An aircraft autopilot amplifier inspection device and method

Abstract

The application discloses an airplane pilot amplifier inspection device and method, and belongs to the technical field of aircraft inspection. The airplane pilot amplifier inspection device provided by the application comprises a main control module, a pitch module, a roll module, a yaw module, a speed maintaining module and a steering engine module, and the main control module is connected with the pitch module, the roll module, the yaw module, the speed maintaining module and the steering engine module in series. The pilot amplifier function and performance are checked by simulating the pitch state, the roll state, the yaw state and the speed maintaining state of the airplane, and the automatic detection function is provided, so that the work burden of the tester is reduced, and the airplane detection efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft inspection technology, and in particular to an aircraft cockpit amplifier inspection device and method. Background Technology

[0002] The autopilot amplifier can control the pitch, roll (dual motor) servos, and yaw trim servos based on the stabilization signals established by the control and stabilization computer. On the other hand, it can also provide various signals used by the control and stabilization computer (speed hold, yaw electronic trim, etc.). The autopilot amplifier also has the circuitry of a common monitoring system.

[0003] The driver amplifier mainly has the following functions:

[0004] 1. Amplify the stabilization signals from the two circuits in the roll and pitch channels, output by the control stabilization computer. The average value of this amplified stabilization signal controls the motors of the dual-motor servo in the pitch channel or the two dual-motor servos in the roll channel.

[0005] 2. Monitor the operation of the entire autopilot's roll and pitch channels, and activate alarms and deactivate automatic trim in case of malfunction.

[0006] 3. By controlling the signals of the stabilization computer and other components of the stabilization system, the control servo and trim servo of the yaw channel are controlled to ensure the monitoring of the yaw channel operation.

[0007] 4. When the "Speed ​​Hold" function is activated, it can control the aircraft speed at the value selected by the pilot.

[0008] The current inspection device uses indicator lights to display the output signals of each channel of the autopilot amplifier. Since the autopilot amplifier has many output signals, the current inspection device has a large operating panel. Furthermore, because the operation does not provide prompts, each step of the operation requires relevant professional knowledge, resulting in an unfriendly human-machine interface. The current inspection device does not have the function of simulating a servo motor, which increases the difficulty of the inspection operation. Summary of the Invention

[0009] The purpose of this invention is to overcome the shortcomings of the prior art and provide an aircraft pilot amplifier inspection device and method.

[0010] The objective of this invention is achieved through the following technical solution: The first aspect of this invention provides: an aircraft autopilot amplifier inspection device, comprising a main control module, a pitch module, a roll module, a yaw module, a speed holding module, and a servo module. The main control module is serially connected to the pitch module, roll module, yaw module, speed holding module, and servo module. The main control module includes a main controller and a current acquisition circuit connected to the main controller. The pitch module includes a pitch microprocessor and a pitch control circuit connected to the pitch microprocessor. The roll module includes a roll microprocessor and a roll control circuit connected to the roll microprocessor. The yaw module includes a yaw microprocessor and a yaw control circuit connected to the yaw microprocessor. The speed holding module includes a speed holding microprocessor and a speed holding control circuit connected to the speed holding microprocessor. The servo module includes a servo microprocessor and a servo simulator connected to the servo microprocessor. The servo simulator is connected to the pitch control circuit, roll control circuit, yaw control circuit, and speed holding control circuit to simulate the aircraft's pitch, roll, yaw, and speed holding states.

[0011] Preferably, the main control module is serially connected to the pitch module, roll module, yaw module, speed holding module, and servo module via an RS232 serial bus.

[0012] Preferably, it also includes a display module connected to the main controller. When a display serial port command arrives, the main controller decodes the received data and sends the corresponding command to the pitch module, roll module, yaw module, speed holding module, and servo module.

[0013] Preferably, the current acquisition circuit includes a sixth relay K6, a fourteenth resistor R14, a seventeenth resistor R17, an eighteenth resistor R18, a twenty-fourth resistor R24, a twenty-fifth resistor R25, and a seventh differential amplifier U7; the trigger terminal of the sixth relay K6 is connected to the first terminal of the fourteenth resistor R14 and the first terminal of the seventeenth resistor R17; the second terminal of the fourteenth resistor R14 is connected to the first terminal of the eighteenth resistor R18; the second terminal of the seventeenth resistor R17 is connected to the first terminal of the twenty-fourth resistor R24 ​​and the negative input terminal of the seventh differential amplifier U7; the second terminal of the eighteenth resistor R18 is connected to the positive input terminal of the seventh differential amplifier U7 and the first terminal of the twenty-fifth resistor R25; the second terminal of the twenty-fourth resistor R24 ​​is grounded to GND; the second terminal of the twenty-fifth resistor R25 is grounded to GND; the output terminal of the seventh differential amplifier U7 is connected to the main controller; and the fourteenth resistor R14 is 0.1Ω.

[0014] Preferably, the pitch module further includes a relay control circuit and a relay drive circuit. The relay control circuit is connected to the relay drive circuit. The relay drive circuit includes a buffer U9 and an open-drain driver U11. The buffer U9 is connected to the open-drain driver U11. The open-drain driver U11 contains a Darlington transistor. After the buffer U9 converts the level output by the main controller, the Darlington transistor is turned on.

[0015] Preferably, the pitch module further includes an AD acquisition step-down circuit, which includes a first operational amplifier U1A, a second operational amplifier U1B, a second resistor R2, and a fourth resistor R4. The output terminal of the first operational amplifier U1A is connected to the negative input terminal of the first operational amplifier U1A and the first terminal of the second resistor R2. The second terminal of the second resistor R2 is connected to the first terminal of the fourth resistor R4 and the positive input terminal of the second operational amplifier U1B. The second terminal of the fourth resistor R4 is grounded (GND). The output terminal of the second operational amplifier U1B is connected to the negative input terminal of the second operational amplifier U1B and the main controller.

[0016] Preferably, the servo module further includes a positive and negative reference generation circuit, which includes a ninth reference voltage chip U9, a thirty-first operational amplifier U31, a twelfth capacitor C12, a thirteenth capacitor C13, a fourteenth capacitor C14, a fifteenth capacitor C15, a sixteenth capacitor C16, a first inductor L1, a sixty-fourth resistor R64, a sixty-fifth resistor R65, and a sixty-sixth resistor R66. The positive terminal of the twelfth capacitor C12 is connected to the power supply and the VS terminal of the ninth reference voltage chip U9, and the negative terminal of the twelfth capacitor C12 is grounded. The positive terminal of the thirteenth capacitor C13 is connected to the power supply and the VS terminal of the ninth reference voltage chip U9, and the negative terminal of the thirteenth capacitor C13 is grounded. The positive terminal of the fourteenth capacitor C14 is connected to the OU terminal of the ninth reference voltage chip U9. Terminal T, the negative terminal of the fourteenth capacitor C14 is grounded, the positive terminal of the fifteenth capacitor C15 is connected to the OUT terminal of the ninth reference voltage chip U9 and the first terminal of the first inductor L1, the negative terminal of the fifteenth capacitor C15 is grounded, the second terminal of the first inductor L1 is connected to the positive terminal of the sixteenth capacitor C16 and the first terminal of the sixty-fifth resistor R65, the negative terminal of the sixteenth capacitor C16 is grounded, the second terminal of the sixty-fifth resistor R65 is connected to the negative input terminal of the thirty-first operational amplifier U31 and the first terminal of the sixty-fourth resistor R64, the second terminal of the sixty-fourth resistor R64 is connected to the output terminal of the thirty-first operational amplifier U31, the first terminal of the sixty-sixth resistor R66 is connected to the positive input terminal of the thirty-first operational amplifier U31, and the second terminal of the sixty-sixth resistor R66 is grounded (GND).

[0017] Preferably, the servo module further includes a DAC conversion circuit, which includes a seventeenth digital-to-analog converter U17, a fifteenth operational amplifier U15, a fourteenth operational amplifier U14A, and a thirteenth operational amplifier U14B. The Iout1 terminal of the seventeenth digital-to-analog converter U17 is connected to the negative input terminal of the fifteenth operational amplifier U15, the Iout2 terminal of the seventeenth digital-to-analog converter U17 is connected to the positive input terminal of the fifteenth operational amplifier U15, the output terminal of the fifteenth operational amplifier U15 is connected to the positive input terminal of the fourteenth operational amplifier U14A, and the output terminal of the fourteenth operational amplifier U14A is connected to the positive input terminal of the thirteenth operational amplifier U14B.

[0018] A second aspect of the present invention provides: a method for inspecting an aircraft cockpit amplifier, used in any of the aforementioned aircraft cockpit amplifier inspection devices, comprising the following steps:

[0019] S1: Initialization phase, initialize the basic parameters of the display module, main control module, pitch module, roll module, yaw module, speed holding module and servo module;

[0020] S2: Standby phase: The main control module determines whether a command has been received. If a command is received, it enters the S3 execution phase; otherwise, it returns to the S2 standby phase.

[0021] S3: Execution phase. The main control module determines whether it needs to send the command to other modules. If not, it directly executes the received command. If so, it sends the command to other modules. After the other modules complete the corresponding operation, they issue a completion command and enter the S4 termination phase.

[0022] S4: End phase. After setting all modules except the main control module and display module to their initial state, disconnect the power.

[0023] Preferably, the S2 standby phase receives commands from the display module.

[0024] The beneficial effects of this invention are:

[0025] 1) By simulating the output of DC, ramp, and AC signals through the servo circuit, closed-loop control is achieved to realize automatic testing; the embedded microcontroller design makes the testing more intelligent, which can improve testing efficiency and reduce labor intensity.

[0026] 2) The design incorporates a touchscreen, providing excellent human-computer interaction capabilities.

[0027] 3) It is compatible with different test cables and test software, enabling the testing of autopilot amplifiers of different models.

[0028] 4) By simulating and acquiring signals from the pitch, roll, yaw, and speed hold components, and simultaneously analyzing and processing the test data, the performance of the aircraft's autopilot amplifier can be checked. Attached Figure Description

[0029] Figure 1 for Figure 1 Block diagram of the aircraft cockpit amplifier inspection device of the present invention;

[0030] Figure 2 This is a functional block diagram of the main control module of the aircraft pilot amplifier inspection device of the present invention;

[0031] Figure 3 This is a simplified circuit diagram of the main controller of the aircraft pilot amplifier inspection device of the present invention;

[0032] Figure 4 This is a circuit diagram of the power supply and current acquisition section of the aircraft pilot amplifier inspection device of the present invention.

[0033] Figure 5 This is a circuit diagram of the ADC analog-to-digital converter for the aircraft pilot amplifier testing device of the present invention.

[0034] Figure 6 This is a circuit diagram of the relay control circuit for the aircraft pilot amplifier inspection device of the present invention.

[0035] Figure 7 This is a circuit diagram of the relay drive circuit for the aircraft pilot amplifier inspection device of the present invention.

[0036] Figure 8 This is a circuit diagram of the AD acquisition step-down circuit of the aircraft pilot amplifier testing device of the present invention;

[0037] Figure 9 This is a circuit diagram of the alarm signal step-down circuit of the aircraft cockpit amplifier inspection device of the present invention;

[0038] Figure 10 This is a circuit diagram of the differential amplification and step-down circuit of the aircraft pilot amplifier testing device of the present invention;

[0039] Figure 11 This is a circuit diagram of the positive and negative reference generation device for the aircraft pilot amplifier testing device of the present invention;

[0040] Figure 12 This is a circuit diagram of the DAC conversion device for the aircraft pilot amplifier testing device of the present invention;

[0041] Figure 13 This is a flowchart of the aircraft cockpit amplifier inspection method of the present invention;

[0042] Figure 14 This is a front view of the panel of the aircraft pilot amplifier inspection device of the present invention;

[0043] Figure 15 This is a rear view of the panel of the aircraft pilot amplifier inspection device of the present invention;

[0044] In the diagram: 1-LCD display screen, 2-Adjustment knob, 3-First amplifier interface, 4-Second amplifier interface, 5-First O-amplifier interface, 6-Instrument interface, 7-First overcurrent protection, 8-Second overcurrent protection, 9-Power input port, 10-Power indicator light, 11-Power switch, 12-First voltage measurement black test port, 13-Second voltage measurement black test port, 14-Third voltage measurement black test port, 15-Fourth voltage measurement black test port, 16-First voltage measurement red test port, 17-Second voltage measurement red test port Hole, 18-Third voltage meter red test hole, 19-Fourth voltage meter red test hole, 20-Fifth voltage meter black test hole, 21-Sixth voltage meter black test hole, 22-Seventh voltage meter black test hole, 23-Eighth voltage meter black test hole, 24-Ninth voltage meter black test hole, 25-Fifth voltage meter red test hole, 26-Sixth voltage meter red test hole, 27-Seventh voltage meter red test hole, 28-Eighth voltage meter red test hole, 29-Ninth voltage meter red test hole, 30-Ground, 31-Label. Detailed Implementation

[0045] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. 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 skilled in the art without creative effort are within the scope of protection of the present invention.

[0046] See Figures 1-15The first aspect of the present invention provides: an aircraft autopilot amplifier inspection device, comprising a main control module, a pitch module, a roll module, a yaw module, a speed holding module, and a servo module, wherein the main control module is serially connected to the pitch module, roll module, yaw module, speed holding module, and servo module; the main control module includes a main controller and a current acquisition circuit connected to the main controller; the pitch module includes a pitch microprocessor and a pitch control circuit connected to the pitch microprocessor; the roll module includes a roll microprocessor and a roll control circuit connected to the roll microprocessor; the yaw module includes a yaw microprocessor and a yaw control circuit connected to the yaw microprocessor; the speed holding module includes a speed holding microprocessor and a speed holding control circuit connected to the speed holding microprocessor; the servo module includes a servo microprocessor and a servo simulator connected to the servo microprocessor; the servo simulator is connected to the pitch control circuit, roll control circuit, yaw control circuit, and speed holding control circuit to simulate the aircraft's pitch state, roll state, yaw state, and speed holding state.

[0047] The main control processor uses an STM32103RC chip as its core processor and connects serially to other modules (lower-level devices) via an RS232 serial bus. The main control microprocessor first initializes the display function and waits for serial port commands from the external display. When a serial port command arrives, the main control microprocessor is triggered. The processor decodes the received data and sends the corresponding command to the lower-level device via the serial port. After receiving the command from the main control processor, the lower-level device decodes the command, returns the received instruction, and executes the corresponding action. Its functional block diagram is shown below. Figure 2 As shown.

[0048] In some embodiments, the main control module is serially connected to the pitch module, roll module, yaw module, speed holding module, and servo module via an RS232 serial bus.

[0049] In some embodiments, a display module connected to the main controller is also included. When a display serial port command arrives, the main controller decodes the received data and sends the corresponding command to the pitch module, roll module, yaw module, speed holding module, and servo module.

[0050] The main control unit primarily performs three functions: receiving and decoding / forwarding touchscreen commands, powering on, and acquiring current. Receiving serial port commands: such as... Figure 3The diagram shows a simplified circuit diagram of a microprocessor. The microprocessor has three serial ports: one for communication with the display, one for communication with the lower-level module, and one for communication with an external measuring device such as a benchtop multimeter. After receiving data, the processor first checks the frame header. If the header is correct, it extracts the command code and determines whether to send it to the lower-level module or perform its own action. The self-action mainly involves powering on the power supply and measuring the current. The STM32 microprocessor is chosen because it offers advantages such as high speed, numerous peripherals, ease of operation, stability, reliability, and powerful computing capabilities. It can quickly process received data and send it to the lower-level module, shortening the overall system communication time and ensuring reliability.

[0051] In some embodiments, the current acquisition circuit includes a sixth relay K6, a fourteenth resistor R14, a seventeenth resistor R17, an eighteenth resistor R18, a twenty-fourth resistor R24, a twenty-fifth resistor R25, and a seventh differential amplifier U7. The trigger terminal of the sixth relay K6 is connected to the first terminal of the fourteenth resistor R14 and the first terminal of the seventeenth resistor R17. The second terminal of the fourteenth resistor R14 is connected to the first terminal of the eighteenth resistor R18. The second terminal of the seventeenth resistor R17 is connected to the first terminal of the twenty-fourth resistor R24 ​​and the negative input terminal of the seventh differential amplifier U7. The second terminal of the eighteenth resistor R18 is connected to the positive input terminal of the seventh differential amplifier U7 and the first terminal of the twenty-fifth resistor R25. The second terminal of the twenty-fourth resistor R24 ​​is grounded to GND. The second terminal of the twenty-fifth resistor R25 is grounded to GND. The output terminal of the seventh differential amplifier U7 is connected to the main controller. The fourteenth resistor R14 is 0.1Ω.

[0052] Power-on and current acquisition: When a command arrives from the display and a specific operation is performed, the main controller should immediately power on and continue operating until the display issues a command indicating that the operation is complete. For example... Figure 4 The diagram shows a partial circuit diagram for power-on and current acquisition. When both the processor's PC1 and PE2 ports output high levels, an external +28V power supply is connected to the J50-N port of the device under test (DUT), completing power supply and simultaneously activating the current acquisition function. After the external power supply enters, it is first filtered by a TT-type filter, and then output in series with a sampling resistor. To reduce the voltage drop and energy consumption caused by the sampling resistor, a 0.1Ω resistor is selected. When the main circuit current is 1A, the voltage drop in the main circuit is 0.1V, which is a reasonable design. Current acquisition is accomplished using a differential amplifier. The maximum current in the main circuit is 250mA, therefore the voltage drop across the sampling resistor is 0.025V. Figure 4 U7 is a 100x fixed-gain differential amplifier. Therefore, when the main circuit current is at its maximum, the maximum output voltage of U7 is 0.025 x 100 = 2.5V. This voltage is input to the ADC (Analog-to-Digital Converter), such as... Figure 5 As shown, the main control microprocessor reads the voltage data from the converter. Finally, the main control microprocessor converts the voltage value into a current value and sends the data to the display for display.

[0053] In some embodiments, the pitch module further includes a relay control circuit and a relay drive circuit. The relay control circuit is connected to the relay drive circuit. The relay drive circuit includes a buffer U9 and an open-drain driver U11. The buffer U9 is connected to the open-drain driver U11. The open-drain driver U11 contains a Darlington transistor. After the buffer U9 converts the level output by the main controller, the Darlington transistor is turned on.

[0054] The pitch, roll, yaw, and speed hold circuits are similar in structure and type; here, we'll use the pitch circuit as an example. The pitch section mainly controls discrete quantities, analog input signals, acquires voltage data, and determines high and low voltage. The pitch section primarily consists of a microprocessor and control circuitry. The microprocessor communicates with the main controller via a serial port to complete the actions corresponding to the main controller's commands and sends the data back to the main controller. Controlling discrete quantities includes... Figure 6 As shown, this circuit controls the activation of pitch circuits 1 and 2. Pitch circuit 1 is activated when J50-E receives a +28V power supply, and pitch circuit 2 is activated when J51-V receives a +28V power supply. After receiving the activation command, the pitch section microprocessor controls PB10 and PB9, which, through the drive circuit, control the switching of relays K1 and K2. Figure 6 It is a relay control circuit. Figure 7 This is a relay drive circuit. For example... Figure 7 In the circuit shown, U9 is a buffer that also serves as an isolation and level converter. U9 converts the 3.3V output from the microprocessor to a 5V level, while U11 is an open-drain driver for an internal Darlington transistor. When the microprocessor outputs a high level, the relay coil acts as a pull-up resistor for the collector. By selecting an appropriate resistor, the Darlington transistor conducts, and the relay operates.

[0055] The input of analog signals is also accomplished through relay control, and its control circuit is similar to... Figure 6 , Figure 7 similar.

[0056] In some embodiments, the pitch module further includes an AD acquisition step-down circuit, which includes a first operational amplifier U1A, a second operational amplifier U1B, a second resistor R2, and a fourth resistor R4. The output terminal of the first operational amplifier U1A is connected to the negative input terminal of the first operational amplifier U1A and the first terminal of the second resistor R2. The second terminal of the second resistor R2 is connected to the first terminal of the fourth resistor R4 and the positive input terminal of the second operational amplifier U1B. The second terminal of the fourth resistor R4 is grounded (GND). The output terminal of the second operational amplifier U1B is connected to the negative input terminal of the second operational amplifier U1B and the main controller.

[0057] For voltage acquisition, to prevent interference from downstream circuits to the upstream servo simulator, an operational amplifier follower—step-down—operational amplifier follower mode is used at the voltage acquisition end. Since the maximum external voltage can reach 12V, step-down processing is necessary, such as... Figure 8 The circuit shown is a step-down circuit for the data acquisition unit. The maximum output voltage through the operational amplifier is 12 / 5 = 2.5V, which matches the maximum acquisition voltage range of the subsequent ADC converter. The ADC converter circuit is as follows: Figure 5 As shown.

[0058] like Figure 9 The circuit shown is for acquiring alarm signals. Since alarm signals are all level signals, the high-level voltage is 15V. Figure 9 After the voltage reduction process, the maximum high-level voltage becomes 15 / 3.5 = 4.28V, which is within the TTL range and meets the voltage range of the microprocessor input signal.

[0059] In some embodiments, the servo module further includes a positive and negative reference generation circuit. The positive and negative reference generation circuit includes a ninth reference voltage chip U9, a thirty-first operational amplifier U31, a twelfth capacitor C12, a thirteenth capacitor C13, a fourteenth capacitor C14, a fifteenth capacitor C15, a sixteenth capacitor C16, a first inductor L1, a sixty-fourth resistor R64, a sixty-fifth resistor R65, and a sixty-sixth resistor R66. The positive terminal of the twelfth capacitor C12 is connected to the power supply and the VS terminal of the ninth reference voltage chip U9, and the negative terminal of the twelfth capacitor C12 is grounded. The positive terminal of the thirteenth capacitor C13 is connected to the power supply and the VS terminal of the ninth reference voltage chip U9, and the negative terminal of the thirteenth capacitor C13 is grounded. The positive terminal of the fourteenth capacitor C14 is connected to the ninth reference voltage chip U9. At the OUT terminal, the negative terminal of the fourteenth capacitor C14 is grounded. The positive terminal of the fifteenth capacitor C15 is connected to the OUT terminal of the ninth reference voltage chip U9 and the first terminal of the first inductor L1. The negative terminal of the fifteenth capacitor C15 is grounded. The second terminal of the first inductor L1 is connected to the positive terminal of the sixteenth capacitor C16 and the first terminal of the sixty-fifth resistor R65. The negative terminal of the sixteenth capacitor C16 is grounded. The second terminal of the sixty-fifth resistor R65 is connected to the negative input terminal of the thirty-first operational amplifier U31 and the first terminal of the sixty-fourth resistor R64. The second terminal of the sixty-fourth resistor R64 is connected to the output terminal of the thirty-first operational amplifier U31. The first terminal of the sixty-sixth resistor R66 is connected to the positive input terminal of the thirty-first operational amplifier U31. The second terminal of the sixty-sixth resistor R66 is grounded (GND).

[0060] The servo simulator section mainly consists of a microprocessor, operational amplifiers, an ADC (analog-to-digital converter), and a DAC (digital-to-analog converter). The microprocessor controls the ADC and DAC, performing functions such as servo voltage acquisition, outputting servo feedback voltage, and generating the necessary signals for pitch and roll. In yaw and airspeed holding, the servo simulator only provides various signals. During servo operation, the pitch section requires two feedback signals, and the roll section requires four. Including other external input signals, the servo section has a total of eight signal outputs, all with identical circuit structures. Additionally, the servo requires voltage acquisition at its terminals, necessitating a six-channel ADC acquisition circuit, also with the same circuit structure.

[0061] The ADC analog-to-digital converter circuit consists of a differential amplifier, a step-down converter, and an ADC acquisition unit, where the ADC acquisition unit is as follows: Figure 5 As shown, further details will not be repeated. The differential amplifier and buck converter circuits are as follows: Figure 10As shown, since the subsequent ADC acquisition unit can acquire both positive and negative voltages, there is no need to perform absolute value processing on the differentially amplified signal. U6A performs the differential function, and then a voltage follower is used after resistor division to match the input impedance of the subsequent ADC. The output voltage of U6 is U = (UB - UA) / 6.1. The maximum voltage of UB - UA is 28V. Therefore, the maximum voltage of AD1 is 4.59V < 5.3V, which is within the acquisition voltage range of the subsequent ADC analog-to-digital converter.

[0062] In some embodiments, the servo module further includes a DAC conversion circuit, which includes a seventeenth digital-to-analog converter U17, a fifteenth operational amplifier U15, a fourteenth operational amplifier U14A, and a thirteenth operational amplifier U14B. The Iout1 terminal of the seventeenth digital-to-analog converter U17 is connected to the negative input terminal of the fifteenth operational amplifier U15, the Iout2 terminal of the seventeenth digital-to-analog converter U17 is connected to the positive input terminal of the fifteenth operational amplifier U15, the output terminal of the fifteenth operational amplifier U15 is connected to the positive input terminal of the fourteenth operational amplifier U14A, and the output terminal of the fourteenth operational amplifier U14A is connected to the positive input terminal of the thirteenth operational amplifier U14B.

[0063] A DAC (Digital-to-Analog Converter) circuit mainly consists of a reference source, a switching circuit, and a DAC conversion circuit. Since it needs to generate both positive and negative signals, the reference source must also have positive and negative values. For example... Figure 11 The diagram shows the reference source circuit. The negative reference is obtained by passing the positive reference through a non-amplifying inverting amplifier. The selection of the positive and negative references is accomplished by a microprocessor-controlled analog switch. The DAC conversion circuit is shown below. Figure 12 As shown, U17 is a digital-to-analog converter (DAC), and U15 is an operational amplifier. The DAC7811 is a serial-channel current-output 12-bit multiplicative DAC with an accuracy of [missing information - likely a value] when the reference voltage is 1.65V. It has an R-2R trapezoidal structure, with each 2R pin connected to the end of Iout1 or Iout2. This R-2R structure is connected to an external reference input Vref, enabling the DAC to draw its full current. The DAC7811's external reference current can vary from -15V to +15V, thus allowing for bipolar current output. After passing through the subsequent operational amplifier, positive and negative polarity signals can be output. The maximum voltage of the signal output through U15 is 3.3V, which does not meet the required signal specifications, therefore further amplification is necessary. U14A is the post-amplifier, and U14B is a voltage follower used to improve the signal's load-driving capability.

[0064] A second aspect of the present invention provides: a method for inspecting an aircraft cockpit amplifier, used in any of the aforementioned aircraft cockpit amplifier inspection devices, comprising the following steps:

[0065] S1: Initialization phase, initialize the basic parameters of the display module, main control module, pitch module, roll module, yaw module, speed holding module and servo module;

[0066] S2: Standby phase: The main control module determines whether a command has been received. If a command is received, it enters the S3 execution phase; otherwise, it returns to the S2 standby phase.

[0067] S3: Execution phase. The main control module determines whether it needs to send the command to other modules. If not, it directly executes the received command. If so, it sends the command to other modules. After the other modules complete the corresponding operation, they issue a completion command and enter the S4 termination phase.

[0068] S4: End phase. After setting all modules except the main control module and display module to their initial state, disconnect the power.

[0069] The testing procedures for all parts of the inspection device are the same. The program is written in C language and employs structured programming, using a top-down approach to decompose each functional module. Each functional module is designed as a subroutine, and the main program implements various functions by calling the corresponding subroutines, giving the program excellent readability and extensibility. See the software flowchart below. Figure 13 .

[0070] In some embodiments, the S2 standby phase receives a command from the display module.

[0071] In the inspection device, the main controller acts as both the lower-level machine for the display and the upper-level machine for other parts. Upon receiving serial data from the display, the main controller first decodes it and determines whether a command needs to be sent to other parts. If not, it directly executes the corresponding command and returns the measurement data. If so, it also performs tasks necessary to ensure the normal operation of other parts and simultaneously sends the serial command to its lower-level machine. Upon receiving the data, the lower-level machine directly executes the corresponding operation according to the command until a completion command is issued. At this point, all parts of the inspection device except the main controller and the display are set to their initial state, and the power is then disconnected.

[0072] like Figures 14-15 As shown, the LCD screen 1 is used for display and user operation interaction; the adjustment knob 2 is used for user forced interruption and reset; the first amplifier interface 3 and the second amplifier interface 4 are used for amplifier signal input or output; the first O amplifier interface 5 is used for O amplifier signal input or output; the instrument interface 6 is a reserved debugging interface; the first overcurrent protection 7 is a fuse 1A; the second overcurrent protection 8 is a fuse 2A; the power input port 9 is used for +27V and ~115V power input; the power indicator light 10 is used to indicate the power status; and the power switch 11 is used to control the power on and off.

[0073] The above description is merely a preferred embodiment of the present invention. It should be understood that the present invention is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the concept described herein through the above teachings or related technologies or knowledge. Modifications and variations made by those skilled in the art that do not depart from the spirit and scope of the present invention should be within the protection scope of the appended claims.

Claims

1. An aircraft autopilot amplifier check device, characterized by: The system includes a main control module, a pitch module, a roll module, a yaw module, a speed holding module, and a servo module. The main control module is serially connected to the pitch, roll, yaw, speed holding, and servo modules. The main control module includes a main controller and a current acquisition circuit connected to the main controller. The pitch module includes a pitch microprocessor and a pitch control circuit connected to the pitch microprocessor. The roll module includes a roll microprocessor and a roll control circuit connected to the roll microprocessor. The yaw module includes a yaw microprocessor and a yaw control circuit connected to the yaw microprocessor. The speed holding module includes a speed holding microprocessor and a speed holding control circuit connected to the speed holding microprocessor. The servo module includes a servo microprocessor and a servo simulator connected to the servo microprocessor. The servo simulator is connected to the pitch control circuit, roll control circuit, yaw control circuit, and speed holding control circuit to simulate the aircraft's pitch, roll, yaw, and speed holding states. The current acquisition circuit includes a sixth relay K6, a fourteenth resistor R14, a seventeenth resistor R17, an eighteenth resistor R18, a twenty-fourth resistor R24, a twenty-fifth resistor R25, and a seventh differential amplifier U7. The trigger terminal of the sixth relay K6 is connected to the first terminal of the fourteenth resistor R14 and the first terminal of the seventeenth resistor R17. The second terminal of the fourteenth resistor R14 is connected to the first terminal of the eighteenth resistor R18. The second terminal of the seventeenth resistor R17 is connected to the first terminal of the twenty-fourth resistor R24 ​​and the negative input terminal of the seventh differential amplifier U7. The second terminal of the eighteenth resistor R18 is connected to the positive input terminal of the seventh differential amplifier U7 and the first terminal of the twenty-fifth resistor R25. The second terminal of the twenty-fourth resistor R24 ​​is grounded to GND. The second terminal of the twenty-fifth resistor R25 is grounded to GND. The output terminal of the seventh differential amplifier U7 is connected to the main controller. The fourteenth resistor R14 has a resistance of 0.1Ω.

2. The aircraft autopilot amplifier check device of claim 1, wherein: The main control module is serially connected to the pitch module, roll module, yaw module, speed holding module, and servo module via an RS232 serial bus.

3. The aircraft autopilot amplifier check device of claim 1, wherein: It also includes a display module connected to the main controller. When a display serial port command arrives, the main controller will decode the received data and send the corresponding command to the pitch module, roll module, yaw module, speed holding module, and servo module.

4. The aircraft autopilot amplifier check device of claim 1, wherein: The pitch module also includes a relay control circuit and a relay drive circuit. The relay control circuit is connected to the relay drive circuit. The relay drive circuit includes a buffer U9 and an open-drain driver U11. The buffer U9 is connected to the open-drain driver U11. The open-drain driver U11 contains a Darlington transistor. After the buffer U9 converts the level output by the main controller, the Darlington transistor is turned on.

5. The aircraft autopilot amplifier check device of claim 4, wherein: The pitch module also includes an AD acquisition step-down circuit, which includes a first operational amplifier U1A, a second operational amplifier U1B, a second resistor R2, and a fourth resistor R4. The output terminal of the first operational amplifier U1A is connected to the negative input terminal of the first operational amplifier U1A and the first terminal of the second resistor R2. The second terminal of the second resistor R2 is connected to the first terminal of the fourth resistor R4 and the positive input terminal of the second operational amplifier U1B. The second terminal of the fourth resistor R4 is grounded (GND). The output terminal of the second operational amplifier U1B is connected to the negative input terminal of the second operational amplifier U1B and the main controller.

6. The aircraft autopilot amplifier check device of claim 1, wherein: The servo module further includes a positive and negative reference generation circuit, which includes a ninth reference voltage chip U9, a thirty-first operational amplifier U31, a twelfth capacitor C12, a thirteenth capacitor C13, a fourteenth capacitor C14, a fifteenth capacitor C15, a sixteenth capacitor C16, a first inductor L1, a sixty-fourth resistor R64, a sixty-fifth resistor R65, and a sixty-sixth resistor R66. The positive terminal of the twelfth capacitor C12 is connected to the power supply and the VS terminal of the ninth reference voltage chip U9, and the negative terminal of the twelfth capacitor C12 is grounded. The positive terminal of the thirteenth capacitor C13 is connected to the power supply and the VS terminal of the ninth reference voltage chip U9, and the negative terminal of the thirteenth capacitor C13 is grounded. The positive terminal of the fourteenth capacitor C14 is connected to the OUT terminal of the ninth reference voltage chip U9. The negative terminal of the fourteenth capacitor C14 is grounded. The positive terminal of the fifteenth capacitor C15 is connected to the OUT terminal of the ninth reference voltage chip U9 and the first terminal of the first inductor L1. The negative terminal of the fifteenth capacitor C15 is grounded. The second terminal of the first inductor L1 is connected to the positive terminal of the sixteenth capacitor C16 and the first terminal of the sixty-fifth resistor R65. The negative terminal of the sixteenth capacitor C16 is grounded. The second terminal of the sixty-fifth resistor R65 is connected to the negative input terminal of the thirty-first operational amplifier U31 and the first terminal of the sixty-fourth resistor R64. The second terminal of the sixty-fourth resistor R64 is connected to the output terminal of the thirty-first operational amplifier U31. The first terminal of the sixty-sixth resistor R66 is connected to the positive input terminal of the thirty-first operational amplifier U31. The second terminal of the sixty-sixth resistor R66 is grounded (GND).

7. The aircraft autopilot amplifier check device of claim 6, wherein: The servo module also includes a DAC conversion circuit, which includes a seventeenth digital-to-analog converter U17, a fifteenth operational amplifier U15, a fourteenth operational amplifier U14A, and a thirteenth operational amplifier U14B. The Iout1 terminal of the seventeenth digital-to-analog converter U17 is connected to the negative input terminal of the fifteenth operational amplifier U15, and the Iout2 terminal of the seventeenth digital-to-analog converter U17 is connected to the positive input terminal of the fifteenth operational amplifier U15. The output terminal of the fifteenth operational amplifier U15 is connected to the positive input terminal of the fourteenth operational amplifier U14A, and the output terminal of the fourteenth operational amplifier U14A is connected to the positive input terminal of the thirteenth operational amplifier U14B.

8. A method for checking an aircraft autopilot amplifier, for use in an apparatus for checking an aircraft autopilot amplifier as claimed in any one of claims 1-7, characterized in that: Includes the following steps: S1: Initialization phase, initialize the basic parameters of the display module, main control module, pitch module, roll module, yaw module, speed holding module and servo module; S2: Standby phase: The main control module determines whether a command has been received. If a command is received, it enters the S3 execution phase; otherwise, it returns to the S2 standby phase. S3: Execution phase. The main control module determines whether it needs to send the command to other modules. If not, it directly executes the received command. If so, it sends the command to other modules. After the other modules complete the corresponding operation, they issue a completion command and enter the S4 termination phase. S4: End phase. After setting all modules except the main control module and display module to their initial state, disconnect the power.

9. The aircraft autopilot amplifier check method of claim 8, wherein: The S2 standby phase receives commands from the display module.

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