Aircraft measurement and control device based on data transmission module

Abstract

An aircraft measurement and control device based on a data transmission module comprises a main circuit and a drive circuit. The main circuit comprises a main control module, a power supply voltage reduction module, a parameter storage module, a voltage detection module, a charging control module, a circuit state indication module and a level conversion module; the power supply voltage reduction module is used for respectively providing required power supply voltage for each module; the voltage detection module comprises a 24V voltage detection module and a 7.2 V voltage detection module; the charging control module is used for controlling on and off of an energy storage capacitor power supply in the driving circuit; and the driving circuit is used for receiving a signal from the main control module, and the energy storage capacitor outputs a driving voltage to the outside. The aircraft measurement and control device not only meets the requirement that the drive circuit and the main circuit use different power supplies, but also adds a power supply detection module, a parameter storage module, a circuit state indication module and the like, improves the drive circuit, and ensures the safety and reliability of the whole device.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, especially an aircraft measurement and control device based on data transmission module. BACKGROUND

[0002] With the rapid development of aviation technology and unmanned aerial vehicle technology, aircraft measurement and control devices are increasingly widely used in military, civilian and scientific research fields. Aircraft measurement and control devices are responsible for receiving signals from other devices (usually ground control stations or command centers) and executing corresponding instructions based on these signals. Measurement and control devices based on data transmission modules are the core components of aircraft state monitoring, instruction transmission and task execution, and their power supply stability, functional integrity, drive reliability and main control adaptability directly affect the success rate of aircraft task execution and equipment safety. However, current similar measurement and control devices on the market still have many technical shortcomings in actual application, making it difficult to meet the high-precision and high-reliability requirements under complex working conditions. The specific defects are as follows:

[0003] (1) The power supply adaptation capability is insufficient, and it is difficult to meet the power supply needs of multiple circuits. The power supply system design of existing measurement and control devices is relatively simple, and most of them can only provide a single specification output voltage, making it difficult to meet the use requirements of different voltages for drive circuits and main circuits. Some devices attempt to be compatible with two voltages, but do not use a reasonable voltage conversion structure, resulting in poor voltage output stability. When the load current fluctuates or the input voltage changes, power supply instability problems are likely to occur, affecting the action accuracy of the drive circuit and the signal processing accuracy of the main circuit, and even causing equipment failure.

[0004] (2) The function module is missing, and the monitoring and maintenance capability is insufficient. Existing devices generally only have basic data transmission and control core functions, lacking necessary auxiliary modules: on the one hand, there is no dedicated power supply detection module, which cannot monitor the power supply working state in real time. When the power supply has voltage abnormalities, power supply interruption precursors and other problems, it cannot provide timely warning, which may lead to sudden interruption of measurement and control tasks; on the other hand, there is no parameter storage module, which cannot store key configuration information and historical data during device operation. When the device fails later, it is difficult to trace the cause of the failure, increasing the difficulty of troubleshooting; at the same time, there is no circuit state indication module, and maintenance personnel cannot directly judge the working state of each circuit unit, and need to use professional instruments for detection, which prolongs the maintenance time and affects the efficiency of device reuse.

[0005] (3) The drive circuit design has defects and is not reliable. The drive circuit of existing devices mostly uses traditional single loop structure. When multiple tasks need to be executed at the same time (such as simultaneously releasing two items), it is difficult to ensure the action reliability.

[0006] (4) the start mode design is unreasonable. The start mode of the existing device is single, and is mostly dependent on external command triggering. If the external signal transmission is interrupted or the command cannot be received, the device cannot start, resulting in task stagnation and greatly reducing the task execution success rate.

[0007] Therefore, there is an urgent need for a spacecraft measurement and control device based on a data transmission module that can solve the above-mentioned defects of the prior art and has excellent performance in power supply, functional modules, drive circuits, and master control start, in order to improve the reliability and task execution efficiency of spacecraft measurement and control. SUMMARY

[0008] In order to overcome the above-mentioned shortcomings of the existing spacecraft measurement and control, the utility model provides a kind of spacecraft measurement and control device based on data transmission module, the spacecraft measurement and control device not only satisfies the drive circuit and main circuit use different power supply, still increase power detection, parameter storage, circuit state indication etc.

[0009] The technical scheme for solving the above-mentioned problems is: a spacecraft measurement and control device based on a data transmission module, comprising a main circuit and a drive circuit; the main circuit comprises a master control module, a power supply step-down module, a parameter storage module, a voltage detection module, a charging control module, a circuit state indication module and a level conversion module;

[0010] The power supply step-down module is connected with the master control module, the drive circuit, the voltage detection module, the parameter storage module and the level conversion module, respectively, to provide the required power supply voltage for each module;

[0011] The parameter storage module is connected with the master control module and is used to store signals received by the device from other devices;

[0012] The voltage detection module comprises a 24V voltage detection module and a 7.2V voltage detection module; the 24V voltage detection module is connected with the power supply step-down module and the master control module, respectively, to detect whether the input voltage of the device is 24V; the 7.2V voltage detection module is connected with the master control module and the drive circuit, respectively, to detect the voltage of the energy storage capacitor in the drive circuit;

[0013] The charging control module is connected with the master control module, the 7.2V voltage detection module and the drive circuit, respectively, to control the start and stop of the energy storage capacitor power supply in the drive circuit;

[0014] The drive circuit is connected with the master control module, the charging control module and the 7.2V voltage detection module, respectively, to receive signals from the master control module and output drive voltage to the outside through the energy storage capacitor;

[0015] The circuit state indication module is connected with the master module, and is used for displaying the state of the device;

[0016] The level conversion module is connected with the master module, and is used for communication between the device and other devices;

[0017] The master module is used for receiving signals from other devices, and executing corresponding instructions according to the signals.

[0018] Further technical solutions of the application are as follows: the power step-down module comprises a power step-down circuit, the power step-down circuit comprises a first step-down chip U3 and a second step-down chip U4 connected in sequence, the first step-down chip U3 is connected with a 24V voltage input end J3, the 24V voltage input end J3 is connected with a grounding overvoltage diode D2, an input filter capacitor C8, an input filter capacitor C10 and a 24V voltage output end J4, and the 24V voltage input end J3 is further connected in series with an anti-reverse diode D1 and a self-recovery fuse F1; a plurality of output filter capacitors are arranged between the first step-down chip U3 and the second step-down chip U4, and the output end of the second step-down chip U4 is connected with a plurality of output filter capacitors.

[0019] Further technical solutions of the application are as follows: the parameter storage module comprises a parameter storage circuit, the parameter storage circuit comprises a parameter storage chip, and the parameter storage chip is an AT24C04.

[0020] Further technical solutions of the application are as follows: the voltage detection module comprises a 24V voltage detection circuit and a 7.2V voltage detection circuit.

[0021] The 24V voltage detection circuit is composed of a voltage dividing resistor R15, a voltage dividing resistor R16 and a filter capacitor C22; one end of the voltage dividing resistor R15 is connected with a 24V power supply, the other end of the voltage dividing resistor R15 is connected with the master module, one end of the filter capacitor C22 and one end of the voltage dividing resistor R16 respectively, and the other end of the filter capacitor C22 is connected with the other end of the voltage dividing resistor R16 and then grounded.

[0022] The 7.2V voltage detection circuit comprises a voltage detection chip U5, a filter capacitor C21, voltage dividing resistors R3, R11, R12, R14, a pull-up resistor R13 and an optocoupler OP2; the optocoupler OP2 comprises an optocoupler primary and an optocoupler secondary; the optocoupler primary is a light emitter, and the optocoupler secondary is a light receiver; the filter capacitor C21 and the voltage dividing resistor R3 are connected in parallel, one end of which is connected to the GND end of the voltage detection chip U5, and the other end is connected to the VCC end of the voltage detection chip U5; the voltage dividing resistor R11 and the voltage dividing resistor R12 are connected in series and then connected to the `MR end of the voltage detection chip U5; the 7.2V voltage is connected between the voltage dividing resistor R11 and the voltage dividing resistor R12; one end of the voltage dividing resistor R14 is connected to the optocoupler primary input end of the optocoupler OP2 and the `MR end of the voltage detection chip U5, respectively, and the other end is connected to the optocoupler primary output end of the optocoupler OP2 and grounded; the optocoupler secondary input end of the optocoupler OP2 is connected to the main control module; the optocoupler secondary output end of the optocoupler OP2 is grounded; the pull-up resistor R13 is arranged between the optocoupler secondary input end of the optocoupler OP2 and the main control module, and the pull-up resistor R13 is connected to a 3.3V voltage.

[0023] Further technical solutions are as follows: the charging control module comprises a charging control circuit, the charging control circuit comprises resistors R4, R5, R8, a pull-up resistor R6, an optocoupler OP3, a switch MOS tube T1 and an anti-reverse connection MOS tube T2; the optocoupler OP3 comprises an optocoupler primary and an optocoupler secondary, the optocoupler primary is a light emitter, and the optocoupler secondary is a light receiver; the optocoupler primary input end of the optocoupler OP3 is connected to the main control module in series with the resistor R4; the output end of the optocoupler primary of the optocoupler OP3 is grounded; the optocoupler secondary output end of the optocoupler OP3 is connected to the gate of the switch MOS tube T1 through the resistor R5, the gate of the MOS tube T1 is connected to the source of the switch MOS tube T1 and the source of the anti-reverse connection MOS tube T2 through the resistor R8; the drain of the MOS tube T1 is grounded; the optocoupler secondary input end of the optocoupler OP3 is connected to the gate of the anti-reverse connection MOS tube T2 through the pull-up resistor R6; the source of the MOS tube T1 and the source of the anti-reverse connection MOS tube T2 are grounded; the optocoupler secondary input end of the optocoupler OP3 is connected to a 7.2V voltage; the optocoupler secondary input end of the optocoupler OP3 and the drain of the anti-reverse connection MOS tube T2 are connected to the energy storage capacitor power switch circuit interface J1 in the driving circuit.

[0024] Further technical solutions are as follows: the main control chip of the main control module is STM32F103C8T6; the main control chip STM32F103C8T6 adopts an ARM Cortex-M3 core.

[0025] Its further technical scheme is that the driving circuit adopts double-pole double-throw relays in parallel winding low-voltage series super-high energy storage capacitors, the capacity is 0.3F / 7.5V, the direct current internal resistance is 200mΩ, and the alternating current internal resistance is 600mΩ.

[0026] Its further technical scheme is that the circuit state indication module comprises three indicator lamps, indicator lamp 1 is blue, indicator lamp 2 is green, and indicator lamp 3 is red; indicator lamp 1 and indicator lamp 2 display the energy storage capacitor voltage condition in the driving circuit; and indicator lamp 3 displays the main circuit input voltage condition.

[0027] Its further technical scheme is that the level conversion module adopts an RS232 communication protocol.

[0028] Its further technical scheme is that the main circuit adopts a 24v output power supply, and the driving circuit adopts a 7.2V output power supply.

[0029] Compared with the prior art, the aircraft measurement and control device based on the data transmission module has the following beneficial effects due to the adoption of the above technical scheme.

[0030] 1、The first-stage voltage reduction chip U3 of the power supply voltage reduction module of the utility model converts 24V voltage into 5V voltage, the second-stage voltage reduction chip U4 converts 5V voltage into 3.3V voltage available for the control chip, and the requirement of using different power supply voltages by the driving circuit and the main circuit is met;By the segmented voltage reduction, not only the high voltage can be efficiently converted into the required lower voltage, but also the stability of the output voltage can be maintained under the condition of load current and input voltage fluctuation. Through the multiple grounding capacitors and the electrolytic capacitor, the filtering effect is guaranteed;Meanwhile, the anti-reverse connection diode D1 and the self-recovery fuse F1 are arranged, the anti-reverse connection diode D1 can protect the power supply from being burnt out under the condition of power supply reverse connection, and the self-recovery fuse F1 can restart and recover the circuit under the condition of abnormal overload and overcurrent of the circuit, so that the performance and reliability of the device are improved.

[0031] 2、The power supply detection module added in the utility model can monitor the power supply state, ensure the stability of power supply, and timely alarm when an exception occurs. The parameter storage module: saves important configuration information and historical data, which is convenient for subsequent analysis and troubleshooting. The charging control module: manages the energy storage capacitor charging process to prevent overcharging and ensure the safety of the circuit. The circuit state indication module: directly displays the working state of each part through indicator lamps (LED lamps) or other ways, which is convenient for maintenance personnel to quickly judge the system condition.

[0032] 3. The utility model discloses an optimization design to drive circuit, adopt double-pole double-throw relay parallel winding low voltage series superhigh energy storage capacitor, capacity 0.3F / 7.5V, direct current resistance 200m omega, alternating current resistance 600m omega. In order to guarantee the reliability of energy storage capacitor to realize the simultaneous investment of two materials, the current limiting resistance of 8.2 omega is connected in series in each ignition loop. The drive circuit also adopts independent power supply mode, improves its efficiency and stability, reduces the system failure risk caused by the drive problem.

[0033] 4. The utility model discloses using STM32F103C8T6 as main control chip, this chip is famous with its high performance, low power consumption and rich peripheral interface, is very suitable for being used in embedded control system. The starting program is stored in the main control chip, and the automatic and artificial two starting modes are combined, can guarantee that the device normally operates even in the case of unable to receive external command, improves the success rate of task execution.

[0034] The technical features of the aircraft measurement and control device based on the data transmission module will be further described below in combination with the drawings and examples. DESCRIPTION OF DRAWINGS

[0035] Figure 1 It is the overall block diagram of the aircraft measurement and control device based on the data transmission module of the utility model;

[0036] Figure 2 It is the main control module circuit schematic diagram (main control chip circuit schematic diagram) of the example;

[0037] Figure 3 It is the power supply step-down circuit schematic diagram of the example;

[0038] Figure 4 It is the parameter storage circuit schematic diagram of the example;

[0039] Figure 5 It is the 24V voltage detection circuit schematic diagram of the example;

[0040] Figure 6 It is the 7.2V voltage detection circuit schematic diagram of the example;

[0041] Figure 7 It is the charging control circuit schematic diagram of the example;

[0042] Figure 8 It is the circuit state indication circuit schematic diagram of the example;

[0043] Figure 9 It is the level conversion circuit schematic diagram of the example;

[0044] Figure 10 It is the drive circuit circuit schematic diagram of the example;

[0045] Figure 11 This is a schematic diagram of the connection system of this device. Detailed Implementation

[0046] like Figure 1 As shown: An aircraft telemetry and control device based on a data transmission module includes a main circuit and a drive circuit; the main circuit includes a main control module, a power supply step-down module, a parameter storage module, a voltage detection module, a charging control module, a circuit status indication module, and a level conversion module.

[0047] The main control module is used to receive signals from other devices and execute corresponding instructions based on these signals.

[0048] The power step-down module is connected to the main control module, drive circuit, voltage detection module, parameter storage module, and level conversion module, respectively, and provides the required power voltage to each module.

[0049] The parameter storage module is connected to the main control module and is used to store signals received from other devices.

[0050] The voltage detection module includes a 24V voltage detection module and a 7.2V voltage detection module; the 24V voltage detection module is connected to the power supply step-down module and the main control module respectively, and is used to detect whether the input voltage of the device is 24V; the 7.2V voltage detection module is connected to the main control module and the drive circuit respectively, and is used to detect the voltage of the energy storage capacitor in the drive circuit.

[0051] The charging control module is connected to the main control module, the 7.2V voltage detection module and the drive circuit respectively, and is used to control the start and stop of the energy storage capacitor power supply in the drive circuit.

[0052] The drive circuit is connected to the main control module, the charging control module and the 7.2V voltage detection module respectively, and is used to receive signals from the main control module and output drive voltage to the external energy storage capacitor.

[0053] The circuit status indicator module is connected to the main control module and is used to display the status of the device.

[0054] The level conversion module is connected to the main control module and is used for communication between this device and other devices. The level conversion module requires a 24V power supply and a 3.3V power supply from the main control module.

[0055] The master control chip of the master control module in the embodiment is replaced by STM32F103C8T6 instead of the existing AT89C2051; the master control chip STM32F103C8T6 adopts an ARM Cortex-M3 core, has a high frequency of 72MHz, provides strong processing capacity and operation performance, can process complex real-time tasks, and realizes efficient embedded application. Meanwhile, a variety of peripherals are integrated, which can meet various application requirements. The performance and peripheral functions of AT89C2051 are relatively limited and do not meet the requirements of the device. The master control chip is connected with a power step-down module, a parameter storage module, a voltage detection module, a charging control module, a circuit state indication module, a level conversion module and a driving circuit respectively.

[0056] As shown in Figure 2 The master control module circuit mainly consists of an STM32F103C8T6 single-chip microcomputer U1, a crystal oscillator X1, load capacitors C1 and C2 of the crystal oscillator, a filter capacitor C3, resistors R1, R9 and R10, and a socket J6. The STM32F103C8T6 single-chip microcomputer can quickly process complex control tasks. The clock circuit provides a system clock for the single-chip microcomputer, and provides power for the operation of various modules in the chip. The specific circuit connection is as follows:

[0057] The pin 5 (PD0-OSC-IN end) of the chip STM32F103C8T6 is connected with one end of the crystal X1, the other end of the crystal X1 is connected with the pin 6 (PD1-OSC-OUT end) of the chip STM32F103C8T6, and the ground end of the crystal X1 is grounded; the pin 5 (PD0-OSC-IN end) of the chip STM32F103C8T6 is connected with one end of the load capacitor C1 of the crystal, and the other end of the load capacitor C1 of the crystal is grounded; the pin 6 (PD1-OSC-OUT end) of the chip STM32F103C8T6 is connected with one end of the load capacitor C2 of the crystal, and the other end of the load capacitor C2 of the crystal is grounded. The pin 7 (NRST end) of the chip STM32F103C8T6 is connected with one end of the filter capacitor C3, the other end of the filter capacitor C3 is connected with the pin 8 (VSSA end) of the chip STM32F103C8T6, and the pin 8 (VSSA end) of the chip STM32F103C8T6 is grounded; the pin 44 (BOOT0 end) of the chip STM32F103C8T6 is connected with one end of the resistor R1, and the other end of the resistor R1 is grounded; the pin 37 (PA14 end) of the chip STM32F103C8T6 is connected with one end of the resistor R9, and the other end of the resistor R9 is connected with the pin 1 of the socket J6; the pin 2 of the socket J6 is connected with one end of the resistor R10, and the other end of the resistor R10 is connected with the pin 34 (PA13 end) of the chip STM32F103C8T6; the pins 23, 35 and 47 (VSS_1, VSS_2 and VSS_3 ends) of the chip STM32F103C8T6 are all grounded; the pins 1, 9, 24, 36 and 48 (VBAT, VDD_1, VDD_2, VDD_3 ends) of the chip STM32F103C8T6 are all connected with 3.3V voltage; the pins 4, 5 and 6 of the socket J6 are all grounded; and the pin 3 of the socket J6 is connected with 3.3V voltage.

[0058] The power supply step-down scheme adopted in the embodiment is as follows: because the input voltage of the power supply is 24V, and the voltage required by the single-chip microcomputer is 3.3V, a power supply step-down circuit is needed to reduce the input voltage of 24V to 3.3V. The power supply step-down circuit can efficiently convert high voltage into the required lower voltage, while ensuring the stability of the output voltage under the conditions of load current and input voltage fluctuation.

[0059] The power supply step-down module includes a power supply step-down circuit, such as Figure 3As shown, the power supply step-down circuit includes a first step-down chip U3 and a second step-down chip U4 connected in sequence, the first step-down chip U3 is connected with a 24V voltage input end J3, the 24V voltage input end J3 is connected with a ground overvoltage diode D2, an input filter capacitor C8, an input filter capacitor C10 and a 24V voltage output end J4, the 24V voltage input end J3 and the first step-down chip U3 are also connected in series with an anti-reverse diode D1 and a self-restoring fuse F1; a plurality of output filter capacitors are arranged between the first step-down chip U3 and the second step-down chip U4, and the output end of the second step-down chip U4 is connected with a plurality of output filter capacitors.

[0060] The power supply step-down circuit of the embodiment includes a 24V input end J3, a 24V output end J4, a first step-down chip U3 and a second step-down chip U4; the first step-down chip U3 adopts a WRB2412S-3WR2 chip, and the second step-down chip U4 adopts an AMS1117 chip. The specific circuit connection is as follows:

[0061] One end of the 24V input end J3 is connected with the anode of the anti-reverse diode D1, the cathode of the anti-reverse diode D1 is connected with one end of the self-restoring fuse F1, the other end of the self-restoring fuse F1 is connected with the cathode of the overvoltage diode D2, one end of the input filter capacitor C8 (C8 is an electrolytic capacitor), one end of the input filter capacitor C10, and the Vin end of the first step-down chip U3; the other end of the 24V input end J3 is connected with the anode of the overvoltage diode D2, the other end of the input filter capacitor C8, the other end of the input filter capacitor C10, and the GND end of the first step-down chip U3; the GND end of the first step-down chip U3 is grounded; one end of the 24V output end J4 is connected with the Vin end of the first step-down chip U3, and the other end is grounded; the +V0 end of the first step-down chip U3 is connected with the input end Vi of the second step-down chip U4 and one end of a first capacitor group, the first capacitor group includes output filter capacitors C9, C11, C12 connected in parallel (C9 is an electrolytic capacitor); the other end of the first capacitor group is connected with the OV port of the first step-down chip U3 and the GND port of the second step-down chip U4; the GND port of the second step-down chip U4 is grounded; the output end Vo of the second step-down chip U4 is connected with one end of a second capacitor group; the second capacitor group includes output filter capacitors C13, C14, C15, C16, C17, C18, C19 and C20 connected in parallel; the other end of the second capacitor group is connected with the GND port of the second step-down chip U4; the first step-down chip U3 outputs a 5V voltage, and the second step-down chip U4 outputs a 3.3V voltage.

[0062] To store signals received from other devices, this embodiment uses the AT24C04 memory chip based on the I2C bus, a two-wire serial communication protocol that allows the microcontroller to communicate easily bidirectionally with other peripheral devices (such as the STM32F103C8T6). Function: Stores signals received from the serial port via I2C communication. Its simple read / write operations and reliable data retention make it an ideal non-volatile memory solution for many applications.

[0063] like Figure 4 As shown, the parameter storage module includes a parameter storage circuit, which mainly consists of a parameter storage chip U6 (AT24C04C) and pull-up resistors R17 and R18. Pins 1, 2, 3, and 4 (A0, A1, A2, and GND terminals) of the parameter storage chip U6 are all grounded. Pins 5 and 6 (SDA and SCL terminals) of the parameter storage chip U6 are connected to pull-up resistors R18 and R17 respectively and then connected to a 3.3V voltage. Pin 5 (SDA terminal) of the parameter storage chip U6 is connected to pin 14 (PB14 terminal) of the STM32F103C8T6 chip in the main control module between the pull-up resistor R18 and pin 6 (SCL terminal) of the parameter storage chip U6 is connected to pin 13 (PB13 terminal) of the STM32F103C8T6 chip in the main control module between the pull-up resistor R17 and pin 6 (SCL terminal) of the parameter storage chip U6.

[0064] Power Supply Scheme for the Drive Circuit: The energy storage capacitor of the drive circuit is powered by a 7.2V / 1A power supply, ensuring that the charging voltage of the energy storage capacitor is below the rated voltage, and simultaneously ensuring that the drive circuit is not interfered with during the instant the entire device is powered on. In previous circuit designs, the main circuit and drive circuit used the same power supply. However, during testing, it was found that when the entire device was powered on, the main chip of the main circuit was easily interfered with, automatically sending commands to the drive circuit, potentially leading to personal injury. In later research and design, we found that as long as the main circuit and drive circuit are powered by different power supplies, the drive circuit remains unaffected even if the main circuit is interfered with and sends commands. Therefore, the drive circuit uses a separate power supply for charging, ensuring the safety of the entire device at the instant of power-on.

[0065] The voltage detection module includes a 24V voltage detection circuit and a 7.2V voltage detection circuit.

[0066] For the circuit to function properly, a 24V voltage detection circuit needs to be added. This circuit is used to detect whether the input voltage is 24V, ensuring that the input voltage of the main chip is less than 3.3V.

[0067] like Figure 5As shown, the 24V voltage detection circuit consists of voltage divider resistors R15 and R16 and filter capacitor C22. One end of the voltage divider resistor R15 is connected to the 24V power supply, and the other end is connected to the main control module, one end of the filter capacitor C22 and one end of the voltage divider resistor R16, and the other end of the filter capacitor C22 is connected to the other end of the voltage divider resistor R16 and then grounded.

[0068] Because the rated voltage of the energy storage capacitor is 7.2V, exceeding 7.2V can be dangerous, so a 7.2V voltage detection circuit is required. This 7.2V voltage detection circuit is an isolated voltage detection system used to detect whether the energy storage capacitor in the drive circuit is fully charged. A 3.3V voltage from this 7.2V voltage detection circuit needs to be provided by the power supply step-down module.

[0069] like Figure 6 As shown, the 7.2V voltage detection circuit includes a voltage detection chip U5, a filter capacitor C21, voltage divider resistors R3, R11, R12, R14, a pull-up resistor R13, and an optocoupler OP2. The optocoupler OP2 includes a primary and a secondary winding; the primary winding is a light emitter, and the secondary winding is a light receiver. The filter capacitor C21 and the voltage divider resistor R3 are connected in parallel, with one end connected to the GND terminal of the voltage detection chip U5 and the other end connected to the VCC terminal of the voltage detection chip U5. The voltage divider resistors R11 and R12 are connected in series to the MR terminal of the voltage detection chip U5. A 7.2V voltage is connected between resistor R11 and voltage divider resistor R12; one end of voltage divider resistor R14 is connected to the primary input terminal of optocoupler OP2 and the `MR terminal of voltage detection chip U5, and the other end of voltage divider resistor R14 is connected to the primary output terminal of optocoupler OP2 and grounded; the secondary input terminal of optocoupler OP2 is connected to the main control module (i.e., pin 12 of chip STM32F103C8T6); the secondary output terminal of optocoupler OP2 is grounded; a pull-up resistor R13 is provided between the secondary input terminal of optocoupler OP2 and the main control module, and the pull-up resistor R13 is connected to a 3.3V voltage.

[0070] The charging control module includes a charging control circuit. When the 7.2V power supply detection module detects that the energy storage capacitor in the drive circuit is fully charged, it sends a signal to the STM32F103C8T6 chip. Upon receiving the 7.2V power supply detection signal, the STM32 sends a command to the charging control module, which immediately disconnects the power supply across the energy storage capacitor in the drive circuit to prevent overcharging and potential danger. Function: The charging control module controls the start and stop of the power supply to the energy storage capacitor in the drive circuit.

[0071] like Figure 7As shown, the charging control circuit includes resistors R4, R5, R8, pull-up resistor R6, optocoupler OP3, switching MOSFET T1, and reverse connection protection MOSFET T2; the optocoupler OP3 includes an optocoupler primary and an optocoupler secondary, the optocoupler primary being a light emitter and the optocoupler secondary being a light receiver; when the charging signal is valid, optocoupler OP3 is turned on, switching MOSFET T1 is turned on, and the energy storage capacitor is charged.

[0072] The primary input terminal of optocoupler OP3 is connected to the main control module (i.e., pin 15 of chip STM32F103C8T6) after being connected in series with resistor R4; the output terminal of the primary input terminal of optocoupler OP3 is grounded; the secondary output terminal of optocoupler OP3 is connected to the gate of switching MOSFET T1 through resistor R5; the gate of MOSFET T1 is connected to the source of switching MOSFET T1 and the source of reverse-connected MOSFET T2 through resistor R8; the drain of MOSFET T1 is grounded; the secondary input terminal of optocoupler OP3 is connected to the gate of reverse-connected MOSFET T2 through pull-up resistor R6; the source of MOSFET T1 and the source of reverse-connected MOSFET T2 are grounded; the secondary input terminal of optocoupler OP3 is connected to a 7.2V voltage; the secondary input terminal of optocoupler OP3 and the drain of reverse-connected MOSFET T2 are connected to the energy storage capacitor power switch circuit interface J1 in the drive circuit.

[0073] The circuit status indicator module includes three indicator lights to display the status of the entire device. Indicator light 1 is blue, indicator light 2 is green, and indicator light 3 is red; indicator lights 1 and 2 display the voltage of the energy storage capacitor in the drive circuit; indicator light 3 displays the input voltage of the main circuit.

[0074] like Figure 8 As shown, the three indicator LEDs are connected to pins 20, 19, and 18 of the main control chip STM32F103C8T6 through current-limiting resistors R19, R21, and R20, respectively.

[0075] This device uses the RS232 communication protocol. To enable communication with other devices, a level conversion circuit needs to be designed. Function: To convert the microcontroller's TTL level to RS232 level, enabling bidirectional communication.

[0076] like Figure 9 As shown, the level conversion module includes an integrated circuit chip MAX3232ESE, a filter capacitor C4, boost capacitors C5, C6, and C7, current-limiting resistors R2 and R7, and a socket J2.

[0077] Pin 1 of the integrated circuit chip MAX3232ESE is connected to pin 3 via boost capacitor C5, and pin 2 is connected to pin 16 via filter capacitor C4. Pin 16 is connected to a 3.3V voltage. Pin 4 of the integrated circuit chip MAX3232ESE is connected to pin 5 via boost capacitor C7, and pin 6 is connected to pin 15 via boost capacitor C6. Pin 15 is grounded. Pin 4 of the socket J2 is connected to pin 7 of the integrated circuit chip MAX3232ESE via current-limiting resistor R7, and pin 3 is connected to pin 8 of the integrated circuit chip MAX3232ESE via current-limiting resistor R2. Pin 2 is connected to a 24V voltage, and pin 1 is grounded. Pin 10 of the integrated circuit chip MAX3232ESE is connected to pin 31 of the main control chip STM32F103C8T6, and pin 9 is connected to pin 30 of the main control chip STM32F103C8T6.

[0078] Drive circuit optimization scheme: The original drive circuit is improved by using a double-pole double-throw relay connected in parallel with a low-voltage series ultra-high energy storage capacitor. The capacitor has a capacitance of 0.3F / 7.5V, a DC internal resistance of 200mΩ, and an AC internal resistance of 600mΩ. To ensure the reliability of simultaneously releasing two items using the energy storage capacitor, an 8.2Ω current-limiting resistor is connected in series in each ignition circuit. The drive circuit also uses an independent power supply. The discharge time is calculated according to Formula 1, and the discharge current is calculated according to Formulas 2 and 3.

[0079] Th=0.75RC...... 1

[0080] τ=RC........... 2

[0081]

[0082] In the formula:

[0083] Th -- Capacitor discharge time, unit: s

[0084] t -- Discharge duration, in seconds

[0085] R -- Discharge circuit resistance, unit: Ω

[0086] C -- Capacitance value, unit: F

[0087] I -- Capacitor discharge current, unit: A.

[0088] The drive circuit receives signals from the microcontroller (i.e., the main control chip STM32F103C8T6) to control the conduction and cutoff of the transistor, and the energy storage capacitor enables the output drive voltage. For example... Figure 10 As shown.

[0089] Function: Outputs drive voltage to external systems.

[0090] Components: K_#G6S is a relay, C2_# is an energy storage capacitor, R4_# is a charging current-limiting resistor, R5_# is a discharging current-limiting resistor, D_# is a breakdown protection diode, Q_# is a transistor controlling the relay state, R3_# and R2_# are voltage divider resistors, and C1_# is a filter capacitor. The value of # is any integer from 1 to 8. See the diagram for component connections. Figure 10 .

[0091] Connection scheme between this device and the system:

[0092] The aircraft telemetry and control device consists of a main circuit and a drive circuit. The main circuit is connected to the aircraft system via a serial port, and the drive circuit is connected to the load. The aircraft system receives commands from the operator and then transmits them to the main circuit. The main circuit controls the operation of the drive circuit. (See [link to documentation]). Figure 11 .

[0093] This device incorporates new modules for power detection, parameter storage, and circuit status indication. These improvements not only enhance the functionality of the aircraft telemetry and control system but also improve its adaptability to complex environments. Hardware optimizations provide a foundation for software-level optimizations. For example, the device employs CRC checksums, which effectively prevent frame positioning errors and significantly improve the reliability and accuracy of data transmission, especially crucial in noisy wireless communication environments. This device aims to build a more robust and easily managed and maintained system. Such a system can better serve various aircraft testing and control needs, providing reliable performance support in both experimental and practical operations.

[0094] All parts not covered in this utility model are the same as or can be implemented using existing technology. The above description is a further detailed explanation of this utility model in conjunction with specific preferred embodiments. It should not be construed that the specific implementation of this utility model is limited to the descriptions of the above embodiments. For those skilled in the art, several simple deductions or substitutions can be made without departing from the concept of this utility model, and all such deductions or substitutions should be considered as falling within the patent protection scope defined by the submitted claims.

Claims

1. An aircraft telemetry and control device based on a data transmission module, characterized in that: The main circuit comprises a main control module, a power supply step-down module, a parameter storage module, a voltage detection module, a charging control module, a circuit state indication module and a level conversion module. The power supply step-down module is connected with the main control module, the driving circuit, the voltage detection module, the parameter storage module and the level conversion module respectively, and provides required power supply voltage for each module. The parameter storage module is connected with the main control module, and is used for storing signals received from other devices. The voltage detection module comprises a 24V voltage detection module and a 7.2V voltage detection module. The 24V voltage detection module is connected with the power supply step-down module and the main control module respectively, and is used for detecting whether the input voltage of the device is 24V. The 7.2V voltage detection module is connected with the main control module and the driving circuit respectively, and is used for detecting the voltage of the energy storage capacitor in the driving circuit. The charging control module is connected with the main control module, the 7.2V voltage detection module and the driving circuit respectively, and is used for controlling the start and stop of the power supply of the energy storage capacitor in the driving circuit. The driving circuit is connected with the main control module, the charging control module and the 7.2V voltage detection module respectively, and is used for receiving signals from the main control module and outputting driving voltage to the outside by the energy storage capacitor. The circuit state indication module is connected with the main control module, and is used for displaying the state of the device.

2. The aircraft TT&C device based on the data transmission module according to claim 1, characterized in that: The level conversion module is connected with the main control module, and is used for communication between the device and other devices.

3. The aircraft TT&C device based on the data transmission module according to claim 1, characterized in that: The main control module is used for receiving signals from other devices, and executing corresponding instructions according to the signals.

4. The aircraft TT&C device based on the data transmission module according to claim 1, characterized in that: The power supply step-down module comprises a power supply step-down circuit, the power supply step-down circuit comprises a first step-down chip U3 and a second step-down chip U4 connected in sequence, the first step-down chip U3 is connected with a 24V voltage input end J3, the 24V voltage input end J3 is connected with a ground overvoltage diode D2, an input filter capacitor C8, an input filter capacitor C10 and a 24V voltage output end J4 in sequence, and the 24V voltage input end J3 is further connected with an anti-reverse diode D1 and a self-recovery fuse F1 in series; a plurality of output filter capacitors are arranged between the first step-down chip U3 and the second step-down chip U4, and the output end of the second step-down chip U4 is connected with a plurality of output filter capacitors. The parameter storage module comprises a parameter storage circuit, the parameter storage circuit comprises a parameter storage chip, and the model of the parameter storage chip is AT24C04. The voltage detection module comprises a 24V voltage detection circuit and a 7.2V voltage detection circuit. The 24V voltage detection circuit is composed of a voltage dividing resistor R15, a voltage dividing resistor R16 and a filter capacitor C22; one end of the voltage dividing resistor R15 is connected with a 24V power supply, the other end of the voltage dividing resistor R15 is connected with the main control module, one end of the filter capacitor C22 and one end of the voltage dividing resistor R16 respectively, and the other end of the filter capacitor C22 is connected with the other end of the voltage dividing resistor R16 and then grounded. The 7.2V voltage detection circuit comprises a voltage detection chip U5, a filter capacitor C21, voltage dividing resistors R3, R11, R12, R14, a pull-up resistor R13 and a photocoupler OP2; the photocoupler OP2 comprises a photocoupler primary and a photocoupler secondary; the photocoupler primary is a light emitter, and the photocoupler secondary is a light receiver; the filter capacitor C21 and the voltage dividing resistor R3 are connected in parallel, one end of which is connected to the GND end of the voltage detection chip U5, and the other end is connected to the VCC end of the voltage detection chip U5; the voltage dividing resistor R11 and the voltage dividing resistor R12 are connected in series and then connected to the `MR end of the voltage detection chip U5; the 7.2V voltage is connected between the voltage dividing resistor R11 and the voltage dividing resistor R12; one end of the voltage dividing resistor R14 is connected to the photocoupler primary input end of the photocoupler OP2 and the `MR end of the voltage detection chip U5, respectively, and the other end is connected to the photocoupler primary output end of the photocoupler OP2 and grounded; the photocoupler secondary input end of the photocoupler OP2 is connected to the main control module; the photocoupler secondary output end of the photocoupler OP2 is grounded; the pull-up resistor R13 is arranged between the photocoupler secondary input end of the photocoupler OP2 and the main control module, and the pull-up resistor R13 is connected to a 3.3V voltage.

5. The aircraft TT&C device based on the data transmission module according to claim 1, characterized in that: The charging control module comprises a charging control circuit, and the charging control circuit comprises resistors R4, R5, R8, a pull-up resistor R6, a photocoupler OP3, a switch MOS tube T1 and an anti-reverse connection MOS tube T2; the photocoupler OP3 comprises a photocoupler primary and a photocoupler secondary, the photocoupler primary is a light emitter, and the photocoupler secondary is a light receiver; the photocoupler primary input end of the photocoupler OP3 is connected to the main control module in series with the resistor R4; the output end of the photocoupler primary of the photocoupler OP3 is grounded; the photocoupler secondary output end of the photocoupler OP3 is connected to the gate of the switch MOS tube T1 through the resistor R5, the gate of the MOS tube T1 is connected to the source of the switch MOS tube T1 and the source of the anti-reverse connection MOS tube T2 through the resistor R8; the drain of the MOS tube T1 is grounded; the photocoupler secondary input end of the photocoupler OP3 is connected to the gate of the anti-reverse connection MOS tube T2 through the pull-up resistor R6; the source of the MOS tube T1 and the source of the anti-reverse connection MOS tube T2 are grounded; the photocoupler secondary input end of the photocoupler OP3 is connected to a 7.2V voltage; the photocoupler secondary input end of the photocoupler OP3 and the drain of the anti-reverse connection MOS tube T2 are connected to the energy storage capacitor power switch circuit interface J1 in the driving circuit.

6. The aircraft TT&C device based on the data transmission module according to claim 1, characterized in that: The main control chip of the main control module is of the STM32F103C8T6 type; the main control chip STM32F103C8T6 adopts an ARMCortex-M3 core.

7. The aircraft TT&C device based on the data transmission module according to claim 1, characterized in that: The driving circuit adopts a double-pole double-throw relay in parallel with a low-voltage series super-high energy storage capacitor, with a capacity of 0.3F / 7.5V, a direct-current resistance of 200mΩ and an alternating-current resistance of 600mΩ; the driving circuit is provided with a current-limiting resistor of 8.2Ω in series in each ignition loop.

8. The aircraft TT&C device based on the data transmission module according to claim 1, characterized in that: The circuit state indication module comprises three indicator lights, indicator light 1 is blue, indicator light 2 is green, and indicator light 3 is red; indicator light 1 and indicator light 2 display the voltage condition of the energy storage capacitor in the driving circuit; and indicator light 3 displays the input voltage condition of the main circuit.

9. The aircraft TT&C device based on the data transmission module according to claim 1, characterized in that: The level conversion module adopts an RS232 communication protocol.

10. The aircraft TT&C device based on the data transmission module according to claim 7, characterized in that: The main circuit adopts a 24v output power supply, and the driving circuit adopts a 7.2V output power supply.

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