CN211630393U

CN211630393U - Flight control system

Info

Publication number: CN211630393U
Application number: CN202020591860.8U
Authority: CN
Inventors: 王军
Original assignee: Zhengzhou University of Aeronautics
Current assignee: Zhengzhou University of Aeronautics
Priority date: 2020-04-20
Filing date: 2020-04-20
Publication date: 2020-10-02
Anticipated expiration: 2030-04-20

Abstract

A flight control system relates to the field of flight control. The aircraft comprises flight equipment and an airspace monitoring station, wherein the flight equipment comprises an aircraft and an aircraft controller which are used in a matched mode, and the airspace monitoring station is used for being in communication connection with the aircraft controller. The aircraft controller is in communication connection with the airspace monitoring station, so that the endurance efficiency of the stored electric energy carried by the aircraft can be fully exerted.

Description

Flight control system

Technical Field

The utility model relates to a flight control technical field, concretely relates to flight control system.

Background

With the low price of the unmanned aerial vehicle, the availability of the unmanned aerial vehicle is higher and higher, but after the unmanned aerial vehicle enters an airspace, the unmanned aerial vehicle is extremely easy to cause negative effects on aircrafts in the airspace. The research on the source constitution of the unmanned aerial vehicle is mainly produced and manufactured by companies, and is rarely manufactured by individuals, because the unmanned aerial vehicle flight control system has higher technical requirements. Therefore, in the aspect of airspace management, unmanned aerial vehicles from company production and manufacturing can be managed and controlled, and thus the airspace management cost can be greatly reduced.

Patent document CN105608930A describes an unmanned aerial vehicle safety management system, which includes an onboard control end located in a machine body and a ground remote monitoring and control end, the onboard control end is connected with an unmanned aerial vehicle self-driving instrument control and realizes control of an unmanned aerial vehicle structural platform, an identity recognition module and a positioning system in the onboard control end are connected with a system control module, identity verification information and geographic position information are transmitted to the system control module for judgment, the system control module transmits a signal to the remote monitoring and control end through a wireless communication module, the judgment result of the remote monitoring and control end is reminded through a connected display and an alarm, and an instruction is sent to an execution control module, and the execution control module is connected with the unmanned aerial vehicle self-driving instrument; the remote monitoring and control end comprises a network server communicated with the airborne control end, a monitoring center for exchanging information with the network server is arranged inside the remote monitoring and control end, the monitoring center is connected with a map positioning display module for displaying coordinates, an alarm prompt module for prompting and a remote control module for operating the unmanned aerial vehicle system in an unauthorized mode, and the monitoring center sends instructions to a system control module in the airborne control end. The system control module in its airborne control end sends this equipment unmanned aerial vehicle's ID number and locating information to surveillance center through wireless communication module, and on the one hand the airborne control end can increase unmanned aerial vehicle's weight, and on the other hand, the system control module of airborne control end can consume the electric energy that unmanned aerial vehicle carried through wireless communication module and surveillance center communication connection, reduces unmanned aerial vehicle's continuation of the journey efficiency.

SUMMERY OF THE UTILITY MODEL

The invention aims to provide a flight control system to solve the technical problem of how to furthest exert the endurance efficiency of an aircraft on the basis of realizing monitoring the aircraft in the airspace.

In order to solve the technical problems, the following technical scheme can be selected according to the needs:

the flight control system comprises flight equipment and an airspace monitoring station, wherein the flight equipment comprises an aircraft and an aircraft controller which are used in a matched mode, and the airspace monitoring station is used for being in communication connection with the aircraft controller.

In monitoring an aircraft within an airspace, one approach is to communicatively couple the aircraft with an airspace monitoring station to report the aircraft's position to the airspace monitoring station; another approach is to communicatively couple the aircraft controller with an airspace monitoring station to report the aircraft's position to the airspace monitoring station. Make aircraft and airspace monitoring station communication connection, need occupy the limited stored electric energy of aircraft side on the one hand, on the other hand has the unstable technical problem of communication signal. Considering that when an operator uses the aircraft controller to control the aircraft, the aircraft needs to feed back aircraft position information to the aircraft controller, so that the aircraft controller is in communication connection with the airspace monitoring station, on one hand, communication signals are stable, and on the other hand, the aircraft controller side can be provided with sufficient stored electric energy. In comparison, the endurance efficiency of the stored electric energy carried by the aircraft can be fully exerted by the communication connection of the aircraft controller and the airspace monitoring station.

Preferably, the aircraft includes aircraft side orientation module and aircraft side communication module, aircraft side orientation module is used for exporting aircraft position signal, aircraft controller includes controller side communication module, airspace monitoring station includes monitoring station side communication module, the aircraft position signal warp of aircraft side communication module output the relay of controller side communication module sends to monitoring station side communication module.

Further, the aircraft controller further comprises a controller side positioning module, the controller side positioning module is used for outputting the controller position signal, and the controller side communication module is further used for outputting the controller position signal to the monitoring station side communication module.

Preferably, the aircraft-side communication module comprises a SIM800C type communication module.

Preferably, the aircraft-side communication module comprises a GYM2003B type communication module.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the aircraft controller is in communication connection with the airspace monitoring station, so that the endurance efficiency of the stored electric energy carried by the aircraft can be fully exerted.

2. When the aircraft controller includes the controller-side positioning module, the airspace monitoring station can receive the position of the aircraft controller, and then determine the position of an operator of the aircraft controller.

Drawings

Fig. 1 is a signal flow diagram of a flight control system according to the present invention.

Fig. 2 is a circuit diagram of a power supply module of the flight control system of the present invention.

Fig. 3 is a circuit diagram of a control module of the flight control system of the present invention.

Fig. 4 is a circuit diagram of a communication module of the flight control system of the present invention.

Fig. 5 is a circuit diagram of an RS232 interface module of the flight control system of the present invention.

Fig. 6 is a signal flow diagram of another flight control system according to the present invention.

Detailed Description

The present invention is described below in terms of embodiments with reference to the accompanying drawings to assist those skilled in the art in understanding and realizing the invention. Unless otherwise indicated, the following embodiments and technical terms therein should not be understood to depart from the background of the technical knowledge in the technical field.

In the prior art, a GyM2003B Beidou I RDSS communication module has a Beidou RDSS navigation positioning function, a Beidou RDSS short message communication function and a Beidou RDSS satellite granting function, and a physical communication interface of the GyM2003B Beidou I RDSS communication module is an RS232 interface.

The utility model discloses a flight control system, see figure 1, including flight equipment and airspace monitoring station, flight equipment is including pairing aircraft and the aircraft controller who uses, and airspace monitoring station is used for with aircraft controller communication connection. Generally, an aircraft operator uses an aircraft controller to operate an aircraft, so the aircraft controller needs to be paired with the aircraft, and in use, the aircraft transmits aircraft position information to the aircraft controller so that the aircraft operator can operate the aircraft to a destination position through the aircraft controller. When an aircraft operator uses the aircraft controller to control the aircraft, a power supply circuit of the aircraft controller is in a closed state, at the moment, the aircraft controller is in communication connection with the airspace monitoring station and transmits aircraft position information to the airspace monitoring station, and therefore the airspace monitoring station can acquire the position of the aircraft. In general, an airspace monitoring station may be communicatively coupled to a plurality of aircraft controllers.

Preferably, the aircraft comprises an aircraft-side positioning module and an aircraft-side communication module. To facilitate a simple and precise circuit, the aircraft may further include an aircraft control processing module. The output end of the aircraft side positioning module is correspondingly and electrically connected with the GPIO interface of the aircraft control processing module and used for outputting aircraft position signals. The GPIO interface of the aircraft control processing module is correspondingly and electrically connected with the aircraft side communication module so as to convert the data signals into the communication signals or convert the communication signals into the data signals. The aircraft controller includes a controller-side communication module. To facilitate a simple and precise circuit, the aircraft controller may further include a controller-side control processing module. And the controller side communication module is correspondingly and electrically connected with the GPIO interface of the controller side control processing module. Referring to fig. 2-5, the SIM800C communication module supports 4-frequency GSM/GPRS communications, which in cooperation with existing communication networks may implement wireless communication and data communication functions. Of course, other communication modules supporting 2G, 3G, 4G, 5G functions or wireless communication functions exist in the prior art, and may also be used as the communication module. The power of the SIM800C communication module is relatively high, the voltage reduction circuit formed by the LM2596-a type power chip in fig. 2 can independently supply power to the communication module, and the pin 5 of the LM2596-a type power chip is an enable pin. The STM32F103 type single chip microcomputer in the figure 3 is a control processing module and adopts a 3.3VDC voltage-stabilizing output circuit formed by an LM1117-3.3 type power supply chip in the figure 2 for power supply. Fig. 4 provides a 5VDC high-level communication RS232 interface module, and an ADUM5402 type four-channel digital isolation chip is used as a 3.3VDC high-level to 5VDC high-level output isolation circuit of an STM32F103 type single chip microcomputer.

In fig. 3, the STM32F103 type single chip microcomputer is further connected with an MS5611 type altimeter, and the MS5611 type altimeter can assist in determining the altitude information of the aircraft.

GyM2003B big dipper generation RDSS communication module has big dipper location and big dipper short message function concurrently among the prior art, and it can install on the aircraft. By means of an existing communication network, the aircraft controller side is provided with a SIM800C communication module shown in FIG. 4, so that the positioning of the aircraft and the communication function between the aircraft and the aircraft controller can be realized. And an RS232 interface of the GYM2003B Beidou I RDSS communication module is correspondingly and electrically connected with the RS232 interface module in the figure 5. The LM1117-5.0 type voltage-stabilizing output module in the figure 2 is used for outputting 5VDC voltage and supplying power to a GYM2003B Beidou I RDSS communication module. Compared with GSM/GPRS communication of SIM800C, the Beidou short message function belongs to satellite communication, and can meet the communication requirement of an aircraft and an aircraft controller for more than 1000 meters.

The airspace monitoring station comprises a monitoring station side communication module, and the airspace monitoring station can use an electronic computer which is generally provided with an RS232 interface. The RS232 interface of the electronic computer is connected with the circuit shown in the figures 2-5, and the communication connection between the airspace monitoring station and the aircraft controller can be realized by the aid of the existing communication network.

The utility model discloses in, the aircraft position signal of aircraft side communication module output sends to monitoring station side communication module through controller side communication module transfer, and like this, airspace monitoring station just can learn the position of aircraft.

Further, the aircraft controller may also include a controller-side positioning module, the controller-side positioning module being configured to output a controller position signal, and the controller-side communication module being further configured to output the controller position signal to the monitoring station-side communication module. In this way, the airspace monitoring station can receive the position information of the aircraft of the flight equipment and the position information of the aircraft controller. Generally, in an unused state, the position of the aircraft is similar to the position of the aircraft controller; in the use state, the position of the aircraft is away from the position of the aircraft controller, so that the aircraft in the non-use state can be filtered through the distance between the position of the aircraft and the position of the aircraft controller, and the position of an aircraft operator can be conveniently determined by the airspace monitoring station.

Meanwhile, the inventor also provides a structure on the basis of the structure disclosed by the utility model. Referring to FIG. 6, the airspace monitoring station is adapted to be communicatively coupled to the aircraft and the aircraft controller. Therefore, a communication channel is established between the aircraft side communication module and the monitoring station side communication module, so that aircraft position signals output by the aircraft side communication module can be conveniently output to the monitoring station side communication module; in addition, a communication channel is also established among the aircraft side communication module, the controller side communication module and the monitoring station side communication module, so that aircraft position signals output by the aircraft side communication module are transferred and sent to the monitoring station side communication module through the controller side communication module. The airspace monitoring station can receive position signals of the aircraft by means of the two communication channels to form redundant configuration, and the probability of data loss caused by failure of a single communication channel can be reduced.

Generally, the aircraft side communication module and the controller side communication module have hardware identification codes, so that the monitoring station side communication module can correspond the aircraft side communication module to the position information of the aircraft and the controller side communication module to the position information of the controller.

The present invention has been described in detail with reference to the accompanying drawings and examples. It should be understood that in practice the description of all possible embodiments is not exhaustive and that the inventive concepts of the present invention are presented herein by way of illustration as much as possible. Without departing from the inventive concept of the present invention and without paying creative labor, technical personnel in the technical field can make or delete combinations, specific parameters to perform experimental changes to the technical features in the above embodiments, or use the prior art in the technical field to perform the specific embodiments of conventional replacement and formation by the disclosed technical means, which all belong to the content hidden in the present invention.

Claims

1. A flight control system comprises flight equipment and an airspace monitoring station, wherein the flight equipment comprises an aircraft and an aircraft controller which are used in a matched mode, and the airspace monitoring station is used for being in communication connection with the aircraft controller;

the aircraft comprises an aircraft side positioning module and an aircraft side communication module, the aircraft side positioning module is used for outputting aircraft position signals, the aircraft controller comprises a controller side communication module, the airspace monitoring station comprises a monitoring station side communication module, and the aircraft position signals output by the aircraft side communication module are transmitted to the monitoring station side communication module through the controller side communication module in a transfer mode.

2. The flight control system of claim 1, wherein the aircraft controller further comprises a controller-side location module configured to output the controller position signal, and wherein the controller-side communication module is further configured to output the controller position signal to the monitoring station-side communication module.

3. The flight control system of claim 1, wherein the aircraft-side communication module comprises a SIM 800C-type communication module.

4. The flight control system of claim 1, wherein the aircraft-side communication module comprises a GYM2003B type communication module.