CN115268303A - Unmanned aerial vehicle high-power electrical load on-off circuit and control method thereof - Google Patents

Abstract

The invention provides a high-power electrical load on-off circuit of an unmanned aerial vehicle and a control method thereof. The circuit includes an on-board power supply, an on-board satellite communication signal transceiver device, an electrical load, an analog signal box and an electrical distribution box. The communication signal transceiver equipment is connected with the analog signal box, the analog signal box is respectively connected with the on-board power supply and the electrical distribution box, and the electrical power distribution box is respectively connected with the electrical load and the on-board power supply. The airborne satellite signal transceiver equipment receives ground control commands and transmits them to the analog signal box to control the work of the optocoupler. The electrical distribution box controls the disconnection of the on-board power supply and the electrical load. The invention provides an on-off circuit of a high-power electrical load of an unmanned aerial vehicle and a control method thereof, and the connection between the high-power electrical load inside the unmanned aerial vehicle and the on-board power supply can be controlled by a low-power signal source. The control circuits are physically isolated by optocouplers, which improves the safety of the UAV control circuits.

Description

An unmanned aerial vehicle high-power electrical load on-off circuit and its control method

technical field

The invention relates to the field of electrical load control of an unmanned aerial vehicle, in particular to an on-off circuit of a high-power electrical load of an unmanned aerial vehicle and a control method thereof.

Background technique

The electrical system is one of the important components of the UAV system. It provides stable and reliable electrical energy for the various systems of the UAV. The stable operation of the electrical system is the basis for ensuring the normal operation of the various systems of the UAV. The power distribution of traditional aircraft to high-power electrical loads is to directly control the on-off of the relay to control the on-off of the contactor. This kind of power distribution requires high input power at the control end and high requirements for the circuit system. Because it is directly connected, there is no The transition circuit also has a great influence on the safety performance of the circuit operation of the UAV. At this stage, the functions equipped with UAVs are gradually increasing. Due to the inconsistent operating power of different functional modules, the power supply stability of the high-power equipment on board and the safety of the electrical power distribution system are required to be higher. In order to solve the above problems, it is now necessary to find a The power distribution design of controlling high-power loads with low-power signal sources meets the electrical power distribution needs in the current field, and designs a stable, safe and reliable UAV electrical load power distribution control method.

Contents of the invention

In order to solve the technical problem of the appeal, the present invention provides a high-power electrical load on-off circuit for drones and its control method. By setting a triode in the control circuit, the automatic power-on and power-off functions of the high-power electrical load of the drone are realized. , and physically isolate the control signal and the control circuit to improve the safety protection of the control system.

An unmanned aerial vehicle high-power electrical load on-off circuit, including on-board power supply, on-board satellite communication signal transceiver equipment, electrical load, analog signal box and electrical distribution box, on-board satellite communication signal transceiver equipment and analog signal box The control input terminal is connected, the analog signal box is connected with the onboard power supply and the electrical distribution box respectively, the output terminal of the onboard power supply is connected with the input terminal of the electrical distribution box, and the output terminal of the electrical distribution box is connected with the electrical load.

Preferably, the analog signal box includes an optocoupler triode, a Darlington circuit, an output amplifier circuit and an insurance FU, the input end of the optocoupler triode is connected to the airborne satellite communication signal transceiver device, and the output end is connected to the Darlington circuit; The circuit is connected with the output amplifier circuit; the on-board power supply provides working power for the output amplifier circuit through the fuse FU, and the output amplifier circuit outputs control electrical signals to the electrical distribution box through the E terminal.

Preferably, the electrical distribution box includes a relay and a contactor, the relay control input terminal is connected to the output amplifier circuit output terminal, the two input terminals of the contactor are respectively connected to the onboard power supply, the contactor control output terminal is connected to the relay input terminal, and the contactor control output terminal is connected to the relay input terminal. The output terminal of the device is connected to the electrical load.

Preferably, the onboard power supply is an aircraft 28V DC power supply.

The method for controlling the on-off circuit of the high-power electrical load of the unmanned aerial vehicle includes the following steps:

A. The ground equipment sends a control signal to the airborne satellite communication signal transceiver equipment;

B. The airborne satellite communication signal transceiver equipment transmits the control signal to the analog signal box;

C. The analog signal box transmits control electrical signals to the electrical distribution box according to the received signal;

D. The electrical distribution box controls the connection and disconnection between the onboard power supply and the electrical load according to the received control electrical signal.

Preferably, in step C, the airborne satellite communication signal transceiver device controls the working state of the optocoupler triode through the received control command, controls the Darlington circuit to be turned on and off through the optocoupler triode working state, and controls the output through the Darlington circuit The amplifying circuit is turned on and off, so that the control signal is transmitted to the electrical distribution box; in step D, the relay receives the control electrical signal from the output amplifying circuit, controls the contactor to be turned off, and realizes the electrical load and the onboard Power on and off.

Preferably, the current intensity of the control signal in step A is 1.6mA-5mA.

Preferably, in step C, when the Darlington circuit is turned on by the output amplifier circuit, the amplified current intensity of the output terminal connected to the electrical distribution box is 35mA-63mA.

Preferably, the working current intensity of the electrical load is 20A-50A.

The present invention provides a high-power electrical load on-off circuit for an unmanned aerial vehicle and its control method, which can control the connection between the high-power electrical load inside the unmanned aerial vehicle and the on-board power supply through a low-power signal source. The physical isolation between the control circuits improves the safety of the UAV control circuit.

Description of drawings

Figure 1 is a schematic diagram of the electric high-power load on-off circuit of the drone;

As shown in the figure: 1-airborne satellite communication signal transceiver equipment; 2-analog signal box; 3-electrical distribution box; 4-airborne power supply; 5-electrical load; 21-optocoupler transistor; 22-Darlington Circuit; 23-output amplifier circuit; 24-insurance FU; 31-relay; 32-contactor.

Detailed ways

The present invention will be further described in detail below in conjunction with specific embodiments.

It should be noted that the structures, proportions, sizes, etc. drawn in the drawings of this specification are only used to match the content disclosed in the specification, for those who are familiar with this technology to understand and read, and are not used to limit the conditions for the implementation of the invention, so Without technical substantive significance, any modification of structure, change of proportional relationship or adjustment of size shall still fall within the technology disclosed in the present invention without affecting the effect and purpose of the present invention. within the scope of the content. At the same time, terms such as "upper", "lower", "left", "right", and "middle" quoted in this specification are only for convenience of description, and are not used to limit the scope of the present invention. , the change or adjustment of its relative relationship, without substantive changes in the technical content, should also be regarded as the scope of the present invention that can be implemented.

A high-power electrical load on-off circuit for a drone as shown in Figure 1 includes an on-board power supply 4, an on-board satellite communication signal transceiver device 1, an electrical load 5, an analog signal box 2 and an electrical distribution box 3, The airborne satellite communication signal transceiver device 1 is connected to the control input end of the analog signal box 2, the analog signal box 2 is respectively connected to the onboard power supply 4 and the electrical power distribution box 3, and the output end of the airborne power supply 4 is input to the electrical power distribution box 3 The output terminal of the electrical distribution box 3 is connected to the electrical load 5. In this circuit, the on-board power supply 4 used is the 28V DC power supply of the aircraft.

The analog signal box includes an optocoupler transistor 21, a Darlington circuit 22, an output amplifier circuit 23 and a fuse FU24. The control signal input terminal of the optocoupler transistor 21 is connected to the airborne satellite communication signal transceiver device 1, and the output terminal is connected to the Darlington circuit 22. connection; the input end of the Darlington circuit 22 is connected with the output end of the output amplifying circuit 23; the output amplifying circuit 23 has two output ends, one output end is directly connected with the electrical distribution box 3, and the other output end is connected with the Darlington circuit 22 Connect, the input terminal of the output amplifier circuit 23 is connected with the on-board power supply 4 through the insurance FU24. Among them, the optocoupler transistor 21 is used for "electrical-optical-electrical" conversion of the control signal to realize physical isolation between the control signal and the control circuit, and the output amplifier circuit 23 includes a resistor R4, a resistor R5 and a PNP transistor T3.

The electrical distribution box 3 includes a relay 31 and a contactor 32. The control input terminal of the relay 31 is connected to the output terminal E of the output amplifier circuit 23, the two input terminals of the contactor 32 are connected to the onboard power supply 4, and the output terminal of the contactor 32 is connected to the electrical load 5 connections. More specifically, terminal A1 of relay 31 is connected to terminal 3 of contactor 32 , terminal A2 is connected to terminal X2 , terminal X2 is connected to power ground, and terminal X1 is connected to the collector of transistor T3 in analog signal box 2 . Terminals 1 and 4 of the contactor 32 are connected to the positive pole of the onboard power supply 4 , and terminals 2 are connected to the positive pole of the power supply port of the electrical load 6 .

In order to realize the on-off of the high-power electrical load of the drone through the on-off circuit of the high-power electrical load of the drone, the present invention also provides a control method for the circuit, including the following steps:

A. The ground equipment sends a control signal to the airborne satellite communication signal transceiver equipment 1;

B. The airborne satellite communication signal transceiver device 1 transmits the instruction to the analog signal box 2;

C. The analog signal box 2 transmits control electrical signals to the electrical distribution box 3 according to the received signal, and the airborne satellite communication signal transceiver device 1 sends instructions to the optocoupler triode 21 to control its working state, and the optocoupler triode 21 works in the state Control the Darlington circuit 22 to turn on and off, and transmit the control electrical signal to the electrical distribution box 3 through the output amplifier circuit 23;

D. The electrical distribution box 3 controls the connection and disconnection between the onboard power supply 4 and the electrical load 5 according to the received control electrical signal. After the relay 31 receives the control electrical signal from the output amplifying circuit 23, it controls the contactor 32 to be turned off, and the electrical load 5 and the onboard power supply 4 are connected and disconnected by turning the contactor 32 on and off.

In step A, the current intensity of the control signal is 1.6mA-5mA. In step C, when the output amplifier circuit 23 is turned on by the Darlington circuit 22, the output end E of the output amplifier circuit 23, that is, the amplified current intensity of the collector of the triode T3 is 35mA. ～63mA, the working current intensity of electrical load 5 is 20A～50A.

The control method of this circuit is further explained in conjunction with Figure 1 below:

When the ground operator sends a control signal to power up the electrical load, the airborne satellite communication signal transceiver device 1 receives and sends the control signal. At this time, the control signal current is 1.6mA≤I _f ≤5mA, and the optocoupler transistor 21 in the analog signal box 2 1 end of the terminal is connected to the power supply to complete the "electrical-optical-electrical" conversion, and the optocoupler transistor 21 is turned on. At this time, U _A > U _B > U _C , and the Darlington circuit 22 is turned on, so that the analog signal The voltage drop on the resistor R4 of the output amplifying circuit 23 in the box 2 increases, at this time, U _D > U _F > U _E , the voltage drop on the resistor R4 in the output amplifying circuit 23 increases to make the transistor T3 conduct and work in the amplifying area , the output current from the E terminal of the triode T3 is _35mA≤I O≤63mA, and the amplified current is output from the E terminal of the triode T3 to the X1 terminal of the relay 31 in the electrical distribution box 3 as the working current, and the A1 terminal and A2 terminal of the relay 31 absorb 3 and 4 ends of the contactor 32 have current through them, and the 1 and 2 ends of the contactor 32 are pulled in, wherein the working current of the contactor 32 is 60mA≤I _J ≤100mA, so that the onboard power supply 4 and the electrical load The circuit between 5 is connected to realize the power-on function of the electrical load 5.

When the ground operator sends the control signal as the electrical load power-off signal, the airborne satellite communication signal transceiver device 1 receives and sends out the control signal, and the optocoupler transistor 21 in the analog signal box 2 is disconnected and no longer outputs current. At this time, the analog signal box 2 The middle Darlington circuit 22 has U _B =U _C =0V, the Darlington circuit 22 is closed and cut off, the output amplifier circuit 23 has U _D =U _F =28V, the transistor T3 is closed and cut off and no longer outputs current, the electrical distribution box 3. The working current of relay 31 drops to 0A, the A1 terminal and A2 terminal of relay 31 are disconnected, so that the working current of contactor 32 drops to 0A, and the 1 terminal and 2 terminal of contactor 32 are disconnected, so as to realize the power off of electrical load 5 Function.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the scope of the present invention. within the scope of protection.

Claims (9)

1. The utility model provides a high-power electrical load break-make circuit of unmanned aerial vehicle, includes airborne power supply (4), airborne satellite communication signal transceiver equipment (1) and electrical load (5), its characterized in that: still include analog signal box (2) and electric distribution box (3), airborne satellite communication signal transceiver (1) is connected with analog signal box (2) control input, and analog signal box (2) signal output part is connected with relay (31) control input of electric distribution box (3), and airborne power supply (4) output is connected with output amplifier circuit (23) input, and electric distribution box (3) output is connected with electric load (5).

2. The high-power electrical load on-off circuit of unmanned aerial vehicle of claim 1, characterized in that: the analog signal box (2) comprises an optical coupling triode (21), a Darlington circuit (22), an output amplification circuit (23) and a safety FU (24), wherein the input end of the optical coupling triode (21) is connected with the airborne satellite communication signal transceiver (1), and the output end of the optical coupling triode (21) is connected with the Darlington circuit (22); the circuit provides a working power supply for the Darlington circuit (22) through the F end of the output amplifying circuit (23); the airborne power supply (4) provides working power supply for the output amplifying circuit (23) through the safety FU (24), and the output amplifying circuit (23) is connected with the electric distribution box (3) through the E end to provide control electric signals for the on-off of the electric load (5).

3. The high-power electrical load on-off circuit of unmanned aerial vehicle of claim 2, characterized in that: electric distribution box (3) include relay (31) and contactor (32), relay (31) control signal input end is connected with output amplifier circuit (23) output E end, two input ends of contactor (32) are connected with airborne power supply (4) respectively, contactor (32) control output end is connected with relay (31) input end, contactor (32) output end is connected with electrical load (5).

4. The high-power electrical load on-off circuit of unmanned aerial vehicle of claim 3, characterized in that: the airborne power supply (4) is an airplane 28V direct current power supply.

5. The control method of the on-off circuit of the high-power electrical load of the unmanned aerial vehicle as claimed in claim 1, characterized by comprising the following steps:

A. the ground equipment sends a control signal to the airborne satellite communication signal transceiving equipment (1);

B. the airborne satellite communication signal receiving and sending equipment (1) transmits the instruction to the analog signal box (2);

C. the analog signal box (2) transmits a control electric signal to the electric distribution box (3) according to the received control signal;

D. the electrical distribution box (3) controls the connection and disconnection between the onboard power supply (4) and the electrical load (5) according to the type of the received control electrical signal.

6. The control method of the on-off circuit of the high-power electrical load of the unmanned aerial vehicle according to claim 5, characterized in that:

in the step C, the airborne satellite communication signal receiving and transmitting equipment (1) controls the working state of the optical coupling triode (21) through the received control instruction, controls the conduction and the cut-off of the Darlington circuit (22) through the working state of the optical coupling triode (21), and controls the conduction and the cut-off of the output amplifying circuit (23) through the Darlington circuit (22), so that a control signal is transmitted to the electrical distribution box (3);

in the step D, after the relay (31) receives the control electric signal of the output amplifying circuit (23), the contactor (32) is controlled to be switched on and off, and the on-off of the electrical load (5) and the onboard power supply (4) is realized through the on-off of the contactor (32).

7. The control method of the on-off circuit of the high-power electrical load of the unmanned aerial vehicle as claimed in claim 6, wherein: and controlling the current intensity of the signal to be 1.6 mA-5 mA in the step A.

8. The control method of the on-off circuit of the high-power electrical load of the unmanned aerial vehicle as claimed in claim 6, wherein: and in the step C, when the Darlington circuit (22) is conducted, the output end of the output amplifying circuit (23) connected with the electric distribution box (3) amplifies the current intensity to 35 mA-63 mA.

9. The control method of the on-off circuit of the high-power electrical load of the unmanned aerial vehicle as claimed in claim 6, wherein: the working current intensity of the electrical load (5) is 20-50A.

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