Low-Thrust Trajectory Optimization for Cubesat Lunar Mission: HORYU-VI
A 12U CubeSat uses four Hall-effect thrusters to achieve lunar capture in 200 days, verified by NASA's GMAT tool.
Deep Dive
A research team led by Omer Burak Iskender presents a trajectory optimization strategy for the HORYU-VI CubeSat. The 12U satellite, a secondary payload on NASA's SLS, uses four Hall-effect thrusters. Their Sequential Quadratic Programming (SQP) method plots a three-phase journey, achieving lunar capture in 200 days and a stable 100 km science orbit by day 450 using only 710 m/s of Delta-V, verified with NASA's General Mission Analysis Tool (GMAT).
Why It Matters
Demonstrates a viable, low-cost path for small satellites to conduct complex deep-space missions, expanding access to lunar science.