CN204597451U - A kind of aircraft protective circuit - Google Patents
A kind of aircraft protective circuit Download PDFInfo
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- CN204597451U CN204597451U CN201520305720.9U CN201520305720U CN204597451U CN 204597451 U CN204597451 U CN 204597451U CN 201520305720 U CN201520305720 U CN 201520305720U CN 204597451 U CN204597451 U CN 204597451U
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- voltameter
- resistance
- aircraft
- resistive module
- circuit
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- 230000001681 protective effect Effects 0.000 title claims abstract description 15
- 238000013461 design Methods 0.000 abstract description 3
- 238000001514 detection method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008280 blood Substances 0.000 description 1
- 210000004369 blood Anatomy 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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Abstract
The utility model discloses a kind of aircraft protective circuit; comprise battery, aircraft, logic switch and the resistive module of connecting successively; resistive module comprises the resistance of N number of series connection, and also comprise the voltameter in parallel with resistive module, voltameter is also connected with logic switch.Design of the present utility model breaches the extreme value scope of voltameter; expand the operating voltage of voltameter or the scope of electric current; need big current or high-tension workplace also can normal use voltameter at some; and effectively can protect power consumption equipment; protection aircraft and voltameter, avoid aircraft and voltameter to burn.
Description
Technical field
The utility model relates to vehicle technology field, specifically, is a kind of aircraft protective circuit.
Background technology
In the design of circuit, the voltameter connected in general circuit has an extreme value worked, and may be a voltage extremity or a current limit.In other words, electricity in respect of a maximum carrying magnitude of voltage and a minimum functional resistance value, with the power consumption equipment in this protective circuit.
If the resistance value of short-circuit protection signals collecting end series connection is too small, the testing result of voltameter will be had influence on, very large error can be caused, and power consumption equipment can be made normally to work; If electric current is excessive, then the magnitude of voltage at these resistive module two ends likely can exceed the upper limit detection magnitude of voltage of voltameter, voltameter may be made normally to work, also probably can burn out the power consumption equipment be connected in circuit.
At present, the occupation mode of voltameter is and certain resistor coupled in parallel in circuit, therefore its operating voltage is identical with the voltage of above-mentioned resistance, and operating current is the half of main circuit current value, and therefore its current limit that can detect is only the half of main circuit current value.
Therefore, when the process of whole circuit working, voltage or electric current just cannot normally work after breaking through this extreme value, also just cannot play protective circuit, prevent from burning the function of device.
And under the immovable condition of existing voltameter, how under the prerequisite of protection power consumption equipment, to break through this extreme value and can work under larger current value, become the direction of those skilled in the art's research.
Utility model content
For overcoming the defect that cannot break through voltameter work extreme value in prior art, the utility model provides a kind of aircraft protective circuit, achieves the object improving voltameter operating current or voltage.
For achieving the above object, the utility model discloses a kind of aircraft protective circuit, comprise battery, aircraft, logic switch and the resistive module of connecting successively, resistive module comprises the resistance of N number of series connection, also comprise the voltameter in parallel with resistive module, voltameter is also connected with logic switch; Wherein, N be not less than 2 integer.
The present invention innovatively uses multiple resistance, and voltameter connects the two ends of any one resistance or multiple series resistance respectively.Therefore, the voltage of voltameter is identical with the voltage at any resistance two ends, and its limiting current is increased to the current value of way circuit by the half of original way circuit current value.When circuit may break down, disconnect logic switch in time, the safety of protection aircraft and voltameter.
Further, the two ends of resistive module are current acquisition end, and voltameter has four binding posts, and two binding posts are connected to resistive module two ends, and two other binding post is connected to the two ends of one or two above series resistances.
Further, the resistance of each resistance in resistive module is identical.
Further, the resistance of each resistance in resistive module is different.
The beneficial effects of the utility model are: design of the present invention breaches the extreme value scope of voltameter; expand the operating voltage of voltameter or the scope of electric current; need big current or high-tension workplace also can normal use voltameter at some; and effectively can protect power consumption equipment; protection aircraft and voltameter, avoid aircraft and voltameter to burn.
Accompanying drawing explanation
Fig. 1 is aircraft protective circuit connection diagram.
In figure,
1, battery; 2, aircraft; 3, logic switch; 4, voltameter; 40, current acquisition end; 41, short-circuit protection signals collecting end; 50, the first resistance; 51, the second resistance; 52, N resistance.
Embodiment
Below in conjunction with accompanying drawing, explanation is explained in detail to structure of the present utility model.
Aircraft protective circuit as shown in Figure 1, comprise battery 1, aircraft 2, logic switch 3 and the resistive module of connecting successively, resistive module comprises the resistance of N number of series connection, also comprise the voltameter 4 with four binding posts, two binding posts are connected to resistive module two ends, and two other binding post is connected to the two ends of one or two above series resistances; Voltameter 4 is also connected with logic switch 3; Wherein, N be not less than 2 integer.
During actual enforcement, each resistance in resistive module can be identical; Certainly, the resistance of each resistance in resistive module also can be different.
For the ease of distinguishing; resistive module can comprise first resistance 50, second resistance 51 and the N resistance 52 of connecting successively; the two ends of the first resistance 50 can be current acquisition end 40 and short-circuit protection signals collecting end 41 respectively; the two ends of the second resistance 51 can be short-circuit protection signals collecting end 41, but are not limited to above-mentioned connected mode.
The present embodiment selects the voltameter 4 chip BQ20Z655-R1 of Texas Instrument; in the circuit of this embodiment; resistive module comprises the first resistance 50, second resistance 51; resistance value is all m milliohm; the two ends that the two ends of the first resistance 50 are respectively current acquisition end 40 and short-circuit protection signals collecting end 41, second resistance 51 are all short-circuit protection signals collecting end 41.Current acquisition end 40 and short-circuit protection signals collecting end 41, in order to distinguish, being convenient to understanding, separate by the utility model, during practical application, and the same position of two kinds of collection terminals likely in series circuit.
It should be noted that, it is v millivolt that the upper limit of the voltameter 4 that the present embodiment is used detects voltage, and the series resistance of current acquisition end 40 normally will work at the above guarantee voltameter 4 of 2m milliohm.Because voltameter 4 of the present utility model is respectively at each resistor coupled in parallel, so the magnitude of voltage at its two ends is the product by the electric current of each resistance and the resistance of this resistance.
After logic switch 3 in circuit is opened, battery 1 just starts as aircraft 2 is powered, and on aircraft 2, the supply current of battery 1 can reach u peace.
If it is u1 peace that current acquisition end 40 collects supply current; and u1 is less than or equal to u, then the magnitude of voltage v1=m*u1 at series resistance two ends that measures of short-circuit protection signals collecting end 41, and v1<=v millivolt; voltameter 4 and aircraft 2 can normally work
When the electric current u2 on aircraft 2 circuit is more than u ampere-hour; likely burn out aircraft 2; the now magnitude of voltage v2=m*u2>v at series resistance two ends that measures of short-circuit protection signals collecting end 41, now voltameter 4 control logic switch 3 disconnects, to protect aircraft 2 and voltameter 4.
Due to the circuit in the present invention, detection electric current that in the present embodiment, voltameter 4 can carry is set up from 0.5u and has been raised to u peace, substantially increase the scope of application and the job security of voltameter 4, also protect the fail safe of equipment in circuit.
The utility model is worked by following mode: after logic switch 3 is opened; battery 1 starts to power to aircraft 2; current acquisition end 40 collects the current value by aircraft 2; short-circuit protection signals collecting end 41, according to the resistance value of the current value collected and resistive module, obtains the magnitude of voltage at series resistance two ends.
If the magnitude of voltage that voltameter 4 measures is greater than voltameter 4 capping magnitude of voltage, then voltameter 4 control logic switch 3 open circuit is with the power consumption equipment in protective circuit and voltameter 4; If the magnitude of voltage that voltameter 4 measures is in normal range (NR), then voltameter 4 just can measure the current electric quantity of battery 1 according to the data collected.
Voltameter 4 of the present utility model expands the scope of application of voltameter 4 by the resistive module in parallel with it.
The foregoing is only preferred embodiment of the present utility model, not in order to limit the utility model, all do in the utility model flesh and blood any amendment, equivalent to replace and simple modifications etc., all should be included within protection range of the present utility model.
Claims (4)
1. an aircraft protective circuit, it is characterized in that: comprise battery (1), aircraft (2), logic switch (3) and the resistive module of connecting successively, resistive module comprises the resistance of N number of series connection, also comprise the voltameter (4) in parallel with resistive module, voltameter is also connected with logic switch; Wherein, N be not less than 2 integer.
2. aircraft protective circuit according to claim 1, is characterized in that: voltameter has four binding posts, and two binding posts are connected to resistive module two ends, and two other binding post is connected to the two ends of one or two above series resistances.
3. aircraft protective circuit according to claim 1 and 2, is characterized in that: the resistance of each resistance in resistive module is identical.
4. aircraft protective circuit according to claim 1 and 2, is characterized in that: the resistance of each resistance in resistive module is different.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520305720.9U CN204597451U (en) | 2015-05-13 | 2015-05-13 | A kind of aircraft protective circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520305720.9U CN204597451U (en) | 2015-05-13 | 2015-05-13 | A kind of aircraft protective circuit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204597451U true CN204597451U (en) | 2015-08-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520305720.9U Active CN204597451U (en) | 2015-05-13 | 2015-05-13 | A kind of aircraft protective circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204597451U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104836195A (en) * | 2015-05-13 | 2015-08-12 | 零度智控（北京）智能科技有限公司 | Aircraft protection circuit |
-
2015
- 2015-05-13 CN CN201520305720.9U patent/CN204597451U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104836195A (en) * | 2015-05-13 | 2015-08-12 | 零度智控（北京）智能科技有限公司 | Aircraft protection circuit |
| CN104836195B (en) * | 2015-05-13 | 2018-05-08 | 天津远翥科技有限公司 | A kind of aircraft protects circuit |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Aircraft protection circuit Effective date of registration: 20170327 Granted publication date: 20150826 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.)|Beijing Civil Aviation Heyuan Investment Center (L.P.) Pledgor: ZEROTECH (BEIJING) INTELLIGENCE TECHNOLOGY Co.,Ltd. Registration number: 2017990000242 |
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| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20190906 Granted publication date: 20150826 |
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| PD01 | Discharge of preservation of patent | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20220406 Granted publication date: 20150826 |
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| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20220406 Granted publication date: 20150826 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20221008 Granted publication date: 20150826 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.)|Beijing Civil Aviation Heyuan Investment Center (L.P.) Pledgor: ZEROTECH (BEIJING) INTELLIGENCE TECHNOLOGY Co.,Ltd. Registration number: 2017990000242 |
|
| PD01 | Discharge of preservation of patent | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20220918 Granted publication date: 20150826 |
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| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20220918 Granted publication date: 20150826 |