JPH08150225A - Automatic fire extinguisher for aircraft - Google Patents

Abstract

PURPOSE: To provide an automatic fire extinguisher for aircraft which can extinguish an aircraft fire caused by forced landing in its early stages by activating an extinguisher when a detection signal which is the results of detecting impact and temperature at forced landing meets a specified condition. CONSTITUTION: The impact when an aircraft is landing is detected by an impulse sensor 1 and input to a control device 4. When an impact detection signal exceeds a specified value, the control device 4 regards it as a forced landing. Temperature detection signals of temperature sensors 2 and 2 begin to be input. The first input temperature is stored in a RAM, and it is compared with a temperature after t seconds. An increasing range in temperature of the comparison results is more than the specified value B, it is regarded as a fire, and an activation signal is sent to an extinguisher activating means 3 to activate an extinguisher 5. As an alternative, instead of this temperature rising detection, the system can be designed so that a fire is judged based on whether temperature reaches a specified value or not.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an automatic fire extinguishing system for aircraft, and more particularly, to an automatic fire extinguishing system for an aircraft capable of detecting an aircraft fire and automatically spraying a fire extinguishing agent, and receiving a start command. The present invention relates to an automatic fire extinguishing device for an aircraft that can automatically extinguish an aircraft fire by spraying a fire extinguisher.

[0002]

2. Description of the Related Art In an emergency landing accident of an aircraft, a crew member is often injured by crashing into a seat, a panel, a windshield or the like due to an impact during an emergency landing. . Equipment such as seat belts for aircraft is quite effective in reducing the injuries caused by collisions due to impact during an emergency landing.

On the other hand, in an emergency landing accident, a fire often occurs due to ignition of fuel leaking from a fuel tank or an engine part. Even if a crash accident due to an impact during an emergency landing does not result in death, an aircraft fire may cause the crew to be burnt to death. In addition, even if not fatal, the degree of injury is significantly deteriorated due to a burn or oxygen deficiency due to a fire, and a serious injury is often caused.

An unfortunate example in which a crew member is burned to death when a rescuer cannot evacuate due to the deformation of an aircraft due to an impact force caused by an emergency landing accident and a fire occurs during the rescue of a crew member by a rescuer. Is also known. In this case, if the fire does not occur, the crew can be rescued, and the worst result of the death of the crew may be avoided.

The damage is caused not only by the crew of the aircraft that caused the accidental landing, but also by igniting the aircraft, buildings and other facilities in the vicinity of the accidental landing site, and sometimes by the gas or smoke generated by combustion or combustion. Oxygen deficiency often damages others.

However, the protection against such a fire is only to the extent that the fire engine is on standby at the airport or the fire extinguisher is loaded on the aircraft, and in most aircrafts, the defense is currently unprotected.

Therefore, there has been a demand for a device which can be installed in an aircraft and can extinguish a fire that has occurred.

The present invention has been completed based on such circumstances. That is, an object of the present invention is to solve the above problems, and more specifically to provide an automatic fire extinguishing device for an aircraft capable of extinguishing a fire caused by an accidental landing accident at an early stage. Another object of the present invention is to provide an automatic fire extinguishing device for an aircraft that can extinguish an aircraft fire easily and quickly.

[0009]

As a result of earnest studies by the present inventors in order to solve the above-mentioned problems, as a result, the impact sensor and / or the temperature sensor are installed in the aircraft, or the optical sensor and / or the impact sensor are installed in the aircraft. Then, the control means is caused to detect the occurrence of a fire based on the detection signals output from these, and the fire extinguishing agent is sprayed from the fire extinguishing means under the control of the control means that has detected the occurrence of the aircraft fire, or it is manually started. The present invention has been reached by discovering that an aircraft fire can be extinguished effectively at an early stage by inputting a command and driving the fire extinguisher starting means from this start command to spray the fire extinguishing agent from the fire extinguishing means.

The invention according to claim 1 for solving the above-mentioned problems is a temperature sensor and / or a shock sensor, a temperature detection signal output from the temperature sensor and / or a shock output from the shock sensor. Control means for detecting an aircraft fire by inputting a detection signal and outputting an activation signal, fire extinguisher activation means driven by the activation signal output from the control means, and extinguishing agent by driving the fire extinguisher activation means. An automatic fire extinguishing device for an aircraft, comprising: an extinguishing means for spraying in an aircraft, wherein the invention according to claim 2 for solving the above-mentioned problems includes an optical sensor and / or an impact sensor. , A light detection signal output from the light sensor and /
Alternatively, control means for detecting an aircraft fire by inputting an impact detection signal output from the impact sensor and outputting an activation signal, fire extinguisher activation means driven by the activation signal output from the control means, and extinguishing a fire An automatic fire extinguisher for an aircraft, characterized in that the fire extinguishing means for spraying a fire extinguishing agent by driving a firearm starting means is provided in the aircraft, and the invention according to claim 3 for solving the above-mentioned problems. , A start command input means for inputting a start command and outputting a start signal, a fire extinguisher starting means driven by a start signal output from the start command input means, and a fire extinguisher sprayed by driving the fire extinguisher starting means An automatic fire extinguisher for an aircraft, characterized in that the fire extinguishing means is provided inside the aircraft.

[0011]

The automatic fire-extinguishing system for aircraft according to the first aspect of the present invention operates as follows. Impact sensors and / or temperature sensors are installed at appropriate locations on the aircraft. The impact sensor issues an impact detection signal when an impact due to an accidental landing occurs. The impact detection signal is input to the control means. A temperature detection signal generated by the temperature sensor is also input to the control means. The control means analyzes the impact detection signal and / or the temperature detection signal, and issues an activation signal to the fire extinguisher activation means when a certain condition is satisfied. When satisfying the certain condition, (1) the impact detection signal input from the impact sensor is a signal indicating an impact of a predetermined value or more, and / or the temperature detection signal output from the temperature sensor is at a constant temperature. (2) the impact detection signal input from the impact sensor is a signal indicating an impact of a predetermined value or more, and / or a temperature detection signal input from the temperature sensor Is a signal indicating a temperature increase above a certain speed.

The fire extinguisher starting means starts driving by the start signal output from the control means to start the fire extinguishing means. Then, the fire extinguishing agent is sprayed from the activated fire extinguishing means. The fire extinguishing means is preferably arranged so that the fire extinguishing agent can be sprayed to a place where a fire is likely to occur due to fuel leakage or the like of the aircraft.

In this way, the automatic fire extinguishing system for an aircraft of the present invention automatically detects a fire caused by an unplanned landing accident, and automatically extinguishes the fire by spraying a fire extinguishing agent. I do.

The aircraft automatic fire-extinguishing system according to the second aspect of the present invention operates as follows. Impact sensors and / or optical sensors are installed at appropriate locations on the aircraft. The impact detection signal output from the impact sensor and / or the light detection signal output from the optical sensor is input to the control means. The control means analyzes the input impact detection signal and / or the light detection signal, and issues an activation signal to the fire extinguisher activation means when a certain condition is satisfied. When the certain condition is satisfied, (1) the impact detection signal input from the impact sensor is a signal indicating an impact of a predetermined value or more, and / or the light detection signal output from the optical sensor is constant. (2) the impact detection signal input from the impact sensor is a signal indicating an impact of a predetermined value or more, and / or the light detection input from the optical sensor The case where the signal is a signal indicating an increase or a change in the light amount at a certain speed or more can be mentioned.

The fire extinguisher starting means starts driving in response to a start signal output from the control means, and the fire extinguishing means is started to spray the fire extinguishing agent.
This is the same as in the automatic fire extinguishing system for an aircraft according to the invention described in (1).

The automatic fire extinguishing system for an aircraft according to the third aspect of the present invention operates as follows. When a fire occurs due to an accidental landing or other causes, a start command is manually input to a start command input means provided at an appropriate position of the aircraft. When the activation command is input, the activation command input means outputs an activation signal to the fire extinguisher activation means. The fire extinguisher starting means that has received the start signal starts driving, and the fire extinguishing means is started to spray the fire extinguishing agent in the same manner as described above.

[0017]

【Example】

(Embodiment 1) The invention according to claim 1 or 2 will be described with reference to an aircraft automatic fire extinguishing system according to an embodiment of the present invention.

The automatic fire extinguishing system for an aircraft shown in FIG. 1 includes an impact sensor 1 installed at an appropriate position in the aircraft, and a plurality of temperature sensors 2 installed at appropriate positions in the aircraft.
2, control means 4 for inputting a temperature detection signal output from the temperature sensors 2 and 2 and an impact detection signal output from the impact sensor 1 and outputting a start signal, and output from the control means 4. The fire extinguisher starting means 3 is driven by a start signal, and the fire extinguisher 5 is sprayed by driving the fire extinguisher starting means 3.

As the temperature sensor, a temperature sensitive element, bimetal, thermocouple, measuring resistor or the like can be used. Among these, a temperature-sensitive element that is small and has high sensitivity is preferable.

As the temperature sensitive element, a temperature sensitive semiconductor element such as a negative characteristic thermistor, a positive characteristic thermistor, a critical temperature thermistor, a plastic thermistor, a temperature sensitive diode, an IC temperature sensor, a temperature sensitive capacitor, a temperature sensitive inductor, or the like. Reactance elements, temperature sensitive resonators, thermistor bolometers, pyroelectric elements, thermal radiation detection elements such as quantum infrared detectors, and the like can be mentioned.

The temperature sensor according to the present invention may be a sensor that detects infrared rays or the like as temperature, like the thermal radiation detecting element.

Examples of the sensor for detecting the infrared rays and the like as temperature include a temperature sensor having a filter that transmits only infrared rays in a specific wavelength range and a pyroelectric element that is heated by the infrared rays that have passed through this filter. be able to. Since such a temperature sensor responds only to infrared rays in a specific wavelength range, it is less likely that the fire extinguisher malfunctions in response to sunlight other than infrared rays due to aircraft fire, lighting, or the like.

Further, the temperature sensor in the present invention may be not only a temperature sensor capable of measuring a temperature change with time but also a temperature sensor capable of detecting only that a predetermined temperature is reached.

As such a temperature sensor, a thermal fuse as shown in FIG. 2 can be exemplified. The thermal fuse 6 has a substantially cylindrical fuse body 8 having conductivity and a first lead 7 connected to one end, and a contact terminal 9 at an end, and the end is located inside the fuse body 8. The first lead. The second lead 10 is fixed as described above, the sliding contact terminal 11 is in sliding contact with the inner peripheral surface of the fuse body 8, and the terminal 12 is in contact with the contact terminal 9 of the second lead 10. 7 for electrically connecting the second lead 10 to each other, and a biasing means 14 for biasing the connecting member 13 in a direction in which the terminal 12 and the contact terminal 9 are separated from each other.
When the temperature is lower than a predetermined temperature, the connection member 13 is solid and presses the connection member 13 to maintain contact between the terminal 12 and the contact terminal 9 of the second lead 10, and when the temperature reaches the predetermined temperature,
The temperature-sensitive pellets 15 allow the connection member 13 to move so that the terminals 12 and the contact terminals 9 do not come into contact with each other when melted.

The temperature-sensitive fuse 6 maintains the electrical connection between the first lead 7 and the second lead 10 when the temperature is lower than a predetermined value, and when the temperature rises to reach the predetermined temperature, the electrical connection is made. The fact that the predetermined temperature has been reached is output as an electrical signal by breaking the physical connection. In this case, the control means determines whether the electrical connection is maintained or the electrical connection is broken due to a fire.

Among the various temperature sensors described above, thermistors such as the negative characteristic thermistor and the positive characteristic thermistor can be preferably used because of their small size.

In this embodiment, a thermistor having a negative characteristic in which the resistance value decreases with an increase in temperature is adopted. If a thermistor with negative characteristics is adopted, the lead that electrically connects the temperature sensor and the control means may be cut or the resistance value may increase due to deformation or impact of the aircraft or the like caused by the accidental landing. However, it is advantageous because it is not erroneously determined to be due to the temperature rise.

FIG. 3 is a schematic view showing an impact sensor in this embodiment.

The impact sensor 20 includes a support 21, a coil 22 formed by a wide wire placed on the support 21, and a cylindrical metal weight 23 placed on the coil 22. And have. Both ends of the coil 22 are connected to the support 21 and the weight 23, respectively. The coil 22 is closely wound in a compressed state. The weight 23 is stably placed on the coil 22. As shown in FIG. 4, a wire 24 having sufficient flexibility and being non-conductive is connected to the central portion of the lower surface of the weight 23. The other end of the wire 24 is inserted into a through hole 25 provided on the upper surface of the support base 21 and fixed to an insulating plate 26 inside the support base 21 at the tip of a flexible movable contact terminal 27. It is connected.

Another contact terminal 28 is fixed above the movable contact terminal 27 on the insulating plate 26.

When an impact force less than a predetermined value is applied to the impact sensor 20, the weight 23 is stabilized in the original state by the restoring force of the coil 22 even if the weight 23 swings back and forth and right and left. . Therefore, the weight 23
Does not detach from the support table 21. On the other hand, when an impact force of a predetermined value or more is applied to the impact sensor 20, the weight 23 is detached from the support base 21. Along with this detachment, the coil 22 is greatly stretched. At the same time, by pulling the wire 24 connected to the weight 23, the movable contact terminal 27 comes into contact with the other contact terminal 28. In this way, the shock can be converted into an electrical signal.

As the impact sensor in the present invention,
It is not limited to the impact sensor shown in the embodiment,
For example, a strain gauge, an impact sensor in which an object and a strain gauge are combined, or the like can also be suitably used.

Examples of the strain gauge include a metal resistance strain gauge and a semiconductor strain gauge,
Examples of the metal resistance strain gauge include a line gauge and a foil gauge, and examples of the semiconductor strain gauge include a bulk gauge, a vapor deposition gauge, a diffusion gauge, and other pressure sensitive elements.

The shock detection signal generated by the shock sensor according to the present invention may be two kinds of shock detection signals indicating whether the shock force is a predetermined value or more, as in the case of the shock sensor described in detail above. Alternatively, it may be a continuous impact detection signal.

In the present invention, the impact may be detected by detecting the impact itself or by detecting the occurrence of strain. Furthermore, the pressure applied to the object at the time of impact,
It may be based on a method of detecting a change in acceleration or the like.

In this embodiment, the control means determines whether the impact detection signal generated by the impact sensor is equal to or more than a predetermined value. When it is determined that the value is equal to or more than the predetermined value, it is determined that the aircraft emergency landing accident has occurred. When it is determined that the accident has occurred, the temperature detection signal output by the temperature sensor is instantly recorded by the control means. Then, for example, the temperature increase rate (change in temperature per unit time) is calculated, and when the calculated temperature increase rate exceeds the set value, it is determined that a fire has occurred. The set value of the temperature rising rate can be set to a free value depending on the place where the temperature sensor is installed.

In this embodiment, the unit time is 0.2
It was set to seconds, and when a temperature rising rate of 0.2 ° C. or more per unit time was recognized, it was determined that a fire occurred.

In this embodiment, unless the impact detection signal from the impact sensor is input to the control means and it is determined that an accident has occurred, the control means records the temperature detection signal from the temperature sensor and raises the temperature above the set value. Even if it is judged to be speed, it is not judged to be a fire. Conversely, even if it is determined that an accident has occurred by the impact detection signal, if a rise in temperature above the set value is not detected in a unit time, it is not similarly determined that a fire has occurred. Therefore,
When a fire does not occur due to an emergency landing accident, it is possible to prevent a malfunction such as the automatic fire extinguisher spraying the fire extinguishing agent.

The mechanism from the occurrence of the accidental landing accident to the determination of the fire occurrence in one specific example of the control means that can be adopted in the present invention will be explained with reference to FIG.

It is judged whether or not the shock detection signal output from the shock sensor is equal to or more than a predetermined value (A) (step 2), and if it is less than the predetermined value, the shock detection signal wait state is resumed. When the value is equal to or more than the predetermined value (A), it is determined that the accidental landing accident has occurred, and the input of the temperature detection signal of the temperature sensor is started (step 3). RAM for the temperature at the first input
It is recorded in and is compared with the temperature t seconds after the first input (step 6).

As a result, when the temperature rise during the unit time t seconds is equal to or greater than the predetermined value (B), it is determined that a fire has occurred, and an electrical activation signal is issued to the fire extinguisher activation means. If the rise in temperature is less than or equal to the predetermined value (B), it is not determined that a fire has occurred, and comparison with the temperature after a unit time is further performed.

In the present invention, the occurrence of a fire may be judged by the impact and the detection of the temperature increase rate above the set value as described above. Instead of the detection of the temperature increase rate above the set value, a certain set temperature may be detected. The judgment may be made by detecting that it has reached.

Preferably, the judgment is made by detecting the temperature rising speed above the set value. This is because according to this determination method, it can be determined that a fire has occurred in a short time after the fire has occurred.

The control means in this embodiment records the temperature detection signal from the temperature sensor after the impact is detected by the above-described method, and when the temperature rises at a certain temperature rise speed or more, the occurrence of a fire is detected. to decide. The control means
When a fire is detected, a fire extinguisher activation means is activated, and upon receipt of this signal, the fire extinguisher activation means starts driving.

FIG. 6 is a schematic sectional view showing a fire extinguisher starting means in this embodiment.

The fire extinguisher starting device 30, which is the fire extinguisher starting means in this embodiment, is provided at a substantially cylindrical body of the fire extinguisher starting device 31 and an end portion of the fire extinguisher starting device main body 31 and extinguishes the fire. Fixing member 32 to be attached to the opening of the container
And a shock absorbing material piercing member 33 and an explosive 34 housed in the fire extinguisher starting device body 31.

The shock-absorbing material punching member 33 has a sharp shock-absorbing material punching blade 35 at one end, and the other end is provided on a support 36 slidable along the inner peripheral surface of the fire extinguisher starter body. The support 36 is inserted into the notched recess 37.
Supported by.

The explosive 34 is filled in the rear of the support 36, and has an ignition ball 38 for ignition at the center thereof.

A concave groove is formed on the outer peripheral surface of the support 36, and an O-ring 40 is provided in the concave groove. By the O-ring 40, the adhesion of the support to the inner peripheral surface of the fire extinguisher starter body and the slidability along the inner peripheral surface are simultaneously secured. In the figure, 41 is a lead for electrically connecting the ignition ball and the control means.

The fire extinguisher includes a fire extinguisher body having a fire extinguisher injection port, a fire extinguisher contained in the fire extinguisher body, and an injection gas for high-pressure injection of the fire extinguishing agent from the fire extinguisher injection port. And a filled gas-filled inner container. This fire extinguisher can destroy the sealing plate in the gas filled inner container by the fire extinguisher starting means according to the present invention, and the fire extinguisher can be ejected from the fire extinguishing agent injection port by the gas pressure ejected from the gas filled inner container It is like this.

When an activation signal is issued from the control means, that is, when a current is applied to the ignition ball 38 via the lead 41 in this embodiment, the ignition ball 38 is ignited. As a result, the explosive 34 filled in the surrounding area is also ignited and explodes. Due to the energy of the explosive explosion, the support 36 and the support 36
The cushioning material perforating member 33 supported by the instantly moves toward the fire extinguisher in the fire extinguisher activation device body. Then, the cushioning material perforating blade 35 at the tip portion perforates the sealing plate of the gas-filled inner container loaded in the fire extinguisher body. The extinguishant is ejected from the extinguishant jet by the gas pressure that expands inside the extinguisher body due to the perforation of the sealing plate of the gas-filled inner container.

Immediately after that, the cushioning material punching blade 33 is pushed back by the cushioning material punching member 33, and the cushioning material punching blade is pushed back to its original position by the urging force of the spring 44 which is contracted by the explosive force of the explosive.

In this way, activation of the fire extinguisher activation means by the activation command from the control means and spraying of the fire extinguishing agent by activation are achieved.

The aircraft automatic fire extinguisher shown in this embodiment comprises both a temperature sensor and an impact sensor, but in the invention described in claim 1, it comprises either one of the temperature sensor and the impact sensor. It may be an automatic fire extinguisher for aircraft.

(Embodiment 2) An embodiment of an automatic fire extinguishing apparatus for an aircraft according to claim 2 will be described.

The aircraft automatic fire extinguishing system according to this embodiment includes an impact sensor installed at an appropriate position in the aircraft, an optical sensor installed at an appropriate position in the aircraft,
Control means for inputting the light detection signal output from the optical sensor and the impact detection signal output from the impact sensor and outputting an activation signal, and a fire extinguisher activation means driven by the activation signal output from the control means And a fire extinguisher for spraying a fire extinguishing agent by driving the fire extinguisher starting means.

The optical sensor is not particularly limited as long as it can detect infrared rays and visible light, and may be a sensor that detects infrared rays or the like by detecting a temperature change of a substance due to a heating action of infrared rays or the like. It may be a sensor that detects infrared rays or the like by a quantum effect between the energy level of a semiconductor or the like and the infrared rays or the like that are irradiated.

A sensor which detects infrared rays and the like by detecting a temperature change of a substance due to a heating action of infrared rays and the like is preferable. As a specific example of such a sensor, a filter that transmits only light in a specific wavelength range,
A thermistor bolometer, which is heated by the transmitted light,
Mention may be made of infrared sensors consisting of a combination with a thermopile or TGS. The sensor that detects the heating effect of infrared rays does not require cooling,
Moreover, it is inexpensive and advantageous.

The optical sensor according to the present invention may detect visible light. In the case of detecting visible light, for example, a photoconductive element using CdS, CdSe, a solid solution thereof, or the like can be adopted. It is also possible to employ a solar cell, a photodiode, a phototransistor, a photothyristor, or the like.

In the present invention, the photodetection signal output from the photosensor is input to the control means. Then, the input light detection signal and / or impact detection signal is analyzed to detect the occurrence of fire. In the control means of this embodiment, the impact detection signal input from the impact sensor is a signal indicating an impact force of a predetermined value or more, and the light detection signal input from the optical sensor is a light amount of a predetermined value or more. If the signal indicates that a fire has occurred.

In the aircraft automatic fire extinguishing system of this embodiment, the process from the fire extinguishing means to the spraying of the fire extinguishing agent after the impact sensor and the control means detect the occurrence of a fire is the same as in the first embodiment. Is.

(Embodiment 3) Next, the invention according to claim 3 will be described with reference to an embodiment.

FIG. 7 shows an automatic fire extinguishing system for an aircraft which is an embodiment of the invention described in claim 3. The automatic fire extinguisher 50 for an aircraft shown in FIG. 7 has a start command input means 51, a fire extinguisher starting means 52, and the same number of fire extinguishers 5 as the fire extinguisher starting means.
3 and 3.

As the start command input means, for example,
Toggle switch, push switch, seesaw switch,
An input device equipped with switches such as a slide switch, a key lock switch, and a touch switch can be adopted.

The fire extinguisher starting means 52 and the fire extinguisher 53 are
This is the same as in the first embodiment.

In this aircraft automatic fire extinguisher, the activation command is directly or indirectly input to the activation command input means. The start instruction input means 51 that has input the start instruction is
An activation signal is output to the fire extinguisher activation means. When the fire extinguisher activation means 52 receives the activation signal, the fire extinguisher activation means 52 is activated to activate the fire extinguisher 53, which is a fire extinguishing means, to spray the fire extinguisher.

As a method of inputting a start command to the start command input means, a method of manually operating and inputting switches provided in the start command input means or a method of transmitting radio waves or infrared rays from outside the aircraft, A method of inputting this by receiving this as a start command can be adopted.

If the method of inputting a start command using the radio waves or infrared rays is adopted, the start command can be transmitted from the outside of the aircraft to start the fire extinguishing means. If it does occur, it can be extinguished by remote control from the outside.

The start signal output by the start command input means may be an electrical change, that is, a change in voltage, current or resistance value, or may be a mechanically transmitted signal.

(Modification) The fire extinguisher starting means in the present invention is not limited to the structure shown in the first embodiment. For example, it is mounted on a fire extinguisher body that is filled with a fire extinguisher, and has an explosive configured to be ignited by a start signal. It may be configured to squirt.

The extinguishing means in the present invention is not particularly limited as long as it has a function of extinguishing a fire, and is not limited to the extinguisher used in this embodiment.

The extinguishing means that can be used in the present invention is as follows:
In addition to fire extinguishers, water spray fire extinguishing equipment that uses the suffocation effect of water spray cooling and generated steam, foam extinguishing equipment that extinguishes the combustion surface with released foam, and carbon dioxide, halogenated hydrocarbon-based gas, Examples include gas-based fire extinguishing equipment that extinguishes by releasing a gas-based fire extinguishing agent such as powder fire extinguishing agent.

Of these, a fire extinguisher can be preferably used. Because the fire extinguisher is portable, it can be easily replaced at regular intervals or after a safety check.

As the above-mentioned fire extinguisher, one that emits water in the form of a rod or powder, one that emits a strengthening liquid, one that emits bubbles, one that emits carbon dioxide, one that emits a halide, phosphate, etc. And the like, which emits a fire-extinguishing powder.

In the present invention, the activation signal output from the control means to the fire extinguisher activation means and the activation signal output from the activation command input means to the fire extinguisher activation means may be voltage, current, These include electrical changes such as resistance values, changes in pressure, and mechanical changes. Electrical changes such as the voltage, current, resistance value, etc. can be transmitted through electric wires, etc., and the pressure change can be achieved by a method of applying a pressure change to a pressure medium such as oil enclosed in a tube. Can be communicated. The mechanical change is transmitted by a method of converting the mechanical change given to one member into forward and backward movements, rotational movements, etc. of a transmission member such as a wire or a rod and transmitting it to a member provided on the other. can do.

A nonel tube having an inner wall surface of a resin tube coated with explosive may be employed as the activation signal transmission means. In this case, ignition means for igniting one end of the nonel tube is provided in the control means or the start command input means. As the ignition means,
Conventional devices such as heating elements such as nichrome wire that heat when energized, or devices that ignite explosives or gases by applying a high voltage between two opposing electrodes with a slight gap between them Known ignition means can be adopted.

Examples of aircraft equipped with the automatic fire extinguishing system for aircraft of the present invention include heavy aircraft such as passenger planes, cargo planes, helicopters, and military planes, as well as light aircraft such as balloons and airships, and space rockets. There is no particular limitation.

Although there is no limitation on the place where the automatic fire extinguishing system for an aircraft of the present invention is installed, it is preferable to install the temperature sensor and the optical sensor in the lower part of the aircraft, the fuel tank, or the engine part such as the engine. When installed in the lower part of the aircraft, in a fuel tank, or in an engine part such as an engine, ignition of the leaked fuel can be instantly detected, and the fire can be extinguished early. Similarly, it is desirable to install a fire extinguisher so that the extinguishing agent can be sprayed in such a place.

[0079]

According to the automatic fire extinguishing system for an aircraft of the present invention, a fire caused by an unplanned landing accident is detected and a fire extinguishing agent is automatically sprayed, so that the fire can be extinguished early and surely. You can Therefore, it is possible to reduce the possibility of death or injury of the passengers of the aircraft that caused the accidental landing.

According to the aircraft automatic fire extinguishing system of the present invention, when an aircraft fire occurs, the fire can be extinguished by a very simple operation.

[Brief description of drawings]

FIG. 1 is a schematic explanatory view showing a specific example of an automatic fire extinguishing apparatus for aircraft according to the present invention.

FIG. 2 is a partial cross-sectional explanatory view showing a specific example of the temperature sensor according to the present invention.

FIG. 3 is a schematic explanatory view showing a specific example of an impact sensor according to the present invention.

FIG. 4 is a sectional view showing a specific example of an impact sensor according to the present invention.

FIG. 5 is a flow chart showing the operation of the control means according to the embodiment of the present invention.

FIG. 6 is a schematic explanatory view showing a specific example of a fire extinguisher activating means according to the present invention.

FIG. 7 is a schematic explanatory view showing another specific example of the aircraft automatic fire extinguishing apparatus of the present invention.

[Explanation of symbols]

1 ... Impact sensor, 2 ... Temperature sensor, 3 ...
・ Fire extinguisher starting means, 4 ... control means, 5 ... fire extinguisher, 51 ... start command input means

Claims (3)

[Claims] 1. An aircraft fire is detected by inputting a temperature sensor and / or impact sensor, a temperature detection signal output from the temperature sensor and / or an impact detection signal output from the impact sensor, and a start signal. And a fire extinguisher starting means that is driven by a starting signal output from the control means, and a fire extinguishing means that sprays a fire extinguishing agent by driving the fire extinguisher starting means. Automatic fire extinguisher for aircraft. 2. An optical sensor and / or an impact sensor, and an optical detection signal output from the optical sensor and / or
Alternatively, control means for detecting an aircraft fire by inputting an impact detection signal output from the impact sensor and outputting an activation signal, fire extinguisher activation means driven by the activation signal output from the control means, and extinguishing a fire An automatic fire extinguisher for an aircraft, comprising: an extinguishing means for spraying an extinguishing agent by driving a firearm starting means in the aircraft. 3. A start instruction input means for inputting a start instruction and outputting a start signal, a fire extinguisher starting means driven by a start signal output from the start instruction input means, and a fire extinguisher starting means for extinguishing a fire. An automatic fire-extinguishing system for an aircraft, comprising: a fire-extinguishing means for spraying the agent inside the aircraft.