DocumentCode :
2639213
Title :
Maximum crossrange for hypersonic boost-glide missile
Author :
Li, Yu ; Cui, Nai-Gang
Author_Institution :
Sch. of Astronaut., Harbin Inst. of Technol., Harbin
fYear :
2008
fDate :
10-12 Dec. 2008
Firstpage :
1
Lastpage :
6
Abstract :
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 4748.4 km.
Keywords :
missile guidance; optimal control; position control; quadratic programming; HBG missile design; aeroheating; hypersonic boost-glide missile; intercontinental guided weapon; maximum crossrange; multiconstraints multiphase trajectory optimization; nonlinear constraint; nonlinear programming; optimal control; sequential quadratic programming solver; Aerodynamics; Atmosphere; Design optimization; Dynamic programming; Missiles; Nose; Optimal control; Optimization methods; Quadratic programming; Weapons;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Systems and Control in Aerospace and Astronautics, 2008. ISSCAA 2008. 2nd International Symposium on
Conference_Location :
Shenzhen
Print_ISBN :
978-1-4244-3908-9
Electronic_ISBN :
978-1-4244-2386-6
Type :
conf
DOI :
10.1109/ISSCAA.2008.4776361
Filename :
4776361
Link To Document :
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