CN213026386U - Battery cabin section capable of being repeatedly used on bullet - Google Patents
Battery cabin section capable of being repeatedly used on bullet Download PDFInfo
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- CN213026386U CN213026386U CN202021568008.5U CN202021568008U CN213026386U CN 213026386 U CN213026386 U CN 213026386U CN 202021568008 U CN202021568008 U CN 202021568008U CN 213026386 U CN213026386 U CN 213026386U
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- battery
- cabin body
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- speed regulator
- batteries
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- 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
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Abstract
The utility model relates to a repeatedly usable's battery cabin section on bullet belongs to guided missile technical field. Comprises a cabin body, a battery box, a speed regulator and a charging socket; a motor is fixed on the front cover of the battery cabin section; the battery is a rechargeable battery, and a plurality of battery boxes are arranged in the cabin body, so that the utilization rate of the space in the cabin body is maximum; a speed regulator is arranged in the space of the cabin body where the battery box is not arranged; a plurality of batteries are connected in parallel to form a parallel battery pack, the parallel battery pack is placed in a battery box, and a plurality of parallel battery packs are connected in series to form a total battery pack; the positive pole of the total battery pack is connected with the positive pole line of the speed regulator, the negative pole of the total battery pack is connected with the negative pole line of the speed regulator, the load line of the speed regulator is connected with the motor, and the control signal cable of the speed regulator is connected with the missile-borne control system; the charging socket is fixed on the cabin body, and the plurality of parallel battery packs are respectively connected with the charging socket. The short circuit of the battery pack can be avoided, and the battery is effectively protected; in the use, need not to dismantle and to charge.
Description
Technical Field
The utility model relates to a repeatedly usable's battery cabin section on bullet belongs to guided missile technical field.
Background
At present, in the technical field of missiles, a traditional missile-borne storage battery is required to be detached from a missile body during charging and discharging, and meanwhile, the requirement of the missiles on the battery capacity is increased more and more. Therefore, it is necessary to properly design the battery pack structure in a limited space of the pack body.
SUMMERY OF THE UTILITY MODEL
In view of this, the present invention provides a battery compartment section that can be reused in a bullet.
In order to achieve the above purpose, the technical scheme of the utility model is as follows:
a battery cabin section capable of being reused on a bomb comprises a cabin body, a battery box, a speed regulator and a charging socket; a motor is fixed on the front cover of the battery cabin section; the battery is a rechargeable battery, and a plurality of battery boxes are arranged in the cabin body, so that the utilization rate of the space in the cabin body is maximum; a speed regulator is arranged in the space of the cabin body where the battery box is not arranged; a plurality of batteries are connected in parallel to form a parallel battery pack, the parallel battery pack is placed in a battery box, and a plurality of parallel battery packs are connected in series to form a total battery pack; the positive pole of the total battery pack is connected with the positive pole line of the speed regulator, the negative pole of the total battery pack is connected with the negative pole line of the speed regulator, the load line of the speed regulator is connected with the motor, and the control signal cable of the speed regulator is connected with the missile-borne control system; the speed controller is butted with one of two connecting wires of the anode and the cathode of the main battery pack outside the cabin body through a plug; the charging socket is fixed on the cabin body, and the plurality of parallel battery packs are respectively connected with the charging socket; the external dimension of the cabin body is designed according to the space structure of the missile body, and the number of the parallel battery packs is determined according to the electric quantity required by the missile and the total number of the batteries which can be accommodated by the battery box; the battery box is made of non-metal materials, and gaps among batteries and between the batteries are subjected to insulation treatment.
Furthermore, the batteries in the parallel battery pack are connected through electrode plates; when the batteries in the same parallel battery pack cannot be placed in the same battery box, the batteries which are not in the same battery box are connected in parallel through the connecting lines.
Furthermore, the positive wire of the speed regulator is in butt joint with the positive electrode of the main battery pack outside the cabin body through a plug.
Further, the speed controller is arranged at the front part of the cabin body.
Furthermore, insulating glue is coated on gaps among the batteries and the battery box.
Further, the battery box is prepared through 3D printing.
Furthermore, the rear end of the cabin body is provided with a mechanical interface which is in butt joint with other structures of the missile.
Furthermore, the charging socket is fixed on the cabin body through a fixing seat.
Furthermore, an insulating protective cover is arranged outside the charging socket.
Advantageous effects
The space is reasonably utilized, the battery pack is integrally packaged in the battery box made of non-metal materials, the short circuit of the battery pack is avoided, and the battery is protected by gluing; the positive pole of the battery pack is connected with the power supply positive pole line of the speed regulator outside the cabin body through a switch, and on-off control is performed during take-off and landing, so that the operation is convenient, and the reliability is high; in the use, when the electric quantity is not enough, can charge in good time, need not to dismantle, use repeatedly, save the cost.
Drawings
Fig. 1 is a schematic structural view of a battery compartment section according to the present invention;
fig. 2 is a schematic view of the connection between the battery compartment section and the external structure according to the present invention;
the missile-borne control system comprises a battery cabin section 1, a cabin body 2, batteries 3, a first battery box 4, a second battery box 5, a third battery box 6, a speed regulator 7, a motor 8, a front cover 9, a charging socket 10, a fixed seat 11, an insulating protective cover 12, a missile body 13 and a missile-borne control system 14.
Detailed Description
The present invention will be described in further detail with reference to specific examples.
As shown in fig. 1-2, a battery compartment section 1 which is reusable on a bullet comprises a compartment body 2, batteries 3, a battery box, a speed governor 7 and a charging socket 10; a motor 8 is fixed on a front cover 9 of the battery cabin section 1; wherein, the battery 3 is a chargeable battery, and a plurality of battery boxes are arranged in the cabin body 2, so that the space utilization rate in the cabin body 2 is maximum; a speed regulator 7 is arranged in the space of the cabin body 2 where no battery box is arranged; a plurality of batteries 3 are connected in parallel to form a parallel battery pack, the parallel battery pack is placed in a battery box, and a plurality of parallel battery packs are connected in series to form a total battery pack; the positive pole of the total battery pack is connected with the positive pole line of the speed regulator 7, the negative pole of the total battery pack is connected with the negative pole line of the speed regulator 7, the load line of the speed regulator 7 is connected with the motor, and the control signal cable of the speed regulator is connected with the missile-borne control system 14; the speed controller 7 is butted with one of the two connecting wires of the anode and the cathode of the main battery pack outside the cabin body through a plug; the charging socket 10 is fixed on the cabin 2, and the plurality of parallel battery packs are respectively connected with the charging socket; the external dimension of the cabin body 2 is designed according to the space structure of the missile body 13, and the number of the parallel battery packs is determined according to the electric quantity required by the missile and the total number of the batteries 3 which can be accommodated by the battery box; the battery box is made of non-metal materials, and gaps among the batteries 3 and between the batteries 3 and the battery box are subjected to insulation treatment.
The batteries 3 in the parallel battery pack are connected through electrode plates; when the batteries 3 in the same parallel battery pack cannot be placed in the same battery box, the batteries not in the same battery box are connected in parallel through the connecting lines.
And the positive wire of the speed regulator 7 is butted with the positive electrode of the main battery pack outside the cabin body 2 through a plug.
The governor 7 is arranged at the front part of the nacelle 2.
And the rear end of the cabin body 2 is provided with a mechanical interface which is in butt joint with other structures of the missile.
The charging socket 10 is fixed on the cabin through a fixing seat 11.
An insulating protective cover 12 is arranged outside the charging socket 10.
Example 1
On a certain type of missile, the battery 3 adopts a 21700 battery. And 5 batteries and 3 groups of batteries are connected in parallel to form a parallel battery pack, and then 12 parallel battery packs are connected in series to form an overall battery pack. In order to fully utilize the limited space of the cabin body 2, the parallel battery packs are arranged in a first battery box 4, a second battery box 5 and a third battery box 6 for 3D printing during welding, wherein, under the condition that a group of 5 batteries needing to be connected in parallel are arranged in two different battery boxes, the 5 batteries are connected through cables to realize the parallel connection of the 5 batteries; insulating glue is coated on gaps among the batteries 3, gaps among the batteries 3 and the inside of the first battery box 4, gaps among the batteries 3 and the inside of the second battery box 5 and gaps among the batteries 3 and the inside of the third battery box 6, so that the battery pack is reinforced and protected; the first battery compartment 4, the second battery compartment 5, and the third battery compartment 6 are mounted inside the cabin 2. The speed regulator 7 is arranged on the rear end face of the first battery box 4, a power supply negative wire of the speed regulator 7 is connected with the negative electrode of the main battery pack, and a power supply positive wire of the speed regulator 7 is butted with the positive electrode of the main battery pack outside the cabin body 6 through a plug, so that the power-on and power-off operation can be performed, and the operation is convenient and reliable; the motor 8 is fixed on the front end face of the cabin body 2 through the front cover 9, the motor can be replaced without disassembling the internal structure of the battery cabin section 1, three cables of the motor 8 are connected with three load lines of the speed regulator 7, the total battery pack provides power for the motor 8, a control signal cable of the speed regulator 7 is connected with a missile-borne control system 14 of a missile, and the speed regulator 7 controls the rotating speed of the motor 8. The charging socket 10 is installed on the cabin 2 through a fixed seat 11, the positive and negative poles of each parallel battery pack are connected with the charging socket 10 through cables, the charging socket 10 can be connected with an external charger, the remaining electric quantity of each group of current batteries can be displayed through the charger, and each battery 3 can be charged; an insulating protective cover 12 is arranged outside the charging socket 10, the insulating protective cover 12 is installed on the fixed seat 11, the insulating protective cover 12 is made of a non-metal material, and foreign matters can be prevented from entering the charging socket 10 while the charging socket 10 is subjected to insulating protection. The rear end face of the cabin body 2 is provided with a mechanical interface which is convenient to butt joint with the rest parts of the missile.
In summary, the present invention includes but is not limited to the above embodiments, and any equivalent substitutions or partial modifications made under the spirit and principle of the present invention are considered to be within the protection scope of the present invention.
Claims (7)
1. A battery compartment section that can be reused on a bullet, characterized in that: comprises a cabin body (2), a battery (3), a battery box, a speed regulator (7) and a charging socket (10); a motor (8) is fixed on a front cover (9) of the battery compartment section (1); the batteries (3) are rechargeable batteries, and a plurality of battery boxes are arranged in the cabin body (2) to maximize the space utilization rate in the cabin body (2); a speed regulator (7) is arranged in the space of the cabin body (2) where no battery box is arranged; a plurality of batteries (3) are connected in parallel to form a parallel battery pack, the parallel battery pack is placed in a battery box, and a plurality of parallel battery packs are connected in series to form a total battery pack; the positive pole of the total battery pack is connected with the positive pole line of the speed regulator (7), the negative pole of the total battery pack is connected with the negative pole line of the speed regulator (7), the load line of the speed regulator (7) is connected with the motor, and the control signal cable of the speed regulator is connected with the missile-borne control system (14); the speed controller (7) is butted with one of the two connecting wires of the anode and the cathode of the main battery pack outside the cabin body through a plug; the charging socket (10) is fixed on the cabin body (2), and the plurality of parallel battery packs are respectively connected with the charging socket; the overall dimension of the cabin body (2) is designed according to the space structure of the missile body (13), and the number of the parallel battery packs is determined according to the electric quantity required by the missile and the total number of the batteries (3) which can be accommodated by the battery box; the battery box is made of non-metal materials, and gaps among the batteries (3) and between the batteries (3) and the battery box are subjected to insulation treatment.
2. A resiliently reusable battery compartment section as claimed in claim 1, wherein: the batteries (3) in the parallel battery pack are connected through electrode plates; when the batteries (3) in the same parallel battery pack cannot be placed in the same battery box, the batteries which are not in the same battery box are connected in parallel through connecting wires.
3. A resiliently reusable battery compartment section as claimed in claim 1, wherein: and the positive wire of the speed regulator (7) is butted with the positive electrode of the main battery pack outside the cabin body (2) through a plug.
4. A resiliently reusable battery compartment section as claimed in claim 1, wherein: the speed controller (7) is arranged at the front part of the cabin body (2).
5. A resiliently reusable battery compartment section as claimed in claim 1, wherein: the rear end of the cabin body (2) is provided with a mechanical interface which is in butt joint with other structures of the missile.
6. A resiliently reusable battery compartment section as claimed in claim 1, wherein: the charging socket (10) is fixed on the cabin body through a fixing seat (11).
7. A resiliently reusable battery compartment section as claimed in claim 1, wherein: an insulating protective cover (12) is arranged outside the charging socket (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021568008.5U CN213026386U (en) | 2020-08-01 | 2020-08-01 | Battery cabin section capable of being repeatedly used on bullet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021568008.5U CN213026386U (en) | 2020-08-01 | 2020-08-01 | Battery cabin section capable of being repeatedly used on bullet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213026386U true CN213026386U (en) | 2021-04-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021568008.5U Active CN213026386U (en) | 2020-08-01 | 2020-08-01 | Battery cabin section capable of being repeatedly used on bullet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213026386U (en) |
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2020
- 2020-08-01 CN CN202021568008.5U patent/CN213026386U/en active Active
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