KR101885730B1 - General purpose electronic safety and arming device with flight environment and target collision detection function - Google Patents

Abstract

Embodiments of the present invention relate to an electronic safety and loading device capable of providing a loading signal by using a plurality of independent flight environment detectors in equipment. Since the possibility of early loading due to malfunctioning of exterior equipment is completely excluded such that the present invention has high safeness and operation reliability. By using a subsidiary target detecting means within the equipment, a detonating pipe can be detonated such that the electronic safety and loading device are compatible and expandable by being applicable to different flight environments of various kinds of weapon systems. The electronic safety and loading device comprises: a flight environment detecting portion; a safety loading portion; and a boost voltage detonating portion.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a general electronic safety loading device having a flight environment and a target collision detection function,

Embodiments relate to a general-purpose electronic safety loading apparatus having a function of detecting a flying environment and a target collision in the equipment, and a control method thereof.

A mechanical safety loading device is a safety loading device using an explosive tube made of a primary explosive, which is sensitive to the surrounding environment. It keeps the explosion series in an out-of-line state and leaves the safety zone. It works by mechanically moving the tube to ignite the explosion series in an in-line state. In recent years, however, the safety of the bullet has been improved by using an explosion tube composed of an insensitive second explosive which operates only when a high voltage is applied, and the explosion series is arranged in an aligned state from the beginning without a physical cutoff device in the explosion series, Electronic safety loading devices are now widely used.

Electronic safety loading devices must be designed with safety as a top priority because there is no mechanical energy cutoff device and should be designed so that the safety of the burnt is not threatened by other external factors. Therefore, the loading signal of the electronic safety loading device must be loaded using at least two flight environment signals.

The conventional electronic safety loading device receives a loading signal generated by the flying environment detection from an external device and performs loading, and generates an aerial signal by receiving an aerial command from a target detection device and a collision detector located outside the safety loading device It acted in a way to detonate the detonator. Therefore, there is a risk that the existing electronic safety loading device may be switched to a loading state that is capable of being exploded due to malfunction of an external device or an interface transmitting a loading signal, and when an external device generating an awakening signal causes a malfunction There is a possibility that the shot will not explode even if it has reached its goal.

[Prior Art Document Number]

Prior Art Document 1: Korean Patent No. 10-0652905

Prior Art Document 2: Korean Patent No. 10-1343421

Embodiments provide an electronic safety loading device having a function of providing a loading signal by using a plurality of independent flying environment sensors in the inside of the equipment. It completely eliminates the possibility of premature loading due to malfunction of external equipment and has high safety and operational reliability, The present invention provides a universal electronic safety loading device and its control method that are compatible and scalable so that they can be applied even under different flight environments of various weapon systems by enabling the weapon to be detonated through auxiliary target detection means in the equipment.

According to an embodiment, an electronic safety loading device includes a plurality of sensors for sensing a flying environment in an electronic safety loading device, and determines a flying environment after the fire is launched based on a sensing signal output from the plurality of sensors, A flight environment sensing unit for generating a charging signal; A safety charger for outputting first and second charging control signals based on a first charging signal input from the flying environment sensing unit and a second charging signal inputted from the outside; And generating a second voltage boosted by a first power supply voltage applied in accordance with the first and second charging control signals and storing the generated second voltage in an awakening capacitor and storing the generated voltage in the awakening capacitor according to the awakening command signal input from the safety charger, And a voltage rising unit for transmitting the energy to the explosion pipe to ignite the explosion pipe.

The safety loading unit may further include a target collision detector, and may generate the detonation command signal based on at least one of an externally input detonation command and a collision detection signal output from the target collision detector.

The safety loading unit may determine whether there is a normal operation based on the input timing of the first and second loading control signals, and output the checking result signal to the outside according to the determination result.

Wherein the voltage rising portion includes first and second charge control switches connected in series and the first and second charge control switches are turned on according to the application of the first and second charge control signals have.

The voltage rising unit may further include a discharge resistor for discharging energy stored in the ignition capacitor when at least one of the first and second charge control switches is not turned on or is determined to be in an abnormal state.

The electronic safety loading apparatus may further include a mode selecting unit for determining whether to apply at least one of the sensing signal output from the plurality of sensors and the collision sensing signal to the first loading signal and the detonating command signal .

In the electronic safety charging apparatus, a second power supply voltage different from the first power supply voltage may be applied to the flying environment sensing unit and the safety protection unit.

According to another aspect of the present invention, there is provided a control method for an electronic safety loading apparatus, including a plurality of sensors for detecting a flying environment in an electronic safety loading apparatus, Determining a flying environment of the first loading signal to generate a first loading signal; Outputting first and second loading control signals on the basis of the generated first loading signal and a second loading signal input from the outside, Generating a second voltage that boosts a first power supply voltage applied according to the first and second charging control signals and storing the generated second voltage in an ignition capacitor; And transmitting the energy stored in the awakening capacitor to the awakening tube in accordance with the awake command signal input from the safety energizing section to detonate the awakening tube.

The control method of the electronic safety loading apparatus may further include generating the detonating command signal based on at least one of an externally input detonating command and a collision detecting signal output from a target collision detector included in the electronic safety loading apparatus can do.

The method of controlling the electronic safety loading apparatus may include determining whether there is a normal operation based on input timings of the first and second loading control signals; And outputting the check result signal to the outside in accordance with the determination result.

And a recording medium on which a program for causing the computer to execute the control method according to another embodiment is recorded.

The electronic safety loading apparatus according to the embodiment includes a plurality of flight environment detectors and a collision detector built in the apparatus to generate and use a loading signal and an awakening command signal necessary for the electronic safety loading apparatus, Even if the malfunction is input, the operation reliability and safety of the equipment can be maintained.

In addition, it can be applied universally to different weapon systems operating under various flight environments by setting the self-flying environment detector and collision detector signal judgment criteria which are used as loading signal and detonation signal by program setting or external communication at the time of program injection .

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a schematic diagram of an electronic safety loading device according to one embodiment.
2 is an exemplary view for explaining the self-diagnosis performance of the electronic safety deposit apparatus according to another embodiment.
3 is a flow chart illustrating an operation sequence of the safety deposit unit and the flying environment sensing unit of the electronic safety deposit apparatus according to another embodiment.
4 is a flow chart for explaining the operation sequence of the safety input section and the voltage rising section of the electronic safety loading apparatus according to another embodiment.

Although the terms used in the present embodiments have been selected in consideration of the functions in the present embodiments and are capable of being widely used in general terms, they may vary depending on the intention or circumstance of a technician working in the art, the emergence of new technology . Also, in certain cases, there are arbitrarily selected terms, and in this case, the meaning will be described in detail in the description part of the embodiment. Therefore, the terms used in the embodiments should be defined based on the meaning of the terms, not on the names of simple terms, and on the contents of the embodiments throughout.

In the description of the embodiments, when a part is connected to another part, it includes not only a direct connection but also a case where the part is electrically connected with another part in between. In addition, when a part includes an element, it does not exclude other elements unless specifically stated otherwise, but may include other elements. Further, the term " part " described in the embodiments means a unit for processing at least one function or operation, which may be implemented in hardware or software, or a combination of hardware and software.

The terms " comprising " or " comprising ", etc. used in the embodiments should not be construed as necessarily including the various elements described in the specification or the various steps, Steps may not be included, or may be interpreted to include additional components or steps.

The following description of the embodiments should not be construed as limiting the scope of the present invention and should be construed as being within the scope of the embodiments of the present invention. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Exemplary embodiments will now be described in detail with reference to the accompanying drawings.

Embodiments relate to a general-purpose electronic safety loading apparatus having a flight environment and a target collision detection function and a control method thereof. The electronic safety loading apparatus can be applied to various shot-type weapon systems, and is applicable to missiles, missiles, launch vehicles, rockets, It can be applied to weapon systems such as guns and shells.

BRIEF DESCRIPTION OF THE DRAWINGS FIG.

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a schematic diagram of an electronic safety loading device according to one embodiment.

Referring to FIG. 1, the electronic safety loading apparatus 10 includes a flying environment sensing unit 400 for sensing an acceleration generated during a flight and generating a loading signal, a high- A safety charger 200 for controlling the energy flow of the circuit, a voltage generator for generating a high voltage capable of operating the igniter 500 by receiving a voltage from the outside, A power supply unit 140, and a power supply unit 140. The power supply unit 140, 150 may be a power supply unit,

The safety grounding unit 200 and the flying environment sensing unit 400 can quickly and accurately process an input signal using a signal processor including a microprocessor or a logic device.

The safety charger 200 removes noise from the charging signals 101, 402, and 103 received from the outside or the flying environment sensing unit 400 using a microprocessor or a logic device mounted therein, And operates the charging switches 302, 304, and 306 of the voltage rising unit 300. Here, three loading signals are shown as an example, but the present invention is not limited to this. The loading signals 101 and 402 may be composed of only two loading signals, and the loading switches may be composed of only two loading switches 302 and 306. [

As shown in FIG. 1, the voltage rising unit is configured in a series structure so that even if one charging switch is not operated, the flow is cut off. In addition to the charging control function, the safety loading part checks the state of the peripheral device in real time as shown in FIG. 2, and outputs the abnormality occurrence time and abnormality cause to the outside through the check result signal line 108 when an abnormality occurs.

The flight environment sensing unit 400 includes a plurality of flight environment sensors 410. Each sensor senses an independent flight environment and generates a loading signal 402. [ When the magnitude of the signal of the detector exceeds the reference value, the loading signal 402 is generated, and the safety device (not shown) 200). Here, the flight environment detector 410 may be a plurality of sensors, and may be a sensor that detects different flight environments, for example, an acceleration sensor, a gyro sensor, an altitude sensor, and the like.

In order to load the electronic safety loading apparatus 10, the loading signals 101, 402, and 103 must be input according to a predetermined procedure. When the loading order is unintentionally inputted, it is judged to be in an abnormal state, the loading is released, and the abnormality occurrence time and the cause of the failure are outputted to the outside through the signal line of the check result (108).

The electronic safety loading device 10 enhances safety by utilizing one or more loading signals 402 of the plurality of loading signals by utilizing the signals of the self-generated flying environment sensor 410 in the safety loading device. The collision detector 210 located within the safety loading device assists the external detonation command 104 to enhance operational reliability.

The electronic safety loading apparatus 10 according to the embodiment may be applied to various weapon systems in general. The user may set a self-flight environment detector 410 signal and a collision detector 210 signal Mode selection 106 as to how to use as a loading signal and an aerial signal in a certain manner, so that it is universally applicable to different flight environments and operating conditions.

The power supply units 140 and 150 serve to stably supply the power supplies 142 and 152 required by the respective components, and may be configured as two or more types as shown in FIG. The power source 142 supplied to the voltage rising unit 300 can be operated in a manner using a power source activated at the time of firing or right before firing so as to prevent early charging during storage and transportation of the bullet have.

3 is a flow chart illustrating an operation sequence of the safety deposit unit and the flying environment sensing unit of the electronic safety deposit apparatus according to another embodiment.

When a power is applied to the safety charger 200, a signal processor composed of a microprocessor or a logic device inside the safety charger receives an external detonating command 104, a collision detector 210, loading signals 101, 402 and 103, The control switches 302, 304, and 306, and the like in real time. After the inspection is completed, the inspection result 108 is output to the outside so that the user can check the inspection result. If an abnormality occurs in the inspection site, the user can identify the time and cause as shown in FIG.

When the charge 1 signal 101, the charge 2 signal 402 and the charge 3 signal 103 using the events occurring from the start to the end of the charge are input, Control switches 302, 304, and 306 are operated. When all of the charging control switches are turned on, the input power of the high voltage converter 310 is supplied and the high voltage is charged to the ignition capacitor 330.

At least one loading signal 402 among charging signals 101, 402 and 103 involved in the operation of the safety charger 200 is input from the flying environment detecting unit 400. [

When the input of the loading signals 101, 402 and 103 is not intended or an abnormality occurs in the inspection region, the operation of the charging control switches 302, 304, and 306 is stopped to prevent the ignition capacitor 330 from being charged Block the flow.

The flight environment sensing unit 400 receives a mode selection command including the type of the object or the flight environment information from the safety load unit 200 and sets the mode selection command as a judgment criterion of the signal of the flight environment sensor 410. Upon receipt of the flight environment detection start command 202 from the safety device, the signal of the flight environment detector 410 is measured. When a signal of a certain level is detected, the load signal 402 is generated and transmitted to the safety device. In order to recognize the flying environment in the flight environment sensing unit, the signal of the sensor that detects two or more independent flight environments must be judged as an effective signal.

The input power of the electronic safety loading apparatus 10 is divided into two or more power sources 142 and 152, and the input power is transmitted to each component through a power source unit. Accordingly, the power source 142, which is transmitted to the voltage rising unit 300, can be operated in a manner using a power source activated after or immediately before the discharge of the bullet to prevent early charging in the transportation and storage of the bullet.

4 is a flow chart for explaining the operation sequence of the safety input section and the voltage rising section of the electronic safety loading apparatus according to another embodiment.

When the charging signals 101, 402 and 103 are normally received, both of the charging control switches 302, 304 and 306 of the voltage rising unit 300 are operated to charge the ignition capacitor 330. When the collision sensor 210 receives the external detonating command 104 from the external target sensing device or the crush switch or when the collision sensing signal 210 is generated from the collision sensor 210, And outputs the detonation signal 204 to the detonation circuit 320 to operate the detonation switch 308 so that the energy of the detonation capacitor is transmitted to the detonator 500 to be detonated.

The electronic safety loading apparatus according to the embodiment includes a plurality of flight environment detectors and a collision detector built in the apparatus to generate and use a loading signal and an awakening command signal necessary for the electronic safety loading apparatus, It is possible to maintain the operational reliability and safety of the equipment even if it is inputted as a malfunction.

In addition, it can be applied universally to different weapon systems operated in various flight environments by setting self-flight environment detector and collision detector signal criterion used as loading signal and detonation signal through program setting or external communication at program injection There are advantages.

One embodiment may also be implemented in the form of a recording medium including instructions executable by a computer, such as program modules, being executed by a computer. Computer readable media can be any available media that can be accessed by a computer and includes both volatile and nonvolatile media, removable and non-removable media. In addition, the computer-readable medium may include both computer storage media and communication media. Computer storage media includes both volatile and nonvolatile, removable and non-removable media implemented in any method or technology for storage of information such as computer readable instructions, data structures, program modules or other data. Communication media typically includes any information delivery media, including computer readable instructions, data structures, program modules, or other data in a modulated data signal such as a carrier wave, or other transport mechanism.

It will be understood by those of ordinary skill in the art that the foregoing description is for the purpose of illustration and that those skilled in the art can easily modify the invention to other specific forms without departing from the spirit or essential characteristics of the present invention. It is therefore to be understood that the above-described embodiments are illustrative in all aspects and not restrictive. For example, each component described as a single entity may be distributed and implemented, and components described as being distributed may also be implemented in a combined form.

The scope of the present invention is defined by the appended claims rather than the detailed description and all changes or modifications derived from the meaning and scope of the claims and their equivalents are to be construed as being included within the scope of the present invention do.

Claims (11)

A flight environment sensing unit that includes a plurality of sensors for sensing a flying environment in the electronic safety loading device and determines a flight environment after the fire based on the sensing signals output from the plurality of sensors to generate a first loading signal;
A safety charger for outputting first and second charging control signals based on a first charging signal input from the flying environment sensing unit and a second charging signal inputted from the outside; And
And a second voltage that is increased according to the first and second charging control signals, and stores the generated voltage in an awakening capacitor. The energy stored in the awakening capacitor according to the awakening command signal input from the safety charger, And a voltage rising unit for transmitting the voltage to the ignition tube to ignite the ignition tube,
The rising-
And first and second charge control switches connected in series,
Wherein the first and second charging control switches comprise:
And the second charging control signal is turned on according to the application of the first and second charging control signals. The method according to claim 1,
The safety loading unit includes:
Further comprising a target collision detector,
Wherein the ignition command signal is generated based on at least one of an ignition command input from the outside and a collision detection signal output from the target collision detector. A flight environment sensing unit that includes a plurality of sensors for sensing a flying environment in the electronic safety loading device and determines a flight environment after the fire based on the sensing signals output from the plurality of sensors to generate a first loading signal;
A safety charger for outputting first and second charging control signals based on a first charging signal input from the flying environment sensing unit and a second charging signal inputted from the outside; And
And a second voltage that is increased according to the first and second charging control signals, and stores the generated voltage in an awakening capacitor. The energy stored in the awakening capacitor according to the awakening command signal input from the safety charger, And a voltage rising unit for transmitting the voltage to the ignition tube to ignite the ignition tube,
Determines whether the normal operation is performed based on the input timing of the first and second loading control signals, and outputs an inspection result signal according to the determined result to the outside. delete The method according to claim 1,
The rising-
Further comprising a discharge resistor for discharging energy stored in the ignition capacitor when at least one of the first and second charge control switches is not turned on or is determined to be in an abnormal state. 3. The method of claim 2,
Further comprising a mode selection unit for determining whether to apply at least one of the sensing signal output from the plurality of sensors and the collision sensing signal to the first loading signal and the detonating command signal, . The method according to claim 1,
And a second power source voltage different from the first power source voltage is applied to the flying environment sensing unit and the safety charger unit. The flying environment detecting unit includes a plurality of detectors for detecting a flying environment in the electronic safety loading device. The flying environment after the fire is determined based on the sensing signals output from the plurality of sensors to generate a first loading signal step;
Outputting first and second loading control signals on the basis of the generated first loading signal and a second loading signal input from the outside,
Generating a second voltage that boosts a first power supply voltage applied according to the first and second charging control signals and storing the generated second voltage in an ignition capacitor; And
And transmitting the energy stored in the awakening capacitor to the awakening pipe according to the awakening command signal input from the safety switch, thereby detonating the awakening pipe,
Determining whether there is a normal operation based on input timings of the first and second loading control signals; And
And outputting the check result signal to the outside according to the determination result. 9. The method of claim 8,
Further comprising the step of generating the detonation command signal based on at least one of an externally input detonation command and a collision detection signal output from a target collision detector included in the electronic safety loading device / RTI > delete A recording medium on which a program for causing a computer to execute the control method according to claim 8 or 9 is recorded.

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