CN111509162B - Circuit board, battery, power supply module and aircraft - Google Patents

Circuit board, battery, power supply module and aircraft Download PDF

Info

Publication number
CN111509162B
CN111509162B CN202010397303.7A CN202010397303A CN111509162B CN 111509162 B CN111509162 B CN 111509162B CN 202010397303 A CN202010397303 A CN 202010397303A CN 111509162 B CN111509162 B CN 111509162B
Authority
CN
China
Prior art keywords
battery
circuit board
aircraft
electrical connection
connection terminal
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202010397303.7A
Other languages
Chinese (zh)
Other versions
CN111509162A (en
Inventor
胡海
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Fangyi Beijing Technology Co ltd
Original Assignee
Fangyi Beijing Technology Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Fangyi Beijing Technology Co ltd filed Critical Fangyi Beijing Technology Co ltd
Priority to CN202010397303.7A priority Critical patent/CN111509162B/en
Publication of CN111509162A publication Critical patent/CN111509162A/en
Application granted granted Critical
Publication of CN111509162B publication Critical patent/CN111509162B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/50—Current conducting connections for cells or batteries
    • H01M50/531—Electrode connections inside a battery casing
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
    • H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R12/00—Structural associations of a plurality of mutually-insulated electrical connecting elements, specially adapted for printed circuits, e.g. printed circuit boards [PCB], flat or ribbon cables, or like generally planar structures, e.g. terminal strips, terminal blocks; Coupling devices specially adapted for printed circuits, flat or ribbon cables, or like generally planar structures; Terminals specially adapted for contact with, or insertion into, printed circuits, flat or ribbon cables, or like generally planar structures
    • H01R12/70—Coupling devices
    • H01R12/71—Coupling devices for rigid printing circuits or like structures
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/10—Energy storage using batteries

Landscapes

  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Battery Mounting, Suspending (AREA)

Abstract

The invention relates to a circuit board, a battery, a power supply module and an aircraft. The power supply module (50) comprises a circuit board (10) and a battery (20), wherein at least two first electric connection terminals (31) are arranged on one of the circuit board (10) and the battery (20), at least one second electric connection terminal (32) which is matched with the at least two first electric connection terminals (31) is arranged on the other one of the circuit board (10) and the battery (20) is matched with the second electric connection terminals (32) so that the battery (20) is connected with the circuit board (10) in a plug-in mode. Through the technical scheme, when the battery is plugged, the unidirectional plugging of the battery and the circuit board is facilitated, and the double-sided plugging of the battery on the circuit board is realized. The battery and the circuit board are allowed to be electrically connected under the condition that the plugging direction of the battery is not considered, so that the user experience can be improved while the battery is convenient to install.

Description

Circuit board, battery, power supply module and aircraft
Technical Field
The invention relates to the field of aircrafts, in particular to a circuit board, a battery, a power supply module and an aircraft.
Background
In the power supply module of the aircraft (such as the ornithopter) provided by the related art, the circuit board adopts a single-socket design, and the battery adopts a single-plug design. That is, only one side of the circuit board is provided with a socket, and a plug for mating with the socket is provided on the battery. When the battery is connected, the battery can be connected with the circuit board in a butt joint mode only by adopting the specific direction for connection, and the battery and the circuit board can be electrically connected to normally supply power to the aircraft. In actual operation, if the user does not distinguish the plugging direction of the battery, the plug cannot be normally docked with the socket, normal power supply to the aircraft cannot be realized, a certain trouble can be caused for the user, and the user experience is affected.
Disclosure of Invention
The invention aims to provide a circuit board, a battery, a power supply module and an aircraft. In this power supply module, the electrical connection of the battery to the circuit board is allowed irrespective of the plugging direction of the battery.
In order to achieve the above object, the present invention provides a power supply module, including a circuit board and a battery, wherein one of the circuit board and the battery is provided with at least two first electrical connection terminals, and the other one is provided with at least one second electrical connection terminal respectively matched with at least two first electrical connection terminals, and the first electrical connection terminals are matched with the second electrical connection terminals so that the battery and the circuit board are connected in a plug-in manner.
Optionally, at least two first electrical connection terminals are disposed on the circuit board, and at least one second electrical connection terminal is disposed on the battery.
Optionally, the circuit board has opposite a face and a B face, at least one first electric connection terminal is disposed on each of the a face and the B face, and a projection of the first electric connection terminal located on the a face on the B face along a normal direction of the a face coincides with the first electric connection terminal located on the B face.
Optionally, the battery has opposite A1 face, B1 face, and an end face between the A1 face and B1 face, one of the second electrical connection terminals being located on the end face and being closer to one of the A1 face and B1 face than the other.
Optionally, at least one second electrical connection terminal is disposed on the circuit board, and at least two first electrical connection terminals are disposed on the battery, where at least two first electrical connection terminals are located on the same surface of the battery, or at least two first electrical connection terminals are located on different surfaces of the battery respectively.
Optionally, one of the first electrical connection terminal and the second electrical connection terminal is a socket, and the other is a plug.
Optionally, a clamping rib for being matched with the device to be powered in a clamping way is arranged on the battery.
Optionally, the battery includes the electric core, covers and establishes the lid of electric core one end, first electric connection terminal or second electric connection terminal set up in on the lid and with electric core electricity is connected, the joint strip sets up on the lid.
According to another aspect of the present invention, there is provided a circuit board, which is the above circuit board.
According to still another aspect of the present invention, there is provided a battery as described above.
According to an aspect of the invention, there is provided an aircraft comprising the aircraft body and the above-described power supply module.
Optionally, the circuit board is mounted on the aircraft body, the circuit board and the battery are arranged along the length direction of the aircraft, and the central axes of the circuit board and the battery along the length direction of the aircraft are respectively coincident with the central axes of the length direction of the aircraft.
Optionally, the aircraft main part has the battery and holds the chamber, be provided with on the aircraft and prevent the battery is followed the length direction of aircraft main part drops the backstop structure, the backstop structure includes base and backstop piece, the base install in the aircraft main part or with aircraft main part integrated into one piece after the battery is inserted to the circuit board, the one end of backstop piece with the base locking, the other end stretches into in the battery holds the intracavity, so as to prevent the battery is followed under the exogenic action the battery holds the intracavity and withdraws from.
Optionally, the base has a cylindrical portion, a guide groove extending through the cylindrical portion in an axial direction is formed on an inner wall of the cylindrical portion, a clamping groove extending along a circumferential direction of the cylindrical portion and communicating with the guide groove is further formed on an inner wall of the cylindrical portion, the stopper includes a pin section for stopping the battery, and a pin head connected to one end of the pin section, the pin head has a clamping portion extending in a radial direction of the pin head for adapting to the guide groove and the clamping groove, and the clamping portion can be switched from one of the guide groove and the clamping groove to the other by operating the stopper.
Through the technical scheme, due to the fact that the at least two first electric connection terminals and the at least one second electric connection terminal are arranged in the plugging fit mode, when the battery is plugged, the battery and the circuit board can be plugged in a non-directional mode, and double-sided plugging of the battery on the circuit board is achieved. The battery and the circuit board are allowed to be electrically connected under the condition that the plugging direction of the battery is not considered, so that the user experience can be improved while the battery is convenient to install.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate the invention and together with the description serve to explain, without limitation, the invention. In the drawings:
FIG. 1 is a schematic front view of a power module according to one embodiment of the invention with a battery plugged into a circuit board;
fig. 2 is a schematic top view of a battery of a power supply module according to an embodiment of the present invention when plugged into a circuit board, wherein A1 side of the battery is on the same side as a side of the circuit board;
FIG. 3 is a schematic top view of a battery of a power module according to one embodiment of the invention plugged into a circuit board, wherein the B1 side of the battery is on the same side as the A side of the circuit board;
FIG. 4 is a schematic right-side view of a circuit board according to one embodiment of the invention;
fig. 5 is a schematic front view of a battery according to an embodiment of the present invention.
Fig. 6 is a schematic left-hand view of a battery according to one embodiment of the present invention.
FIG. 7 is a schematic cross-sectional view of an aircraft along a length direction, showing a power module, according to one embodiment of the invention;
FIG. 8 is a schematic view of an arrangement of a power module on an aircraft according to one embodiment of the invention;
FIG. 9 is a schematic front view of a rear structure of an aircraft in which a battery is not mounted within a battery receiving cavity and a stop is not shown, according to one embodiment of the invention;
FIG. 10 is a schematic top view of the aft structure of an aircraft with no battery mounted within the battery receiving cavity according to one embodiment of the invention;
FIG. 11 is a schematic top view of the aft structure of an aircraft with a battery receiving cavity having a battery mounted therein according to one embodiment of the invention;
FIG. 12 is a schematic front view of a rear structure of an aircraft in which a battery is mounted to a battery receiving cavity and showing a stop, according to one embodiment of the invention;
FIG. 13 is a schematic view of a partial structure of an aircraft according to one embodiment of the invention, wherein a stop structure is shown;
fig. 14 is a schematic cross-sectional view of a stop structure of an aircraft according to one embodiment of the invention.
Description of the reference numerals
100-aircraft; 10-a circuit board; 11-A; 12-B surface; 20-cell; a 21-A1 side; 22-B1; 23-cell part; 24-cover cap; 25-end face; 31-a first electrical connection terminal; 32-a second electrical connection terminal; 40-an aircraft body; 50-a power supply module; 60-a battery receiving cavity; 71-clamping ribs; 72-clamping grooves; 80-a stop structure; 81-a base; 810-a cylindrical portion; 811-a guide slot; 812-a clamping groove; 82-a stopper; 821-pin section; 822-pin head; 823-clamping parts; 824-an operation section; l-central axis in the length direction of the aircraft.
Detailed Description
The following describes specific embodiments of the present invention in detail with reference to the drawings. It should be understood that the detailed description and specific examples, while indicating and illustrating the invention, are not intended to limit the invention.
In the present invention, directional terms such as "upper, lower, left, right, front, rear" and the like are used, and it should be noted that the use of these directional terms is merely for convenience in describing the relative positional relationship between the parts or elements referred to, and does not indicate or imply that the parts or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Unless otherwise indicated, terms of orientation such as "up, down, left, right, front, and rear" are generally used with respect to the normal flight state of the aircraft 100 (e.g., a ornithopter), and specifically, when the aircraft 100 is in normal flight, the direction toward the sky is "up", the direction toward the ground is "down", the direction toward the nose of the aircraft 100 is "front", the direction toward the tail of the aircraft 100 is "rear", the direction toward the left wing of the aircraft 100 is "left", and the direction toward the right wing of the aircraft 100 is "right"; the "longitudinal direction" refers to the "front-rear direction" of the aircraft 100, the "width direction" refers to the "left-right direction" of the aircraft 100, and the "height direction" refers to the "up-down direction" of the aircraft 100. "inner and outer" refer to the inner and outer of the associated components.
Furthermore, terms such as "first," "second," and the like, are used herein to distinguish one element from another element without sequence or importance.
As shown in fig. 1 to 14, the present invention provides a power supply module 50, the power supply module 50 includes a circuit board 10 and a battery 20, at least two first electrical connection terminals 31 are disposed on one of the circuit board 10 and the battery 20, at least one second electrical connection terminal 32 respectively mated with the at least two first electrical connection terminals 31 is disposed on the other of the circuit board 10 and the battery 20 and the circuit board 10 are connected in a pluggable manner by the first electrical connection terminals 31 mated with the second electrical connection terminals 32.
Wherein, alternatively, one of the first electrical connection terminal 31 and the second electrical connection terminal 32 may be a socket, and the other may be a plug, to facilitate quick plugging of the battery 20 and the circuit board 10.
Through the above technical scheme, due to the fact that the at least two first electric connection terminals 31 and the at least one second electric connection terminal 32 are arranged in the plugging fit mode, when the battery 20 is plugged, the battery 20 and the circuit board 10 are plugged in a non-directional mode, electric connection between the battery 20 and the circuit board 10 is allowed to be achieved under the condition that the plugging direction of the battery 20 is not considered, and user experience can be improved when the battery 20 is installed conveniently.
For example, in the embodiment shown in fig. 1 to 3, the a-side 11 and the B-side 12 of the circuit board 10 are respectively provided with a first electrical connection terminal 31 (e.g., a socket), and the battery 20 is provided with a second electrical connection terminal 32 (e.g., a plug). When the battery 20 is mounted, as shown in fig. 2, if the A1 surface 21 of the battery 20 is plugged in the direction of the same side as the a surface 11 of the circuit board 10, the second electrical connection terminal 32 of the battery 20 is plugged into one of the first electrical connection terminals 31 of the circuit board 10, so that the battery 20 is electrically connected to the circuit board 10. As shown in fig. 3, if the B1 surface 22 of the battery 20 is plugged in the direction of the same side as the a surface 11 of the circuit board 10, the second electrical connection terminal 32 of the battery 20 is plugged into the other first electrical connection terminal 31 of the circuit board 10, so that the normal power supply of the battery 20 to the circuit board 10 can be realized. Thus, double-sided plugging of the battery 20 on the circuit board 10 can be achieved.
Here, for convenience of description, only an embodiment in which the circuit board 10 is provided with two first electric connection terminals 31 and the battery 20 is provided with one second electric connection terminal 32 is illustrated.
In other embodiments, the circuit board 10 may be provided with one second electrical connection terminal 32, and the battery 20 may be provided with two first electrical connection terminals 31. For example, corresponding to fig. 2 and 3 of the foregoing embodiment, the second electrical connection terminal 32 may be provided on the a-side 11 (or the B-side 12) of the circuit board 10, and one of the two first electrical connection terminals 31 may be provided on the A1-side 21 of the battery 20, and the other may be provided on the B1-side 22 of the battery 20. In this way, when the battery 20 is mounted, if the A1 surface 21 of the battery 20 is inserted in the same direction as the a surface 11 of the circuit board 10, one of the first electrical connection terminals 31 of the battery 20 is inserted in the second electrical connection terminal 32 of the circuit board 10. If the battery 20 is plugged in the direction in which the B1 face 22 of the battery 20 is located on the same side as the a face 11 of the circuit board 10, the other first electrical connection terminal 31 of the battery 20 is plugged with the second electrical connection terminal 32 of the circuit board 10, thereby realizing double-sided plugging of the battery 20.
In addition, in other embodiments, the circuit board 10 may be provided with a plurality of first electrical connection terminals 31 such as 3, 4, 5, and the like, and the battery 20 may be provided with a plurality of second electrical connection terminals 32 such as 3, 4, 5, and the like. Thus, the second electrical connection terminal 32 of the battery 20 can be selectively plugged with the first electrical connection terminal 31 of the circuit board 10 as required to achieve non-directional plugging of the battery 20 with the circuit board 10.
In one embodiment, as shown in fig. 2 and 3, the circuit board 10 is provided with at least two first electrical connection terminals 31, and the battery 20 is provided with at least one second electrical connection terminal 32. The circuit board 10 is larger in size and larger in surface size relative to the battery 20, facilitating the placement of more electrical connection terminals. Particularly, in the case where the first electrical connection terminal 31 is a socket, the two sockets are provided on the circuit board 10, which is advantageous in reducing the difficulty of processing to a certain extent as compared with the case where two sockets are provided on the battery 20.
Here, the two first electrical connection terminals 31 may be coplanar or may be located on different planes on the circuit board 10, which is not limited in the present invention.
In one embodiment, as shown in fig. 3, the circuit board 10 may have a surface a 11 and a surface B12 opposite to each other, where at least one first electrical connection terminal 31 (such as a socket) is disposed on each of the surface a 11 and the surface B12, that is, the number of the first electrical connection terminals 31 is at least two, and the projection of the first electrical connection terminal 31 located on the surface a 11 onto the surface B12 along the normal direction of the surface a 11 coincides with the first electrical connection terminal 31 located on the surface B12, that is, the first electrical connection terminals 31 located on the surface a 11 and the surface B12 are symmetrically disposed on the circuit board 10.
The benefits of such a symmetrical arrangement are: on one hand, the attractive appearance of the product is improved; on the other hand, when the power module 50 is applied to an aircraft, for example, to an ornithopter. Based on the principle of the ornithopter, the gravity center is important to balance flight, and particularly for the micro ornithopter, the gravity center is slightly deviated, so that the left deviation and the right deviation of the flight can be caused, and even the flapping cannot take off. To ensure a smooth flight of the aircraft from side to side, it is required that the center of gravity of the aircraft is maintained on the central axis L in the longitudinal direction of the aircraft. The first electrical connection terminals 31 are symmetrically arranged on two opposite sides of the circuit board 10 and by properly arranging the position of the circuit board 10 on the aircraft 100. For example, as shown in fig. 2, 3, 7 and 8, the number of first electrical connection terminals 31 is two, one first electrical connection terminal 31 is symmetrically provided on each of the a-side 11 and the B-side 12 of the circuit board 10, and the a-side 11 and the B-side 12 of the circuit board 10 are surfaces located on both sides of the longitudinal center plane of the aircraft 100 in the longitudinal direction. In this way, it is advantageous to make the central axis of the circuit board 10 in the longitudinal direction of the aircraft 100 coincide with the central axis L of the aircraft 100 in the longitudinal direction, so that it is advantageous to reduce the influence of the first electrical connection terminal 31 on the balance of the aircraft.
In other embodiments, the at least two first electrical connection terminals 31 may be disposed asymmetrically on the a-side 11 and the B-side 12 of the circuit board 10, which is not limited in the present invention.
Further, in other embodiments, referring to fig. 3, at least two first electrical connection terminals 31 may be provided on one of the a-side 11 and the B-side 12 of the circuit board 10, i.e., the first electrical connection terminals 31 may be provided on one of the a-side 11 or the B-side 12 alone.
The specific shape of the battery 20 is not limited in the present invention. In one embodiment, as shown in fig. 3, 5 and 6, the battery 20 has opposing A1 face 21, B1 face 22, and an end face 25 between the A1 face 21 and the B1 face 22, with a second electrical connection terminal 32 located on the end face 25 and closer to one of the A1 face 21 and the B1 face 22 than the other. That is, in the present embodiment, the second electrical connection terminal 32 is provided offset on the end face 25. In one embodiment, as shown in fig. 3, the second electrical connection terminal 32 is located on the end face 25 and is disposed closer to the A1 face 21 than the B1 face 22. It will be appreciated that in other embodiments, referring to fig. 3, the second electrical connection terminals 32 are located on the end face 25 and are disposed closer to the B1 face 22 than the A1 face 21.
For the circuit board 10, in view of its small thickness dimension, the first electrical connection terminals 31 are generally not provided on the end face of the circuit board 10, but are directly provided (e.g., soldered) on both side faces, as the a-face 11 and the B-face 12 shown in fig. 3. For this reason, the arrangement in which the second electrical connection terminals 32 are offset on the end face 25, when the power supply module 50 is applied to the aircraft 100, as shown in fig. 8, is advantageous in ensuring that the longitudinal center axis of the battery 20 coincides as much as possible with the center axis L of the aircraft 100 in the longitudinal direction, so that the influence of the battery 20 on the flying balance of the aircraft 100 is advantageously reduced.
The above specifically describes the arrangement of at least two first electrical connection terminals 31 (sockets) on the circuit board 10 and at least one second electrical connection terminal 32 (plug) on the battery 20. As can be seen from the above, in other embodiments, the second electrical connection terminal 32 may be provided on the circuit board 10, and the first electrical connection terminal 31 may be provided on the battery 20. Specifically, at least one second electrical connection terminal 32 is provided on the circuit board 10, and at least two first electrical connection terminals 31 are provided on the battery 20. Wherein the at least two first electrical connection terminals 31 are located on the same surface of the battery 20, or the at least two first electrical connection terminals 31 are located on different surfaces of the battery 20, respectively, so as to provide corresponding first electrical connection terminals 31 at suitable positions according to different shapes of the battery 20.
Here, at least two first electrical connection terminals 31 of the battery 20 are mated with at least one second electrical connection terminal 32 of the circuit board 10, so that the unidirectional plugging of the battery 20 with the circuit board 10 is facilitated when the battery 20 is mounted.
In order to prevent the battery 20 and the circuit board 10 from accidentally falling off and ensure the stability of the battery 20 mounted on the device to be powered after plugging and the reliability of the electrical connection with the circuit board 10, in one embodiment, as shown in fig. 2, 3 and 6, a clamping rib 71 for being in clamping fit with the device to be powered is provided on the battery 20. For example, when the power supply module 50 is applied to the aircraft 100, a structure (such as a clamping groove 72 shown in fig. 10 and 11) matched with the clamping rib 71 may be disposed at a corresponding position of the aircraft 100 to be clamped with the clamping rib 71, so as to realize limit locking of the battery 20, thereby ensuring stability of installation of the battery 20 on the aircraft 100 and reliability of electrical connection with the circuit board 10.
As noted above, the battery 20 may have any suitable shape, such as a rectangular parallelepiped, cylindrical, or other shaped battery (e.g., a delta-shaped battery). In one embodiment, as shown in fig. 5 and 6, the battery 20 has a substantially rectangular parallelepiped structure. The battery 20 may include a battery cell 23, a cap 24 provided to cover one end of the battery cell 23, and a first electrical connection terminal 31 or a second electrical connection terminal 32 provided to the cap 24 and electrically connected to the battery cell 23. Wherein, the rib 71 may be disposed on the cover 24, the A1 surface 21 and the B1 surface 22 may be two opposite surfaces of the cover 24, and the rib 71 may be located on the A1 surface 21 or the B1 surface 22.
In this embodiment, the battery core 23 may be a lithium battery, and the positive and negative poles of the battery core 23 are connected to a second electrical connection terminal 32 (such as a plug), which is fixed by the cover 24 and passes through a via hole of the cover 24. Alternatively, the cover 24 may be plastic to reduce the weight of the battery 20.
In other embodiments, the beads 71 may be provided on the housing of the cell portion 23. The invention is not limited in this regard.
According to another aspect of the present invention, there is provided a circuit board 10, which is the circuit board 10 described above.
According to still another aspect of the present invention, there is provided a battery 20 as described above as the battery 20.
According to a further aspect of the invention, an aircraft 100 is provided, which aircraft 100 comprises an aircraft body 40 and the above-described power supply module 50, as shown in fig. 7 and 8. Alternatively, the aircraft 100 may be an ornithopter.
Wherein the circuit board 10 is mountable to the aircraft body 40. For example, a circuit board receiving cavity and corresponding securing structure may be provided on the aircraft body 40 to enable the circuit board 10 to be reliably mounted on the aircraft 100.
The circuit board 10 and the battery 20 may be disposed along the length direction of the aircraft 100, and when the battery 20 is mounted in place, the central axes of the circuit board 10 and the battery 20 along the length direction of the aircraft 100 respectively coincide with the central axis L of the length direction of the aircraft 100.
The a-side 11 and the B-side 12 of the circuit board 10 are surfaces of the circuit board 10 on both sides of a longitudinal center surface of the aircraft 100, and at least one first electrical connection terminal 31 is provided on the a-side 11 and the B-side 12, or at least one second electrical connection terminal 32 is provided on the a-side 11 and the B-side 12, respectively.
In the case of the aircraft 100, particularly in the case of a micro-ornithopter, a slight deviation in the center of gravity in the lateral direction may result in a left-hand offset or even a right-hand offset in the flight. In the present embodiment, when a structure such as the first electrical connection terminal 31 or the second electrical connection terminal 32 is arranged on the circuit board 10, since the circuit board 10 is arranged vertically (in the aircraft height direction), it is advantageous to reduce the size of the circuit board 10 in the aircraft left-right direction, thereby advantageously reducing the influence of the structure such as the electrical connection terminal on the circuit board 10 on the flying balance of the aircraft 100.
Optionally, the specific number of the first electrical connection terminals 31 or the second electrical connection terminals 32 is two, and the two first electrical connection terminals 31 or the two second electrical connection terminals 32 are symmetrically arranged on the circuit board 10 about the longitudinal plane of the aircraft in the length direction, so as to further reduce the influence of the first electrical connection terminals 31 or the second electrical connection terminals 32 on the flying balance of the aircraft 100.
In order to ensure the stability of the installation of the battery 20 on the aircraft 100 and the reliability of the electrical connection with the circuit board 10, in one embodiment, the ornithopter 100 is provided with a clamping structure for locking the battery 20, by which the battery 20 and the aircraft body 40 do not move relatively after the battery 20 is installed in place (the battery 20 is positioned at a position of being plugged into the circuit board 10), and the situation that the battery 20 is shifted or even falls off from the aircraft body 40 during the flying process is avoided.
The invention is not limited to the specific structure of the clamping structure. In one embodiment, as shown in fig. 7, 9 and 10, the rear portion of the aircraft body 40 is provided with a battery receiving chamber 60, and the battery 20 can be inserted into or withdrawn from the battery receiving chamber 60 reserved on the aircraft body 40. In one embodiment, the clamping structure includes a clamping rib 71 provided on one of the battery 20 or the battery receiving cavity 60 and a clamping groove 72 provided on the other. When the battery 20 is in place, the ribs 71 are tightly fitted in the grooves 72 to lock the battery 20. The locking structure formed by the locking rib 71 and the locking groove 72 is easy to operate while the locking reliability is ensured. The locking cooperation of the clamping ribs 71 and the clamping grooves 72 can be completed in the plugging action of the battery 20 and the circuit board 10, namely, the locking is realized when the battery 20 is plugged in place, the unlocking is realized when the battery 20 is pulled out, and the operation steps are simplified. In addition, the clamping structure formed by the clamping ribs 71 and the clamping grooves 72 has the advantages of simple structure and easy processing.
In one embodiment, as shown in fig. 10 and 11, the card slot 72 is provided on a side wall of the battery receiving chamber 60 and extends in the height direction of the aircraft 100. Generally, since the battery 20 is most likely to displace in the longitudinal direction of the aircraft 100, in the present embodiment, the extending direction of the clamping groove 72 is specifically designed to be perpendicular to the longitudinal direction of the aircraft 100, so that the clamping rib 71 on the battery 20 is better limited and locked in the longitudinal direction of the aircraft 100, thereby avoiding the displacement of the battery 20 along the longitudinal direction of the aircraft 100 and improving the limiting effect.
In one embodiment, as shown in fig. 2, 3 and 10, a clamping rib 71 is arranged on the surface a 21 of the battery 20, and a clamping groove 72 corresponding to the position and structure of the clamping rib 71 is respectively arranged on the side wall of the battery accommodating cavity 60 symmetrical to the longitudinal center plane of the ornithopter. Thus, no matter the front side or the back side of the battery 20 is spliced, the clamping ribs 71 can be matched with the clamping grooves 72, and only one clamping rib 71 is arranged on the battery 20, so that the weight of the battery 20 and the aircraft 100 is reduced.
In one embodiment, as shown in fig. 12 to 14, the aircraft body 40 has a battery receiving chamber 60, and a stopper structure 80 for preventing the battery 20 from falling off in the longitudinal direction of the aircraft body 40 is provided on the aircraft 100. The stop structure 80 includes a base 81 and a stop member 82, wherein the base 81 is mounted on the aircraft body 40 or integrally formed with the aircraft body 40, and after the battery 20 is plugged into the circuit board 10, one end of the stop member 82 is locked with the base 81, and the other end extends into the battery accommodating cavity 60, so as to prevent the battery 20 from exiting from the battery accommodating cavity 60 under the action of external force.
In this manner, the stop structure 80 may function as a child lock on the one hand. When the battery 20 is used, even if the child disconnects the battery 20 from the circuit board 10 by mistake, the battery 20 cannot be taken out of the battery accommodating cavity 60, so that the situations that the child takes out the battery 20 to eat the battery 20 by mistake or the battery 20 is lost due to the fact that the child discards the battery 20 at will can be avoided, and the use of the battery is safer for the child. On the other hand, the stopper structure 80 can supplement the engaging structure (the engaging rib 71 and the engaging groove 72) to prevent the battery 20 from falling off the aircraft 100. For example, if the locking structure of the locking rib 71 and the locking groove 72 fails in the case that the aircraft 100 is flying upward in an accelerated manner, the battery 20 does not drop from the aircraft 100 accidentally due to the stopper structure 80. Therefore, the cooperation of the stop structure 80 and the clamping structure plays a role in dual protection, so that the risk possibly caused by high-altitude falling of the battery 20 can be effectively avoided.
After the stopper 82 extends into the battery accommodating chamber 60, it may abut against the battery 20, for example, against the rear end surface of the battery 20, or may be spaced a certain distance from the rear end surface of the battery 20 as shown in fig. 12, so long as it is ensured that the battery 20 cannot be withdrawn from the battery accommodating chamber 60 without withdrawing the stopper 82 from the battery accommodating chamber 60.
The specific structure and shape of the base 81 and the stopper 82 are not limited in the present invention. In one embodiment, as shown in fig. 13, the base 81 has a cylindrical portion 810, a guide groove 811 extending through the cylindrical portion 810 in the axial direction is formed in the inner wall of the cylindrical portion 810, and a locking groove 812 extending in the circumferential direction of the cylindrical portion 810 and communicating with the guide groove 811 is formed in the inner wall of the cylindrical portion 810.
The stopper 82 includes a pin section 821 for stopping the battery 20, and a pin head 822 connected to one end of the pin section 821, the pin head 822 having a clamping portion 823 extending in a radial direction thereof for fitting with the guide groove 811 and the clamping groove 812, the clamping portion 823 being able to be switched from one of the guide groove 811 and the clamping groove 812 to the other by operating the stopper 82.
After the battery 20 is mounted in place, the clamping portion 823 of the stopper 82 may be inserted into the cylindrical portion 810 along the guide groove 811, and when the clamping portion 823 moves to be aligned with the clamping groove 812 in the axial direction of the stopper 82, the clamping portion 823 is rotated by a certain angle along the circumferential direction of the cylindrical portion 810 of the base 81, so that the clamping portion 823 enters the clamping groove 812, and limiting of the stopper 82 is achieved. At this time, as shown in fig. 12, the pin segment 821 of the stopper 82 is partially located in the battery accommodating chamber 60, and the battery 20 cannot be removed from the battery accommodating chamber 60 by the stopper action of the pin segment 821.
When it is desired to remove the battery 20 from the aircraft 100. For example, when it is necessary to remove the battery 20 for charging or replace a new battery, the stopper 82 may be rotated by a certain angle along the circumferential direction of the cylindrical portion 810, so that the engaging portion 823 moves from the engaging groove 812 into the guide groove 811, and then moves the stopper 82 in the axial direction of the stopper 82 to a position where the stopper 20 is prevented from being stopped, for example, the stopper 82 is completely withdrawn from the base 81, at which time the battery 20 may be removed from the aircraft 100.
To enhance the effect of the stopper structure 80 as a child lock, in one embodiment, as shown in fig. 14, when the engaging portion 823 is engaged in the engaging groove 812, the end surface of the pin head 822 away from the battery accommodating chamber 60 does not protrude beyond the end surface of the cylindrical portion 81 away from the battery accommodating chamber 60 (the lower end surface as shown in fig. 12), and an operation portion 824 for engaging with a tool is provided on the end surface of the pin head 822 away from the battery accommodating chamber 60 (the lower end surface as shown in fig. 12).
Since the outer end surface of the stopper 82 is located in the cylindrical portion 81 when the stopper 82 is located at the stopping position, difficulty in unlocking the stopper 82 is increased, and thus safety of the stopper 82 as the stopper structure 80 is further improved.
In one embodiment, as shown in fig. 13 and 14, the operation portion 824 may be a straight slot, and when the stopper 82 needs to be unlocked or locked, a straight screwdriver may be used to engage with the operation portion 824 of the straight slot. In other embodiments, the operating portion 824 may also be a slot of other shapes, such as a cross slot. In addition, the operation portion 824 may be a protrusion structure, in which case, a tool similar to a socket wrench may be used to lock and unlock the stopper 82 on the base 81.
In the present invention, after the battery 20 is mounted in place, the battery 20 may be located either behind the circuit board 10 or in front of the circuit board 10. In one embodiment of the present invention, as shown in fig. 7, a battery receiving cavity 60 is provided at the rear of the aircraft body 40, with the battery 20 in place (after electrical connection with the circuit board 10), and the battery 20 located behind the circuit board 10.
It will be appreciated that in other embodiments, when the battery 20 and the circuit board 10 are arranged in the left-right direction of the aircraft 100, the stopper 82 is correspondingly adjusted in position for preventing the battery 20 from falling off in the width direction of the aircraft body 40.
Further, in other embodiments, the base 81 has an internally threaded bore, and the stopper 82 has a threaded section thereon that is threadedly engaged with the internally threaded bore, so that the stopper 82 can be movably provided on the base 81 in the axial direction of the internally threaded bore. In this way, by adjusting the length of the stopper 82 that protrudes into the battery receiving chamber 60, the stopper 82 stops the battery 20.
The preferred embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the specific details of the above embodiments, and various simple modifications can be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and all the simple modifications belong to the protection scope of the present invention.
In addition, the specific features described in the above embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, various possible combinations are not described further.
Moreover, any combination of the various embodiments of the invention can be made without departing from the spirit of the invention, which should also be considered as disclosed herein.

Claims (11)

1. The power supply module is characterized by being applied to a ornithopter and comprising a circuit board (10) and a battery (20), wherein one of the circuit board (10) and the battery (20) is provided with at least two first electric connection terminals (31), the other one of the circuit board and the battery is provided with at least one second electric connection terminal (32) which is matched with the at least two first electric connection terminals (31), and the first electric connection terminals (31) are matched with the second electric connection terminals (32) so that the battery (20) and the circuit board (10) are connected in a plug-in mode;
at least two first electric connection terminals (31) are arranged on the circuit board (10), and at least one second electric connection terminal (32) is arranged on the battery (20);
the circuit board (10) is provided with an A surface (11) and a B surface (12) which are opposite, at least one first electric connection terminal (31) is arranged on each of the A surface (11) and the B surface (12), and the projection of the first electric connection terminal (31) positioned on the A surface (11) on the B surface (12) along the normal direction of the A surface (11) is overlapped with the first electric connection terminal (31) positioned on the B surface (12); the surface A (11) and the surface B (12) are respectively surfaces of the circuit board (10) on two sides of a longitudinal center surface of the ornithopter in the length direction;
the circuit board (10) is mounted on an aircraft main body (40) of the flapping-wing aircraft, the circuit board (10) and the battery (20) are arranged along the length direction of the flapping-wing aircraft, and central axes of the circuit board (10) and the battery (20) along the length direction of the flapping-wing aircraft are respectively overlapped with a central axis (L) of the length direction of the flapping-wing aircraft.
2. The power supply module according to claim 1, characterized in that the battery (20) has opposite A1 face (21), B1 face (22), and an end face (25) located between the A1 face (21) and B1 face (22), one of the second electrical connection terminals (32) being located on the end face (25) and being closer to one of the A1 face (21) and B1 face (22) than the other.
3. The power supply module according to claim 1, characterized in that at least one second electrical connection terminal (32) is provided on the circuit board (10), at least two first electrical connection terminals (31) are provided on the battery (20), wherein at least two first electrical connection terminals (31) are located on the same face of the battery (20), or at least two first electrical connection terminals (31) are located on different faces of the battery (20), respectively.
4. A power supply module according to any one of claims 1-3, characterized in that one of the first electrical connection terminal (31) and the second electrical connection terminal (32) is a socket, the other of which is a plug.
5. A power supply module according to any one of claims 1-3, characterized in that the battery (20) is provided with a snap-fit rib (71) for snap-fit engagement with a device to be powered.
6. The power supply module according to claim 5, wherein the battery (20) includes a battery core (23), a cover (24) provided at one end of the battery core (23), the first electrical connection terminal (31) or the second electrical connection terminal (32) is provided on the cover (24) and electrically connected to the battery core (23), and the clip rib (71) is provided on the cover (24).
7. Circuit board, characterized in that the circuit board (10) is applied to a power supply module according to any one of claims 1-6.
8. Battery, characterized in that the battery (20) is applied to a power supply module according to any one of claims 1-6.
9. Aircraft characterized in that the aircraft (100) is a ornithopter, comprising the aircraft body (40), a power supply module (50) according to any one of claims 1-6.
10. The aircraft according to claim 9, wherein the aircraft body (40) has a battery accommodating cavity (60), a stop structure (80) for preventing the battery (20) from falling off along the length direction of the aircraft body (40) is arranged on the aircraft (100), the stop structure (80) comprises a base (81) and a stop piece (82), the base (81) is mounted on the aircraft body (40) or is integrally formed with the aircraft body (40), and after the battery (20) is inserted into the circuit board (10), one end of the stop piece (82) is locked with the base (81), and the other end of the stop piece extends into the battery accommodating cavity (60) so as to prevent the battery (20) from exiting from the battery accommodating cavity (60) under the action of external force.
11. The aircraft according to claim 10, wherein the base (81) has a cylindrical portion (810), a guide groove (811) extending through the cylindrical portion (810) in the axial direction is formed in an inner wall of the cylindrical portion (810), a locking groove (812) extending in the circumferential direction of the cylindrical portion (810) and communicating with the guide groove (811) is further formed in an inner wall of the cylindrical portion (810),
the stopper (82) includes a pin section (821) for stopping the battery (20), and a pin head (822) connected to one end of the pin section (821), the pin head (822) having a clamping portion (823) extending in a radial direction of itself for fitting with the guide groove (811) and the clamping groove (812), the clamping portion (823) being able to be switched from one of the guide groove (811) and the clamping groove (812) to the other by operating the stopper (82).
CN202010397303.7A 2020-05-12 2020-05-12 Circuit board, battery, power supply module and aircraft Active CN111509162B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202010397303.7A CN111509162B (en) 2020-05-12 2020-05-12 Circuit board, battery, power supply module and aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202010397303.7A CN111509162B (en) 2020-05-12 2020-05-12 Circuit board, battery, power supply module and aircraft

Publications (2)

Publication Number Publication Date
CN111509162A CN111509162A (en) 2020-08-07
CN111509162B true CN111509162B (en) 2023-11-07

Family

ID=71871859

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202010397303.7A Active CN111509162B (en) 2020-05-12 2020-05-12 Circuit board, battery, power supply module and aircraft

Country Status (1)

Country Link
CN (1) CN111509162B (en)

Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004049516A1 (en) * 2002-11-27 2004-06-10 Research In Motion Limited Battery connector
AT502552A1 (en) * 2005-10-11 2007-04-15 Fronius Int Gmbh ASSEMBLY METHOD AND CLUTCH ELEMENT FOR A HIGH-PERFORMANCE CONTACT, AND BATTERY CHARGER WITH A CLUTCH DEVICE
CN201130749Y (en) * 2007-08-17 2008-10-08 富士康(昆山)电脑接插件有限公司 Batteries connector
CN101826667A (en) * 2009-03-06 2010-09-08 北京华旗资讯数码科技有限公司 Socket with double plug-in surfaces
JP2011086401A (en) * 2009-10-13 2011-04-28 Japan Aviation Electronics Industry Ltd Electric connection member and method of manufacturing electric connection member
CN202150504U (en) * 2011-07-12 2012-02-22 深圳市沃特玛电池有限公司 Connection structure of battery management system and battery box
CN103220878A (en) * 2012-01-18 2013-07-24 原瑞电池科技股份有限公司 Combined device of thin type battery and circuit board
KR20130095045A (en) * 2012-02-17 2013-08-27 재단법인대구경북과학기술원 Flapping type aerial vehicle
DE102012011511A1 (en) * 2012-06-09 2013-12-12 Volkswagen Aktiengesellschaft Air-conditioned battery system for use in motor vehicle, has rotary valve that connects fluid channel connection port to battery modules, for optional allocation of fluid flow to modules
CN203466319U (en) * 2013-09-09 2014-03-05 番禺得意精密电子工业有限公司 Socket connector and electrical connector assembly
CN105244697A (en) * 2015-10-23 2016-01-13 中山市威奥特电子有限公司 Novel double-side plug-in USB plug
CN106169543A (en) * 2016-07-11 2016-11-30 深圳市统凌科技有限公司 A kind of battery modules and electric motor car thereof
CN206218239U (en) * 2016-12-05 2017-06-06 深圳市道通智能航空技术有限公司 Unmanned vehicle
CN207303437U (en) * 2017-06-27 2018-05-01 上海与德科技有限公司 A kind of connector, battery and terminal
CN207304046U (en) * 2017-08-09 2018-05-01 深圳市时商创展科技有限公司 Back splint battery
CN211980701U (en) * 2020-05-12 2020-11-20 仿翼(北京)科技有限公司 Circuit board, battery, power module and aircraft

Patent Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004049516A1 (en) * 2002-11-27 2004-06-10 Research In Motion Limited Battery connector
AT502552A1 (en) * 2005-10-11 2007-04-15 Fronius Int Gmbh ASSEMBLY METHOD AND CLUTCH ELEMENT FOR A HIGH-PERFORMANCE CONTACT, AND BATTERY CHARGER WITH A CLUTCH DEVICE
CN201130749Y (en) * 2007-08-17 2008-10-08 富士康(昆山)电脑接插件有限公司 Batteries connector
CN101826667A (en) * 2009-03-06 2010-09-08 北京华旗资讯数码科技有限公司 Socket with double plug-in surfaces
JP2011086401A (en) * 2009-10-13 2011-04-28 Japan Aviation Electronics Industry Ltd Electric connection member and method of manufacturing electric connection member
CN202150504U (en) * 2011-07-12 2012-02-22 深圳市沃特玛电池有限公司 Connection structure of battery management system and battery box
CN103220878A (en) * 2012-01-18 2013-07-24 原瑞电池科技股份有限公司 Combined device of thin type battery and circuit board
KR20130095045A (en) * 2012-02-17 2013-08-27 재단법인대구경북과학기술원 Flapping type aerial vehicle
DE102012011511A1 (en) * 2012-06-09 2013-12-12 Volkswagen Aktiengesellschaft Air-conditioned battery system for use in motor vehicle, has rotary valve that connects fluid channel connection port to battery modules, for optional allocation of fluid flow to modules
CN203466319U (en) * 2013-09-09 2014-03-05 番禺得意精密电子工业有限公司 Socket connector and electrical connector assembly
CN105244697A (en) * 2015-10-23 2016-01-13 中山市威奥特电子有限公司 Novel double-side plug-in USB plug
CN106169543A (en) * 2016-07-11 2016-11-30 深圳市统凌科技有限公司 A kind of battery modules and electric motor car thereof
CN206218239U (en) * 2016-12-05 2017-06-06 深圳市道通智能航空技术有限公司 Unmanned vehicle
CN207303437U (en) * 2017-06-27 2018-05-01 上海与德科技有限公司 A kind of connector, battery and terminal
CN207304046U (en) * 2017-08-09 2018-05-01 深圳市时商创展科技有限公司 Back splint battery
CN211980701U (en) * 2020-05-12 2020-11-20 仿翼(北京)科技有限公司 Circuit board, battery, power module and aircraft

Also Published As

Publication number Publication date
CN111509162A (en) 2020-08-07

Similar Documents

Publication Publication Date Title
US7226692B2 (en) Battery lock
US6004158A (en) Electrical connector with secondary locking plates
US7638968B2 (en) Electrical device
CN105846242A (en) Handle-type high-voltage connector
CN211980701U (en) Circuit board, battery, power module and aircraft
CN111509162B (en) Circuit board, battery, power supply module and aircraft
US20190109312A1 (en) Connection structure for power storage module and control device
CN212587561U (en) Battery replacing cabinet control system for portable battery replacing electric vehicle
CN106953044B (en) Battery mounting structure
CN209993649U (en) Quick assembly disassembly formula battery reaches unmanned aerial vehicle who contains it for unmanned aerial vehicle
CN111244667A (en) 120 integrative connector structure of non-switching
CN212257852U (en) Plug-in type connecting device and electric connector
CN221262889U (en) Safety socket of electric vehicle
CN210111234U (en) Wireless cable type electricity taking gun
CN210111109U (en) High-voltage interlocking connector
EP3653338B1 (en) Disassembling tool and battery module using disassembling tool
CN219393921U (en) Energy storage connector
CN206640446U (en) Motor and electric machine fixation structure
CN219643056U (en) Terminal limiting assembly and battery pack
CN110890654A (en) Small-size large-current battery pack connector
CN211670356U (en) Firm portable connector of installation
CN219406931U (en) A modularization quick detach structure and unmanned aerial vehicle for unmanned aerial vehicle
CN214542737U (en) USB module of charging convenient to installation is dismantled
CN211456035U (en) Positioning rubber core
CN213816304U (en) Battery connecting assembly, battery unit, electric device and electric device kit

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant