Helicopter emergency flotation system

Abstract

The application provides a helicopter emergency floating system, which comprises an emergency floating switch board 10, a floating control box 20, a gas cylinder system 30, an electromechanical management computer 40, a speed / height detector 50, a main total distance rod float inflation switch 60, a secondary total distance rod float inflation switch 70 and a water immersion sensor 80, wherein the emergency floating switch board 10, the main total distance rod float inflation switch 60 and the secondary total distance rod float inflation switch 70 are connected with the floating control box 20; the floating control box 20 is connected with the gas cylinder system 30, the electromechanical management computer 40, the speed / height detector 50 and the water immersion sensor 80 respectively; the electromechanical management computer 40 is connected with an emergency lifesaving positioning system 401, a key position self-destruction system 402, a rotor brake system 403, an engine 404, a weapon control board 405 and an engine fire extinguishing system 406 respectively; and the weapon control board 405 is connected with a weapon hanging rack 4051 and an inert explosive system 4052.

Description

Technical Field

[0001] This invention belongs to the field of helicopter emergency escape equipment, specifically relating to a helicopter emergency flotation system. Background Technology

[0002] As a multi-purpose transport platform suitable for complex weather conditions, helicopters possess characteristics not found in conventional fixed-wing aircraft, such as vertical takeoff and landing, hovering, and low-altitude or low-speed flight. They are often used as key equipment for short-haul maritime transport, patrol, and search and rescue. With the rapid increase in helicopter maritime missions, flight time, and frequency of use, the probability of malfunctions is also continuously increasing. Due to aerodynamic design limitations, helicopters have relatively poor watertightness. In the event of an emergency landing at sea, the buoyancy provided by the helicopter's body cannot support it to float on the surface for an extended period, preventing the safe escape of crew and passengers. This severely restricts the practicality and safety of helicopters.

[0003] Currently, some scholars have designed and manufactured various types of helicopter emergency flotation systems, which install floats on the outside of the fuselage and provide buoyancy to the helicopter by inflating and deploying them in an emergency.

[0004] However, practical applications have revealed that emergency water landing of helicopters involves the dynamic interconnection of multiple systems. Planned operation of these systems is required when activating the emergency flotation system to ensure stable buoyancy after landing. Currently, there is no effective control method that can comprehensively manage all systems of the helicopter. Summary of the Invention

[0005] This application provides a helicopter emergency flotation system that can effectively coordinate the entire aircraft system.

[0006] Technical solution: A helicopter emergency flotation system, comprising an emergency flotation switch panel 10, a flotation control box 20, an air cylinder system 30, an electromechanical management computer 40, a speed / altitude detector 50, a positive collective pitch rod float inflation switch 60, a negative collective pitch rod float inflation switch 70, and a water immersion sensor 80, wherein:

[0007] Emergency float switch 10, positive collective pitch rod float inflation switch 60, and negative collective pitch rod float inflation switch 70 are all connected to float control box 20; float control box 20 is connected to gas cylinder system 30, electromechanical management computer 40, speed / altitude detector 50, and immersion sensor 80 respectively; electromechanical management computer 40 is connected to emergency rescue positioning system 401, critical component self-destruct system 402, rotor brake system 403, engine 404, weapon control board 405, and engine fire extinguishing system 406 respectively; weapon control board 405 is connected to control weapon rack 4051 and inert powder combustion system 4052 respectively;

[0008] The electromechanical management computer 40 is used to simultaneously control the emergency rescue positioning system 401, the critical component self-destruct system 402, the rotor braking system 403, the engine 404, the weapon control board 405, and the engine fire extinguishing system 406.

[0009] The weapon control panel 405 is used to simultaneously control the weapon mount 4051 and the inert powder combustion system 4052.

[0010] Specifically, in normal startup mode:

[0011] The positive collective pitch rod float inflation switch 60 or the secondary collective pitch rod float inflation switch 70 is used to input a start signal to the float control box 20 within a time of no more than 30ms.

[0012] The float control box 20, upon receiving a start signal, first reads the signal from the speed-altitude detector 50. If the flight altitude data is greater than the altitude threshold, or the flight speed is greater than the speed threshold, to ensure the safety of the helicopter, the float control box 20 reads the data from the speed-altitude detector 50 every 10ms until the altitude data is lower than the altitude threshold and the speed data is lower than the speed threshold, then sends a start signal to the gas cylinder system 30. If the helicopter speed is still greater than the speed threshold after reaching the altitude threshold, a start signal is forcibly sent to the gas cylinder system 30 after a delay of 1000ms. If the float control box 20 cannot read the data from the speed-altitude detector 50, a start signal is forcibly sent to the gas cylinder system 30 after a delay of 500ms.

[0013] After receiving the start signal, the gas cylinder system 30 activates the inflation valve within 50ms, allowing the gas stored in the gas cylinder to be injected into the helicopter's float along a preset pipeline, thus deploying the float to provide buoyancy for the helicopter after it lands on water.

[0014] Specifically, the height threshold ranges from 500 to 700 meters, and the speed threshold ranges from 140 to 160 km / h.

[0015] Specifically, the floating control box 20 is also used to send a start signal to the gas cylinder system 30 during the normal start-up procedure, while simultaneously sending a status signal indicating that the emergency floating system is in normal operation to the electromechanical management computer 40.

[0016] The electromechanical management computer 40, upon receiving a normal start signal from the emergency flotation system, first sends the signal to the black box of the emergency rescue positioning system 401 to record the normal start signal. Within a time of no more than 50ms, it sends a weapon deployment signal in the normal start state of the flotation system to the weapon control board 405. Subsequently, the weapon control board 405 controls the inert powder combustion system 4052 to destroy the powder, and after a delay of 150-200ms, controls the weapon rack 4051 to open the onboard connection mechanism for separation.

[0017] Specifically, the electromechanical management computer 40 is also used to input a normal start signal to the emergency rescue positioning system 401 7000ms-7350ms after the weapon rack 4051 performs the separation mission. The emergency rescue positioning system 401 is then activated and the black box and locator are deployed at the same time to meet the requirements of helicopter flight record retention and personnel rescue positioning.

[0018] Specifically, the electromechanical management computer 40 is also used to send a stop signal to the engine 404 1000ms before the water landing time calculated based on the altitude threshold, shutting down the engine and causing the helicopter to lose power and continue to fall under inertia; after a delay of 450ms-500ms, it sends a braking signal to the rotor braking system 403, which activates the internal mechanism of the rotor braking system 403 to apply damping to the rotor and stop it from rotating; thus preventing the helicopter from flipping over due to water splashing from the rotor after water landing.

[0019] Specifically, in emergency startup mode:

[0020] When the pilot is unable to actively activate the emergency float system via the emergency float switch 10, the main collective pitch rod float inflation switch 60, or the auxiliary collective pitch rod float inflation switch 70, after the helicopter crashes into the water, the water immersion sensor module inside the water immersion sensor 80 will issue an emergency activation signal in response to environmental changes, which will be sent to the float control box 20 within 10ms.

[0021] After receiving the emergency start signal, the floating control box 20 stops reading the signal from the speed and height detector 50, controls the gas cylinder system 30 to inflate the float within 30ms, and sends an emergency start signal to the electromechanical management computer 40 at the same time.

[0022] After receiving the emergency start signal, the electromechanical management computer 40 determines that the helicopter has entered the water. In order to ensure the safety of the helicopter, it is necessary to change the control strategy of each system as follows: The electromechanical management computer 40 simultaneously sends emergency start signals to the emergency rescue positioning system 401, the critical component self-destruct system 402, the rotor braking system 403, the engine 404, the weapon control board 405, and the engine fire suppression system 406.

[0023] Specifically, after receiving the emergency start signal, the emergency rescue positioning system 401 stores the emergency start signal within 50ms and then performs the tasks of black box deployment and locator deployment.

[0024] After receiving the emergency start signal, the critical component self-destruct system 402 executes the self-destruct program on the map and critical data recording box within 50ms.

[0025] Upon receiving an emergency start signal, the rotor braking system 403 immediately activates the damping system to brake the rotor within 50ms.

[0026] After receiving the emergency start signal, the engine 404 immediately disconnects the fuel supply line, cuts off the connection with the APU, and completes the engine shutdown.

[0027] After receiving the emergency start signal, the weapon control board 405 immediately controls the weapon mount 4051 to open the on-board connection mechanism for separation, without operating the inert powder combustion system 4052.

[0028] Upon receiving an emergency start signal, the engine fire suppression system 406 immediately activates the fire extinguishing bottle solenoid valve to release the extinguishing agent, preventing the engine from igniting and exploding due to incomplete closure in emergency water ignition situations.

[0029] Therefore, this application provides a helicopter emergency flotation system and control method. By linking with an electromechanical management computer, it enables orderly control of multiple key helicopter systems, such as the flotation system, engine, rotor system, emergency rescue and positioning system, and weapon system, under different states. This improves the helicopter's safety and reliability when landing on water after the emergency flotation system is activated, creating a greater chance for helicopter pilots and passengers to escape from the water. Attached Figure Description

[0030] Figure 1 This is a structural schematic diagram of a helicopter emergency flotation system provided in this application.

[0031] Among them, 10-Emergency floating switch panel, 20-Floating control box, 30-Gas cylinder system, 40-Electromechanical management computer, 50-Speed / altitude detector, 60-Positive collective pitch rod float inflation switch, 70-Deputy collective pitch rod float inflation switch, 80-Water immersion sensor, 401-Emergency rescue positioning system, 402-Critical component self-destruct system, 403-Rotor brake system, 404-Engine, 405-Weapon control panel, 406-Engine fire extinguishing system, 4051-Weapon rack, 4052-Inert powder combustion and explosion system. Detailed Implementation

[0032] Example 1

[0033] like Figure 1As shown, the helicopter emergency flotation system provided in this application includes an emergency flotation switch panel 10, a flotation control box 20, an air cylinder system 30, an electromechanical management computer 40, a speed / altitude detector 50, a positive collective pitch stick float inflation switch 60, a negative collective pitch stick float inflation switch 70, and a water immersion sensor 80, wherein:

[0034] Emergency float switch 10, positive collective pitch rod float inflation switch 60, and negative collective pitch rod float inflation switch 70 are all connected to float control box 20; float control box 20 is connected to gas cylinder system 30, electromechanical management computer 40, speed / altitude detector 50, and immersion sensor 80 respectively; electromechanical management computer 40 is connected to emergency rescue positioning system 401, critical component self-destruct system 402, rotor brake system 403, engine 404, weapon control board 405, and engine fire extinguishing system 406 respectively; weapon control board 405 is connected to control weapon rack 4051 and inert powder combustion system 4052 respectively.

[0035] Specifically, the electromechanical management computer 40 is used to simultaneously control the emergency rescue positioning system 401, the critical component self-destruct system 402, the rotor braking system 403, the engine 404, the weapon control board 405, and the engine fire extinguishing system 406.

[0036] Specifically, the weapon control panel 405 is used to simultaneously control the weapon mount 4051 and the inert powder combustion system 4052.

[0037] This application provides a helicopter emergency flotation system comprising three modes: normal start, backup start, and emergency start. Specifically, the normal start mode is used when the helicopter needs to perform an emergency water landing mission in the air; the backup start mode is used when the normal start mode fails; and the emergency start mode is used when neither normal start nor backup start has been initiated, and the helicopter has already entered the water.

[0038] The working principle of the helicopter emergency flotation system provided in this application in the normal start-up mode is as follows:

[0039] The positive collective pitch rod float inflation switch 60 or the secondary collective pitch rod float inflation switch 70 is used to input a start signal to the float control box 20 within a time of no more than 30ms.

[0040] The float control box 20, upon receiving a start signal, first reads the signal from the speed-altitude detector 50. If the flight altitude data is greater than the altitude threshold, or the flight speed is greater than the speed threshold, to ensure the safety of the helicopter, the float control box 20 reads the data from the speed-altitude detector 50 every 10ms until the altitude data is lower than the altitude threshold and the speed data is lower than the speed threshold, then sends a start signal to the gas cylinder system 30. If the helicopter speed is still greater than the speed threshold after reaching the altitude threshold, a start signal is forcibly sent to the gas cylinder system 30 after a delay of 1000ms. If the float control box 20 cannot read the data from the speed-altitude detector 50, a start signal is forcibly sent to the gas cylinder system 30 after a delay of 500ms.

[0041] Specifically, the height threshold ranges from 500 to 700 meters, and the speed threshold ranges from 140 to 160 km / h.

[0042] After receiving the start signal, the gas cylinder system 30 activates the inflation valve within 50ms, allowing the gas stored in the gas cylinder to be injected into the helicopter's float along a preset pipeline, thus deploying the float to provide buoyancy for the helicopter after it lands on water.

[0043] The floating control box 20 is also used to send a start signal to the gas cylinder system 30 during the normal start-up procedure, while simultaneously sending a status signal indicating that the emergency floating system is in normal operation to the electromechanical management computer 40.

[0044] The electromechanical management computer 40, upon receiving a normal start signal from the emergency flotation system, first sends the signal to the black box of the emergency rescue positioning system 401 to record the normal start signal. Within a time of no more than 50ms, it sends a weapon deployment signal in the normal start state of the flotation system to the weapon control board 405. Subsequently, the weapon control board 405 controls the inert powder combustion system 4052 to destroy the powder, and after a delay of 150-200ms, controls the weapon rack 4051 to open the onboard connection mechanism for separation.

[0045] The electromechanical management computer 40 is also used to input a normal start signal to the emergency rescue positioning system 401 7000ms-7350ms after the weapon rack 4051 performs the separation mission. The emergency rescue positioning system 401 is then activated and the black box and locator are deployed at the same time to meet the requirements of helicopter flight record retention and personnel rescue positioning.

[0046] The electromechanical management computer 40 is also used to send a stop signal to the engine 404 1000ms before the water-landing time calculated based on the altitude threshold, shutting down the engine and causing the helicopter to lose power and continue falling under inertia; after a delay of 450ms-500ms, it sends a braking signal to the rotor braking system 403, which activates its internal mechanism to apply damping to the rotor and stop its rotation. This prevents the helicopter from tipping over due to water splashing from the rotor after water landing.

[0047] It should be noted that in normal startup mode, the electromechanical management computer 40 does not transmit signals to the critical self-destruct system 402 and the engine fire suppression system 406.

[0048] Preferably, the helicopter emergency flotation system provided in this application operates in backup startup mode as follows:

[0049] If the flotation system does not respond after the operator presses the positive collective pitch float inflation switch 60 or the co-operator presses the auxiliary collective pitch float inflation switch 70, a backup start procedure must be executed. The operator presses the backup button on the emergency flotation switch panel 10, sending a backup start signal to the flotation control box 20 within no more than 30ms.

[0050] After receiving the backup start signal, the float control box 20 operates similarly to the normal start mode. First, it acquires the signal from the speed and altitude detector 50. Once the preset speed and altitude thresholds are met, it activates the gas cylinder system 30 to open the float and controls the electromechanical management computer 40 to control the emergency rescue positioning system 401, rotor brake system 403, engine 404, and weapon control board 405 to perform their respective tasks after a predetermined time delay. The difference lies in that the information archived in the black box of the emergency rescue positioning system 401 is backup start information, providing data for subsequent fault diagnosis.

[0051] Preferably, the working principle of the helicopter emergency flotation system provided in this application in emergency activation mode is as follows:

[0052] When the pilot is unable to actively activate the emergency flotation system via the emergency flotation switch 10, the main collective pitch rod float inflation switch 60, or the auxiliary collective pitch rod float inflation switch 70, after the helicopter crashes into the water, the immersion sensor module inside the immersion sensor 80 will issue an emergency activation signal in response to environmental changes, which will be sent to the flotation control box 20 within 10ms.

[0053] After receiving the emergency start signal, the floating control box 20 stops reading the signal from the speed and height detector 50, controls the gas cylinder system 30 to inflate the float within 30ms, and sends an emergency start signal to the electromechanical management computer 40 at the same time.

[0054] After receiving the emergency start signal, the electromechanical management computer 40 determines that the helicopter has entered the water. In order to ensure the safety of the helicopter, it is necessary to change the control strategy of each system as follows: The electromechanical management computer 40 simultaneously sends emergency start signals to the emergency rescue positioning system 401, the critical component self-destruct system 402, the rotor braking system 403, the engine 404, the weapon control board 405, and the engine fire suppression system 406.

[0055] After receiving the emergency start signal, the emergency rescue positioning system 401 stores the emergency start signal within 50ms and then performs the black box deployment and locator deployment tasks.

[0056] After receiving the emergency start signal, the critical component self-destruct system 402 executes the self-destruct program on the map and critical data recording box within 50ms.

[0057] Upon receiving an emergency start signal, the rotor braking system 403 immediately activates the damping system to brake the rotor within 50ms.

[0058] After receiving the emergency start signal, the engine 404 immediately disconnects the fuel supply line, cuts off the connection with the APU, and completes the engine shutdown.

[0059] After receiving the emergency start signal, the weapon control board 405 immediately controls the weapon mount 4051 to open the on-board connection mechanism for separation, without operating the inert powder combustion system 4052.

[0060] Upon receiving an emergency start signal, the engine fire suppression system 406 immediately activates the fire extinguishing bottle solenoid valve to release the extinguishing agent, preventing the engine from igniting and exploding due to incomplete closure in emergency water ignition situations.

[0061] The key points of this invention are as follows:

[0062] 1. A control method for a helicopter emergency flotation system, comprising three modes: normal start-up, backup start-up, and emergency start-up;

[0063] 2. In normal startup mode, the operation of systems such as weapons, engine, and rotor can be handled more systematically, which not only improves the safety of the pilot in emergency water landing, but also effectively increases the possibility of repairing and reusing the helicopter's various systems after water landing.

[0064] 3. A helicopter emergency flotation system with a built-in speed and altitude detector and an action delay function. It does not operate the gas cylinder and other actuators at high altitudes, which can reduce the adverse effects on maintaining the normal attitude of the helicopter during the emergency landing and improve the success rate of helicopter water landing.

[0065] 4. A helicopter emergency flotation system, which, when activated in normal mode, can more effectively handle explosives, weapons, and engines on board, significantly improving the safety of emergency water landing;

[0066] 5. In normal mode, because the pilot has a higher probability of survival, critical components will not be self-destructed, thus increasing the likelihood of helicopter preservation.

[0067] 6. In emergency situations, it can operate all systems simultaneously in a short period of time to meet the needs of rapid survival under emergency conditions. It also adds self-destruction functions for critical parts and engine fire suppression functions to reduce the possibility of combustion and fire caused by engines that are not shut down in advance and weapons and gunpowder that are not disposed of in advance.

[0068] 7. When the helicopter has a large number of external weapons and the design of the emergency flotation system float is limited, this control method can be used to design the float according to the buoyancy balance requirements, so as to avoid interference with the external weapons when the float is inflated and deployed, which would cause damage to the float.

[0069] In summary, this application provides a control method for a helicopter emergency flotation system. It designs three modes: normal start-up, backup start-up, and emergency start-up. Utilizing the timing delays of actions performed by a flotation control box, speed and altitude detectors, and an electromechanical management computer, it coordinates and plans all systems of the helicopter, controlling them systematically according to different modes. This effectively improves the safety of the helicopter in emergency water landing situations, significantly enhancing its preservation after water landing and the probability of secondary use of each system. Furthermore, it is interconnected with the self-destruct system of critical components to prevent the leakage of secrets after accidental water landing on the battlefield. The control method proposed in this paper is the first to plan and control the entire helicopter system, demonstrating good inventiveness and practicality.

Claims

1. A helicopter emergency flotation system, characterized in that, The helicopter emergency flotation system includes an emergency flotation switch panel (10), a flotation control box (20), an air cylinder system (30), an electromechanical management computer (40), a speed / altitude detector (50), a positive collective pitch rod float inflation switch (60), a negative collective pitch rod float inflation switch (70), and a water immersion sensor (80), wherein: The emergency float switch (10), the positive collective pitch rod float inflation switch (60), and the negative collective pitch rod float inflation switch (70) are all connected to the float control box (20); the float control box (20) is connected to the gas cylinder system (30), the electromechanical management computer (40), the speed / altitude detector (50), and the immersion sensor (80) respectively; the electromechanical management computer (40) is connected to the emergency rescue positioning system (401), the critical component self-destruct system (402), the rotor brake system (403), the engine (404), the weapon control board (405), and the engine fire extinguishing system (406) respectively; the weapon control board (405) is connected to the weapon rack (4051) and the inert powder combustion system (4052) respectively; The electromechanical management computer (40) is used to simultaneously control the emergency rescue positioning system (401), the critical component self-destruct system (402), the rotor braking system (403), the engine (404), the weapon control panel (405), and the engine fire extinguishing system (406). The weapon control panel (405) is used to simultaneously control the weapon rack (4051) and the inert propellant combustion system (4052).

2. The helicopter emergency flotation system according to claim 1, characterized in that, In normal startup mode: A positive collective pitch rod float inflation switch (60) or a negative collective pitch rod float inflation switch (70) is used to input a start signal to the float control box (20) within a time of no more than 30ms. The float control box (20) is used to read the signal from the speed-altitude detector (50) when it receives the start signal. If the flight altitude data is greater than the altitude threshold or the flight speed is greater than the speed threshold, in order to ensure the safety of the helicopter, the float control box (20) reads the data from the speed-altitude detector (50) every 10ms until the altitude data is lower than the altitude threshold and the speed data is lower than the speed threshold, and then sends the start signal to the gas cylinder system (30). If the helicopter speed is still greater than the speed threshold after reaching the altitude threshold, the start signal is forcibly sent to the gas cylinder system (30) after a delay of 1000ms. If the float control box (20) cannot read the data from the speed-altitude detector (50), the start signal is forcibly sent to the gas cylinder system (30) after a delay of 500ms. After receiving the start signal, the gas cylinder system (30) starts the inflation valve within a time of no more than 50ms, so that the gas stored in the gas cylinder is filled into the helicopter's float along the preset pipeline, and the float is deployed to provide buoyancy for the helicopter after landing on water.

3. The helicopter emergency flotation system according to claim 2, characterized in that, The height threshold range is 500-700m, and the speed threshold range is 140-160km / h.

4. The helicopter emergency flotation system according to claim 1, characterized in that, The floating control box (20) is also used to send a start signal to the gas cylinder system (30) during the normal start-up procedure, while simultaneously sending a status signal of normal start-up of the emergency floating system to the electromechanical management computer (40); The electromechanical management computer (40) is used to send the normal start signal of the emergency flotation system to the black box of the emergency rescue positioning system (401) after receiving the normal start signal, record the normal start signal, and send the weapon release signal of the normal start state of the flotation system to the weapon control board (405) within a time of no more than 50ms. Then the weapon control board (405) controls the inert gunpowder combustion system (4052) to destroy the gunpowder, and controls the weapon rack (4051) to open the on-board connection mechanism for separation after a delay of 150-200ms.

5. The helicopter emergency flotation system according to claim 1, characterized in that, The electromechanical management computer (40) is also used to input a normal start signal to the emergency rescue positioning system (401) after the weapon rack (4051) performs the separation task for 7000ms-7350ms. The emergency rescue positioning system (401) is then activated and the black box and locator are deployed at the same time to meet the requirements of helicopter flight record retention and personnel rescue positioning.

6. The helicopter emergency flotation system according to claim 1, characterized in that, The electromechanical management computer (40) is also used to send a stop signal to the engine (404) 1000ms before the water landing time calculated according to the altitude threshold, shut down the engine, and the helicopter loses power and continues to fall under the action of inertia; after a delay of 450ms-500ms, it sends a braking signal to the rotor braking system (403), and the internal mechanism of the rotor braking system (403) is activated to apply damping to the rotor to stop it from rotating; to avoid the rotor splashing water after landing and causing the helicopter to roll over.

7. The helicopter emergency flotation system according to claim 1, characterized in that, In emergency start mode: When the pilot is unable to actively operate the emergency float system to start via the emergency float switch (10), the main collective pitch rod float inflation switch (60) or the auxiliary collective pitch rod float inflation switch (70), after the helicopter falls into the water, the water immersion sensor (80) inside the water immersion sensor will send an emergency start signal to the float control box (20) within 10ms due to the change in environment. After receiving the emergency start signal, the floating control box (20) stops reading the signal from the speed and height detector (50), controls the gas cylinder system (30) to inflate the float within 30ms, and sends an emergency start signal to the electromechanical management computer (40); After receiving the emergency start signal, the electromechanical management computer (40) determines that the helicopter has entered the water. In order to ensure the safety of the helicopter, it is necessary to change the control strategy of each system as follows: The electromechanical management computer (40) simultaneously sends emergency start signals to the emergency rescue positioning system (401), the critical component self-destruct system (402), the rotor braking system (403), the engine (404), the weapon control board (405), and the engine fire extinguishing system (406).

8. The helicopter emergency flotation system according to claim 7, characterized in that, After receiving the emergency start signal, the emergency rescue positioning system (401) stores the emergency start signal within 50ms and then performs the black box deployment and locator deployment tasks. After receiving the emergency start signal, the critical component self-destruct system (402) executes a self-destruct procedure on the map and critical data recording box within 50ms. Upon receiving an emergency start signal, the rotor braking system (403) immediately activates the damping system to brake the rotor within 50ms. After receiving the emergency start signal, the engine (404) immediately disconnects the fuel supply line, cuts off the connection with the APU, and completes the engine shutdown. After receiving the emergency start signal, the weapon control board (405) immediately controls the weapon rack (4051) to open the on-board connection mechanism for separation, without operating the inert gunpowder combustion system (4052); Upon receiving an emergency start signal, the engine fire suppression system (406) immediately activates the solenoid valve of the fire extinguishing bottle to release the fire extinguishing agent, thus preventing the engine from igniting and exploding due to insufficient closure in emergency water ignition situations.

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