DEVELOPMENT OF THE FILAMENT WOUND COMPOSITE MOTORCASE FOR THE COMPACT KINETIC ENERGY MISSILE

摘要

The Compact Kinetic Energy Missile (CKEM) is a technology demonstration program being conducted by the U.S. Army Aviation and Missile Command (AMCOM) as part of the Army After Next (AAN) and Future Combat System (FCS) initiatives. The objective of the CKEM program is to develop and demonstrate a guided hypervelocity missile system that is soft launched from a fixed launcher and is capable of providing high lethality against armored ground vehicles. The CKEM, as presently configured, consists of a composite motorcase with a permanently affixed penetrator that is embedded in and along a major portion of the motor chamber length. The primary design constraint is the desire to deliver 8.8X10~6 ft-lbf(12 MJ) of penetrator kinetic energy at a range of 13123 ft (4 km) while maintaining sufficient control authority for engaging targets at a range of 1312 ft (400 m). The propulsion system selected to meet these requirements consists of a non-discardable motor that operates with a boost-coast thrust profile. Additionally, the motorcase must have a high propellant weight fraction (PWF) in order to place the propulsion unit energy into lethal mechanism energy as opposed to carrying parasitic motor weight. This paper will present the CKEM filament wound composite motorcase design methodology and unique fabrication techniques, as well as hydroburst and motor static test data.