CN219096979U

CN219096979U - Aircraft on-board control system, aircraft control system and aircraft

Info

Publication number: CN219096979U
Application number: CN202222619116.6U
Authority: CN
Inventors: 胡华智; 薛鹏
Original assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Current assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date: 2022-09-29
Filing date: 2022-09-29
Publication date: 2023-05-30
Anticipated expiration: 2032-09-29

Abstract

The embodiment of the application discloses an airborne control system of an aircraft, which is used for remotely piloting a manned aircraft through a ground control station, and comprises the following components: a redundant flight control system provided with at least three flight control units, one of the at least three flight control units being provided as a dynamically switchable main control unit during a flight, the flight control units other than the main control unit being provided as dynamically switchable standby control units during the flight; and the cradle head control unit is connected with the redundant flight control system and used for controlling the cradle head to execute actions according to flight control instructions output by the redundant flight control system. The embodiment of the application also discloses a corresponding aircraft control system and an aircraft. The method and the device can ensure that the flight control system can safely and efficiently realize the active-standby switching, and effectively avoid the probability of all faults of the active-standby flight control system.

Description

Aircraft on-board control system, aircraft control system and aircraft

Technical Field

The embodiment of the application relates to the field of aircrafts, in particular to an airborne control system of an aircraft, an airborne control system of the aircraft and the aircraft.

Background

For manned aircraft remotely piloted by ground control stations, it is a fundamental need to ensure safety during their manned flight, in which the aircraft's flight control system must be in a real-time controllable state in any case.

For system safety and reliability, redundant configuration of the aircraft on-board flight control system is necessary. When the flight control system fails or other accidents, the safety and reliability of the manned aircraft can be effectively ensured by switching to the standby flight control system to replace the failure system.

However, the redundancy processing scheme in the prior art is often too simple, only one standby flight control system is used for switching emergency when the main control system has a problem, but even if the standby flight control system still has a possibility of failure, the scheme is difficult to meet the requirements of safety and reliability, and the highest standard of manned aircraft remotely piloted through a ground control station is required.

Disclosure of Invention

The embodiment of the application provides an airborne control system of an aircraft, the airborne control system of the aircraft and the aircraft, so that the flight control system can safely and efficiently realize active-standby switching, and the probability of all faults of the active-standby flight control system is effectively avoided.

In a first aspect, embodiments of the present application provide an aircraft on-board control system for a manned aircraft remotely piloted by a ground control station, comprising:

a redundant flight control system provided with at least three flight control units, one of the at least three flight control units being provided as a dynamically switchable main control unit during a flight, the flight control units other than the main control unit being provided as dynamically switchable standby control units during the flight;

and the cradle head control unit is connected with the redundant flight control system and used for controlling the cradle head to execute actions according to flight control instructions output by the redundant flight control system.

In some possible embodiments, each of the flight control units includes:

the flight data acquisition unit is used for acquiring real-time flight data in the flight process of the aircraft;

the flight data processing unit is used for performing data processing according to the instruction data from the ground control station and the flight data acquired by the flight data acquisition unit and outputting corresponding flight control signals to the cradle head;

the flight data processing unit of the main control unit is in an on state, and the flight data processing units of the standby control units are all set in an off state.

In some possible embodiments, each of the flight control units is provided with at least two flight data acquisition units.

In some possible embodiments, each flight data acquisition unit includes at least one of a gyroscope, an accelerometer, a magnetic compass, a satellite positioning device, and a barometer.

In some possible embodiments, the at least three flight control units are connected by a shared CAN bus.

In some possible embodiments, the CAN bus includes a complete machine CAN bus and the same number of electrically-controlled CAN buses as the spare flight control units.

In some possible embodiments, the device further comprises an environment monitoring control unit connected with the pan-tilt control unit.

In some possible embodiments, the environment monitoring control unit includes an external environment monitoring unit and an internal environment control unit.

In some possible embodiments, the internal environment control unit comprises a cabin light control unit.

In some possible embodiments, the system further comprises a central control display control system connected with the redundant flight control system and the pan-tilt control unit.

In a second aspect, embodiments of the present application provide an aircraft control system comprising a ground control station and an on-board control system as described above.

In a third aspect, embodiments of the present application provide an aircraft comprising an on-board control system as described above.

The beneficial effects of this application are:

according to the redundant flight control system provided with the at least three flight control units, one of the at least three flight control units is set to be the main control unit capable of being dynamically switched in the flight process, and the flight control units except the main control unit are all set to be the standby control units capable of being dynamically switched in the flight process, so that the flight control system can safely and efficiently realize the main and standby switching under any condition, the probability of occurrence of all faults of the main and standby flight control systems is effectively avoided, and the safety and reliability of the manned aircraft are guaranteed.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, a brief description will be given below of the drawings required for the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present application, and that other drawings may be obtained according to these drawings without the need for inventive effort for a person skilled in the art.

Fig. 1 is a schematic structural view of an aircraft on-board control system according to an embodiment of the present application.

Fig. 2 is a schematic structural view of a flight control unit in an aircraft on-board control system according to an embodiment of the present application.

Fig. 3 is a schematic structural view of an aircraft control system according to an embodiment of the present application.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail by way of embodiments with reference to the accompanying drawings in the examples of the present application. Obviously, embodiments and features of embodiments in this application may be combined with each other without conflict.

It should be noted that: in the drawings, like or similar reference numerals refer to like or similar elements throughout or elements having like or similar functions; in the description of the present application, the terms "center," "longitudinal," "transverse," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present application and simplify description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be configured and operated in a particular orientation, and therefore should not be construed as limiting the scope of protection of the present application; in the description of the present application, "first", "second", etc. are used merely for distinguishing one from another, and do not denote their importance or order or the like.

In the description of the present application, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, movably connected, or detachably connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, can be communicated with the inside of two elements, and the like. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.

Referring to fig. 1, an embodiment of the present application provides an airborne control system for a manned aircraft remotely piloted by a ground control station, comprising:

a redundant flight control system 10 provided with at least three flight control units 1, one of which is provided as a dynamically switchable main control unit during a flight, and the flight control units other than the main control unit are provided as dynamically switchable standby control units during the flight;

and the cradle head control unit 2 is connected with the redundant flight control system 10 and is used for controlling the cradle head to execute actions according to flight control instructions output by the redundant flight control system 10.

Referring to fig. 2, in some possible embodiments, each of the flight control units 1 includes:

a flight data acquisition unit 11 for acquiring real-time flight data during the flight of the aircraft;

a flight data processing unit 12, configured to perform data processing according to the instruction data from the ground control station and the flight data collected by the flight data collecting unit, and output a corresponding flight control signal to the pan-tilt;

wherein the flight data processing unit 12 of the main control unit is in an on state, and the flight data processing units 12 of the standby control units are all set in an off state.

In some possible embodiments, each of said flight control units 1 is provided with at least two flight data acquisition units 11.

In some possible embodiments, each flight data acquisition unit 11 includes at least one of a gyroscope, an accelerometer, a magnetic compass, a satellite positioning device, and a barometer.

In some possible embodiments, an environmental monitoring control unit is further included that is connected to the pan-tilt control unit 2.

In some possible embodiments, a central control display control system is further included, which is connected to the redundant flight control system 10 and the pan/tilt control unit 2.

Referring to fig. 3, an embodiment of the present application further provides an aircraft control system including a ground control station 120 and an on-board control system 110 according to any one of the foregoing embodiments.

Embodiments of the present application also provide an aircraft including an on-board control system 110 of any one of the possible embodiments described above.

Those skilled in the art will appreciate that in one or more of the examples described above, the functions described in the embodiments of the present application may be implemented in hardware, software, firmware, or any combination thereof. When implemented in software, these functions may be stored on or transmitted over as one or more instructions or code on a computer-readable medium. Computer-readable media includes both computer storage media and communication media including any medium that facilitates transfer of a computer program from one place to another. A storage media may be any available media that can be accessed by a general purpose or special purpose computer.

Note that the above is only a preferred embodiment of the present application and the technical principle applied. Those skilled in the art will appreciate that the present application is not limited to the particular embodiments described herein, but is capable of numerous obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the present application. Therefore, while the present application has been described in connection with the above embodiments, the present application is not limited to the above embodiments, but may include many other equivalent embodiments without departing from the spirit of the present application, the scope of which is defined by the scope of the appended claims.

Claims

1. An aircraft on-board control system for a manned aircraft remotely piloted by a ground control station, comprising:

2. The aircraft on-board control system of claim 1, wherein each of the flight control units comprises:

3. The aircraft on-board control system of claim 2, wherein: each flight control unit is provided with at least two flight data acquisition units.

4. An aircraft on-board control system according to claim 3, wherein: each flight data acquisition unit comprises at least one of a gyroscope, an accelerometer, a magnetic compass, a satellite positioning device and a barometer.

5. The aircraft on-board control system of claim 4, wherein: the at least three flight control units are connected through a shared CAN bus.

6. The aircraft on-board control system of claim 5, wherein: the CAN bus comprises a complete machine CAN bus and electric control CAN buses with the same quantity as the standby flight control units.

7. The aircraft on-board control system of any of claims 1-6, wherein: the environment monitoring control unit is connected with the cradle head control unit.

8. The aircraft on-board control system of claim 7, wherein: the environment monitoring control unit comprises an external environment monitoring unit and an internal environment control unit.

9. The aircraft on-board control system of claim 8, wherein: the internal environment control unit comprises a cabin light control unit.

10. The aircraft on-board control system of any of claims 1-6, wherein: the system also comprises a central control display control system connected with the redundant flight control system and the cradle head control unit.

11. An aircraft control system, characterized by: comprising a ground control station and an on-board control system according to any of claims 1-9.

12. An aircraft, characterized by: an on-board control system comprising any one of claims 1-9.