一种基于推进剂消耗优化的卫星小推力器布局设计  

Satellite Thruster Configuration Design Based on Propellant Consumption Optimization

作　　者：彭磊[1] 刘莉[1] 龙腾[1] 郭晓松[1] 史人赫 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《宇航学报》2015年第3期268-277,共10页Journal of Astronautics

基　　金：国家自然科学基金(51105040;11372036);航空科学基金(2011ZA72003)

摘　　要：针对小推力器安装角度对卫星南北位置保持、东西位置保持和姿态控制效率的影响,从而决定推进剂需求量,提出一种推进剂消耗过程耦合建模与求解方法,并建立了小推力器安装角度优化模型。该方法采用定点迭代对转移轨道阶段推进剂消耗量和静止轨道阶段推进剂消耗量与贮箱尺寸之间耦合过程进行解耦,并建立了不同阶段推进剂消耗量估算模型。以卫星寿命期推进剂需求量最少为优化目标,建立了小推力器布局优化模型。通过实际的小推力器布局设计实例,分别采用遗传算法和序列径向基函数代理模型(SRBF)优化策略进行优化。优化结果表明相比于基于经验设计,SRBF可以有效地降低推进剂需求量,而且对比遗传算法,优化效率得到了显著提高。Considering the influence of installation angles of thrusters on the efficiency of north-south / east-west station keeping and attitude control,which determine the mass of required propellant,a modeling and calculational method is proposed for the coupled process of propellant consumption,and an optimization model is built for installation angles of small thrusters. In the proposed method,a fixed-point iterative method is used to decouple the coupled process between the required propellant at transfer orbit / geostationary orbit and the size of tank,and estimation models are built for the propellant consumption at different phases. Aiming to minimize the required propellant mass,a thruster configuration optimization model is built. Through a case for the practical thruster configuration design,Genetic Algorithm（ GA） and Sequential Radial Basis Function（ SRBF） surrogate model are applied respectively to deal with the optimization problem.The results demonstrate that SRBF effectively decreases the required propellant mass compared with the experience design,and distinctly improves the optimization efficiency compared with GA.

关 键 词：小推力器布局 推进剂优化 卫星设计优化 代理模型 

分 类 号：V423[航空宇航科学与技术—飞行器设计]