Patent Description:
In recent years, industrial application of flight objects has been accelerating with the development of autonomous control technology and flight control technology. As described in Patent Literature <NUM> below, such flight objects include a safety mechanism in which a safety device (such as an airbag device) is deactivated by a safety signal during normal operation.

Note that when an igniter is used in a safety device in a flight object as described in Patent Literature <NUM> below, it is necessary to at least periodically diagnose whether there is an abnormality in circuits including a circuit for the igniter not only before operation but also during operation. Conventionally, an example of an abnormality diagnosis method for the circuit includes applying a predetermined voltage to the circuit, measuring a weak current flowing through the circuit (the current that would not cause the igniter to operate), determining whether the circuit is normal (whether there is a predetermined circuit resistance value), and confirming whether a connection failure (disconnection) occurs.

<CIT> discloses a circuit abnormality diagnosis device that diagnoses a circuit abnormality in a safety device for a flight object including an igniter and a circuit connected to the igniter, the circuit abnormality diagnosis device comprising:.

However, in the above abnormality diagnosis method, when the accuracy of a current sensor is low because the weak current is measured, it is not possible to distinguish whether a short circuit has occurred in the circuit or the circuit is in a normal state. Further, in recent years, there has been a demand for a device capable of easily performing the abnormality diagnosis above with a simple device, instead of a highly accurate current sensor that costs relatively high for introduction.

Therefore, the present invention has been made in view of such circumstances, and an object of the present invention is to provide a circuit abnormality diagnosis device capable of simply and easily diagnosing a circuit abnormality without using a highly accurate current sensor that costs relatively high, a current generating device including the circuit abnormality diagnosis device, a deployed object ejection device for a flight object including the current generating device, an airbag device for a flight object including the current generating device, and a cutting device for a flight object including the current generating device.

According to the present invention, it is possible to simply and easily diagnose a circuit abnormality without using a highly accurate current sensor that costs relatively high. Additionally, in a case where it is determined that the circuit is abnormal, a safety device (an ejection device, an airbag device, a cutting device, and others) for a flight object can be automatically actuated.

Hereinafter, a first embodiment of the present invention will be described with reference to <FIG>.

As illustrated in <FIG>, a deployed object ejection device for a flight object <NUM> includes an actuator <NUM> and a parachute or a paraglider <NUM> which is a deployed object.

The actuator <NUM> includes a gas generator <NUM> for a flight object having a cup-shaped case <NUM> for containing an ignition charge (not illustrated), a piston <NUM> having a recess portion <NUM> and a piston head <NUM> integrally formed with the recess portion <NUM>, and a bottomed cylindrical housing <NUM> for containing the piston <NUM> and regulating a propulsion direction of the piston <NUM>. The parachute or the paraglider <NUM> is housed in the housing <NUM> in a state of being arranged on the piston head <NUM>. In such a configuration, the parachute or the paraglider <NUM> can be directly pushed out and deployed by the propulsion of the piston <NUM>. Note that an opening end of the housing <NUM> is closed by a lid <NUM> in an initial state, and is detached from the opening end by extrusion of the parachute or the paraglider <NUM>.

Further, as illustrated in <FIG>, a communication portion S1 which is a gap (clearance) is formed between an inner wall of the housing <NUM> and an outer peripheral portion of the piston head <NUM>. When the piston <NUM> moves (is ejected in the arrow direction of <FIG>), a space S between the inner wall of the housing <NUM> and the piston head <NUM> has a negative pressure which can be reduced by air flowing into the space S from the communication portion S1, leading to a smooth movement of the piston <NUM>.

The gas generator <NUM> is provided in the recess portion <NUM>. A gas ejection port is provided at an end portion of the gas generator <NUM>, and a gas can be generated as a propulsive force for ejecting the piston <NUM> in the arrow direction of <FIG> within the recess portion <NUM> by ignition via an electric signal. A seal member <NUM> such as an O-ring is provided between the recess portion <NUM> and an outer wall portion of the gas generator <NUM> to prevent gas leakage during operation.

Here, the gas generator <NUM> is small and light, and includes a cup body filled with a gas generating agent, an igniter <NUM> (not illustrated) for igniting the gas generating agent, and a holder for holding the igniter <NUM>. Further, examples of the gas generator <NUM> include a micro gas generator, but any device which can generate a gas may be used. Note that the gas generating agent is a chemical agent (an explosive or a propellant) which is ignited by thermal particles generated by operation of the igniter <NUM> and generates a gas by burning.

Generally, the gas generator can be roughly classified into non-explosive and explosive types. In main non-explosive type gas generators, a sharp member such as a needle and a compressed spring are connected to a gas cylinder in which a gas such as carbon dioxide or nitrogen is sealed, and the sharp member is blown off using a spring force and collided with a sealing plate which seals the cylinder to release the gas. At this time, a drive source such as a servo motor is usually used to release the compressive force of the spring. Next, in explosive type gas generators, an igniter may be used solely, or an igniter and a gas generating agent may be provided. Further, a hybrid type or a stored type gas generator may be used which cleaves a sealing plate in a small gas cylinder by an explosive force and discharges an internal gas to the outside. In this case, a pressurized gas in the gas cylinder is selected from at least one or more of non-combustible gases such as argon, helium, nitrogen, and carbon dioxide. Additionally, when the pressurized gas is released, the gas generator may be provided with an explosive type heating element for reliable inflation. The gas generator may further include a filter or/and an orifice for adjusting a gas flow as needed.

As the gas generating agent, a non-azide gas generating agent is preferably used, and the gas generating agent is generally formed as a molded body containing a fuel, an oxidizing agent, and an additive. As the fuel, for example, a triazole derivative, a tetrazole derivative, a guanidine derivative, an azodicarbonamide derivative, a hydrazine derivative, or a combination thereof is used. Specific preferable examples include nitroguanidine, guanidine nitrate, cyanoguanidine, and <NUM>-aminotetrazole. Further, examples of the oxidizing agent include a basic nitrate such as a basic copper nitrate, a perchlorate such as an ammonium perchlorate and a potassium perchlorate, and a nitrate containing a cation selected from an alkali metal, an alkaline earth metal, a transition metal, and ammonia. Preferable examples of the nitrate include a sodium nitrate and a potassium nitrate. In addition, examples of the additive include a binder, a slag forming agent, and a combustion regulator. Preferable examples of the binder include an organic binder such as a metal salt and a stearate of carboxymethyl cellulose, and an inorganic binder such as a synthetic hydroxytalcite and acid clay. Preferable examples of the slag forming agent include a silicon nitride, silica, and acid clay. Additionally, preferable examples of the combustion regulator include a metal oxide, ferrosilicon, activated carbon, and graphite. Additionally, a single base powder, a double base powder, and a triple base powder which contain nitrocellulose as a main component may be used.

In addition, examples of the shape of the molded body of the gas generating agent include a particle shape such as a granular shape, a pellet shape, and a cylindrical shape, and a disk-like shape. Further, as the cylindrical molded body, a perforated (for example, a single hole cylindrical or a porous cylindrical) molded body having a through hole inside the molded body may also be used. In addition to the shape of the gas generating agent, it is preferable to select a size and a filling amount of the molded body as appropriate in consideration of a linear burning rate, a pressure index, and the like of the gas generating agent.

The parachute or the paraglider <NUM> is connected to and housed in the housing <NUM> via a line (the coupling member) (not illustrated) such as a string member in a state of being arranged on the piston head <NUM>. Further, an umbrella portion or a canopy (not illustrated) of the parachute or the paraglider <NUM> at a normal time (before being deployed), and the line (the coupling member) (not illustrated) are folded and housed in the housing <NUM> so as not to disturb the movement of the piston <NUM> during operation, and are deployed and used after being ejected from the inside of the housing <NUM> to the outside by actuation of the gas generator <NUM> which receives a predetermined signal (such as an abnormal signal generated when flight of a flight object <NUM> is in an abnormal state) from a control unit (not illustrated) of the flight object <NUM> in an emergency.

Also, the deployed object ejection device for a flight object <NUM> includes a circuit abnormality diagnosis device <NUM> not illustrated in <FIG>, but illustrated in <FIG>. The circuit abnormality diagnosis device <NUM> includes a calculation unit <NUM>, an inspection power supply <NUM>, a rectifier element <NUM>, overcurrent preventing resistors <NUM> and <NUM>, a voltage amplification unit <NUM>, a voltage reading unit <NUM>, and a light emitting unit <NUM>, and performs a circuit abnormality diagnosis at a preset time (including the time of initial mounting) or every predetermined time. Here, an igniter circuit <NUM> of the igniter <NUM> connected to a ground <NUM> will be described as an example of a circuit whose abnormality is diagnosed.

The calculation unit <NUM> is, for example, a computer (not illustrated) including a CPU, a ROM, a RAM, and the like, and can automatically transmit a command signal, an operation signal, and the like to each unit according to a situation, or receive a command signal and the like from the outside via a communication unit (not illustrated) and transmit a command signal, an operation signal, and the like to each unit. For example, the calculation unit <NUM> transmits an operation signal for applying a predetermined voltage to the igniter circuit <NUM> to the inspection power supply <NUM> at a preset time (including the time of initial mounting) or every predetermined time.

Additionally, the calculation unit <NUM> determines that (<NUM>) a case where a voltage value is within a range of a predetermined voltage value V<NUM> or more and V<NUM> or less (V<NUM> to V<NUM>) is a normal state, (<NUM>) a case where the voltage value is less than the voltage value V<NUM> is a short-circuit state in which the circuit is short-circuited, and (<NUM>) a case where the voltage value is higher than the voltage value V<NUM> is a disconnection state in which the circuit is disconnected, based on a voltage value (a digital signal) transmitted from the voltage reading unit <NUM> at a preset time (including the time of initial mounting) or every predetermined time.

Note that for the range of the voltage values V<NUM> to V<NUM>, the voltage values of the igniter circuits <NUM> of a plurality of the igniters <NUM> before mounting are actually measured in advance, and a voltage value corresponding to a case where the igniter circuit <NUM> has a normal resistance value is set as a voltage value in the normal state, and the calculation unit <NUM> performs an abnormality diagnosis of the igniter circuit <NUM> based on information on the voltage value.

The inspection power supply <NUM> applies a voltage of a predetermined value (for example, <NUM> V) to a downstream side by receiving the operation signal from the calculation unit <NUM>.

The rectifier element <NUM> prevents a reverse current, and is electrically connected in series to the downstream side of the inspection power supply <NUM>. Additionally, the rectifier element <NUM> is connected to an upstream side of the overcurrent preventing resistor <NUM>.

The overcurrent preventing resistor <NUM> is a resistor (for example, <NUM>Ω) which prevents an overcurrent from flowing through the igniter circuit <NUM> of the igniter <NUM>, and is electrically connected in series to a downstream side of the rectifier element <NUM>. Further, the overcurrent preventing resistor <NUM> is connected to an upstream side of the igniter circuit <NUM>. Note that the overcurrent preventing resistor <NUM> can prevent the igniter <NUM> from operating during the abnormality diagnosis.

The overcurrent preventing resistor <NUM> is a resistor (for example, <NUM> kΩ) which prevents an overcurrent from flowing through the voltage reading unit <NUM>, and is electrically connected in parallel to the igniter circuit <NUM>. Further, the overcurrent preventing resistor <NUM> is electrically connected in series to an upstream side of the voltage amplification unit <NUM>. Note that the overcurrent preventing resistor <NUM> can prevent failure of the voltage reading unit <NUM> due to an overcurrent during the abnormality diagnosis.

The voltage amplification unit <NUM> amplifies the applied voltage (for example, an operational amplifier), and is electrically connected in series to a downstream side of the overcurrent preventing resistor <NUM>. Additionally, a downstream side of the voltage amplification unit <NUM> is electrically connected in series to the voltage reading unit <NUM>.

The voltage reading unit <NUM> is a voltmeter or the like that reads the applied voltage, and is electrically connected in series to the downstream side of the voltage amplification unit <NUM>. Further, a downstream side of the voltage reading unit <NUM> is connected to a ground <NUM>. Note that the voltage reading unit <NUM> converts a measured voltage value (an analog amount) into a digital signal and transmits the digital signal to the calculation unit <NUM>.

The light emitting unit <NUM> receives information on a result of the abnormality diagnosis determined by the calculation unit <NUM>, and causes an LED or the like to emit a light using a power supply so as to correspond to each type of the information on the determined result of the abnormality diagnosis. For example, a light emission state of each LED is controlled such that when the information on the result of the abnormality diagnosis received from the calculation unit <NUM> is information of the normal state, a normal signal is transmitted to cause a green LED to emit a light, when the information is information of the short-circuit state, a short-circuit signal is transmitted to cause a yellow LED to emit a light, and when the information is information of the disconnection state, a disconnection signal is transmitted to cause a red LED to emit a light.

Here, a specific example of a case where the calculation unit <NUM> having <NUM>-bit processing performance reads a voltage with a reading accuracy of a resistance value of the igniter circuit <NUM> set to <NUM>Ω will be described. For example, when a state in which a value of circuit resistance of the igniter circuit <NUM> is <NUM>Ω to <NUM>Ω, using an amplification factor of the voltage amplification unit <NUM> of <NUM> times, a resistance of <NUM>Ω for the overcurrent preventing resistor <NUM>, and a resistance of any value of <NUM>Ω to <NUM>Ω for the overcurrent preventing resistor <NUM>, is the normal state, the voltage value of <NUM> V to <NUM> V in the corresponding range is treated as a voltage value in the normal state, the voltage value of less than <NUM> V corresponding to a case where the resistance value of the circuit is less than <NUM>Ω is treated as a voltage value in the short-circuit state, and the voltage value of more than <NUM> V corresponding to a case where the resistance value of the circuit exceeds <NUM>Ω is treated as a voltage value in the disconnection state.

Here, the reason will be shown why in the configuration of the example above, the state in which the circuit resistance value of the igniter circuit <NUM> is <NUM>Ω to <NUM>Ω is the normal state, the state in which the circuit resistance value of the igniter circuit <NUM> is less than <NUM>Ω is the short-circuit state, and the state in which the circuit resistance value of the igniter circuit <NUM> is more than <NUM>Ω is the disconnection state.

In the configuration of the example above, the circuit resistance value of the igniter circuit <NUM> in the normal state is any value of <NUM>Ω to <NUM>Ω in a case where a resistance value of the igniter <NUM> is designed as <NUM>Ω to <NUM>Ω, a resistance of a connector connecting the igniter <NUM> to the igniter circuit <NUM> is designed as <NUM>Ω to <NUM>Ω, and a conductive wire resistance (maximum <NUM>) is designed as <NUM>Ω to <NUM>Ω in consideration of variations in values. Accordingly, if the igniter circuit <NUM> is in the short-circuit state, the circuit resistance value of the igniter circuit <NUM> is less than <NUM>Ω. Additionally, if the igniter circuit <NUM> is in the disconnection state, the circuit resistance value of the igniter circuit <NUM> exceeds <NUM>Ω, but a case where the circuit resistance value exceeds <NUM>Ω with a margin is set as the disconnection state. In this way, the state in which the circuit resistance value of the igniter circuit <NUM> is <NUM>Ω to <NUM>Ω is set as the normal state, the state in which the circuit resistance value of the igniter circuit <NUM> is less than <NUM>Ω is set as the short-circuit state, and the state in which the circuit resistance value of the igniter circuit <NUM> is more than <NUM>Ω is set as the disconnection state.

Note that when a measurement error of the igniter circuit <NUM> is corrected to be, for example, the maximum error of ±<NUM>%, the circuit resistance value of the igniter circuit <NUM> in the normal state falls within a range of <NUM>Ω to <NUM>Ω. Accordingly, when considering the measurement error of the igniter circuit <NUM>, a state in which the circuit resistance value of the igniter circuit <NUM> is <NUM>Ω to <NUM>Ω with a margin may be set as the normal state, a state in which the circuit resistance value of the igniter circuit <NUM> is less than <NUM>Ω may be set as the short-circuit state, and a state in which the circuit resistance value of the igniter circuit <NUM> is more than <NUM>Ω may be set as the disconnection state.

As described above, the normal state, the short-circuit state, and the disconnection state can be set in advance for the circuit resistance values of the igniter circuit <NUM> in consideration of the design. Then, voltages corresponding to these circuit resistance values are set respectively, and the circuit state of the igniter circuit <NUM> is diagnosed by measuring the voltage of the igniter circuit <NUM>.

Further, in the circuit abnormality diagnosis device <NUM>, increasing the reading accuracy of the resistance value of the igniter circuit <NUM> can be achieved by increasing the bit number of the calculation unit <NUM> (increasing processing capability) or decreasing the resistance value of the overcurrent preventing resistor <NUM>.

<FIG> illustrates the flight object <NUM> to which the deployed object ejection device for a flight object <NUM> is applied. The flight object <NUM> includes a fuselage <NUM>, the deployed object ejection device for a flight object <NUM> coupled to the fuselage <NUM>, one or more propulsion mechanisms (for example, propellers) <NUM> coupled to the fuselage <NUM> and configured to propel the fuselage <NUM>, and a plurality of legs <NUM> provided in a lower portion of the fuselage <NUM>.

Next, operation of the circuit abnormality diagnosis device <NUM> of the deployed object ejection device for a flight object <NUM> will be described. First, the calculation unit <NUM> transmits an operation signal for applying a predetermined voltage to the igniter circuit <NUM> to the inspection power supply <NUM> at a preset time (including the time of initial mounting) or every predetermined time. An inspection power supply <NUM> that has received the operation signal applies the predetermined voltage to the igniter circuit <NUM> via a rectifier element <NUM> and the overcurrent preventing resistor <NUM> on a downstream side. At this time, the predetermined voltage is also applied to the overcurrent preventing resistor <NUM> via the rectifier element <NUM> and the overcurrent preventing resistor <NUM>. Then, after the voltage applied via the overcurrent preventing resistor <NUM> is amplified by the voltage amplification unit <NUM>, the voltage reading unit <NUM> reads a value of the amplified voltage (the voltage value). The voltage value read by the voltage reading unit <NUM> is converted into a digital signal and then transmitted to the calculation unit <NUM>.

Subsequently, the calculation unit <NUM> diagnoses (determines) whether the igniter circuit <NUM> is in the normal state, the short-circuit state, or the disconnection state based on the received digital signal of the voltage value. When the calculation unit <NUM> diagnoses (determines) that the igniter circuit <NUM> is in the normal state, the calculation unit <NUM> transmits the normal signal to the light emitting unit <NUM>. The light emitting unit that has received the normal signal causes the green LED to emit a light. On the other hand, the calculation unit <NUM> diagnoses (determines) that the igniter circuit <NUM> is in the short-circuit state, the calculation unit <NUM> transmits the short-circuit signal to the light emitting unit <NUM>. The light emitting unit that has received the short-circuit signal causes the yellow LED to emit a light. In addition, the calculation unit <NUM> diagnoses (determines) that the igniter circuit <NUM> is in the disconnection state, the calculation unit <NUM> transmits the disconnection signal to the light emitting unit <NUM>. The light emitting unit that has received the disconnection signal causes the red LED to emit a light.

In the flight object <NUM> to which the deployed object ejection device for a flight object <NUM> configured as described above is applied, the abnormality diagnosis of the igniter circuit <NUM> can be simply and easily performed by using a voltage drop characteristic generated when the circuit resistance value decreases without using a highly accurate current sensor that costs high.

Additionally, the light emitting unit <NUM> can easily notify the outside of the device whether the result of the abnormality diagnosis of the igniter circuit <NUM> is the normal state, the short-circuit state, or the disconnection state.

Next, a second embodiment of the present invention will be described with reference to <FIG> and <FIG>. Note that in the present embodiment, parts having the same reference numerals as those in the first embodiment up to the last two digits are the same as the parts in the first embodiment, and thus descriptions thereof may be omitted.

A deployed object ejection device for a flight object (not illustrated) according to the present embodiment can be applied to the same flight object (not illustrated) as the flight object <NUM> of the first embodiment, instead of the deployed object ejection device for a flight object <NUM> of the first embodiment. Further, as illustrated in <FIG>, the deployed object ejection device for a flight object according to the present embodiment includes substantially the same circuit abnormality diagnosis device <NUM> as that of the first embodiment, but is different from that of the first embodiment in including a power storage unit <NUM>, a switch unit <NUM>, and a physical switch unit <NUM> provided in an igniter circuit <NUM>.

The power storage unit <NUM> has a power storage function like a capacitor, and can discharge electricity as needed. Further, a downstream side of the power storage unit <NUM> is electrically connected in series with the switch unit <NUM>. Note that the power storage unit <NUM> stores power in advance before operation of the deployed object ejection device for a flight object <NUM>.

The switch unit <NUM> is electrically connected to the downstream side of the power storage unit <NUM>, and is electrically connected in series to the physical switch unit <NUM> on a downstream side. In addition, when receiving an ON signal from a calculation unit <NUM>, the switch unit <NUM> turns on a switch function, and a stored current is discharged from the power storage unit <NUM> to a physical switch unit <NUM> side.

The physical switch unit <NUM> prevents a current from flowing through the igniter circuit <NUM> when operation is not required, for example, during transportation. Examples of the physical switch unit <NUM> include those illustrated in <FIG>. The physical switch unit <NUM> in <FIG> will be described below.

The physical switch unit <NUM> in <FIG> includes a main body portion <NUM>, a pin portion <NUM>, and a switch mechanism <NUM>.

The main body portion <NUM> includes a tubular portion <NUM> into which a long rod-shaped pin portion <NUM> is inserted, a recess portion <NUM> into which a ball portion of a ball lock mechanism <NUM> provided at a predetermined position from a tip end of the pin portion <NUM> fits, and a space <NUM> in which the switch mechanism <NUM> is fixedly disposed.

As illustrated in <FIG>, a part in the middle of the tubular portion <NUM> and a part of the space <NUM> are communicated with each other, and in the communicated space, a portion including a leaf spring <NUM>, a roll portion <NUM>, and a pressing portion <NUM> of the switch mechanism <NUM> is in a state of being movable within a predetermined range around one end side of the leaf spring <NUM> (a main body side of the switch mechanism <NUM>) as an axis.

The pin portion <NUM> includes a ring-shaped member <NUM> provided near one end portion and the ball lock mechanism <NUM> provided at a predetermined position from the tip end of the other end portion.

In the ball lock mechanism <NUM>, a spring (not illustrated) is provided inside a recess portion provided in the pin portion <NUM>, and biases the ball portion provided in a state of not protruding from the recess portion toward the outside. Accordingly, in the state of <FIG>, the ball lock mechanism <NUM> is in a state in which the ball portion protrudes most from the pin portion <NUM>; in the state of <FIG>, the ball lock mechanism <NUM> is pushed by the tubular portion <NUM> to be recessed in and enter the pin portion <NUM>; and in the state of <FIG>, the ball lock mechanism <NUM> is in a state in which the ball portion protrudes from the pin portion <NUM> and fits into the recess portion <NUM>. Therefore, in the state of <FIG>, the pin portion <NUM> is temporarily fixed to the main body portion <NUM>, and cannot be easily removed.

The switch mechanism <NUM> includes a main body 161a, an on/off switch unit <NUM>, the leaf spring <NUM>, the roll portion <NUM>, and the pressing portion <NUM>.

The on/off switch unit <NUM> is provided with a spring (not illustrated) having a biasing force from the inside of the switch mechanism <NUM> to the outside, and can be depressed by being pressed by the pressing portion <NUM> as shown in <FIG> of the protruding state, <FIG> in this order. In addition, the on/off switch unit <NUM> is in an on state (an electrical conduction state) when in the protruding state of <FIG>, and is in an off state (an electrical disconnection state) when in the state shown in <FIG>.

One end portion of the leaf spring <NUM> is fixed to the main body 161a of the switch mechanism <NUM>, and the other end portion is movable within a predetermined range. Additionally, at the other end portion of the leaf spring <NUM>, the roll portion <NUM> is rotatably and pivotally supported, and a pressing portion <NUM> is provided.

Since the roll portion <NUM> is rotatably and pivotally supported by the other end portion of the leaf spring <NUM>, as illustrated in <FIG>, the roll portion <NUM> rotates to reduce friction generated when the tip end of the pin portion <NUM> abuts on the roll portion <NUM>. Accordingly, the pin portion <NUM> can be smoothly inserted into the tubular portion <NUM>. Further, certainly, the pin portion <NUM> can also be smoothly taken out from the tubular portion <NUM>.

According to the physical switch unit <NUM>, the following operation can be performed in the present embodiment. For example, in a case where the flight object is flying with the physical switch unit <NUM> on, an operation signal is transmitted from the calculation unit <NUM> when the calculation unit <NUM> diagnoses (determines) that the igniter circuit <NUM> is in an abnormal state (a short-circuit state or a disconnection state), and the switch unit <NUM> that has received the operation signal discharges the current from the power storage unit <NUM>. The current is applied to the igniter circuit <NUM> via the physical switch unit <NUM> to start an igniter <NUM>. Accordingly, after a parachute or a paraglider is ejected from the inside to the outside of a housing of the same ejection device as that of the first embodiment, the parachute or the paraglider is deployed.

In the flight object to which the deployed object ejection device for a flight object <NUM> configured as described above is applied, the same effects as those of the first embodiment can be produced.

Further, according to the present embodiment, by keeping the physical switch unit <NUM> off in a state where the flight object is not used, for example, during transportation, operation due to a malfunction (unintended energization of an operating current) of the igniter can be prevented. Additionally, since the pin portion <NUM> is temporarily fixed to the main body portion <NUM> by the ball lock mechanism, the pin portion <NUM> is not be easily removed, and the operation due to the malfunction (unintended energization of an operating current) of the igniter can be further prevented.

Further, according to the present embodiment, for example, in a case where the flight object is flying with the physical switch unit <NUM> on, the igniter <NUM> is actuated when it is diagnosed (determined) that the igniter circuit <NUM> is in the abnormal state (the short-circuit state or the disconnection state), and the parachute or the paraglider can be deployed after the parachute or the paraglider is ejected from the inside to the outside of the housing of the same ejection device as that of the first embodiment by a gas generator. Consequently, the flight object can be protected before an abnormality occurs in a portion other than an igniter circuit of the igniter circuit <NUM>. In other words, when an abnormality occurs in the portion other than the igniter circuit, it is possible to prevent a situation in which an abnormality also occurs in the igniter circuit and the deployed object ejection device for a flight object does not operate.

Next, a third embodiment of the present invention will be described with reference to <FIG>. Note that in the present embodiment, parts having the same reference numerals as those in the first embodiment up to the last two digits are the same as the parts in the first embodiment, and thus descriptions thereof may be omitted. Further, in the present embodiment, the same part names as those in the second embodiment are used for the same parts as those in the second embodiment, and descriptions thereof may be omitted.

An airbag device for a flight object <NUM> according to the present embodiment can be applied to the same flight object (not illustrated) as the flight object <NUM> of the first embodiment. Further, the airbag device for a flight object <NUM> according to the present embodiment includes the same circuit abnormality diagnosis device as that of the second embodiment, and is the same as that of the second embodiment except that an igniter (not illustrated) in the present embodiment is provided in a gas generator (not illustrated) that generates a gas to inflate an airbag <NUM>. Details will be described below.

A flight object <NUM> includes the airbag device for a flight object <NUM> that inflates the airbag <NUM> by a gas pressure generated based on operation of the same gas generator (not illustrated) as the gas generator of the first embodiment. Note that the airbag <NUM> and the gas generator before deployment (device actuation) are in a state of being accommodated in a container (not illustrated), and in this state, the airbag device for a flight object <NUM> is provided at a lower portion of a fuselage <NUM> in the normal attitude shown in <FIG>.

A calculation unit of the airbag device for a flight object <NUM> according to the present embodiment diagnoses (determines) a state of an igniter circuit by the same circuit abnormality diagnosis device as that of the second embodiment.

According to the airbag device for a flight object <NUM>, the following operation can be performed in the present embodiment. For example, in a case where the flight object is flying with a physical switch unit on, an operation signal is transmitted from the calculation unit when the calculation unit diagnoses (determines) that the igniter circuit is in an abnormal state (a short-circuit state or a disconnection state), and the switch unit that has received the operation signal discharges a current from a power storage unit. The current is applied to the igniter circuit via the physical switch unit, a gas generating agent is combusted by starting the igniter, and the airbag <NUM> is inflated and deployed by the generated gas.

In the flight object to which the airbag device for a flight object <NUM> configured as described above is applied, the same effects as those of the first embodiment can be produced.

Further, according to the present embodiment, for example, in a case where the flight object is flying with the physical switch unit <NUM> on, the airbag <NUM> can be deployed after the igniter is actuated and the airbag <NUM> is inflated by the gas generator when it is diagnosed (determined) that the igniter circuit is in an abnormal state (a short-circuit state or a disconnection state). Consequently, the flight object can be protected before an abnormality occurs in a portion other than the igniter circuit. In other words, when an abnormality occurs in the portion other than the igniter circuit, it is possible to prevent a situation in which an abnormality also occurs in the igniter circuit and the airbag device for a flight object <NUM> does not operates.

Next, a fourth embodiment of the present invention will be described with reference to <FIG> and <FIG>. Note that in the present embodiment, parts having the same reference numerals as those in the first embodiment up to the last two digits are the same as the parts in the first embodiment, and thus descriptions thereof may be omitted. Further, in the present embodiment, the same part names as those in the second embodiment are used for the same parts as those in the second embodiment, and descriptions thereof may be omitted.

As illustrated in <FIG>, a cutting device for a flight object <NUM> according to the present embodiment can be applied to the same flight object (not illustrated) as the flight object <NUM> of the first embodiment. Further, the cutting device for a flight object <NUM> according to the present embodiment includes the same circuit abnormality diagnosis device as that of the second embodiment, and is the same as that of the second embodiment except that an igniter <NUM> according to the present embodiment cuts (breaks) a current supply path <NUM>. Details will be described below.

The cutting device for a flight object <NUM> includes the igniter <NUM> which is an example of a destructive source (a power source), a cutting chamber <NUM> having an internal space, a rupture plate <NUM> which is damaged and cleaved by application of heat and pressure generated by operation of the igniter <NUM> and cuts the current supply path <NUM>, and the same physical switch unit <NUM> as that of the second embodiment.

The igniter <NUM> generates flame, and includes an ignition unit <NUM> internally including an ignition charge (not illustrated) that ignites and burns during operation to generate flame and a resistor (not illustrated) for igniting the ignition charge, and a pair of terminal pins <NUM>, <NUM> connected to the ignition unit <NUM>. Note that the pair of terminal pins <NUM>, <NUM> is also a part of an igniter circuit.

The rupture plate <NUM> is formed in, for example, a circular shape in plan view, and is provided in the cutting chamber <NUM> and below the igniter <NUM>. Since the rupture plate <NUM> is easily cleaved and requires an appropriate strength, it can be made of a lightweight metal such as iron and aluminum. Further, the rupture plate <NUM> may be made of a non-conductive material, for example, a hard resin material such as ebonite, or fine ceramics. The rupture plate <NUM> has a width larger than the width of the igniter <NUM> in the length direction of the current supply path <NUM>. The igniter <NUM> is held on an upper wall of the cutting chamber <NUM> so that the generated flame can be emitted toward the rupture plate <NUM> located below.

For example, in a case where the flight object is flying with the physical switch unit <NUM> on, an operation signal is transmitted from a calculation unit when the calculation unit diagnoses (determines) that the igniter circuit is in an abnormal state (a short-circuit state or a disconnection state), and the switch unit that has received the operation signal discharges a current from a power storage unit. A predetermined amount of the current flows to the resistor via the physical switch unit <NUM> and the pair of terminal pins <NUM>, <NUM>. When the current flows through the resistor, Joule heat is generated in the resistor, and the ignition charge starts combustion. The hot flame resulting from the combustion ruptures a squib cup (not illustrated) containing the ignition charge. In the igniter <NUM>, the time from when the current flows through the resistor to when the resistor is actuated is generally <NUM> milliseconds or less in a case where a nichrome wire is used for the resistor.

A through hole <NUM> is provided in a peripheral wall of the cutting chamber <NUM>, and a through hole <NUM> is provided in another portion of the peripheral wall. The current supply path <NUM> is bridged through the through holes <NUM> and <NUM>. The current supply path <NUM> is made of, for example, a metal plate or a metal wire, and has one end connected to a storage battery (not illustrated) of an electric circuit and the other end connected to an electrical device (not illustrated) of the flight object.

In the configuration as described above, in a case where the flight object is flying with the physical switch unit <NUM> on when an abnormality of the flight object is detected, the rupture plate <NUM> is damaged by heat and pressure generated by operation of the igniter <NUM> when a predetermined amount of the current is supplied to the pair of terminal pins <NUM>, <NUM> of the igniter <NUM> in a case where the calculation unit diagnoses (determines) that the igniter circuit is in the abnormal state (the short-circuit state or the disconnection state). In this case, the rupture plate <NUM> is damaged such that a central portion thereof is cleaved and bent toward the current supply path <NUM>. Then, the current supply path <NUM> is cut as in <FIG> by the rupture plate <NUM> damaged as described above. Note that in the present invention, a target of the current supply path <NUM> to be cut off is desirably a wiring from a positive electrode portion.

In this way, according to the cutting device for a flight object <NUM> of the present embodiment, for example, when the flight object is flying with the physical switch unit <NUM> on and it is diagnosed (determined) that the igniter circuit is in the abnormal state (the short-circuit state or the disconnection state), the igniter <NUM> is actuated as a destructive source. The igniter <NUM> applies heat and pressure toward the current supply path <NUM> to the rupture plate <NUM>. As a result, the rupture plate <NUM> can be damaged and cleaved, and the current supply path <NUM> can be cut by a cleaved portion of the cleaved rupture plate <NUM>. Accordingly, the current supply to the electrical device of the flight object can be cut off. Consequently, it is possible to prevent occurrence of a contact accident between a part such as an operating propeller and a person, fire, or an electric shock when the flight object crashes. Additionally, when a part of the propeller stops, the flight is normally maintained by controlling the rotation speed of another propeller, but in this case, a load on a motor is excessively applied and thus causes failure. However, since the current supply can be forcibly cut off as described above, the motor failure can be avoided.

Although the embodiments of the present invention have been described above, they are merely specific examples and do not particularly limit the present invention, and the specific configurations can be modified in design as appropriate, as long as these fall within the scope of the appended claims.

For example, in each of the above embodiments, the igniter circuit of the igniter has been described as an example of the circuit whose abnormality is diagnosed, but a target circuit of the abnormality diagnosis is not limited thereto. For example, an abnormality diagnosis of a circuit related to the ejection device other than the igniter circuit may be performed.

In addition, the calculation unit in each of the above embodiments may also have the function of the voltage reading unit. At this time, the calculation unit is electrically connected to the ground.

Further in the pin portion <NUM> in the second embodiment, the end portion may be tapered. Accordingly, the tapered shape makes it easier to rotate a roller portion, and thus, the pin portion <NUM> can be inserted more smoothly.

Further, in the fourth embodiment, the current supply path is cut, but the present invention is not limited to the one exemplified. For example, there may be a situation where it is desirable to cut a line connected to the parachute or the paraglider after deployment. In such a situation, the line may be burned off by flame of the igniter, or may be cut by operating a cutting means such as a cutter using a flame force of the igniter.

Claim 1:
A circuit abnormality diagnosis device (<NUM>) that diagnoses a circuit abnormality in a safety device for a flight object including an igniter (<NUM>) and a circuit connected to the igniter, the circuit abnormality diagnosis device comprising:
a power supply (<NUM>) capable of loading a test voltage to the circuit;
a calculation unit (<NUM>) that controls on/off of the power supply: characterized in that it further comprises :
a first overcurrent prevention unit (<NUM>) that is electrically connected in series to the power supply and prevents an overcurrent from flowing through the circuit;
a voltage amplification unit (<NUM>) that is configured to be electrically connected in parallel to the circuit and amplifies a voltage to a predetermined order;
a voltage reading unit (<NUM>) that is electrically connected in series to the voltage amplification unit and reads a value of the voltage amplified by the voltage amplification unit (hereinafter, the voltage value); and
a second overcurrent prevention unit (<NUM>) that is electrically connected in series to the voltage reading unit on an upstream side of the voltage reading unit and prevents an overcurrent from flowing,
wherein the calculation unit
receives information on the voltage value from the voltage reading unit, and determines that
a case where the voltage value is within a range of a first voltage value V<NUM> or more and a second voltage value V<NUM> or less, which is set in advance as a range of voltage values indicating that the circuit is normal, is a normal state;
a case where the voltage value is less than the voltage value V<NUM> is a short-circuit state in which the circuit is short-circuited; and
a case where the voltage value is higher than the voltage value V<NUM> is a disconnection state in which the circuit is disconnected.