KR101528904B1 - Method for controlling separating flight vehicle using time delay - Google Patents

Abstract

The present invention provides a method for controlling separation of a flying object using time delay capable of detonating a separation device by generating a loading signal and a detonating signal by hardware, and generating a detonating signal with time difference. According to the present invention, the method comprises: a step of determining whether the current state of a flying object is normal; a step of generating and outputting electric energy for separating a body part of the flying object from a propulsion part of the flying object in order based on predetermined time difference when determining that the current state of the flying object is abnormal; a step of separating the body part from the propulsion part on the basis of the electric energy input in order; and a step of outputting an image by using a terminal formed outside the flying object by obtaining the image containing a process, wherein the body part is separated from the propulsion part.

Description

TECHNICAL FIELD [0001] The present invention relates to a method and apparatus for separating flight vehicles using time delay,

The present invention relates to a method for separating a flying body into a body part and a propulsion part. More particularly, the present invention relates to a method for separating a flight body into a body part and a propulsion part in the event of an emergency.

Emergency stop system is installed in the missile to prepare for the emergency situation such as the abnormal behavior of the missile and the escape of safety zone during the missile flight test.

The existing emergency shutdown system consists of new buildings and explosives, and electronic / physical devices are installed inside the fuse to detonate explosives. The fuse also constitutes a safety device with several loading signals.

However, such an emergency termination system has the following problems.

First, in the case of a system executed by the processor judgment of the operation control device of the missile gun, the emergency explosion system can not be normally operated when a problem occurs in the flight while the emergency explosion system is loaded and allowed to fire.

Second, in the case of an electronic fuse, when exploding a number of explosives, it requires a temporary amount of a snubber current proportional to the number of explosives.

Korean Patent No. 1,063,843 proposes an air bag separation control device. However, the above-mentioned problem can not be solved because the apparatus performs horizontal separation by mechanical assembly without using explosives in order to eliminate an impact amount due to the explosion pressure.

Disclosure of Invention Technical Problem [8] The present invention has been devised in order to solve the above-described problems, and it is an object of the present invention to provide a flight object separation control method using a time delay generated by generating a loading signal and an awake signal by hardware, .

However, the objects of the present invention are not limited to those mentioned above, and other objects not mentioned can be clearly understood by those skilled in the art from the following description.

SUMMARY OF THE INVENTION The present invention has been made in order to achieve the above-mentioned object, and it is an object of the present invention to provide an air conditioner, An electric energy generating unit sequentially generating and outputting electric energy for separating the body of the air vehicle and the propulsion unit of the air vehicle based on a predetermined time difference when the current state of the air vehicle is determined to be abnormal; And a flying body separation control unit for separating the body unit and the propulsion unit based on the electric energy sequentially input to the flying body separation control unit.

Preferably, the flight status determination unit compares the steering control information input to the flight and the motion information of the flight to determine whether the current status of the flight is normal, or the flight travels along a predetermined flight path Based on whether or not the current state of the air vehicle is normal.

Preferably, the electric energy generating unit sequentially generates and outputs the electric energy using at least two time delay circuit units and a constant current circuit unit connected to each time delay circuit unit.

Preferably, at least two detonators are attached to the connecting portion between the body and the propulsion unit, and the air bag separation control unit sequentially ignites the detonator using the electric energy whenever the electric energy is inputted, And finally separates the propulsion section and the propulsion section.

Preferably, the air bag separation control apparatus includes a first determination unit for determining whether or not the electric energy is generated and output at a current time point; A second determination unit for determining whether the elapsed time from the time when the current state of the airplane is determined to be abnormal to the current time is greater than or equal to a reference time when it is determined that the electric energy is not generated and output at the present time; And a signal receiving unit for receiving a signal requesting the sequential generation of the electric energy from the outside if it is determined that the elapsed time is equal to or longer than the reference time.

Preferably, the air bag separation control device includes a first power supply unit for supplying the first power supply necessary for the air conditioner determination unit to operate; And a second power supply unit for supplying a second power supply necessary for the electric energy generation unit to operate.

Preferably, the air bag separation control apparatus further includes a supply connection line connecting the first power supply unit and the second power supply unit so as to make the second power supply available as the first power supply, And a Schottky diode is formed on one side to prevent the first power source from being supplied to the second power source.

Advantageously, the second power supply utilizes the supply connection line to supply the second power source to the first power source before the airplane starts flying.

Preferably, the second power supply unit supplies power to the second power source having a higher voltage than the first power source.

According to another aspect of the present invention, Sequentially generating and outputting electric energy for separating the body part of the air vehicle and the propulsion part of the air vehicle based on a predetermined time difference when it is determined that the current state of the air vehicle is abnormal; Separating the body and the propulsion unit based on the electrical energy sequentially input; And a step of acquiring an image of the process of separating the body part and the propulsion part and outputting the image using a terminal provided outside the air vehicle, .

The controller may determine whether the current state of the airplane is normal by comparing the manipulation control information input to the airplane and the motion information of the airplane or may determine whether the airplane travels along a predetermined flight path Based on whether or not the current state of the air vehicle is normal.

Preferably, the sequentially generating and outputting step sequentially generates and outputs the electric energy using at least two time delay circuit parts and a constant current circuit part connected to each time delay circuit part.

Preferably, at least two detonators are attached to the connecting portion of the body portion and the propulsion portion, and the separating step consecutively expels the detonator using the electric energy each time the electric energy is inputted, And finally separates the propulsion section and the propulsion section.

Preferably, the step of determining whether or not the electric energy is generated and outputted at the present time between the step of sequentially generating and outputting and the step of separating comprises: Determining whether the elapsed time from the time when the current state of the airplane is determined to be abnormal to the current time is equal to or longer than a reference time when it is determined that the electric energy is not generated and output at the present time; And receiving a signal requesting sequential generation of the electric energy from the outside if it is determined that the elapsed time is equal to or longer than the reference time.

Preferably, the method further comprises a step of supplying a first power source necessary for performing the determining step prior to the determining step, wherein the step of sequentially generating and outputting, before the step of sequentially generating and outputting, And supplying a second power source necessary for performing the second power supply.

Preferably, the step of supplying the second power supply may include supplying the second power source to the second power source using a supply connection line that connects the configuration for supplying the first power source and the configuration for supplying the second power source before the air vehicle starts flying, And supplies power to the first power source.

Preferably, the supplying of the first power is performed by using a Schottky diode formed on one side of a supply connection line connecting the configuration for supplying the first power and the configuration for supplying the second power, To the second power source.

Preferably, the step of supplying the second power supplies a power source having a voltage higher than that of the first power source to the second power source.

The present invention relates to a method for controlling flight separation using time delay, and the following effects can be obtained.

First, the present invention generates a loading signal and an awakening signal by hardware, thereby exploiting a single separation device. The present invention makes it possible to generate a hardware load and a malfunction signal even if an error occurs in the operation control device processor.

Second, the present invention proposes a safety design for preventing erroneous circuit operation of a new pipe. The present invention can prevent the occurrence of an erroneous signal due to a malfunction of a new pipe circuit in a power ramp interval.

Third, the present invention utilizes a design and operation method of an arithmetic and control unit having a built-in circuit for a single stage unit. The present invention can reduce the weight of the end separating device by incorporating a new pipe device into the operation control device, thereby eliminating the need for a separate pipe device.

Fourth, the present invention generates an ignition signal with a time lag. The present invention can reduce the instantaneous maximum required power of the system through the function of generating two or more single separation unit detonating time difference signals.

FIG. 1 is a conceptual diagram illustrating an internal configuration and a connection relationship of an operation control device incorporating a single stage device fuze system according to an embodiment of the present invention.
FIG. 2 is a flowchart illustrating an operation method of an operation control device incorporating a simplex separation device system according to an embodiment of the present invention. Referring to FIG.
3 is a conceptual diagram showing an internal configuration of a fuse circuit unit constituting an operation control device according to an embodiment of the present invention.
4 is a flowchart illustrating a method of operating a new tube circuit according to an embodiment of the present invention.
5 is a reference diagram showing experimental results according to an embodiment of the present invention.
FIG. 6 is a block diagram illustrating an apparatus for controlling flight separation using a time delay according to a preferred embodiment of the present invention.
FIG. 7 is a flowchart illustrating an air vehicle separation control method using a time delay according to a preferred embodiment of the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In the drawings, the same reference numerals are used to designate the same or similar components throughout the drawings. In the following description of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the subject matter of the present invention rather unclear. In addition, the preferred embodiments of the present invention will be described below, but it is needless to say that the technical idea of the present invention is not limited thereto and can be variously modified by those skilled in the art.

The present invention proposes a system for short-ended time-delayed emergency termination.

Emergency shutdown system is a system using a single separation device, which connects the front part and the rear part of the missile with a single separation device. When the system emergency shutdown is required, the single separation device is detonated to separate the front part and the rear part, Emergency shutdown of the system. Emergency shutdown systems also require loading and disarming methods that consider electronic / physical fuse and safety to detonate a single disconnect device.

FIG. 1 is a conceptual diagram illustrating an internal configuration and a connection relationship of an operation control device incorporating a single stage device fuze system according to an embodiment of the present invention.

The present invention is basically the same as the first embodiment of the present invention except that the system 100 including the launch device 110, the battery 120, the power supply 130, the data remote receiving device 150, 161, a single separation device 2 162, and the like, and only the items related to the new system among functions of the operation control device 140 are shown.

The launch device 110 is a mounting device for launching the missile.

The battery 120 is a battery that supplies power to the missile.

The power supply 130 is a power supply for supplying power to the missile.

The arithmetic and control unit 140 is an apparatus for performing arithmetic processing and control for operating the missile.

The arithmetic and control unit 140 includes a processor unit 141, a power supply circuit unit 142, a fuse circuit unit 143 and a Schottky diode 144.

The processor unit 141 is a circuit unit on which a processor is mounted.

The power supply circuit portion 142 is a circuit portion for generating power used in the operation control device 140.

The new pipe circuit part 143 is a circuit part that performs the new pipe function.

The Schottky diode 144 is a diode that prevents the system power supply 173 from flowing into the ignition power supply 172 and the battery 120.

The data remote receiving device 150 is an emergency explosion command receiving device for remote emergency explosion.

The first stage separator 161 and the second stage separator 162 are devices that can connect the front part and the rear part of the guide car with explosives so that they can be exploded.

The loading signal 171 is a signal generated at the launch device 110 when the guided vehicle is fired.

The ignition power source 172 is a power source supplied from the battery 120 and is used as an ignition power source for the new pipe circuit part 143. [

The system power supply 173 is a power supply to the power supply circuit 142.

The new pipe power source 174 is a power source supplied to the electronic circuit of the new pipe circuit portion 143.

The self-length signal 1 (175) is an initiation permission signal generated by the processor unit 141 itself.

The self-destructing signal 2 (176) is an enabling permission signal generated when the data remote receiving apparatus 150 receives the demolition command.

The ceiling current 1 177 is a current input from the trunk circuit portion 143 to the single separator 1 161 to ignite the single separator 1 161.

The awakening current 2 178 is a current input from the fuse circuit 143 to the short-circuit separator 2 162 to ignite the short-circuit separator 2 162.

FIG. 2 is a flowchart illustrating an operation method of an operation control device incorporating a simplex separation device system according to an embodiment of the present invention. Referring to FIG.

The power supply 130 supplies the power supply 174 to the power supply circuit portion 143 of the operation control device 140 via the power supply circuit portion 142 in steps S205 and S210 to bring the power supply circuit 174 into a normal operation state in step S215.

Here, the ignition power supply 172 by the battery 120 is not initially supplied. The power of the power supply 130 is not supplied to the ignition power supply 172 by the Schottky diode 144. [ Therefore, even if there is a malfunction in the power ramp interval that may occur depending on the degree of circuit design of the new pipe circuit part 143 during the initial power supply through the power supply 130, the short-circuiting device 161, Is safe.

The missile is supplied with the system power supply 173 from the power supply 130 and then supplied with the ignition power supply 172 and the system power supply 173 by the operation of the battery 120 by the user operation S225, S230). However, the voltage of the battery 120 should be higher than the voltage supplied by the power supply 130. In addition, the power supply 130 must have another Schottky diode internally.

The launch device 110 is a mechanism device for launching the missile. The launching device 110 provides a loading signal 171 so that the arithmetic and control unit 140 can detect that the missile is fired and out of the launching device 110 (S235). The charging signal 171 is transmitted to the new pipe circuit 143 and utilized as a signal source for charging the new pipe circuit 143 when the charcoal is fired.

When the processor unit 141 detects abnormal behavior and departure from the safety zone during flight of the missile, it transmits the self-length signal 1 175 to the new tube circuit 143 (S240) And transmits the self-destructing signal 2 176 to the new pipe circuit 143 remotely (S245).

The new pipe circuit part 143 receiving the at least one self-wide-width signal is activated (S247) to generate the aerobic current 1 177 and the aerobic current 2 178 (S250 and S255) 2 162 and the like (S260, S265), and emergency fire is terminated (S270).

3 is a conceptual diagram showing an internal configuration of a fuse circuit unit constituting an operation control device according to an embodiment of the present invention. Hereinafter, the function and operation of each component constituting the novel tube circuit portion 143 will be described.

The circuit power supply unit 310 receives the fuse power supply 174 through the power supply circuit unit 350. The fuse power supply 174 supplied to the circuit power supply unit 310 is used for the fuse circuit unit 143 to operate.

The time delay circuit 1 (320a) and the time delay circuit 2 (320b) are circuits for delaying and outputting the detonation permission signal 372 with a time delay. In this embodiment, for example, two time delay circuits are formed in the new pipe circuit 143. However, the number of time delay circuits in the present invention is not limited to this.

The detonation permission signal 372 is a signal output after the self-length-width signal 1 (175) and the self-length-width signal 2 (176) are OR-processed.

Buffer enable signal 371 is a signal that activates or deactivates 3-state buffer 330. Buffer activation signal 371 is based on loading signal 171.

The 3-state buffer 330 receives the input signals delayed by the time delay circuit 1 320a and the time delay circuit 2 320b at the time of activation into the delayed enable signal 1 374 and the delayed enable signal 2 375 . In addition, the 3-state buffer 330 switches the above output to a high impedance state when inactive.

The detonation permission delay signal 1 374 and the detonation permission delay signal 2 375 are signals delayed and outputted by the time delay circuit 1 320a and the time delay circuit 2 320b.

The ignition power supply electronic switch 350 is an electronic switch for turning on the switch upon activation by the ignition power supply activating signal 373 and outputting the ignition power supply 172 to the ignition current power supply 376. The ignition power supply electronic switch 350 is configured such that the ignition power supply 172 is input to the constant current circuit 1 360a and the constant current circuit 2 360b as the ignition current power supply 376 when inactivated by the ignition power activation signal 373 .

The ignition power activation signal 373 is a signal to activate or deactivate the ignition power electronic switch 350.

The ignition current source 376 is a source for generating the ignition current 1 177 and the ignition current 2 178 generated in the constant current circuit 1 360a and the constant current circuit 2 360b.

The constant current circuit 1 360a and the constant current circuit 2 360b generate a ceasing current 1 177 as a source when the ceasing permission delay signal 1 374 and the ceasing permission delay signal 2 375 are applied, And an awakening current 2 (178).

On the other hand, a pull-down resistor 340 is applied to one side of the connection line between the 3-state buffer 330 and the ignition power supply electronic switch 350, and a connection line between the 3-state buffer 330 and the constant current circuit 1 360a, A pull-down resistor 340 is also applied to one side of the connection line of the buffer 330 and the constant current circuit 2 (360b).

4 is a flowchart illustrating a method of operating a new tube circuit according to an embodiment of the present invention.

The new pipe circuit 143 receives the new pipe power supply 174 and turns all the electronic circuits into a normal operation state (S405). Here, since the ignition power source 172 is not inputted, the awakening currents 1 177 and the awakening currents 2 178 do not occur even if various signals of the new tube circuit 143 malfunction in the power ramp.

Thereafter, when the ignition power source 172 is applied after various signals outside the new pipe circuit 143 are set to a normal initial state, preparation for emergency explosion is completed (S410).

① Loading procedure

When the loading signal 171 is generated (S415), the 3-state buffer 330 is activated (S425) through the buffer activation signal 371 (S420).

When the 3-state buffer 330 is activated, the input of the explosion enable signal 372 by the self-explosion signal 1 (175) or the self-explosion signal 2 (176) is switched to the state of outputting by the explosion power supply activating signal 373.

And the output of the time delay circuit 1 (320a) and the time delay circuit 2 (320b) is switched to a state of being output to the ignition permission delay signal 1 (374) and the ignition permission delay signal 2 (375).

② Procedure for generating an aerial signal

When the self-length signal 1 (175) or the self-length signal 2 (176) is input (S430 and S435), an exploitation permission signal 372 is generated through a hardware OR operation (S440).

The detonation enable signal 372 generates the awakening power source activation signal 373 through the 3-state buffer 330 and activates the time delay circuit 1 320a and the time delay circuit 2 320b (S460, S480).

The time delay circuit 1 (320a) and the time delay circuit 2 (320b) have different time delays and output an awake permission signal at different time points, and the output signal is passed through a 3-state buffer 330, (Step S465 and step S485).

For example, time delay circuit 1 320a delays time T1 and time delay circuit 2 320b delays time T2. T1 and T2 have different values.

While the signal is delayed in the time delay circuit 1 (320a) and the time delay circuit 2 (320b), the awakening power supply activation signal 373 activates the awning power supply electronic switch 350 (S450) And is supplied to the constant current circuit 1 (360a) and the constant current circuit 2 (360b) (S455).

Here, even if the charging of the new tube circuit part 143 is completed, the awkward current power source 376 is supplied according to whether the ignition power source electronic switch 350 is operated or not so that the ignition current power source 376 is applied only after actual charging Thereby enhancing safety.

When the detonation permitting delay signal 1 374 and the detonation permitting delay signal 2 375 are generated, the constant current circuit 1 360a and the constant current circuit 2 360b are activated (S470, S490). At this time, the awakening current 1 (177) and the awakening current 2 (178) are generated only when the power source 376 for the awakening current is applied (S475, S495).

In this embodiment, the awakening current 1 (177) and the awakening current 2 (178) are generated at different times according to the time delay of the explosion permitting delay signal 1 374 and the explosion permitting delay signal 2 375, However, only one instantaneous current is required to reduce the instantaneous maximum power requirement of the system.

Through the above-described design, the time difference can be exploited through the data remote receiver 150 even during the abnormal operation of the processor unit 141 during the missile flight.

5 is a reference diagram showing experimental results according to an embodiment of the present invention.

FIG. 5 is a graphical representation of the result of measurement of the delayed permit signal. As shown in FIG. 5, the delayed enable signal 1 374 delayed in time with different values T1 and T2 according to the self- And the detonation permission delay signal 2 (375). The detonation permission signal 372 is a signal obtained by calculating the detonation permission delay signal 1 374 and the detonation permission delay signal 2 375 using the OR gate.

The above-described embodiment of the present invention can be applied to an emergency shutdown system using a single separation device, various fuse systems requiring a safety device, and the like.

1 to 5, an embodiment of the present invention has been described. Best Mode for Carrying Out the Invention Hereinafter, preferred forms of the present invention that can be inferred from the above embodiment will be described.

FIG. 6 is a block diagram illustrating an apparatus for controlling flight separation using a time delay according to a preferred embodiment of the present invention.

The air bag separation control apparatus 600 using time delay according to the preferred embodiment of the present invention includes a flight state determination unit 605, an electric energy generation unit 610, a flight separation control unit 615, a power supply unit 620, (625).

The power supply unit 620 performs a function of supplying power to each configuration of the air bag separation control apparatus 600.

The main control unit 625 controls the overall operation of each component constituting the air vehicle separation control apparatus 600. [

The flight status determination unit 605 determines whether the current status of the flight is normal or not. The flight status determination unit 605 is a concept corresponding to the processor unit 141 of FIG.

The flight state determination unit 605 compares the steering control information input to the airplane with the motion information of the airplane to determine whether the current state of the airplane is normal or whether the airplane travels along a predetermined flight path It is possible to judge whether the current state of the air vehicle is normal or not.

When it is determined whether the current state of the air vehicle is normal by comparing the steering control information input to the air vehicle and the motion information of the air vehicle, the air conditioner state determination unit 605 determines whether the steering control information matches the motion information And determines that the current state of the flying object is abnormal if it is determined that the steering control information does not match the motion information.

In addition, when it is determined whether the current state of the air vehicle is normal based on whether the air vehicle is traveling along a predetermined flight path, the air conditioner state determination unit 605 determines whether the air vehicle It is judged that the state is normal. If it is judged that the flight body is not observing the flight route, it is judged that the current state of the flight body is abnormal.

The electric energy generating unit 610 sequentially generates and outputs electrical energy for separating the body of the air vehicle and the propulsion unit of the air vehicle based on a predetermined time difference when it is determined that the current state of the air vehicle is abnormal. The electric energy generating unit 610 corresponds to the new tube circuit unit 143 of FIG.

The electric energy generating unit 610 may sequentially generate and output electric energy using at least two time delay circuit units and a constant current circuit unit connected to each time delay circuit unit.

The air body separation control unit 615 performs a function of separating the body part and the propulsion part based on sequentially inputted electric energy. The aircraft body separation control unit 615 corresponds to the concept of the stage separating apparatus 1 (161) and the stage separating apparatus 2 (162) shown in Fig.

In this embodiment, at least two detonators may be attached to the connection between the body and the propulsion unit. At this time, the air body separation control unit 615 can sequentially detonate the detonator using electrical energy whenever electric energy is input, thereby finally separating the body and the propelling unit. In this embodiment, the detonators may be attached to the connection portion of the body portion and the propulsion portion in a columnar form.

The air vehicle separation control apparatus 600 may further include a first determination unit 630, a second determination unit 635, and a signal reception unit 640.

In the present embodiment, in principle, the processor section transmits the self-length signal to the new tube circuit section. However, if the processor part malfunctions, such a self-explanatory signal may not be normally transmitted to the new tube circuit part. The first judging unit 630, the second judging unit 635 and the signal receiving unit 640 are provided for solving the above problems. Even if the processor unit does not operate normally, the self-length signal is normally transmitted .

The first determination unit 630 determines whether electric energy is generated and output at the current time.

The second determination unit 635 determines whether the elapsed time from the time when the current state of the air vehicle is determined to be abnormal to the current time is greater than or equal to the reference time, .

If it is determined that the elapsed time is equal to or longer than the reference time, the signal receiving unit 640 receives a signal requesting sequential generation of electrical energy from the outside. The signal receiving unit 640 corresponds to the data remote receiving apparatus 150 of FIG.

If the air vehicle separation control apparatus 600 further includes the first determination unit 630, the second determination unit 635 and the signal reception unit 640, the electric energy generation unit 610 may sequentially generate electric energy from the outside Upon receipt of the request signal, electric energy for separating the body part from the propulsion part can be sequentially generated and output.

The air vehicle separation control apparatus 600 may further include a first power supply unit 645 and a second power supply unit 650.

The first power supply unit 645 functions to supply the first power source necessary for the operation of the flight state determination unit 605. The first power supply unit 645 corresponds to the power supply 130 of FIG.

The second power supply unit 650 performs a function of supplying a second power required for the electric energy generation unit 610 to operate. The second power supply unit 650 corresponds to the battery 120 of FIG.

The air vehicle separation control apparatus 600 further includes a supply connection line for connecting the first power supply unit 645 and the second power supply unit 650 so that the second power supply can be used as the first power supply, A Schottky diode may be formed on one side of the first power source to prevent the first power source from being supplied to the second power source.

The second power supply 650 may be operable to supply the second power source to the first power source using the supply connection line before the airplane starts flying.

The second power supply unit 650 may supply a second power supply having a higher voltage than the first power supply.

Next, an operation method of the air bag separation control apparatus will be described.

FIG. 7 is a flowchart illustrating an air vehicle separation control method using a time delay according to a preferred embodiment of the present invention. The following description refers to Fig. 6 and Fig.

First, the flight status determination unit 605 determines whether the current status of the flight is normal (S710).

If it is determined that the current state of the airplane is abnormal, the electric energy generating unit 610 sequentially generates and outputs electric energy for separating the body of the airplane and the propulsion unit of the airplane based on a predetermined time difference (S720).

Then, the air bag separation control unit 615 separates the body and the propelling unit based on the sequentially inputted electrical energy (S730).

Thereafter, the display control device provided outside the air bag separation control device obtains the captured image of the process of separating the body part and the propelling part, and outputs the image using the terminal provided outside the air vehicle (step S740).

In the present embodiment, it is determined whether or not the first determination unit 630 generates and outputs electric energy at the current time. If it is determined that no electric energy is generated and output at the present time, the second determination unit 635 determines Determining whether the elapsed time from the time when the current state of the current state is abnormal to the present time is equal to or longer than a reference time, and if the elapsed time is greater than the reference time, A step of receiving a signal requesting generation, and so on.

The three steps mentioned above can be performed between the step of sequentially generating and outputting in this embodiment and the step of separating. When the above three steps are performed sequentially, a step of successively generating and outputting electric energy for separating the body part and the propulsion part of the air vehicle (when a signal requesting sequential generation of electric energy is received) can be performed .

Meanwhile, before the step of determining, the first power supply unit 645 may perform the step of supplying the first power supply necessary for performing the step of determining, and before the step of sequentially generating and outputting, And supplying the second power source necessary for performing the step of sequentially generating and outputting by the supplying unit 650. [

The step of supplying the first power source may include supplying the first power source to the second power source using a Schottky diode formed on one side of the supply connection line connecting the configuration for supplying the first power source and the configuration for supplying the second power source .

The step of supplying the second power may use the second power as the first power by using the supply connection line connecting the configuration for supplying the first power and the configuration for supplying the second power before the flight starts to fly Can supply.

The step of supplying the second power source may supply a power source having a higher voltage than the first power source to the second power source.

It is to be understood that the present invention is not limited to these embodiments, and all elements constituting the embodiment of the present invention described above are described as being combined or operated in one operation. That is, within the scope of the present invention, all of the components may be selectively coupled to one or more of them. In addition, although all of the components may be implemented as one independent hardware, some or all of the components may be selectively combined to perform a part or all of the functions in one or a plurality of hardware. As shown in FIG. In addition, such a computer program may be stored in a computer readable medium such as a USB memory, a CD disk, a flash memory, etc., and read and executed by a computer to implement an embodiment of the present invention. As the recording medium of the computer program, a magnetic recording medium, an optical recording medium, a carrier wave medium, and the like can be included.

Furthermore, all terms including technical or scientific terms have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined in the Detailed Description. Commonly used terms, such as predefined terms, should be interpreted to be consistent with the contextual meanings of the related art, and are not to be construed as ideal or overly formal, unless expressly defined to the contrary.

It will be apparent to those skilled in the art that various modifications, substitutions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims. will be. Therefore, the embodiments disclosed in the present invention and the accompanying drawings are intended to illustrate and not to limit the technical spirit of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments and the accompanying drawings . The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.

Claims (9)

Determining whether the current state of the air vehicle is normal;
Sequentially generating and outputting electric energy for separating the body part of the air vehicle and the propulsion part of the air vehicle based on a predetermined time difference when it is determined that the current state of the air vehicle is abnormal;
Separating the body and the propulsion unit based on the electrical energy sequentially input; And
A step of acquiring an image of a process of separating the body part and the propulsion part and outputting the image using a terminal provided outside the air vehicle
/ RTI >
Between the step of sequentially generating and outputting and the step of separating,
Determining whether or not the electric energy is generated and outputted at a current time point;
Determining whether the elapsed time from the time when the current state of the airplane is determined to be abnormal to the current time is equal to or longer than a reference time when it is determined that the electric energy is not generated and output at the present time; And
Receiving a signal requesting the sequential generation of the electric energy from the outside if it is determined that the elapsed time is equal to or longer than the reference time
The method of claim 1, The method according to claim 1,
The determining step may include determining whether the current state of the airplane is normal by comparing steering control information input to the airplane and motion information of the airplane, or determining whether the airplane travels along a predetermined flight path, And determining whether the current state of the air vehicle is normal or not. The method according to claim 1,
Wherein the sequentially generating and outputting step sequentially generates and outputs the electric energy using at least two time delay circuit parts and a constant current circuit part connected to each time delay circuit part. The method according to claim 1,
At least two detonators are attached to the connecting portion of the body portion and the pushing portion,
Wherein the separating step sequentially detonates the detonator using the electric energy each time the electric energy is input, thereby finally separating the body and the propulsion unit. delete The method according to claim 1,
Supplying a first power source necessary for performing the determining step; And
A step of supplying a second power source necessary for performing the step of sequentially generating and outputting
Further comprising the step of determining whether the time delay is greater than a predetermined time. The method according to claim 6,
Wherein the step of supplying the second power supplies the second power source to the second power source using a supply connection line that connects the configuration for supplying the first power source and the configuration for supplying the second power source before the flight starts, 1 power source. 2. The method of claim 1, The method according to claim 6,
Wherein the supplying of the first power is performed by using a Schottky diode formed on one side of a supply connection line connecting a configuration for supplying the first power and a configuration for supplying the second power, And the power supply is prevented from being supplied to the power source. The method according to claim 6,
Wherein the step of supplying the second power supplies a power source having a higher voltage than the first power source to the second power source.

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