Abstract:
The present invention discloses a missile ejection system and a canister thereof. The missile ejection system comprises: comprising: a canister formed as a cylindrical shell, a partition wall protruding from an inner wall of the canister so as to divide the canister into a first chamber for housing a missile therewithin and a second chamber, and having at least one hole therethrough for allowing the flowing of gas through the partition wall, a gas generator secured to the partition wall in the second chamber so that a gas outlet thereof faces in an opposite direction from the first chamber, and an obturator including a sealing plate formed with a concave surface toward a fore-end of the missile for enclosing a tail end of the missile, and a radially extending skirt plate extended from the circumference of the sealing plate to the inner wall of the canister and inclined toward the fore-end of the missile for covering the space between the missile and the inner canister, wherein the missile is propelled by the pressure of the gas discharged out of the gas generator from the second chamber to the first chamber through the hole, being pressurized by the flown-in gas in the first chamber, pushing upon the obturator. Thereby, the system is able to effectively release a missile from a canister by a gas generator without using a missile propulsion engine, thereby fundamentally preventing the damage of ground equipments or peripheral missiles.

Description:
BACKGROUND OF THE INVENTION 
   1. Field of the Invention 
   The present invention relates to a missile ejection system and a canister thereof, and more particularly relates to a missile ejection system which is capable of fundamentally preventing ground equipment or peripheral missiles from being damaged, by releasing a missile from a canister without using a missile propulsion engine therein. 
   2. Description of the Background Art 
   Up to the present, in many countries the majority of missile launching systems have been developed to be of such a type that a missile is released from a canister using a thrust generated by a propulsion ignition engine of the missile. However, in this type of launching system, there is a risk that ground equipment or peripheral missiles in a launcher might be damaged due to the high temperature and high pressure flames from the missile propulsion engine. Accordingly, a flame treatment device or a protective measure is required necessarily for protecting those equipments. Besides, this type of launching system had problems that a thrust loss occurs as a detent is unlocked and a missile is released by using its propulsion engine during the initial launch period. 
   SUMMARY OF THE INVENTION 
   Therefore, an object of the present invention is to provide a missile ejection system which is capable of fundamentally preventing ground equipment or peripheral missiles from being damaged by releasing a missile from a canister without using a propulsion engine of the missile, thereby protecting those equipments from flames without need for a flame treatment device or a measure for protection. 
   To achieve the above-described object, there is provided a missile-ejection system in accordance with the present invention comprising: a canister formed as a cylindrical shell, a partition wall protruding from an inner wall of the canister so as to divide the canister into a first chamber for housing a missile therewithin and a second chamber, and having at least one hole therethrough for allowing the flowing of gas through the partition wall, a gas generator secured to the partition wall in the second chamber so that a gas outlet thereof faces in an opposite direction from the first chamber, and an obturator including a sealing plate formed with a concave surface toward a fore-end of the missile for enclosing a tail end of the missile, and a radially extending skirt plate extended from the circumference of the sealing plate to the inner wall of the canister and inclined toward the fore-end of the missile for covering the space between the missile and the inner canister, wherein the missile is propelled by the pressure of the gas discharged out of the gas generator from the second chamber to the first chamber through the hole, being pressurized by the flown-in gas in the first chamber, pushing upon the obturator. 
   This is to effectively release a missile from the canister by the gas generator without using any missile propulsion engine by forming an enclosed space between the gas generator and the obturator, and thus, to fundamentally prevent the damage of ground equipment or peripheral missiles. 
   Preferably, the missile ejection system further comprises a guide formed on the outer circumference of the skirt plate so that the outer circumference thereof is in contact with the inner wall of the canister. This is for achieving a smooth missile ejecting by reducing a friction between the guide and the inner wall of the canister during the advance of the missile. Further, plural guides can be formed. 
   Furthermore, it is easy to manufacture the partition wall when formed integrally with the canister. 
   It is desirable that the canister consists of a front cover, a rear cover and a combination of a plurality of tubes between the front cover and the rear cover. With the combination of plurality of tubes, any heavy machine tools are not required and an error rate produced in the manufacture of the canister can be drastically lowered. Further, in the event of moving or storing the canister for an assembly purpose, the size of a unit tube becomes smaller, and thus handling of the canister is made easier. 
   Herein, tongues and grooves engageable with each other are respectively formed on the ends of the adjacent tubes in order to easily assemble the adjacent tubes to each other. Moreover, tapered recesses are formed in the inner walls of adjacent tubes so as to eliminate a level difference in the inner surfaces of the adjacent tubes. 
   Furthermore, a support part is formed on at least two tubes thereof in order to make it easier to mount or lay the canister on a launcher, thereby realizing an easy mounting of the ejection system on the launching stand and thus realizing a convenient transportation of the same conveniently. 
   In an effective way, the missile ejection system further comprises at least one guide rail formed inside the canister along the longitudinal direction of the canister in order to prevent rolling motion of the missile within the canister. In order to achieve this function, the skirt plate of the obturator has at least one guide part which engages the corresponding guide rail. 
   Preferably, the missile ejection system further comprises at least one detent engaging the tail end of the missile so as to restrain the missile in the longitudinal direction. 
   It is also effective that the missile ejection system further comprises at least one immobilizer which contacts with a corresponding sabot protruding on the outer peripheral surface of the missile so as to restrain the missile in a transverse direction. Accordingly, a clearance between the missile and the canister is completely eliminated so that a relative motion therebetween is not permitted any longer. 
   Preferably, the immobilizer further comprises a friction pin urged in contact with the outer peripheral surface of the corresponding sabot. 
   Further, the missile ejection system further comprises: a connector connected with a peripheral surface of the missile so as to exchange an electric signals between the missile and the outside of the missile; and at least one connection link hinge-coupled between the connector and the inner surface of the canister; wherein, during the missile&#39;s launching, the connector connected with the missile moves along the missile and then the connector becomes disconnected from the missile when the connecter cannot follow the missile any longer. 
   Herein, the missile ejection system comprises an obturator separator, including at least one stop bar provided on the inner surface of the canister, and at least one snatcher formed integrally on an outer circumference of the skirt plate of the obturator and having a receiving part which is aligned with the stop bar so as to receive and engage the stop bar as the missile is ejected from the canister. Therefore, it can eliminate the possibility of damaging the ground objects upon the missile&#39;s falling down on the ground after the obturator is released from the canister and separated by the missile propulsion engine. 
   It is desirable that the stop bar further comprises a deformable member absorbing a shock by plastic deformation. 
   The a V-shaped plate spring is preferably provided at a front end of the corresponding each stop bar, stopping protuberances protruding inward are formed at an opening of the snatcher so that the opening has a smaller width than the receiving parts does, and when the stop bars are inserted into the receiving parts of the snatcher, the V-shaped plate spring at a front end of the stop bars is contracted and locked with the snatcher so as to prevent from being released. This is for preventing the obturator not released from the canister from being dropped on the bottom of the canister and damaging the inside of the canister. 
   Additionally, there is provided a canister of a missile ejection system in accordance with the present invention, comprising: a front cover for opening and closing a front portion of a missile; a rear cover for surrounding a rear portion of the missile; and at least two tubes rigidly connected on the ends thereof between the front cover and the rear cover. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
     The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. 
     In the drawings: 
       FIG. 1  is a cut away view showing the interior of a missile ejection system in accordance with one embodiment of the present invention; 
       FIG. 2  is a side view showing the exterior of the missile ejection system of  FIG. 1 ; 
       FIG. 3  is an enlarged cross sectional view of part ‘B’ of  FIG. 1 ; 
       FIG. 4  is an enlarged cross sectional view of part ‘A’ of  FIG. 1 ; 
       FIG. 5  is an enlarged cross sectional view of part ‘C’ of  FIG. 4 ; 
       FIG. 6  is an enlarged perspective view of part ‘A’ of  FIG. 1 ; 
       FIG. 7  is a side cross sectional view illustrating the construction of a sabot and of an immobilizer of a canister of the missile ejection system of  FIG. 1 ; 
       FIG. 8  is a partially cutaway perspective view of parts of the canister of the missile ejection system of  FIG. 1 ; 
       FIG. 9  is a side schematic view illustrating the construction of a umbilical cable separator of the missile ejection system of  FIG. 1 ; 
       FIG. 10  is a side cross sectional view illustrating the construction of an obturator separator of the missile ejection system of  FIG. 1 ; 
       FIG. 11  is a side cross sectional view illustrating an inoperative state of the obturator separator of the missile ejection system of  FIG. 1 ; 
       FIG. 12  is a side cross sectional view illustrating an operative state of the obturator separator of  FIG. 10 ; and 
       FIG. 13  is a front view illustrating the construction of the obturator of the missile ejection system of  FIG. 1 . 
   

   DETAILED DESCRIPTION OF THE INVENTION 
   Hereinafter, the present invention will be described in detail with reference to the accompanying drawings. 
   Detailed description of well-known functions and structures is omitted in order to clarify the key points of the present invention. 
   A missile ejection system  1  in accordance with one embodiment of the present invention includes a canister  20  protecting a missile  10  from the exterior disturbance before the launching of the missile  10  and serving as a cylinder during launching of the missile  10 , a plurality of detents  30  restraining the missile  10  in the longitudinal direction before the launching of the missile  10 , a gas generator  40  generating pressure in order to eject the missile  10  from the canister  20  in the event the missile  10  is launched, a plurality of sabots  50  fitting to the missile  10  in the canister  20  and protruding on the outer peripheral surface of the missile  10 , an umbilical cable separator  60  arranged to smoothly separate a nib connector  63  from a peripheral surface of the missile  10  in the event the missile  10  is launched, a plurality of obturator separators  70  mounted in the front portion of the canister  20  so as to separate an obturator  80  attached on the tail end of the missile  10  from the canister  20  in the event the missile  10  is launched, the obturator  80  being placed on the tail end of the missile  10  so as to move integrally with the missile  10  for launching and guiding the missile  10  in the canister  20  by being pushed by a high pressure gas ejected from the gas generator  40 , and a plurality of immobilizers  90  arranged to restrain the transverse motion of the missile  10  by contacting with corresponding ones of the sabots  50  protruding on the peripheral surface of the missile  10  in the event the missile  10  in the canister  20  moves in its housed state. 
   The tail end of the missile  10  is secured longitudinally in the canister  20  by the detents  30 . Thus, it is possible to prevent the missile  10  from fluctuating in the longitudinal direction in the canister  20  before launching of the missile  10 . 
   The canister  20  is divided by a partition wall  28   b  into a first chamber I for housing the missile  10  and a second chamber II excluding the first chamber I. The canister  20  which houses the missile  10  mounted in the first chamber I protects the missile  10  from external effects such as humidity and from foreign substances, serves as a cylinder that pushes the missile  10  out when the missile  10  is to be launched, and is provided with a front cover  21  covering the front portion of the missile  10 , a rear cover  22  protecting an ejection system and supporting an impact load upon launching, a missile restraining tube  28  connected to the rear cover  22  and mounting the tail end of the missile  10 , the gas generator  10  and the like thereon, a plurality of tubes  23  to  27  each formed in a hollow cylindrical shell shape between the missile restraining tube  28  and the front cover  21 , tube connecting parts  23   a  to  27   a  connecting between the tubes  23  to  27 , and guide rails  29  extended lengthwise on an inner wall of the canister  20  along the longitudinal direction of the missile  10  so as to prevent in cooperation with the obturator  80  the rolling motion of the missile  10  during the missile  10  is ejected. 
   That is, the first chamber I of the canister  20  is formed by the front cover  21 , the plurality of tubes  23  to  27  sequentially connected to the front cover  21  and the partition wall  28   b  of the missile restraining tube  28 , and the second chamber II of the canister  20  is formed by the missile restraining tube  28  including the partition wall  28   b  and the rear cover  22 . 
   The canister  20  is formed of the plurality of tubes  23  to  28  in order to manufacture a relatively long canister  20  at a lower cost and to make the manufacture easier and quicker. Conventionally, since a substantially long canister was manufactured in a single unit, many problems occurred such that a huge production facility was required for the manufacture thereof, a high material cost and a processing cost was incurred due to a defect ratio of the manufactured products, and it was very troublesome to carry the canister to an assembly place after the manufacturing. However, the canister of this invention can overcome these problems. 
   In the procedure of forming the canister  20  by the plurality of tubes  23  to  27  and the missile restraining tube  28 , no protruding part should be formed on an inner wall  20   b  of the connecting parts  23   a  to  28   a  between the tubes  23  to  28 , so that the missile  10  can move smoothly. This is because, in case any protruding part is formed, an interference with the obturator  80  moving along with the missile  10  is produced and an unnecessary pressure loss is also caused. For this reason, in the connecting parts  24   a  to  28   a  of the respective tubes  23  to  28 , as shown in  FIG. 3 , coupling grooves  24   c  and  25   c  are dovetailed. Protuberances formed on the tubes  23  to  28  and on the end of front cover  21  are inserted into the grooves formed in adjacent tubes  24  to  28  and in rear cover  22  and are engaged by bolts  24   b  and  28   b,  and a chamfer or tapered recess  25   d  is formed on adjacent mating parts of the interiors of the tubes  23  to  28 , thereby eliminating any protruding interior surface on the connecting parts  23   a  to  28   a.    
   Among the plurality of tubes  23  to  28 , the supporting tube  27  is provided at an outer peripheral surface thereof with a supporter  27   b  for easily placing or laying the ejection system  1  on a launcher. Further, the missile restraining tube  28  is provided with the partition wall  28   b  dividing the canister  20  into the first chamber I and the second chamber II. Around the partition wall  28   b  with a constant interval therebetween, multiple gas discharge through holes  28   c  are arranged serving as orifices or passages enabling a high pressure gas from the second chamber II to push the obturator  80  located on the first chamber I. 
   The obturator  80  is fixed at the tail end of the missile  10  so as to be moved integrally with the missile  10  in the canister  20 . That is, as shown in  FIG. 5 , a first protuberance  28   d  is protruded on the partition wall  28   b  for surrounding a rear protruding part  82   a  of the obturator  80  and mounting the same within the first protuberance  28   d.  A second protuberance  82   b  is protruded on the front surface of the obturator  80  for surrounding a protruding part of the tail end of the missile  10 , whereby the obturator  80  is engaged between the tail end of the missile  10  and the front surface of the partition wall  28   a  without using any fastening mechanism and thus the tail end of the missile  10  is restrained in a transverse direction. As shown in  FIG. 13 , the obturator  80  includes a sealing plate  81  formed with a concave surface curved toward the fore-end  10   a  of the missile  10  so as to enclose the tail end of the missile  10 , a radially extended skirt plate  82  extending from the circumference of the sealing plate  81  close to the inner wall of the canister  20  so as to be sloped in a direction toward the fore-end  10   a  of the missile  10 , snatchers  83  arranged around the circumference of the skirt plate  82  at a 90° interval, guides  84  arranged at proper intervals between the snatchers  83  on the circumference of the skirt plate  82  so as to guide the launching of the missile  10  by contacting between the obturator  80  and the inner wall of the canister  20 , guide grooves  86  formed in the circumference of the skirt plate  82  so as to suppress the rolling motion of the obturator  80  and the missile  10  by engaging with guide rails  29  and grooves  87  formed so as to avoid an interference with friction pins  91  of immobilizers  90 . 
   Herein, as shown in  FIG. 11 , the snatchers  83  are provided with recessed receiving parts  83   a,  and protruding parts  83   b  at the openings of the receiving parts  83   a  having a smaller inner diameter than the width of the receiving parts  83   a  are formed on the openings of the receiving parts  83   a.    
   Teflon clips  85  are mounted on the external surfaces of the guides  84  in contact with the inner wall of the canister  20  in order to reduce a frictional force. Thus, the missile  10  is capable of smoothly traveling along the inner wall  20   b  of the canister  20  in the process of being released from the canister  20 . 
   The detent  30  includes a bolt  31  through the partition wall  28   b  of the missile for restraining tube  28 . With the bolt  31  passing through the partition wall  28   b,  one end thereof is fitted in a self-aligning connector  32  placed on the tail end of the missile  10  and the other end thereof is engaged at the tail end of the partition wall  28   b,  whereby the bolt  31  serves to restrain the missile  10  in the longitudinal direction of the missile  10  in the canister  20  from any disturbance before launching of the missile  10 . More specifically, the self-aligning connector  32  is freely rotatable in the transverse direction (i.e., a direction perpendicular to the axial direction) of the bolt  31  and thus enables the end of the bolt  31  to rotate freely in the transverse direction. Also, since a flat surface of a semi-spherical washer  34  is in contact with the head portion of the bolt  31 , and since a curved surface of the semi-spherical washer  34  is placed in contact with a curved surface of a bushing  33  inserted between the partition wall  28   b  and the bolt  31 , the bolt  31  is capable of rotating freely, and thus the bolt  31  is always given only a tensile force. In case that the missile is to be ejected, by supplying a current though the bolt  31  (not shown in the Figure) right before launching of the missile, the area  31   a  having smaller diameter is broken in advance. 
   The gas generator  40  has a small quantity of a highly efficient propellant stored in an inner chamber thereof, and is fastened and secured at four places  41  to the center part of the partition wall  28   b.  When a launching signal of the missile  10  is inputted from the outside, high pressure gas is discharged toward the rear cover  22 , the enclosed space of the second chamber II is filled with the high pressure gas to build a pressure therewithin, the filled high pressure gas flows to the first chamber I through the plurality of gas discharge through holes  28   c  penetrating around the partition wall  28   b  in the direction of the arrows indicated at  40   a  and pushes against the rear surfaces of the sealing plate  81  and skirt plate  82  of the obturator  80 , thereby urging the missile  10  to start moving in the canister  20 . 
   Herein, with the enclosed space formed between the gas outlet of the gas generator  40  and the obturator  80  in order to minimize the leakage of the high pressure gas from the gas generator  40 , the efficiency of the gas generator  40  can be maximized. Therefore, the obturator  80  enclosing the tail end of the missile  10  is effectively formed in a concavedly curved shape similarly to a semi-spherical shape or semi-elliptical shape. That is, as the sealing plate  81  of the obturator  80  is formed with a curved surface, it becomes a structure capable of supporting a big force with a smaller thickness. And, as the convex side of the curved surface of the sealing plate  81  is toward the fore-end  10   a  of the missile  10 , the obturator  80  occupies almost no space in the longitudinal direction of the missile  10 , thereby enabling to reduce the length of the canister  20 . Further, the skirt plate  82  is formed at an angle of inclination toward the fore-end  10   a  of the missile  10 . Thus, if some bending is generated between the sealing plate  81  and the skirt plate  82  due to the pressure of the high pressure gas, a clearance between the missile  10  and the canister  20  becomes slightly bigger, thereby allowing smooth moving of the missile  10  forwardly. 
   In the sabots  50 , pins  51   b  are fitted in the grooves recessed in the outer peripheral surface of the missile  10 . In other words, the pins  51   b  are not fastened but are only inserted into the grooves in the missile  10 . Each sabot  50  is provided with an external case  51  formed of nylon and with springs  52  which are installed in a normally compressed condition therewithin. Consequently, the sabots  50  are released when the missile  10  is expelled from the canister  20 , and, thereafter, the sabots  50  can be separated from the missile  10  by the elastic force of the expanding springs  52 . 
   As shown in  FIG. 8 , the immobilizers  90  are apparatuses which are formed at 90° intervals at four places on the outer peripheral surface of the missile  10 , and which protect the missile  10  by adjusting the clearance between the canister  20  and the missile  10 , so that the clearance between the sabot  50  and the immobilizers  90  become the minimum and relative motion does not occur therebetween even when the missile  10  mounted in the canister  20  is fluctuated in a transverse direction during transportation or the like. The immobilizers  90  are each provided with a main body  92  secured to the canister  20  and comprise a friction pin  91  placed in the main body  92  with a predetermined contact force with the corresponding sabot  50 , a clamping bolt  91   a  clamping the main body  92  to the canister  20 , and a main body cover  93  formed for preventing the release of the friction pin  91 . As a contact surface is formed between the bottom surface  91   a  of the friction pin  91  and the main body surface  51   a  of the sabot  50 , they are kept contacted by friction based on a normal force. 
   Accordingly, if a force overcoming the friction between the contact surface  51   a  of the sabots  50  and the friction pin  91  is applied with respect to the longitudinal direction of the missile  10 , the restraining state by the immobilizers  90  can be released. 
   The umbilical cable separator  60  is constructed in a manner to smoothly separate the umbilical cable  65  of a nib connector  63  from the missile  10  when the missile  10  is launched. As shown in  FIGS. 8 and 9 , the umbilical cable separator  60  includes connection links  61  having opposite ends  61   a  and  61   b  thereof respectively hinge-coupled to the body of the nib connector  63  and to a casing  64  and all having the same length, a compressed spring  62  connected between the casing  64  and one of the connection links  61  for preventing the connection link  61  from moving by more than a predetermined extent, the casing  64  surrounding the umbilical cable separator  60 , and the umbilical cable  65  being connected between the missile  10  and the nib connector  63 . 
   Herein, as the lengths of the connection links  61  are all the same, thus the nib connector  63  is able to keep parallel to the inner surface of the casing  64  regardless of the motion of the connection links  61 . The one of the connection links  61  is connected to the coil spring  62  via the end of a link  66  formed in an L-shape and protruded therefrom, and the spring  62  applies such a force that it urges the connection link  61  to normally stand upright whereby the nib connector  63  is kept firmly coupled to the missile  10 . Moreover, when the missile  10  is launched and travels in the longitudinal direction, the nib connector  63  moves along with the missile  10  while keeping parallel thereto. With the movement, when the missile  10  moves upwardly over some extent, nib connector  63  cannot follow the missile  10  due to the length limitation of the connection links  61 , and thus, the umbilical cable  65  becomes disconnected with the nib connector  63 , and the spring  62  applies a force in such a direction that the connection links  61  are laid onto the inner surface of the casing  64  (i.e., to the left direction as shown in  FIG. 9 ), thereby keeping the connection links  61  and the nib connector  63  lying onto the casing  64 . 
   The obturator separator  70  is provided for eliminating the possibility that the obturator  80  falls down on the ground and damages ground equipment and neighboring canisters when the missile is expelled out of the canister. More concretely, when the missile  10  is released from the canister  20  with the obturator  80  mounted on the tail end thereof, the missile  10  is firstly launched by the gas pressure created in the canister by the gas generator  40 , and then the missile  10  expelled out of the canister  20  is secondly launched toward a target by a propulsion engine mounted in the missile  10 . As shown in  FIGS. 10 to 12 , the ejection separator  70  includes a plurality of holders  71  mounted at spaced intervals on the inner surface of the stopping tube  23  of the canister  20 , a stop bar  72  held within each holder  71 , a shock absorber  73  made of metal installed surrounding the periphery of each of stop bars  72  in the shape of a conical tube, and a V-shaped plate spring  74  mounted on the end  72   a  of the front part of each of the stop bars  72 . 
   By the aforementioned construction, while the missile  10  travels together with the obturator  80  within the canister  20 , the receiving parts  83   a  of the snatchers  83  of the obturator  80  are aligned with the stop bars  72  respectively. Therefore, as the missile  10  travels further, as shown in  FIG. 12 , the ends of the stop bars  72  begin to enter the corresponding receiving parts  83   a  of the snatchers  83 , and then the shock absorption parts  73  are compressed as the missile travels further for thereby absorbing the kinetic energy by the deformation of the shock absorption parts  73 . Then, when the obturator  80  can no longer move together with the missile  10  because of the interference with the snatchers  83 , the obturator  80  is separated from the tail end of the missile  10 . Herein, the V-shaped plate springs  74  are contracted when the stop bars  73  begin to enter the receiving parts  83   a,  and then the V-shaped plate springs  74  can become inserted into the receiving parts  83   a.  As the rear part of each of the V-shaped plate springs  74  is engaged with the corresponding protruding part  83   b,  the obturator  80  will not drop down to the bottom part of the canister  20  but will be hung on the obturator separator  70  thereby being secured within canister  20  for enabling to reuse it. 
   Hereinafter, the operating principle of the present invention will be described. 
   In the event the missile  10  is transported, after being placed in the missile ejection system  1  in accordance with the present invention, even if an external shock is applied thereto, it is possible to prevent the missile  10  from relatively moving within the canister  20  by the detents  30  longitudinally securing the missile  10  and the immobilizers  90  respectively securing the missile longitudinally and transversely. 
   In the event the missile  10  is launched using the ejection system  1  in accordance with the present invention, when a launching signal is transferred to the missile  10  through the umbilical cable  65 , the detents  30  longitudinally restraining the missile  10  are broken, and when high pressure gas is blown off from the gas generator  40  into the enclosed space between the obturator  80  mounted on the tail end of the missile  10  and the gas generator  40 , the missile  10  starts to move within the canister  20 . At this time, the front cover  21  is broken at an initial stage since the gas pressure is partially transferred thereto. With the traveling of the missile  10 , a frictional contact between the friction pins  91  of the immobilizers  90  laterally restraining the missile  10  and the sabots  50  is released. And, the connection links  61  of the umbilical cable separator  60  also undergo a rapid rotary motion by the urging of the spring  62 , to thus separate an electrical connection between the nib connector  63  and the missile  10 . 
   Regarding the traveling of the missile  10  in the canister  20 , since the obturator  80  moves along the guide rail  29  formed lengthwise upon the inner wall of the canister  20 , the missile  10  engaged to the obturator  80  cannot move in a rolling direction within the canister  20 . At the same time, the obturator  80  is also restrained not to move in the rolling direction, and thus the snatchers  83  of the obturator  80  are precisely engaged with the stop bars  73  of the ejection separators  70 . Further, with the missile  10  being almost released from the canister  20 , the obturator  80  mounted at the tail end of the missile  10  is separated from the missile  10  by the obturator separators  70 , and the V-shaped plate springs  74  at the front parts of the stop bars  73  are inserted into the receiving parts  83   a  of the snatchers and hung therein, thereby making the obturator  80  remain hung on the front part of the canister  20  without dropping down to the bottom of the canister  20 . Then, the missile  10  released from the canister  20  is launched toward a target by its propulsion engine. Meanwhile, in order to absorb or disperse a launching shock, it is preferred to perform launching with the rear cover  22  being contacted to the ground. The missile  10  is accelerated while passing through the canister  20 , and the missile  10  is released out of the canister  20  at the maximum speed the moment the missile  10  reaches to the front end of the canister  20 . 
   As the present invention may be embodied in various forms without departing from the spirit or essential characteristics thereof, it should also be understood that the above-described embodiment is not limited by any of the details of the foregoing description, unless otherwise specified, but rather should be construed broadly within its spirit and scope as defined in the appended claims, and therefore all changes and modifications that fall within the metes and bounds of the claims, or equivalents of such metes and bounds are therefore intended to be embraced by the appended claims. 
   As explained above, in accordance with the present invention, there is provided a missile ejection system which is able to effectively release a missile from a canister by employing a gas generator without using a missile propulsion engine, by having an obturator formed in a concavedly recessed curved shape toward the front part of the missile and forming an enclosed space between the obturator and a rear cover, thereby fundamentally preventing damage to ground equipment or peripheral missiles. 
   Furthermore, the system of the present invention may comprise one or more guides extending from the obturator for preventing control fins  18  of the missile from impacting the inner wall of the canister by making the guides slide along the inner wall of the canister during the traveling of the missile. Moreover, the canister of the missile ejection system in accordance with the present invention is made up of a combination of a plurality of tubes joined end-to-end, whereby it is made possible to manufacture the canister without using any heavy machine tools, a defect rate is lowered to reduce the manufacturing cost, and it becomes much easier to handle and assemble. 
   Furthermore, the system of the present invention may comprise one or more guide rails formed along the longitudinal direction in the canister for preventing the rolling motion of the missile upon launching of the missile, and one or more detents engaged to the rear end of the missile for longitudinally restraining the missile in the canister even under an external shock. Moreover, the system of the present invention may further comprise one or more immobilizers for transversely restraining the missile, whereby there occurs no relative motion between the missile and the canister even under an external vibration or shock before launching the missile. 
   Furthermore, the system of the present invention may comprise one or more obturator separators for preventing the obturator from being released from the canister, thereby being able to eliminate damage to ground objects which could occur in the event the obturator was released from the canister along with the missile and subsequently separated in the air by action of a missile propulsion engine. Further, the obturator is constructed in a manner so as not to be released from the canister but hung on the obturator separators, thereby being able to completely eliminate the possibility of damage to the canister which could occur in the event the obturator was separated and dropped down in a vertically raised canister.