Session
Session 3: Next On The Pad 1
Abstract
OMOTENASHI (Outstanding MOon exploration TEchnologies demonstrated by Nano Semi-Hard Impactor) is a JAXA 6U cubesat that aims to perform a semi-hard landing at the Moon surface after being deployed into a lunar fly-by orbit by the American Space Launch System, Exploration Mission-1. In this paper, we present the analysis and design of OMOTENASHI trajectory, divided in a Earth-Moon transfer using a cold gas thruster and a landing phase using a solid rocket motor. Strong constrains exists between the two phases, making the mission design a very challenging task. The flight path angle at Moon arrival must be shallow in order to minimize the effect of delays at the deceleration maneuver. This, together with the execution error of the cold gas maneuver, demands a correction maneuver after the first one to compensate for these errors. Requirements on the ground station tracking are also deduced from this analysis. Under the current subsystems design, we found that the most critical factors in the landing success rate are the maneuver orientation, thrust duration and total delta-v errors. Results suggest accuracy requirements to the landing devices, solid rocket motor and attitude accuracy, as well as to the transfer phase trajectory design.
Presentation
Trajectory Design for the JAXA Moon Nano-Lander OMOTENASHI
OMOTENASHI (Outstanding MOon exploration TEchnologies demonstrated by Nano Semi-Hard Impactor) is a JAXA 6U cubesat that aims to perform a semi-hard landing at the Moon surface after being deployed into a lunar fly-by orbit by the American Space Launch System, Exploration Mission-1. In this paper, we present the analysis and design of OMOTENASHI trajectory, divided in a Earth-Moon transfer using a cold gas thruster and a landing phase using a solid rocket motor. Strong constrains exists between the two phases, making the mission design a very challenging task. The flight path angle at Moon arrival must be shallow in order to minimize the effect of delays at the deceleration maneuver. This, together with the execution error of the cold gas maneuver, demands a correction maneuver after the first one to compensate for these errors. Requirements on the ground station tracking are also deduced from this analysis. Under the current subsystems design, we found that the most critical factors in the landing success rate are the maneuver orientation, thrust duration and total delta-v errors. Results suggest accuracy requirements to the landing devices, solid rocket motor and attitude accuracy, as well as to the transfer phase trajectory design.
