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This paper describes the development of the dual-thrust flight motor for enhancing the hit probability of unguided rockets. We designed dual-thrust flight motor by shape modification of the double base propellant with high burning rate, and confirmed the dual-thrust performance by static firing tests. The test results showed the thrust ratio of about 1:7.6 between sustaining phase and boosting phase, and had a quitely normal dual-thrust characteri stics. And the results showed that there was not the fire extinction phenomenon of propellant due to the pressure drop.             .           ,      .         1:7.6    ,      . Key Words: Dual Thrust(), Double Base Propellant( ), Boosting Phase( ), Sustaining Phase( )Received 11 December 2013 / Revised 2 July 2014 / Accepted 10 J uly 2014

A Study on Development of the Dual-thrust Flight Motor for Enhancing the Hit Probability