Manned eVTOL passenger cabin emergency landing button control system and method

Abstract

The invention discloses a manned eVTOL passenger cabin emergency landing button control system, which comprises an emergency landing button module with a mechanical protection cover, which needs to be unlocked by composite operation to prevent mistaken touch; the pilot state monitoring unit is used for detecting heart rate, blood oxygen and operation input in real time; the steering column state monitoring module is used for detecting a steering column displacement signal through a Hall sensor; the multi-stage control logic unit integrates the functions of priority judgment, voice verification and landing execution of the steering column; and the flight control system interface communicates with a main flight controller based on an ARINC 664 protocol to realize permission switching. The control logic comprises a response and observation stage, an inquiry stage, a starting stage and an execution stage. Through the composite unlocking button and the multi-stage verification logic, the problem of safe takeover when a pilot is disabled is solved, and the safety and operability of eVTOL emergency landing are remarkably improved.

Description

Technical Field

[0001] The present invention relates to the technical field of manned eVTOL cabin control systems, and in particular to a manned eVTOL cabin emergency landing button control system and method. Background Art

[0002] A more common understanding of electric vertical take-off and landing aircraft eVTOL is an electric aircraft that can take off and land vertically without a runway. As a sub-sector of the future air transportation industry, eVTOL is the hottest track, attracting a number of start-up technology companies, traditional automobile and aircraft manufacturers to participate.

[0003] In order to reduce costs, manned eVTOLs mostly adopt a single-pilot flight mode. However, when the pilot becomes incapacitated, there is no co-pilot to take over the control of the aircraft, which is a catastrophic state for the passengers. When the pilot suddenly becomes incapacitated (such as fainting, sudden illness), there is no co-pilot takeover mechanism, and passengers cannot intervene in flight control. The emergency takeover scheme of traditional aircraft (such as the Boeing 787 co-pilot system) relies on complex authority switching logic and is not suitable for cabin passenger operation. Therefore, an intervention mode for cabin passengers in this situation is proposed, that is, to add an emergency landing button to the cabin. At the same time, in order to prevent the accidental touch of the cabin emergency button from causing danger to the flight or a significant impact on the control of the aircraft, a control logic is required to ensure the safety of normal flight. Summary of the invention

[0004] 1. Technical issues to be solved

[0005] In view of the deficiencies of the prior art, the present invention solves the problem of safe takeover when the pilot is incapacitated by using a composite unlocking button and multi-level verification logic.

[0006] (II) Technical solution

[0007] To achieve the above object, the present invention provides the following technical solution: a manned eVTOL cabin emergency landing button control system, comprising:

[0008] The emergency landing button module with a mechanical protection cover requires a combination of operations to unlock to prevent accidental touches;

[0009] Pilot status monitoring unit, real-time detection of heart rate, blood oxygen and operation input;

[0010] The steering column status monitoring module detects the steering column displacement signal through the Hall sensor;

[0011] Multi-level control logic unit, integrating joystick priority judgment, voice verification and landing execution functions;

[0012] The flight control system interface communicates with the main flight control based on the ARINC 664 protocol to achieve permission switching.

[0013] As a preferred solution, the emergency landing button module comprises:

[0014] The button protection cover needs to be rotated 45° clockwise and then pressed to unlock. After unlocking, the red warning light will be triggered;

[0015] Pressure sensor, pressing threshold ≥ 8N, generates a trigger signal after 3 seconds;

[0016] Fingerprint recognition unit verifies that the passenger's biometric information matches the preset whitelist.

[0017] As a preferred solution, the pilot status monitoring unit includes:

[0018] Head posture detection camera, through infrared image analysis, the pilot's line of sight deviates from the instrument panel by more than 30° for 10 seconds;

[0019] The wristband physiological sensor generates a disability signal when the monitored heart rate is less than 40 beats / minute or the blood oxygen is less than 85%.

[0020] As a preferred solution, the control system also includes an authority isolation mechanism subsystem, which includes: the emergency landing button module command priority is lower than the flight control system automatic obstacle avoidance command and if the pilot resumes operation (control stick displacement > threshold) during landing, control is immediately returned.

[0021] A manned eVTOL cabin emergency landing button control method includes the following process:

[0022] In the response and observation phase, the system detects the abnormal state of the pilot and responds, and the cabin passengers observe whether there is any abnormality in the cockpit control;

[0023] During the inquiry phase, the cabin passengers ask the pilot. If the pilot does not respond, the mechanical protective cover of the emergency landing button is opened and the emergency landing button is pressed;

[0024] During the startup phase, start the emergency landing procedure, start and wait for 5 seconds, enter a 5-second countdown to monitor the joystick input in real time;

[0025] During the execution phase, if the joystick displacement is greater than ±2°, it is determined that the pilot has resumed operation and the process is terminated; if there is no operation on the joystick, the emergency landing procedure is executed.

[0026] As a preferred solution, the system also includes a data black box module, which is responsible for recording:

[0027] Emergency landing button trigger timestamp (accuracy 1ms);

[0028] Joystick operation history (sampling frequency 100Hz);

[0029] Sensor data and control commands during landing.

[0030] (III) Beneficial effects

[0031] Compared with the prior art, the present invention provides a manned eVTOL cabin emergency landing button control system and method, which has the following beneficial effects:

[0032] The present invention can timely monitor cockpit abnormalities by monitoring the pilot's status and the joystick status, and can prevent accidental button touching by adopting a composite unlocking method of the emergency landing button module with a mechanical protection cover. The joystick operation has a higher priority than the emergency button, avoiding accidental touching that interferes with normal flight, and significantly improving the safety and operability of eVTOL emergency landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a schematic diagram of the module structure and function of the control system of the present invention;

[0034] Figure 2 It is a schematic diagram of the control system logic and control method flow of the present invention. DETAILED DESCRIPTION

[0035] In order to better understand the purpose, structure and function of the present invention, a manned eVTOL cabin emergency landing button control system and method of the present invention will be further described in conjunction with the accompanying drawings and specific embodiments.

[0036] Example 1

[0037] refer to Figure 1-2 The present invention provides a manned eVTOL cabin emergency landing button control system, comprising:

[0038] The emergency landing button module with a mechanical protection cover requires a combination of operations to unlock to prevent accidental touches;

[0039] Pilot status monitoring unit, real-time detection of heart rate, blood oxygen and operation input;

[0040] The steering column status monitoring module detects the steering column displacement signal through the Hall sensor;

[0041] Multi-level control logic unit, integrating joystick priority judgment, voice verification and landing execution functions;

[0042] The flight control system interface communicates with the main flight control based on the ARINC 664 protocol to achieve permission switching.

[0043] This embodiment aims to propose a measure for safety protection based on eVTOL in the event of pilot incapacitation, including a cabin emergency landing button, a button protection cover, and control logic, to improve the safety of eVTOL flight.

[0044] Specifically, the emergency landing button module in this embodiment includes:

[0045] The button protection cover needs to be rotated 45° clockwise and then pressed to unlock. After unlocking, the red warning light will be triggered;

[0046] Pressure sensor, pressing threshold ≥ 8N, generates a trigger signal after 3 seconds;

[0047] Fingerprint recognition unit verifies that the passenger's biometric information matches the preset whitelist.

[0048] The mechanical protective cover in this embodiment needs to be rotated bidirectionally (30° clockwise + 60° counterclockwise) to unlock to prevent a single accidental touch. After being triggered, fingerprint verification or voice confirmation must be completed within 5 seconds, otherwise it will automatically reset.

[0049] Specifically, the pilot status monitoring unit in this embodiment includes:

[0050] Head posture detection camera, through infrared image analysis, the pilot's line of sight deviates from the instrument panel by more than 30° for 10 seconds;

[0051] The wristband physiological sensor generates a disability signal when the monitored heart rate is less than 40 beats / minute or the blood oxygen is less than 85%.

[0052] When the pilot suddenly faints, the biosensor detects that the heart rate drops sharply to 35 beats per minute. The passenger can start the emergency landing procedure by rotating the protective cover and pressing and holding the button.

[0053] Furthermore, the control system of this embodiment also includes an authority isolation mechanism subsystem, which includes: the emergency landing button module command priority is lower than the automatic obstacle avoidance command of the flight control system and if the pilot recovery operation (control stick displacement > threshold) is detected during landing, the control right is immediately returned. The authority isolation in this embodiment is that the button command takes effect only when the pilot control signal is interrupted and the flight control system is in "emergency mode".

[0054] The control system also has a data black box module, which is responsible for recording:

[0055] Emergency landing button trigger timestamp (accuracy 1ms);

[0056] Joystick operation history (sampling frequency 100Hz);

[0057] Sensor data and control commands during landing.

[0058] Taking the urban air traffic (UAM) scenario as an example, the data black box module records the entire process from button triggering to safe landing.

[0059] Example 2

[0060] refer to Figure 1-2 The present invention provides a method for controlling an emergency landing button in a manned eVTOL cabin, comprising the following steps:

[0061] In the response and observation phase, the system detects the abnormal state of the pilot and responds, and the cabin passengers observe whether there is any abnormality in the cockpit control;

[0062] During the inquiry phase, the cabin passengers ask the pilot. If the pilot does not respond, the mechanical protective cover of the emergency landing button is opened and the emergency landing button is pressed;

[0063] During the startup phase, start the emergency landing procedure, start and wait for 5 seconds, enter a 5-second countdown to monitor the joystick input in real time;

[0064] During the execution phase, if the joystick displacement is greater than ±2°, it is determined that the pilot has resumed operation and the process is terminated; if there is no operation on the joystick, the emergency landing procedure is executed.

[0065] Specifically, the logic scheme adopted by the process in this embodiment is as follows:

[0066] First, when the system detects an abnormal state of the driver, it will respond (such as an alarm). When the passenger finds that the aircraft is flying abnormally (such as abnormal deflection of heading, route, attitude, etc.), he will communicate with the pilot. If the pilot responds at this time, no measures need to be taken; if the pilot does not respond, first open the mechanical protection cover (rotate + press), and after the fingerprint verification is passed, press the emergency landing button to generate an emergency signal; at this time, the multi-level control logic unit is connected. After the emergency button is triggered, if the displacement of the joystick within 5 seconds is greater than the threshold (±2°), the joystick has control information, and the emergency landing button information is ignored; if the joystick does not respond after 5 seconds, the emergency landing procedure is triggered. This can be configured according to environmental perception. For example, in low-altitude mode (altitude <100 meters), the preset apron coordinates with a slope of <3° are preferred. In high-altitude mode (altitude ≥500 meters), the parachute ejection procedure is started and the distress coordinates are sent. Among them, the reset of the emergency landing button must be performed during ground maintenance.

[0067] The present invention adopts a dual safety mechanism, namely, the joystick operation has a higher priority than the emergency button to avoid accidental touches interfering with normal flight, and a 5-second buffer period provides a time window for the pilot to resume operation, ensuring safe takeover of flight control when the pilot is incapacitated, while avoiding unnecessary landings caused by accidental touches.

[0068] It is to be understood that the present invention is described by some embodiments, and it is known to those skilled in the art that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention. In addition, under the teachings of the present invention, these features and embodiments may be modified to adapt to specific circumstances and materials without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the scope of protection of the present invention.

Claims

1. A manned eVTOL cabin emergency landing button control system, characterized in that: include: The emergency landing button module with a mechanical protection cover requires a combination of operations to unlock to prevent accidental touches; Pilot status monitoring unit, real-time detection of heart rate, blood oxygen and operation input; The steering column status monitoring module detects the steering column displacement signal through the Hall sensor; Multi-level control logic unit, integrating joystick priority judgment, voice verification and landing execution functions; The flight control system interface communicates with the main flight control based on the ARINC 664 protocol to achieve permission switching.

2. A manned eVTOL cabin emergency landing button control system according to claim 1, characterized in that: The emergency landing button module comprises: The button protection cover needs to be rotated 45° clockwise and then pressed to unlock. After unlocking, the red warning light will be triggered; Pressure sensor, pressing threshold ≥ 8N, generates a trigger signal after 3 seconds; Fingerprint recognition unit verifies that the passenger's biometric information matches the preset whitelist.

3. A manned eVTOL cabin emergency landing button control system according to claim 1, characterized in that: The pilot status monitoring unit comprises: Head posture detection camera, through infrared image analysis, the pilot's line of sight deviates from the instrument panel by more than 30° for 10 seconds; The wristband physiological sensor generates a disability signal when the monitored heart rate is less than 40 beats / minute or the blood oxygen is less than 85%.

4. A manned eVTOL cabin emergency landing button control system according to claim 1, characterized in that ,The control system also includes an authority isolation mechanism subsystem, which includes: the emergency landing button module command priority is lower than the ,automatic obstacle avoidance command of the flight control system and if the pilot recovery operation (the ,displacement of the joystick > the threshold) is detected during the landing process, the control right will be ,returned immediately.

5. A method for controlling an emergency landing button in a manned eVTOL cabin, comprising a control system as claimed in any one of claims 1 to 4, characterized in that , including the following processes: In the response and observation phase, the system detects the abnormal state of the pilot and responds, and the cabin passengers observe whether there is any abnormality in the cockpit control; During the inquiry phase, the cabin passengers ask the pilot. If the pilot does not respond, the mechanical protective cover of the emergency landing button is opened and the emergency landing button is pressed; During the startup phase, start the emergency landing procedure, start and wait for 5 seconds, enter a 5-second countdown to monitor the joystick input in real time; During the execution phase, if the joystick displacement is greater than ±2°, it is determined that the pilot has resumed operation and the process is terminated; if there is no operation on the joystick, the emergency landing procedure is executed.

6. According to a manned eVTOL cabin emergency landing button control method according to claim 5, it is characterized in that: It also includes a data black box module, which is responsible for recording: Emergency landing button trigger timestamp (accuracy 1ms); Joystick operation history (sampling frequency 100Hz); Sensor data and control commands during landing.

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