CN217404835U - Power-down protection circuit and power supply circuit of unmanned helicopter flight control computer - Google Patents
Power-down protection circuit and power supply circuit of unmanned helicopter flight control computer Download PDFInfo
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- CN217404835U CN217404835U CN202221121536.5U CN202221121536U CN217404835U CN 217404835 U CN217404835 U CN 217404835U CN 202221121536 U CN202221121536 U CN 202221121536U CN 217404835 U CN217404835 U CN 217404835U
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Abstract
The utility model discloses a power-down protection circuit and power supply circuit of unmanned helicopter flight control computer, above-mentioned electric protection circuit includes tank circuit, tank circuit is connected with the output of external power source and the input of DC-DC step-down circuit respectively through first unidirectional conduction switch circuit, and tank circuit is connected with the input of DC-DC step-down circuit through second unidirectional conduction switch circuit; the power supply circuit comprises a DC-DC voltage reduction circuit and the power failure protection circuit, wherein the DC-DC voltage reduction circuit is connected between an external power supply and the unmanned helicopter flight control computer circuit. The circuit structure of the invention is simple, and no logic judgment and logic processing link exists, thus not only reducing the production cost and reducing the space of the circuit board, but also improving the response speed of the power-down protection, reducing the error rate of the power-down protection mechanism and ensuring the reliability of the power-down protection of the flight control computer.
Description
Technical Field
The utility model relates to a power down protection circuit and power supply circuit of unmanned helicopter flight control computer.
Background
The circuit structure of the prior art is shown in fig. 1 and mainly comprises a backup battery, a voltage comparison circuit and a DC-DC booster circuit. When the external power supply normally supplies power, the external power supply directly supplies power to the flight control computer after passing through the DC-DC voltage reduction circuit; when the external power supply is abnormally powered off, the voltage comparison circuit sends an alarm signal to the flight control computer after logic judgment and logic processing, then the backup battery discharges, the voltage is boosted and stabilized to a set voltage value through the DC-DC booster circuit, the boosted voltage supplies power to the flight control computer circuit, and the power failure protection effect is achieved only after a series of complex processes are completed. The circuit has the problems of complex structure, large occupied circuit board space, high production cost, low response speed, high error rate and the like due to the existence of logic judgment and logic processing links.
Therefore, in order to solve the above problems, a power failure protection circuit for an unmanned helicopter flight control computer, which is developed to improve the response speed of power failure protection, reduce the error rate of an electric protection mechanism, and have a simple circuit structure, is a technical problem to be solved urgently.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a power down protection circuit and supply circuit of unmanned helicopter flight control computer to there is the problem that circuit structure is complicated and the reliability is poor in solving present unmanned helicopter flight control computer protection circuit.
In order to solve the technical problem, the utility model provides a power down protection circuit of unmanned helicopter flight control computer, this power down protection circuit include tank circuit, and tank circuit is connected with external power source's output and DC-DC step-down circuit's input respectively through first one-way switch circuit that switches on, and tank circuit is connected with DC-DC step-down circuit's input through the one-way switch circuit that switches on of second.
When the external power supply normally supplies power, the external power supply directly supplies power to the flight control computer circuit after passing through the DC-DC voltage reduction circuit; when the external power supply is abnormally powered off, the energy storage circuit directly discharges to the DC-DC voltage reduction circuit through the second unidirectional conduction switch circuit and then directly supplies power to the flight control computer. The power-down protection circuit is designed by adopting a simpler circuit structure, simplifies a power-down protection mechanism, improves the response speed, reduces the error rate, and solves the problems of low response speed and high error rate in the prior art.
Further, the tank circuit includes a capacitor C connected to the first unidirectional conducting switch circuit and the second unidirectional conducting switch circuit, respectively. By adopting the super large capacitor C to store and release electric quantity, instantaneous large current and continuous current can be provided when the super large capacitor C discharges, so that the load of the flight control computer can work normally and durably.
Further, the first unidirectional switch circuit comprises a first diode D1 connected in series, the anode of the first diode D1 is connected with the output end of the external power supply and the input end of the DC-DC voltage reduction circuit respectively, and the cathode of the first diode D1 is connected with the energy storage circuit. The diode is adopted to realize the unidirectional current transmission, so that the charging path and the discharging path are independent and do not interfere with each other, and the discharging path has directivity.
Further, the first unidirectional conducting switch circuit further comprises a resistor R connected between the cathode of the first diode D1 and the tank circuit. The resistor R can play a role in charging and current limiting so as to ensure that the energy storage circuit is charged within a safe current range, the service life of the energy storage circuit is prolonged, and the current pressure of an external power supply can be reduced.
Further, the second unidirectional conducting switch circuit comprises a second diode D2, a cathode of the second diode D2 is connected with the input terminal of the DC-DC step-down circuit, and an anode of the second diode D2 is connected with a connection node between the first unidirectional conducting switch circuit and the tank circuit. The diode is adopted to realize the unidirectional current transmission, so that the charging path and the discharging path are independent and do not interfere with each other, and the discharging path has directivity.
The power-down protection circuit in the application adopts common discrete components, reduces the production cost, solves the situation of high cost in the prior art, simultaneously enables the design space of a circuit board to be more saved, has faster response speed and lower error rate, and ensures the power-down protection reliability of the flight control computer.
Furthermore, the utility model also discloses an unmanned helicopter flies to control computer supply circuit, fly the above-mentioned power down protection circuit of DC-DC step-down circuit between the control computer circuit including connecting external power source and unmanned helicopter. The power supply circuit of the unmanned helicopter flight control computer adopts the power-down protection circuit, and can provide a reliable power-down protection function for the flight control computer.
The utility model has the advantages that: the circuit of the invention has simple structure and no logic judgment and logic processing links, thereby not only reducing the production cost and the space of the circuit board, but also improving the response speed of power-down protection, reducing the error rate of a power-down protection mechanism and ensuring the reliability of the power-down protection of the flight control computer.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a prior art circuit configuration;
fig. 2 is a schematic circuit diagram of an embodiment of the present invention.
Detailed Description
The power-down protection circuit of the unmanned helicopter flight control computer shown in fig. 1 comprises an energy storage circuit, wherein the energy storage circuit is respectively connected with the output end of an external power supply and the input end of a DC-DC voltage reduction circuit through a first one-way conduction switch circuit, and the energy storage circuit is connected with the input end of the DC-DC voltage reduction circuit through a second one-way conduction switch circuit.
When the external power supply normally supplies power, the external power supply directly supplies power to the flight control computer circuit after passing through the DC-DC voltage reduction circuit; when the external power supply is abnormally powered off, the energy storage circuit directly discharges to the DC-DC voltage reduction circuit through the second unidirectional conduction switch circuit and then directly supplies power to the flight control computer. The power-down protection circuit is designed by adopting a simpler circuit structure, simplifies a power-down protection mechanism, improves the response speed, reduces the error rate (the error rate is almost zero), and solves the problems of low response speed and high error rate in the prior art.
According to one embodiment of the application, the tank circuit comprises a capacitor C connected to the first and second unidirectional conducting switch circuits, respectively. By adopting the super large capacitor C to store and release electric quantity, instantaneous large current and continuous current can be provided when the super large capacitor C discharges, so that the load of the flight control computer can work normally and durably.
According to an embodiment of the application, the first unidirectional conducting switch circuit comprises a first diode D1 connected in series, an anode of the first diode D1 is connected with an output end of an external power supply and an input end of the DC-DC voltage reduction circuit respectively, and a cathode of the first diode D1 is connected with the energy storage circuit. The diode is adopted to realize unidirectional current transmission, so that the charging path and the discharging path are independent and do not interfere with each other, and the discharging path has directivity.
According to an embodiment of the present application, the first unidirectional conducting switch circuit further comprises a resistor R connected between the cathode of the first diode D1 and the tank circuit. The resistor R can play a role in charging and current limiting so as to ensure that the energy storage circuit is charged within a safe current range, the service life of the energy storage circuit is prolonged, and the current pressure of an external power supply can be reduced.
According to an embodiment of the application, the second unidirectional conducting switch circuit comprises a second diode D2, a cathode of the second diode D2 is connected with the input terminal of the DC-DC voltage step-down circuit, and an anode of the second diode D2 is connected with the connection node between the first unidirectional conducting switch circuit and the tank circuit. The diode is adopted to realize the unidirectional current transmission, so that the charging path and the discharging path are independent and do not interfere with each other, and the discharging path has directivity.
The power-down protection circuit in the application adopts common discrete components, reduces the production cost, solves the situation of high cost in the prior art, simultaneously ensures that the design space of the circuit board is more saved, the response speed is faster and the error rate is lower, and ensures the power-down protection reliability of the flight control computer.
Furthermore, the utility model also discloses an unmanned helicopter flies to control computer supply circuit, fly the above-mentioned power down protection circuit of DC-DC step-down circuit between the control computer circuit including connecting external power source and unmanned helicopter. The power supply circuit of the flight control computer of the unmanned helicopter adopts the power-down protection circuit, and can provide a reliable power-down protection function for the flight control computer.
Finally, it is noted that the above embodiments are only used for illustrating the technical solutions of the present invention and not for limiting, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the technical solutions of the present invention can be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should be covered by the scope of the claims of the present invention.
Claims (6)
1. The power-down protection circuit of the unmanned helicopter flight control computer is characterized by comprising an energy storage circuit, wherein the energy storage circuit is respectively connected with the output end of an external power supply and the input end of a DC-DC voltage reduction circuit through a first one-way conduction switch circuit, and the energy storage circuit is connected with the input end of the DC-DC voltage reduction circuit through a second one-way conduction switch circuit.
2. The power-down protection circuit of the unmanned helicopter flight control computer of claim 1, wherein the tank circuit comprises a capacitor C connected to the first unidirectional conductive switch circuit and the second unidirectional conductive switch circuit, respectively.
3. The power-fail protection circuit of the unmanned helicopter flight control computer of claim 1, wherein the first one-way conduction switch circuit comprises a first diode D1 connected in series, an anode of the first diode D1 is connected to an output terminal of an external power supply and an input terminal of the DC-DC voltage reduction circuit, respectively, and a cathode of the first diode D1 is connected to the energy storage circuit.
4. The power-down protection circuit for the unmanned helicopter flight control computer of claim 3, wherein the first one-way conduction switch circuit further comprises a resistor R connected between the cathode of the first diode D1 and the tank circuit.
5. The power-fail protection circuit of the unmanned helicopter flight control computer of claim 1, wherein the second unidirectional conducting switch circuit comprises a second diode D2, a cathode of the second diode D2 is connected to an input terminal of the DC-DC voltage reduction circuit, and an anode of the second diode D2 is connected to a connection node between the first unidirectional conducting switch circuit and the energy storage circuit.
6. A power supply circuit for an unmanned helicopter flight control computer, which is characterized by comprising a DC-DC voltage reduction circuit and a power failure protection circuit according to any one of claims 1 to 4, wherein the DC-DC voltage reduction circuit is connected between an external power supply and the unmanned helicopter flight control computer circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221121536.5U CN217404835U (en) | 2022-05-11 | 2022-05-11 | Power-down protection circuit and power supply circuit of unmanned helicopter flight control computer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221121536.5U CN217404835U (en) | 2022-05-11 | 2022-05-11 | Power-down protection circuit and power supply circuit of unmanned helicopter flight control computer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217404835U true CN217404835U (en) | 2022-09-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221121536.5U Active CN217404835U (en) | 2022-05-11 | 2022-05-11 | Power-down protection circuit and power supply circuit of unmanned helicopter flight control computer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217404835U (en) |
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2022
- 2022-05-11 CN CN202221121536.5U patent/CN217404835U/en active Active
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