Maximum Crossrange for Hypersonic Boost-Glide Missile
Hypersonic Boost-Glide Missile is a new intercontinental guided weapon intends to fly along an optimized trajectory. Its glide warhead with sharp nose needs to endure long-time serious aeroheating to long-range glide in atmosphere. The trajectory optimization problem is an important aspect for HBG missile design. The trajectory optimization problem is characterized by a boost phase followed by a glide phase. A multi-constraints multi-phase trajectory optimization method is adopted to optimize the crossrange, under near-real condition. The associated optimal control problem has been solved by selecting a direct method approach. The dynamics has been transcribed to a set of nonlinear constraints and the arising nonlinear programming problem has been solved through a sequential quadratic programming solver. Numerical results represent the optimal trajectory solved is a combined boost-glide-dive trajectory, and the crossrange can attain 4748.4km.
Yu Li Nai-gang Cui
School of Astronautics,Harbin Institute of Technology,Harbin,150001,China
国际会议
深圳
英文
1240-1245
2008-12-10（万方平台首次上网日期，不代表论文的发表时间）