Civil aircraft autonomous operation sensing calculation control airborne end calculation support module

Abstract

The utility model discloses a civil aircraft autonomous operation sensing calculation control airborne end calculation support module, which comprises a wireless transceiver module, a data sorting / caching element, a built-in gyroscope, an analog-to-digital converter, an STM32 minimum system chip and other components, the STM32 chip executes a core operation process, and finally data is output through the data sorting module, so that a civil aircraft autonomous operation sensing calculation control airborne end calculation support module is formed, real-time risk sensing calculation, conflict-free four-dimensional flight path planning and flight guide tasks are executed through multi-link information fusion, and reliable decision support is provided for civil aircraft pilots. The airborne calculation module aims at improving the intelligent and automatic level of current air traffic management, reducing the workload of controllers and pilots, further liberating the airspace capacity and improving the air traffic operation efficiency.

Description

Technical Field

[0001] The utility model belongs to the field of airborne decision support hardware for air transport aircraft, and particularly relates to an airborne computing support module for civil aircraft autonomous operation sensing, transmission, computing and control. Background Art

[0002] In terms of advanced air traffic flow management, situation awareness, and operation control decision-making technologies for civil aviation aircraft, relevant domestic and international research has formed a relatively complete method system, such as advanced technologies for four-dimensional trajectory prediction intelligent situation awareness methods, trajectory planning decisions, and flight control guidance for aircraft under trajectory-based operation / autonomous operation modes. However, due to the differences in the comprehensive development level of civil aviation transportation worldwide, and even the differences in infrastructure construction and control rules among domestic airports and air traffic control units, the resistance to the reform of trajectory-based operation and autonomous operation in the civil aviation system is significant, which is mainly reflected in problems such as insufficient hardware support capabilities of communication and planning decision-making systems in mainstream aircraft in the civil aviation transportation market and traditional air traffic control systems, and closed-source aircraft system interfaces. As a result, a large number of advanced control concepts and methods cannot be effectively implemented and promoted at the actual operation level. A multifunctional integrated hardware that can promote the smooth transition of civil aviation transportation to the trajectory-based operation mode at a low cost is urgently needed in the current industrial innovation in the civil aviation transportation field. Content of the Utility Model

[0003] To achieve the above object, the technical solution of the utility model is as follows: An airborne computing support module for civil aircraft autonomous operation sensing, transmission, computing and control, the module includes a wireless transceiver module, an STM32 minimum system board, an air-to-ground information transmission module, a data sorting module, an RS485 data buffer element, a built-in gyroscope / accelerometer, a flight management system data processing element, a radar meteorological data receiving element, a power supply and other operation control components, and an analog-to-digital converter functional block. Each block is controlled by the STM32 minimum system board and connected through a data bus.

[0004] As an improvement of the utility model, the RS485 data buffer element is respectively connected to the TXD1-3 ports and RXD 1-3 ports of three STM32 minimum system boards to implement serial communication.

[0005] As an improvement of the utility model, the wireless transceiver module and the air-to-ground information transmission module are respectively connected to the PA10 ports, PA9 ports, CC2530 TXD1 ports, and CC2530 RXD1 ports of two STM32 minimum system boards.

[0006] As an improvement of the utility model, the data sorting module is a 51 single-chip microcomputer minimum system board, which is connected to the RST port, MCU1_TXD port, and MCU1_RXD port, and is connected to the power supply and the timing crystal oscillator.

[0007] As an improvement of the present utility model, the data processing element of the flight management system is connected to the GY1_RST port, GY1_SCK port, GY1_MO port, GY1_MI port, GY_GRN port, and GY_TXO port, and is simultaneously connected to the power supply system.

[0008] As an improvement of the present utility model, the radar meteorological data receiving element is connected to the GY_GRN port, GY_RX1 port, GY_TXO port, GY_BLK port, GY2_RST port, GY2_SCK port, GY2_MO port, and GY2_MI port.

[0009] As an improvement of the present utility model, the analog-to-digital converter functional block is connected to the ADS_RDY port, ADS_ADDR port, ADS_SCL port, and ADS_SDA port; the gyroscope accelerometer is connected to the MPU_SCL port and MPU_SDA port.

[0010] Compared with the prior art, the beneficial effects of the present utility model are as follows: The present utility model adopts a standard RS485 control bus, and standard SPI serial communication is used between internal components. The program has a high degree of modularization, the hardware circuit is reliable, and the computing power is powerful and stable; it can add decision support functions in the closed-source environment of the current civil aviation large aircraft system, and has civil aviation airworthiness capabilities as well as human-machine interaction and decision support capabilities during the airworthiness process; it integrates complete functional modules required for the autonomous operation of civil aircraft, and can realize closed-loop decision support service functions at the tactical operation level such as multi-type conflict detection, conflict-free flight path planning, and four-dimensional flight path flight guidance on the airborne side. Description of the Drawings

[0011] Figure 1 It is the main composition and basic architecture of the airborne computing support module for sensing, transmitting, computing, and controlling.

[0012] Figure 2 It is the detailed interface design diagram of the airborne computing support module for sensing, transmitting, computing, and controlling.

[0013] List of drawing reference signs: Wireless transceiver module 1, STM32 minimum system board 2, air-to-ground information transmission module 3, data sorting module 4, RS485 data buffer element 5, built-in gyroscope / accelerometer 6, data processing element of flight management system 7, radar meteorological data receiving element 8, power supply and other operation control components 9, analog-to-digital converter and other functional blocks 10. Detailed Embodiments

[0014] The following further clarifies the present utility model in conjunction with the drawings and specific embodiments. It should be understood that the following specific embodiments are only used to illustrate the present utility model and not to limit the scope of the present utility model.

[0015] Example: As Figure 1-2 shown, a civil aircraft autonomous operation sensing, transmitting, computing and controlling airborne computing support module, the module includes a wireless transceiver module, an STM32 ARM Cortex-M minimum system board, an air-to-ground information transmission module, an 89C52RC data sorting module, an RS485 data cache element, a built-in gyroscope / accelerometer, a flight management system data processing element, a radar weather data receiving element, a power supply and other operation control components, and an analog-to-digital converter functional block. Each block is controlled by the STM32 minimum system board and connected through a data bus.

[0016] In this embodiment, the wireless transceiver module is used to receive the aircraft operation situation data uploaded from the ground, including Automatic Dependent Surveillance-Broadcast (ADS-B) data, flight plan information, and the operation status data of surrounding aircraft. The STM32 ARM Cortex-M minimum system board. A total of three groups of STM32 ARM Cortex-M minimum system board components are designed for this airborne computing support module, which are used to receive data from each input interface (such as the operation situation of the operating aircraft, the situation of surrounding aircraft, and the meteorological situation), and perform calculations for aircraft operation risk perception, conflict-free flight path planning, and flight guidance instruction calculation. The air-to-ground information transmission module is used for the aircraft to send data to the air-to-ground information transmission link on board. The data content mainly includes: the real-time risk perception result of aircraft operation, the conflict-free four-dimensional flight path data of the aircraft planned by the computing support module, and the guidance instruction text for guiding the pilot to execute the planned flight path. The 89C52RC data sorting module is used to sort the calculation results of the STM32 ARM Cortex-M minimum system board, and sort and format the real-time risk perception result of aircraft operation, the conflict-free four-dimensional flight path data of the aircraft planned by the computing support module, and the guidance instruction text for guiding the pilot to execute the planned flight path according to the agreed format, and then send them to each output port. The S485 data cache element: A total of three groups of RS485 data cache elements are designed for this airborne computing support module, which are respectively used for port output and caching of the real-time risk perception result of aircraft operation, the conflict-free four-dimensional flight path data of the aircraft planned by the computing support module, and the guidance instruction text data for guiding the pilot to execute the planned flight path. The built-in gyroscope / accelerometer is used to measure the flight attitude (roll angle, pitch angle, yaw angle), speed, acceleration and other flight state information of the autonomously operating aircraft. The flight management system data processing element is used to receive the operation situation data of the aircraft body, including real-time aircraft data such as speed (true airspeed, ground speed), heading (magnetic heading, true heading), altitude (corrected sea-level pressure altitude, standard pressure altitude), pitch angle, roll angle, yaw angle, and remaining fuel. The radar meteorological data receiving element is used to receive the contour line information of the meteorological avoidance area obtained by meteorological radar scanning. The power supply and other operation control components are used to power on this computing module and perform interruption control in abnormal states. Functional blocks such as analog-to-digital converters are used to convert the internal analog signals of the computing module into electrical signals / digital signals.

[0017] Further, the three-part RS485 communication board is respectively connected to the TXD1-3 and RXD 1-3 ports of three STM32 minimum system boards to implement serial communication. The wireless transceiver module and the air-to-ground information transmission module are respectively connected to the PA10, PA9, CC2530 TXD1, and CC2530 RXD1 ports of two STM32 minimum system boards. The data sorting module is a 51 single-chip microcomputer minimum system board, which is connected to the RST, MCU1_TXD, and MCU1_RXD ports, and is connected to the power supply and the timing crystal oscillator. The flight data management chip is connected to the GY1_RST, GY1_SCK, GY1_MO, GY1_MI, GY_GRN, and GY_TXO ports, and is simultaneously connected to the power supply system. The radar meteorological data receiving chip is connected to the GY_GRN, GY_RX1, GY_TXO, GY_BLK, GY2_RST, GY2_SCK, GY2_MO, and GY2_MI ports. The M-D converter is connected to the ADS_RDY, ADS_ADDR, ADS_SCL, and ADS_SDA ports; the gyroscope accelerometer is connected to the MPU_SCL and MPU_SDA ports.

[0018] Working principle: After the airborne computing support module of the "sensing, transmitting, computing, and controlling" for civil aircraft autonomous operation is powered on, the surrounding aircraft and meteorological avoidance area situation information is obtained in real time through the wireless transceiver module and 8 radar meteorological data receiving elements; the operation situation information of this aircraft is obtained through functional blocks such as the built-in gyroscope / accelerometer 6, the built-in gyroscope / accelerometer 7, the flight management system data processing element, and the 10 analog-to-digital converter; then the information is integrated through the designed data bus and transmitted to the element 2 STM32 ARM Cortex-M minimum system board, and the STM32 minimum system board 2 performs aircraft operation risk perception calculation, conflict-free flight path planning calculation, and flight guidance instruction calculation; after the STM32 minimum system board 2 completes its core computing function, the air-to-ground information transmission module 3 integrates and sends the operation results of the STM32 minimum system board 2, including the real-time aircraft operation risk perception results, the conflict-free four-dimensional flight path data of the aircraft planned by the computing support module, and the guidance instruction text data for guiding the pilot to execute the planned flight path, to the ground receiving port; the element 4 89C52RC data sorting module sorts and formats the real-time aircraft operation risk perception results, the conflict-free four-dimensional flight path data of the aircraft planned by the computing support module, and the guidance instruction text for guiding the pilot to execute the planned flight path according to the agreed format, and then sends them to each output port of this airborne computing module; finally, the operation of this airborne computing module can be shut down through the 9 power supply and other operation control components. It should be noted that the above working principle is used to explain the principle of the present invention, and is to explain and elaborate on the specific structure to be protected by the present invention.

[0019] It should be noted that the above content only illustrates the technical idea of the present utility model, and the protection scope of the present utility model cannot be limited thereby. For those of ordinary skill in the art, without departing from the principle of the present utility model, several improvements and refinements can still be made, and these improvements and refinements all fall within the protection scope of the claims of the present utility model.

Claims

1. A civil aircraft autonomous operation sensing, computing and control airborne computing support module, characterized in that: The module comprises a wireless transceiver module (1), an STM32 minimum system board (2), an air-to-ground information transmission module (3), a data sorting module (4), an RS485 data buffer element (5), a built-in gyroscope / accelerometer (6), a flight management system data processing element (7), a radar meteorological data receiving element (8), a power supply and other operation control components (9), and an analog-to-digital converter functional block (10), wherein each block is controlled by the STM32 minimum system board (2) and connected by a data bus.

2. According to claim 1, the onboard computing support module for sensing, calculating and controlling autonomous operation of civil aircraft is characterized in that: The RS485 data buffer element (5) is respectively connected to the TXD1-3 and RXD 1-3 ports of the three STM32 minimum system boards to implement serial communication.

3. The onboard computing support module for sensing, calculating and controlling autonomous operation of a civil aircraft according to claim 1 is characterized in that: The wireless transceiver module and the air-to-ground information transmission module are respectively connected to the PA10 port, PA9 port, CC2530 TXD1 port and CC2530 RXD1 port of the two STM32 minimum system boards.

4. The onboard computing support module for sensing, calculating and controlling autonomous operation of a civil aircraft according to claim 1, characterized in that: The data sorting module (4) is a minimum system board of a 51 single-chip microcomputer, connected to the RST port, the MCU1_TXD port, the MCU1_RXD port, and connected to a power supply and a timing crystal oscillator.

5. The onboard computing support module for sensing, calculating and controlling autonomous operation of civil aircraft according to claim 1, characterized in that: The flight management system data processing element (7) is connected to the GY1_RST port, the GY1_SCK port, the GY1_MO port, the GY1_MI port, the GY_GRN port, and the GY_TXO port, and is also connected to the power supply system.

6. The onboard computing support module for sensing, computing and controlling autonomous operation of a civil aircraft according to claim 1, characterized in that: The radar weather data receiving element (8) is connected to the GY_GRN port, the GY_RX1 port, the GY_TXO port, the GY_BLK port, the GY2_RST port, the GY2_SCK port, the GY2_MO port, and the GY2_MI port.

7. The onboard computing support module for sensing, calculating and controlling autonomous operation of civil aircraft according to claim 1, characterized in that: The analog-to-digital converter functional block (10) is connected to the ADS_RDY port, the ADS_ADDR port, the ADS_SCL port, and the ADS_SDA port, and the gyroscope accelerometer is connected to the MPU_SCL port and the MPU_SDA port.

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