CN120096818A - A manned eVTOL cabin emergency landing button control system and method - Google Patents
A manned eVTOL cabin emergency landing button control system and method Download PDFInfo
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- CN120096818A CN120096818A CN202510268224.9A CN202510268224A CN120096818A CN 120096818 A CN120096818 A CN 120096818A CN 202510268224 A CN202510268224 A CN 202510268224A CN 120096818 A CN120096818 A CN 120096818A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
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- A—HUMAN NECESSITIES
- A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
- A61B—DIAGNOSIS; SURGERY; IDENTIFICATION
- A61B5/00—Measuring for diagnostic purposes; Identification of persons
- A61B5/02—Detecting, measuring or recording for evaluating the cardiovascular system, e.g. pulse, heart rate, blood pressure or blood flow
- A61B5/0205—Simultaneously evaluating both cardiovascular conditions and different types of body conditions, e.g. heart and respiratory condition
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- A—HUMAN NECESSITIES
- A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
- A61B—DIAGNOSIS; SURGERY; IDENTIFICATION
- A61B5/00—Measuring for diagnostic purposes; Identification of persons
- A61B5/02—Detecting, measuring or recording for evaluating the cardiovascular system, e.g. pulse, heart rate, blood pressure or blood flow
- A61B5/024—Measuring pulse rate or heart rate
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- A—HUMAN NECESSITIES
- A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
- A61B—DIAGNOSIS; SURGERY; IDENTIFICATION
- A61B5/00—Measuring for diagnostic purposes; Identification of persons
- A61B5/103—Measuring devices for testing the shape, pattern, colour, size or movement of the body or parts thereof, for diagnostic purposes
- A61B5/11—Measuring movement of the entire body or parts thereof, e.g. head or hand tremor or mobility of a limb
- A61B5/1116—Determining posture transitions
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- A—HUMAN NECESSITIES
- A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
- A61B—DIAGNOSIS; SURGERY; IDENTIFICATION
- A61B5/00—Measuring for diagnostic purposes; Identification of persons
- A61B5/145—Measuring characteristics of blood in vivo, e.g. gas concentration or pH-value ; Measuring characteristics of body fluids or tissues, e.g. interstitial fluid or cerebral tissue
- A61B5/14542—Measuring characteristics of blood in vivo, e.g. gas concentration or pH-value ; Measuring characteristics of body fluids or tissues, e.g. interstitial fluid or cerebral tissue for measuring blood gases
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- A—HUMAN NECESSITIES
- A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
- A61B—DIAGNOSIS; SURGERY; IDENTIFICATION
- A61B2503/00—Evaluating a particular growth phase or type of persons or animals
- A61B2503/20—Workers
- A61B2503/22—Motor vehicles operators, e.g. drivers, pilots, captains
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0065—Black boxes, devices automatically broadcasting distress signals
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Abstract
The invention discloses a passenger cabin emergency drop button control system of a manned eVTOL, which comprises an emergency drop button module with a mechanical protective cover, a pilot state monitoring unit, a driving lever state monitoring module, a multistage control logic unit and a flight control system interface, wherein the emergency drop button module needs to be subjected to composite operation and unlocking to prevent false touch, the pilot state monitoring unit detects heart rate, blood oxygen and operation input in real time, the driving lever state monitoring module detects a driving lever displacement signal through a Hall sensor, the multistage control logic unit integrates driving lever priority judgment, voice verification and drop execution functions, and the flight control system interface is communicated with a main flight control based on an ARINC 664 protocol to realize permission switching. Its control logic includes response and observation phase, inquiry phase, start-up phase and execution phase. According to the invention, through the composite unlocking button and the multistage verification logic, the problem of safe takeover when the pilot fails is solved, and the safety and operability of eVTOL emergency landing are obviously improved.
Description
Technical Field
The invention relates to the technical field of passenger cabin control systems of manned eVTOL, in particular to an emergency drop button control system and method for a passenger cabin of a manned eVTOL.
Background
The electric vertical takeoff and landing aircraft eVTOL is more popular in understanding that an aircraft which is motorized and can be taken off and landing vertically without a runway is considered as a subdivision of the future air traffic industry, eVTOL is the hottest track, and attracts to include a batch of initially created technological enterprises, traditional automobiles and aircraft manufacturers.
In order to reduce the cost, the man eVTOL mostly adopts a single-man driving flight mode. However, when the pilot experiences a disabling condition, no co-pilot can take over the manoeuvre of the aircraft, a catastrophic condition for the passengers. When pilots are suddenly disabled (e.g., syncope, sudden illness), the passenger cannot intervene in flight control due to lack of a copilot take over mechanism. Conventional aircraft emergency take-over schemes (such as boeing 787 co-pilot systems) rely on complex authority switching logic and are not suitable for cabin passenger operation. Thus, one mode of intervention for the cabin passengers in such a situation is proposed, namely the addition of a cabin emergency landing button. At the same time, in order to prevent the danger to the flight or the great influence to the control of the aircraft caused by the false touching of the cabin emergency button, a control logic is needed to ensure the safety of the normal flight.
Disclosure of Invention
(One) solving the technical problems
Aiming at the defects of the prior art, the invention solves the problem of safe takeover when the pilot loses energy by compounding the unlocking button and the multi-stage verification logic.
(II) technical scheme
In order to achieve the purpose, the invention provides a passenger cabin emergency drop button control system of a manned eVTOL, which comprises the following technical scheme:
the emergency drop button module with the mechanical protective cover needs to be unlocked by compound operation to prevent false touch;
The pilot state monitoring unit detects heart rate, blood oxygen and operation input in real time;
the driving rod state monitoring module detects a driving rod displacement signal through a Hall sensor;
the multistage control logic unit integrates the functions of judging the priority of the driving rod, verifying the voice and executing the landing;
and the flight control system interface is communicated with the main flight control based on ARINC 664 protocol to realize permission switching.
Preferably, the emergency drop button module comprises:
The button protective cover is required to be rotated 45 degrees clockwise and then is pressed for unlocking, and the red warning lamp is triggered after unlocking;
the pressure sensor generates a trigger signal after the pressing threshold value is more than or equal to 8N for 3 seconds;
and the fingerprint identification unit is used for verifying that the passenger biological information is matched with a preset white list.
Preferably, the pilot status monitoring unit comprises:
The head gesture detection camera analyzes that the pilot sight deviates from the instrument panel angle by more than 30 degrees for 10 seconds through an infrared image;
the bracelet-type physiological sensor generates an disabling signal when the heart rate is monitored for <40 times/min or the blood oxygen is monitored for < 85%.
The control system also comprises a permission isolation subsystem which comprises an emergency drop button module instruction priority lower than the automatic obstacle avoidance instruction of the flight control system and immediate return control right if pilot recovery operation (the displacement of the steering column > threshold value) is detected in the drop process.
A passenger cabin emergency drop button control method of a passenger eVTOL comprises the following steps:
In the response and observation stage, the system monitors the abnormal state of the driver, responds, and passengers in the passenger cabin observe whether the control of the cockpit is abnormal or not;
In the inquiring stage, passenger in passenger cabin inquires pilot, if pilot doesn't respond, the mechanical protecting cover of the emergency drop button is opened, and the emergency drop button is pressed down;
The starting stage, starting an emergency landing program, starting and waiting for 5 seconds, and entering a 5-second countdown real-time monitoring driving rod input;
And in the execution stage, if the displacement of the steering column is > +/-2 degrees, judging that the pilot resumes operation, stopping the flow, and if the steering column is not operated, executing an emergency landing program.
As a preferred scheme, the system also comprises a data black box module which is responsible for recording:
an emergency drop button trigger time stamp (precision 1 ms);
Steering column operation history (sampling frequency 100 Hz);
sensor data and control instructions during landing.
(III) beneficial effects
Compared with the prior art, the invention provides a passenger cabin emergency drop button control system and method for a passenger cabin of a passenger eVTOL, which have the following beneficial effects:
According to the invention, through state monitoring and driving lever state monitoring of a pilot, the abnormality of the cockpit can be monitored in time, the situation of mistaken touch of the button can be prevented by adopting a mode of compositely unlocking the emergency drop button module with the mechanical protective cover, the operation priority of the driving lever is higher than that of the emergency button, the mistaken touch is avoided to interfere with normal flight, and the safety and operability of eVTOL emergency drop are obviously improved.
Drawings
FIG. 1 is a schematic diagram of the control system module structure and function of the present invention;
FIG. 2 is a flow chart of the control system logic and control method of the present invention.
Detailed Description
For a better understanding of the objects, structure and function of the present invention, a system and method for controlling an emergency drop button for a passenger compartment of a passenger eVTOL in accordance with the present invention is described in conjunction with the accompanying drawings and the detailed description.
Example 1
Referring to fig. 1-2, a passenger cabin emergency drop button control system of the present invention for passenger eVTOL includes:
the emergency drop button module with the mechanical protective cover needs to be unlocked by compound operation to prevent false touch;
The pilot state monitoring unit detects heart rate, blood oxygen and operation input in real time;
the driving rod state monitoring module detects a driving rod displacement signal through a Hall sensor;
the multistage control logic unit integrates the functions of judging the priority of the driving rod, verifying the voice and executing the landing;
and the flight control system interface is communicated with the main flight control based on ARINC 664 protocol to realize permission switching.
The present embodiment aims to provide a measure for safety protection based on eVTOL in case of incapacitation of the pilot, including cabin emergency drop buttons, button protection covers and control logic, so as to improve the safety of eVTOL flight.
Specifically, the emergency drop button module in this embodiment includes:
The button protective cover is required to be rotated 45 degrees clockwise and then is pressed for unlocking, and the red warning lamp is triggered after unlocking;
the pressure sensor generates a trigger signal after the pressing threshold value is more than or equal to 8N for 3 seconds;
and the fingerprint identification unit is used for verifying that the passenger biological information is matched with a preset white list.
The mechanical protection cover in the embodiment needs to be unlocked by bidirectional rotation (30 degrees clockwise+60 degrees anticlockwise), so that single false touch is prevented, fingerprint verification or voice confirmation needs to be completed within 5 seconds after triggering, and otherwise, automatic reset is achieved.
Specifically, the pilot status monitoring unit in this embodiment includes:
The head gesture detection camera analyzes that the pilot sight deviates from the instrument panel angle by more than 30 degrees for 10 seconds through an infrared image;
the bracelet-type physiological sensor generates an disabling signal when the heart rate is monitored for <40 times/min or the blood oxygen is monitored for < 85%.
When the pilot suddenly syncs, the biosensor detects that the heart rate suddenly drops to 35 times/min, and the passenger rotates the protective cover and presses the button for a long time, so that the emergency landing program can be started.
Furthermore, the control system of the embodiment also comprises a permission isolation subsystem which comprises an emergency drop button module instruction priority lower than the automatic obstacle avoidance instruction of the flight control system and immediate return control right if pilot recovery operation (the displacement of the steering column > threshold value) is detected in the landing process. The authority isolation in this embodiment is only enabled when the pilot control signal is interrupted and the flight control system is in "emergency mode".
The control system is also provided with a data black box module which is responsible for recording:
an emergency drop button trigger time stamp (precision 1 ms);
Steering column operation history (sampling frequency 100 Hz);
sensor data and control instructions during landing.
Taking urban air traffic (UAM) as an example, the data black box module records the whole process from button triggering to safe landing.
Example 2
Referring to fig. 1-2, the method for controlling the emergency drop button of the passenger cabin of the manned eVTOL comprises the following steps:
In the response and observation stage, the system monitors the abnormal state of the driver, responds, and passengers in the passenger cabin observe whether the control of the cockpit is abnormal or not;
In the inquiring stage, passenger in passenger cabin inquires pilot, if pilot doesn't respond, the mechanical protecting cover of the emergency drop button is opened, and the emergency drop button is pressed down;
The starting stage, starting an emergency landing program, starting and waiting for 5 seconds, and entering a 5-second countdown real-time monitoring driving rod input;
And in the execution stage, if the displacement of the steering column is > +/-2 degrees, judging that the pilot resumes operation, stopping the flow, and if the steering column is not operated, executing an emergency landing program.
Specifically, the logic scheme adopted by the flow in this embodiment is specifically:
Firstly, when the system monitors the abnormal state of a driver, the system responds (such as an alarm), when passengers find that the aircraft flies abnormally (such as abnormal deflection of a course, a route, a gesture and the like), the system communicates with a pilot, if the pilot has a reaction, no measures are needed, if the pilot does not have the reaction, a mechanical protective cover (rotation and pressing) is firstly opened, an emergency landing button is pressed after fingerprint verification is passed, an emergency signal is generated, a multistage control logic unit is connected, after the emergency button is triggered, if the displacement of a steering column is greater than a threshold value (+ -2 DEG) within 5 seconds, steering information is provided for the steering column, the emergency landing button information is ignored, if the steering column is not reacted after 5 seconds, an emergency landing program is triggered, and the emergency landing program is specifically configured according to environmental awareness, for example, in a low-altitude mode (height <100 m), a preset parking apron coordinate with a gradient <3 DEG is preferentially selected, in a high-altitude mode (height is greater than or equal to 500 m), a parachute ejection program is started, and the distress call coordinate is sent. Wherein the emergency landing button reset must be performed during ground maintenance.
The invention adopts a double safety mechanism, namely, the operation priority of the steering column is higher than that of the emergency button, so that the error touch is avoided to interfere with normal flight and a 5 second buffer period is provided for the pilot to resume operation, the safety taking over of flight control when the pilot is disabled is ensured, and meanwhile, unnecessary landing caused by the error touch is avoided.
It will be understood that the application has been described in terms of several embodiments, and that various changes and equivalents may be made to these features and embodiments by those skilled in the art without departing from the spirit and scope of the application. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the application without departing from the essential scope thereof. Therefore, it is intended that the application not be limited to the particular embodiment disclosed, but that the application will include all embodiments falling within the scope of the appended claims.
Claims (6)
1. A passenger cabin emergency drop button control system for a passenger's eVTOL, comprising:
the emergency drop button module with the mechanical protective cover needs to be unlocked by compound operation to prevent false touch;
The pilot state monitoring unit detects heart rate, blood oxygen and operation input in real time;
the driving rod state monitoring module detects a driving rod displacement signal through a Hall sensor;
the multistage control logic unit integrates the functions of judging the priority of the driving rod, verifying the voice and executing the landing;
and the flight control system interface is communicated with the main flight control based on ARINC 664 protocol to realize permission switching.
2. The manned eVTOL cabin emergency drop button control system of claim 1, wherein the emergency drop button module comprises:
The button protective cover is required to be rotated 45 degrees clockwise and then is pressed for unlocking, and the red warning lamp is triggered after unlocking;
the pressure sensor generates a trigger signal after the pressing threshold value is more than or equal to 8N for 3 seconds;
and the fingerprint identification unit is used for verifying that the passenger biological information is matched with a preset white list.
3. The manned eVTOL cabin emergency drop button control system of claim 1, wherein the pilot status monitoring unit includes:
The head gesture detection camera analyzes that the pilot sight deviates from the instrument panel angle by more than 30 degrees for 10 seconds through an infrared image;
the bracelet-type physiological sensor generates an disabling signal when the heart rate is monitored for <40 times/min or the blood oxygen is monitored for < 85%.
4. The manned eVTOL cabin emergency drop button control system of claim 1, further comprising a permission isolation subsystem that includes an emergency drop button module command priority below the flight control system automatic obstacle avoidance command and immediate return of control if pilot recovery (stick displacement > threshold) is detected during landing.
5. A method for controlling an emergency drop button of a passenger cabin of a passenger eVTOL, comprising the control system according to any one of claims 1 to 4, characterized by comprising the following steps:
In the response and observation stage, the system monitors the abnormal state of the driver, responds, and passengers in the passenger cabin observe whether the control of the cockpit is abnormal or not;
In the inquiring stage, passenger in passenger cabin inquires pilot, if pilot doesn't respond, the mechanical protecting cover of the emergency drop button is opened, and the emergency drop button is pressed down;
The starting stage, starting an emergency landing program, starting and waiting for 5 seconds, and entering a 5-second countdown real-time monitoring driving rod input;
And in the execution stage, if the displacement of the steering column is > +/-2 degrees, judging that the pilot resumes operation, stopping the flow, and if the steering column is not operated, executing an emergency landing program.
6. The method for controlling an emergency drop button of a passenger compartment of a passenger eVTOL according to claim 5, further comprising a data black box module for recording:
an emergency drop button trigger time stamp (precision 1 ms);
Steering column operation history (sampling frequency 100 Hz);
sensor data and control instructions during landing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510268224.9A CN120096818A (en) | 2025-03-07 | 2025-03-07 | A manned eVTOL cabin emergency landing button control system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510268224.9A CN120096818A (en) | 2025-03-07 | 2025-03-07 | A manned eVTOL cabin emergency landing button control system and method |
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| Publication Number | Publication Date |
|---|---|
| CN120096818A true CN120096818A (en) | 2025-06-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202510268224.9A Pending CN120096818A (en) | 2025-03-07 | 2025-03-07 | A manned eVTOL cabin emergency landing button control system and method |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0124680D0 (en) * | 2001-10-13 | 2001-12-05 | Central Research Lab Ltd | An aircraft hijack prevention system |
| FR2829864A1 (en) * | 2001-09-17 | 2003-03-21 | M2Ct | ANTI-DIVERSION DEVICE OF AN AIRCRAFT |
| JP2011006224A (en) * | 2009-06-26 | 2011-01-13 | Mitsubishi Electric Corp | Emergency button device of elevator |
| JP2016200974A (en) * | 2015-04-10 | 2016-12-01 | 新潟トランシス株式会社 | Emergency button malfunction preventing cover and emergency button |
| DE102017114782A1 (en) * | 2016-07-04 | 2018-01-04 | Dormakaba Deutschland Gmbh | emergency button |
| CN109131908A (en) * | 2017-06-15 | 2019-01-04 | 极光飞行科学公司 | System and method for executing forced landing and landing |
| CN115309188A (en) * | 2022-09-06 | 2022-11-08 | 上海沃兰特航空技术有限责任公司 | Aircraft control method, system, device, electronic device and storage medium |
| CN117719537A (en) * | 2023-12-29 | 2024-03-19 | 岚图汽车科技有限公司 | Driving assistance methods, devices, equipment and storage media |
-
2025
- 2025-03-07 CN CN202510268224.9A patent/CN120096818A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2829864A1 (en) * | 2001-09-17 | 2003-03-21 | M2Ct | ANTI-DIVERSION DEVICE OF AN AIRCRAFT |
| GB0124680D0 (en) * | 2001-10-13 | 2001-12-05 | Central Research Lab Ltd | An aircraft hijack prevention system |
| JP2011006224A (en) * | 2009-06-26 | 2011-01-13 | Mitsubishi Electric Corp | Emergency button device of elevator |
| JP2016200974A (en) * | 2015-04-10 | 2016-12-01 | 新潟トランシス株式会社 | Emergency button malfunction preventing cover and emergency button |
| DE102017114782A1 (en) * | 2016-07-04 | 2018-01-04 | Dormakaba Deutschland Gmbh | emergency button |
| CN109131908A (en) * | 2017-06-15 | 2019-01-04 | 极光飞行科学公司 | System and method for executing forced landing and landing |
| CN115309188A (en) * | 2022-09-06 | 2022-11-08 | 上海沃兰特航空技术有限责任公司 | Aircraft control method, system, device, electronic device and storage medium |
| CN117719537A (en) * | 2023-12-29 | 2024-03-19 | 岚图汽车科技有限公司 | Driving assistance methods, devices, equipment and storage media |
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