An aircraft landing and taking-off brake integrated verification platform and verification method

Abstract

The application relates to the field of airplane take-off and landing control technology, in particular to an airplane take-off and landing brake integrated verification platform, which comprises a ground system, a wireless communication system and an onboard system, the onboard system performs bidirectional data transmission with the ground system through the wireless communication system; wherein the onboard system is used for generating control instructions according to preset headings, altitudes, speeds and operation instructions input by the ground system, and is used for controlling the power system and the control system of the airplane according to the control instructions; is used for collecting videos of different perspectives, and is used for transmitting feedback signals of the control system and the videos collected by the onboard system to the ground system through the wireless communication system; the ground system is used for remotely controlling the movement of the airplane on the ground according to the videos of different perspectives, remotely operating relevant equipment on the airplane, monitoring the movement track and running state of the airplane and observing the running safety of the airplane through the videos; and the application realizes synchronous verification of brake control, turning and reducing swing control and folding and unfolding control.

Description

Technical Field

[0001] This invention relates to the field of aircraft takeoff and landing control technology, specifically to an integrated verification platform and verification method for aircraft takeoff and landing braking. Background Technology

[0002] In existing aircraft takeoff and landing systems, braking control, turning control, and retraction control are controlled and verified separately, without an integrated verification platform for aircraft takeoff and landing braking.

[0003] Insufficient data exchange between braking control, steering control, and retraction / extension control, along with independent control of each system, can lead to problems such as abnormal aircraft yaw, insufficient steering safety, limited retraction / extension safety redundancy, and limited post-failure handling measures. To establish an integrated takeoff and landing braking environment and ensure the safety of the takeoff and landing braking system, an integrated aircraft takeoff and landing braking verification platform is developed. Summary of the Invention

[0004] To address the issue of independent verification of each takeoff and landing braking system in existing technologies, this invention provides an integrated verification platform and method for aircraft takeoff and landing braking, thereby solving the existing problems.

[0005] The first aspect of the present invention provides an integrated verification platform for aircraft takeoff and landing braking. The device adopts the following technical solution, including: a ground system, a wireless communication system, and an onboard system. The onboard system transmits data bidirectionally to the ground system through the wireless communication system. The onboard system generates control commands based on preset heading, altitude, speed, and operational instructions input from the ground system, and controls the aircraft's power and control systems according to these commands. It also collects video from different perspectives and transmits feedback signals from the control system and the video collected by the onboard system to the ground system via a wireless communication system. The ground system remotely controls the aircraft's movement based on the video from different perspectives, remotely manipulates relevant equipment on the aircraft, monitors the aircraft's trajectory and operating status, and observes the aircraft's operational safety through video.

[0006] A further technical solution of the present invention is that the onboard system includes: The flight control system is used to receive the real-time status of the aircraft, generate control commands based on preset heading, altitude, speed and operation commands input from the ground system, and adjust the real-time status of the aircraft according to the control commands. The control system is used to control the aircraft to brake or turn based on the braking or turning commands output by the flight control system. The video acquisition and transmission system is used to acquire video from different angles of the aircraft and transmit it to the ground system in real time. The onboard power system is used to distribute power to onboard equipment via a power distribution board. And the power system, which provides the aircraft with the power to fly.

[0007] A further technical solution of the present invention is that the onboard system also includes a communication expansion interface module, wherein the flight control system is electrically connected to the control system, the video acquisition and transmission system, and the power system through the communication expansion interface module.

[0008] A further technical solution of the present invention is that the real-time status includes: the aircraft's attitude, heading, altitude, and speed.

[0009] A further technical solution of the present invention is that the ground system includes: The ground-based driver assistance video receiving system is used to receive and decode video captured by the video acquisition and transmission system. The ground station operating system is used to remotely control the aircraft's movement, remotely operate relevant equipment on the aircraft, monitor the aircraft's trajectory and operating status, and observe the aircraft's operational safety through video based on the video decoded by the ground-assisted pilot video receiving system. And a ground power system, used to power the ground station operating system.

[0010] A further technical solution of the present invention is that the ground station operating system includes: a ground station desktop system and a ground station mobile operating system, both of which are used to install and integrate operating equipment, wireless communication equipment, ground station control software, and monitoring and display software.

[0011] A further technical solution of the present invention is that the communication expansion interface module includes: an RS232 bus interface, an RS422 bus interface, an RS485 bus, and a CAN bus interface.

[0012] A further technical solution of the present invention is that the flight control system is electrically connected to the control system, the video acquisition and transmission system, and the power system via an RS232 bus interface or a CAN bus interface.

[0013] The second aspect of this invention provides an integrated verification method for aircraft takeoff and landing braking, which utilizes the integrated verification platform for aircraft takeoff and landing braking of the first aspect of this invention for verification. The verification steps are as follows: The ground station operating system powers on and starts up. To power and fuel the aircraft; Set the braking mode to taxiing mode: after 1 second, set the turning mode to either left turn or right turn; after 5 seconds, set the braking mode to differential braking; after 6 seconds, set it to automatic takeoff mode; after takeoff, set the landing gear retraction control to "retract" command, detect whether the braking system is immediately locked when the retraction command is issued, and detect hydraulic system pressure pulsation. Set the braking operation mode to landing mode: Set the landing gear deployment control to "deploy" command, detect the braking system's response the instant the deployment command is issued, and test the timing coordination verification of landing gear retraction and braking; After the aircraft has fully landed, when the aircraft speed is less than 150 km / h, conduct tests on dry and wet runways respectively, set the turning operation mode to left turn command or right turn command, and set the braking operation mode to differential braking, verify the coupling control logic of nose wheel turning and differential braking, and ensure that "lock-up sideslip" or "oversteer" will not occur; Operational commands are transmitted to the flight control system via a wireless communication system; The power signal is sent to the power system, and the control signal is sent to the control system. The control system will then send feedback to the flight control system. The flight control system sends execution feedback and status information to the ground station operating system via a wireless communication system; the ground station operating system displays the data in real time.

[0014] The beneficial effects of this invention are: This invention provides an integrated verification platform for aircraft takeoff and landing braking. This platform includes the simultaneous verification of braking control, turn yaw reduction control, and retraction control. It is adaptable to the verification needs of various types of takeoff and landing braking systems, provides a unified hardware and software interface, and has good scalability and compatibility. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a system block diagram of an integrated verification platform for aircraft takeoff and landing braking according to the present invention; Figure 2 This is a flowchart of the aircraft takeoff and landing braking integrated verification method of the present invention. Detailed Implementation

[0017] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] An embodiment of the aircraft takeoff and landing braking integrated verification platform of the present invention, such as... Figure 1 As shown, it includes: a ground system, a wireless communication system, and an onboard system. The onboard system transmits data bidirectionally to the ground system via the wireless communication system. The onboard system generates control commands based on preset heading, altitude, speed, and operational instructions input from the ground system, and controls the aircraft's power and control systems according to these commands. It also collects video from different perspectives and transmits feedback signals from the control system and the video collected by the onboard system to the ground system via the wireless communication system. The ground system remotely controls the aircraft's movement based on the video from different perspectives, remotely operates relevant equipment on the aircraft, monitors the aircraft's trajectory and operational status, and observes the aircraft's operational safety through video.

[0019] For example, in one specific embodiment, the onboard system includes: a flight control system, a control system, a video acquisition and transmission system, an onboard power system, and a propulsion system. The flight control system receives the real-time status of the aircraft and generates control commands based on preset heading, altitude, speed, and operation commands input from the ground system, and adjusts the real-time status of the aircraft according to the control commands. The control system controls the aircraft to brake or turn according to braking or turning commands output by the flight control system. The video acquisition and transmission system acquires video from different perspectives of the aircraft and transmits it to the ground system in real time. The onboard power system distributes power to the onboard equipment through a power distribution board. The propulsion system provides flight propulsion for the aircraft. It should be noted that the video acquisition and transmission system includes cameras with at least four perspectives, which acquire video of the environment surrounding the aircraft.

[0020] In this embodiment, the onboard system further includes a communication expansion interface module, wherein the flight control system is electrically connected to the control system, the video acquisition and transmission system, and the power system through the communication expansion interface module.

[0021] In this embodiment, the real-time status includes: the aircraft's attitude, heading, altitude, and speed. The aircraft's attitude and heading are collected via GPS, the aircraft's acceleration and angular velocity are collected via IMU (Inertial Measurement Unit), the altitude is collected via altimeter, and the speed is collected via airspeed meter.

[0022] For example, in one specific embodiment, the ground system includes: a ground-assisted driving video receiving system, a ground station operating system, and a ground power system. The ground-assisted driving video receiving system is used to receive and decode the video acquired by the video acquisition and transmission system. The ground station operating system is used to remotely control the movement of the aircraft on the ground, remotely operate relevant equipment on the aircraft, monitor the aircraft's movement trajectory and operating status, and observe the aircraft's operational safety through video, based on the video decoded by the ground-assisted driving video receiving system. The ground power system is used to redistribute power through a power distribution board and supply power to the ground station operating system.

[0023] In this embodiment, the ground station operating system includes a ground station desktop system and a ground station mobile operating system, both used to install and integrate operating equipment, wireless communication equipment, ground station control software, and monitoring and display software. The ground station desktop system is a Windows laptop platform, and the ground station mobile operating system uses the Android system, which has the advantages of full functionality, high integration, convenient procurement, and strong portability. The ground station software should be compatible with both Windows and Android systems.

[0024] In this embodiment, the communication expansion interface module includes an RS232 bus interface, an RS422 bus interface, an RS485 bus interface, and a CAN bus interface. The communication expansion interface module is used to adapt to different models of power systems to meet compatibility requirements. The flight control system is electrically connected to the control system through the RS232 bus interface or the CAN bus interface, and the video acquisition and transmission system and the power system are electrically connected.

[0025] An integrated verification platform for aircraft takeoff and landing braking is fundamental to solving the problem of multi-system coupling verification, such as... Figure 2 As shown, the verification steps using this platform are as follows: (1) The ground station operating system is powered on and started; (2) Operate the power start / stop button to power on the aircraft; (3) Operate the hydraulic power supply start / stop button to supply fuel to the aircraft; (4) Set the braking working mode to taxiing mode; after 1 second, set the turning working mode to left / right turn command; after 5 seconds, set the braking working mode to differential braking; after 6 seconds, set it to automatic take-off mode; after the aircraft takes off, set the landing gear retraction control to "retraction" command, detect whether the braking system is immediately locked at the moment the retraction command is issued, and detect the pressure pulsation of the hydraulic system. (5) Set the braking working mode to landing mode; set the landing gear lowering control to "lower" command, detect the response of the braking system at the moment the lowering command is issued, and test the timing coordination verification of landing gear retraction and braking; after the aircraft has fully landed, when the aircraft speed is less than 150 km / h, conduct tests on dry and wet runways respectively, set the turning working mode to left / right turning command, set the braking working mode to differential braking, verify the coupling control logic of front wheel turning and differential braking, and ensure that "lock-up sideslip" or "oversteer" will not occur; (6) Operation commands are transmitted to the flight control system via a wireless communication system; (7) The power signal is sent to the power system, and the control signal is sent to the control system; (8) The control system will send feedback to the flight control system; (9) The flight control system sends execution feedback and status information to the ground station operating system via a wireless communication system. The ground station operating system displays data in real time.

[0026] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An integrated verification method for aircraft takeoff and landing braking, characterized in that, The verification was conducted using an integrated verification platform for aircraft takeoff and landing braking. The verification steps were as follows: The ground station operating system powers on and starts up. To power and fuel the aircraft; Set the braking mode to taxiing mode: after 1 second, set the turning mode to left turn or right turn command; after 5 seconds, set the braking mode to differential braking; after 6 seconds, set it to automatic takeoff mode; after takeoff, set the landing gear retraction control to "retract" command, detect whether the braking system is immediately locked at the moment the retraction command is issued, and detect hydraulic system pressure pulsation. Set the braking operation mode to landing mode: Set the landing gear deployment control to "deploy" command, detect the braking system's response the instant the deployment command is issued, and test the timing coordination verification of landing gear retraction and braking; After the aircraft has fully landed, when the aircraft speed is less than 150 km / h, conduct tests on dry and wet runways respectively, set the turning operation mode to left turn command or right turn command, and set the braking operation mode to differential braking, verify the coupling control logic of the nose wheel turning and differential braking, and ensure that "lock-up sideslip" or "oversteer" will not occur; Operational commands are transmitted to the flight control system via a wireless communication system; The power signal is sent to the power system, and the control signal is sent to the control system. The control system will then send feedback to the flight control system. The flight control system will send execution feedback and status information to the ground station operating system via a wireless communication system; Real-time data display from the ground station operating system; The aircraft takeoff, landing, and braking integrated verification platform includes a ground system, a wireless communication system, and an onboard system. The onboard system transmits data bidirectionally to the ground system via the wireless communication system. Specifically, the onboard system generates control commands based on preset heading, altitude, speed, and operational instructions input from the ground system, and controls the aircraft's power and control systems accordingly. It also collects video from different perspectives and transmits feedback signals from the control system and the video collected by the onboard system to the ground system via the wireless communication system. The ground system remotely controls the aircraft's movement based on the video from different perspectives, remotely manipulates relevant equipment on the aircraft, monitors the aircraft's trajectory and operational status, and observes the aircraft's operational safety through video.

2. The integrated verification method for aircraft takeoff and landing braking according to claim 1, characterized in that, The onboard systems include: The flight control system is used to receive the real-time status of the aircraft, generate control commands based on preset heading, altitude, speed and operation commands input from the ground system, and adjust the real-time status of the aircraft according to the control commands. The control system is used to control the aircraft to brake or turn based on the braking or turning commands output by the flight control system. The video acquisition and transmission system is used to acquire video from different angles of the aircraft and transmit it to the ground system in real time. The onboard power system is used to distribute power to onboard equipment via a power distribution board. And the power system, which provides the aircraft with the power to fly.

3. The integrated verification method for aircraft takeoff and landing braking according to claim 2, characterized in that, The onboard system also includes a communication expansion interface module, through which the flight control system is electrically connected to the control system, video acquisition and transmission system, and power system.

4. The integrated verification method for aircraft takeoff and landing braking according to claim 1, characterized in that, Real-time status includes: aircraft attitude, heading, altitude, and speed.

5. The integrated verification method for aircraft takeoff and landing braking according to claim 3, characterized in that, The ground system includes: The ground-based driver assistance video receiving system is used to receive and decode video captured by the video acquisition and transmission system. The ground station operating system is used to remotely control the aircraft's movement, remotely operate relevant equipment on the aircraft, monitor the aircraft's trajectory and operating status, and observe the aircraft's operational safety through video based on the video decoded by the ground-assisted pilot video receiving system. And a ground power system, used to power the ground station operating system.

6. The integrated verification method for aircraft takeoff and landing braking according to claim 5, characterized in that, The ground station operating system includes a ground station desktop system and a ground station mobile operating system, both of which are used to install and integrate operating equipment, wireless communication equipment, ground station control software, and monitoring and display software.

7. The integrated verification method for aircraft takeoff and landing braking according to claim 3, characterized in that, The communication expansion interface module includes: RS232 bus interface, RS422 bus interface, RS485 bus interface and CAN bus interface.

8. The integrated verification method for aircraft takeoff and landing braking according to claim 7, characterized in that, The flight control system is electrically connected to the control system, video acquisition and transmission system, and power system via an RS232 bus interface or a CAN bus interface.

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