CN204650270U

CN204650270U - A kind of flight control system for SUAV (small unmanned aerial vehicle)

Info

Publication number: CN204650270U
Application number: CN201520301121.XU
Authority: CN
Inventors: 陈乐春
Original assignee: Jiangsu Numeral Accipitridae Skill Development Co Ltd
Current assignee: Jiangsu digital Eagle Polytron Technologies Inc
Priority date: 2015-05-11
Filing date: 2015-05-11
Publication date: 2015-09-16
Anticipated expiration: 2025-05-11

Abstract

The utility model discloses a kind of flight control system for SUAV (small unmanned aerial vehicle), comprise Master control chip, coprocessor, power circuit, ADC interface circuit, usb circuit, LED circuit, SPI interface circuit and flight control chip; Master control chip is connected with SPI interface circuit with coprocessor, ADC interface circuit, usb circuit, LED circuit respectively; Power circuit connects Master control chip and coprocessor, is its power supply; SPI interface circuit is connected with flight control chip; Flight control chip comprises three-axis gyroscope, electronic compass and baroceptor.The utility model can realize the multitask coordinated work of unmanned vehicle, realizes high integration, high-speed data process and computing and automatically to fly control.Data processing and equipment control to be separated to make structure is simplified more, simultaneously flight control is more accurate automatically, can be widely used in current all kinds of small-sized unmanned aircrafts.

Description

A kind of flight control system for SUAV (small unmanned aerial vehicle)

Technical field

The utility model relates to unmanned vehicle control technology, especially for the flight control system of unmanned vehicle.

Background technology

Flight control system (flight control system) be aircraft in flight course, the configuration of aircraft, flight attitude and kinematic parameter are implemented to the system controlled.Flight control system can be used to ensure aircraft stability and control, improve the ability of finishing the work and flight quality, strengthen the safety of flying and alleviate driver's burden.

Small-sized unmanned aircraft, owing to having multiple utilities, can be applied in the various fields such as agricultural, detection, meteorology, hazard forecasting and rescue, present flourish trend at home and abroad.The general Bian industrial computer of flight control system of current unmanned vehicle or single-chip microcomputer are as process core, and module volume is comparatively large, structure between multilayer module is compact not, and design technology is complicated, and the construction cycle is long, and workload greatly, is not easy to realize the system integration.In view of this, develop a kind of flight control system of unmanned vehicle of practicality, become the active demand of industry.

Utility model content

The purpose of this utility model is to provide a kind of flight control system for SUAV (small unmanned aerial vehicle), to meet the flight demand for control of small-sized unmanned aircraft.

The technical solution of the utility model is as follows:

For a flight control system for SUAV (small unmanned aerial vehicle), comprise Master control chip, coprocessor, power circuit, ADC interface circuit, usb circuit, LED circuit, SPI interface circuit and flight control chip; Described Master control chip is connected with SPI interface circuit with coprocessor, ADC interface circuit, usb circuit, LED circuit respectively; Described power circuit connects Master control chip and coprocessor, is its power supply; Described SPI interface circuit is connected with flight control chip; Described flight control chip comprises the first three-axis gyroscope, the second three-axis gyroscope, electronic compass and baroceptor.

Advantageous Effects of the present utility model is:

The utility model can realize the multitask coordinated work of unmanned vehicle, realizes high integration, high-speed data process and computing and automatically to fly control.Data processing and equipment control to be separated to make structure is simplified more, simultaneously flight control is more accurate automatically, can be widely used in current all kinds of small-sized unmanned aircrafts.

The advantage that the utility model adds provides in the description of embodiment part below, and part will become obvious from the following description, or be recognized by practice of the present utility model.

Accompanying drawing explanation

Fig. 1 is general principles block diagram of the present utility model.

Fig. 2 is Master control chip schematic diagram of the present utility model.

Fig. 3 is coprocessor schematic diagram of the present utility model.

Fig. 4 is power circuit principle figure of the present utility model.

Fig. 5 is ADC interface circuit schematic diagram of the present utility model.

Fig. 6 is usb circuit schematic diagram of the present utility model.

Fig. 7 is LED circuit schematic diagram of the present utility model.

Fig. 8 is SPI interface circuit schematic diagram of the present utility model.

Fig. 9 is the first three-axis gyroscope schematic diagram of the present utility model.

Figure 10 is the second three-axis gyroscope schematic diagram of the present utility model.

Figure 11 is electronic compass schematic diagram of the present utility model.

Figure 12 is baroceptor schematic diagram of the present utility model.

Embodiment

Below in conjunction with accompanying drawing, embodiment of the present utility model is described further.

Fig. 1 is theory diagram of the present utility model.As shown in Figure 1, the utility model comprises Master control chip 1, coprocessor 2, power circuit 3, ADC interface circuit 4, usb circuit 5, LED circuit 6, SPI interface circuit 7 and flight control chip 8 ~ 12.Master control chip 1 is connected with SPI interface circuit 7 with coprocessor 2, ADC interface circuit 4, usb circuit 5, LED circuit 6 respectively.Power circuit 3 connects Master control chip 1 and coprocessor 2, is its power supply.SPI interface circuit 7 is connected with flight control chip 8 ~ 12.Flight control chip 8 ~ 12 comprises the first three-axis gyroscope 8, second three-axis gyroscope 9, electronic compass 10 and baroceptor 11.

In Fig. 1, the physical circuit of each several part is see Fig. 2 to Figure 12.As shown in Figure 2, Master control chip U1 adopts STM32f 427 Series MCU, STM32f 427 have employed NVM technique and the ART accelerator of STMicw Electronics, when being performed by flash memory under the frequency of operation of 180MHz, handling property reaches 225DMIPS/608 CoreMark, comprising eight compatible digital signal controller DSC product lines, is the perfect adaptation body of MCU Real Time Control Function and DSP signal processing function.Master control chip U1 is connected to the ferroelectric memory U102 that model is FM25V01.As shown in Figure 3, coprocessor U801 adopts STM32F10XCXT6, and the effect of coprocessor is the Processing tasks alleviating Master control chip.As shown in Figure 4, power circuit 3 have employed the collocation of master control power supply LTC4417 and low pressure difference linear voltage regulator MIC5332.Figure 5 shows that analog to digital converter interface.As shown in Figure 7, LED circuit 6 adopts LT3469 as LED driver.SPI interface circuit shown in Fig. 8 is a kind of synchronous serial Peripheral Interface, and Master control chip and various peripherals can be made to carry out in a serial fashion communicating to exchange information.Fig. 9 to Figure 12 constitutes flight control chip jointly, wherein, Figure 9 shows that three-axis gyroscope MPU6000, Figure 10 shows that three-axis gyroscope L3GD20, Figure 11 shows that electronic compass LSM303D, Figure 12 shows that baroceptor MS5611.

Above-described is only preferred implementation of the present utility model, and the utility model is not limited to above embodiment.Be appreciated that the oher improvements and changes that those skilled in the art directly derive or associate under the prerequisite not departing from basic conception of the present utility model, all should think and be included within protection domain of the present utility model.

Claims

1. the flight control system for SUAV (small unmanned aerial vehicle), it is characterized in that, comprise Master control chip (1), coprocessor (2), power circuit (3), ADC interface circuit (4), usb circuit (5), LED circuit (6), SPI interface circuit (7) and flight control chip; Described Master control chip (1) is connected with SPI interface circuit (7) with coprocessor (2), ADC interface circuit (4), usb circuit (5), LED circuit (6) respectively; Described power circuit (3) connects Master control chip (1) and coprocessor (2), is its power supply; Described SPI interface circuit (7) is connected with flight control chip; Described flight control chip comprises the first three-axis gyroscope (8), the second three-axis gyroscope (9), electronic compass (10) and baroceptor (11).