Controlling apparatus for ejecting guided missile and method thereof

Abstract

Provided are a controlling apparatus for ejecting a guided missile and a method for ejecting the guided missile inserted into a launching tube. More particularly, The present invention provides a controlling apparatus for ejecting a guided missile additionally including a power supply controller which applies a signal for ejecting a guided weapon to a fuse during separating the fuse used for igniting a propulsion engine in the guided weapon and an ejection controlling method using the same.

1 . A controlling apparatus for ejecting a guided missile for ejecting the guided missile inserted into a launching tube, the apparatus comprising:
 a power supply unit providing a first electric signal and a second electric signal;   a signal guiding unit outputting a first ignition signal depending on whether to input the first electric signal outputted to the power supply unit;   a mounting/demounting connection unit connecting a ground (GND) and the signal guiding unit while the guided missile is inserted into the launching tube and disconnecting the ground and the signal guiding unit from each other while the guided missile is separated from the launching tube;   an ignition signal generating unit generating a second ignition signal for igniting a propulsion engine provided in the guided missile so as to provide thrust force to the guided missile by receiving the first ignition signal;   a relay unit transferring the first ignition signal to the ignition signal generating unit by using the first ignition signal outputted from the signal guiding unit and the second electric signal from the power supply unit; and   a power controller controlling the second electric signal provided from the power supply unit to be applied to the relay unit.   
     
     
         2 . The apparatus of  claim 1 , wherein the relay unit includes:
 a first port into which the first ignition signal is inputted;   a second port connected with the ground; and   a switch connected to any one of the first port and the second port,   wherein a port connected to the switch is determined depending on whether to input the second electric signal.   
     
     
         3 . The apparatus of  claim 1 , wherein the power controller includes:
 a power supply squib signal applying unit applying the second electric signal provided from the power supply unit to the relay unit; and   a check signal applying unit controlling the ignition signal generating unit to generate the second ignition signal in order to check an operation state of the ignition signal generating unit.   
     
     
         4 . The apparatus of  claim 1 , wherein the ignition signal generating unit generates the second ignition signal when a predetermined time elapses after receiving the first ignition signal. 
     
     
         5 . The apparatus of  claim 1 , wherein the power supply unit includes a transmitting unit that remotely transmits voltage data of the second electric signal outputted from the power supply unit so as for an ejection controller of the guided missile to monitor the voltage data. 
     
     
         6 . A controlling method for ejecting a guided missile for ejecting the guided missile inserted into a launching tube, the method comprising:
 (a) controlling a second electric signal to be outputted from a power supply unit providing a first electric signal and the second electric signal;   (b) applying an ejection signal for ejecting the guided missile from the launching tube;   (c) stopping input of the first electric signal supplied from the power supply unit as the guided missile is separated from the launching tube by applying the ejection signal;   (d) outputting a first ignition signal as the input of the first electric signal is stopped at step (c); and   (e) supplying a second ignition signal to a propulsion engine provided in the guided missile so as to provide thrust force to the guided missile by receiving the first ignition signal generated at step (d).   
     
     
         7 . The method of  claim 6 , wherein at step (e), the second ignition signal is supplied to the propulsion engine by generating the second ignition signal by using the second electric signal outputted at step (a). 
     
     
         8 . The method of  claim 6 , wherein after step (a), (a 1 ) generating voltage data of the second electric signal and remotely transmitting the voltage data so as for an ejection controller of the guided missile to monitor the voltage data are performed and step (b) is performed. 
     
     
         9 . The method of  claim 6 , wherein at step (e), the second ignition signal is supplied to the propulsion engine when a predetermined time elapses after the first ignition signal is received.