Patent ID: 8028625

Claim:
A missile separation device, comprising: a locking unit configured to fix a propulsion system to a missile; a string disposed to cross a rear portion of the propulsion system, configured to be cut off by heat of the propulsion system; and an unlocking unit configured to unlock the missile when the string is cut off, wherein the locking unit comprises: a missile fixing frame formed at a rear portion of the missile; a propulsion system fixing frame formed at the propulsion system; a fixing pin disposed to be perpendicular to the string, configured to couple the missile fixing frame to the propulsion system fixing frame; and a first spring supported between the missile and the propulsion system and disposed to apply an elastic force to a direction to unlock the propulsion system, wherein the unlocking unit comprises: a release latch having one side connected to the string, and installed to orbit with respect to the missile such that the fixing pin is slipped out of the pin holes when the string is cut off; and a second spring supported between the missile and the release latch, and configured to apply an elastic force to the release latch in the direction to separate the fixing pin, wherein the missile fixing frame and the propulsion system fixing frame are configured to be overlapped with each other, and pin holes, in which the fixing pin is inserted, are formed respectively in the corresponding overlapped sections between the missile fixing frame and the propulsion system fixing frame.