Aircraft current cut-off device

Abstract

[Subject] Provide a current cut-off device for aircraft that can prevent accidents in which components such as propellers in operation come into contact with people when an aircraft falls, and prevent improper deployment of lift-generating components. [Solution] The current cut-off device 100 for aircraft includes a rupture plate 23 that cuts off a current supply circuit that electrically connects electronic equipment and circuits; an igniter 10 that damages the rupture plate 23 by directly or indirectly applying a destructive force (heat and pressure) toward the current supply circuit 30 to the rupture plate 23, thereby cutting off the current supply circuit 30 through the damaged rupture plate 23; and a control unit 24 that drives the igniter 10 when an abnormality is detected.

Description

Technical Field

[0001] The present invention relates to an aircraft current cut-off device for cutting off the current supply of electronic equipment installed on the aircraft. Background Art

[0002] In recent years, drones and other aircraft that have become popular are equipped with a circuit that includes an electronic device that operates a plurality of propellers and a battery (current supply source) that supplies current to the electronic device. The current from the battery is supplied to the electronic device, thereby operating the propellers.

[0003] Such aircraft are controlled to fly by multiple propellers, but there is a risk of falling when some propellers are not in operation due to, for example, a sudden strong wind. Therefore, there is a risk of the falling aircraft coming into contact with a person, causing a risk of injury to the person.

[0004] In addition, there is a proposal to install a circuit disconnection device, which is not used in aircraft, but is used to cut off the power supply to electronic equipment when an electric vehicle accidentally has an accident in order to prevent leakage, electric shock, etc. caused by the accident (for example, refer to patent document 1).

[0005] Patent document 1 discloses a circuit disconnection device that is suitable for a vehicle equipped with a circuit having a converter and a battery, and that disconnects the power supply from the battery to the converter when a collision of the vehicle is detected. The circuit disconnection device is equipped with a power supply circuit disconnector that is driven by a powder-type actuator that operates when a collision of the vehicle is detected. The operation of the power supply circuit disconnector disconnects the power supply circuit that electrically connects the battery and the converter.

[0006] Prior art literature

[0007] Patent Literature

[0008] Patent Document 1: Japanese Patent Application Publication No. 2011-25912 Summary of the invention

[0009] Problem that the invention aims to solve

[0010] As described above, in the event of an aircraft crash, an accident may occur in which the aircraft comes into contact with a person. In the unfortunate event of an accident in which the aircraft comes into contact with a person, it is particularly necessary to at least avoid an accident in which a running propeller comes into contact with a person. However, in the event of an aircraft crash, no effective means have been proposed to prevent accidents in which various components such as a running propeller come into contact with a person. In addition, there is a risk that a running propeller may become entangled with a string component connected to a lift-generating component (parachute, paraglider, etc.), thereby causing the lift-generating component to be poorly deployed.

[0011] Therefore, an object of the present invention is to provide a current cut-off device for an aircraft, which can prevent accidents such as propellers in operation from coming into contact with people when the aircraft falls, and prevent the lift-generating components from being poorly deployed.

[0012] Solution to the problem

[0013] (1) A current cut-off device for an aircraft, for use in an aircraft having an electric circuit, the circuit having an electronic device and a current supply source for supplying electric current to the electronic device, and cutting off the current supply from the current supply source to the circuit when an abnormality of the aircraft is detected, wherein the device comprises a rupture plate for cutting off the current supply circuit electrically connecting the electronic device and the circuit; a rupture force source for damaging the rupture plate by directly or indirectly applying a rupture force toward the current supply circuit to the rupture plate, thereby cutting off the current supply circuit through the damaged rupture plate; and a control unit for driving the rupture force source when the abnormality is detected.

[0014] According to the structure of (1) above, when an abnormality of the aircraft is detected, the destructive force source is driven by the control unit. The destructive force source directly or indirectly applies a destructive force (physical force such as heat or pressure) to the rupture plate toward the current supply circuit. As a result, the rupture plate can be damaged, and the current supply circuit can be cut off by the damaged and cracked rupture plate. As a result, the current supply to the electronic equipment of the aircraft can be cut off. As a result, when the aircraft falls, it is possible to prevent the occurrence of contact accidents between the running propeller and other components and people, fire, electric shock, and poor deployment of lift-generating components. In addition, when a part of the propeller stops, the flight is usually maintained by controlling the number of rotations of other propellers, but at this time, the load on the motor is too large, which may cause a failure. However, as described above, since the current supply can be forcibly cut off, the motor failure can be avoided. In addition, as the destructive force source, for example, an igniter, a gas bottle, or a hydraulic cylinder can be used. When the igniter is operated as a destructive force source when an abnormality is detected, the heat and pressure generated by the combustion of the gunpowder are applied to the rupture plate.

[0015] (2) In the aircraft current interruption device of (1) above, preferably, the rupture plate has one or more fragile portions.

[0016] According to the structure of (2) above, the rupture plate is easily broken by the pressure from the rupture force source, and the current supply circuit is easily cut off by the broken rupture plate.

[0017] (3) In the aircraft current cut-off device described in (2) above, the rupture plate is preferably arranged so that its center position is substantially consistent with the center axis of the rupture force source and its width is wider than the width of the rupture force source in the long side direction of the current supply circuit, and the fragile portion of the rupture plate is arranged at an eccentric position of the rupture plate.

[0018] According to the structure of (3) above, compared with the mode in which the central axis of the fragile portion and the rupture force source is substantially aligned, the destructive force generated by the destructive force source (e.g., heat and pressure generated by the igniter) can damage the rupture plate to a wider extent, making the rupture portion larger. As a result, the current supply circuit can be cut off, and at the same time, since each end of the cut current supply circuit can be drawn into the damaged rupture plate, the spacing distance of the cut portion of the current supply circuit can be increased. As a result, arc discharge can be prevented from occurring between one part of the cut current supply circuit and another part.

[0019] (4) The aircraft current cut-off device described in any one of (1) to (3) above may be provided between the rupture force source and the rupture plate, and may be configured to cover at least a portion of the rupture force source on the side where the rupture force is applied, and may further include a cup-shaped body having a bottom, wherein the bottom of the cup-shaped body is formed into a conical shape in an inwardly sunken manner, and is configured to be displaced toward the rupture plate side by receiving the rupture force, thereby transmitting the rupture force to the rupture plate.

[0020] According to the structure of (4) above, the pressure generated by the destructive force source can be made smaller than that without the cup-shaped body. That is, when the destructive force source is, for example, an igniter or a gas bottle-type component, the amount of gunpowder used can be reduced compared to when there is no cup-shaped body. That is, in this structure, because the bottom of the cup-shaped body is formed in a conical shape, the so-called Neumann effect is exerted, and the pressure increases. The displaceable bottom of the cup-shaped body is subjected to such pressure, and the bottom can increase the above pressure to a level that can damage the rupture plate and transmit it to the rupture plate. As a result, when the destructive force source is an igniter or a gas bottle-type component, cost reduction can be achieved.

[0021] (5) As another perspective, the aircraft current cut-off device described in any one of (1) to (3) above can be arranged between the rupture force source and the rupture plate, configured in a manner to cover at least a portion of the side of the rupture force source on which the rupture force is applied, and further has a cylinder with a bottom, and the bottom of the cylinder is provided with one or more fragile portions.

[0022] According to the configuration of (5) above, since the destination of the destructive force generated by the destructive force source can be limited by the cylindrical body, it is easy to apply the destructive force to the rupture plate while suppressing the loss of the destructive force.

[0023] (6) As another perspective, the aircraft current cut-off device described in any one of (1) to (3) above can be arranged between the rupture force source and the rupture plate, and can be configured in a manner that covers at least a portion of the side of the rupture force source on which the rupture force is applied, and further comprises a cylindrical body with an opening at the front end, and the bottom of the cylindrical body is provided with one or more fragile portions.

[0024] According to the configuration of (5), since the direction of the destructive force generated by the destructive force source can be restricted by the cylindrical body, it is easy to apply the destructive force to the rupture plate while suppressing the loss of the destructive force.

[0025] (7) In the aircraft current interruption device described in any one of (1) to (6) above, preferably, an insulating material is provided between the rupture plate and the current supply circuit.

[0026] According to the structure of (7) above, the insulating material is supplied to the current supply circuit together with the rupture plate or by receiving the above-mentioned destructive force from the rupture plate. Thus, the insulation of the current supply circuit is ensured. Thus, the reliability of current interruption can be improved.

[0027] (8) In the aircraft current interruption device of (7) above, preferably, the insulating material is held on the lower surface of the rupture plate.

[0028] According to the structure of (8) above, there is no need to provide another member for holding the insulating material.

[0029] (9) The aircraft current cut-off device of the present invention is used for an aircraft provided with an electric circuit, wherein the electric circuit has an electronic device and a current supply source for supplying electric current to the electronic device, and when an abnormality of the aircraft is detected, the current supply from the current supply source to the electronic device is cut off. The aircraft current cut-off device comprises an insulating material; a destructive force source, which cuts off the current supply circuit by applying pressure to the current supply circuit electrically connecting the electronic device and the electric circuit, and releases the insulating material into the cut-off current supply circuit by applying the pressure to the insulating material; and a control unit, which drives the destructive force source when the abnormality is detected.

[0030] According to the structure of (9) above, when an abnormality of the aircraft is detected, the destructive force source is driven by the control unit. The destructive force source can cut off the current supply circuit by applying a destructive force (physical force such as heat or pressure) to the current supply circuit. As a result, the current supply to the circuit can be cut off. As a result, it is possible to prevent the occurrence of contact accidents between the running propeller and other components and people, fire, electric shock, and poor deployment of the lift generating components when the aircraft falls. In addition, when a part of the propeller stops, the flight is usually maintained by controlling the number of rotations of other propellers, but at this time, the load on the motor is too large, which may cause a failure. However, as described above, because the current supply can be forcibly cut off, the motor failure can be avoided. In addition, the destructive force source can release the insulating material to the current supply circuit by applying the pressure to the insulating material. As a result, the reliability of the current cutoff can be improved. In addition, as the destructive force source, for example, an igniter can be used. By operating the igniter when an abnormality is detected, heat and pressure are generated by the combustion of gunpowder, and the heat and pressure are applied to the current supply circuit and the insulating material.

[0031] (10) In the aircraft current interruption device of (9) above, preferably, the destructive force source is an igniter.

[0032] According to the structure of (10) above, the destructive force source can be activated instantaneously and the weight of the destructive force source can be reduced.

[0033] (11) The aircraft current cut-off device of the present invention is used for an aircraft provided with an electric circuit, wherein the electric circuit has an electronic device and a current supply source for supplying electric current to the electronic device, and when an abnormality of the aircraft is detected, the aircraft current cut-off device cuts off the current supply from the current supply source to the electronic device, and comprises a rupture force source for cutting off the current supply circuit by applying a rupture force in the direction of the current supply circuit to a copper plate current supply circuit electrically connecting the electronic device and the electric circuit; and a control unit for driving the rupture force source when the abnormality is detected.

[0034] According to the structure of (11) above, when an abnormality of the aircraft is detected, the destructive force source is driven by the control unit. The destructive force source can cut off the current supply circuit by applying a destructive force (physical force such as heat or pressure) to the current supply circuit. In this way, the current supply to the circuit can be cut off. In this way, when the aircraft falls, it is possible to prevent the occurrence of contact accidents between the running propeller and other components and people, fire, electric shock, and poor deployment of the lift generating components. In addition, when a part of the propeller stops, the flight is usually maintained by controlling the number of rotations of other propellers, but at this time, due to the excessive load on the motor, it will cause a failure. However, as mentioned above, because the current supply can be forcibly cut off, the motor failure can be avoided. In addition, as the destructive force source, for example, an igniter can be used. By running the igniter when an abnormality is detected, heat and pressure are generated by the combustion of gunpowder, and the heat and pressure are applied to the current supply circuit.

[0035] Effects of the Invention

[0036] The present invention can provide a current cutoff device for aircraft, which can prevent accidents such as contact between a propeller and a person, fire, electric shock, and poor deployment of lift-generating components when the aircraft falls. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] [ Figure 1 ] is a cross-sectional view showing a current interruption device for aircraft according to a first embodiment of the present invention.

[0038] [ Figure 2 ] is shown Figure 1 Illustration of a state in which a current supply circuit is cut off by a rupture plate.

[0039] [ Figure 3 ] is a cross-sectional view showing a current interruption device for aircraft according to a second embodiment of the present invention.

[0040] [ Figure 4 ] is shown Figure 3 (a) is a plan view showing an example of a fragile portion of a rupture plate, and (b) is a plan view showing a modified example of the fragile portion of the rupture plate.

[0041] [ Figure 5 ] is a cross-sectional view showing a current interruption device for aircraft according to a third embodiment of the present invention.

[0042] [ Figure 6 ] is a cross-sectional view showing a current interruption device for aircraft according to a fourth embodiment of the present invention.

[0043] [ Figure 7 ](a) is a diagram showing Figure 6 (b) and (c) are plan views showing an example of a fragile portion at the bottom of a cylindrical body, and (b) and (c) are plan views showing modified examples of the fragile portion.

[0044] [ Figure 8 ] is a cross-sectional view showing a current interruption device for aircraft according to a fifth embodiment of the present invention.

[0045] [ Fig. 9 ] is shown Figure 8 Illustration of a state in which a current supply circuit is cut off by a rupture plate.

[0046] [ Fig.10 ] is a cross-sectional view showing a current interruption device for aircraft according to a sixth embodiment of the present invention.

[0047] [ Fig.11 ] is a cross-sectional view showing a current interruption device for aircraft according to the seventh embodiment of the present invention. DETAILED DESCRIPTION

[0048] The following is an explanation of an aircraft current cutoff device according to an embodiment of the present invention with reference to the accompanying drawings. The aircraft current cutoff device according to this embodiment is used in an aircraft provided with a circuit, the circuit having an electronic device and a current supply source for supplying current to the electronic device, and when an abnormality such as the fall of the aircraft is detected, the current supply from the current supply source to the electronic device is cut off. In addition, in the present invention, the current supply source is not particularly limited, and examples thereof include a current supply source using a Li-ion battery, a Li-ion polymer battery, a fuel cell, hydrogen fuel, gasoline, gas, sunlight, etc. as a generating source, or a generator, etc.

[0049] (First embodiment)

[0050] like Figure 1 As shown, the current cut-off device 100 for aircraft of the present embodiment comprises an igniter 10, which is an example of a destructive force source (power source); a cut-off chamber 20, which has an internal space; a rupture plate 23, which is damaged and cracked by the heat and pressure generated by the operation of the igniter, while cutting off the current supply circuit 30; and a control unit 24, which drives the igniter 10 when an aircraft abnormality is detected.

[0051] A known igniter can be used as the igniter 10. The igniter 10 is a flame generating component, and includes an ignition powder (not shown) that ignites and burns to generate flames during operation; an ignition unit 11 that includes a resistor (not shown) for igniting the ignition powder; and a pair of terminal pins 12, 12 connected to the ignition unit 11.

[0052] The rupture plate 23 is formed into a circular shape in a top view, for example, and is disposed in the cutoff chamber 20 and below the igniter 10. The rupture plate 23 needs to be easy to crack and have appropriate strength, so it can be made of a lightweight metal such as iron or aluminum. In addition, the rupture plate 23 can also be made of a non-conductive material, such as a hard resin material such as hard plastic or precision ceramics.

[0053] The width of the rupture plate 23 is wider than the width of the igniter 10 in the longitudinal direction of the current supply circuit 30. The igniter 10 is held on the upper wall of the cutoff chamber 20 so that the generated flame can be released toward the rupture plate 23 located at a lower position.

[0054] When an abnormality of the aircraft is detected, a predetermined amount of current is caused to flow through the resistor via a pair of terminal pins 12, 12 under the control of the control unit 24. When the current flows through the resistor, Joule heat is generated in the resistor, and the ignition charge begins to burn. The high-temperature flame generated by the combustion causes a squib cup (not shown) containing the ignition charge to rupture. In the igniter 10, the time from the current flowing through the resistor to the operation is generally less than 2 milliseconds when a nickel-chromium alloy wire is used as the resistor.

[0055] The peripheral wall of the cutting chamber 20 is provided with a through hole 21, and the other part of the peripheral wall is provided with a through hole 22. The current supply circuit 30 is bridged through the through holes 21 and 22. The current supply circuit 30 is composed of, for example, a metal plate or a metal wire, one end of which is connected to a battery (not shown) of the circuit, and the other end thereof is in contact with an electronic device (not shown) of the aircraft.

[0056] In the above-mentioned structure, when an abnormality of the aircraft is detected, a predetermined amount of current is supplied to the pair of terminal pins 12, 12 of the igniter 10 by the control of the control unit 24, and the rupture plate 23 is damaged due to the heat and pressure generated by the operation of the ignition unit 11. At this time, the rupture plate 23 is damaged in such a manner that its central portion is cracked and bent toward the current supply circuit 30. Then, the current supply circuit 30 is disconnected as described above by the rupture plate damaged as described above. Figure 2 In the present invention, it is desirable that the object of the current supply circuit 30 to be cut off is the wiring drawn out from the positive electrode portion.

[0057] As described above, by the current cut-off device 100 for aircraft of the present embodiment, when an abnormality of the aircraft is detected, the igniter 10 as a destructive force source is operated by the control unit 24. The igniter 10 applies heat and pressure to the rupture plate 23 toward the current supply circuit 30. As a result, the rupture plate 23 can be damaged and cracked, and the current supply circuit 30 is cut off by the cracked portion of the cracked rupture plate 23. As a result, the current supply to the electronic equipment of the aircraft can be cut off. As a result, when the aircraft falls, it is possible to prevent the occurrence of a contact accident between the running propeller and the like and a person, fire, electric shock, and poor deployment of the lift generating component. In addition, when a part of the propeller stops, the flight is usually maintained by controlling the number of rotations of the other propellers, but at this time, the load on the motor is too large, which may cause a failure. However, as described above, since the current supply can be forcibly cut off, the motor failure can be avoided.

[0058] (Second embodiment)

[0059] Next, an aircraft current interruption device according to a second embodiment will be described with reference to the drawings.

[0060] Figure 3 2 is a cross-sectional view showing an aircraft current interruption device 200 according to a second embodiment. Figure 3 Unless otherwise specified, Figure 1 The parts with the same sign in the last two digits are Figure 1 The same is true for the drawings in the following embodiments.

[0061] exist Figure 3 In the aircraft current interruption device 200, the rupture plate 123 is provided with a fragile portion. Figure 4 As shown in FIG. 2A , the rupture plate 123 is provided with a fragile portion 25. The fragile portion 25 is arranged at a position away from the central axis of the rupture plate 123, in other words, away from the igniter 110 (see FIG. 2B ). Figure 3 ) of the central axis (a position not passing through the central axis position, an eccentric position of the rupture plate 123). A plurality of such fragile portions 123 may be provided.

[0062] Thus, according to the aircraft current interruption device 200 of the present embodiment, the rupture plate 123 is easily damaged and ruptured by the pressure from the igniter 110. Then, the current supply circuit 130 is easily interrupted by the ruptured portion of the rupture plate 123.

[0063] In addition, in the aircraft current cut-off device 200, the fragile portion 25 of the rupture plate 123 is arranged at a position away from the central axis of the igniter 110 (a position that does not pass through the central axis position). Therefore, compared with the embodiment in which the fragile portion is located directly below the igniter 110, the entire fragile portion is easily subjected to the pressure of the igniter 110. Therefore, compared with the embodiment in which the fragile portion is located directly below the igniter 110, the rupture plate 123 can be damaged to a greater extent and the cracked portion can be larger. As a result, Figure 3 As shown, when the current supply circuit 130 is cut off, each end of the cut current supply circuit 130 can be drawn into the ruptured rupture plate 123, so that the spacing distance of the cut portion of the current supply circuit 130 can be increased. As a result, arc discharge can be prevented from occurring between one part of the cut current supply circuit and another part.

[0064] In addition, replace Figure 4 (a) If Figure 4 As shown in (b), the rupture plate 123a may be provided with a straight line bent into a "く"-shaped fragile portion 26. In this case, the fragile portion 26 does not pass through the central axis position of the rupture plate 123a, but is arranged at a position away from the central axis position. Figure 4 (b) Rupture plate ratio Figure 4 In the case of (a), cracking is more likely to occur, so the current supply circuit 30 is more likely to be cut off.

[0065] (Third embodiment)

[0066] Next, an aircraft current interruption device according to a third embodiment will be described with reference to the drawings.

[0067] Figure 5 It is a cross-sectional view showing an aircraft current interruption device 300 according to a third embodiment. Figure 5 The aircraft current interruption device 300 is provided between the igniter 210 and the rupture plate 223, and has a cup-shaped body 40 configured to cover at least a portion of the pressure-applying side of the igniter 210. In the initial state, the cup-shaped body 40 has a conical bottom 41 formed with a pointed top (depressed inward).

[0068] In the above structure, the bottom 41 is subjected to pressure from the igniter 210, such as Figure 5 As shown by the double-dotted line, the circuit 230 is displaced toward the rupture plate 223, deformed downward into a convex shape, and further cracked, thereby indirectly transmitting pressure to the rupture plate 223. In addition, the method of cutting off the current supply circuit 230 by the rupture plate 223 under pressure is similar to the above-mentioned Figure 1 The main points are the same.

[0069] By using the current cut-off device 300 for aircraft of this embodiment, if the same pressure as that of the first embodiment is desired, the pressure generated by the igniter 210 can be made smaller than that of the first embodiment. That is, when the same pressure as that of the first embodiment is desired, the amount of gunpowder used in the igniter 210 can be less than that of the first embodiment. That is, in this structure, because the bottom 41 of the cup-shaped body 40 is formed in a conical shape, the so-called Neumann effect is exerted, and the pressure increases. The displaceable bottom 41 of the cup-shaped body 40 is subjected to such a pressure of the igniter 210, and the bottom 41 can increase the above-mentioned pressure to a force that can damage the rupture plate 223 and cause it to crack, and transmit it to the rupture plate 223. As a result, compared with the first embodiment, it is possible to reduce the cost of the igniter 210 (reduce the gunpowder cost of the igniter 210).

[0070] (Fourth embodiment)

[0071] Next, an aircraft current interruption device according to a fourth embodiment will be described with reference to the drawings.

[0072] Figure 6 It is a cross-sectional view showing an aircraft current interruption device 400 according to a fourth embodiment. Figure 6 The aircraft current interruption device 400 is provided between the igniter 310 and the rupture plate 323 , is arranged to cover at least a portion of the pressure-applying side of the igniter 310 , and includes a cylinder 42 having a bottom 43 .

[0073] like Figure 7 As shown in (a), the bottom 43 of the cylinder 42 is provided with one or more fragile parts 44. These fragile parts 44 are arranged radially with the center of the bottom 43 formed in a circular shape in a top view as a reference. Figure 7 As shown in (b), the bottom 143 is provided with a plurality of fragile portions 144, which may also be Figure 7 As shown in (c), the bottom 243 is provided with a fragile portion 244.

[0074] According to the aircraft current cutoff device 400 of the present embodiment, the destination of the pressure generated by the igniter 310 can be limited by the cylinder 42, so that the pressure loss can be suppressed and the pressure can be easily applied to the rupture plate 323. In addition, the rupture plate 323 can be damaged by the pressure whose pressure loss is suppressed, and the current supply circuit 330 can be easily cut off by the high pressure from the rupture plate 323.

[0075] (Fifth embodiment)

[0076] Next, an aircraft current interruption device according to a fifth embodiment will be described with reference to the drawings.

[0077] Figure 8FIG. 4 is a cross-sectional view showing an aircraft current interruption device 500 according to a fifth embodiment. Figure 8 In the aircraft current interruption device 500 , the insulating material 50 is held on one surface of the rupture plate 423 on the current supply circuit 430 side.

[0078] Generally speaking, the insulating material 50 is preferably a compound with a low dielectric constant. For example, the insulating material 50 is preferably a polymer material, a resin material, or a hydrocarbon.

[0079] Examples of polymer materials include polyamide, polyethylene, polyisobutylene, polyvinyl chloride, polychlorotrifluoroethylene, polyvinyl acetate, polyacrylate, polystyrene, polyethylene terephthalate, polycarbonate, polyphenylene ether, polyphenylene ether resin, modified polyphenylene ether (m-PEE), ethylene-tetrafluoroethylene copolymer, polyvinylidene fluoride (polyfluoride vinylidene), polypropylene, polymethylpentene, polyphenylene sulfide, polybutylene terephthalate, polybutene, polycaprolactam, polymonochloro, polystyrene, polysulfonic acid, polyvinyl alcohol, cellulose acetate, cellulose nitrate, ethyl cellulose, dextrin, polystyrene particles, polypropylene particles, and polyethylene particles.

[0080] Examples of the resin material include alkyd resin, epoxy resin, tetrafluoroethylene resin, vinyl fluoride resin, phenolic resin, urea-formaldehyde resin, melamine resin, unsaturated polyester resin, vinyl ester resin, diallyl phthalate resin, epoxy resin, silicone resin, xylene resin, amino resin, aniline resin, guanamine resin, acrylic resin, polyetherimide resin, acrylonitrile-butadiene-styrene (ABS) resin, ETFE resin, fluororesin, PET resin, polyacetal resin, polyamide-imide resin, polyimide resin, polyurethane resin, PEK resin, polyethersulfone resin, polyetherimide resin, polyolefin resin, polytetrafluoroethylene resin, isobutyl resin, and PEEK resin.

[0081] Examples of hydrocarbons include cycloheptasiloxane, cyclohexane, cyclopentane, decane, decene, dimethylpentane, dimethyl-2-hexane, dimethylheptane, dimethylpentane, 2-methyl-2-butene, butane, kerosene, isooctane, gasoline, dipentene, styrene, xylene, menthol, hexane, naphthalene, pentadiene, pentane, liquefied petroleum gas, dodecane, dodecyne, ), ethylene pentane, petrolatum, xylene, turpentine, undecane, docosane, cis-3-hexane, acetylene, dichlorostyrene, ethylcyclobutane, heptane, hexene, methylcyclopentane, trimethyl-3-heptene, octane, trans-3-hexyne, methylbutane, and microhexane.

[0082] In addition, as other examples of the insulating material 50, an aromatic compound, a halogen compound, and a gas stored in a predetermined storage portion can be used.

[0083] Examples of the aromatic compound include benzene, ethyltoluene, isobutylbenzene, diphenylmethane, diphenylethane, biphenyl, isopropylbenzene, cumene, thiophene, trimethylbenzene, trinitrobenzene, decalin, triphenylmethane, p-isopropyltoluene, dichlorobenzene, limonene, camphene, diethyl succinylsuccinate, dimethylquinoxaline, dioxane, eugenol, mesitylene, nitrotoluene, nonane, p-cymene, phenanthrene, phenylcarbamate, styrene, propylbenzene, 1,2,4-trimethylbenzene, quinoline, and terpineol.

[0084] Examples of the halogen compound include arsine, bromine, chlorine, fluorine, boron bromide, freon, trichloropropane, and naphtha.

[0085] Examples of the gas include argon, carbon dioxide, carbon disulfide, nitrous oxide, nitrogen tetroxide, nitrogen, liquid air, hydrogen, methane, deuterium, oxygen, nitrous oxide, sulfur hexafluoride, chlorofluorocarbons, and carbon dioxide.

[0086] Furthermore, other examples of the insulating material 50 include aluminum powder, ammonia, carbon tetrachloride, cholesterol, isoprene, lead acetate, lead tetrachloride, mercury, diethylmercury, phosphorus, phosphorus pentachloride, diethylzinc, copper oleate, iron ore, cotton, aluminum hydroxide, aluminum oleate, asphalt, diamylamine, 2,7-dimethyloctane (ジイソアミル), diisopentene, aluminum fluoride, hexanoic acid, caprolactam, cyclohexanecarboxylic acid, decamethylcyclopentasiloxane, decamethyltetrasiloxane, diisopropylamine, dodecamethylcyclohexylsiloxane, dodecamethylpentasiloxane, hard rubber, tetrafluoroethylene, iron oleate, ferrochrome, fly ash, acidic clay, germanium tetrachloride (tetrachlorinated glume), heptanoic acid, hexamethyldisiloxane, hydrocyanic acid, isovaleric acid, isobutyric acid, isophthalic acid, and isopropylamine. , linoleic acid, methylal, insulating stone, butyl formate, butyl acetate, octamethylcyclotetrasiloxane, oleic acid, palmitic acid, cycloalkanes, paraffin, chlorinated paraffin, perlite, phenyl-1-propane, aluminum silicate, silicon tetrachloride, silicone oil, sodium oleate, sodium phosphate, stearic acid, stearin, tetrachloroethylene, tetrafluoroethylene, tetranitromethane, titanium chloride, triethylaluminum, zinc (II) oxide, valeric acid, shell sand, ferrosilicon, nitrogen (liquid), ferrite (ferrate) (powder), iron (II) oxide, precipitated silica (toxil), telluric acid (tetrakal acid), terephthalic acid, ferrite (powder), PVC fluid, PE cube (PE cube), calcium carbonate, polycarbonate powder, propane (liquid), carbaryl, talc, calcium hypochlorite, calcium phosphate.

[0087] Among the above-mentioned insulating materials 50, a thermosetting resin that can block the cut-off portion of the current supply circuit 430 by curing with the heat generated by gunpowder is more preferred. Therefore, the insulating material 50 is preferably a phenolic resin, a melamine resin, a urea-formaldehyde resin, an epoxy resin, an unsaturated polyester resin, an alkyd resin, a silicone resin, a polyurethane resin, a diallyl phthalate resin, a furan resin, a ketone resin, a xylene resin, a polyimide resin, a polybismaleimide-triazine, a (benzo)guanamine resin, and a vinyl ester resin, and an epoxy resin with good adhesion to metal is more preferred. In addition, among the above-mentioned epoxy resins, there are a one-component type that is cured by a reaction of a curing agent contained in the present reagent by heating, and a two-component type that is cured by mixing the present reagent and the curing agent. Although the one-component type begins to cure once heated, it may cure when exposed to direct sunlight from above and the temperature becomes high, but because two storage containers are not required, it has the advantage of being lightweight and miniaturized. On the contrary, the two-component type will not cure even if heated, so it has the reliability of being able to maintain the original state for a long time. Therefore, one-component type and two-component type can be appropriately selected according to the application.

[0088] In the aircraft current interruption device 500, the insulating material 50 receives the pressure generated by the igniter 410 together with the rupture plate 423 or from the rupture plate 423, such as Fig. 9 As shown, the current is supplied to the current supply circuit 430 cut off by the rupture plate 423. As a result, the insulation of the cut-off current supply circuit 430 is ensured. Thus, the reliability of current cutoff of the aircraft current cutoff device 500 can be further improved.

[0089] (Sixth Implementation Method)

[0090] Next, an aircraft current interruption device according to a sixth embodiment will be described with reference to the drawings.

[0091] Fig.10 2 is a cross-sectional view showing an aircraft current interruption device 600 according to a sixth embodiment. Fig.10 In the aircraft current interruption device 600 , no rupture plate is provided, and the insulating material 150 is retained at the lower part of the igniter 510 .

[0092] In the aircraft current cut-off device 600, the insulating material 150 is supplied (released) to the current supply circuit 530 cut off by the pressure from the igniter 510. As a result, the cut-off current supply circuit 530 is covered with the insulating material 150, and the insulation of the cut-off current supply circuit 530 is ensured, as in the fifth embodiment. As a result, the reliability of the current cut-off of the aircraft current cut-off device 600 can be further improved.

[0093] (Seventh Implementation Method)

[0094] Next, an aircraft current interruption device according to a seventh embodiment will be described with reference to the drawings.

[0095] Fig.11 FIG. 2 is a cross-sectional view showing a current interruption device 700 for aircraft according to a seventh embodiment. Fig.11 In the aircraft current cut-off device 700, no rupture plate and insulating material are provided. In addition, in this embodiment, the current supply circuit 630 is composed of a copper plate (busbar), one end and the other end of which are connected to the terminal 622 of the terminal plate 621.

[0096] When an abnormality of the aircraft is detected by the current cut-off device 700 for the aircraft, the destructive force source, i.e., the igniter 610, is driven by the control unit 624. The igniter 610 can cut off the current supply circuit 630 by applying a destructive force (physical force such as heat or pressure) to the current supply circuit 630. In this way, the current supply to the circuit can be cut off. In this way, when the aircraft falls, it is possible to prevent accidents such as contact between the running propeller and the human body, fire, electric shock, and poor deployment of the lift-generating components. In addition, when a part of the propeller stops, the flight is usually maintained by controlling the number of rotations of the other propellers, but at this time, the load on the motor is too large, which may cause a failure. However, as described above, because the current supply can be forcibly cut off, motor failure can be avoided.

[0097] The above describes the embodiments of the present invention based on the drawings, but the specific structure is not limited to the above embodiments. The scope of the present invention is not limited to the description of the above embodiments, but is shown by the claims, and further includes all changes within the scope of the same concept as the patent application, etc.

[0098] In the above-mentioned embodiments, an igniter is used as a destructive force source, but it is not limited to this. For example, a hydraulic cylinder type (a component that drives a piston, etc., or damages a rupture plate, or causes insulating materials to fly) that receives a command signal from the control unit to operate the hydraulic cylinder to generate a destructive force; a gas cylinder type that receives a command signal from the control unit to open a gas cylinder to generate the same destructive force (pressure) as the above-mentioned igniter, and other destructive force sources may be used.

[0099] In addition, the bottom portion 41 formed in a conical shape in the third embodiment may be provided with Figure 7 (a)-(c) show the fragile part. As a result, the bottom 41 can be smoothly destroyed, and the rupture plate can be damaged and cracked more efficiently. As a result, the current supply circuit can be destroyed more easily.

[0100] In the fourth embodiment, the cylinder 42 is closed with the bottom 43, but the present invention is not limited thereto and the bottom 43 may not be provided. In this case, since the flame and pressure generated by the igniter can be controlled in one direction, the rupture plate can be more easily damaged and cracked than when there is no cylinder. As a result, the current supply circuit can be more easily destroyed.

[0101] In the fifth and sixth embodiments described above, a gas generating agent may be mixed with the insulating material 50, 150. This can prevent arc discharge caused by the residue of the gas generating agent or the generated gas.

[0102] In addition, in the rupture plate of the first, second and fifth embodiments, the cut-off chamber may be divided into two sections, and the cut-off chamber on the igniter side may be sealed with a sealing member, etc. Thus, the pressure generated by the igniter can be more effectively transmitted to the rupture plate, and the current supply circuit can be more easily destroyed.

[0103] In addition, in the above-mentioned seventh embodiment, the busbar is directly cut off by the firepower of the igniter, but a material such as hard rubber can also be set on the pressure generating side of the igniter, and the pressure of the driven igniter can be used to scatter the hard rubber and other materials to indirectly cut off the busbar.

[0104] In the aircraft current cutoff device of each embodiment provided with a rupture plate, a piston may be provided on the wiring side of the rupture plate, and when the igniter operates to rupture the rupture plate, the piston is pushed out to cut off the current (cut off the wiring).

[0105] In addition, in each embodiment, a parachute or the like wire may be used instead of the wiring, and when the igniter is operated to rupture the rupture plate, the wire is cut off. In this way, the parachute or the like can be separated as needed.

[0106] Explanation of symbols

[0107] 10, 110, 210, 310, 410, 510, 610 Ignitor

[0108] 11, 111, 211, 311, 411, 511, 611 Ignition Department

[0109] 12, 112, 212, 312, 412, 512, 612 terminal pins

[0110] 20, 120, 220, 320, 420, 520, 620 cutting chamber

[0111] 21, 121, 221, 321, 421, 521 through holes

[0112] 22, 122, 222, 322, 422, 522 through holes

[0113] 23, 123, 123a, 223, 323, 423 Rupture plate

[0114] 24, 124, 224, 324, 424, 524, 624 Control unit

[0115] 25, 26 Vulnerable Department

[0116] 30, 130, 230, 330, 430, 530, 630 current supply circuit

[0117] 40 cups

[0118] 41 Bottom of cup

[0119] 42 Cylinder

[0120] 43, 143, 243 Bottom of the cylinder

[0121] 44, 144, 244 Vulnerable Ministry

[0122] 50, 150 Insulation material

[0123] 100, 200, 300, 400, 500, 600 Aircraft current cut-off device

[0124] 621 Terminal Block

[0125] 622 terminal

Claims

1. An aircraft current cut-off device, which is used in an aircraft provided with a circuit, the circuit having an electronic device and a current supply source for supplying current to the electronic device, and cuts off the current supply from the current supply source to the electronic device when an abnormality of the aircraft is detected, characterized in that have a rupture plate which cuts off a current supply circuit electrically connecting the electronic device and the circuit, a rupture force source that directly or indirectly applies a rupture force toward the current supply circuit to the rupture plate to damage the rupture plate, thereby cutting off the current supply circuit through the damaged rupture plate, a control unit that drives the rupture force source when the abnormality is detected, and A cup-shaped body with a bottom is provided between the rupture force source and the rupture plate and is arranged so as to cover at least a portion of the rupture force source on the side where the rupture force is applied. The bottom of the cup-shaped body is formed in an inwardly depressed conical shape, and is configured to be displaced toward the rupture plate side upon receiving the rupture force, thereby transmitting the rupture force to the rupture plate.

2. The aircraft current cut-off device according to claim 1, characterized in that The rupture plate is provided with one or more fragile parts.

3. The aircraft current cut-off device according to claim 2, characterized in that The rupture plate is arranged in such a manner that the central position thereof is substantially consistent with the central axis of the rupture force source and the width thereof is wider than the width of the rupture force source in the long side direction of the current supply circuit. The fragile portion of the rupture plate is disposed at an eccentric position of the rupture plate.

4. The aircraft current cut-off device according to any one of claims 1 to 3, characterized in that An insulating material is provided between the rupture plate and the current supply circuit.

5. The aircraft current cut-off device according to claim 4, characterized in that The insulating substance is held on the lower surface of the rupture plate.

6. The aircraft current cut-off device according to any one of claims 1 to 3, characterized in that have Insulating materials, A rupture force source applies a rupture force to a current supply circuit electrically connecting the electronic device and the circuit to cut off the current supply circuit, and applies the rupture force to the insulating material to release the insulating material into the cut-off current supply circuit.

7. The aircraft current cut-off device according to any one of claims 1 to 3, characterized in that The source of the rupture force is an igniter.

8. The aircraft current cut-off device according to any one of claims 1 to 3, characterized in that have A rupture force source applies a rupture force in a direction of a copper plate current supply circuit electrically connecting the electronic device and the circuit, thereby cutting off the current supply circuit.

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