CN109606715B - Voice warning system for airplane and implementation method thereof - Google Patents
Voice warning system for airplane and implementation method thereof Download PDFInfo
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- CN109606715B CN109606715B CN201811627344.XA CN201811627344A CN109606715B CN 109606715 B CN109606715 B CN 109606715B CN 201811627344 A CN201811627344 A CN 201811627344A CN 109606715 B CN109606715 B CN 109606715B
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- 238000000034 method Methods 0.000 title claims abstract description 9
- 230000002159 abnormal effect Effects 0.000 claims abstract description 80
- 238000002955 isolation Methods 0.000 claims abstract description 76
- 230000003287 optical effect Effects 0.000 claims abstract description 19
- 230000008878 coupling Effects 0.000 claims abstract description 13
- 238000010168 coupling process Methods 0.000 claims abstract description 13
- 238000005859 coupling reaction Methods 0.000 claims abstract description 13
- 238000001514 detection method Methods 0.000 claims abstract description 4
- 239000003990 capacitor Substances 0.000 claims description 45
- 230000000087 stabilizing effect Effects 0.000 claims description 37
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 230000005856 abnormality Effects 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000005236 sound signal Effects 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 229910052715 tantalum Inorganic materials 0.000 description 1
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Emergency Alarm Devices (AREA)
- Alarm Systems (AREA)
Abstract
The invention discloses a voice warning system for an aircraft, which is characterized by comprising an optical coupling isolation unit, a singlechip, a voice recording and playing unit and a power supply unit. The invention also discloses a realization method of the voice warning system for the aircraft, which is characterized by comprising the following steps of: initializing a system, inputting an abnormal voice warning signal and a stall abnormal voice warning signal of the landing gear to a voice recording and playing unit, and entering a warning trigger signal detection state; step 2: and detecting whether landing gear warning trigger signals or stall warning trigger signals are input or not by the optical coupling isolation unit. The invention warns the stall abnormality of the aircraft and the landing gear abnormality by voice, improves the recognition degree of the warning, and enables a pilot to accurately and rapidly judge the warning information so as to accurately control the aircraft.
Description
Technical Field
The invention relates to the field of aircraft safety warning, in particular to a voice warning system for an aircraft and an implementation method thereof.
Background
The PA-44-180 aircraft provides a warning signal of the fault condition of the airframe and engine. As with most general aircraft, the warning signal is provided to the flight personnel and ground maintenance personnel in the form of light or buzzer; for buzzer alarms, different fault buzzer alarms only differentiate in frequency; for light warning, the warning light is an incandescent light, which is an amber or red light cover, mounted on the dashboard, and lights up when the relevant warning message appears.
From the above warning mode, it can be seen that the PA-44-180 type aircraft warning has a certain defect in functional design. Firstly, the design of an aircraft warning system does not have redundancy, and a pilot cannot receive a warning signal under the fault condition; secondly, the stall warning and the landing gear warning of the aircraft are provided by the buzzer, and the stall warning and the landing gear warning are distinguished only in frequency, so that the recognition degree is insufficient, and the sound of the buzzer is easily ignored by a pilot under the condition of high tension; for example, a 3.08 accident in 2014 is most likely an accident caused by the pilot missing the stall warning sound and missing the change-out time; as another example, the 3.13 event of 2015 also fully illustrates that the landing gear warning system has some drawbacks in terms of audio cues. Therefore, the warning system and the warning method with higher identification degree are of great significance for improving the operation safety of the PA-44-180 type aircraft.
Disclosure of Invention
The invention aims to overcome the defect of insufficient recognition of stall warning and landing gear warning of the current PA-44-180 type aircraft, and provides a voice warning system with redundancy and higher recognition degree and an implementation method thereof.
The purpose of the invention is realized by the following technical scheme: a voice warning system for an aircraft comprises an optical coupling isolation unit, a singlechip, a voice recording and playing unit and a power supply unit;
an optical coupling isolation unit: the system is used for receiving landing gear warning trigger signals and stall warning trigger signals outside the system and outputting the landing gear warning signals and stall warning signals to the singlechip; simultaneously, voltage conversion is completed;
and the singlechip is used for: the optical coupler isolation unit is connected with the voice recording and playing unit and used for sending an undercarriage warning trigger instruction to the voice recording and playing unit according to the undercarriage warning signal or sending a stall warning trigger instruction to the voice recording and playing unit according to the stall warning signal;
a voice recording and playing unit: the single chip microcomputer is connected with the landing gear voice warning signal output according to the landing gear warning trigger instruction or the stall voice warning signal output according to the stall warning trigger instruction;
a power supply unit: and the device is respectively connected with the optocoupler isolation unit, the singlechip and the voice recording and playing unit and is used for converting the voltage of the aircraft power supply system and supplying power to the optocoupler isolation unit, the singlechip and the voice recording and playing unit.
Further, the device also comprises an aircraft audio board; the aircraft audio board is connected with the voice recording and playing unit and is used for playing the abnormal voice warning of the landing gear according to the voice warning signal of the landing gear or playing the abnormal voice warning of stall according to the voice warning signal of stall.
The system also comprises a key signal input unit and a recording input unit;
the key signal input unit is connected with the singlechip and is used for inputting control instructions to the singlechip;
the singlechip is also used for sending a recording instruction to the voice recording and playing unit according to the control instruction;
the voice recording and playing unit is also used for receiving voice signals according to the recording instruction;
the recording input unit is connected with the voice recording and playing unit and is used for recording voice signals to the voice recording and playing unit.
The LED display device also comprises an LED indication unit and a reset unit;
the LED indicating unit is connected with the singlechip and used for displaying the running state of the system;
the reset unit is connected with the singlechip and is used for resetting the system.
The power supply unit comprises a voltage stabilizing chip U1, a polarity capacitor C2, and a voltage reducing circuit, wherein the positive electrode of the polarity capacitor C1 is connected with a pin 2 of the voltage stabilizing chip U1, the negative electrode of the polarity capacitor C1 is grounded, the positive electrode of the polarity capacitor C2 is connected with a pin 3 of the voltage stabilizing chip U1, the negative electrode of the polarity capacitor C2 is grounded, the output end of the polarity capacitor C2 is connected with a pin 3 of the voltage stabilizing chip U1, and the input end of the polarity capacitor C1 is connected with an aircraft power supply system; and the pin 1 of the voltage stabilizing chip U1 is grounded, and the pin 2 of the voltage stabilizing chip U1 is respectively connected with the optocoupler isolation unit, the singlechip and the voice recording and playing unit.
The step-down circuit comprises five step-down units which are sequentially connected end to end; the step-down unit comprises two diodes connected in parallel.
The optocoupler isolation unit comprises a photoelectric isolation chip U2, a resistor R1, a resistor R2, a resistor R3 and a resistor R4, wherein one end of the resistor R1 is connected with a pin 2 of the photoelectric isolation chip U2, the other end of the resistor R1 is grounded, one end of the resistor R2 is connected with a pin 4 of the photoelectric isolation chip U2, the other end of the resistor R2 is used as an input end of a stall warning trigger signal, one end of the resistor R3 is connected with a pin 8 of the photoelectric isolation chip U2, the other end of the resistor R3 is connected with a pin 2 of the voltage stabilizing chip U1, and one end of the resistor R4 is connected with a pin 6 of the photoelectric isolation chip U2; the 1 pin of the photoelectric isolation chip U2 is used as an input end of an undercarriage warning trigger signal, the 3 pin of the photoelectric isolation chip U2 is connected with an aircraft power supply system, the 7 pin and the 5 pin of the photoelectric isolation chip U2 are grounded, the 8 pin of the photoelectric isolation chip U2 is used as an undercarriage warning signal output end, and the 6 pin of the photoelectric isolation chip U2 is used as a stall warning signal output end.
The voice recording and playing unit comprises a voice recording and playing chip U3, a polar capacitor C4, a capacitor C3, a resistor R5, a polar capacitor C6, a resistor R5, a resistor R6, a capacitor C5, and a capacitor C3, wherein the positive electrode of the resistor R5 is connected with a pin 1 of the voice recording and playing chip U3, the negative electrode of the resistor C4 is connected with a pin 28 of the voice recording and playing chip U3, one end of the capacitor C3 is connected with a pin 2 of the voice recording and playing chip U3 after passing through an indicator lamp VD, the other end of the resistor R5 is connected with a pin 2 of the voltage stabilizing chip U1, the positive electrode of the resistor R5 is connected with a pin 18 of the voice recording and playing chip U3, the negative electrode of the resistor C6 is grounded, and the resistor R6 is connected between a pin 20 of the voice recording and playing chip U3 and the negative electrode of the polar capacitor C6 in series, and the capacitor C5 is connected with a pin 9 of the voice recording and playing chip U3 at one end of the resistor C5; the 1 pin of the voice recording and playing chip U3 is connected with the 2 pin of the voltage stabilizing chip U1, the 28 pin of the voice recording and playing chip U3 is grounded, the 8 pin of the voice recording and playing chip U3 is connected with the recording input unit, and the 15 pin of the voice recording and playing chip U3 and the negative electrode of the polar capacitor C6 jointly form an output end and are connected with an aircraft audio board.
A method of implementing a voice warning system for an aircraft, comprising the steps of:
step 1: initializing a system, inputting an abnormal voice warning signal and a stall abnormal voice warning signal of the landing gear to a voice recording and playing unit, and entering a warning trigger signal detection state;
step 2: the optical coupling isolation unit detects whether an undercarriage warning trigger signal or a stall warning trigger signal is input, if yes, the undercarriage warning signal is output to the singlechip, and the step 3 is executed; outputting a stall warning signal to the singlechip if the stall warning trigger signal is detected to be input, and executing the step 4;
step 3: outputting an undercarriage warning triggering instruction to the voice recording and playing unit by the singlechip, and executing the step 5;
step 4: the singlechip outputs a stall warning triggering instruction to the voice recording and playing unit and executes the step 6;
step 5: the voice recording and playing unit outputs a landing gear voice warning signal to the aircraft audio board, and the aircraft audio board broadcasts a landing gear abnormal voice warning;
step 6: the voice recording and playing unit outputs a stall voice warning signal to the aircraft audio board, and the aircraft audio board broadcasts a stall abnormal voice warning.
Further, the recording of the landing gear abnormal voice warning signal and the stall abnormal voice warning signal to the voice recording and playing unit in step 1 includes the following steps:
(1) Transmitting an undercarriage abnormal voice warning signal and a stall abnormal voice warning signal to a voice recording and playing unit;
(2) Recording an abnormal voice warning recording control command of the landing gear and a stall abnormal voice warning recording control command to the singlechip; when the single chip microcomputer receives the landing gear abnormal voice warning recording control command, sending a landing gear abnormal voice warning recording command to the voice recording and playing unit, and executing the step (3); when the singlechip receives a stall abnormal voice warning recording control command, sending a stall abnormal voice warning recording command to the voice recording and playing unit, and executing the step (4);
(3) The voice recording and playing unit stores an abnormal voice warning signal of the landing gear;
(4) The voice recording and playing unit stores stall abnormal voice warning signals.
Compared with the prior art, the invention has the following advantages:
(1) The invention warns the stall abnormality of the aircraft and the landing gear abnormality by voice, improves the recognition degree of the warning, and enables a pilot to accurately and rapidly judge the warning information so as to accurately control the aircraft.
(2) The invention adds redundant voice warning function to the aircraft audio board, thereby ensuring that whether the pilot wears the earphone or not does not influence the receiving of warning audio, and improving the safety level of the aircraft.
(3) The warning system of the invention does not conflict or interfere with any existing airborne equipment, thereby ensuring the safety performance of the aircraft.
Drawings
Fig. 1 is a structural diagram of the present invention.
Fig. 2 is a circuit configuration diagram of the power supply unit of the present invention.
Fig. 3 is a circuit configuration diagram of an optocoupler isolation unit according to the present invention.
Fig. 4 is a circuit configuration diagram of a voice recording and reproducing unit according to the present invention.
Detailed Description
The present invention will be described in further detail with reference to specific examples, but embodiments of the present invention are not limited thereto.
Example 1
As shown in fig. 1, the voice warning system for an aircraft in this embodiment includes an optocoupler isolation unit, a single-chip microcomputer connected to the optocoupler isolation unit, a voice recording and playing unit connected to the single-chip microcomputer, and a power supply unit connected to the optocoupler isolation unit, the single-chip microcomputer, and the voice recording and playing unit, respectively.
Specifically, the optocoupler isolation unit is used for receiving landing gear warning trigger signals and stall warning trigger signals outside the system and outputting the landing gear warning signals and stall warning signals to the singlechip; because the landing gear warning trigger signal and the stall warning trigger signal received by the optical coupling isolation unit are both 12V-14V voltage signals, and the signal processed by the singlechip is 5V voltage, the optical coupling isolation unit also converts the landing gear warning trigger signal and the stall warning trigger signal into the 5V voltage and outputs the 5V voltage to the singlechip, so that the voltage conversion is completed.
The stall warning and landing gear warning of the existing PA-44-180 type aircraft are provided by a buzzer, and the two warning information are only distinguished in frequency; the PA-44-180 type aircraft detects whether the aircraft is stall abnormal through stall warning blades, namely one end of a buzzer of the traditional warning system is connected with a bus bar of the aircraft, the other end of the buzzer is connected with the stall warning blades, when the aircraft approaches a stall state, the stall warning blades lift up and switch on internal contacts, and then stall warning trigger signals are output to sound the buzzer; the landing gear abnormality is that when the landing gear is in the retracted position and the power of the engine of the aircraft is reduced to below 14 in-hg, a trigger circuit of the landing gear warning on the aircraft provides a power supply signal for the buzzer, so that the buzzer sounds. Therefore, the optocoupler isolation unit of the embodiment is respectively connected with the output end of the landing gear warning trigger signal and the output end of the stall warning trigger signal of the original onboard warning system, and is used for receiving the landing gear warning trigger signal and the stall warning trigger signal of the aircraft.
The optical coupling isolation unit is adopted to realize the electrical isolation between the trigger signal output by the aircraft and the internal circuit of the system, so that the interference is reduced.
The singlechip is used for sending a landing gear warning trigger instruction to the voice recording and playing unit according to the landing gear warning signal sent by the optical coupling isolation unit, or sending a stall warning trigger instruction to the voice recording and playing unit according to the stall warning signal; the singlechip is realized by adopting an AT89S52 singlechip. The voice recording and playing unit is used for outputting a landing gear voice warning signal according to the landing gear warning triggering instruction sent by the singlechip or outputting a stall voice warning signal according to the stall warning triggering instruction. The power supply unit is used for converting the voltage of the aircraft power supply system and supplying power to the optocoupler isolation unit, the singlechip and the voice recording and playing unit; the input end of the power supply unit is connected with the aircraft power supply system, and the output end of the power supply unit is respectively connected with the optocoupler isolation unit, the singlechip and the voice recording and playing unit.
As a preferred aspect, the voice warning system further comprises an aircraft audio board; the aircraft audio board is connected with the voice recording and playing unit and is used for playing the abnormal voice warning of the landing gear according to the landing gear voice warning signal output by the voice recording and playing unit or playing the stall abnormal voice warning according to the stall voice warning signal. The audio board of the aircraft is an original onboard device of the aircraft, and the audio board of the PA-44-180 type aircraft is a GMA340 audio board; the aircraft audio board broadcasts the landing gear abnormal voice warning and the stall abnormal voice warning, so that whether a pilot wears the earphone is guaranteed not to influence the receiving of warning audio, and the safety level of the aircraft is improved.
As another preferable scheme, the voice warning system also comprises a key signal input unit and a recording input unit, wherein the key signal input unit is connected with the singlechip, and the recording input unit is connected with the voice recording and playing unit; specifically, the recording input unit is connected with the voice recording and playing unit through an audio signal line interface.
The key signal input unit is used for inputting control instructions to the singlechip, and is realized by adopting a traditional singlechip key input circuit, wherein one end of the key signal input unit is connected with an I/0 interface of the singlechip, and the other end of the key signal input unit is grounded; the control commands include landing gear abnormal voice warning entry control commands and stall abnormal voice warning entry control commands. The recording input unit is used for inputting voice signals to the voice recording and playing unit, and is an audio output unit of the computer; the voice signals include landing gear abnormal voice warning signals and stall abnormal voice warning signals. The singlechip is also used for sending a recording instruction to the voice recording and playing unit according to the control instruction input by the key signal input unit, wherein the recording instruction comprises an undercarriage abnormal voice warning recording instruction and a stall abnormal voice warning recording instruction; when the voice recording and playing unit receives a recording instruction, the voice recording unit receives a voice signal output by the recording input unit.
As another preferable scheme, the voice warning system further comprises an LED indicating unit and a resetting unit, wherein the LED indicating unit and the resetting unit are connected with the singlechip. Specifically, the LED indicating unit is a conventional LED indicating circuit for displaying an operation state of the system. The reset unit is a traditional reset circuit and is used for resetting the system, namely, the reset circuit is used for generating a pulse signal with proper width to a reset pin of the singlechip in the initial power-on stage of the system to reset the singlechip to an initial state, and the reset circuit also comprises a circuit for enabling a developer to conveniently and manually generate the pulse signal in the debugging stage so as to restart the whole circuit system.
Specifically, as shown in fig. 2, the power supply unit includes a voltage stabilizing chip U1, a polarity capacitor C1 with an anode connected to pin 2 of the voltage stabilizing chip U1 and a cathode grounded, a polarity capacitor C2 with an anode connected to pin 3 of the voltage stabilizing chip U1 and a cathode grounded, and a voltage reducing circuit with an output end connected to pin 3 of the voltage stabilizing chip U1 and an input end connected to an aircraft power supply system; and the pin 1 of the voltage stabilizing chip U1 is grounded, and the pin 2 of the voltage stabilizing chip U1 is respectively connected with the optocoupler isolation unit, the singlechip and the voice recording and playing unit.
The step-down circuit comprises five step-down units which are sequentially connected end to end; the step-down unit comprises two diodes connected in parallel. Specifically, as shown in fig. 2, the step-down circuit includes a diode D1, a diode D2, a diode D3, a diode D4, a diode D5, a diode D6, a diode D7, a diode D8, a diode D9, and a diode D10. The P pole of the diode D10 is connected with an aircraft power supply system, and the N pole of the diode D9 is connected with the P pole of the aircraft power supply system; the P pole of the diode D8 is connected with the P pole of the diode D10, and the N pole of the diode D8 is connected with the N pole of the diode D10; the N pole of the diode D9 is connected to the P pole of the diode D6, the P pole of the diode D7 is connected to the P pole of the diode D9, and the N pole thereof is connected to the N pole of the diode D9. The N pole of the diode D6 is connected to the P pole of the diode D4, the P pole of the diode D5 is connected to the P pole of the diode D6, and the N pole thereof is connected to the N pole of the diode D6. The N pole of the diode D4 is connected to the P pole of the diode D2, the P pole of the diode D3 is connected to the P pole of the diode D4, and the N pole thereof is connected to the N pole of the diode D4. The N pole of the diode D2 is connected with the 3 pin of the voltage stabilizing chip U1, the P pole of the diode D1 is connected with the P pole of the diode D2, and the N pole of the diode D2 is connected with the N pole of the diode D2.
In the above configuration, the diode D1 and the diode D2 form a step-down unit, the diode D3 and the diode D4 form a step-down unit, the diode D5 and the diode D6 form a step-down unit, the diode D7 and the diode D9 form a step-down unit, and the diode D8 and the diode D10 form a step-down unit. The voltage reducing circuit reduces the input power supply voltage of the aircraft of 12-14.5V to 8.5-11V through five voltage reducing units, the voltage stabilizing chip U1 inputs the voltage to the voltage stabilizing chip U1, and the voltage stabilizing chip U1 outputs stable 5V voltage from a 2 pin of the voltage stabilizing chip to the optocoupler isolation unit, the singlechip and the voice recording and playing unit. The polar capacitor C1 and the polar capacitor C2 are tantalum capacitors, and the polar capacitor C1 and the polar capacitor C2 perform voltage stabilization and filtering treatment on the voltage so as to ensure that the 2 pin of the voltage stabilizing chip U1 outputs reliable 5V voltage. The voltage stabilizing chip U1 is realized by adopting an AMS1117-5 voltage stabilizing chip, the AMS1117-5 voltage stabilizing chip has 1% precision, and an overheat protection circuit and a current limiting circuit are integrated inside the AMS1117-5 voltage stabilizing chip, so that the circuit can be well protected.
As shown in fig. 3, the optocoupler isolation unit includes an optocoupler isolation chip U2, a resistor R1, a resistor R2, a resistor R3, and a resistor R4. When in connection, one end of the resistor R1 is connected with the 2 pin of the photoelectric isolation chip U2, the other end of the resistor R1 is grounded, one end of the resistor R2 is connected with the 4 pin of the photoelectric isolation chip U2, the other end of the resistor R2 is used as the input end of a stall warning trigger signal and is connected with the output end of the stall warning trigger signal of the original onboard warning system, one end of the resistor R3 is connected with the 8 pin of the photoelectric isolation chip U2, the other end of the resistor R3 is connected with the 2 pin of the voltage stabilizing chip U1, one end of the resistor R4 is connected with the 6 pin of the photoelectric isolation chip U2, and the other end of the resistor R4 is connected with the 2 pin of the voltage stabilizing chip U1. The 1 pin of the photoelectric isolation chip U2 is used as the input end of an undercarriage warning trigger signal and is connected with the output end of the undercarriage warning trigger signal of the original onboard warning system, the 3 pin of the photoelectric isolation chip U2 is connected with the aircraft power supply system, the 7 pin and the 5 pin of the photoelectric isolation chip U2 are grounded, the 8 pin of the photoelectric isolation chip U2 is used as the output end of the undercarriage warning signal and is connected with the singlechip, and the 6 pin of the photoelectric isolation chip U2 is used as the output end of a stall warning signal and is connected with the singlechip.
The voltage of the aircraft power supply system is input by the 3 pin of the photoelectric isolation chip U2, and the working voltage is provided for the photoelectric isolation chip U2. When the landing gear is abnormal, landing gear warning trigger signals are input into the photoelectric isolation chip U2 from the pin 1 of the photoelectric isolation chip U2, so that the light emitting diode in the photoelectric isolation chip U2 emits light, the photosensitive diode is conducted, and the landing gear warning signals are output to the singlechip from the pin 8. When the aircraft has stall abnormality, stall warning trigger signals are input to the 4 pins of the photoelectric isolation chip U2 after passing through the resistor R2, so that the light emitting diode in the photoelectric isolation chip U2 emits light, the photosensitive diode is conducted, and the 6 pins of the photosensitive diode output stall warning signals to the singlechip. The resistor R1 and the resistor R2 are current limiting resistors and are used for limiting the current flowing through the light emitting diode under the condition of signal input, so that the light emitting diode at the input end of the optocoupler is prevented from being burnt by excessive current. The resistor R3 and the resistor R4 are pull-up resistors for outputting signals, when no warning signal exists, the landing gear signal output end and the stall signal output end are ensured to be in high potential of 5V in the circuit, and the I/O port of the singlechip is prevented from receiving uncertain voltage signals.
As shown in fig. 4, the voice recording and playing unit includes a voice recording and playing chip U3, a jac, a resistor R5, a resistor R6, a capacitor C3, a polarity capacitor C4, a capacitor C5 and a polarity capacitor C6. Specifically, the positive pole of the polar capacitor C4 is connected to pin 1 of the voice recording and playing chip U3, the negative pole thereof is connected to pin 28 of the voice recording and playing chip U3, the capacitor C3 is connected in parallel with the polar capacitor C4, one end of the resistor R5 is connected to pin 2 of the voice recording and playing chip U3 after passing through the indicator lamp VD, the other end thereof is connected to pin 2 of the voltage stabilizing chip U1, the positive pole of the polar capacitor C6 is connected to pin 18 of the voice recording and playing chip U3, the negative pole thereof is grounded, the resistor R6 is connected in series between pin 20 of the voice recording and playing chip U3 and the negative pole of the polar capacitor C6, one end of the capacitor C5 is connected to pin 9 of the voice recording and playing chip U3, and the other end thereof is connected to the recording and inputting unit. The 1 pin of the voice recording and playing chip U3 is connected with the 2 pin of the voltage stabilizing chip U1, the 28 pin of the voice recording and playing chip U3 is grounded, the 8 pin of the voice recording and playing chip U3 is connected with the recording input unit, and the 15 pin of the voice recording and playing chip U3 and the negative electrode of the polar capacitor C6 jointly form an output end and are connected with an aircraft audio board. Specifically, the capacitor C5 and the 8 pin of the voice recording and playing chip U3 are connected with the recording input unit through an audio signal line interface.
In this embodiment, the voice recording and playing chip U3 is implemented by using an ISD1760 chip, the negative electrode of the polarity capacitor C6 is connected to the COM3return pin of the GMA340 audio board, and the 15 pin of the voice recording and playing chip U3 is connected to the COM3in pin of the GMA340 audio board. The singlechip is connected with the voice recording and playing unit through an SPI serial port, namely pins 4, 5, 6 and 7 of the voice recording and playing chip U3 are connected with the singlechip through the SPI serial port.
When the voice warning system is manufactured and debugged, the recording input unit records voice signals from pins 8 and 9 of the voice recording and playing chip U3. When the voice warning system is used by a loader after debugging, and when the singlechip outputs an undercarriage warning trigger instruction to the voice recording and playing chip U3 through the SPI serial port, pins 15 and 18 of the voice recording and playing chip U3 output undercarriage voice warning signals to an aircraft audio board; when the singlechip outputs a stall warning trigger instruction to the voice recording and playing chip U3, pins 15 and 18 of the voice recording and playing chip U3 output stall voice warning signals to the audio board of the aircraft. The indicator lamp VD is used for indicating that the voice recording and playing chip U3 works in a single-chip key mode, in this embodiment, the voice recording and playing chip U3 works in an SPI serial command mode, and the indicator lamp VD is inactive, so that the pin is suspended, and therefore, the hardware circuit design of the indicator lamp VD is reserved.
When the voice warning system is manufactured and debugged, the key signal input unit inputs the landing gear abnormal voice warning recording control command to the singlechip, the singlechip receives the landing gear abnormal voice warning recording control command and then sends a landing gear abnormal voice warning recording command to the voice recording and playing unit, and the voice recording and playing unit receives the landing gear abnormal voice warning signal output by the recording input unit after receiving the landing gear abnormal voice warning recording command; the key signal input unit inputs a stall abnormal voice warning recording control command to the singlechip, the singlechip receives the stall abnormal voice warning recording control command and then sends a stall abnormal voice warning recording command to the voice recording and playing unit, and the voice recording and playing unit receives the stall abnormal voice warning signal output by the recording input unit after receiving the stall abnormal voice warning recording command, so that voice recording is completed.
When the voice warning system is installed to work, when the optical coupler isolation unit receives the landing gear warning trigger signal, the optical coupler isolation unit outputs the landing gear warning signal to the singlechip, at the moment, the singlechip sends a landing gear warning trigger instruction to the voice recording and playing unit, and the voice recording and playing unit sends a landing gear voice warning signal to the aircraft audio board according to the landing gear warning trigger instruction, so that the aircraft audio board broadcasts an abnormal landing gear voice warning, and a pilot is reminded. When the optical coupler isolation unit receives the stall warning trigger signal, the optical coupler isolation unit outputs the stall warning signal to the singlechip, at the moment, the singlechip sends a stall warning trigger instruction to the voice recording and playing unit, and the voice recording and playing unit sends the stall voice warning signal to the aircraft audio board according to the stall warning trigger instruction, so that the aircraft audio board broadcasts stall abnormal voice warning, and a pilot is reminded.
In particular, the remaining modular units, except for the aircraft audio boards, are mounted in an 8cm x 10cm aluminum box mounted on an aircraft tail electrical equipment bay (SAT 160, WS 16) on an electrical equipment mounting platform. After the installation of the voice warning system is completed, the current required by the voice warning system in the standby state is 30mA through actual measurement, and the current required by the voice warning system in the playback state is 80mA. The 1A breaker can be additionally arranged on the instrument panel of the airplane as the power supply protection. According to the limit working state, after the additional installation work is completed, the load added by the aircraft power supply system is only 80mA. With respect to the current output capability of the two generators 120A of the PA-44-180 aircraft, the added load is negligible, and no conflict or interference occurs to any existing on-board equipment, so that the safety performance of the aircraft is ensured.
Example 2
The present embodiment is a method for implementing the voice warning system for an aircraft of embodiment 1, comprising the steps of:
step 1: initializing a system, inputting an undercarriage abnormal voice warning signal and a stall abnormal voice warning signal to a voice recording and playing unit through a recording input unit, and entering a warning trigger signal detection state. Specifically, recording the landing gear abnormal voice warning signal and the stall abnormal voice warning signal to the voice recording and playing unit comprises the following steps:
(1) And sending the landing gear abnormal voice warning signal and the stall abnormal voice warning signal to the voice recording and playing unit through the recording input unit.
(2) Recording an undercarriage abnormal voice warning recording control command and a stall abnormal voice warning recording control command to the singlechip through the key signal input unit; when the single chip microcomputer receives the landing gear abnormal voice warning recording control command, sending a landing gear abnormal voice warning recording command to the voice recording and playing unit, and executing the step (3); and (4) when the singlechip receives the stall abnormal voice warning recording control instruction, sending a stall abnormal voice warning recording instruction to the voice recording and playing unit, and executing the step (4).
(3) The voice recording and playing unit stores the landing gear abnormal voice warning signal.
(4) The voice recording and playing unit stores stall abnormal voice warning signals.
Step 2: the optical coupling isolation unit detects whether an undercarriage warning trigger signal or a stall warning trigger signal is input, if yes, the undercarriage warning signal is output to the singlechip, and the step 3 is executed; and outputting a stall warning signal to the singlechip if the stall warning trigger signal is detected to be input, and executing the step 4.
Step 3: and (5) outputting an undercarriage warning triggering instruction to the voice recording and playing unit by the singlechip, and executing the step (5).
Step 4: and the singlechip outputs a stall warning triggering instruction to the voice recording and playing unit and executes the step 6.
Step 5: the voice recording and playing unit outputs a landing gear voice warning signal to the aircraft audio board, and the aircraft audio board broadcasts a landing gear abnormal voice warning.
Step 6: the voice recording and playing unit outputs a stall voice warning signal to the aircraft audio board, and the aircraft audio board broadcasts an undercarriage abnormal voice warning.
Through the steps, the voice warning system can broadcast the landing gear abnormal voice warning and the landing gear abnormal voice warning, the recognition degree of the warning is improved, and a pilot can better recognize the warning type.
As described above, the present invention can be well implemented.
Claims (6)
1. The voice warning system for the aircraft is characterized by comprising an optical coupling isolation unit, a singlechip, a voice recording and playing unit and a power supply unit;
an optical coupling isolation unit: the system is used for receiving landing gear warning trigger signals and stall warning trigger signals outside the system and outputting the landing gear warning signals and stall warning signals to the singlechip; simultaneously, voltage conversion is completed;
and the singlechip is used for: the optical coupler isolation unit is connected with the voice recording and playing unit and used for sending an undercarriage warning trigger instruction to the voice recording and playing unit according to the undercarriage warning signal or sending a stall warning trigger instruction to the voice recording and playing unit according to the stall warning signal;
a voice recording and playing unit: the single chip microcomputer is connected with the landing gear voice warning signal output according to the landing gear warning trigger instruction or the stall voice warning signal output according to the stall warning trigger instruction;
a power supply unit: the device is respectively connected with the optocoupler isolation unit, the singlechip and the voice recording and playing unit, and is used for converting the voltage of the aircraft power supply system and supplying power to the optocoupler isolation unit, the singlechip and the voice recording and playing unit;
also included is an aircraft audio board; the aircraft audio board is connected with the voice recording and playing unit and is used for playing an abnormal voice warning of the landing gear according to the voice warning signal of the landing gear or playing an abnormal voice warning of stall according to the voice warning signal of stall;
the system also comprises a key signal input unit and a recording input unit;
the key signal input unit is connected with the singlechip and is used for inputting control instructions to the singlechip;
the singlechip is also used for sending a recording instruction to the voice recording and playing unit according to the control instruction;
the voice recording and playing unit is also used for receiving voice signals according to the recording instruction;
the recording input unit is connected with the voice recording and playing unit and is used for inputting voice signals to the voice recording and playing unit;
the implementation method of the voice warning system for the aircraft comprises the following steps of:
step 1: initializing a system, inputting an abnormal voice warning signal and a stall abnormal voice warning signal of the landing gear to a voice recording and playing unit, and entering a warning trigger signal detection state;
step 2: the optical coupling isolation unit detects whether an undercarriage warning trigger signal or a stall warning trigger signal is input, if yes, the undercarriage warning signal is output to the singlechip, and the step 3 is executed; outputting a stall warning signal to the singlechip if the stall warning trigger signal is detected to be input, and executing the step 4;
step 3: outputting an undercarriage warning triggering instruction to the voice recording and playing unit by the singlechip, and executing the step 5;
step 4: the singlechip outputs a stall warning triggering instruction to the voice recording and playing unit and executes the step 6;
step 5: the voice recording and playing unit outputs a landing gear voice warning signal to the aircraft audio board, and the aircraft audio board broadcasts a landing gear abnormal voice warning;
step 6: the voice recording and playing unit outputs a stall voice warning signal to the aircraft audio board, and the aircraft audio board broadcasts a stall abnormal voice warning;
the step 1 of inputting the landing gear abnormal voice warning signal and the stall abnormal voice warning signal to the voice recording and playing unit comprises the following steps:
(1) Transmitting an undercarriage abnormal voice warning signal and a stall abnormal voice warning signal to a voice recording and playing unit;
(2) Recording an abnormal voice warning recording control command of the landing gear and a stall abnormal voice warning recording control command to the singlechip; when the single chip microcomputer receives the landing gear abnormal voice warning recording control command, sending a landing gear abnormal voice warning recording command to the voice recording and playing unit, and executing the step (3); when the singlechip receives a stall abnormal voice warning recording control command, sending a stall abnormal voice warning recording command to the voice recording and playing unit, and executing the step (4);
(3) The voice recording and playing unit stores an abnormal voice warning signal of the landing gear;
(4) The voice recording and playing unit stores stall abnormal voice warning signals.
2. The voice warning system for an aircraft of claim 1, further comprising an LED indication unit and a reset unit;
the LED indicating unit is connected with the singlechip and used for displaying the running state of the system;
the reset unit is connected with the singlechip and is used for resetting the system.
3. The voice warning system for an aircraft according to claim 1 or 2, wherein the power supply unit comprises a voltage stabilizing chip U1, a polarity capacitor C1 with a positive electrode connected to pin 2 of the voltage stabilizing chip U1 and a negative electrode grounded, a polarity capacitor C2 with a positive electrode connected to pin 3 of the voltage stabilizing chip U1 and a negative electrode grounded, and a voltage reducing circuit with an output end connected to pin 3 of the voltage stabilizing chip U1 and an input end connected to the aircraft power supply system; and the pin 1 of the voltage stabilizing chip U1 is grounded, and the pin 2 of the voltage stabilizing chip U1 is respectively connected with the optocoupler isolation unit, the singlechip and the voice recording and playing unit.
4. A voice warning system for an aircraft according to claim 3 wherein the step-down circuit comprises five step-down units connected end to end in sequence; the step-down unit comprises two diodes connected in parallel.
5. The voice warning system for an aircraft according to claim 4, wherein the optocoupler isolation unit includes a optocoupler isolation chip U2, a resistor R1 having one end connected to a 2 pin of the optocoupler isolation chip U2 and the other end grounded, a resistor R2 having one end connected to a 4 pin of the optocoupler isolation chip U2 and the other end serving as an input end of a stall warning trigger signal, a resistor R3 having one end connected to an 8 pin of the optocoupler isolation chip U2 and the other end connected to a 2 pin of the voltage regulator chip U1, and a resistor R4 having one end connected to a 6 pin of the optocoupler isolation chip U2 and the other end connected to a 2 pin of the voltage regulator chip U1; the 1 pin of the photoelectric isolation chip U2 is used as an input end of an undercarriage warning trigger signal, the 3 pin of the photoelectric isolation chip U2 is connected with an aircraft power supply system, the 7 pin and the 5 pin of the photoelectric isolation chip U2 are grounded, the 8 pin of the photoelectric isolation chip U2 is used as an undercarriage warning signal output end, and the 6 pin of the photoelectric isolation chip U2 is used as a stall warning signal output end.
6. The system according to claim 4 or 5, wherein the voice recording and playing unit comprises a voice recording and playing chip U3, a polar capacitor C4 with a positive electrode connected to pin 1 of the voice recording and playing chip U3, a negative electrode connected to pin 28 of the voice recording and playing chip U3, a capacitor C3 with a parallel connection to the polar capacitor C4, a resistor R5 with one end connected to pin 2 of the voice recording and playing chip U3 after passing through the indicator lamp VD, and the other end connected to pin 2 of the voltage stabilizing chip U1, a polar capacitor C6 with a positive electrode connected to pin 18 of the voice recording and playing chip U3, a negative electrode grounded, a resistor R6 connected in series between pin 20 of the voice recording and playing chip U3 and the negative electrode of the polar capacitor C6, and a capacitor C5 with one end connected to pin 9 of the voice recording and playing chip U3 and the other end connected to the recording and inputting unit; the 1 pin of the voice recording and playing chip U3 is connected with the 2 pin of the voltage stabilizing chip U1, the 28 pin of the voice recording and playing chip U3 is grounded, the 8 pin of the voice recording and playing chip U3 is connected with the recording input unit, and the 15 pin of the voice recording and playing chip U3 and the negative electrode of the polar capacitor C6 jointly form an output end and are connected with an aircraft audio board.
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| CN111583727B (en) * | 2020-06-17 | 2023-08-25 | 中国民用航空飞行学院 | Automatic alarm for air dangerous approaching and alarm control method thereof |
| CN112373697B (en) * | 2020-10-30 | 2022-11-18 | 哈尔滨飞机工业集团有限责任公司 | Aircraft icing stall warning system and method |
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