Patent Abstract:
A lateral support device system of a canister-launched missile of the present invention is provided for eliminating the clearances between missile and the canister in 4 places by 90 degrees interval, and therefore no relative movement occurs between the missile and the canister. Therefore, the missile and the detent is free from shocks and vibrations that occurs during the handling, transportation and operation. In addition, when the missile is fired, those lateral lock become free with a little energy loss.

Full Description:
BACKGROUND OF THE INVENTION 
   1. Field of the Invention 
   The present invention relates to a lateral support device system for canister-launched missile, more particularly, to a lateral support device system of a canister-launched missile for removing the clearance between a missile and a canister thereby inducing no relative movement therebetween. 
   2. Description of the Related Art 
   For all the lateral support device system for canister-launched missile developed up to the present, there always exist some clearances between the inner surface of the canister and the outer surface of missile. Therefore, some lateral movement of the missile relative to the canister occurs during the handling, transportation and operation, and the lateral movement causes the harmful effects on the missile and the missile detent. 
   Sabots are installed on an outer circumferential surface of the missile so that they can support the missile when the missile is insertedly installed and operated in the canister, and guide the missile within the canister when the missile is launched from the canister. The sabots allow a gap between the missile and the canister in order to prevent the missile from being caught in the canister when it is moved therein. In this respect, however, the gap causes vibrations and shocks of the missile within the canister when the missile is transported, handled and operated, and thus, resulting in a breakdown of the missile. 
   BRIEF DESCRIPTION OF THE INVENTION 
   Therefore, one object of the present invention is to provide a canister-launched missile capable of restraining a relative lateral movement of a missile within a canister when the canister-launched missile is being transported or handled and releasing the missile with negligible resistance force when it is launched. 
   To achieve these and other advantages and in accordance with the purpose of the present invention, as embodied and broadly described herein, there is provided a lateral support device system for a canister-launched missile comprising: sabots separably formed on an outer circumferential surface of a missile; travel lock bar which is integrally fixed to the sabots; and travel lock bolt fixed at the canister and selectively pressing the upper end of the travel lock bar. 
   Herein, a groove is formed on the upper surface of the sabots in the direction of the missile launching, and the travel lock bar is fixed to the sabot so that the upper end of the travel lock bar is located below the upper surface of the sabots. 
   The lateral support device system further comprises: a position adjustment pin fixed at the bottom surface of the sabot so as to be inserted in a position adjustment recess formed on the outer circumferential surface of the missile, and a spring installed and compressed inside the sabot and allowing the position adjustment pin to be pressed and inserted in the position adjustment recess of the missile. 
   The lateral support device system further including a spring seat having a convex portion at one end for accommodating one end of the spring and having a portion at the other end for fixing the a position adjustment pin. 
   A load support plate is formed between the bottom surface of the sabot and the outer circumferential surface of the missile, so that when the travel lock bolt presses the sabot, the load support plate contacts with the outer circumferential surface of the missile. 
   A plurality of sabots and a plurality of travel lock bolts are formed at certain intervals on the outer circumferential surface of the missile. 
   On the other hand, the present invention provides a lateral support device system for a canister-launched missile comprising: sabots formed on an outer circumferential surface of a missile; travel lock bar which is integrally fixed to the sabots; and travel lock bolt fixed at the canister and selectively pressing the upper surface of the sabots. 
   The foregoing and other objects, features, aspects and advantages of the present invention will become more apparent from the following detailed description of the present invention when taken in conjunction with the accompanying drawings. 

   
     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 side perspective view of a canister-launched missile including a lateral support device system in accordance with the present invention; 
       FIG. 2  is a sectional view taken along line II-II of  FIG. 1 ; and 
       FIG. 3  is a perspective view showing the shape that the construction of  FIG. 2  is mounted in the missile. 
   

   DETAILED DESCRIPTION OF THE INVENTION 
   The present invention will now be described in detail with reference to the accompanying drawings. 
   In describing the present invention, detailed descriptions with respect to a known function or construction will be omitted to make the gist of the present invention clear. The construction of the lateral support device system  100  in accordance with the present invention will be described in detail. 
   The lateral support device system  100  includes sabots  110  protruded from the side of an outer circumference of the missile  10 ; a travel lock bar  120  formed inside the sabot  110 ; a load support plate  130  formed to cover the circumference of the bottom of the sabot  110  and contacting with the outer circumferential surface of the missile  10  when a certain load is applied to the sabot  110 ; a position adjustment pin  140  is fixed to the spring seat  150  and inserted in a position adjustment recess  10   a  formed on an outer circumferential surface of the missile  10 ; a spring seat  150  for receiving a portion of the position adjustment pin  140  at one end thereof; a spring  160  installed to be compressed between a receiving portion formed at the other end of the spring seat  150  and an inner surface of the sabot  110 ; a travel lock bolt  170  installed to press the upper end of the travel lock bar  120  of the sabot  110  with a certain load; and a lock bolt fixture  180  for fixing the travel lock bolt  170  and helping transfer of the travel took bolt  170 . 
   The sabot  110  is formed as a sabot body  111  with a hollow portion formed therein, and installed not to be fixed on the outer circumferential surface of the missile  10  but to contact therewith. 
   When the travel lock bolt  170  is fixed at the lock bolt fixture  180  and transferred in the direction of the missile  10  to press the front end of the travel lock bar  120  of the sabot  110 , the load support plate  130  is pressed by the bottom of the circumference of the sabot body  111  and tightly attached with the outer circumferential surface of the missile  10 . 
   The position adjustment pin  140  has thread on one end and is fastened to the other end of the spring seat  150 . And the other end of the position adjustment pin  140  inserted in the position adjustment recess  10   a  of the missile  10 , rather than being fastened in the recess. Therefore, although the depth of the recess is different from other one, as the position adjustment pin is fixed to the spring seat  150 , the position adjustment pin  140  can be inserted into the recess with the constant depth. 
   One end of the spring seat  150  includes a convex portion for accommodating the one end of the spring  160  and a receiving portion for fixing the position adjustment pin  140 . 
   A contact surface  190  of the travel lock bolt  170  pressed by a certain force contacts with a front end of the travel lock bar  120  of the sabot  110 , which is not fixed at the travel lock bar  120 . Accordingly, as the missile  10  is launched in the canister  20 , the frictional restriction condition between the travel lock bolt  170  and the travel lock bar  120  is smoothly released. 
   Accordingly, when the missile  10  is launched by force overcoming the frictional force between the travel lock bolt  170  and the travel lock bar  120 , the constraint according to the frictional force between the travel lock bolt  170  and the travel lock bar  120  is naturally released according to the launching thrust of the missile  10 . 
   The lock bolt fixture  180  includes a fixing portion  181  having a screw thread formed at the center thereof and fastened with the outer circumferential surface of the canister  20  with a fixing bolt  181   a , an adjusting portion  182  having a protrusion to be inserted into a polygonal recess formed on a front end of the travel lock bolt  170 , and a position fixing bolt  183  for rotating the travel lock bolt  170  by using the adjusting portion  182  and fastening the adjusting portion  182  and the fixing portion  181 . 
   As shown in  FIG. 3 , the lateral support device system  100  is formed at four positions by 90° intervals on the outer circumferential surface of the missile  10  and protects the missile  10  such that when the missile  10  mounted within the canister  20  is moved (fluctuated) in the lateral direction when being handled, transported and operated, a relative movement between the canister  20  and the missile  10  may not occur. 
   Namely, in order not to allow formation of a gap between the outer circumferential surface of the sabot  110  and the inner surface of the canister  20 , the travel lock bolt  170  is installed at the lock bolt fixture  180 , which is fastened to strongly press the travel lock bar  120  provided at the center of the sabot  110  to make the load support plate  140  contact with the outer circumferential surface of the missile  10 . 
   The sabots  110  are supportedly installed at the outer circumferential surface of the missile  10  at 90° intervals not to allow formation of a gap between the canister  20  and the missile  10  before the missile is launched. When the missile  10  starts to be launched, the missile  10  caught by the sabots  110  by means of the position adjustment pin  140  proceeds together with the sabots  110  within the canister  20 , overcoming the frictional force generated by a load in an axial direction between the travel lock bolt  170  and the travel lock bar  120 . Then, the contact state between the travel lock bolt  170  and the travel lock bar  120  is released, and accordingly, the outer circumferential surface of the sabot body  111  is slid in a state of contacting with the inner surface of the canister  20  by virtue of the spring  160  and the spring seat  150 . At the moment the missile  10  blasts off after being highly accelerated within the canister  20 , the sabots  110  scatter in all directions by a restoration force of the compressed spring  160 . 
   As stated above, the scope of the present invention is not limited to the above-described specific embodiment of the present invention but can be modified suitably within the coverage of the claims. For example, without installing an travel lock bar  120  in the sabots, the travel lock bolt can contact directly with the upper surface of the sabot so as to remove the clearance between the missile and the canister. 
   As so far described, a lateral support device system of a canister-launched missile in accordance with the present invention has the following advantages. 
   That is, by installing sabots separably formed on the outer circumferential surface of the missile and the travel lock bolt fixed at the canister and selectively pressing a front end surface of the sabots so as to contact with the sabots, with the missile placed inside the canister before being launched, no gap is formed between the canister and the missile even without an additional protrusion or unit, so that an impact that may be applied to the missile can be restrained to the maximum and thus the missile can be stably fixed in the lateral direction. 
   Moreover, after the missile is launched from the canister, the sabots can be automatically separated from the missile without using an additional unit. 
   As the present invention may be embodied in several forms without departing from the spirit or essential characteristics thereof, it should also be understood that the above-described embodiments are 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, to and therefore all changes and modifications that fall within the metes and bounds of the claims, or equivalence of such metes and bounds are therefore intended to be embraced by the appended claims.

Technology Classification (CPC): 5