Modular integrated control system on airdrop aircraft

Abstract

The present invention discloses a modular integrated control system for an airdrop aircraft. In the system, a power circuit board, a main control circuit board, an inertial navigation / satellite navigation circuit board, a rudder control circuit board and a servo drive board are centrally installed in a supporting shell, so that the control system can be miniaturized, integrated and modularized. The sensors required for the airdrop aircraft can be integrated in the modular shell, and the overall working performance of the system is stable and reliable by reasonably matching the interaction relationship between various plates and components.

Description

Technical Field

[0001] The invention relates to a control system of an aircraft, and in particular to a modular integrated control system on an airdrop-type aircraft. Background Art

[0002] In the prior art, the guidance and control system of an airdrop aircraft is composed of a guidance system and a control system. In the existing design method, the guidance system and the control system are designed separately, and the data and signals are processed by the guidance system and the controller in turn, and finally transmitted to the actuator, and the actuator responds to the instructions it receives. When using this design method, data and signals are transmitted between various systems, which is prone to response delays and error accumulation, and the transmission of various signals is prone to interference, making the response of the aircraft less accurate. At the same time, it is necessary to embed multiple microprocessors in the guidance system and the control system respectively, which increases the production and application costs;

[0003] The existing control system involves many components, and its hardware structure is complex, the volume is large, and the space utilization rate is low. It is a pity to waste space on the aircraft.

[0004] In addition, when designing and manufacturing aircraft, it is often necessary to design a unique control system based on the specific model size, flight environment and flight status of the aircraft. This design method is time-consuming and labor-intensive, and increases the production cost of the aircraft. If a universal modular integrated control system suitable for various types of aircraft can be provided, the design and manufacture of aircraft can be based on this, which can greatly improve the design and manufacturing process of aircraft.

[0005] Due to the above reasons, the inventors have conducted in-depth research on the control systems in existing aircraft, and combined with the structural characteristics of the airdrop aircraft itself, designed a modular integrated control system for the airdrop aircraft that can solve the above problems. Summary of the invention

[0006] In order to overcome the above-mentioned problems, the inventors have conducted intensive research and designed a modular integrated control system for an airdrop aircraft. In this system, a power supply circuit board, a main control circuit board, an inertial navigation / satellite navigation circuit board, a rudder control circuit board and a servo drive board are centrally installed in a supporting shell, so that the control system can be miniaturized, integrated and modularized. The sensors required for the airdrop aircraft can be integrated in the modular shell. By reasonably matching the interaction between various panels and components, the overall working performance of the system is stable and reliable, thereby completing the present invention.

[0007] Specifically, the purpose of the present invention is to provide a modular integrated control system for an airdrop aircraft, the control system comprising a power supply circuit board 1, a main control circuit board 2, an inertial navigation / satellite navigation circuit board 3, a rudder control circuit board 4, a servo drive board 5 and a support shell 6;

[0008] Among them, the power supply circuit board 1, the main control circuit board 2, the inertial navigation / satellite navigation circuit board 3, the steering control circuit board 4 and the steering gear drive board 5 are arranged parallel to each other with a predetermined gap between them, and are all fixedly installed in the supporting shell 6.

[0009] Among them, a limit link 7 is also provided on the control system, through which the power supply circuit board 1, the main control circuit board 2, the inertial navigation / satellite navigation circuit board 3, the rudder control circuit board 4 and the servo drive board 5 are sequentially passed and fixed into an integrated structure.

[0010] Wherein, an isolated power supply module is arranged on the power supply circuit board 1, and the primary electrical ground is isolated from the secondary electrical ground by arranging the isolated power supply module.

[0011] Among them, a plurality of groups of optocouplers and MOS tubes are also arranged on the power circuit board 1, and the power-on control of the engine and the fuse is performed through the optocouplers and MOS tubes, and the thermal battery is also activated through the optocouplers and MOS tubes.

[0012] A TLP281 optocoupler chip is also provided on the power circuit board 1, through which the main control circuit board 2 can know the connection status between the aircraft and the carrier aircraft in real time.

[0013] Among them, the main control circuit board 2 adopts the STM32F429 chip;

[0014] Preferably, the main control circuit board 2 communicates with the peripheral device using RS422, and each RS422 communication uses MAXIM's MAX3490 chip as a communication level conversion chip, and converts the RS422 differential communication signal into a single-ended TTL signal.

[0015] Among them, the inertial navigation / satellite navigation circuit board 3 integrates a satellite receiving antenna, an inertial navigation module, and a satellite navigation solution module;

[0016] Receive GPS and BD signals through the satellite receiving antenna;

[0017] The position, speed and time information are obtained in real time through the satellite navigation solution module;

[0018] The inertial navigation module includes a gyroscope and a MEMS accelerometer.

[0019] The satellite receiving antenna includes an active antenna 1 and an active antenna 2, and the satellite navigation solution module includes a combiner, a down-conversion ionizer, an A / D conversion circuit and a baseband processing module;

[0020] The two RF signals from the active antenna 1 and the active antenna 2 are combined by the combiner;

[0021] The down-conversion circuit module converts the radio frequency signal into an analog intermediate frequency signal that is convenient for baseband processing;

[0022] Converting the simulator intermediate frequency signal into a digital intermediate frequency signal through the A / D conversion circuit module;

[0023] The baseband processing module is used to perform anti-narrowband interference processing, baseband positioning solution and communication with the main control circuit board 2.

[0024] The beneficial effects of the present invention include:

[0025] (1) The modular integrated control system on the airdrop aircraft provided by the present invention brings together multiple device units, reducing resource utilization and space utilization, so that it can carry a larger warhead than aircraft of the same specifications;

[0026] (2) The modular integrated control system on the airdrop aircraft provided by the present invention adopts a miniaturized, integrated and modular design method, has strong versatility, a simplified production process, a wide range of applications, and is suitable for mass production. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 A cross-sectional view showing the overall structure of a modular integrated control system on an air-drop aircraft according to a preferred embodiment of the present invention;

[0028] Figure 2 A schematic diagram showing the overall structure of a modular integrated control system on an airdrop aircraft according to a preferred embodiment of the present invention;

[0029] Figure 3 A schematic diagram showing a power supply circuit board in a modular integrated control system on an airdrop aircraft according to a preferred embodiment of the present invention;

[0030] Figure 4 A schematic diagram showing a main control circuit board in a modular integrated control system on an airdrop aircraft according to a preferred embodiment of the present invention;

[0031] Figure 5 A schematic diagram showing an inertial navigation / satellite navigation circuit board in a modular integrated control system on an airdrop aircraft according to a preferred embodiment of the present invention;

[0032] Figure 6 A schematic diagram showing a satellite guidance solution module in a modular integrated control system on an airdrop aircraft according to a preferred embodiment of the present invention;

[0033] Figure 7 A schematic diagram showing an inertial navigation module in a modular integrated control system on an airdrop aircraft according to a preferred embodiment of the present invention;

[0034] Figure 8 A schematic diagram showing a case where an optocoupler chip in a modular integrated control system on an airdrop aircraft according to a preferred embodiment of the present invention outputs a separation signal;

[0035] Fig. 9 A schematic diagram showing the output of an address signal by an optocoupler chip in a modular integrated control system on an airdrop aircraft according to a preferred embodiment of the present invention.

[0036] Description of Figure Numbers:

[0037] 1- Power circuit board

[0038] 11-Isolated power module

[0039] 12-MOS tube

[0040] 13- Optocoupler

[0041] 14- Optocoupler chip

[0042] 15-Power supply detection circuit

[0043] 16-Surge suppressor

[0044] 17-Switching diode

[0045] 2- Main control circuit board

[0046] 21-STM32F429 chip

[0047] 22-MAX3490 chip

[0048] 23-LDO power chip

[0049] 3-Inertial navigation / satellite navigation circuit board

[0050] 31-Inertial Navigation Module

[0051] 32-Satellite guide solution module

[0052] 4-Rudder control circuit board

[0053] 5-Servo drive board

[0054] 6-Support shell

[0055] 7-Limiting connecting rod

[0056] 8-Electrical connector DETAILED DESCRIPTION

[0057] The present invention will be further described in detail below through the accompanying drawings and embodiments. Through these descriptions, the characteristics and advantages of the present invention will become more clear and distinct.

[0058] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise noted.

[0059] According to the modular integrated control system on the airdrop aircraft provided by the present invention, Figure 1 and Figure 2 As shown in the figure, the control system includes a power supply circuit board 1, a main control circuit board 2, an inertial navigation / satellite navigation circuit board 3, a rudder control circuit board 4, a steering gear drive board 5 and a support shell 6; a limit connecting rod 7 is also provided on the control system, through which the power supply circuit board 1, the main control circuit board 2, the inertial navigation / satellite navigation circuit board 3, the rudder control circuit board 4 and the steering gear drive board 5 are sequentially passed, and are fixed into an integrated structure and fixed to the support shell 6 to facilitate synchronous movement and installation, while ensuring that the circuit boards will not move relative to each other.

[0060] Preferably, each circuit board is positioned and connected and fixed to the limiting connecting rod 7 by means of screws.

[0061] Nylon pads are also provided between the circuit boards to ensure the relative distance between the circuit boards and to provide buffering and insulation. Preferably, notches are provided at both ends of the support shell 6 to allow the electrical connector 8 to extend from the support shell 6.

[0062] Preferably, the thickness of the power supply circuit board 1, the main control circuit board 2, the inertial navigation / satellite navigation circuit board 3, the steering control circuit board 4 and the steering gear drive board 5 are all 2 mm, and they are arranged in parallel with each other in sequence, with a predetermined gap between each other, and are all fixedly installed in the supporting shell 6; more preferably, the distance between the power supply circuit board 1 and the main control circuit board 2 is 11 mm, the distance between the main control circuit board 2 and the inertial navigation / satellite navigation circuit board 3 is 11 mm, the distance between the inertial navigation / satellite navigation circuit board 3 and the steering control circuit board 4 is 23 mm, and the distance between the steering control circuit board 4 and the steering gear drive board 5 is 15 mm.

[0063] In the present application, by integrating the above-mentioned power supply circuit board 1, main control circuit board 2, inertial navigation / satellite navigation circuit board 3, rudder control circuit board 4, and servo drive board 5 into an integrated structure and arranging them in parallel to reduce the gaps between them, the control system can be made highly integrated and modularized, which is convenient for mass production of equipment and reduces production costs. It can also compress the spatial volume of the control system and reserve more space for the warhead.

[0064] Specifically, in the present application, by specifically setting the gap size between the above-mentioned plates in the control system, the control system saves 53% of the volume compared to traditional functional products carried in the aircraft, thereby being able to carry a larger warhead than traditional aircraft.

[0065] In addition, in this application, by reasonably matching the relative position relationship and relative distance between each circuit board in the control system and adding nylon pads, it is ensured that there is no signal interference between each other, each circuit board and the devices thereon can work normally, and the overall operation of the control system is smooth and reliable.

[0066] In a preferred embodiment, the power circuit board 1 is used to manage the power supply on the aircraft. Specifically, the power circuit board is used to control the power distribution of the carrier power supply and the thermal battery, control the activation of the thermal battery, control the power supply of the thermal battery, etc.; at the same time, ensure the smooth switching of the carrier power supply and the thermal battery power supply; the carrier is the aircraft carrying the aircraft. When the aircraft reaches the predetermined position, the aircraft is dropped. The aircraft will continue to glide along the speed and direction of the aircraft's flight due to inertia, and due to the effect of gravity, its gliding trajectory is a parabola; after the aircraft is dropped by the carrier, the power supply on the aircraft is adjusted from the original carrier supply to the thermal battery supply carried by the aircraft itself.

[0067] Preferably, the power supply circuit board 1 is connected to the power supply on the carrier and also to the thermal battery on the aircraft. After the thermal battery and the carrier power supply are merged, a 28V power supply is provided to the power supply board 1, and then the rest of the modular integrated control system is powered. The carrier power supply is turned on by default and can also be disconnected by the main control circuit board 2. The thermal battery is turned off by default and needs to be turned on by the main control circuit board 2.

[0068] Preferably, if Figure 3 As shown in the figure, the power circuit board 1 is provided with a DC / DC isolated power module 11, more preferably, a DC / DC isolated power module LCD20-24S05 of PDUKE. Under the condition of +28V power supply, the peak current of the modular integrated control system is within 5A, and the current during stable operation does not exceed 0.8A (20W), and the output voltage of the DC / DC is selected to be +5V.

[0069] In the present application, the primary power supply is isolated from the secondary power supply by setting up the isolated power supply module. The primary power refers to the power supply directly input from the outside and not processed, and the secondary power refers to the power supply that can be used by the internal modules of the missile-borne computer after filtering, isolating, converting, etc. the primary power.

[0070] The isolated power supply module provided in the present application includes components such as inductors and capacitors used in combination, so that surges, ripples, etc. occurring in any of the two power circuits will not affect the other circuit.

[0071] Preferably, the modular integrated control system is used to perform timing control of power supply to other devices on the aircraft except the modular integrated control system. The control signal is sent by the main control circuit board 2, and a MOS tube 12 is arranged on the power circuit board 1 to control the on-off of the power circuit.

[0072] The other devices include an engine, a thermal battery, and a fuse, etc., wherein a plurality of groups of optical couplers 13 and MOS tubes 12 are arranged on the power supply circuit board 1, and the power-on control of the engine and the fuse is performed through the optical couplers and MOS tubes, and the thermal battery is activated through the optical couplers and MOS tubes. That is, at least three groups of optical couplers and MOS tubes are arranged.

[0073] After receiving the thermal battery activation command sent by the main control circuit board 2, the carrier turns on the activation power supply of the thermal battery to complete the activation of the thermal battery. The battery activation current requirement is not less than 4A, not more than 15A, the standard value is 4A, and it lasts for 150ms. The optocoupler and MOS tube use Infineon's IRFR5305PBF and AVAGO's ACPL-024L optocoupler chips.

[0074] Preferably, a TLP281 optical coupler chip 14 is also provided on the power circuit board 1. Figure 3 , Figure 8 and Fig. 9 As shown in the figure, the input end of the TLP281 optocoupler chip is connected to the carrier, and the output end is connected to the main control circuit board 2. When the aircraft is normally connected to the carrier, the output end can transmit an address signal. When the aircraft is disconnected from the carrier, the output end can transmit a separation signal, so that the main control circuit board 2 can know the connection status between the aircraft and the carrier in real time.

[0075] Preferably, a power supply detection circuit 15 is also provided on the power supply circuit board 1, through which the power supply detection circuit monitors the power supply voltage and current of the system during self-test, periodic test and other detection processes; since the various parts of the system that are powered are in different power supply circuits, the power supply detection circuit is ground-isolated from the processing circuit of the main control circuit board. In the present application, the front-end power supply voltage is divided by resistors and then isolated by optical couplers and then given to the main control circuit board 2 for power-on detection of the system, etc.

[0076] Preferably, a surge suppressor 16 and a switching diode 17 are also provided on the power circuit board 1. The surge suppressor is used to suppress transient surge voltage, and the switching diode is used for reverse connection protection. Considering the volume and reliability, the SMBJ36A transient suppression diode of Littelfuse (USA) is selected, so that the power circuit board 1 has the functions of transient voltage suppression, adjustable output clamping voltage, reverse connection protection and overcurrent protection.

[0077] Preferably, the electrical connector 8 is also installed on the power circuit board 1. By respectively arranging the electrical connector 8 and the isolated power supply module 11 at three positions of the power circuit board 1, the overall weight of the power circuit board is basically balanced. Then, by selectively arranging devices such as optocouplers, surge suppressors, and MOS tubes, the center of mass of the power circuit board 1 is located at the center.

[0078] In a preferred embodiment, the main control circuit board 2 is used to implement functions such as software loading, calculation, serial port communication, timing output, switch quantity reception, etc., thereby realizing flight control.

[0079] Preferably, after the aircraft is mounted on the aircraft, the main control circuit board 2 receives and transmits identification signals, thereby identifying each other with the carrier aircraft, and completing the self-check operation of the equipment on the aircraft according to the detection information on the circuit; after the aircraft takes off with the aircraft, the target information and carrier information transmitted by the aircraft are received, the target information includes the position and speed information of the target, and the carrier information includes the position, speed and attitude information of the carrier aircraft; when the carrier aircraft is ready to drop the aircraft, the launch instruction is received, and the thermal battery carried on the aircraft is activated accordingly; after the aircraft is airdropped, the control program is started to stabilize the flight attitude of the aircraft.

[0080] Preferably, if Figure 4 As shown in the figure, the main control circuit board 2 adopts the STM32F429 chip 21 in hardware, with a maximum main frequency of 180M, supports CF card, SRAM, PSRM, NOR and NAND memory, and has built-in SPI, USART, USB, CAN, SDIO and other interface controllers; it has three modes of sleep, shutdown and standby, thereby reducing the power consumption of the chip.

[0081] The main control circuit board 2 communicates with at least five peripheral devices using RS422, and each RS422 communication uses MAXIM's MAX3490 chip 22 as a communication level conversion chip, and converts the RS422 differential communication signal into a single-ended TTL signal. The five devices include an inertial measurement device, a satellite receiving device, a steering gear control board, a guidance head, and a data recorder.

[0082] The power supply voltage of the main control circuit board 2 is +3.3V, and TI's LM1117IMPX-3.3V is used to power the main control circuit board component board; the LM1117IMPX-3.3V is an LDO power chip 23, and the system power board converts 5V power supply into 3.3V to supply the processor. The chip can provide a maximum current of 800mA, and the external configuration circuit is simple, thereby reducing the PCB board area occupied.

[0083] In a preferred embodiment, the inertial navigation / satellite navigation circuit board 3 is used to provide inertial measurement parameters and satellite navigation parameters, and has high navigation measurement accuracy. Figure 5 As shown, the inertial navigation / satellite navigation circuit board 3 integrates devices such as a satellite receiving antenna, an inertial navigation module 31, and a satellite navigation solution module 32, wherein the inertial navigation module 31 is a MEMS inertial navigation, the satellite receiving antenna can receive both GPS and BD signals, and the satellite navigation solution module collects satellite signals received by the satellite antenna, and after anti-interference processing, sends the satellite data to the main control circuit board 2.

[0084] Preferably, the satellite navigation solution module has an anti-narrowband interference function and is used to provide real-time position, speed and time information to the main control circuit board; the satellite receiving antenna simultaneously receives airborne and missile-borne signals, and receives satellite information through the airborne antenna when the aircraft is mounted on the carrier aircraft; after the aircraft is launched, positioning is performed through the satellite receiving antenna.

[0085] Preferably, the satellite receiving antenna comprises an active antenna 1 and an active antenna 2, wherein the active antenna 1 is arranged on the aircraft, i.e., the shell of the missile body, and the active antenna 2 is arranged on the carrier aircraft;

[0086] Preferably, if Figure 6 As shown in , the satellite navigation solution module includes a combiner, a down-conversion circuit module, an A / D conversion circuit module and a baseband processing module.

[0087] The two RF signals from active antenna 1 and active antenna 2 are combined by the combiner to realize the dual antenna function. Specifically, when the device is actually used, active antenna 1 is installed on the outer wall of the missile body. As a missile-borne antenna, its volume and gain are small. Active antenna 2 is installed on the carrier aircraft. The signal is connected to the missile body through the RF cable and then connected to the missile-borne computer. As an airborne antenna, its volume is large and its gain is large.

[0088] Two active antennas are provided in the present application to ensure the stability of the positioning effect of the aircraft; when the aircraft is flying on hangar, the onboard active antenna 1 is very likely to be blocked by the metal shell or metal rack of the carrier aircraft, and satellite reception and positioning cannot be completed. At this time, the connected onboard active antenna 2 is installed in a suitable position of the carrier aircraft that is not blocked, and satellite signals can be received normally, so that the onboard computer satellite receiving device can still obtain satellite signals for calculating ephemeris and positioning, avoiding the problem that the onboard active antenna 1 is blocked during the hangar process and the aircraft cannot complete positioning.

[0089] The radio frequency signal is converted into an analog intermediate frequency signal that is convenient for baseband processing by the down-conversion circuit module, and the down-conversion circuit module can be implemented by using the radio frequency chip produced by Guangzhou Runxin;

[0090] The simulator intermediate frequency signal is converted into a digital intermediate frequency signal through the A / D conversion circuit module, so as to facilitate the anti-narrowband interference processing and baseband resolution; the A / D conversion circuit is implemented by an AD chip;

[0091] The baseband processing module is used to perform anti-narrowband interference processing, baseband positioning solution and communication with the main control circuit board 2. The module is implemented using a multi-mode multi-frequency baseband chip. The multi-mode multi-frequency baseband chip uses a 32-bit high-performance ARM embedded processor, a baseband module with a built-in BDS / GPS / GLONASS / GALILEO algorithm engine, NOR-Flash and SDRAM / SRAM storage controllers, DMA controllers, USB1.1 devices and other related IO peripherals.

[0092] Preferably, the inertial navigation module is as follows Figure 5 and Figure 7 As shown in , the inertial navigation module includes a gyroscope and a MEMS accelerometer, and the inertial navigation module is a packaged integral combined module, in which the gyroscope and the accelerometer are both packaged.

[0093] In the present application, preferably, the inertial navigation module 31 and the satellite navigation solution module 32 are respectively installed on two surfaces of the inertial navigation / satellite navigation circuit board, so that the center of mass of the inertial navigation / satellite navigation circuit board is located at its center position.

[0094] In a preferred embodiment, the rudder control circuit board 4 is used to complete the control and drive functions of the 4-way servos of the system;

[0095] The steering operation of the servo is controlled by the servo drive board 5, thereby adjusting the flight attitude of the aircraft.

[0096] The present invention has been described above in conjunction with preferred embodiments, but these embodiments are only exemplary and serve only as an illustration. On this basis, the present invention may be subjected to a variety of substitutions and improvements, all of which fall within the scope of protection of the present invention.

Claims

1. A modular integrated control system for an airdrop aircraft, characterized in that: The control system comprises a power supply circuit board (1), a main control circuit board (2), an inertial navigation / satellite navigation circuit board (3), a rudder control circuit board (4), a servo drive board (5) and a support housing (6); The power circuit board (1), the main control circuit board (2), the inertial navigation / satellite navigation circuit board (3), the rudder control circuit board (4) and the servo drive board (5) are all 2 mm thick and are arranged in parallel with each other with a predetermined gap between them. They are all fixedly mounted in the support shell (6); notches are also provided at both ends of the support shell (6) to allow the electrical connector (8) to extend from the support shell (6); Nylon pads are also provided between the circuit boards to ensure the relative distance between the circuit boards. The distance between the power circuit board (1) and the main control circuit board (2) is 11 mm, the distance between the main control circuit board (2) and the inertial navigation / satellite navigation circuit board (3) is 11 mm, the distance between the inertial navigation / satellite navigation circuit board (3) and the rudder control circuit board (4) is 23 mm, and the distance between the rudder control circuit board (4) and the servo drive board (5) is 15 mm; The control system is also provided with a limit connecting rod (7), which passes through the power supply circuit board (1), the main control circuit board (2), the inertial navigation / satellite navigation circuit board (3), the rudder control circuit board (4) and the steering gear drive board (5) in sequence and is fixedly connected to form an integrated structure; A PDUKE DC / DC isolated power module LCD20-24S05 is provided on the power circuit board (1); when powered by +28V, the peak current of the modular integrated control system is within 5A, the current during stable operation does not exceed 0.8A (20W), and the DC / DC output voltage is selected to be +5V; by providing the isolated power module, the primary electrical ground is isolated from the secondary electrical ground; The isolated power supply module includes an inductor and a capacitor used in combination, so that surge and ripple in any of the two power circuits will not affect the other circuit; The modular integrated control system is used to control the timing of power supply to other devices on the aircraft except the modular integrated control system, the control signal is sent by the main control circuit board (2), and a MOS tube (12) is arranged on the power circuit board (1) to control the on and off of the power circuit; The other devices include an engine, a thermal battery and a fuse, wherein at least three groups of optical couplers (13) and MOS tubes (12) are arranged on the power supply circuit board (1), the power-on control of the engine and the fuse is performed by the optical couplers and the MOS tubes, and the thermal battery is activated by the optical couplers and the MOS tubes; After receiving the thermal battery activation command sent by the main control circuit board (2), the carrier turns on the activation power supply of the thermal battery to complete the activation of the thermal battery. The battery activation current requirement is not less than 4A and not more than 15A, the standard value is 4A, and it lasts for 150ms. The optical coupler and MOS tube are selected from Infineon's IRFR5305PBF and AVAGO's ACPL-024L optical coupler chips; A TLP281 optocoupler chip (14) is also provided on the power supply circuit board (1); the input end of the TLP281 optocoupler chip is connected to the carrier, and the output end is connected to the main control circuit board (2); when the aircraft is normally connected to the carrier, the output end is capable of transmitting an address signal; when the aircraft is disconnected from the carrier, the output end is capable of transmitting a separation signal, thereby enabling the main control circuit board (2) to obtain real-time information on the connection status between the aircraft and the carrier; A surge suppressor (16) and a switching diode (17) are also provided on the power supply circuit board (1), wherein the surge suppressor is used to suppress transient surge voltage, and the switching diode is used to provide reverse connection protection; By arranging the electrical connector (8) and the isolated power supply module (11) at three positions of the power supply circuit board (1), the overall weight of the power supply circuit board is basically balanced, and by selectively arranging the optical coupler, surge suppressor, and MOS tube, the center of mass of the power supply circuit board (1) is located at the center.

2. The modular integrated control system on the airdrop aircraft according to claim 1, characterized in that: The main control circuit board (2) uses the STM32F429 chip; The main control circuit board (2) communicates with the peripheral equipment via RS422. Each RS422 communication channel uses a MAX3490 chip from MAXIM as a level conversion chip for the communication, and converts the RS422 differential communication signal into a single-ended TTL signal.

3. The modular integrated control system on the airdrop aircraft according to claim 1, characterized in that: The inertial navigation / satellite navigation circuit board (3) integrates a satellite receiving antenna, an inertial navigation module, and a satellite navigation solution module; Receive GPS and BD signals through the satellite receiving antenna; The position, speed and time information are obtained in real time through the satellite navigation solution module; The inertial navigation module includes a gyroscope and a MEMS accelerometer.

4. The modular integrated control system on the airdrop aircraft according to claim 3, characterized in that: The satellite receiving antenna includes an active antenna 1 and an active antenna 2. The satellite navigation solution module includes a combiner, a down-conversion circuit module, an A / D conversion circuit module and a baseband processing module; The two RF signals from the active antenna 1 and the active antenna 2 are combined by the combiner; The down-conversion circuit module converts the radio frequency signal into an analog intermediate frequency signal that is convenient for baseband processing; Converting the simulator intermediate frequency signal into a digital intermediate frequency signal through the A / D conversion circuit module; Anti-narrowband interference processing, baseband positioning calculation and communication with the main control circuit board (2) are performed through the baseband processing module.

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