Avionics control system for small sounding rocket

Abstract

The utility model discloses an avionics control system for a small sounding rocket, and the system comprises a power voltage stabilizing circuit and an STM32 microprocessor. The STM32 microprocessor is respectively connected with the MOS tube switching circuit, the emission level reading module, the buzzer driving circuit, the steering engine driving circuit, the height sensor BMP280 driving circuit, the six-axis acceleration sensor MPU6050 driving circuit and the storage module W25Q64 driving circuit; the system can quickly, simply and conveniently complete flight data acquisition and attitude control of the rocket, is simple in structure and convenient to operate, has high integration level, high flexibility and stable attitude control and data acquisition and storage capabilities, is suitable for diversified experiment requirements, greatly simplifies the rocket control process, reduces the dependence on the experiment environment, and improves the experiment efficiency. The method is suitable for various engineering education and scientific research scenes, and the application value of the small sounding rocket in teaching and scientific research is improved.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aerospace, and particularly relates to an avionics control system for a small sounding rocket. BACKGROUND

[0002] With the increasing demand for aerospace education and engineering practice, small sounding rockets have been widely used as an educational and scientific research carrier in various teaching and popular science projects. In particular, in engineering courses in colleges and universities, small sounding rockets can be used to simulate real rockets, allowing students to gain practical experience in experiments. However, the current avionics system of small sounding rockets still has many deficiencies in design and function, which limits its comprehensive application in teaching and scientific research.

[0003] The avionics system of large space rockets usually integrates highly precise sensors and complex control systems, which can provide comprehensive flight control and data acquisition. However, such systems are complex in design and costly, and are usually used in large space projects that require high precision and stable control. Directly applying such systems to small sounding rockets not only greatly increases the cost, but also causes resource waste, exceeding the precision and functional requirements of teaching. In addition, the avionics system of traditional space rockets is usually designed as a whole, suitable for a single scene, and lacks flexibility and scalability to meet the needs of multi-scene applications.

[0004] According to a research report by the Chinese Space magazine, most of the current domestic sounding rockets belong to "uncontrolled rockets", that is, they lack precise attitude and flight trajectory control. The commonly used rocket avionics system in China is also relatively basic in data acquisition and storage function, and can only record single parameters such as the flight height of the rocket, with low accuracy and functional expandability of data recording.

[0005] In contrast, foreign simple control systems have gradually developed towards miniaturization, integration and low cost. The ERIG Rocket Association of the University of Braunschweig in Germany has a high level in the design and production of sounding rockets. The system of the association uses multiple high-precision sensors to collect information such as the flight height and attitude of the rocket, and realizes attitude stabilization through tail rudder control during flight. The data transmission module of the system supports transmission of flight data to a computer after recovery for subsequent analysis. However, although the system performs well in attitude control and data recording, it is not suitable for widespread promotion in basic teaching due to its high cost due to complex design and expensive sensors. In addition, the non-uniformity of the interfaces of each module increases the difficulty of debugging and maintenance, limiting the flexibility in practical application.

[0006] Therefore, the prior art has deficiencies in system accuracy, data storage capacity, expansibility and cost, etc., and cannot meet the actual needs of modern engineering teaching and scientific research experiments. A small-scale sounding rocket avionics system with high integration, strong data acquisition and storage capacity, high expansibility and suitability for teaching promotion is urgently needed. SUMMARY

[0007] In order to overcome the deficiencies of the prior art, the present application provides an avionics control system for a small-scale sounding rocket, comprising a power stabilizing circuit and an STM32 microprocessor, the STM32 microprocessor being connected with a MOS tube switching circuit, a launch level reading module, a buzzer driving circuit, a rudder driving circuit, a height sensor BMP280 driving circuit, a six-axis acceleration sensor MPU6050 driving circuit and a storage module W25Q64 driving circuit respectively; the system can quickly and simply complete flight data acquisition and attitude control of the rocket, has a simple structure, is easy to operate, has high integration, high flexibility and stable attitude control and data acquisition and storage capacity, is suitable for diversified experimental needs, greatly simplifies the rocket control process, reduces the dependence on the experimental environment, is suitable for various engineering education and scientific research scenes, and improves the application value of the small-scale sounding rocket in teaching and scientific research.

[0008] The technical scheme adopted by the present application to solve its technical problems is as follows:

[0009] An avionics control system for a small-scale sounding rocket, comprising a power stabilizing circuit, an STM32 microprocessor, a MOS tube switching circuit, a launch level reading module, a buzzer driving circuit, a buzzer, a rudder driving circuit, a rudder, a height sensor BMP280 driving circuit, a height sensor BMP280, a six-axis acceleration sensor MPU6050 driving circuit, a six-axis acceleration sensor MPU6050, a storage module W25Q64 driving circuit and a storage module W25Q64;

[0010] The power stabilizing circuit provides stable voltage input;

[0011] The STM32 microprocessor is connected with the MOS tube switching circuit, and is used for outputting a high level to realize rocket second-stage ignition;

[0012] The STM32 microprocessor is connected with the launch level reading module, and is used for reading level changes to determine the rocket launch state;

[0013] The STM32 microprocessor is connected with the buzzer driving circuit, and is used for controlling the buzzer to prompt the rocket state;

[0014] The STM32 microprocessor is connected with the rudder driving circuit, and is used for controlling the rudder to realize adjustment of the rocket attitude after the rocket body is launched;

[0015] The STM32 microprocessor is connected with a height sensor BMP280 driving circuit, and is used for controlling the height sensor BMP280.

[0016] The STM32 microprocessor is connected with a six-axis acceleration sensor MPU6050 driving circuit, and is used for controlling the six-axis acceleration sensor MPU6050 to transmit height and acceleration data.

[0017] The STM32 microprocessor is connected with a storage module W25Q64 driving circuit, and is used for controlling the storage module W25Q64 to record and store.

[0018] Preferably, the power stabilizing module is composed of an LM7805 stabilizing chip, an input filter capacitor, an output filter capacitor and a diode protection circuit, and is used for stabilizing the input 8.4V rocket voltage to 5V, so as to provide stable voltage input for each module in the system.

[0019] Preferably, the STM32 microprocessor is built-in with a 32-bit ARM Cortex-M3 core, and is connected with the height sensor BMP280 and the six-axis acceleration sensor MPU6050 through an I 2 C interface, is connected with the storage module W25Q64 through an SPI interface, and is connected with a MOS tube switching circuit, a buzzer driving circuit and a steering engine driving module through a GPIO interface.

[0020] Preferably, the MOS tube switching circuit is composed of an N-channel MOS tube, a current-limiting resistor and a protection diode, and is used for controlling the second-stage ignition of the rocket.

[0021] Preferably, the launch level reading module is composed of a voltage dividing resistor and a comparator circuit, and is used for monitoring the launch level change of the rocket.

[0022] Preferably, the buzzer driving circuit is composed of a buzzer and a driving transistor, and is used for providing audio prompts in different system states.

[0023] Preferably, the BMP280 height sensor and the MPU6050 six-axis acceleration sensor transmit data through I 2 C interfaces.

[0024] Preferably, the storage module W25Q64 stores the height and attitude data in the chip through an SPI interface.

[0025] The beneficial effects of the present application are as follows:

[0026] The system can quickly and simply complete flight data acquisition and attitude control of the rocket, has simple structure, convenient operation, high integration, high flexibility, stable attitude control and data acquisition and storage capacity, is suitable for diversified experimental requirements, greatly simplifies the rocket control process, reduces the dependence on experimental environment, is suitable for various engineering education and scientific research scenes, and improves the application value of the small sounding rocket in teaching and scientific research. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 is a circuit schematic diagram of the system of the present application;

[0028] Figure 2 is a printed circuit board principle diagram front of the system of the present application;

[0029] Figure 3 is a printed circuit board principle diagram back of the system of the present application.

[0030] Marked numbers in the figure: 1, power supply voltage stabilizing circuit, 2, STM32 microprocessor, 3, MOS tube switch circuit, 4, transmitting level reading module, 5, buzzer driving circuit, 6, buzzer, 7, steering engine driving circuit, 8, steering engine, 9, height sensor BMP280 driving circuit, 10, height sensor BMP280, 11, six-axis acceleration sensor MPU6050 driving circuit, 12, six-axis acceleration sensor MPU6050, 13, storage module W25Q64 driving circuit, 14, storage module W25Q64. DETAILED DESCRIPTION

[0031] The present application is further illustrated below in combination with the drawings and examples.

[0032] The technical problem to be solved by the present application is to overcome the deficiencies of the existing small sounding rocket avionics system in precision, data storage, expandability and cost, and to provide a low-cost and integrated avionics system suitable for small sounding rockets to meet the demand of engineering education and scientific research experiments for multifunctional, multidimensional data acquisition and attitude control.

[0033] The application provides a modularized sounding rocket control system for data acquisition, attitude control, data storage and transmission tasks of a small-sized sounding rocket, and the system comprises: each module in a power stabilizing circuit provides stable voltage input, an STM32 microprocessor outputs a high level through a MOS tube switch circuit to realize rocket second stage ignition, a launch level reading module reads level changes to determine the rocket launch state, or a height trigger algorithm and an attitude trigger algorithm are used to determine the rocket launch state, and a buzzer driving circuit is used to control a buzzer to prompt the rocket state, a rudder driving circuit is used to control a rudder to realize adjustment of the rocket attitude after the rocket body is launched, a rocket control algorithm is embedded in an execution system, a height sensor BMP280 driving circuit is used to control a height sensor BMP280, a six-axis acceleration sensor MPU6050 driving circuit is used to control a six-axis acceleration sensor MPU6050 to transmit height and acceleration data, a storage module W25Q64 driving circuit is used to control a storage module W25Q64 to record and store, and a fixed-height recovery algorithm or a fixed-time recovery algorithm is used to realize parachute recovery of the rocket body.

[0034] The system uses an STM32 microprocessor as a core control unit, has efficient data processing and control capabilities, and can respond to various state changes in real time during flight, ensuring the accuracy of attitude control and the real-time performance of data acquisition.

[0035] The system designs multiple trigger modes, including level jump, attitude change and height mutation trigger mechanisms, so as to flexibly select trigger conditions according to different launch requirements, thereby ensuring reliable launch of the rocket and meeting diversified experimental requirements.

[0036] The system is equipped with a BMP280 height sensor and a MPU6050 six-axis acceleration sensor, which can accurately collect height and attitude information during flight. Sensor data is transmitted through an I 2 C interface, ensuring the stability and accuracy of data acquisition and providing high-quality data support for subsequent data analysis.

[0037] The storage module W25Q64 supports large-capacity flight data recording, and stores height, attitude and other data in the chip through an SPI interface, realizes efficient and complete data saving, and facilitates data export and analysis after flight.

[0038] The system supports flexible use of expansion interfaces, can connect external airspeed meters, GPS and other modules, and provides a wider functional selection space for application of the sounding rocket in different experimental scenarios.

[0039] Embodiment:

[0040] Figure 1 and Figure 2The circuit schematic and the printed circuit board schematic of the avionics control system for the small sounding rocket according to the application are shown respectively.

[0041] As shown in Figure 1 The modules of the small sounding rocket control system according to the application are interconnected through corresponding circuits to ensure real-time control and data acquisition during the flight of the rocket. The power stabilizing module is composed of an LM7805 stabilizing chip, an input filter capacitor, an output filter capacitor and a diode protection circuit, and is used to stabilize the input 8.4V rocket-borne voltage to 5V to provide stable voltage input for each module in the system. The stabilizing module is connected with the main control microprocessor, sensors and driving circuits to ensure continuous and stable operation of the system during the flight and avoid the influence of voltage fluctuation on the attitude control and data acquisition accuracy of the rocket. The main control microprocessor STM32 has a 32-bit ARM Cortex-M3 core built-in, and its I 2 The C interface is connected with the height sensor BMP280 and the acceleration sensor MPU6050, connected with the storage module W25Q64 through the SPI interface, and connected with the MOS tube switching circuit, the buzzer driving circuit and the servo driving module through the GPIO interface.

[0042] The MOS tube switching circuit is composed of an N-channel MOS tube, a current-limiting resistor and a protection diode, and is used to control the secondary ignition of the rocket. The GPIO output of the STM32 microprocessor sends a high-level signal to the gate of the MOS tube to make the MOS tube conductive, thereby triggering the secondary ignition. The current-limiting resistor is used to prevent instantaneous large current from damaging the element, and the diode protection circuit prevents reverse current from entering the MOS tube to protect the safety of the circuit.

[0043] The launch level reading module is composed of a voltage dividing resistor and a comparator circuit, and is used to monitor the change of the launch level of the rocket. After the module detects a level jump, it transmits a launch signal to the STM32 microprocessor, and the system enters the flight mode. The launch condition can be judged by the height trigger algorithm or the attitude trigger algorithm to ensure that the rocket starts the flight control program after meeting the launch condition.

[0044] The buzzer driving circuit is composed of a buzzer and a driving transistor, and is used to provide audio prompts in different system states, which facilitates the ground monitoring personnel to understand the working state of the rocket in the preparation of launch, flight process and recovery state. The circuit controls the current input of the buzzer through an NPN transistor, and the STM32 microprocessor triggers the buzzer to emit different audio signals by controlling the base of the transistor.

[0045] The steering engine driving module is used to control the attitude adjustment of the rocket, which is composed of a PWM signal generation circuit and a driving transistor, and is connected with the STM32 microprocessor and the steering engine respectively. The PWM signal generation circuit can be realized by a NE555 timing chip, and the STM32 microprocessor controls the frequency and duty cycle of the PWM signal, so as to adjust the angle of the steering engine and ensure the stability of the rocket flight. The steering engine adjusts the direction to realize the roll and pitch control of the rocket, and cooperates with the attitude control algorithm to adjust the attitude in real time, so as to realize the precise flight trajectory.

[0046] The height sensor BMP280 and its driving circuit are connected with the STM32 microprocessor through the I 2 C interface, and real-time flight height data of the rocket are collected. The height sensor BMP280 uses MEMS technology and can provide high-precision height data during flight to ensure the accuracy of flight data. The height sensor BMP280 driving circuit includes I 2 C interface and pull-up resistance, and the pull-up resistance ensures the stable transmission of I 2 C signal. After receiving the height data, the STM32 stores it in the storage module W25Q64 through the SPI interface.

[0047] The six-axis acceleration sensor MPU6050 and its driving circuit are used to detect the attitude and acceleration changes of the rocket, which is composed of a three-axis acceleration sensor and a three-axis gyroscope, and is connected with the STM32 microprocessor through the I 2 C interface, and real-time attitude and acceleration data are transmitted. The circuit contains a power filter capacitor and an interface pull-up resistance to ensure the stability of the data on the I 2 C bus.

[0048] The storage module W25Q64 is a 64Mb SPI NOR Flash chip, and the storage module W25Q64 driving circuit is composed of an SPI interface and a voltage conversion circuit. The STM32 microprocessor transmits the collected flight data to the storage module W25Q64 for storage through the SPI interface, and the flight data can be exported for analysis after the flight is completed.

[0049] After the rocket is launched, the system enters the flight mode. The STM32 microprocessor adjusts the attitude of the rocket according to the signal transmitted by the launch level reading module, combined with the real-time data of the height sensor and the acceleration sensor. The steering engine stabilizes the pitch and roll of the rocket through the attitude control algorithm, and maintains the flight trajectory. Through the SPI interface, the data is stored in the storage module W25Q64 for subsequent analysis and debugging. The system uses the fixed height recovery algorithm and the fixed time recovery algorithm, and when the rocket reaches the preset height or flight time, the recovery parachute is released through the steering engine control module to ensure the safe recovery of the rocket.

[0050] The system also supports multiple replacement options. The STM32 microprocessor can be replaced with a microprocessor with wireless communication capabilities such as ESP32 to enable remote data monitoring. The altitude sensor BMP280 can be replaced with BMP388 to improve the accuracy of altitude measurement. The acceleration sensor MPU6050 can be replaced with MPU9250 to add a magnetometer function for more comprehensive attitude detection. In addition, the power supply stabilization module of the system can use LM2596 DC-DC buck chip to improve power efficiency and reduce heat, meeting the needs of longer flight testing of rockets.

Claims

1. An avionics control system for a small sounding rocket, characterized in that, The power supply voltage stabilizing circuit, the STM32 microprocessor, the MOS tube switch circuit, the launch level reading module, the buzzer driving circuit, the buzzer, the steering engine driving circuit, the steering engine, the height sensor BMP280 driving circuit, the height sensor BMP280, the six-axis acceleration sensor MPU6050 driving circuit, the six-axis acceleration sensor MPU6050, the storage module W25Q64 driving circuit and the storage module W25Q64 are included. The power supply voltage stabilizing circuit provides stable voltage input. The STM32 microprocessor is connected with the MOS tube switch circuit, and is used for outputting a high level to realize the rocket second stage ignition. The STM32 microprocessor is connected with the launch level reading module, and is used for reading the level change to determine the rocket launch state. The STM32 microprocessor is connected with the buzzer driving circuit, and is used for controlling the buzzer to prompt the rocket state. The STM32 microprocessor is connected with the steering engine driving circuit, and is used for controlling the steering engine to realize the rocket attitude adjustment after the rocket body is launched. The STM32 microprocessor is connected with the height sensor BMP280 driving circuit, and is used for controlling the height sensor BMP280. The STM32 microprocessor is connected with the six-axis acceleration sensor MPU6050 driving circuit, and is used for controlling the six-axis acceleration sensor MPU6050 to transmit height and acceleration data. The STM32 microprocessor is connected with the storage module W25Q64 driving circuit, and is used for controlling the storage module W25Q64 to record and store.

2. The avionics control system for small sounding rockets according to claim 1, characterized in that, The power supply voltage stabilizing circuit is composed of an LM7805 voltage stabilizing chip, an input filter capacitor, an output filter capacitor and a diode protection circuit, is used for stabilizing the input 8.4V rocket load voltage to 5V, and provides stable voltage input for each module in the system.

3. The avionics control system for small sounding rockets according to claim 1, characterized in that, The STM32 microprocessor is built-in 32-bit ARM Cortex-M3 core, through I 2 The C interface is connected with the height sensor BMP280 and the six-axis acceleration sensor MPU6050, connected with the storage module W25Q64 through the SPI interface, and connected with the MOS tube switching circuit, the buzzer driving circuit and the steering engine driving module through the GPIO interface.

4. The avionics control system for small sounding rockets according to claim 1, characterized in that, The MOS tube switch circuit is composed of an N-channel MOS tube, a current limiting resistor and a protection diode, and is used for controlling the rocket second stage ignition.

5. The avionics control system for small sounding rockets according to claim 1, characterized in that, The launch level reading module is composed of a voltage dividing resistor and a comparator circuit, and is used for monitoring the rocket launch level change.

6. The avionics control system for small sounding rockets according to claim 1, characterized in that, The buzzer driving circuit is composed of a buzzer and a driving transistor, and is used for providing audio prompts in different system states.

7. The avionics control system for small sounding rockets according to claim 1, characterized in that, The BMP280 altitude sensor and MPU6050 six-axis acceleration sensor transmit data through I 2 C interface.

8. The avionics control system for small sounding rockets according to claim 1, characterized in that, The storage module W25Q64 stores height and attitude data in the chip through an SPI interface.

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