摘要
巨大的小卫星发射市场吸引着国内外竞相研制低成本的固体小型运载火箭。通常的运载火箭是液体,但固体不象液体,其推力大小取决于装药设计,因此不可控,且推力实际值与标称值的偏差也较大,如果发射条件受限制,要约束重量,通常固体火箭耗尽关机,三级也可能自旋稳定,由此带来了制导技术的问题。研究工作较有效地探索了一种固体小运载的制导方案设计问题,进行了算例仿真,作了精度和稳定性的验证研究,结果表明该制导方法可行,稳定性较好,对固体发射小卫星的制导有一定的参考意义。
The huge market of launching small satellite drives the solid launching vehicle to be researched and explored at home and abroad. Unlike liquid vehicle, the thrust of solid vehicle can not be controlled, and the variation is large because of environment. In addition, the propellant exhausting shut off is adopted to decrease the weight of rocket, and these factors become the main barriers of guidance design for solid launching vehicle. The problem is eliminated by putting forward a new efficient iterative method for the guidance design of solid launching vehicle, takes an example to simulate, and the numerical results show that the guidance design is not only feasible but also stable, and it is useful to launch small satellite for the guidance of solid vehicle.
出处
《系统仿真学报》
EI
CAS
CSCD
北大核心
2005年第11期2734-2736,2744,共4页
Journal of System Simulation
关键词
固体小运载
制导
弹道仿真
飞行控制
solid vehicle
guidance and control
ballistic simulation
flight control
