical solution of the present invention, the sliding switch is connected to a first operating slider, and the sliding push rod is connected to a second operating slider.

[0010] Furthermore, in the technical solution of the present invention, the distance between the sealing rings on both sides of the groove of the annular docking slot is less than the thickness of the annular sidewall.

[0011] In another aspect, the present invention provides a battery module that employs a constant-pressure housing structure for a battery pack used in a drone, as described above.

[0012] Beneficial Effects: In summary, this invention provides a constant-pressure housing structure and battery module for a UAV battery pack. The invention utilizes an annular sealing airbag and a connected air chamber and motor push rod to form an active pressure control system. This system can precisely adjust the internal pressure of the airbag according to real-time flight altitude (external air pressure), ensuring that the battery compartment sealing interface maintains a stable and appropriate clamping force at any stage of flight. This fundamentally avoids housing bulging and negative pressure-induced contamination problems caused by pressure differences. Furthermore, by adding a solution chamber filled with insulating liquid and its control mechanism, this invention can inject insulating liquid into the sealing interface when needed (such as to cope with extreme high or low temperatures, or as a final barrier). By filling the gaps with insulating liquid, a higher sealing level is achieved, while also providing insulation and a certain degree of thermal conductivity and buffering, further enhancing adaptability in harsh environments.

[0013] Other features and advantages of the present invention will be set forth in the following description. Attached Figure Description

[0014] To more clearly illustrate the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention. Figure 1 ; Figure 2 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention. Figure 2 ; Figure 3 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention. Figure 3 ; Figure 4 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention. Figure 4 ; Figure 5 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention. Figure 5 ; Figure 6 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention. Figure 6 ; In the diagram: A, Fixed housing; A1, Battery compartment; A2, Opening; A3, Annular sidewall; A4, Annular sealing airbag; A5, Gas chamber; A6, Motor push rod; B, Movable housing; B1, Docking chamber; B2, Docking interface; B3, Annular docking slot; B4, Sealing ring; B5, Solution chamber; B6, Slide switch; B61, First operating slider; B7, Sliding push rod; B71, Second operating slider. Detailed Implementation

[0016] To make the objectives, features, and advantages of this invention more apparent and understandable, the technical solutions of the embodiments of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described below are only a part of the embodiments of this invention, and not all of them. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0017] To address the problems mentioned in the background art, this embodiment provides a solution that can dynamically adapt to changes in the flight environment and intelligently maintain stable internal pressure of the battery pack, thereby significantly improving the reliability and safety of the UAV battery system.

[0018] Figure 1 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention, as shown below. Figure 1As shown, this embodiment provides a constant-pressure battery pack housing structure for a drone. In this embodiment, the constant-pressure battery pack housing structure for a drone includes a fixed housing A and a movable housing B. Specifically, in this embodiment, the fixed housing A is mounted on the drone. Figure 2 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention, as shown below. Figure 2 As shown, the fixed housing A has a battery compartment A1 for installing a battery pack and an opening A2 communicating with the battery compartment A1. The battery compartment A1 is used to install the battery pack. When installing the battery pack, the battery pack is inserted into the battery compartment A1 through the opening A2. The battery compartment A1 includes fixing structures for fixing the battery pack, such as tape, buckles, and clips (not shown in the figure), as well as pins and slots for electrical connection with the battery pack (not shown in the figure). The battery compartment A1 is sealed except for the opening A2. The electrical connection lines inside the battery compartment A1 are led out from the sealed side. Surrounding the opening A2 is an annular sidewall A3 of the battery compartment A1. An annular sealing airbag A4 is also fitted outside the annular sidewall A3, with a gap between the annular sealing airbag A4 and the annular sidewall A3. Specifically, in this embodiment, the movable housing B is used to close the opening A2. Figure 3 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention, as shown below. Figure 3 As shown, the interior of the movable housing B has a docking compartment B1 that mates with the battery compartment A1, and a docking interface B2 that communicates with the docking compartment B1. An annular docking slot B3 is arranged around the docking interface B2. The shape and size of the annular docking slot B3 correspond to the shape and size of the annular sidewall A3. Figure 6 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention, as shown below. Figure 6 As shown, the fixed housing A is inserted into the annular docking slot B3 via the annular sidewall A3 to complete docking with the movable housing B. After the annular sidewall A3 is inserted into the annular docking slot B3, the two side walls of the annular docking slot B3 are located in the gap between the annular sealing airbag A4 and the annular sidewall A3, and in the battery compartment A1 inside the annular sidewall A3, respectively. After docking, the annular sealing airbag A4 is inflated to press and seal the outside of the annular docking slot B3 with the annular sidewall A3 inserted. That is, the annular sealing airbag A4 presses and seals the groove wall of the annular docking slot B3 located in the gap between the annular sealing airbag A4 and the annular sidewall A3. Multiple sets of sealing rings B4 are also arranged vertically on both sides of the groove of the annular docking slot B3. The distance between the sealing rings B4 on both sides of the groove is less than the thickness of the annular sidewall A3, so that when the annular sidewall A3 is inserted, the sealing rings B4 on both sides can fully contact the two side surfaces of the annular sidewall A3 to improve the sealing effect of the sealing rings B4.

[0019] Specifically, in this embodiment, Figure 4 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention, as shown below. Figure 4 As shown, the fixed housing A also has a gas chamber A5 filled with dry nitrogen. The gas chamber A5 is connected to the internal space of the annular sealing airbag A4. The gas chamber A5 has a motor push rod A6 inside, which is controlled by the UAV's control module. The motor push rod A6 is used to: push and compress the internal space of the gas chamber A5, allowing more dry nitrogen to enter the airbag of the annular sealing airbag A4, further increasing the internal air pressure of the annular sealing airbag A4; and retract and release the internal space of the gas chamber A5, allowing part of the gas in the airbag of the annular sealing airbag A4 to flow back into the gas chamber A5, further reducing the internal air pressure of the annular sealing airbag A4. Specifically, the internal air pressure of the annular sealed airbag A4 is adjusted in real time according to the drone's flight altitude. This real-time adjustment process includes: calculating the air pressure within the troposphere based on international standard atmospheric models. ,in, The altitude is expressed as flight altitude. The air pressure at that location Expressed as standard atmospheric pressure at sea level. Expressed as sea level standard temperature, Expressed as the rate of temperature lapse, This represents the altitude at which the drone is flying. Expressed as gravitational acceleration, The gas constant for dry air is calculated in real time based on the drone's flight altitude, representing the external atmospheric pressure at that altitude. Real-time calculation of the internal target air pressure of the annular sealing airbag A4. ,in, This represents the target internal air pressure of the annular sealed airbag A4, calculated in real time. To set the pressure difference, that is, the pressure difference between the inside and outside of the annular sealing airbag A4, a constant set pressure difference is established. To prevent excessive pressure difference between the annular sealing airbag A4 and the external air pressure, which could lead to excessive pressure and damage to the annular sealing airbag A4, and to prevent excessive pressure difference between the annular sealing airbag A4 and the external air pressure, which could lead to a decrease in the sealing effect of the annular sealing airbag A4; the internal target air pressure of the annular sealing airbag A4 is calculated. The advancing or retracting distance of the motor push rod A6 is adjusted in real time. The relationship between the advancing or retracting distance of the motor push rod A6 and the internal air pressure of the annular sealing airbag A4 is as follows: ,in, This refers to the internal air pressure of the annular sealed airbag A4. This represents the initial internal air pressure of the annular sealed airbag A4. Expressed as pressure sensitivity coefficient, This represents the advancing or retracting distance of the motor push rod A6. Because the pressure difference between the inside and outside of the annular sealing airbag A4 is always within the set pressure difference... The expansion degree of the annular sealing airbag A4 can be considered to fluctuate within a constant range, meaning the sum of the internal volume of the annular sealing airbag A4 and the internal volume of the air-containing cavity A5 can be considered to be at a constant value. If the movement is left and right, then the volume change caused by the advancement or retraction of the motor push rod A6 can be calculated as follows: ,in Let be the cross-sectional area of ​​the air chamber for the advancement or retraction of the motor push rod A6, where This is the pressure sensitivity coefficient. The drone's control module calculates the advance or retraction distance of the motor push rod A6 and controls the motor push rod A6 to advance or retract based on the calculation results. In this embodiment, the annular sealing airbag A4, the air chamber A5 connected to it, and the motor push rod A6 constitute an active pressure control system, which can accurately adjust the internal pressure of the annular sealing airbag A4 according to the real-time flight altitude (external air pressure). This ensures that the sealing interface of the battery compartment A1 can maintain a stable and appropriate clamping force at any stage of flight.

[0020] Specifically, in this embodiment, Figure 5 This is a partial structural diagram of a constant-pressure housing structure for a battery pack used in a drone according to an embodiment of the present invention, as shown below. Figure 5 As shown, the interior of the movable housing B also has a solution chamber B5 that communicates with the annular docking slot B3. The solution chamber B5 is filled with insulating liquid and is located below the annular docking slot B3. A sliding switch B6 is provided at the connection between the solution chamber B5 and the annular docking slot B3. The sliding switch B6 is connected to a first operating slider B61. A sliding push rod B7 is provided inside the solution chamber B5 and is connected to a second operating slider B71. The sliding push rod B7 is used to: push and squeeze the internal space of the solution chamber B5, so that the insulating liquid in the solution chamber B5 enters the lower part of the annular docking slot B3, and further fills and seals the gap between the inserted annular sidewall A3 and the annular docking slot B3 with insulating liquid; and retract to release the internal space of the solution chamber B5, so that the insulating liquid in the lower part of the annular docking slot B3 flows back into the solution chamber B5. By adding a solution chamber B5 filled with insulating liquid, the insulating liquid can be injected into the sealing interface, i.e., into the annular docking slot B3 with annular sidewall A3, when needed (such as to cope with extreme high and low temperatures or as a final barrier). The insulating liquid fills the gap between the annular sidewall A3 and the annular docking slot B3, achieving a higher sealing level. At the same time, the multi-layered sealing rings B4 on both sides inside the annular docking slot B3 can also prevent excess insulating liquid from overflowing into the battery compartment A1.

[0021] This embodiment also provides a battery module that adopts a constant-pressure housing structure for a battery pack used in a drone as described above.

[0022] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A constant-pressure housing structure for a battery pack of an unmanned aerial vehicle (UAV), characterized in that, include: A fixed shell (A) is mounted on a drone. Inside the fixed shell (A) is a battery compartment (A1) for mounting a battery pack and an opening (A2) communicating with the battery compartment (A1). An annular sidewall (A3) surrounds the opening (A2) of the battery compartment (A1), and an annular sealing airbag (A4) is fitted outside the annular sidewall (A3). A movable shell (B) is used to close the opening (A2). Inside the movable shell (B) is a docking compartment (B1) that mates with the battery compartment (A1), and a docking... The interface (B2) connected to the compartment (B1) is provided with an annular docking slot (B3) around the interface (B2). Multiple sets of sealing rings (B4) are arranged vertically on both sides of the groove of the annular docking slot (B3). The fixed housing (A) is inserted into the annular docking slot (B3) through the annular sidewall (A3) to dock with the movable housing (B). After docking, the annular sealing airbag (A4) is inflated to press and seal the outside of the annular docking slot (B3) into which the annular sidewall (A3) is inserted.

2. The constant-pressure housing structure for a battery pack of a drone according to claim 1, characterized in that, The fixed housing (A) is further provided with a gas chamber (A5) filled with dry nitrogen. The gas chamber (A5) is connected to the internal space of the annular sealing airbag (A4). The gas chamber (A5) is provided with a motor push rod (A6). The motor push rod (A6) is used to: push and squeeze the internal space of the gas chamber (A5) to allow more dry nitrogen to enter the airbag of the annular sealing airbag (A4), further increasing the internal air pressure of the annular sealing airbag (A4); and retract and release the internal space of the gas chamber (A5) to allow part of the gas in the airbag of the annular sealing airbag (A4) to flow back into the gas chamber (A5), further decreasing the internal air pressure of the annular sealing airbag (A4).

3. A constant-pressure housing structure for a battery pack in a drone according to claim 2, characterized in that, The internal air pressure of the annular sealed airbag (A4) is adjusted in real time according to the flight altitude of the UAV. Specifically, this includes: calculating the internal air pressure in the troposphere based on international standard atmospheric models. ,in, The altitude is expressed as flight altitude. The air pressure at that location Expressed as standard atmospheric pressure at sea level. Expressed as sea level standard temperature, Expressed as the rate of temperature lapse, This represents the altitude at which the drone is flying. Expressed as gravitational acceleration, Expressed as the gas constant of dry air; the internal target air pressure of the annular sealing airbag (A4) is calculated in real time. ,in, This represents the target internal air pressure of the annular sealing airbag (A4), calculated in real time. To set the pressure difference, that is, the pressure difference between the inside and outside of the annular sealing airbag (A4); based on the calculated target internal pressure of the annular sealing airbag (A4). The advancing or retracting distance of the motor push rod (A6) is adjusted in real time, and the relationship between the advancing or retracting distance of the motor push rod (A6) and the internal air pressure of the annular sealing airbag (A4) is as follows: ,in, This refers to the internal air pressure of the annular sealing airbag (A4). This represents the initial internal air pressure of the annular sealing airbag (A4). Expressed as pressure sensitivity coefficient, This is expressed as the advancing or retracting distance of the motor push rod (A6).

4. A constant-pressure housing structure for a battery pack in a drone according to claim 1, characterized in that, The movable housing (B) also has a solution chamber (B5) inside, which communicates with the annular docking slot (B3). The solution chamber (B5) is filled with insulating liquid. The solution chamber (B5) is located below the annular docking slot (B3). A sliding switch (B6) is provided at the connection between the solution chamber (B5) and the annular docking slot (B3). A sliding push rod (B7) is provided inside the solution chamber (B5). The sliding push rod (B7) is used to: push and squeeze the internal space of the solution chamber (B5) to allow the insulating liquid in the solution chamber (B5) to enter the lower part of the annular docking slot (B3), further filling and sealing the gap between the inserted annular sidewall (A3) and the annular docking slot (B3) with insulating liquid; and retract to release the internal space of the solution chamber (B5), allowing the insulating liquid in the lower part of the annular docking slot (B3) to flow back into the solution chamber (B5).

5. A constant-pressure housing structure for a battery pack in a drone according to claim 4, characterized in that, The sliding switch (B6) is connected to a first operating slider (B61), and the sliding push rod (B7) is connected to a second operating slider (B71).

6. A constant-pressure housing structure for a battery pack in a drone according to claim 1, characterized in that, The distance between the sealing rings (B4) on both sides of the annular docking slot (B3) is less than the thickness of the annular sidewall (A3).

7. A battery module, characterized in that, The battery pack constant pressure housing structure for a drone is described in any one of claims 1-6.

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