阅读说明：本技术 一种大型货运无人机机载航电系统 (Large-scale freight transportation unmanned aerial vehicle machine carries avionics system ) 是由 廖智麟 崔志华 于 2020-06-15 设计创作，主要内容包括：一种大型货运无人机机载航电系统,其特征在于,包括飞行控制管理计算机、轮载信号触发系统、飞行参数记录器、角速率陀螺、无线电高度表、磁传感器、灭火系统、主舵面控制系统、发动机与刹车控制系统、继电器盒、发动机起动系统、一次侧发动机控制板、配电控制盒、刹车采集系统、汽油系统、信号处理单元、照明系统、滑油控制系统和发动机采集系统；飞行控制管理计算机与轮载信号触发系统通讯连接,用于控制轮载的开启与关闭；飞行控制管理计算机与飞行参数记录器通讯连接,用于对飞行控制管理计算机数据进行记录。本发明提出一种大型货运无人机机载航电系统,本发明构建出核心关键部件,双余度控制和双余度监控。(An airborne avionics system of a large freight transport unmanned aerial vehicle is characterized by comprising a flight control management computer, a wheel-borne signal triggering system, a flight parameter recorder, an angular rate gyro, a radio altimeter, a magnetic sensor, a fire extinguishing system, a main rudder surface control system, an engine and brake control system, a relay box, an engine starting system, a primary side engine control panel, a power distribution control box, a brake acquisition system, a gasoline system, a signal processing unit, a lighting system, a lubricating oil control system and an engine acquisition system; the flight control management computer is in communication connection with the wheel load signal triggering system and is used for controlling the opening and closing of the wheel load; the flight control management computer is in communication connection with the flight parameter recorder and is used for recording data of the flight control management computer. The invention provides an airborne avionics system of a large freight transport unmanned aerial vehicle.)

1. An airborne avionics system of a large freight transport unmanned aerial vehicle is characterized by comprising a flight control management computer, a wheel-borne signal triggering system, a flight parameter recorder, an angular rate gyro, a radio altimeter, a magnetic sensor, a fire extinguishing system, a main rudder surface control system, an engine and brake control system, a relay box, an engine starting system, a primary side engine control panel, a power distribution control box, a brake acquisition system, a gasoline system, a signal processing unit, a lighting system, a lubricating oil control system and an engine acquisition system;

the flight control management computer is in communication connection with the wheel load signal triggering system and is used for controlling the opening and closing of the wheel load; the flight control management computer is in communication connection with the flight parameter recorder and is used for recording data of the flight control management computer;

the angular rate gyroscope is in communication connection with the flight control management computer and is used for providing an angular speed signal for the navigation system;

the radio altimeter is in communication connection with the flight control management computer and is used for measuring the vertical distance from the airplane to the ground and sending the measured vertical distance to the flight control management computer for data processing; the magnetic sensor, the fire extinguishing system and the main control surface control system are all in communication connection with a flight control management computer;

the engine and the brake control system are in communication connection with the engine and the brake control system and are used for controlling the engine and the brake;

the flight control management computer is respectively connected with the engine starting system and the fire extinguishing system through the relay box; the flight control management computer is respectively in communication connection with the primary side engine control board, the power distribution control box and the signal processing unit;

the signal processing unit is respectively in communication connection with the engine acquisition system and the lubricating oil control system; the signal processing unit is connected with the lighting system through the relay box;

the flight control management computer is in communication connection with a cabin door system, a vertical gyroscope, an atmospheric data system, an optical fiber navigation system, a flap control system, an L-waveband airborne data terminal, a U-waveband airborne data terminal and a brake acquisition system; the L-waveband airborne data terminal is in communication connection with an image encoder; the flight control management computer is connected with an oil heat dissipation air door electric mechanism and a fish scale plate electric mechanism through the relay box in a communication mode.

2. The airborne avionics system of the large-scale freight transportation unmanned aerial vehicle according to claim 1, characterized in that the wheel load signal trigger systems are respectively connected through a left wheel load proximity switch and a right wheel load proximity switch inside the wheel load signal trigger systems.

3. The airborne avionics system of a large-scale freight transportation unmanned aerial vehicle according to claim 1, characterized in that the lighting system comprises a left navigation light, a right navigation light, a tail navigation light, a cockpit overhead light, a cargo bay overhead light and a switch; the left navigation light, the right navigation light and the tail navigation light are respectively connected with the relay box; the cockpit top light and the cargo bay top light are connected with the relay box through the switch.

4. The airborne avionics system of a large-scale cargo drone of claim 1, wherein the lubricant control system includes a lubricant radiator damper position sensor, a lubricant pressure sensor, and a lubricant temperature sensor.

5. The airborne avionics system of a large-scale cargo UAV according to claim 1, characterized in that the engine acquisition system comprises an engine speed sensor, a vaporization temperature sensor, an intake air pressure sensor and a cylinder temperature sensor.

6. The airborne avionics system of a large-scale freight transportation unmanned aerial vehicle according to claim 1, characterized in that the brake acquisition system comprises a left brake pressure sensor, a right brake pressure sensor and a cold air pressure sensor.

7. The airborne avionics system of a large-scale freight transportation unmanned aerial vehicle according to claim 1, characterized in that the cabin door system is connected with the flight control management computer through a cabin door microswitch of the cabin door system.

8. The airborne avionics system of a large-scale cargo drone of claim 1, characterized in that the atmospheric data system comprises an atmospheric data computer, an atmospheric temperature sensor and a nose airspeed head; the atmospheric temperature sensor and the nose airspeed head are connected with the flight control management computer through an atmospheric data computer.

9. The airborne avionics system of a large-scale cargo drone of claim 1, characterized in that the fiber optic navigation system comprises a fiber optic combined inertial navigation and GNSS anti-jamming antenna; the GNSS anti-interference antenna is in communication connection with the flight control management computer through the optical fiber combination inertial navigation.

10. The airborne avionics system of a large-scale cargo unmanned aerial vehicle according to claim 1, characterized in that the flap control system comprises a flap system sensor, a limit switch, an upper flap relay box, a lower flap relay box, an upper flap drive motor and a lower drive motor; the flap system sensor is in communication connection with the flight control management computer; the upper flap driving motor is connected with the upper flap relay; the lower flap driving motor is connected with a lower flap relay; the upper flap driving motor and the lower flap driving motor are connected with a flight control management computer through limit switches.

Technical Field

The invention relates to the field, and mainly relates to an airborne avionics system of a large freight transport unmanned aerial vehicle.

Background

Some unmanned aerial vehicles are improved by unmanned research and development design of a prototype, key technologies of the general design of the unmanned aerial vehicle improved by the human are broken through, the matching of an aircraft-engine-control system, the identification of aircraft pneumatic parameters, the testing of the quality characteristics of the whole unmanned aerial vehicle, the comprehensive testing of the system and the like are broken through, the unmanned aerial vehicle has unique performance advantages of large freight load, long endurance time, remarkable take-off and landing capability and the like, and has huge market prospect and commercial value potential.

The airborne avionic system of the unmanned aerial vehicle changed from the manned aircraft is changed, so that the airborne avionic system of the large-sized freight unmanned aerial vehicle is invented.

Disclosure of Invention

Objects of the invention

In order to solve the technical problems in the background art, the invention provides an airborne avionics system of a large freight transport unmanned aerial vehicle, which constructs key core components, dual-redundancy control and dual-redundancy monitoring; improve the flight and control safety.

(II) technical scheme

In order to solve the problems, the invention provides an airborne avionics system of a large freight transport unmanned aerial vehicle, which comprises a flight control management computer, a wheel-mounted signal triggering system, a flight parameter recorder, an angular rate gyroscope, a radio altimeter, a magnetic sensor, a fire extinguishing system, a main rudder surface control system, an engine and brake control system, a relay box, an engine starting system, a primary side engine control panel, a power distribution control box, a brake acquisition system, a gasoline system, a signal processing unit, a lighting system, a lubricating oil control system and an engine acquisition system;

the flight control management computer is in communication connection with the wheel load signal triggering system and is used for controlling the opening and closing of the wheel load; the flight control management computer is in communication connection with the flight parameter recorder and is used for recording data of the flight control management computer;

the angular rate gyroscope is in communication connection with the flight control management computer and is used for providing an angular speed signal for the navigation system;

the radio altimeter is in communication connection with the flight control management computer and is used for measuring the vertical distance from the airplane to the ground and sending the measured vertical distance to the flight control management computer for data processing; the magnetic sensor, the fire extinguishing system and the main control surface control system are all in communication connection with a flight control management computer;

the engine and the brake control system are in communication connection with the engine and the brake control system and are used for controlling the engine and the brake;

the flight control management computer is respectively connected with the engine starting system and the fire extinguishing system through the relay box; the flight control management computer is respectively in communication connection with the primary side engine control board, the power distribution control box and the signal processing unit;

the signal processing unit is respectively in communication connection with the engine acquisition system and the lubricating oil control system; the signal processing unit is connected with the lighting system through the relay box;

the flight control management computer is in communication connection with a cabin door system, a vertical gyroscope, an atmospheric data system, an optical fiber navigation system, a flap control system, an L-waveband airborne data terminal, a U-waveband airborne data terminal and a brake acquisition system; the L-waveband airborne data terminal is in communication connection with an image encoder; the flight control management computer is connected with an oil heat dissipation air door electric mechanism and a fish scale plate electric mechanism through the relay box in a communication mode.

Preferably, the wheel-load signal trigger system is respectively connected with the left wheel-load proximity switch and the right wheel-load proximity switch through the wheel-load signal trigger system.

Preferably, the lighting system comprises a left navigation light, a right navigation light, a tail navigation light, a cockpit top light, a cargo bay top light and a switch; the left navigation light, the right navigation light and the tail navigation light are respectively connected with the relay box; the cockpit top light and the cargo bay top light are connected with the relay box through the switch.

Preferably, the oil control system includes an oil radiator damper position sensor, an oil pressure sensor, and an oil temperature sensor.

Preferably, the engine acquisition system comprises an engine speed sensor, a vaporization temperature sensor, an intake pressure sensor and a cylinder temperature sensor.

Preferably, the brake acquisition system comprises a left brake pressure sensor, a right brake pressure sensor and a cold air pressure sensor.

Preferably, the door system is connected to the flight control management computer by means of its door microswitch.

Preferably, the atmosphere data system comprises an atmosphere data computer, an atmosphere temperature sensor and a nose airspeed head; the atmospheric temperature sensor and the nose airspeed head are connected with the flight control management computer through an atmospheric data computer.

Preferably, the optical fiber navigation system comprises an optical fiber combination inertial navigation and GNSS anti-interference antenna; the GNSS anti-interference antenna is in communication connection with the flight control management computer through the optical fiber combination inertial navigation.

Preferably, the flap control system comprises a flap system sensor, a limit switch, an upper flap relay box, a lower flap relay box, an upper flap drive motor and a lower flap drive motor; the flap system sensor is in communication connection with the flight control management computer; the upper flap driving motor is connected with the upper flap relay; the lower flap driving motor is connected with a lower flap relay; the upper flap driving motor and the lower flap driving motor are connected with a flight control management computer through limit switches.

The technical scheme of the invention has the following beneficial technical effects:

and the dual-redundancy flight control and management improve the flight safety.

Drawings

Fig. 1 is a schematic structural diagram of an airborne avionics system of a large-scale cargo unmanned aerial vehicle according to the present invention.

Fig. 2 is a detailed diagram of an airborne avionics system of a large-scale cargo unmanned aerial vehicle according to the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.

As shown in fig. 1-2, the onboard avionics system of a large-scale cargo unmanned aerial vehicle provided by the invention comprises a flight control management computer, a wheel-mounted signal trigger system, a flight parameter recorder, an angular rate gyro, a radio altimeter, a magnetic sensor, a fire extinguishing system, a main rudder surface control system, an engine and brake control system, a relay box, an engine starting system, a primary side engine control board, a power distribution control box, a brake acquisition system, a gasoline system, a signal processing unit, a lighting system, a lubricating oil control system and an engine acquisition system;

the flight control management computer is in communication connection with the wheel load signal triggering system and is used for controlling the opening and closing of the wheel load; the flight control management computer is in communication connection with the flight parameter recorder and is used for recording data of the flight control management computer;

the angular rate gyroscope is in communication connection with the flight control management computer and is used for providing an angular speed signal for the navigation system;

the radio altimeter is in communication connection with the flight control management computer and is used for measuring the vertical distance from the airplane to the ground and sending the measured vertical distance to the flight control management computer for data processing; the magnetic sensor, the fire extinguishing system and the main control surface control system are all in communication connection with a flight control management computer;

the engine and the brake control system are in communication connection with the engine and the brake control system and are used for controlling the engine and the brake;

the flight control management computer is respectively connected with the engine starting system and the fire extinguishing system through the relay box; the flight control management computer is respectively in communication connection with the primary side engine control board, the power distribution control box and the signal processing unit;

the signal processing unit is respectively in communication connection with the engine acquisition system and the lubricating oil control system; the signal processing unit is connected with the lighting system through the relay box;

the flight control management computer is in communication connection with a cabin door system, a vertical gyroscope, an atmospheric data system, an optical fiber navigation system, a flap control system, an L-waveband airborne data terminal, a U-waveband airborne data terminal and a brake acquisition system; the L-waveband airborne data terminal is in communication connection with an image encoder; the flight control management computer is connected with an oil heat dissipation air door electric mechanism and a fish scale plate electric mechanism through the relay box in a communication mode.

In an alternative embodiment, the wheel-mounted signal trigger system is connected through a left wheel-mounted proximity switch and a right wheel-mounted proximity switch inside the wheel-mounted signal trigger system respectively.

In an alternative embodiment, the lighting system comprises a left navigation light, a right navigation light, a tail navigation light, a cockpit overhead light, a cargo bay overhead light, and a switch; the left navigation light, the right navigation light and the tail navigation light are respectively connected with the relay box; the cockpit top light and the cargo bay top light are connected with the relay box through the switch.

In an alternative embodiment, the oil control system includes an oil radiator damper position sensor, an oil pressure sensor, and an oil temperature sensor.

In an alternative embodiment, the engine acquisition system comprises an engine speed sensor, a vaporization temperature sensor, an intake pressure sensor, and a cylinder temperature sensor.

In an alternative embodiment, the brake collection system includes a left brake pressure sensor, a right brake pressure sensor, and a cold air pressure sensor.

In an alternative embodiment, the door system is connected to the flight control management computer by its door micro-switches.

In an alternative embodiment, the atmospheric data system comprises an atmospheric data computer, an atmospheric temperature sensor and a nose airspeed head; the atmospheric temperature sensor and the nose airspeed head are connected with the flight control management computer through an atmospheric data computer.

In an optional embodiment, the fiber optic navigation system comprises a fiber optic combined inertial navigation and GNSS anti-jamming antenna; the GNSS anti-interference antenna is in communication connection with the flight control management computer through the optical fiber combination inertial navigation.

In an alternative embodiment, the flap control system comprises a flap system sensor, a limit switch, an upper flap relay box, a lower flap relay box, an upper flap drive motor and a lower flap drive motor; the flap system sensor is in communication connection with the flight control management computer; the upper flap driving motor is connected with the upper flap relay; the lower flap driving motor is connected with a lower flap relay; the upper flap driving motor and the lower flap driving motor are connected with a flight control management computer through limit switches.

It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.