KR101199883B1 - Apparatus of Safety for Ignition in Rocket using MEMS - Google Patents

Abstract

The present invention relates to a rocket ignition safety device that allows the rocket to ignite safely after reaching a certain distance from the launch tube,
A housing 100 for receiving and supporting each component; A delay ignition circuit assembly 110 assembled along a slot machined on an inner surface of the housing 100 and outputting an ignition signal under a specific condition; An input connector 125 installed on the upper cover 120 of the housing 100 to supply power to the delay ignition circuit assembly; A MEMS assembly (150) assembled to the lower cover (130) of the housing (100) and vertically coupled with the delay ignition circuit assembly (110) to provide a trigger signal to the delay ignition circuit assembly (110); An output connector connected to the housing 100 by an output line 145 and coupled to the ignition unit of the propulsion engine and transmitting the ignition signal of the delayed ignition circuit assembly 110 transmitted through the output line 145 to the ignition circuit. 140; characterized in that it comprises a.
Therefore, the propulsion engine is ignited only when a certain amount of inertia force or injection acceleration is applied to prevent the safety accident during launch, and in case of abnormal situation, the trigger signal is not applied, which greatly increases the safety during transportation, handling and storage. .

Description

Apparatus of Safety for Ignition in Rocket using MEMS}

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rocket ignition safety device that allows a rocket to ignite safely after reaching a certain distance from the launcher. In particular, the present invention relates to MEMS (Micro Eletro-Mechanical) in order to activate a delay circuit by sensing an inertial force generated when a rocket is launched. The present invention relates to a rocket ignition safety device using MEMS that can be applied to a small rocket by minimizing installation space by using a system.

In general, a rocket launch device includes an injection device that allows the rocket to leave the launcher unignited and a rocket strayed from the launcher to ensure the safety of the shooter and the rocket itself when firing the rocket. An ignition safety device is provided to allow the propulsion engine to ignite after reaching a certain distance. The ignition safety device is installed inside the rocket, and determines the ignition time of the rocket using a delay ignition circuit. The delayed ignition circuit performs a function of causing the propulsion engine to be ignited when the rocket leaving the injection tube by the injection apparatus reaches a certain distance from the injection apparatus.

However, when the delay ignition circuit malfunctions and the rocket propulsion engine is ignited in the injection device, it may have a fatal effect on the shooter operating the injection device. In order to prevent such a malfunction, a device for activating the delayed ignition circuit by detecting the inertial force emitted by the injection apparatus is required, which is called a rocket ignition safety device.

The conventional rocket ignition safety device, as shown in Figure 1, the front end of the connector connected between the connection switch 11 for operating the electrical delay means and the rocket and the launch tube when the rocket starts to drive in the launch tube It is composed of an induction control unit for detecting a trigger to generate a trigger signal and an oscillator unit for receiving a trigger signal from the induction control unit to transmit an ignition signal to the propulsion engine of the rocket.

The driving means for driving the connection switch 11 of the electrical delay means is largely composed of a rotor 21 and a spring spring 29. Mechanical delay means (gear and pallet assembly) for delaying the driving of the drive means, the first gear and the rotation axis coincide with a larger diameter than the first gear that rotates in engagement with the gear formed on one side of the outer peripheral portion of the rotor 21 A second gear 32 integrally formed with each other; A fourth gear 34 having a diameter larger than that of the third gear that rotates in engagement with the second gear 32 and having an outer circumferential portion formed of a cog wheel and integrally formed so that the third gear and the rotation axis thereof coincide with each other; It is comprised by the pallet 35 which meshes with the tooth of the gear of the 4th gear 34, and controls rotation.

In addition, the first restraining means for restraining the driving of the driving means is mounted on the side of the main body of the ignition safety device 1 so as to be detachable, and is inserted into a groove formed on one side of the outer circumference of the rotor 21 and is rotated. A safety pin 41 for restraining rotation of the electrons 21; When the safety pin 41 is separated from the main body 1, the safety pin 41 is composed of a spring 42 for applying a driving force. Further, the second restraining means for restraining the driving of the driving means is rotated by centrifugal force during rotation of the main body 1 with the rotation shaft 54 symmetrically provided on both side surfaces of the driving means and formed on one side thereof as an axis. It consists of the release | release latch 51, the release pin 52, and the release spring 53 which were installed so that possible. In addition, a first catching jaw that engages with the two primary restraint pins formed on the upper side of the rotor 21 to restrain the rotation of the rotor 21 is formed at an symmetrically opposite end of the rotating shaft 54.

However, the conventional rocket ignition safety device configured as described above can be used only when the rotational inertia force is generated during the injection launch of the rocket, it is not possible to use when the inertial force is generated only in the direction directed to launch the rocket does not rotate. There is this.

In addition, the conventional rocket ignition safety device has a problem that can not be used even when the space for mounting the ignition safety device, such as a small rocket is reduced. Accordingly, it can be applied to the case where inertial force is generated only in the direction of the firing axis while detecting the inertial force caused by the rotation of the rocket as in the conventional rocket ignition safety device, and a situation that requires a miniaturized alternative is urgently needed.

Patent Publication No. 2003-0003873

The present invention has been made to solve the above-mentioned conventional problems, it is mounted by activating the delayed ignition circuit by using the MEMS operated by the rotational inertia force or the rotational inertia force according to the injection acceleration acting when the rocket is launched. The aim is to provide a rocket ignition safety device using MEMS that can significantly reduce space.

In addition, an object of the present invention is to provide a rocket ignition safety device using a MEMS that can prevent the safety accident due to malfunction of the delay ignition circuit by supplying power to the delay ignition circuit only when the rocket is normally launched.

In addition, the present invention uses a MEMS that can prevent the safety accident caused by accidental activation of the delayed ignition circuit during the transport or long distance transport and storage of the bullet by rocket must be launched through the launch tube to activate the delayed ignition circuit. The purpose is to provide a rocket ignition safety device.

The present invention for achieving the above object, and a housing for receiving and supporting each component; A delay ignition circuit assembly assembled along a slot machined to an inner surface of the housing and outputting an ignition signal under a specific condition; An input connector installed at an upper cover of the housing to supply power to the delayed ignition circuit assembly; A MEMS assembly assembled to a lower cover of the housing and vertically coupled to the delay ignition circuit assembly to provide a trigger signal to the delay ignition circuit assembly; And an output connector connected to the housing by an output line and coupled to the ignition unit of the propulsion engine and transmitting the ignition signal of the delayed ignition circuit assembly transmitted through the output line to the ignition circuit.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, the MEMS assembly is a MEMS structure that is triggered by the inertial force or rotational inertia force in the direction of the launch axis due to the injection acceleration of the rocket to generate a trigger signal and the lower cover The MEMS structure and the delayed ignition circuit assembly are assembled to the upper surface, characterized in that it comprises a circular PCB for transmitting the trigger signal generated by the MEMS structure to the delayed ignition circuit assembly.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, the MEMS structure, a pair of contact terminals formed spaced apart from each other and provided with a receiving portion provided on one side, and the protrusions engaged with the receiving portion of the contact terminal And a proof mass for electrically conducting the contact terminal through coupling with the contact terminal, and supported by support blocks disposed at both front ends of the proof mass so that the proof mass is spaced apart from the contact terminal. It characterized in that it comprises a plurality of plate-like elastic member to elastically support to maintain, and a restraining pin assembly disposed on both sides of the rear end of the proof mass to restrain the movement of the proof mass.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, the restraint pin assembly, a pair of restraints are inserted into the insertion groove formed on both sides at the rear end of the proof mass to restrain the proof mass. A pin, a plurality of negative electrode pieces respectively attached to both sides of the restraint pin orthogonally to the restraint pins, an anode terminal disposed on both sides of the restraint pins, and having a plurality of positive electrode pieces attached to one surface of the restraint pin direction; Cathode terminals respectively disposed on both ends of the positive electrode terminal and electrically connected to the constraining pins, and are installed to elastically support the constraining pins in a proof mass direction at both ends of the positive electrode terminal, thereby restricting the plate shape to connect the negative electrode terminal and the constraining pins. It characterized in that it comprises a pin spring.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, the delayed ignition circuit assembly, the main PCB with a delayed ignition circuit is configured on the front, and is attached to the front of the main PCB to perform the electromagnetic shielding function (EMI Shiled) An inductor, a variable resistor attached to the front surface of the main PCB to finely adjust the ignition delay time, a power transistor attached to the front surface of the main PCB to control the ignition current, and attached to a rear surface of the main PCB. Characterized in that consisting of HIC (Hybrid Integrated Circuit).

In addition, according to the rocket ignition safety device using the MEMS of the present invention, the end of the input connector of the upper cover is soldered and electrically integrated on the top of the main PCB of the delayed ignition circuit assembly.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, the main PCB, a first optical coupler coupled to the launch tube and activated by a trigger signal of the MEMS structure provided in the MEMS assembly, the first light When a trigger signal is input through the coupler, a monostable multivibrator IC for determining the delay time and width of the ignition pulse using a plurality of circuit elements is connected to an output terminal of the monostable multivibrator IC. It characterized in that it comprises a power transistor for generating an ignition signal in accordance with the ignition pulse transmitted through the two optical coupler and transmits to the ignition of the propulsion engine.

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In addition, according to the rocket ignition safety device using the MEMS of the present invention, the delayed ignition circuit assembly, the MEMS assembly and the upper cover is integrated by soldering is inserted into the housing, inserted through the screw hole provided in the lower cover A screw is fastened to the stud through the circular PCB of the MEMS assembly and fixed to the housing.

In the rocket ignition safety device using the MEMS of the present invention, the propulsion engine is ignited only when a certain amount of inertia force or injection acceleration is applied to prevent the safety accident during the launch, as well as the trigger signal is not applied in an abnormal situation. However, there is an effect that the safety during handling and storage is greatly expanded.

In addition, the rocket is prevented from being ignited in the launch tube during the launch of the rocket to prevent damage caused by the aftermath of the propulsion engine, as well as to give the rocket operator a psychological stability and has an additional effect of smoothly performing the assigned task. .

In addition, since MEMS is used as a device for activating the delay ignition circuit, the size of the device is small, so it can be applied to a small rocket with a small mounting space. There is an effect that can minimize the performance changes due to errors or assembly tolerances.

Specifically, according to the rocket ignition safety device using the MEMS of the present invention, the MEMS is operated only by the rotational inertia force or the injection acceleration acting on the rocket when the rocket is launched, so that the delay ignition assembly is driven, so that the rocket does not leave the launch tube. If sufficient inertia force or injection acceleration does not occur, the delayed ignition assembly is not driven, thereby preventing a safety accident during launch.

Further, according to the rocket ignition safety device using the MEMS of the present invention, the propulsion engine is ignited after the rocket is sufficiently spaced from the launch tube, which can safely protect the launcher and the rocket operator from the after-storm generated by the operation of the propulsion engine. It works.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, since the MEMS is operated not only by the rotational inertia force acting on the rocket, but also by the injection acceleration during launch, there is an effect that can be applied to a non-rotating rocket.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, the MEMS operates only when an inertial force exceeding the elastic force of the elastic member constituting the MEMS is activated, otherwise the MEMS does not operate to drive the delayed ignition circuit assembly. Since the propulsion engine is prevented from operating by blocking the propulsion engine, the propulsion engine is prevented from being ignited during the launch.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, unless the power supply to the rocket, the purp mass of the MEMS maintains the restrained state, even if a momentary drop occurs during transportation, storage and maintenance of the rocket delayed ignition Since the circuit assembly is not driven, the propulsion engine of the rocket has an effect of being safely preserved without absolutely accidental ignition.

In addition, according to the rocket ignition safety device using the MEMS of the present invention, since the delay ignition circuit configured on the main PCB is short-connected to the launch tube, the rocket does not fire even when the rocket is powered down while handling and the MEMS is operated. There is no trigger signal, which prevents the rocket from accidental ignition.

1 is a configuration diagram showing a conventional rocket ignition safety device.
Figure 2 is an exploded perspective view showing a rocket ignition safety device according to the present invention.
3 is an external view and an internal view of the rocket ignition safety device of the present invention.
Figure 4 is a perspective view showing the state of the non-operation of the MEMS that is the main configuration of the present invention.
Figure 5 is a perspective view showing the appearance of the operation of the main component MEMS of the present invention.
Figure 6 is a delay ignition circuit diagram of the main PCB of the main component of the present invention.

Hereinafter, with reference to the accompanying drawings illustrating a rocket ignition safety device using the MEMS of the present invention.

Rocket ignition safety device using the MEMS of the present invention, as shown in Figure 2 and 3, the housing 100 for receiving and supporting each component; A delay ignition circuit assembly (110) assembled along a slot machined on an inner surface of the housing (100) and outputting an ignition signal under a specific condition; An input connector (125) installed on the upper cover (120) of the housing (100) to supply power to the delayed ignition circuit assembly (110); A MEMS assembly (150) assembled to the lower cover (130) of the housing (100) and vertically coupled with the delay ignition circuit assembly (110) to provide a trigger signal to the delay ignition circuit assembly (110); Output connected to the housing 100, the output line 145, coupled to the ignition of the propulsion engine, and outputs the ignition signal of the delayed ignition circuit assembly 110 transmitted through the output line 145 to the ignition circuit It comprises a connector (140).

The delayed ignition circuit assembly 110, the MEMS assembly 150, and the upper cover 120 are integrated by soldering and inserted into the housing 100. In addition, the MEMS assembly 150 is assembled to the MEMS structure 151 and the lower cover 130 that are actuated by an inertial force or a rotational inertia force in the direction of the firing axis due to the injection acceleration of the rocket, and the lower cover 130. A circular PCB 152 coupled to the MEMS structure 151 and the delayed ignition circuit assembly 110 to transmit the trigger signal generated by the MEMS structure 151 to the delayed ignition circuit assembly 110 and the lower cover; And a stud 153 to which the screw inserted through the screw hole provided in the 130 is fastened, and the screw is fastened to the stud 153 through the circular PCB 152 to the MEMS assembly 150. Is fixed to the housing 100.

As shown in FIG. 4, the MEMS structure 151 is disposed to be spaced apart from each other and has a pair of contact terminals 156 having a receiving portion 156 ′ provided at one side thereof, and accommodating the contact terminals 156. A proof mass 155 having a protrusion 155 'engaged with the portion 156' and electrically connecting the contact terminal 156 through engagement with the contact terminal 156, and the proof mass 155 A plurality of plate-shaped elastic members 157 supported by the support blocks 158 disposed on both front ends of the front end portions to elastically support the proof mass 155 to be spaced apart from the contact terminals 156; Constraining pin assembly 159 disposed on both sides of the rear end of the proof mass 155 to restrain the movement of the proof mass 155.

In addition, the restraint pin assembly 159 has a front end insertion protrusion 159b inserted into insertion grooves 155 ″ formed at both sides at the rear end of the proof mass 155 to restrain the proof mass 155. A pair of restraining pins 159a, a plurality of negative electrode pieces 159c attached orthogonally to the restraining pins 159a, respectively, on both sides of the restraining pins 159a, and on both sides of the restraining pins 159a, respectively. A positive electrode terminal 159d and a plurality of positive electrode pieces 159e attached to one surface of the restriction pin 159a and disposed at both ends of the positive electrode terminal 159d, respectively, and electrically connected to the restriction pin 159a. The negative terminal 159f and the positive terminal 159d which are connected to each other are installed so as to elastically support the restriction pin 159a in the direction of the proof mass 155 so that the negative terminal 159f and the restriction pin 159a are supported. Consists of a plate-shaped restraint pin spring (159g) to connect.

Meanwhile, the delayed ignition circuit assembly 110 includes a main PCB 111 having a delayed ignition circuit formed on a front surface thereof, and an inductor 112 attached to the front surface of the main PCB 111 to perform an electromagnetic shielding function (EMI Shiled). ), A variable resistor 113 attached to the front surface of the main PCB 111 to finely adjust the ignition delay time, and a power transistor 114 attached to the front surface of the main PCB 111 to adjust the ignition current. ), And an HIC (hybrid integrated circuit, 115) attached to the rear surface of the main PCB 111, the upper cover (top) on the top of the main PCB 111 of the delayed ignition circuit assembly 110 An end of the input connector 125 of 120 is soldered and electrically integrated.

As shown in FIG. 6, the main PCB 111 is short-connected to a launch tube and is activated by a trigger signal of a MEMS structure 151 provided in the MEMS assembly 150 and a first optocoupler U4. Monostable multivibrator (U1) and monostable multivibrator IC for determining the delay time and width of the ignition pulse using a plurality of circuit elements when the trigger signal is input through the first optocoupler U4, and the monostable And a power transistor (BDW94C) for generating an ignition signal according to the ignition pulse transmitted through the second optocoupler U3 connected to the output terminal Q2 of the multivibrator IC U1 and transmitting the ignition signal to the ignition unit of the propulsion engine. do. Here, the monostable multivibrator IC (U1) determines the delay time of the ignition pulse by using the resistor value and the capacitor value connected to the first input terminal (Cx1 / Rx1), the second input terminal (Cx2 / Rx2) The width of the ignition pulse is determined by using the resistor value and the capacitor value connected to.

Naturally, the rocket ignition safety device using the MEMS of the present invention should be assembled in a direction in which the MEMS structure 151 can operate. That is, in the case of using the inertial force in the direction of the firing axis due to the injection acceleration, the rocket ignition safety device is assembled so that the direction of the rocket launch and the direction of the MEMS structure 151 are parallel to each other. The rocket ignition safety device is assembled by moving the rocket ignition safety device in a circumferential direction by a predetermined distance from the center of the rotation axis of the rocket, and assembling the rocket ignition safety device so that the direction of the MEMS structure 151 is perpendicular to the launching direction of the rocket.

The acceleration sensing level of the proof mass provided in the MEMS structure 151 is determined by adjusting the weight of the proof mass 155 and the gap between the proof mass 155 and the contact terminal 156. For example, the proof mass 155 may be operated at 20G to 30G to connect the contact terminals 156 to each other.

Referring to the operation of the rocket ignition safety device using the MEMS of the present invention configured as described above are as follows.

Before power is supplied to the MEMS structure 151, the proof mass 155 is constrained by the restraining pin 159a of the restraining pin assembly 159 as shown in FIG. 4, and the proof mass 155 is a contact terminal. The state spaced apart from 156 is maintained. Accordingly, the contact terminals 156 are not electrically connected to each other so that the trigger signal is not generated in the MEMS structure 151.

Subsequently, when power is supplied to the restraint pin assembly 159 from the outside, attraction force is generated between the negative electrode piece 159c and the positive electrode piece 159e to attract the restraining pin 159a, and the restraining pin 159a. ) Is to retreat to overcome the elastic force of the restraint pin spring (159g). Accordingly, the insertion protrusion 159b of the restraining pin 159a is separated from the insertion groove 155 ″ formed at the rear end of the proof mass 155, and the proof mass 155 by the restraining pin assembly 159 is removed. However, since the proof mass 155 is elastically supported by the plate-shaped elastic member 157, the proof mass 155 is kept spaced apart from the contact terminal 156.

In this state, when an inertial force of 20G to 30G is applied in the movable direction of the proof mass 155, the proof mass 155 moves forward to overcome the plate-shaped elastic member 157 to accommodate the contact terminal 156. A protrusion 155 ′ of the proof mass 155 is coupled to 156 ′. Accordingly, the contact terminal 156 is maintained in the electrically conductive state by the proof mass 155, the MEMS structure 151 generates a trigger signal. That is, the trigger signal is generated only when the inertial force applied from the outside is greater than the elastic force of the plate-shaped elastic member 157 supporting the proof mass 155. While the inertial force is applied, as shown in FIG. The contact terminal 156 maintains an electrically conducting state.

When the MEMS structure 151 is operated using the launching axial acceleration of the rocket, the contact terminal 156 maintains the electrical conduction state only until the rocket exits the launch tube. That is, the contact terminal 156 maintains the electrical conduction state by the proof mass 155 only in a section in which the injection acceleration occurs, and when the rocket exits the launch tube and the acceleration value disappears, the proof mass 155 becomes the plate-shaped elasticity. The member 157 is returned to its original position and the contact terminals 156 are separated from each other.

As such, when the trigger signal is supplied to the delay ignition circuit using the contact terminal 156 connected only for a relatively short time, the delay ignition circuit operates only when power is supplied to the rocket and the injection acceleration occurs sequentially. It is a very important contribution to the safety of the rocket.

As described above, if the two contact terminals 156 are connected to the trigger terminal of the delayed ignition circuit as shown in FIG. 6 in the state where the MEMS structure 156 is operated, the rocket was shorted when it was ejected from the launch tube and ejected. The MSLAWY terminal is opened, the first optocoupler U4 is activated, and then a trigger signal is applied to the monostable multivibrator IC U1. The monostable multivibrator IC U1 determines the delay time of the ignition pulse based on a resistance value and a capacitor value connected to the first input terminal Cx1 / Rx1 and a resistance value connected to the second input terminal Cx2 / Rx2. Determine the width of ignition pulse by using and capacitor value. If a predetermined time is delayed after the trigger signal is applied, an ignition pulse is generated through the output terminal Q2. The ignition pulse is transmitted to the power transistor BDW94C via the second optocoupler U3 connected to the output terminal Q2. The ignition pulse flows for a predetermined time in the power transistor BDW94C to ignite the ignition of the propulsion engine. Let's go.

As such, the rocket injected and fired by the gas pressure of the launching device is free to fly without being ignited until a predetermined distance from the launching tube, and after about 400 milliseconds (ms) elapses, Ignite Thus, the rocket is sufficiently spaced apart from the launcher so that the launcher and the rocket operator are safely protected from the after-storm generated by the operation of the propulsion engine.

On the other hand, even if the rocket is temporarily dropped during transportation, storage or repair of the rocket, the proof mass 155 of the MEMS structure 151 is maintained by the restraint pin assembly 159 as long as power is not supplied to the rocket. The proof mass 155 may not move toward the contact terminal 156 and is separated from the contact terminal 156. Therefore, no trigger signal is absolutely applied to the delay ignition circuit and the propulsion engine of the rocket is safely stored without accidental ignition.

In addition, if the rocket falls during handling while power is supplied to the rocket, an impact applied to the rocket is incidentally applied in a direction in which the proof mass 155 can be operated so that the proof mass 155 is instantaneously contacted. Even if the terminals 156 are connected to each other, as long as the MSLAWY terminal of FIG. 6 is connected to the ground (GND), no trigger signal for operating the monostable multivibrator IC U1 is generated and the rocket ignition is It won't happen.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is clearly understood that the same is by way of illustration and example only and is not to be taken by way of limitation, Changes will be possible.

100: Housing
110: delayed lighting circuit assembly
111: main PCB
U1: Monostable Multivibrator IC
Cx1 / Rx1: first input terminal
Cx2 / Rx2: second input terminal
Q2: output terminal
U3: second optocoupler
U4: first optocoupler
BDW94C: Power Transistor
112: inductor
113: variable resistance
114: power transistor
115: HIC (Hybrid Integrated Circuit)
120: top cover
125: input connector
130: lower cover
140: output connector
145: output line
150: MEMS assembly
151: Micro Eletro-Mechanical System Structure
155: Proof Mass 155 ': protrusion
156: contact terminal 156 ': receiving portion
157: plate-shaped elastic member
158: support block
159: restraint pin assembly
159a: restraint pin 159b: insertion protrusion
159c: negative electrode piece 159d: positive electrode terminal
159e: positive electrode piece 159f: negative electrode terminal
159g: restraint pin spring
152: circular PCB
153: Stud

Claims (9)

A housing 100 for receiving and supporting each component;
A delay ignition circuit assembly (110) assembled along a slot machined on an inner surface of the housing (100) and outputting an ignition signal under a specific condition;
An input connector (125) installed on the upper cover (120) of the housing (100) to supply power to the delayed ignition circuit assembly;
A micro eletro-mechanical system (MEMS) assembly assembled to the lower cover 130 of the housing 100 and vertically coupled to the delay ignition circuit assembly 110 to provide a trigger signal to the delay ignition circuit assembly 110. 150;
Output connected to the housing 100, the output line 145, coupled to the ignition of the propulsion engine, and outputs the ignition signal of the delayed ignition circuit assembly 110 transmitted through the output line 145 to the ignition circuit Rocket ignition safety device using a MEMS, characterized in that it comprises a connector (140). The method of claim 1,
The MEMS assembly 150 includes a MEMS structure 151 which is operated by a launch axis direction inertia force or a rotational inertia force caused by the ejection acceleration of the rocket and generates a trigger signal, and is assembled to the lower cover 130 and on the upper surface of the MEMS structure. The structure 151 and the delayed ignition circuit assembly 110 are coupled to include a circular PCB 152 for transmitting a trigger signal generated by the MEMS structure 151 to the delayed ignition circuit assembly 110. Rocket ignition safety device using MEMS. The method of claim 2,
The MEMS structure 151 is arranged to be spaced apart from each other, and a pair of contact terminals 156 formed with a receiving portion 156 'provided on one side and the receiving portion 156' of the contact terminal 156 is engaged. Proof mass 155 having a protruding portion 155 ′ and electrically connecting the contact terminal 156 through engagement with the contact terminal 156, and on both front ends of the proof mass 155. A plurality of plate-shaped elastic members 157 supported by the support blocks 158 disposed therein to elastically support the proof mass 155 to be spaced apart from the contact terminal 156, and the proof mass 155 Rocket ignition safety device using a MEMS characterized in that it comprises a restraining pin assembly (159) disposed on both sides of the rear end to restrain the movement of the proof mass (155). The method of claim 3,
The restraint pin assembly 159 has a pair of insertion protrusions 159b at the ends thereof inserted into insertion grooves 155 ″ formed at both ends of the proof mass 155 to restrain the proof mass 155. Constraining pins 159a, a plurality of negative electrode pieces 159c attached orthogonally to the constraining pins 159a on both sides of the constraining pins 159a, and disposed on both sides of the constraining pins 159a, respectively. A positive electrode terminal 159d having a plurality of positive electrode pieces 159e attached to one surface in a confinement pin 159a direction, and a negative electrode disposed at both ends of the positive electrode terminal 159d and electrically connected to the constraining pin 159a, respectively. The plate 159f is installed to elastically support the restriction pins 159a in the direction of the proof mass 155 at both ends of the positive electrode terminal 159d and is connected to the negative electrode terminal 159f and the restriction pins 159a. Rocket ignition safety device using a MEMS, characterized in that it comprises a restraining pin spring (159g). 5. The method according to any one of claims 1 to 4,
The delayed ignition circuit assembly 110 includes a main PCB 111 having a delayed ignition circuit formed on a front surface thereof, and an inductor 112 attached to a front surface of the main PCB 111 to perform an electromagnetic shielding function (EMI Shiled). ), A variable resistor 113 attached to the front of the main PCB 111 to finely adjust the ignition delay time, and a power transistor attached to the front of the main PCB 111 to adjust the ignition current. Transister, 114), and rocket ignition safety device using a MEMS, characterized in that made of a HIC (hybrid integrated circuit, 115) attached to the back of the main PCB (111). The method of claim 5,
Rocket ignition safety device using a MEMS, characterized in that the end of the input connector 125 of the upper cover 120 is soldered to the top of the main PCB (111) of the delayed ignition circuit assembly (110) and electrically integrated. The method of claim 5,
The main PCB 111 has a first optocoupler (U4) and a short connected to the launch tube and activated by a trigger signal of the MEMS structure 151 provided in the MEMS assembly 150, and Mono-Stable Multivibrator (U1) and a monostable multivibrator IC for determining the delay time and width of the ignition pulse using a plurality of circuit elements when a trigger signal is input through the first optocoupler U4. A power transistor (BDW94C) for generating an ignition signal according to the ignition pulse transmitted through the second optical coupler (U3) connected to the output terminal (Q2) of the vibrator IC (U1) and transmits to the ignition of the propulsion engine (BDW94C) Rocket ignition safety device using a MEMS, characterized in that. delete The method of claim 1,
The delayed ignition circuit assembly 110, the MEMS assembly 150, and the upper cover 120 are integrated by soldering and inserted into the housing 100, and are inserted through screw holes provided in the lower cover 130. A rocket ignition safety device using a MEMS, characterized in that the screw is fastened to the stud 153 through the circular PCB (152) of the MEMS assembly 150 is fixed to the housing (100).

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