Multi-mode cooperative emergency protection system and method for personal aircraft

Abstract

The invention discloses a multi-mode cooperative emergency protection system and method for a personal aircraft, and relates to the technical field of personal safety protection, the multi-mode cooperative emergency protection system comprises an integrated protection garment body, an intelligent sensing and control unit and a multi-mode execution mechanism; the intelligent sensing and control unit and the multi-mode executing mechanism are both integrated on the integrated protective clothing body; the intelligent sensing and control unit is used for sensing and judging whether passengers and the personal aircraft are in an uncontrollable falling state or not in real time, a feasible escape solution is provided for the extreme working condition of low-altitude and short-time falling of the personal aircraft for the first time, effective speed reduction and posture stabilization are achieved within second-level time through the rapid inflation brake parachute, and the safety of the passengers is improved. The technical bottleneck that a traditional ejection umbrella is ineffective is overcome.

Description

Technical Field

[0001] This invention relates to the field of personal safety protection technology, specifically to a multi-mode collaborative emergency protection system and method for personal aircraft. Background Technology

[0002] Personal aerial vehicles (PAVs) typically refer to low-altitude flight devices operated by a single person and powered by a small motor, such as jetpacks, electric skateboards, and single-person helicopters. They are emerging vehicles under the concept of urban air mobility. However, their unique operating mode—usually flying at high speeds at low altitudes below 150 meters—brings unprecedented safety challenges: in the event of mechanical failure, power loss, or control error, the reaction time from loss of control to crash is extremely short, often only a few seconds.

[0003] Existing technologies, such as ejection parachutes used in traditional aircraft, are completely ineffective under the extreme conditions of "low altitude, short duration" because they require an altitude of hundreds of meters to fully deploy and effectively brake. Airbags, borrowed from the automotive industry, are primarily designed for horizontal collisions and cannot effectively cope with the enormous vertical impact forces generated by high-altitude falls. Furthermore, they only trigger at the moment of impact, providing neither sufficient nor timely protection. In addition, many existing safety concepts rely on single protection mechanisms with extremely low fault tolerance; failure of such a mechanism can have catastrophic consequences. Moreover, most solutions fail to deeply integrate with the aircraft's real-time status data, lacking intelligent emergency decision-making capabilities.

[0004] To address the shortcomings of existing technologies and provide personal aircraft occupants with an emergency system capable of adapting to low-altitude, short-term fall conditions, and possessing intelligent judgment and multi-level collaborative protection capabilities, thereby significantly improving the survival probability of occupants in fatal fall accidents, a multi-mode collaborative emergency protection system and method for personal aircraft was designed for use. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention provides a multi-mode collaborative emergency protection system and method for personal aircraft, solving the technical problems mentioned in the background section.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a multi-mode collaborative emergency protection system for personal aircraft, comprising: an integrated protective suit body, an intelligent sensing and control unit, and a multi-mode actuator; The intelligent sensing and control unit and the multi-mode actuator are both integrated on the integrated protective suit body; The intelligent sensing and control unit is used to sense and determine in real time whether the occupants and personal aircraft are in an uncontrollable crash state. The multi-mode actuator is used to perform multi-level protection actions according to a preset timing sequence when triggered by the intelligent sensing and control unit. The multi-level protection actions include at least a first-level deceleration, a second-level buffer, and a third-level energy absorption.

[0007] Preferably, the intelligent sensing and control unit includes: A multi-source state sensor is used to collect environmental and state data. The multi-source state sensor includes at least an inertial measurement unit, an altimeter, and a GPS module. The aircraft data interface is used to receive fault status signals from personal aircraft; The main control chip, which is communicatively connected to the multi-source status sensor and the aircraft data interface, is configured to run an intelligent crash determination algorithm. Based on the environmental and status data and the fault status signal, it determines whether the uncontrollable crash state has been entered and generates a corresponding trigger command.

[0008] Preferably, the main control chip is configured to determine that it has entered the uncontrollable fall state when the following conditions are met simultaneously: A sharp drop in altitude was detected, and the acceleration of descent exceeded a first preset threshold. The flight attitude angular velocity was detected to exceed a second preset threshold; and, The aircraft data interface receives fault status signals that characterize power failure or control failure.

[0009] Preferably, the multi-mode execution mechanism includes a primary execution mechanism, a secondary execution mechanism, and a tertiary execution mechanism; The primary actuator is a rapid-inflation deceleration parachute, which is located on the back of the integrated protective suit body. It is configured to first deploy the guide parachute after receiving the first trigger command, and then pull out and inflate the parachute canopy with high-pressure gas within 0.5 seconds to generate air resistance for initial deceleration and attitude stabilization. The secondary actuator is a full-body airbag, with its airbag units distributed in key areas of the integrated protective suit body, including the chest, back, hips, and knees. It is configured to activate after a delay and fully inflate upon receiving a second trigger command to form a buffer layer that envelops the occupant before impact. The third-level actuator is an active energy-absorbing structure, integrated into the key stress areas of the spine and hip of the integrated protective suit. The active energy-absorbing structure adopts a non-Newtonian fluid pad or a collapsible structure and is configured to passively absorb and disperse impact energy when subjected to high-speed impact.

[0010] Preferably, the actions of the primary, secondary, and tertiary actuators are triggered according to a preset multi-level timing control logic: An alarm signal is issued at T+0 seconds after the system confirms that it has entered an emergency state; At time T+0.1, the first-level actuator is triggered; At time T+0.5, if it is determined that an impact is unavoidable based on the updated height and speed data, the secondary actuator is triggered. At the moment of impact, the third-level actuator responds passively.

[0011] Preferably, the canopy of the rapid-inflating deceleration parachute is conical or wing-shaped.

[0012] Preferably, the airbag units of the whole-body airbag are connected through internal air passages and are supplied with air by one or more central inflation devices.

[0013] Preferably, the method, applied to the system as described in any one of claims 1-7, comprises: The status of the occupants and personal aircraft is monitored in real time through intelligent sensing and control units. When the system determines that an uncontrollable fall has occurred based on multi-source information, a trigger command is automatically generated. According to the preset multi-level timing control logic, the first-level, second-level and third-level actuators in the multi-mode actuators are triggered in sequence to perform multi-level coordinated protection of deceleration, buffering and energy absorption.

[0014] Preferably, the determination of entering an uncontrollable fall state includes: Comprehensive analysis of altitude, acceleration, and attitude angular velocity data from multiple state sensors, as well as fault status signals from the personal aircraft; When the following conditions are met simultaneously: a rapid drop in altitude and acceleration exceeding a set threshold, abnormal attitude angular velocity, and receipt of a power failure or control failure signal, an uncontrollable fall state is determined.

[0015] Preferably, the sequentially triggered multi-mode actuator includes: First, the rapid-inflating deceleration parachute located on the back of the protective suit is immediately deployed to perform initial deceleration and attitude stabilization; Subsequently, after a predetermined delay following the deployment of the deceleration parachute, the distributed full-body airbags are inflated to form a buffer layer. Finally, at the moment of impact, the energy is passively absorbed by the active energy-absorbing structure in the critical stress area of ​​the protective suit. Beneficial effects

[0016] This invention provides a multi-mode collaborative emergency protection system and method for personal aircraft. Through an integrated "perception-decision-execution" and multi-mode collaborative design of "deceleration-buffering-energy absorption," this invention achieves significant benefits: For the first time, it provides a feasible escape solution for extreme situations involving low-altitude, short-duration crashes of personal aircraft. The rapid-inflating deceleration parachute achieves effective deceleration and attitude stabilization within seconds, overcoming the technical bottleneck of the ineffectiveness of traditional ejection parachutes. The system achieves progressive and efficient absorption of the impact kinetic energy through a three-stage energy dissipation mechanism: the deceleration parachute first consumes most of the kinetic energy, then the full-body airbags buffer the impact force, and finally, the active energy-absorbing structure protects critical body parts. Its comprehensive protection effect far surpasses any single method, and its multi-level redundancy design provides higher system reliability and fault tolerance. Intelligent judgment and automatic triggering throughout the process ensure instantaneous and precise activation of the protection system in emergency situations where occupants are panicked, greatly improving the probability of survival. Simultaneously, the system is highly integrated into everyday wearable protective clothing, perfectly balancing comfort in non-emergency situations with ultimate reliability in emergency situations. Attached Figure Description

[0017] Figure 1 This is a flowchart illustrating the overall structure and workflow of the system of the present invention.

[0018] Figure 2 This is a timing diagram of the emergency protection process of the present invention.

[0019] Figure 3 This is a timing diagram of the emergency protection process of the present invention. Detailed Implementation

[0020] 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.

[0021] Please see Figure 1-3 The present invention provides a technical solution: a multi-mode collaborative emergency protection system for personal aircraft, comprising: an integrated protective suit body, an intelligent sensing and control unit, and a multi-mode actuator; The intelligent sensing and control unit and the multi-mode actuator are both integrated on the integrated protective suit body; The intelligent sensing and control unit is used to sense and determine in real time whether the occupants and personal aircraft are in an uncontrollable crash state. The multi-mode actuator is used to perform multi-level protection actions according to a preset timing sequence when triggered by the intelligent sensing and control unit. The multi-level protection actions include at least a first-level deceleration, a second-level buffer, and a third-level energy absorption.

[0022] In this embodiment, the intelligent sensing and control unit includes: A multi-source state sensor is used to collect environmental and state data. The multi-source state sensor includes at least an inertial measurement unit, an altimeter, and a GPS module. The aircraft data interface is used to receive fault status signals from personal aircraft; The main control chip, which is communicatively connected to the multi-source status sensor and the aircraft data interface, is configured to run an intelligent crash determination algorithm. Based on the environmental and status data and the fault status signal, it determines whether the uncontrollable crash state has been entered and generates a corresponding trigger command.

[0023] In this embodiment, the main control chip is further configured to determine that it has entered the uncontrollable fall state when the following conditions are met simultaneously: A sharp drop in altitude was detected, and the acceleration of descent exceeded a first preset threshold. The flight attitude angular velocity was detected to exceed a second preset threshold; and, The aircraft data interface receives fault status signals that characterize power failure or control failure.

[0024] In this embodiment, the multi-mode actuator is further configured to include a primary actuator, a secondary actuator, and a tertiary actuator; The primary actuator is a rapid-inflation deceleration parachute, which is located on the back of the integrated protective suit body. It is configured to first deploy the guide parachute after receiving the first trigger command, and then pull out and inflate the parachute canopy with high-pressure gas within 0.5 seconds to generate air resistance for initial deceleration and attitude stabilization. The secondary actuator is a full-body airbag, with its airbag units distributed in key areas of the integrated protective suit body, including the chest, back, hips, and knees. It is configured to activate after a delay and fully inflate upon receiving a second trigger command to form a buffer layer that envelops the occupant before impact. The third-level actuator is an active energy-absorbing structure, integrated into the key stress areas of the spine and hip of the integrated protective suit. The active energy-absorbing structure adopts a non-Newtonian fluid pad or a collapsible structure and is configured to passively absorb and disperse impact energy when subjected to high-speed impact.

[0025] In this embodiment, the actions of the primary actuator, secondary actuator, and tertiary actuator are triggered according to a preset multi-level timing control logic: An alarm signal is issued at T+0 seconds after the system confirms that it has entered an emergency state; At time T+0.1, the first-level actuator is triggered; At time T+0.5, if it is determined that an impact is unavoidable based on the updated height and speed data, the secondary actuator is triggered. At the moment of impact, the third-level actuator responds passively.

[0026] In this embodiment, the canopy of the rapid-inflating deceleration parachute is further configured to be conical or wing-shaped.

[0027] In this embodiment, the airbag units of the whole-body airbag are connected through internal air passages and are supplied with air by one or more central inflation devices.

[0028] This embodiment is further configured to be applied to the system as described in any one of claims 1-7, wherein the method includes: The status of the occupants and personal aircraft is monitored in real time through intelligent sensing and control units. When the system determines that an uncontrollable fall has occurred based on multi-source information, a trigger command is automatically generated. According to the preset multi-level timing control logic, the first-level, second-level and third-level actuators in the multi-mode actuators are triggered in sequence to perform multi-level coordinated protection of deceleration, buffering and energy absorption.

[0029] In this embodiment, the determination of entering an uncontrollable fall state includes: Comprehensive analysis of altitude, acceleration, and attitude angular velocity data from multiple state sensors, as well as fault status signals from the personal aircraft; When the following conditions are met simultaneously: a rapid drop in altitude and acceleration exceeding a set threshold, abnormal attitude angular velocity, and receipt of a power failure or control failure signal, an uncontrollable fall state is determined.

[0030] This embodiment is further configured such that the sequential triggering of the multi-mode execution mechanism includes: First, the rapid-inflating deceleration parachute located on the back of the protective suit is immediately deployed to perform initial deceleration and attitude stabilization; Subsequently, after a predetermined delay following the deployment of the deceleration parachute, the distributed full-body airbags are inflated to form a buffer layer. Finally, at the moment of impact, the energy is passively absorbed by the active energy-absorbing structure in the critical stress area of ​​the protective suit.

[0031] Its detailed connection method is a well-known technology in this field. The following mainly introduces the working principle and process, and the specific work is as follows.

[0032] Example: The system is specifically integrated into a vest-style protective suit designed for flight crew members. This suit utilizes high-strength, abrasion-resistant fabric and flexible joints to ensure comfort and freedom of movement during daily wear. The core intelligent sensing and control unit is embedded in the back lining of the vest as a circuit board integrating a microprocessor (MCU). This MCU is pre-installed with the aforementioned intelligent fall detection algorithm. Multi-source status sensors include a nine-axis IMU (integrating a gyroscope and accelerometer) and a digital barometric altimeter. These communicate with the main control MCU via an I2C bus, acquiring real-time data on the crew's attitude, acceleration, and altitude at a frequency of 100Hz. Simultaneously, the system establishes a connection with the aircraft's flight control system via a wireless Bluetooth module as the aircraft's data interface, continuously monitoring specific signals indicating power loss or serious mechanical failure, such as "sudden battery depletion" or "motor failure." When the main control MCU determines, through comprehensive analysis of the algorithm, that the current state simultaneously meets the following conditions: the height drops by more than 20 meters within 0.5 seconds, the combined acceleration exceeds 4G (pointing towards the ground), the attitude angular velocity is continuously abnormal (such as roll angular velocity > 180 degrees / second), and a "power failure" signal is received, the system immediately confirms that it has entered the "uncontrollable fall" emergency state.

[0033] Upon determining the emergency situation, the system immediately activates multi-level timing control logic. First, at T+0 seconds, a rapid buzzer alarm is emitted via bone conduction headphones connected to the helmet to warn the occupant. Immediately following, at T+0.1 seconds, a trigger command is sent to the primary actuator located on the back of the vest—the rapid-inflation deceleration parachute. This mechanism consists of a pop-out device with a built-in compressed carbon dioxide cylinder. Upon triggering, a small guide parachute is first deployed using a small amount of gunpowder or spring mechanical energy. Under the action of airflow, the guide parachute rapidly pulls the canopy out of the main parachute pack. Almost simultaneously, high-pressure carbon dioxide gas inflates the canopy (in this embodiment, a circular conical parachute with good drag characteristics) into a rigid aerodynamic structure within 0.3 seconds through a conduit, generating significant air resistance. This reduces the occupant's descent speed from an initial over 70 km / h to approximately 40 km / h within 1.5 seconds, effectively suppressing body roll and creating a stable posture and longer buffer time for subsequent protection.

[0034] After the parachute deploys, the system continuously monitors altitude and speed. When the altimeter reading is below 50 meters and the speed is still above the preset safe landing threshold, the main control MCU determines that an impact is unavoidable at approximately T+0.6 seconds and immediately triggers the secondary actuator—the full-body airbag system. This airbag system consists of multiple airbag units distributed across the front chest, back, hips, and outer thighs of the vest. These units are connected by internal flexible air passages and are supplied with gas by a central solid chemical generator. Upon triggering, the generator produces a large amount of harmless nitrogen gas within 0.2 seconds, causing all airbag units to rapidly inflate, forming a complete buffer layer that almost completely covers the occupant's torso and hips. This process is completed approximately 100-200 milliseconds before the occupant hits the ground, ensuring optimal impact protection. Finally, at the moment of impact, the third-level actuator—a non-Newtonian fluid liner (composed of shear-thickening fluid STF material encapsulated in a flexible bladder) integrated into the spine and hip lining of the protective suit—passively comes into play. Upon high-speed impact, the liner material rapidly transforms from a soft state to a high-stiffness state within milliseconds, efficiently absorbing and dispersing impact energy through its own "stiffening" effect, minimizing the risk of injury to the occupant's spine and pelvis. The entire system, from detection to execution, is fully automated, providing unprecedented, redundant, intelligent life support for low-altitude personal flights.

[0035] It should be noted that in this paper, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

Claims

1. A multi-mode coordinated emergency protection system for a personal aerial vehicle, characterized in that, The integrated protective clothing body, the intelligent sensing and control unit and the multi-mode execution mechanism are included. The intelligent sensing and control unit and the multi-mode execution mechanism are integrated on the integrated protective clothing body. The intelligent sensing and control unit is used for sensing and judging in real time whether the occupant and the personal aircraft are in an uncontrollable falling state. The multi-mode execution mechanism is used for executing multi-stage protection actions according to a preset time sequence under the triggering of the intelligent sensing and control unit, and the multi-stage protection actions at least include one-stage deceleration, two-stage buffering and three-stage energy absorption. The intelligent sensing and control unit includes:

2. A multi-mode coordinated emergency protection system for a personal aerial vehicle according to claim 1, characterized in that A multi-source state sensor is used for collecting environment and state data, and the multi-source state sensor at least includes an inertial measurement unit, an altimeter and a GPS module. An aircraft data interface is used for receiving a failure state signal from the personal aircraft. A main control chip is in communication connection with the multi-source state sensor and the aircraft data interface, and is configured to run an intelligent falling judgment algorithm, judge whether to enter the uncontrollable falling state based on the environment and state data and the failure state signal, and generate a corresponding triggering instruction. The main control chip is configured to judge to enter the uncontrollable falling state when the following conditions are met at the same time:

3. A multi-mode coordinated emergency protection system for a personal aerial vehicle according to claim 1, characterized in that A height value is detected to sharply drop and a drop acceleration exceeds a first preset threshold value; A flight attitude angular velocity is detected to exceed a second preset threshold value; and A failure state signal representing power failure or control failure is received through the aircraft data interface. The multi-mode execution mechanism includes a one-stage execution mechanism, a two-stage execution mechanism and a three-stage execution mechanism.

4. A multi-mode synergistic emergency protection system for a personal aerial vehicle according to claim 1, characterized in that The one-stage execution mechanism is a rapid inflation deceleration parachute, which is arranged on the back of the integrated protective clothing body, and is configured to first pop out a guide parachute and then pull out and inflate a canopy by using high-pressure gas within 0.5 seconds to generate air resistance for preliminary deceleration and attitude stabilization after receiving a first triggering instruction. The two-stage execution mechanism is a full-body safety airbag, and airbag units of the two-stage execution mechanism are distributedly arranged in key areas of the front chest, back, hip and knee of the integrated protective clothing body, and are configured to start and fully inflate to form a buffer layer wrapping the occupant before hitting the ground after receiving a second triggering instruction. The three-stage execution mechanism is an active energy absorption structure, which is integrated in key stress areas of the spine and hip of the integrated protective clothing body, and adopts a non-Newtonian fluid gasket or a collapsible structure, and is configured to passively absorb and disperse impact energy when subjected to high-speed impact. The action triggering of the one-stage execution mechanism, the two-stage execution mechanism and the three-stage execution mechanism follows a preset multi-stage time sequence control logic:

5. A multi-mode synergistic emergency protection system for a personal aerial vehicle according to claim 1, characterized in that An alarm signal is sent at T+0 seconds when the system confirms to enter an emergency state; The one-stage execution mechanism is triggered at T+0.1 seconds; The two-stage execution mechanism is triggered based on updated height and speed data when it is judged that the impact is inevitable at T+0.5 seconds; The three-stage execution mechanism is passively responded at the moment of impact. The canopy shape of the rapid inflation deceleration parachute is conical or wing-shaped.

6. A multi-mode coordinated emergency protection system for a personal aerial vehicle according to claim 4, characterized in that ​ 7. A multi-mode synergic emergency protection system for a personal aerial vehicle according to claim 4, characterized in that The airbag units of the full-body airbag are connected by internal air channels and are supplied with air by one or more central inflation devices.

8. A multi-mode synergistic emergency protection method for a personal aerial vehicle according to claim 1, characterized in that The method is applied to the system of any one of claims 1-7, and the method comprises: Real-time monitoring of the state of the occupant and the personal aircraft by the intelligent sensing and control unit; Automatically generating a trigger instruction when it is determined that an uncontrollable falling state is entered based on multi-source information; According to a preset multi-stage timing control logic, a first-stage execution mechanism, a second-stage execution mechanism, and a third-stage execution mechanism in the multi-mode execution mechanism are sequentially triggered to execute multi-stage coordinated protection of deceleration, buffering, and energy absorption.

9. A multi-mode synergistic emergency protection method for a personal aerial vehicle according to claim 8, wherein, The determination of the uncontrollable falling state comprises: Comprehensive analysis of height data, acceleration data, and attitude angular velocity data from multi-source state sensors, and a failure state signal from the personal aircraft; When the height sharply decreases, the acceleration exceeds a set threshold, the attitude angular velocity is abnormal, and the power failure or control failure signal is received simultaneously, the uncontrollable falling state is determined.

10. A multi-mode synergistic emergency protection method for a personal aerial vehicle according to claim 8, wherein, The sequential triggering of the multi-mode execution mechanism comprises: First, a rapid inflation deceleration parachute located on the back of the protective clothing is immediately triggered to expand, and preliminary deceleration and attitude stabilization are performed; Subsequently, after a predetermined delay after the deceleration parachute is expanded, a distributed full-body airbag is triggered to inflate, forming a buffer layer; Finally, at the moment of impact, the active energy absorption structure of the key stress area of the protective clothing passively absorbs the final impact energy.

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