激光推进发射微小卫星弹道仿真与分析

Trajectory simulation and analysis for laser propulsion launching microsat

建立了初步的激光大气传输模型和光船的三维运动模型,通过对单站大气盘旋入轨模式下的推进弹道仿真分析可知,单站推进模式下激光在稠密大气层中行程较大,激光传输衰减严重。针对上述问题,以激光推进发射微小卫星为应用目标,提出了基于过顶接力和等光程接力两种方式下三站入轨的推进模式,给出并分析了相应的仿真结果,并利用等光程接力方式分析了激光推进发射微小卫星的运载能力。结果表明,三站等光程接力方式可以有效的解决激光传输问题,减小了激光在稠密大气层中的传输距离和激光的传输损失,提高入轨质量。

The laser atmosphere propagation model and three-dimensional model of lightcraft are proposed. The propulsion trajectory under single-station-circling-to-orbit mode is simulated, and the result shows that laser energy decays evidently due largely to long laser travel length in dense atmosphere. Under application target that launch Microsat using laser thruster, the three-station-relay-to-orbit modes with two different relay schemes are given and the trajectory simulation results are obtained, the ability of laser propulsion launching Microsat is studied. The results show laser that transmission problem can be resolved effectively and both, travel length and energy decays are reduced in dense atmosphere and final mass can also be increased under three-station-relay-to-orbit modes.