Circuit abnormality diagnosis device, current generation device, deployed body ejection device for aircraft, airbag device for aircraft, and cutting device for aircraft

Abstract

[Problem] To provide a circuit abnormality diagnosis device that can simply and easily diagnose a circuit abnormality, a current generation device including the circuit abnormality diagnosis device, a deployed body ejection device for an aircraft including the current generation device, an airbag device for an aircraft including the current generation device, and a cutting device for an aircraft including the current generation device. [Solution] The circuit abnormality diagnosis device 110 includes an arithmetic unit 1, a power supply for inspection 2, a rectifying element 3, overcurrent prevention resistors 4 and 5, a voltage boosting unit 6, a voltage reading unit 7, and a light emitting unit 8, and diagnoses whether the circuit is abnormal at a predetermined time (including at the initial installation) or at every predetermined time. The circuit abnormality diagnosis device 110 diagnoses (judges) that it is in a normal state when the voltage value is within a range that is equal to or higher than a first voltage value V1 and equal to or lower than a second voltage value V2, which are preset to represent a normal circuit voltage value range, judges that it is in a short-circuit state when the voltage value is lower than the voltage value V1, and judges that it is in an open-circuit state when the voltage value is higher than the voltage value V2.

Description

Technical Field

[0001] The present invention relates to a circuit abnormality diagnosis device, a current generation device including the circuit abnormality diagnosis device, a deployed body ejection device for an aircraft including the current generation device, an airbag device for an aircraft including the current generation device, and a cutting device for an aircraft including the current generation device. Background Art

[0002] In recent years, with the development of autonomous control technology and flight control technology, the industrial use of aircraft has been accelerating. In the above-mentioned aircraft, as described in Patent Document 1 below, a safety mechanism is provided that deactivates a safety device (such as an airbag device) by a safety signal during normal operation.

[0003] In addition, when an igniter is used in the safety device of the aircraft described in Patent Document 1 below, it is necessary to periodically diagnose whether there is an abnormality in the circuit including the igniter circuit not only before operation but also during operation. Conventionally, as a method for diagnosing an abnormality in this circuit, a predetermined voltage is usually applied to the circuit, a weak current (a current that does not cause the igniter to operate) flowing through the circuit is measured, it is determined whether it is normal (whether it is a predetermined circuit resistance value), and it is confirmed whether there is a poor contact (open circuit).

[0004] Prior Art Documents

[0005] Patent Document 1: Japanese Patent No. 5985784 Summary of the Invention

[0006] Problems to be Solved by the Invention

[0007] However, when the accuracy of the current sensor used for measuring the weak current is low, the above-mentioned abnormality diagnosis method cannot distinguish whether a short circuit has occurred in the circuit or it is in a normal state. In addition, in recent years, it has been desired to perform the above-mentioned abnormality diagnosis more easily using a simpler device without using a high-precision current sensor with a high introduction cost.

[0008] Therefore, in view of the above background, an object of the present invention is to provide a circuit abnormality diagnosis device that can easily perform circuit abnormality diagnosis without using a high-precision current sensor with a high cost, a current generation device including the circuit abnormality diagnosis device, a deployed body ejection device for an aircraft including the current generation device, an airbag device for an aircraft including the current generation device, and a cutting device for an aircraft including the current generation device.

[0009] Means for Solving the Problems

[0010] (1) The present invention is a circuit abnormality diagnosis device for diagnosing whether a circuit in a safety device for an aircraft having an igniter and a circuit connected to the igniter is abnormal. It is characterized in that it has a power supply that can apply a check voltage to the circuit; an arithmetic unit that controls the on / off of the power supply; a first overcurrent prevention unit that is electrically connected in series with the power supply to prevent overcurrent from flowing through the circuit; a voltage boosting unit that is electrically connected in parallel with the circuit unit to boost the voltage to a predetermined order; a voltage reading unit that is electrically connected in series with the voltage boosting unit to read the voltage value (hereinafter referred to as the voltage value) boosted by the voltage boosting unit; a second overcurrent prevention unit that is electrically connected in series with the voltage reading unit on the upstream side of the voltage reading unit to prevent overcurrent from flowing through. The arithmetic unit receives the voltage value information from the voltage reading unit and determines that the voltage value is within a first voltage value V of a voltage value range preset to indicate that the circuit is normal 1 The above second voltage value V 2 In the following range, it is determined to be in a normal state. When the voltage value is lower than the voltage value V 1 It is determined to be in a short-circuit state when, and when the voltage value is higher than the voltage value V 2 It is determined to be in an open-circuit state when it is high.

[0011] (2) From another perspective, the present invention can be a circuit abnormality diagnosis device for diagnosing whether a circuit in a safety device for an aircraft having an igniter and a circuit connected to the igniter is abnormal. It has a power supply that can apply a check voltage to the circuit; a first overcurrent prevention unit that is electrically connected in series with the power supply to prevent overcurrent from flowing through the circuit; a voltage boosting unit that is electrically connected in parallel with the circuit unit to boost the voltage; an arithmetic unit that controls the switch unit of the power supply and is electrically connected in series with the voltage boosting unit to read the voltage value (hereinafter referred to as the voltage value) boosted by the voltage boosting unit; a second overcurrent prevention unit that is electrically connected in series with the voltage reading unit on the upstream side of the voltage reading unit to prevent overcurrent from flowing through. The arithmetic unit determines that the voltage value is within a predetermined voltage value V of a voltage value range preset to indicate that the circuit is normal 1 Above V 2 In the following range, it is determined to be in a normal state. When the voltage value is lower than the voltage value V 1 It is determined to be in a short-circuit state when, and it is determined to be in an open-circuit state when the voltage value is higher than the voltage value V2.

[0012] (3) In the circuit abnormality diagnosis device of the above (1) or (2), it is preferable to electrically connect a rectifying element for preventing reverse current in series to the downstream side of the power supply and the upstream side of the first overcurrent prevention unit.

[0013] (4) In the circuit abnormality diagnosis device described in the above (1) to (3), it is preferably provided with a light emitting unit that receives the determined abnormality diagnosis result information from the arithmetic unit and can emit light of a color corresponding to the type of the determined result information when receiving the determined result information from the arithmetic unit.

[0014] (5) The current generation device of the present invention is characterized in that it includes the circuit abnormality diagnosis device described in any one of the above (1) to (4); a power storage unit; a switch unit that is electrically connected to the downstream side of the power storage unit and can discharge the current stored in the power storage unit on the downstream side, and when the arithmetic unit determines that the aircraft is in a flight state and in the short circuit state or the open circuit state, it sends an operation signal for the discharge to the switch unit.

[0015] (6) In the current generation device of (5) above, it is preferable that the power storage unit is a capacitor.

[0016] (7) In the current generation device described in the above (5) or (6), it is preferable to provide a physical switch unit that physically conducts or disconnects the power supply between the circuit and the switch unit in the circuit.

[0017] (8) The present invention is a deployed body ejection device for an aircraft mounted on an aircraft, and is characterized in that it includes the current generation device described in any one of the above (5) to (7); a deployed body; an igniter that operates when the current generated by the operation of the current generation device is energized, and generates a driving force for ejecting the deployed body; a storage unit that internally stores the deployed body and the igniter.

[0018] (9) The present invention is an airbag device for an aircraft mounted on an aircraft, and is characterized in that it includes the current generation device described in any one of the above (5) to (7); an airbag; a gas generator that has an igniter and a gas generating agent, and operates when the current generated by the operation of the current generation device is energized to the igniter, burns the gas generating agent, and generates a gas for inflating the airbag; a storage unit that internally stores the airbag and the gas generator.

[0019] (10) The present invention is a cutting device for an aircraft mounted on an aircraft, and is characterized by including a conductive part or a connecting member; an igniter that operates when the current generated by the operation of the current generation device is energized, and generates heat or a driving force for cutting the conductive part or the connecting member; a driving cutting part that is driven by the driving force when the igniter generates the driving force.

[0020] Effects of the invention

[0021] According to the present invention, circuit abnormalities can be easily diagnosed without using a high-precision current sensor with high cost. In addition, when an abnormality diagnosis is determined, a safety device for an aircraft (ejection device, airbag device, cut-off device, etc.) can be automatically operated. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 FIG. showing a cross-sectional view of an ejection device for an aircraft deployment body according to a first embodiment of the present invention.

[0023] Figure 2 Showing Figure 1 the block diagram of the circuit abnormality diagnosis device in the ejection device for an aircraft deployment body.

[0024] Figure 3 Showing Figure 1 the front view of the aircraft to which the ejection device for an aircraft deployment body is applied.

[0025] Figure 4 FIG. showing the block diagram of the current generation device in the ejection device for an aircraft deployment body according to a second embodiment of the present invention.

[0026] Figure 5 Showing Figure 4 an example of the physical switch section.

[0027] Figure 6 FIG. showing the front view of the state after operation of the airbag device for an aircraft according to a third embodiment of the present invention in the applicable aircraft.

[0028] Figure 7 FIG. showing a cross-sectional view of the cut-off device for an aircraft according to a fourth embodiment of the present invention.

[0029] Figure 8 Showing Figure 7 the cross-sectional view after operation of the cut-off device for an aircraft. DETAILED DESCRIPTION OF THE INVENTION

[0030] <First Embodiment>

[0031] The following is based on Figures 1 to 3 to describe the first embodiment of the present invention.

[0032] As Figure 1 shown, the ejection device 100 for an aircraft deployment body includes an actuator 88 and a parachute or paraglider 10 as the deployment body.

[0033] ​​​​​​​​The actuator 88 includes a gas generator 84 for an aircraft having a cup-shaped container 85 that houses an ignition charge (not shown), a piston 81 having a recess 82 and a piston head 83 integrally formed with the recess 82, and a bottomed cylindrical housing 86 that houses the piston 81 and restricts the advancing direction of the piston 81. A parachute or a paraglider 10 is housed in the housing 86 in a state of being disposed on the piston head 83. In this configuration, the parachute or the paraglider 10 can be directly pushed out and deployed by pushing the piston 81. Further, the open end of the housing 86 is closed by a lid 87 in the initial state and detaches from the above open end by pushing out the parachute or the paraglider 10.

[0034] In addition, as Figure 1 shown, a communication portion S1 serving as a clearance is formed between the inner wall of the housing 86 and the outer peripheral portion of the piston head 83. When the piston 81 moves (shoots in the arrow direction of Figure 1 ), the space S between the inner wall of the housing 86 and the piston head 83 is in a negative pressure state. Since air flows into the space S from the communication portion S1, the negative pressure at this time can be reduced and the piston 81 can move smoothly.

[0035] The gas generator 84 is disposed in the recess 82. A gas ejection port is provided at the front end portion of the gas generator 84, and by being ignited by an electric signal, gas can be generated in the recess 82 as a propulsive force for shooting the piston 81 in the arrow direction of Figure 1 . In addition, a sealing member 89 such as an O-ring is provided between the recess 82 and the outer wall portion of the gas generator 84 so that gas leakage does not occur during operation.

[0036] Here, the gas generator 84 is small and lightweight, and includes a cup filled with a gas generating agent, an igniter 20 (not shown) for igniting the gas generating agent, and a bracket for holding the igniter 20. In addition, the gas generator 84 can be, for example, a micro gas generator or the like, but as long as it can generate gas, it can be any device. Further, the gas generating agent is a chemical agent (gunpowder or propellant) that is ignited by the hot particles generated by operating the igniter 20 and generates gas by combustion.

[0037] Generally speaking, gas generators are divided into non-explosive and explosive types. In the non-explosive type, a gas cylinder filled with gases such as carbon dioxide or nitrogen is usually connected to a sharp component such as a needle and a compression spring. The spring force is used to eject the sharp component, which impacts the sealing plate of the sealed gas cylinder to release the gas. At this time, a driving source such as a servo motor is usually used to release the compression force of the spring. Secondly, in the case of using the explosive type, only an igniter can be used, or a gas generator equipped with an igniter and a gas generant can be used. In addition, a hybrid or gas storage type gas generator that uses the force generated by gunpowder to crack the sealing plate of a small gas cylinder and discharge the internal gas to the outside can be used. At this time, the pressurized gas in the gas cylinder is selected from at least one non-combustible gas such as argon, helium, nitrogen, carbon dioxide, etc. In addition, when releasing the pressurized gas, in order to ensure its expansion, the gas generator can be equipped with an explosive type heating element. Further, the gas generator can be equipped with a filter or / and an orifice for regulating the gas flow as needed.

[0038] The gas generant preferably uses a non-azide gas generant. Generally speaking, the gas generant is formed as a shaped body including a fuel, an oxidizer, and an additive. For example, triazole derivatives, tetrazole derivatives, guanidine derivatives, azodicarbonamide derivatives, hydrazine derivatives, etc. or a combination of the above can be used as the fuel. Specifically, for example, nitroguanidine, guanidine nitrate, cyanoguanidine, 5-aminotetrazole, etc. can be appropriately used. In addition, as the oxidizer, basic nitrates such as basic copper nitrate, perchlorates such as ammonium perchlorate and potassium perchlorate, or nitrates containing cations selected from alkali metals, alkaline earth metals, transition metals, and ammonia can be used. For example, sodium nitrate, potassium nitrate, etc. can be appropriately used as the nitrate. In addition, examples of the additive include binders, slag formers, combustion regulators, etc. For example, organic binders such as metal salts of carboxymethyl cellulose and stearates, or inorganic binders such as synthetic hydrotalcite and acid clay can be appropriately used as the binder. Silicon nitride, silicon dioxide, acid clay, etc. can be appropriately used as the slag former. In addition, metal oxides, ferrosilicon, activated carbon, graphite, etc. can be appropriately used as the combustion regulator. In addition, single-base gunpowder, double-base gunpowder, and triple-base gunpowder mainly composed of nitrocellulose can also be used.

[0039] In addition, the shape of the shaped body of the gas generant is granular, pellet-like, cylindrical and other granular shapes, and various shapes such as disc-shaped. In addition, when it is cylindrical, it can also be a porous shaped body (such as single-hole cylindrical or multi-hole cylindrical, etc.) having a through hole inside the shaped body. In addition, in addition to the shape of the gas generant, it is preferable to appropriately select the size and filling amount of the shaped body in consideration of the linear burning rate, pressure index, etc. of the gas generant.

[0040] The parachute or paraglider 10 is connected and stored in the housing 86 via a line (connecting component) such as a rope-like component in a state where it is disposed on the piston head 83. Further, in normal conditions (before deployment), the canopy or top of the parachute or paraglider 10 (not shown) and the line (connecting component) not shown are folded in a manner that does not impede the movement of the piston 81 during operation and stored in the housing 86, and in the event of an emergency, the gas generator 84 receives a predetermined signal (such as an abnormal signal issued by the aircraft 30 when the flight state is abnormal) from the control unit (not shown) of the aircraft 30 and starts, and is then ejected from the housing 86 to the outside and deployed for use.

[0041] Further, in the ejection device 100 for the deployable body for an aircraft, although Figure 1 not shown, it is provided with Figure 2 the circuit abnormality diagnosis device 110 shown. The circuit abnormality diagnosis device 110 includes an arithmetic unit 1, a power supply for inspection 2, a rectifying element 3, overcurrent prevention resistors 4, 5, a voltage boosting unit 6, a voltage reading unit 7, and a light emitting unit 8, and diagnoses the abnormality of the circuit at a preset time (including at the initial installation) or at regular intervals. Here, the igniter circuit 21 of the igniter 20 connected to the ground wire 12 is described as an example of the circuit for which the abnormality diagnosis is performed.

[0042] The arithmetic unit 1 is, for example, a computer (not shown) having a CPU, ROM, RAM, etc., and can automatically send command signals and operation signals to each part according to the situation, or receive command signals from the outside via a communication unit (not shown) and send command signals and operation signals to each part. For example, the arithmetic unit 1 sends an operation signal for applying a predetermined voltage to the igniter circuit 21 to the power supply for inspection 2 at a preset time (including at the initial installation) or at regular intervals.

[0043] Further, based on the voltage value (digital signal) sent by the voltage reading unit 7 at a preset time (including at the initial installation) or at regular intervals, the arithmetic unit 1 determines that the voltage value (1) is in the normal state when it is in the range of V 1 above V 2 below (V 1 -V 2 ), (2) is in the short-circuit state of short circuit when it is lower than the voltage value V 1 , and (3) is in the open-circuit state of open circuit when it is a voltage value higher than the voltage value V 2 .

[0044] Further, the voltage value is in V 1 -V 2When within a range, the voltage values of the igniter circuits 21 of multiple igniters 20 before installation are measured in advance. The voltage value corresponding to the state where the igniter circuit 21 has a normal resistance value is used as the voltage value in the normal state. Based on the information of this voltage value, the arithmetic unit 1 diagnoses whether the igniter circuit 21 is abnormal.

[0045] The inspection power supply 2 applies a voltage of a predetermined value (e.g., 3.3V) to the downstream side by receiving an operation signal from the arithmetic unit 1.

[0046] The rectifying element 3 prevents current from flowing backward and is electrically connected in series on the downstream side of the inspection power supply 2. In addition, the rectifying element 3 is connected to the upstream side of the overcurrent prevention resistor 4.

[0047] The overcurrent prevention resistor 4 is a resistor (e.g., 300Ω) that prevents overcurrent from passing through the igniter circuit 21 of the igniter 20 and is electrically connected in series on the downstream side of the rectifying element 3. In addition, the overcurrent prevention resistor 4 is connected to the upstream side of the igniter circuit 21. In addition, the overcurrent prevention resistor 4 can prevent the igniter 20 from operating during abnormal diagnosis.

[0048] The overcurrent prevention resistor 5 is a resistor (e.g., 10kΩ) that prevents overcurrent from passing through the voltage reading unit 7 and is electrically connected in parallel with the igniter circuit 21. In addition, the overcurrent prevention resistor 5 is electrically connected in series on the upstream side of the voltage amplification unit 6. In addition, the overcurrent prevention resistor 5 can prevent a failure due to overcurrent in the voltage reading unit 7 during abnormal diagnosis.

[0049] The voltage amplification unit 6 is used to amplify the applied voltage (e.g., an operational amplifier) and is electrically connected in series on the downstream side of the overcurrent prevention resistor 5. In addition, the voltage reading unit 7 is electrically connected in series on the downstream side of the voltage amplification unit 6.

[0050] The voltage reading unit 7 is a voltmeter or the like that reads the applied voltage and is electrically connected in series on the downstream side of the voltage amplification unit 6. In addition, the downstream side of the voltage reading unit 7 is connected to the ground wire 11. In addition, the voltage reading unit 7 converts the measured voltage value (analog quantity) into a digital signal and sends it to the arithmetic unit 1.

[0051] The light emitting unit 8 receives the abnormal diagnosis result information judged by the arithmetic unit 1 and uses a power supply to make an LED or the like emit light to correspond to various types of abnormal diagnosis result information judged respectively. For example, when the abnormal diagnosis result information received from the arithmetic unit 1 is normal state information, a normal signal is sent and the green LED emits light; when it is short - circuit state information, a short - circuit signal is sent and the yellow LED emits light; when it is open - circuit state information, an open - circuit signal is sent and the red LED emits light. In this way, the light emission state of each LED is controlled.

[0052] Here, as an example, a specific example of reading a voltage is shown in an arithmetic unit with a processing performance of 8 bits, with a reading accuracy of 0.1 Ω for the resistance value of the igniter circuit 21. For example, when the amplification rate of the voltage amplification unit 6 is 10 times, the overcurrent prevention resistor 4 uses a 300 Ω resistor, the overcurrent prevention resistor 5 uses a resistor with any value from 300 Ω to 1000 Ω, and the circuit resistance value of the igniter circuit 21 is in the range of 1 Ω to 10 Ω in the normal state, the voltage value in the corresponding range of 0.1 V to 1.1 V is the normal state voltage value. When the resistance value of this circuit is less than 1 Ω, the voltage value less than 0.1 V corresponding to it is regarded as a short - circuit state, and when the resistance value of this circuit exceeds 10 Ω, the corresponding voltage value exceeding 1.1 V is regarded as an open - circuit state.

[0053] Here, in the configuration of the above example, the state where the circuit resistance value of the igniter circuit 21 is in the range of 1 Ω to 10 Ω is regarded as the normal state, the state where the circuit resistance value of the igniter circuit 21 is less than 1 Ω is regarded as the short - circuit state, and the state where the circuit resistance value of the igniter circuit 21 exceeds 10 Ω is regarded as the open - circuit state, and the reasons are shown.

[0054] In the configuration of the above example, while considering the numerical deviation, when the resistance value of the igniter 20 is designed to be 1.0 Ω - 3.0 Ω, the resistance of the connector connecting the igniter 20 and the igniter circuit 21 is designed to be 0.0 Ω - 0.1 Ω, and the wire resistance (maximum 100 m) is designed to be 0.0 Ω - 3.6 Ω, the circuit resistance value of the igniter circuit 21 in the normal state is any value in the range of 1.0 Ω - 6.7 Ω. Therefore, when the igniter circuit 21 is in the short - circuit state, the circuit resistance value of the igniter circuit 21 is less than 1.0 Ω. In addition, when the igniter circuit 21 is in the open - circuit state, the circuit resistance value of the igniter circuit 21 exceeds 6.7 Ω, but for a margin, when it exceeds 10 Ω, it is set as the open - circuit state. Thus, the circuit resistance value of the igniter circuit 21 is set to be in the range of 1 Ω - 10 Ω as the normal state, the circuit resistance value of the igniter circuit 21 less than 1 Ω is set as the short - circuit state, and the circuit resistance value of the igniter circuit 21 exceeding 10 Ω is set as the open - circuit state.

[0055] In addition, if the measurement error of the igniter circuit 21 is corrected to a maximum error of ±6%, for example, the circuit resistance value of the igniter circuit 21 in the normal state is controlled within the range of 0.9 Ω - 7.2 Ω. Therefore, when considering the measurement error of the igniter circuit 21, a margin can also be left. The state where the circuit resistance value of the igniter circuit 21 is in the range of 0.9 Ω - 10 Ω is the normal state, the state where the circuit resistance value of the igniter circuit 21 is less than 0.9 Ω is the short - circuit state, and the state where the circuit resistance value of the igniter circuit 21 exceeds 10 Ω is the open - circuit state.

[0056] As described above, when considering the design, for the circuit resistance value of the igniter circuit 21, the normal state, short-circuit state, and open-circuit state can be preset. Then, by setting the voltages corresponding to the above circuit resistance values respectively and measuring the voltage of the igniter circuit 21, the circuit state of the igniter circuit 21 is diagnosed.

[0057] In addition, in the circuit abnormality diagnosis device 110, when improving the reading accuracy of the resistance value of the igniter circuit 21, it can be achieved by increasing the bit number of the arithmetic unit 1 (improving the processing ability) or reducing the resistance value of the overcurrent prevention resistor 4.

[0058] Figure 3 FIG. is a diagram of an aircraft 30 to which the deployed body ejection device 100 for an aircraft is applied. The aircraft 30 includes a fuselage 31, the deployed body ejection device 100 for an aircraft coupled to the fuselage 31, one or more propulsion mechanisms (e.g., thrusters) 32 coupled to the fuselage 31 and propelling the fuselage 31, and a plurality of legs 33 provided at the lower part of the fuselage 31.

[0059] Next, the operation of the circuit abnormality diagnosis device 110 of the deployed body ejection device 100 for an aircraft will be described. First, the arithmetic unit 1 sends an operation signal for applying a predetermined voltage to the igniter circuit 21 to the inspection power supply 2 at a preset time (including at the initial installation) or at predetermined intervals. The inspection power supply 102 receives this operation signal and applies a predetermined voltage to the igniter circuit 21 via the downstream rectifying element 103 and the overcurrent prevention resistor 4. At this time, a predetermined voltage is also applied to the overcurrent prevention resistor 5 via the rectifying element 103 and the overcurrent prevention resistor 4. Then, the voltage applied to the overcurrent prevention resistor 5 is amplified by the voltage amplification unit 6, and the voltage reading unit 7 reads the value (voltage value) of the amplified voltage. After the voltage value read by the voltage reading unit 7 is converted into a digital signal, it is sent to the arithmetic unit 1.

[0060] Next, based on the digital signal of the received voltage value, the arithmetic unit 1 diagnoses (judges) whether the igniter circuit 21 is in a normal state, a short-circuit state, or an open-circuit state. When the arithmetic unit 1 diagnoses (judges) that the igniter circuit 21 is in a normal state, it sends a normal signal to the light emitting unit 8. After receiving the normal signal, the light emitting unit lights up the green LED. On the contrary, when the arithmetic unit 1 diagnoses (judges) that the igniter circuit 21 is in a short-circuit state, it sends a short-circuit signal to the light emitting unit 8. After receiving the short-circuit signal, the light emitting unit lights up the yellow LED. In addition, when the arithmetic unit 1 diagnoses (judges) that the igniter circuit 21 is in an open-circuit state, it sends an open-circuit signal to the light emitting unit 8. After receiving the open-circuit signal, the light emitting unit lights up the red LED.

[0061] In the aircraft 30 to which the deployed body ejection device 100 for aircraft configured as described above is applied, it is possible to easily diagnose an abnormality in the igniter circuit 21 simply by utilizing the characteristic that the voltage drops when the circuit resistance value decreases, without using a costly high-precision current sensor.

[0062] In addition, it is possible to easily notify the outside of the device whether the abnormality diagnosis result of the igniter circuit 21 is a normal state, a short-circuit state, or an open-circuit state through the light-emitting unit 8.

[0063] <Second Embodiment>

[0064] Next, based on Figure 4 and Figure 5 the second embodiment of the present invention will be described. In addition, in the present embodiment, components having the same last two digits of the reference numerals as those in the first embodiment represent the same components as those in the first embodiment, and thus the description thereof will be omitted.

[0065] The deployed body ejection device for aircraft (not shown) of the present embodiment can be applied to the same aircraft (not shown) as the aircraft 30 of the first embodiment, instead of the deployed body ejection device 100 for aircraft of the first embodiment. In addition, as Figure 4 shown, the deployed body ejection device for aircraft of the present embodiment includes a circuit abnormality diagnosis device 210 that is basically the same as that of the first embodiment. However, different from the first embodiment, it includes a power storage unit 131, a switch unit 132, and a physical switch unit 122 provided in the igniter circuit 121.

[0066] The power storage unit 131 has a power storage function such as a capacitor and can discharge as needed. In addition, the downstream side of the power storage unit 131 is electrically connected in series with the switch unit 132. In addition, the power storage unit 131 is pre-charged before the operation of the deployed body ejection device 200 for aircraft.

[0067] The switch unit 132 is electrically connected to the downstream side of the power storage unit 131 and is electrically connected in series with the physical switch unit 122 on the downstream side. In addition, after receiving an on signal from the arithmetic unit 101, the switch unit 132 makes the switch function in an on state and releases the stored current from the power storage unit 131 to the physical switch unit 122 side.

[0068] The physical switch unit 122 prevents current from flowing in the igniter circuit 121 when it is not necessary to operate, such as during transportation. Examples of the physical switch unit 122 include, for example, Figure 5 as shown. The physical switch unit 122 of Figure 5 will be described below.

[0069] Figure 5 The physical switch unit 122 of

[0070] The main body portion 151 includes a tubular portion 152 for inserting the long ruler-shaped pin portion 141, a concave portion 153 that engages with the spherical portion of the spherical locking mechanism 143 provided at a predetermined position at the front end of the pin portion 141, and a space 154 for fixedly arranging the switch mechanism 161.

[0071] As Figure 5 shown in (a), a part of the middle of the tubular portion 152 and a part of the space 154 are a communicating space. In this communicating space, the state of the portion composed of the leaf spring 163, the roller portion 164, and the pressing portion 165 of the switch mechanism 161 is such that it can move within a predetermined range with one end side (the main body side of the switch mechanism 161) of the leaf spring 163 as the axis.

[0072] The pin portion 141 includes an annular member 142 provided near one end and a spherical locking mechanism 143 provided at a predetermined position at the front end of the other end.

[0073] The spherical locking mechanism 143 is provided with a spring (not shown) inside the concave portion provided in the pin portion 141, and the spherical portion provided is urged in the outward direction in a state where it does not protrude from the concave portion. Therefore, for the spherical locking mechanism 143, in Figure 5 the state of (a), the spherical portion is in the state of protruding most from the pin portion 141. In Figure 5 the state of (b), it is pressed by the tubular portion 152 and sinks into the inside of the pin portion 141. In Figure 5 the state of (c), the spherical portion is in the state of protruding from the pin portion 141 and engaging with the concave portion 153. Therefore, in Figure 5 the state of (c), the pin portion 141 is in a state of being temporarily fixed to the main body portion 151 and is not easily detached.

[0074] The switch mechanism 161 includes a main body 161a, a conduction / disconnection switch portion 162, a leaf spring 163, a roller portion 164, and a pressing portion 165.

[0075] In the conduction / disconnection switch portion 162, a spring (not shown) that urges from the inside to the outside of the switch mechanism 161 is provided. By pressing from the pressing portion 165, it can be in the Figure 5 protruding state of (a), and successively sink as shown in Figure 5 (b), Figure 5 (c). In addition, the conduction / disconnection switch portion 162 is in a conduction state (energized state) in the Figure 5 protruding state of (a), and is in a disconnection state (non-energized state) in the state shown in Figure 5 (c).

[0076] One end of the leaf spring 163 is fixed to the main body 161a of the switch mechanism 161, and the other end can move within a predetermined range. Further, at the other end of the leaf spring 163, while rotatably supporting the roller portion 164 on a shaft, a pressing portion 165 is provided.

[0077] Since the roller portion 164 is rotatably supported on a shaft at the other end of the leaf spring 163, as Figure 5 (b) shows, the friction generated when the front end of the pin portion 141 contacts the roller portion 164 can be reduced by rotation. Thereby, the pin portion 141 can be smoothly inserted into the tubular portion 152. Further, naturally, the pin portion 141 can also be smoothly pulled out from the tubular portion 152.

[0078] Through the above-described physical switch portion 122, in the present embodiment, the following operations can be performed. For example, when the physical switch portion 122 is in the conductive state and the aircraft is flying, in the case where the arithmetic unit 101 diagnoses (judges) that the igniter circuit 121 is in an abnormal state (short-circuit state or open-circuit state), an operation signal is sent from the arithmetic unit 101, and the switch portion 132 receives this operation signal and releases current from the power storage unit 131. This current energizes the igniter circuit 121 through the physical switch portion 122 to start the igniter 120. Thereby, after a parachute or a paraglider is ejected from the inside of the housing of the ejection device identical to that of the first embodiment to the outside, the parachute or the paraglider is deployed.

[0079] The ejection device 200 for the deployable body of the aircraft configured as described above can achieve the same effects as those of the first embodiment in the applicable aircraft.

[0080] Further, according to the present embodiment, in a state where the aircraft is not used such as during transportation, the physical switch portion 122 is set to the off state, thereby preventing the operation caused by the malfunction of the igniter (energization of an unexpected operating current). Further, the pin portion 141 is temporarily fixed to the main body portion 151 by the spherical locking mechanism, and thus is not easily detached, and can better prevent the operation caused by the malfunction of the igniter (energization of an unexpected operating current).

[0081] Further, according to the present embodiment, for example, when the physical switch portion 122 is in the conductive state and the aircraft is flying, in the case where the igniter circuit 121 is diagnosed (judged) to be in an abnormal state (short-circuit state or open-circuit state), the igniter 120 operates, and after a parachute or a paraglider is ejected from the inside of the housing of the ejection device identical to that of the first embodiment to the outside through the gas generator, the parachute or the paraglider can be deployed. As a result, the aircraft can be protected before an abnormality occurs in a place other than the igniter circuit of the igniter circuit 121. That is, it is possible to prevent a situation where an abnormality also occurs in the igniter circuit and the ejection device for the deployable body of the aircraft does not operate when an abnormality occurs in a place other than the igniter circuit.

[0082] <Third Embodiment>

[0083] Next, based on Figure 6 The third embodiment of the present invention will be described. In addition, in this embodiment, components having the same last two digits of the reference numerals as those in the first embodiment represent the same components as those in the first embodiment, and thus the description thereof will be omitted. In addition, in this embodiment, the same part names as those in the second embodiment are sometimes used for the same parts, and the description thereof will be omitted.

[0084] The airbag device 300 for an aircraft according to this embodiment can be applied to the same aircraft (not shown) as the aircraft 30 in the first embodiment. In addition, the airbag device 300 for an aircraft according to this embodiment includes the same circuit abnormality diagnosis device as that in the second embodiment. However, the igniter (not shown) in this embodiment is provided inside a gas generator (not shown) that generates gas for inflating the airbag 341, and is the same as the second embodiment except for this. Details will be described below.

[0085] The aircraft 330 includes an airbag device 300 for an aircraft that inflates the airbag 341 based on the air pressure generated by the operation of the same gas generator (not shown) as that in the first embodiment. In addition, the airbag 341 and the gas generator before deployment (device operation) are housed in a housing (not shown), and in this state, the airbag device 300 for an aircraft is provided at Figure 6 the lower part of the fuselage 331 in the normal posture shown.

[0086] The arithmetic unit of the airbag device 300 for an aircraft according to this embodiment diagnoses (judges) the state of the igniter circuit through the same circuit abnormality diagnosis device as that in the second embodiment.

[0087] With the above-described airbag device 300 for an aircraft, the following operations can be performed in this embodiment. For example, when the physical switch unit is in the conductive state and the aircraft is flying, if the arithmetic unit diagnoses (judges) that the igniter circuit is in an abnormal state (short circuit state or open circuit state), an operation signal is sent from the arithmetic unit, and the switch unit receives this operation signal and releases current from the power storage unit. This current energizes the igniter circuit through the physical switch unit, starts the igniter, burns the gas generating agent, and the generated gas inflates and deploys the airbag 341.

[0088] The airbag device 300 for an aircraft configured as described above can achieve the same effects as those in the first embodiment in the applicable aircraft.

[0089] In addition, according to the present embodiment, for example, when the physical switch unit 122 is in the conductive state and the aircraft is flying, if the igniter circuit is diagnosed (judged) to be in an abnormal state (a short-circuit state or an open-circuit state), the igniter can be started, and the airbag 341 can be inflated and deployed by the gas generator. As a result, the aircraft can be protected before an abnormality occurs in a place other than the igniter circuit. That is, it is possible to prevent a situation where, when an abnormality occurs in a place other than the igniter circuit, the igniter circuit also becomes abnormal and the aircraft airbag device 300 does not operate.

[0090] <Fourth Embodiment>

[0091] Next, based on Figure 7 and Figure 8 the fourth embodiment of the present invention will be described. In addition, in the present embodiment, components having the same last two digits of the reference numerals as those in the first embodiment represent the same components as those in the first embodiment, and thus the description thereof will be omitted. In addition, in the present embodiment, the same part names are used for the same parts as those in the second embodiment, and the description thereof may be omitted sometimes.

[0092] As Figure 7 shown, the aircraft cut-off device 400 of the present embodiment can be applied to the same aircraft (not shown) as the aircraft 30 of the first embodiment. In addition, the aircraft cut-off device 400 of the present embodiment includes the same circuit abnormality diagnosis device as that of the second embodiment, but the igniter 420 of the present embodiment cuts off (disconnects) the current supply path 450, and is otherwise the same as the second embodiment. Details will be described below.

[0093] The aircraft cut-off device 400 includes an igniter 420 as an example of a destructive force source (power source), a cut-off chamber 460 having an internal space, a rupture plate 451 that is damaged and ruptured by heat and pressure generated by the operation of the igniter 420 and simultaneously cuts off the current supply path 450, and a physical switch unit 422 that is the same as that of the second embodiment.

[0094] The igniter 420 generates a flame and includes an ignition unit 423, which includes an ignition charge (not shown) that ignites and burns inside during operation to generate a flame and a resistance element (not shown) for igniting the ignition charge; and a pair of terminal pins 424, 424 connected to the ignition unit 423. In addition, the pair of terminal pins 424, 424 are also part of the igniter circuit.

[0095] The rupture plate 451 is circular in a plan view, for example, and is disposed in the cut-off chamber 460 and below the igniter 420. The rupture plate 451 needs to be easily cracked and have appropriate strength, so it can be made of a lightweight metal such as iron or aluminum. In addition, the rupture plate 451 can also be made of a non-conductive material, such as a hard resin material like hard rubber or fine ceramics. The width of the rupture plate 451 is greater than the width of the igniter 420 in the long side direction of the current supply path 450. The igniter 420 is held on the upper wall of the cut-off chamber 460 to release the generated flame to the rupture plate 451 located below.

[0096] For example, when the physical switch unit 422 is in the conductive state and the aircraft is flying, if the operation unit diagnoses (judges) that the igniter circuit is in an abnormal state (short-circuit state or open-circuit state), a running signal is sent from the operation unit, and the switch unit receives this running signal and releases current from the power storage unit. This current flows through the above-mentioned resistance element through the physical switch unit 422 and a pair of terminal pins 424, 424 in a predetermined amount. Due to the current flowing through the resistance element, Joule heat is generated in the resistance element, and the ignition charge starts to burn. The high-temperature flame generated by the combustion causes the rupture of a squib cup (not shown) that houses the ignition charge. In the igniter 420, when a nickel-chromium alloy wire is used as the resistance element, the time from when the current flows through the above-mentioned resistance element to operation is usually 2 milliseconds or less.

[0097] The peripheral wall of the cut-off chamber 460 is provided with through holes 461, and the other part of the peripheral wall is provided with through holes 462. The current supply path 450 is bridged through these through holes 461, 462. The current supply path 450 is composed of a metal plate or a metal wire, for example, one end of which is connected to a storage battery (not shown) of the circuit, and the other end is connected to an electrical device (not shown) of the aircraft.

[0098] In the above configuration, when an abnormality of the aircraft is detected, when the physical switch unit 422 is in the conductive state and the aircraft is flying, if the operation unit diagnoses (judges) that the igniter circuit is in an abnormal state (short-circuit state or open-circuit state), a predetermined amount of current is supplied to a pair of terminal pins 424, 424 of the igniter 420, and then the heat and pressure generated by the operation of the igniter 420 damage the rupture plate 451. At this time, the rupture plate 451 is damaged in such a way that its central part cracks and bends toward the current supply path 450. Then, as Figure 8 shown, the current supply path 450 is cut off by the damaged rupture plate 451. In addition, in the present invention, the object of the blocked current supply path 450 is preferably the wiring from the positive electrode.

[0099] Thus, in the cutting device 400 for an aircraft according to the present embodiment, for example, when the physical switch unit 122 is in a conductive state and the aircraft is flying, if the igniter circuit is diagnosed (judged) to be in an abnormal state (a short - circuit state or an open - circuit state), the igniter 420, which is a source of destructive force, operates. The igniter 420 applies heat and pressure towards the current supply path 450 to the rupture plate 451. As a result, the rupture plate 451 can be damaged and cracked, and the current supply path 450 can be cut off through the cracked part of the cracked rupture plate 451. Thereby, the supply of current to the electronic devices of the aircraft can be blocked. Thereby, when the aircraft crashes, accidents such as contact between components such as the operating propeller and people, ignition, and electric shock can be prevented. Additionally, when a part of the propeller stops, usually the rotation speed of other propellers is controlled to maintain flight, but in this case, the load on the motor is too heavy, which can cause a malfunction. However, as described above, since the supply of current can be forcibly blocked, motor malfunctions can be avoided.

[0100] The embodiments of the present invention have been described above, but only specific examples are exemplified, and the present invention is not limited thereto. Appropriate design changes can be made to the specific configuration and the like. Additionally, the functions and effects described in the embodiments of the invention only list the most appropriate functions and effects produced by the present invention, and the functions and effects of the present invention are not limited to the content described in the embodiments of the invention.

[0101] For example, in the above - described embodiments, the igniter circuit of the igniter has been described as an example of the circuit for abnormal diagnosis, but the circuit for abnormal diagnosis is not limited thereto. For example, it is also possible to diagnose whether a circuit related to an ejection device other than the igniter circuit is abnormal.

[0102] Additionally, the arithmetic unit in the above - described embodiments can also have the function of a voltage reading unit. In this case, the arithmetic unit is electrically connected to the ground wire.

[0103] Moreover, the front end portion of the pin portion 141 in the above - described second embodiment can be conical. Thus, the conical shape makes it easier for the roller portion to rotate, and thus the pin portion 141 can be inserted more smoothly.

[0104] In addition, in the above - described fourth embodiment, the current supply path is cut off, but it is not limited thereto. For example, it may be desired to cut the line connected to the deployed parachute or paraglider. At this time, the line can be burned by the flame of the igniter, or a cutting device such as a cutter can be operated using the flame force of the igniter to cut the line.

[0105] Furthermore, the present invention can be an aircraft that appropriately combines the above - described embodiments and modification examples.

[0106] Reference Signs

[0107] 1, 101 Arithmetic Unit

[0108] 2. Power supply for 102 inspection

[0109] 3. Rectifying element 103

[0110] 4. and 5. Overcurrent prevention resistors 104 and 105

[0111] 6. Voltage amplification section 106

[0112] 7. Voltage reading section 107

[0113] 8. Light emitting section 108

[0114] 10. Paraglider

[0115] 11, 12, 111, 112. Ground wires

[0116] 20, 120, 420. Igniters

[0117] 21. Circuit for igniter 121

[0118] 30. Aircraft 330

[0119] 31. Airframe 331

[0120] 32. Propulsion mechanism 332

[0121] 33. Legs 333

[0122] 81. Piston

[0123] 82, 153. Recesses

[0124] 83. Piston head

[0125] 84. Gas generator

[0126] 85. Container

[0127] 86. Housing

[0128] 87. Cover

[0129] 88. Actuator

[0130] 89. Sealing component

[0131] 100, 200. Deployed body ejection device for aircraft

[0132] 110, 210. Circuit abnormality diagnosis device

[0133] 122, 422. Physical switch section

[0134] 131. Power storage section

[0135] 132. Switch section

[0136] 141 Pin part

[0137] 142 Ring-shaped part

[0138] 143 Spherical locking mechanism

[0139] 151 Main body part

[0140] 152 Tubular part

[0141] 154 Space

[0142] 161 Switch mechanism

[0143] 161a Main body

[0144] 162 Disconnecting switch part

[0145] 163 Leaf spring

[0146] 164 Roller part

[0147] 165 Pressing part

[0148] 300 Airbag device for aircraft

[0149] 341 Airbag

[0150] 400 Cutting device for aircraft

[0151] 423 Ignition part

[0152] 424 Terminal pin

[0153] 450 Current supply path

[0154] 451 Rupture plate

[0155] 460 Cutting chamber

[0156] 461, 462 Through holes

[0157] S Space

[0158] S1 Connecting part

Claims

1. A circuit abnormality diagnosis device is a circuit abnormality diagnosis device for diagnosing whether there is an abnormality in a circuit in an aircraft safety device having an igniter and a circuit connected to the igniter. Characterized in that it has a power supply that can apply a check voltage to the circuit; an arithmetic unit that controls the conduction / turn-off of the power supply; a first overcurrent prevention unit that is electrically connected in series with the power supply to prevent overcurrent from flowing through the circuit; a voltage boosting unit that is electrically connected in parallel with the circuit and is used to boost the voltage to a predetermined order of magnitude; a voltage reading unit that is electrically connected in series with the voltage boosting unit to read the voltage value boosted by the voltage boosting unit, that is, the voltage value; and a second overcurrent prevention unit that is electrically connected in series with the voltage reading unit on the upstream side of the voltage reading unit to prevent overcurrent from flowing through; the arithmetic unit receives the voltage value information from the voltage reading unit, The voltage value is within a first voltage value V preset as a voltage value range indicating that the circuit is normal. 1 The second voltage value V 2 The following range is considered normal. Determine that it is in a short - circuit state when the voltage value is lower than the voltage value V 1 ​ Determine that it is an open circuit state when the voltage value is higher than the voltage value V 2 ​ 2. A circuit abnormality diagnosis device is a circuit abnormality diagnosis device for diagnosing whether there is an abnormality in a circuit in an aircraft safety device having an igniter and a circuit connected to the igniter. Characterized in that it has a power supply that can apply a check voltage to the circuit; a first overcurrent prevention unit that is electrically connected in series with the power supply to prevent overcurrent from flowing through the circuit; a voltage boosting unit that is electrically connected in parallel with the circuit and is used to boost the voltage; an arithmetic unit that controls the switch unit of the power supply and is electrically connected in series with the voltage boosting unit to read the voltage value boosted by the voltage boosting unit, that is, the voltage value; a second overcurrent prevention unit that is electrically connected in series with the arithmetic unit on the upstream side of the arithmetic unit to prevent overcurrent from flowing through, The arithmetic unit determines that the voltage value is in a normal state when it is within a range of a predetermined voltage value V that is preset to be within a voltage value range indicating normal operation of the circuit 1 equal to or higher than V 2 and equal to or lower than, and determines it as a normal state Determine that it is in a short - circuit state when the voltage value is lower than the voltage value V 1 ​ When the voltage value is higher than the voltage value V 2 it is determined as an open circuit state.

3. The circuit abnormality diagnosis device according to claim 1, wherein a rectifying element for preventing reverse current is electrically connected in series to the downstream side of the power supply and the upstream side of the first overcurrent prevention unit.

4. The circuit abnormality diagnosis device according to claim 2, wherein a rectifying element for preventing reverse current is electrically connected in series to the downstream side of the power supply and the upstream side of the first overcurrent prevention unit.

5. The circuit abnormality diagnosis device according to any one of claims 1 to 4, wherein it is provided with a light emitting unit that receives the abnormal diagnosis result information of the judgment from the arithmetic unit and can emit light of a color corresponding to the type of the judgment result information when receiving the judgment result information from the arithmetic unit.

6. A current generating device, Characterized in that it includes the circuit abnormality diagnosis device according to any one of claims 1 to 5; a power storage unit; a switch unit that is electrically connected to the downstream side of the power storage unit and can discharge the current stored in the power storage unit on the downstream side, when the arithmetic unit judges that the aircraft is in a flight state and is in the short-circuit state or the open-circuit state, it sends an operation signal for the discharge to the switch unit.

7. The current generating device according to claim 6, Characterized in that the power storage unit is a capacitor.

8. The current generating device according to claim 6 or 7, Characterized in that a physical switch unit is provided in the circuit to physically conduct / turn off the energization between the circuit and the switch unit.

9. An ejection device for an object to be deployed for an aircraft, which is an ejection device for an object to be deployed for an aircraft mounted on an aircraft, characterized in that, it includes the current generating device according to any one of claims 6 to 8; an object to be deployed; an igniter that operates when the current generated by the operation of the current generating device is energized, and generates a driving force for ejecting the object to be deployed, a container that houses the object to be deployed and the igniter inside.

10. An airbag device for an aircraft, which is an airbag device for an aircraft mounted on an aircraft, characterized in that, it includes the current generating device according to any one of claims 6 to 8; an airbag; a gas generator that has an igniter and a gas generating agent, operates when the current generated by the operation of the current generating device is energized to the igniter, burns the gas generating agent, and generates a gas for inflating the airbag; a container that houses the airbag and the gas generator inside.

11. A cutting device for an aircraft, which is a cutting device for an aircraft mounted on an aircraft, characterized in that, it has the current generating device according to any one of claims 6 to 8; a conductive part; an igniter that operates when the current generated by the operation of the current generating device is energized, and generates heat or a driving force for cutting the conductive part; a driving cutting part that is driven by the driving force when the igniter generates the driving force.

Images