Aircraft fire extinguishing agent auxiliary gasification system and method

Abstract

The invention discloses an airplane fire extinguishing agent auxiliary gasification system and method, and belongs to the technical field of airplane fire safety. The system comprises a heating resistance wire, a preheated gas inlet pipe network, a fire extinguishing agent storage tank heating pipeline and a fire extinguishing agent preheating automatic control module. The fire extinguishing agent preheating automatic control module can control the electric heating or high-temperature gas heating mode of the fire extinguishing agent according to the flight state of an aircraft, so that the temperature of the fire extinguishing agent can be kept within the set range close to the boiling point of the fire extinguishing agent in the take-off stage and the cruising stage with high fire occurrence and under the conditions that an engine accidentally stops rotating and the like. Quick gasification and efficient chemical fire extinguishing effects can be realized in case of sudden fire hazards; the device is applied to preheating and auxiliary gasification of the airborne high-boiling-point fire extinguishing agent, and the gasification efficiency and the fire extinguishing effect of the airborne high-boiling-point fire extinguishing agent can be improved.

Description

Technical Field

[0001] The invention belongs to the field of aircraft manufacturing technology and aircraft fire safety, and relates to an aircraft fire extinguishing agent auxiliary gasification system and method. Background Art

[0002] Aircraft fire accidents have a very high mortality rate, causing serious casualties and huge economic losses. According to statistics, the ascent and descent phases of aircraft are the phases where fires frequently occur, accounting for as high as 23% of the total number of aircraft fire accidents, the number of aircraft fire accidents during the cruising and parking phases accounts for 12%, the number of aircraft fire accidents during the taxiing phase accounts for 6%, and the rest are aircraft fires caused by collisions. The fire extinguishing system on the aircraft is a key component to ensure flight safety. Once an aircraft fire occurs, the onboard fire extinguishing system needs to release a large amount of fire extinguishing agent in a very short time to quickly reach an effective fire extinguishing concentration to control the spread of the fire. At present, the "halon" chemical gas fire extinguishing agent commonly equipped on aircraft is being phased out due to its ozone destructiveness, and it is expected to be completely decommissioned by 2040. At present, regional "halon" replacement strategies have begun to be adopted on aircraft, such as using HFC-227ea to replace "halon" 1301 in the bathroom, and using 2-BTP to replace "halon" 1211 in portable fire extinguishers. However, for the fixed pipe network fire extinguishing systems installed in key fire-prone areas such as engine compartments and cargo holds, an effective and environmentally friendly chemical gas fire extinguishing agent has not yet been developed to replace "halon".

[0003] Although researchers have tried to use fine water mist or ultrafine dry powder fire extinguishing technology, it is necessary to install dense water or fire extinguishing powder on the aircraft as the fire extinguishing medium, which is not conducive to the lightweight design of the aircraft, and the fire extinguishing performance of the two is significantly lower than that of chemical gas fire extinguishing agents. At present, the new chemical fire extinguishing agents that have been studied in depth and are considered to have the potential to replace "halon" include trifluoroiodomethane (boiling point of -22.5℃), 2-BTP (boiling point of 32℃) and perfluorohexanone (Novec-1230, boiling point of 49℃). However, since their boiling points are significantly higher than Halon 1301 (the boiling point is -57.8℃), they are in liquid form at room temperature and are difficult to vaporize in the transportation pipeline of the fire extinguishing system. They are mainly released into the fire extinguishing space through the nozzle in liquid form. The diffusion efficiency and diffusion concentration of the extinguishing agent droplets in the fire extinguishing space are lower than those of the gaseous Halon fire extinguishing agent. They need to be heated and vaporized before they can further undergo thermal cracking reactions to release chemical extinguishing free radicals and achieve excellent chemical fire extinguishing effects by capturing flame free radicals to interrupt the combustion chain reaction. Therefore, it is necessary to design a supporting fire extinguishing system for this type of high-boiling point fire extinguishing agent that can effectively promote its vaporization and give full play to its efficient chemical fire extinguishing function, and effectively promote the airborne "halon" replacement application of this type of high-boiling point new chemical fire extinguishing agent.

[0004] CN111589020A discloses a perfluorohexanone rapid fire extinguishing device and fire extinguishing system, which includes a perfluorohexanone injection assembly, a CO2 generating device, a water mist generating device, a mixing chamber and a nozzle. The invention uses perfluorohexanone, CO2 and water mist to synergistically extinguish fires to achieve rapid fire extinguishing. It is mainly used in building fire protection systems, and the fire extinguishing system needs to carry multiple fire extinguishing media and multiple storage tanks at the same time, which will significantly increase the load of the aircraft and cannot be used as an aircraft "halon" replacement fire extinguishing system.

[0005] CN111991733A relates to a gas-liquid dual-fluid mixed atomization fire extinguishing device and a fire extinguishing method. The device includes a fire extinguishing medium storage unit, a power output unit, a control unit, a delivery pipeline and an atomization unit, and an operation parameter monitoring unit. The dual-fluid fire extinguishing medium of the invention includes a high-boiling point gas fire extinguishing agent and water. The fire is extinguished after being fully atomized by gas-liquid mixing. The fire extinguishing efficiency is high and the method is clean and environmentally friendly. However, the method is mainly used in confined spaces such as energy storage power stations and underground pipe galleries. The operating environment and airworthiness requirements of key aircraft cabins are not considered, and the method is not suitable for civil aircraft cabins.

[0006] In order to design a fire extinguishing system suitable for the new "halon" alternative to chemical fire extinguishing agents and ensure the gasification efficiency of high-boiling point fire extinguishing agents, we can try to design auxiliary gasification technology in the fire extinguishing system to enable the fire extinguishing agent to reach an appropriate gasification state in the fire extinguishing system pipeline before being released from the nozzle, thereby improving its diffusion efficiency in the fire extinguishing space, promoting its rapid thermal decomposition and releasing high-efficiency chemical fire extinguishing free radicals, so that a high-efficiency fire extinguishing effect can be exerted with a lower fire extinguishing agent filling mass, effectively promoting the airborne "halon" replacement process and aircraft lightweight and energy-saving design. Summary of the invention

[0007] In view of this, the present invention provides an aircraft fire extinguishing agent auxiliary gasification system and method, which are used to at least solve some of the technical problems in the background technology.

[0008] In order to achieve the above object, the present invention adopts the following technical solution:

[0009] On one hand, the present invention discloses an aircraft fire extinguishing agent auxiliary gasification system, including a preheating gas intake pipe network, a first storage tank heating pipe, a first storage tank heating resistance wire, a second storage tank heating pipe, a second storage tank heating resistance wire and a fire extinguishing agent preheating automatic control module;

[0010] The first tank heating pipe is tightly wound around the outer wall of the first fire extinguishing agent tank; the second tank heating pipe is tightly wound around the outer wall of the second fire extinguishing agent tank;

[0011] The preheating gas inlet pipe network is connected to the first tank heating pipe and the second tank heating pipe at the same time, and is used to input the high-temperature gas generated by the aircraft engine into the first tank heating pipe and the second tank heating pipe respectively, so as to realize the high-temperature gas heating of the fire extinguishing agent in the first fire extinguishing agent tank and the second fire extinguishing agent tank;

[0012] The first tank heating resistance wire and the second tank heating resistance wire are respectively placed at the lower half of the inner walls of the two tanks, and are used to electrically heat the fire extinguishing agent inside the first fire extinguishing agent tank and the second fire extinguishing agent tank respectively;

[0013] The fire extinguishing agent preheating automatic control module is used to control the electric heating or high-temperature gas heating mode of the fire extinguishing agent according to the flight status of the aircraft.

[0014] Preferably, the first fire extinguishing agent storage tank is a high-speed release fire extinguishing agent storage bottle for quickly releasing the fire extinguishing agent; and the second fire extinguishing agent storage tank is a low-speed release fire extinguishing agent storage bottle for releasing the fire extinguishing agent to prevent the flame from reigniting.

[0015] Preferably, the fire extinguishing agents placed inside the first fire extinguishing agent storage tank and the second fire extinguishing agent storage tank are both high-boiling point fire extinguishing agents, including 2-BTP or perfluorohexanone.

[0016] Preferably, the preheated gas intake pipe network includes a preheated gas heating pipeline, a preheated gas delivery solenoid valve and a preheated gas delivery pipeline;

[0017] Among them, the preheating gas heating pipeline is used to generate high-temperature gas using the aircraft engine, and the preheating gas delivery solenoid valve is used to input the generated high-temperature gas into the preheating gas delivery pipeline according to the control signal output by the fire extinguishing agent preheating automatic control module; the preheating gas delivery pipeline is simultaneously connected to the first storage tank heating pipeline and the second storage tank heating pipeline.

[0018] Preferably, the preheated gas heating pipe is arranged on the outer wall of the engine combustion chamber, and the high temperature generated by the combustion in the aircraft engine combustion chamber is used to heat the air entering the preheated gas heating pipe to generate high-temperature gas.

[0019] Preferably, the first tank heating pipe, the second tank heating pipe, the outer wall of the first fire extinguishing agent tank, and the outer wall of the second fire extinguishing agent tank are all made of heat-conducting materials.

[0020] Preferably, the outer sides of the first storage tank heating pipe and the second storage tank heating pipe are both wrapped with an outer insulation layer.

[0021] Preferably, the outer wall of the first fire extinguishing agent storage tank and the outer wall of the second fire extinguishing agent storage tank are both wrapped with a layer of heat conductive film.

[0022] Preferably, the first fire extinguishing agent storage tank and the second fire extinguishing agent storage tank are also provided with a pressure sensor for detecting the internal pressure.

[0023] Preferably, the fire extinguishing agent preheating automatic control module controls the electric heating or high-temperature gas heating mode of the fire extinguishing agent according to the flight state of the aircraft, specifically including the following steps:

[0024] When the aircraft is in the take-off state or the aircraft engine stops unexpectedly, the fire extinguishing agent preheating automatic control module is used to start the heating switches of the first tank heating resistor wire and the second tank heating resistor wire to realize the electric heating of the fire extinguishing agent in the tank;

[0025] When the aircraft is in a stable flight state, the fire extinguishing agent preheating automatic control module is used to close the heating switches of the first tank heating resistor wire and the second tank heating resistor wire; at the same time, the preheating gas delivery electromagnetic valve of the hot gas intake pipe network is opened by the preheating fire extinguishing agent preheating automatic control module to realize high-temperature gas heating of the fire extinguishing agent in the tank.

[0026] Another aspect of the present invention also discloses a method for assisting gasification of aircraft fire extinguishing agents, comprising the following steps:

[0027] When the aircraft is in take-off state or the aircraft engine stops unexpectedly, the fire extinguishing agent in the tank is electrically heated by the heating resistance wire inside the fire extinguishing agent storage tank;

[0028] When the aircraft is in a stable flight state, the electric heating is turned off and the high-temperature gas of the fire extinguishing agent in the fire extinguishing agent tank is heated by using the tank heating pipe wrapped around the outer wall of the fire extinguishing agent tank.

[0029] It can be seen from the above technical solutions that, compared with the prior art, the present invention discloses an aircraft fire extinguishing agent auxiliary gasification system and method, which has the following beneficial effects:

[0030] 1. The present invention provides an aircraft fire extinguishing agent auxiliary gasification system and method. When the aircraft enters the take-off stage where fires are more likely to occur, the high-boiling point fire extinguishing agent in the fire extinguishing system can be electrically heated to a temperature suitable for its rapid gasification. After the aircraft engine is operating normally, the high-temperature outer wall of the engine combustion chamber is effectively used as a high-temperature heat source to heat the engine bleed air and the high-temperature gas is used to heat the fire extinguishing agent to save aircraft energy consumption. In addition, in order to deal with unexpected situations such as engine failure and shutdown during operation, the high-temperature gas heating mode can be switched to the electric heating mode to continue to maintain the temperature of the fire extinguishing agent.

[0031] 2. The aircraft fire extinguishing agent auxiliary gasification system of the present invention can heat the fire extinguishing agent in the high-boiling point fire extinguishing agent storage tank to a temperature range close to its boiling point by means of electric heating or high-temperature gas heating, thereby facilitating the fire extinguishing effect of the high-boiling point fire extinguishing agent in the airborne fire extinguishing system pipeline network, improving its diffusion efficiency in the fire extinguishing space after being released through the nozzle and the release of high-efficiency chemical fire extinguishing free radicals, thereby ensuring that the chemical fire extinguishing agent fully exerts its fire extinguishing effect, and to a certain extent reducing the filling mass of the airborne fire extinguishing agent, which is beneficial to the lightweight design of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0033] Figure 1 The present invention is a structural schematic diagram of an aircraft fire extinguishing agent auxiliary gasification system.

[0034] Figure 2 The invention is a cross-sectional schematic diagram of the assembly of a preheating gas heating pipeline of an aircraft fire extinguishing agent auxiliary gasification system inside an engine.

[0035] Figure 3 The present invention is a top view schematic diagram of the assembly of a preheating gas heating pipeline of an aircraft fire extinguishing agent auxiliary gasification system inside an engine.

[0036] Figure 4 The present invention is a schematic diagram of the operation flow of an aircraft fire extinguishing agent auxiliary gasification system and method.

[0037] Legend: 1—preheating gas intake network, 2—first storage tank heating pipeline, 3—second storage tank heating pipeline, 4—external insulation layer, 5—engine turbine outer wall, 6—engine turbine, 7—engine outer duct, 101—preheating gas heating pipeline, 102—preheating gas delivery solenoid valve, 103—preheating gas delivery pipeline, 104—preheating gas inlet, 105—preheating gas outlet, 201, 301—temperature sensor, 202, 302—pressure sensor, 203—first storage tank heating resistor, 303—second storage tank heating resistor. DETAILED DESCRIPTION

[0038] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0039] Example 1

[0040] like Figure 1 As shown, embodiment 1 of the present invention provides an aircraft fire extinguishing agent auxiliary gasification system, which includes a preheating gas intake pipe network 1, a first storage tank heating pipe 2, a first storage tank heating resistor 203, a second storage tank heating pipe 3, a second storage tank heating resistor 303, a storage tank external insulation layer 4, and a fire extinguishing agent preheating automatic control module; the fire extinguishing agent preheating automatic control module is used to control the electric heating or high-temperature gas heating mode of the fire extinguishing agent according to the flight state of the aircraft, automatically realize the switching of the two preheating modes of electric heating or high-temperature gas heating of the high-boiling point fire extinguishing agent, and control the preheating gas delivery electromagnetic valve 102 or the heating resistors 203, 303 to start electric heating, so as to achieve the purpose of preheating the fire extinguishing agent in the fire extinguishing agent storage tank.

[0041] Specifically, the fire extinguishing agent preheating automatic control module controls the electric heating or high-temperature gas heating mode of the fire extinguishing agent according to the flight state of the aircraft, specifically including, when the aircraft is in the take-off state or the aircraft engine is unexpectedly stopped, using the fire extinguishing agent preheating automatic control module to start the heating switches of the first tank heating resistor wire 203 and the second tank heating resistor wire 303 to realize the electric heating of the fire extinguishing agent in the tank;

[0042] When the aircraft is in a stable flight state, the fire extinguishing agent preheating automatic control module is used to turn off the heating switches of the first tank heating resistor 203 and the second tank heating resistor 303; at the same time, the preheating gas delivery electromagnetic valve of the hot gas inlet pipe network 1 is opened by the preheating fire extinguishing agent preheating automatic control module to realize high-temperature gas heating of the fire extinguishing agent in the tank.

[0043] Furthermore, the thermal insulation layer 4 provided on the outside of the storage tank also plays a certain role in the thermal insulation of the subsequent fire extinguishing agent storage tank.

[0044] The preheated gas inlet network 1 is connected to the first tank heating pipe 2 and the second tank heating pipe 3 at the same time, and is used to transport the heated high-temperature gas; the first tank heating pipe 2 is tightly wound around the outer wall of the first fire extinguishing agent tank; the second tank heating pipe 3 is tightly wound around the outer wall of the second fire extinguishing agent tank; the first tank heating resistance wire 203 and the second tank heating resistance wire 303 are respectively placed in the lower half of the inner walls of the two tanks.

[0045] In an embodiment of the present invention, the heating resistor wire is led out from the aircraft auxiliary power unit compartment to the fire extinguishing agent storage tank, and the power supply of the heating resistor wire is located in the aircraft auxiliary power unit compartment (APU, Auxiliary power unit), which provides electricity such as lighting for the aircraft to ensure lighting and air conditioning in the cabin and cockpit.

[0046] Furthermore, the preheating gas intake network includes a preheating gas heating pipeline 101, a preheating gas delivery solenoid valve 102 and a preheating gas delivery pipeline 103; wherein the preheating gas heating pipeline 101 is used to generate high-temperature gas, and the preheating gas delivery solenoid valve 102 is used to input the generated high-temperature gas into the preheating gas delivery pipeline 103 according to the control signal output by the fire extinguishing agent preheating automatic control module; the preheating gas delivery pipeline 103 is simultaneously connected to the first storage tank heating pipeline 2 and the second storage tank heating pipeline 3.

[0047] Further, in the embodiment of the present invention, the first fire extinguishing agent storage tank is configured as a low-speed release fire extinguishing agent storage bottle ( Figure 1 On the left side), after the high-speed bottle releases the fire extinguishing agent into the fire area and suppresses the fire, the low-speed bottle must continue to spray for a period of time to prevent the flame from reigniting; the second fire extinguishing agent storage tank is set as a high-speed release fire extinguishing agent storage bottle for rapid release of fire extinguishing agent ( Figure 1 On the right side), the second extinguishing agent storage tank can quickly release the extinguishing agent to the fire area when a fire occurs.

[0048] Furthermore, in an embodiment of the present invention, the high temperature gas is generated by the aircraft engine itself, such as Figure 2 , Figure 3 As shown, the preheating gas heating pipeline 101 is located inside the engine duct 7, close to the engine turbine outer wall 5 of the engine turbine 6; in this embodiment, the preheating gas heating pipeline 101 placed inside the duct is set as an S-shaped pipeline on the outer wall close to the combustion chamber; this design enables the gas entering the pipeline to make full use of the heat released by the combustion chamber, and quickly heats the gas in the pipe through heat conduction to reach the required high temperature. This process not only effectively increases the thermal energy of the gas, but also provides the necessary heat source for the subsequent preheating of the fire extinguishing agent, thereby ensuring the efficient operation of the system.

[0049] Furthermore, the first tank heating pipe 2 and the second tank heating pipe 3 of the present invention are both wrapped with a tank external insulation layer 4. The tank external insulation layer 4 plays an important role. As a preferred external insulation layer, nano thermal insulation materials can be used. This material can be used in a high temperature environment, such as Al2O3 nano material board, which can maintain stable thermal insulation performance even at a high temperature of 1200°C, and other materials with excellent performance, which can effectively prevent heat dissipation, ensure the temperature inside the system is stable, and provide reliable protection for dealing with sudden fires.

[0050] Furthermore, the heating resistor wire is led from the aircraft auxiliary power unit compartment to the fire extinguishing agent storage tank, and the power supply of the heating resistor wire is located in the aircraft auxiliary power unit compartment, which provides electricity such as lighting for the aircraft to ensure lighting and air conditioning in the cabin and cockpit.

[0051] Furthermore, the outer wall of the first fire extinguishing agent storage tank and the outer wall of the second fire extinguishing agent storage tank are both wrapped with a layer of heat conductive film.

[0052] Furthermore, in the embodiment of the present invention, the first storage tank heating pipe 2, the second storage tank heating pipe 3, the outer wall of the first fire extinguishing agent storage tank, and the outer wall of the second fire extinguishing agent storage tank are all made of heat-conducting materials.

[0053] In the embodiment of the present invention, a temperature sensor 301 and a temperature sensor 201 are respectively installed at the bottom of the first fire extinguishing agent storage tank and the second fire extinguishing agent storage tank, which are used to detect the temperature of the fire extinguishing agent inside the storage tanks in real time.

[0054] In addition, a pressure sensor 302 and a pressure sensor 202 are installed at the bottom of the first fire extinguishing agent storage tank and the second fire extinguishing agent storage tank, respectively, to achieve real-time monitoring of the pressure of the fire extinguishing agent in the fire extinguishing agent storage tanks.

[0055] In the present invention, high-temperature gas enters through the preheating gas intake pipe network 1, which includes a preheating gas heating pipeline 101, a preheater delivery electromagnetic valve 102, and a preheating gas delivery pipeline 103; the engine preheated high-temperature gas passes through the preheating gas delivery electromagnetic valve 102, enters through the preheating gas inlet 104, and is finally discharged from the preheating gas outlet 105.

[0056] The fire extinguishing agents placed inside the aircraft fire extinguishing agent auxiliary gasification system of the present invention are all high-boiling point fire extinguishing agents, including but not limited to 2-BTP and perfluorohexanone (Novec-1230); according to the effective fire extinguishing concentration experiment of n-heptane, the effective fire extinguishing concentration of "halon" 1301 is 5%; the effective fire extinguishing concentration of 2-BTP is 2.6%; the effective fire extinguishing concentration of perfluorohexanone (Novec-1230) is 4.5%; therefore, the present invention is applied to the preheating and heat preservation of the storage device of the aircraft-borne high-boiling point fire extinguishing agent (such as 2-BTP, perfluorohexanone Novec1230), which helps to improve the gasification efficiency and fire extinguishing effect of the high-boiling point airborne fire extinguishing agent, reduce the filling mass of the airborne fire extinguishing agent to a certain extent, and is conducive to the lightweight design of the aircraft.

[0057] The preheating gas delivery electromagnetic valve 102, temperature sensors 201, 301, pressure sensors 202, 302, and heating resistors 203, 303 of the present invention are all controlled by the fire extinguishing agent auxiliary gasification automatic control module and are electrically connected to each other.

[0058] Example 2

[0059] Embodiment 2 discloses a method for assisting gasification of aircraft fire extinguishing agents, comprising the following steps:

[0060] When the aircraft is in take-off state or the aircraft engine stops unexpectedly, the fire extinguishing agent in the tank is electrically heated by the heating resistance wire inside the fire extinguishing agent storage tank;

[0061] When the aircraft is in a stable flight state, the electric heating is turned off and the high-temperature gas of the fire extinguishing agent in the fire extinguishing agent tank is heated by using the tank heating pipe wrapped around the outer wall of the fire extinguishing agent tank.

[0062] The above insulation method can be implemented based on the insulation system of Example 1, as follows Figure 4 The operation process of the aircraft fire extinguishing agent auxiliary gasification system of the present invention will be described by way of example:

[0063] When the aircraft closes the door and prepares to be pushed out, the aircraft engine has not yet run at high speed. The fire extinguishing agent preheating automatic control module automatically starts the fire extinguishing agent auxiliary gasification electric heating mode, and monitors the specific temperature value in the fire extinguishing agent storage tank through the temperature sensor in the fire extinguishing agent preheating automatic control module. Then, according to the boiling point of the fire extinguishing agent in the storage tank, as well as its specific heat capacity and mass, according to Q=C·m·Δt, the heat required to reach the required temperature is calculated, and according to Q=Pt, the heating resistance wire power required to reach the preheating temperature within 5 minutes is calculated, so that the fire extinguishing agent at room temperature can be quickly preheated to respond in real time to sudden fire situations when the aircraft is taxiing on the runway after being pushed out and preparing for flight;

[0064] When the aircraft is flying steadily into the air, the engine is running at a high speed. When the outer wall of the engine turbine can be used as a heat source and preheating gas is provided, the fire extinguishing agent preheating automatic control module automatically turns off the electric heating mode and starts the preheating gas delivery electromagnetic valve 102 at the same time, and uses the high temperature generated by the combustion in the aircraft engine combustion chamber to heat the air entering the preheating gas heating pipe through the engine outer duct. The external gas enters the engine, and an S-shaped pipe is set inside the outer duct close to the outer wall of the combustion chamber, which is called the preheating gas heating pipe 101. The external gas enters through the engine outer duct 7 and is heated to generate high-temperature gas and preheat the fire extinguishing agent in the tank through the first tank heating pipe 2 and the second tank heating pipe 3 wrapped around the outer wall of the fire extinguishing agent tank; this design enables the gas entering the pipe to make full use of the heat released by the combustion chamber, and quickly heats the gas in the pipe through heat conduction to reach the required high temperature. This process not only effectively improves the thermal energy of the gas, but also provides the necessary heat source for the subsequent preheating of the fire extinguishing agent, ensuring the efficient operation of the system.

[0065] The high-temperature gas is introduced from the preheating gas heating pipe 101, passes through the preheating gas delivery electromagnetic valve 102, and flows into the first tank heating pipe 2 and the second tank heating pipe 3 through the preheating gas delivery pipe 103, and the fire extinguishing agent in the tank is insulated by the external insulation layer 4 of the tank; the heat dissipation is effectively prevented to ensure the temperature stability inside the system. The incoming hot gas preheats the fire extinguishing agent so that the temperature of the fire extinguishing material reaches a state close to that of gasification. This design not only improves the gasification rate of the fire extinguishing agent, but also significantly enhances its fire extinguishing efficiency, providing a reliable guarantee for responding to sudden fires.

[0066] The fire extinguishing agent preheating automatic control module monitors the temperature value of the fire extinguishing agent inside the fire extinguishing agent storage tank in real time. When the temperature of the fire extinguishing agent inside the fire extinguishing agent storage tank reaches the set temperature range, the preheating gas delivery electromagnetic valve 102 is automatically closed. When the temperature of the fire extinguishing agent is lower than the lower limit of the set temperature range, the preheating gas delivery electromagnetic valve 102 is automatically started.

[0067] When the fire extinguishing agent preheating automatic control module detects in real time that the engine stops unexpectedly during flight, it automatically switches to the electric heating mode, starts the first tank heating resistor 203 and the second tank heating resistor 303 to open, so as to preheat the fire extinguishing agent in the high-incidence situation of fire such as the engine stopping unexpectedly, so that the fire extinguishing agent is in a preheated state when the fire extinguishing system is turned on at any time, and the fire extinguishing agent can be quickly vaporized when sprayed to exert a high-efficiency fire extinguishing effect.

[0068] In addition, in the embodiment of the present invention, the bottom of the fire extinguishing agent storage tank is equipped with precise temperature sensors 201 and 301 to monitor the temperature of the fire extinguishing agent in the storage tank in real time. When the aircraft is flying smoothly into the air, when the temperature of the fire extinguishing agent in the storage tank reaches the set upper temperature limit T2, the preheating gas delivery electromagnetic valve 102 needs to be closed to stop delivering the high-temperature gas; if the temperature sensor detects that the temperature of the fire extinguishing agent is lower than the set lower temperature limit T1, the preheating gas delivery electromagnetic valve 102 will be opened to allow new gas to enter, and the exhaust gas will be discharged through the exhaust port of the aircraft ventilation system of the aircraft. This cycle process not only ensures the long-term preheating of the fire extinguisher bottle, but also maintains the efficient operation of the system, so that it can respond quickly in the event of a fire. This design reflects the innovation and foresight of the aircraft in terms of safety protection, and provides higher safety protection for passengers and crew members.

[0069] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0070] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An aircraft fire extinguishing agent auxiliary gasification system, characterized in that: It comprises a preheating gas intake pipe network (1), a first storage tank heating pipe (2), a first storage tank heating resistance wire (203), a second storage tank heating pipe (3), a second storage tank heating resistance wire (303) and a fire extinguishing agent preheating automatic control module; The first storage tank heating pipe (2) is tightly wound around the outer wall of the first fire extinguishing agent storage tank; the second storage tank heating pipe (3) is tightly wound around the outer wall of the second fire extinguishing agent storage tank; The preheating gas inlet pipe network (1) is connected to the first storage tank heating pipe (2) and the second storage tank heating pipe (3) at the same time, and is used to input the high-temperature gas generated by the aircraft engine into the first storage tank heating pipe (2) and the second storage tank heating pipe (3) respectively, so as to realize the high-temperature gas heating of the fire extinguishing agent inside the first fire extinguishing agent storage tank and the second fire extinguishing agent storage tank; The first storage tank heating resistance wire (203) and the second storage tank heating resistance wire (303) are respectively placed at the lower half of the inner walls of the two storage tanks, and are used to respectively realize the electrical heating of the fire extinguishing agent inside the first fire extinguishing agent storage tank and the second fire extinguishing agent storage tank; The fire extinguishing agent preheating automatic control module is used to control the electric heating or high-temperature gas heating mode of the fire extinguishing agent according to the flight status of the aircraft.

2. The aircraft fire extinguishing agent auxiliary gasification system according to claim 1, characterized in that: The first fire extinguishing agent storage tank is a high-speed release fire extinguishing agent storage bottle for quickly releasing the fire extinguishing agent; the second fire extinguishing agent storage tank is a low-speed release fire extinguishing agent storage bottle for releasing to prevent the flame from reigniting.

3. The aircraft fire extinguishing agent auxiliary gasification system according to claim 1, characterized in that: The fire extinguishing agents placed inside the first fire extinguishing agent storage tank and the second fire extinguishing agent storage tank are both high-boiling point fire extinguishing agents, including 2-BTP or perfluorohexanone.

4. The aircraft fire extinguishing agent auxiliary gasification system according to claim 1, characterized in that: The preheated gas intake pipe network (1) comprises a preheated gas heating pipe (101), a preheated gas delivery electromagnetic valve (102) and a preheated gas delivery pipe (103); The preheating gas heating pipeline (101) is used to generate high-temperature gas using an aircraft engine, and the preheating gas delivery solenoid valve (102) is used to input the generated high-temperature gas into the preheating gas delivery pipeline (103) according to a control signal output by a fire extinguishing agent preheating automatic control module; the preheating gas delivery pipeline (103) is simultaneously connected to the first storage tank heating pipeline (2) and the second storage tank heating pipeline (3).

5. The aircraft fire extinguishing agent auxiliary gasification system according to claim 4, characterized in that: The preheated gas heating pipe (101) is arranged on the outer wall of the engine combustion chamber, and utilizes the high temperature generated by combustion in the aircraft engine combustion chamber to heat the air entering the preheated gas heating pipe (101) to generate high-temperature gas.

6. The aircraft fire extinguishing agent auxiliary gasification system according to claim 1, characterized in that: The first storage tank heating pipe (2), the second storage tank heating pipe (3), the outer wall of the first fire extinguishing agent storage tank, and the outer wall of the second fire extinguishing agent storage tank are all configured with heat-conducting materials.

7. The aircraft fire extinguishing agent auxiliary gasification system according to claim 1, characterized in that: The outer sides of the first storage tank heating pipe (2) and the second storage tank heating pipe (3) are both wrapped with an external insulation layer.

8. The aircraft fire extinguishing agent auxiliary gasification system according to claim 1, characterized in that: The outer wall of the first fire extinguishing agent storage tank and the outer wall of the second fire extinguishing agent storage tank are both wrapped with a layer of heat conductive film.

9. The aircraft fire extinguishing agent auxiliary gasification system according to claim 1, characterized in that: The fire extinguishing agent preheating automatic control module controls the electric heating or high-temperature gas heating mode of the fire extinguishing agent according to the flight status of the aircraft, which specifically includes the following steps: When the aircraft is in a take-off state or the aircraft engine is unexpectedly stopped, the fire extinguishing agent preheating automatic control module is used to start the heating switches of the first storage tank heating resistor wire (203) and the second storage tank heating resistor wire (303) to achieve electrical heating of the fire extinguishing agent in the tank; When the aircraft is in a stable flight state, the fire extinguishing agent preheating automatic control module is used to close the heating switches of the first storage tank heating resistor wire (203) and the second storage tank heating resistor wire (303); at the same time, the fire extinguishing agent preheating automatic control module is used to open the preheating gas delivery electromagnetic valve of the hot gas intake pipe network (1) to achieve high-temperature gas heating of the fire extinguishing agent in the tank.

10. A method for assisting gasification of aircraft fire extinguishing agents, characterized in that: The following steps are involved: When the aircraft is in take-off state or the aircraft engine stops unexpectedly, the fire extinguishing agent in the tank is electrically heated by the heating resistance wire inside the fire extinguishing agent storage tank; When the aircraft is in a stable flight state, the electric heating is turned off and the high-temperature gas of the fire extinguishing agent in the fire extinguishing agent tank is heated by using the tank heating pipe wrapped around the outer wall of the fire extinguishing agent tank.

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