翼伞系统线目标归航方法

Line target homing method of parafoil system

针对运载火箭助推器或子级无控坠落地面落点散布较大的情况,提出一种翼伞系统的线目标归航方法。建立了矩形边界下的归航计算模型,对点目标归航和线目标归航两种方法进行了收缩区域分析;对翼伞归航能力、落区散布边界特征对归航性能的影响进行对比分析,得到了相应的归航策略,并提出在较大散布区域下设置多个着陆区域的工程解决方案;建立动力学和操纵控制模型,对线目标归航过程进行了仿真。结果表明,所提方法对工程有一定的参考价值。

Aimed to the large dispersion situation of the rocket booster or sub-stage falling to the ground without controlling , the line target homing method of parafoil system was put forward. The calculation model of rectangular boundary was established , and the contraction regional analysis of two kinds of homing methods namely point target and target line was performed. The influence of parafoil homing ability and the scattered boundary characteristics of falling area on homing performance were analyzed , and the corresponding homing strateg was obtained. A solution forseting up multiple landing areas in larger dispersion area was proposed. Finally , the dynamics and control model was establishhoming process was simulated. Satisfactory results are obtained , which shows that the proposed method has some reference value to the project.