A heating control device for an atmospheric data system probe

Abstract

This invention provides a heating control device for an atmospheric data system probe. It integrates existing embedded hardware and software automatic control heating design as a first redundancy, while simultaneously designing a non-similar second redundancy. The second redundancy employs a hardware-only heating control method and is electrically isolated from the first redundancy. While retaining the functionality of the first redundancy, it allows the second redundancy to control the atmospheric data system probe's normal heating even if the first redundancy fails. The first and second redundancies are functionally mutually exclusive via a solid-state relay.

Description

Technical Field

[0001] This invention belongs to the field of atmospheric data sensor heating control technology, specifically relating to an atmospheric data system probe heating control device. Background Technology

[0002] In existing technologies, the heating of the atmospheric data system probe employs embedded hardware and software integrated automatic control. When the aircraft is in the air, it receives airspeed and wheel load signals via a data bus to control the automatic heating of the atmospheric data system probe. When the aircraft is on the ground, it controls the atmospheric data system probe to heat at low power or half power by collecting discrete signals from the ground heating detection command switch.

[0003] The development of this technology has reduced the burden on pilots operating the heating switch, avoided the problem of forgetting to turn on the heating switch and causing the probe to fail to heat up, and solved the problem of the ground probe overheating and damaging the sensor due to excessive heating time.

[0004] However, when the automatic control of the atmospheric data system probe's hardware and software integration fails, the probe cannot be heated, posing a risk of icing in the air. Summary of the Invention

[0005] This invention proposes a heating control device for an atmospheric data system probe, which solves the problem that existing atmospheric data system probe heating cannot be controlled when the integrated automatic control of the hardware and software fails, posing a risk of probe icing in the air.

[0006] This invention proposes a heating control device for an atmospheric data system probe, which is applied to the heating control of an atmospheric data system probe. The atmospheric data system probe heating control device includes: a first redundancy circuit, a second redundancy circuit, and a voting circuit.

[0007] The first redundancy circuit includes a microprocessor and a first heating control circuit; the second redundancy circuit includes a manual heating signal acquisition circuit and a second heating control circuit.

[0008] The microprocessor is used to receive the airspeed and wheel load signals sent by the crosslinking system, and when it is determined that the aircraft is in the air, control the first heating control circuit to be turned on, supply power to the atmospheric data system probe, and control the voting circuit to be turned off.

[0009] The voting circuit is used to activate when the integrated hardware and software automatic control fails.

[0010] The manual heating signal acquisition circuit is used to send the manual heating signal to the second heating control circuit through the voting circuit.

[0011] Optionally, the microprocessor is also used to, when determining that the aircraft is on the ground, control the first heating control circuit to disconnect and control the voting circuit to turn on.

[0012] Optionally, a second heating control circuit is activated when the voting circuit is on and the manual heating signal is valid, to supply power to the atmospheric data system probe.

[0013] Optionally, the voting circuit includes: resistor R5, resistor R1, and solid-state relay K1;

[0014] Solid-state relay K1 is a normally closed switch. The first control terminal is grounded through resistors R1 and R5 in sequence, and the second control terminal is grounded.

[0015] The connection point of resistors R1 and R5 receives the on / off control signal sent by the microprocessor.

[0016] The first output terminal of the solid-state relay K1 is connected to the output terminal of the manual heating signal acquisition circuit, and the second output terminal is connected to the input terminal of the second heating control circuit.

[0017] Optionally, the first heating control circuit includes: resistor R3, optocoupler H1, resistor R6, resistor R7, PMOS transistor and Zener diode V1;

[0018] The microprocessor outputs the first redundancy heating control command, which is connected to the first input terminal of the optocoupler H1 through resistor R3. The second input terminal of the optocoupler H1 is connected to a 5V DC power supply.

[0019] The first output terminal of optocoupler H1 is grounded, and the second output terminal is connected to the second terminal of resistor R7.

[0020] When the first redundancy heating control command is low, the indicator PMOS transistor is turned on, and the 5V voltage forms a circuit through the internal LED of optocoupler H1 and resistor R3. The LED lights up, and the internal transistor of optocoupler H1 turns on after detecting that the LED is lit up. The second end of resistor R7 is grounded.

[0021] When the first redundancy heating control command is high, the indicator PMOS transistor is turned off, the internal LED of optocoupler H1 does not emit light, the internal transistor of optocoupler H1 remains off, and the second terminal of resistor R7 is left floating.

[0022] The first end of resistor R6 is connected to a 270V DC power supply, and the second end is connected to the first end of resistor R7 and the gate of the PMOS transistor.

[0023] When the first redundancy heating control command is low, the 270V DC power supply forms a loop to ground through resistors R6 and R7. The voltage division value of resistors R6 and R7 is connected to the gate of the PMOS transistor, the PMOS transistor is turned on, and the 270V DC power supply powers the atmospheric data system probe.

[0024] When the first redundancy heating control command is high, the voltage Vgs of the PMOS transistor is 0, and the PMOS transistor remains off.

[0025] Zener diode V1 is connected in parallel across resistor R6.

[0026] Optional, the manual heating signal acquisition circuit includes: optocoupler H2 and resistor R2;

[0027] The first input terminal of the optocoupler H2 is connected to a 28V DC power supply, and the second input terminal is connected to a manual heating signal.

[0028] The first output terminal of optocoupler H2 is connected to a 270V DC power supply, and the second output terminal outputs the ground heating detection switch signal, which is connected to the first output terminal of solid-state relay K1 and the first terminal of resistor R2; the second terminal of resistor R2 is grounded.

[0029] The manual heating signal is active at a low level, while the ground heating detection switch signal is active at a high level.

[0030] Optionally, the second heating control circuit includes: resistor R4, optocoupler H3, resistor R8, resistor R9, PMOS transistor and Zener diode V2;

[0031] The manual heating signal acquisition circuit is used to connect the ground heating detection command switch to the first input terminal of optocoupler H3 through resistor R4 via a voting circuit, and the second input terminal of optocoupler H3 is grounded.

[0032] The first output terminal of optocoupler H3 is grounded, and the second output terminal is connected to the second terminal of resistor R9.

[0033] When the ground heating detection command switch is valid, the indicator PMOS transistor is turned on. The high level provided by the second output terminal of the solid-state relay K1 forms a circuit through the internal LED of optocoupler H3 and resistor R4. The LED lights up. The internal transistor of optocoupler H3 detects the LED lighting up and turns on. The second terminal of resistor R9 is grounded.

[0034] When the ground heating detection command switch is invalid, the indicator PMOS transistor is turned off, the internal LED of optocoupler H3 does not emit light, the internal transistor of optocoupler H3 remains off, and the second terminal of resistor R9 is left floating.

[0035] The first end of resistor R8 is connected to a 270V DC power supply, and the second end is connected to the first end of resistor R9 and the gate of the PMOS transistor.

[0036] When the ground heating detection command switch is active, the 270V DC power supply forms a circuit to ground through resistors R8 and R9. The voltage division value of resistors R8 and R9 is connected to the gate of the PMOS transistor, and the PMOS transistor is turned on. The 270V DC power supply powers the atmospheric data system probe.

[0037] When the ground heating detection command switch is invalid, the voltage Vgs of the PMOS transistor is 0, and the PMOS transistor remains off.

[0038] Zener diode V2 is connected in parallel across resistor R8.

[0039] Optionally, the resistance of resistor R4 is 25K-27KΩ.

[0040] This invention proposes a heating control device for an atmospheric data system probe. It utilizes existing embedded hardware and software integrated automatic control heating design as a first redundancy, while simultaneously employing a compatible, dissimilar second redundancy. The second redundancy uses a hardware-only heating control method, completely dissimilar to the first redundancy design and electrically isolated from it. While retaining the functionality of the first redundancy, it allows for normal probe heating control via the second redundancy when the first redundancy fails or the power supply is lost. The first and second redundancies are functionally mutually exclusive via a solid-state relay. This device addresses the issue of hardware and software integrated automatic control failure during flight, allowing for remedial control using the dissimilar circuitry of the second redundancy. This improves the reliability of probe heating, avoids the risk of probe icing due to heating failure, and ensures flight safety. Attached Figure Description

[0041] Figure 1 This is a schematic diagram of the structure of the atmospheric data system probe heating control device of the present invention. Detailed Implementation

[0042] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0043] The heating control device for the atmospheric data system probe provided by the present invention will be explained below with reference to the accompanying drawings.

[0044] like Figure 1 As shown, this invention provides a heating control device for an atmospheric data system probe. It integrates existing embedded hardware and software automatic control heating design as a first redundancy, while simultaneously employing a compatible, dissimilar second redundancy. The second redundancy uses a hardware-only heating control method, completely dissimilar to the first redundancy design and electrically isolated from it. While retaining the functionality of the first redundancy, it allows the second redundancy to control the atmospheric data system probe's normal heating even when the first redundancy control fails or the power supply is lost. The first and second redundancies are functionally mutually exclusive via a solid-state relay.

[0045] The technical solution provided by this invention is the design of a probe heating control device for an atmospheric data system.

[0046] 1) When the automatic control of the integrated hardware and software of the atmospheric data system probe is normal, the first redundancy heating control circuit of the device receives the indicated airspeed and wheel load signals sent by the cross-linking system through the data bus. When the indicated airspeed is ≥120km / h or the wheel load is in the air, it is determined that the aircraft is in the air and the atmospheric data system probe is automatically heated. The heating power is full power heating to achieve the anti-icing effect of the probe in the air.

[0047] 2) During flight, if the integrated hardware and software automatic control fails, the primary redundancy heating control circuit of the device malfunctions, and the probe is at risk of icing, the pilot can manually activate the ground heating detection switch to use the secondary redundancy circuit to control probe heating, achieving probe anti-icing. The secondary redundancy control circuit designed in the device can serve as an emergency response measure in case of a heating failure of the atmospheric data system probe during flight.

[0048] Working principle of the first redundancy circuit:

[0049] When the integrated hardware and software automatic control is working properly, the microprocessor controls LS1-A-1 to output a low level, turning on the H1 optocoupler and controlling the Q1 PMOS transistor to turn on, thus realizing the first redundancy heating control function. At the same time, the microprocessor controls LS1-C to output a high level, so that the input terminal of the solid-state relay K1 is in the conducting state and the output terminal is in the normally open state. The input terminal of the H3 optocoupler is floating, causing the H3 optocoupler to not conduct, the Q2 PMOS transistor to be cut off, and the second redundancy circuit cannot realize the heating control.

[0050] Working principle of the second redundancy circuit:

[0051] When the integrated hardware and software automatic control fails, the microprocessor cannot control the output levels of LS1-A-1 and LS1-C, and the first redundancy circuit fails to function. When the ground heating detection command switch LS1 is manually turned on, LS1 is set to 28V ground, optocoupler H2 is turned on, and LS1-B outputs a high level. LS1-C is at a low level through pull-down resistor R5, the input of solid-state relay K1 is not conducting, and the output is normally closed, controlling optocoupler H3 to conduct, which in turn controls PMOS transistor Q2 to conduct, realizing the second redundancy heating control function.

[0052] Note: Solid-state relays are selected as normally closed devices by default. When the input terminal is not conducting, the output terminal is normally closed; when the input terminal is conducting, the output terminal is normally open.

[0053] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A heating control device for an atmospheric data system probe, characterized in that, The heating control device for atmospheric data system probes includes: a first redundancy circuit, a second redundancy circuit, and a voting circuit. The first redundancy circuit includes a microprocessor and a first heating control circuit; the second redundancy circuit includes a manual heating signal acquisition circuit and a second heating control circuit. The microprocessor is used to receive the airspeed and wheel load signals sent by the crosslinking system, and when it is determined that the aircraft is in the air, control the first heating control circuit to be turned on, supply power to the atmospheric data system probe, and control the voting circuit to be turned off. The voting circuit is used to activate when the integrated hardware and software automatic control fails. The manual heating signal acquisition circuit is used to send the manual heating signal to the second heating control circuit through the voting circuit. The voting circuit includes: resistor R5, resistor R1, and solid-state relay K1; Solid-state relay K1 is a normally closed switch. The first control terminal is grounded through resistors R1 and R5 in sequence, and the second control terminal is grounded. The connection point of resistors R1 and R5 receives the on / off control signal sent by the microprocessor. The first output terminal of the solid-state relay K1 is connected to the output terminal of the manual heating signal acquisition circuit, and the second output terminal is connected to the input terminal of the second heating control circuit. The first heating control circuit includes: resistor R3, optocoupler H1, resistor R6, resistor R7, PMOS transistor and Zener diode V1; The microprocessor outputs the first redundancy heating control command, which is connected to the first input terminal of the optocoupler H1 through resistor R3. The second input terminal of the optocoupler H1 is connected to a 5V DC power supply. The first output terminal of optocoupler H1 is grounded, and the second output terminal is connected to the second terminal of resistor R7. When the first redundancy heating control command is low, the indicator PMOS transistor is turned on, and the 5V voltage forms a circuit through the internal LED of optocoupler H1 and resistor R3. The LED lights up, and the internal transistor of optocoupler H1 turns on after detecting that the LED is lit up. The second end of resistor R7 is grounded. When the first redundancy heating control command is high, the indicator PMOS transistor is turned off, the internal LED of optocoupler H1 does not emit light, the internal transistor of optocoupler H1 remains off, and the second terminal of resistor R7 is left floating. The first end of resistor R6 is connected to a 270V DC power supply, and the second end is connected to the first end of resistor R7 and the gate of the PMOS transistor. When the first redundancy heating control command is low, the 270V DC power supply forms a loop to ground through resistors R6 and R7. The voltage division value of resistors R6 and R7 is connected to the gate of the PMOS transistor, the PMOS transistor is turned on, and the 270V DC power supply powers the atmospheric data system probe. When the first redundancy heating control command is high, the voltage Vgs of the PMOS transistor is 0, and the PMOS transistor remains off. Zener diode V1 is connected in parallel across resistor R6; The manual heating signal acquisition circuit includes: optocoupler H2 and resistor R2; The first input terminal of the optocoupler H2 is connected to a 28V DC power supply, and the second input terminal is connected to a manual heating signal. The first output terminal of optocoupler H2 is connected to a 270V DC power supply, and the second output terminal outputs the ground heating detection switch signal, which is connected to the first output terminal of solid-state relay K1 and the first terminal of resistor R2; the second terminal of resistor R2 is grounded. The manual heating signal is active at a low level, and the ground heating detection switch signal is active at a high level. The second heating control circuit includes: resistor R4, optocoupler H3, resistor R8, resistor R9, PMOS transistor and Zener diode V2; The manual heating signal acquisition circuit is used to connect the ground heating detection command switch to the first input terminal of optocoupler H3 through resistor R4 via a voting circuit, and the second input terminal of optocoupler H3 is grounded. The first output terminal of optocoupler H3 is grounded, and the second output terminal is connected to the second terminal of resistor R9. When the ground heating detection command switch is valid, the indicator PMOS transistor is turned on. The high level provided by the second output terminal of the solid-state relay K1 forms a circuit through the internal LED of optocoupler H3 and resistor R4. The LED lights up. The internal transistor of optocoupler H3 detects the LED lighting up and turns on. The second terminal of resistor R9 is grounded. When the ground heating detection command switch is invalid, the indicator PMOS transistor is turned off, the internal LED of optocoupler H3 does not emit light, the internal transistor of optocoupler H3 remains off, and the second terminal of resistor R9 is left floating. The first end of resistor R8 is connected to a 270V DC power supply, and the second end is connected to the first end of resistor R9 and the gate of the PMOS transistor. When the ground heating detection command switch is active, the 270V DC power supply forms a circuit to ground through resistors R8 and R9. The voltage division value of resistors R8 and R9 is connected to the gate of the PMOS transistor, and the PMOS transistor is turned on. The 270V DC power supply powers the atmospheric data system probe. When the ground heating detection command switch is invalid, the voltage Vgs of the PMOS transistor is 0, and the PMOS transistor remains off. Zener diode V2 is connected in parallel across resistor R8.

2. The atmospheric data system probe heating control device according to claim 1, characterized in that, The microprocessor is also used to control the first heating control circuit to disconnect and the voting circuit to turn on when it is determined that the aircraft is on the ground.

3. The atmospheric data system probe heating control device according to claim 1, characterized in that, The second heating control circuit is activated when the voting circuit is on and the manual heating signal is valid, supplying power to the atmospheric data system probe.

4. The atmospheric data system probe heating control device according to claim 1, characterized in that, The resistance of resistor R4 is 25K-27K ohms.

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