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Analysis on Delta-Vs to Maintain Extremely Low Altitude on the Moon and Its Application to CubeSat Mission

Journal of astronomy and space sciences, v.36 no.3, 2019년, pp.213 - 223  

Song, Young-Joo (Lunar Exploration Program Office, Korea Aerospace Research Institute) ,  Lee, Donghun (Lunar Exploration Program Office, Korea Aerospace Research Institute) ,  Kim, Young-Rok (Lunar Exploration Program Office, Korea Aerospace Research Institute) ,  Jin, Ho (School of Space Research, Kyung Hee University) ,  Choi, Young-Jun (Space Science Division, Korea Astronomy and Space Science Institute)

Abstract AI-Helper 아이콘AI-Helper

This paper analyzes delta-Vs to maintain an extremely low altitude on the Moon and investigates the possibilities of performing a CubeSat mission. To formulate the station-keeping (SK) problem at an extremely low altitude, current work has utilized real-flight performance proven software, the System...

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표/그림 (8)

AI 본문요약
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제안 방법

  • A total of eight different extremely low reference orbit sets for a circular polar orbit around the Moon, having four different reference altitudes above the mean lunar surface (20, 30, 40, and 50 km) and two different deadband sets (±5 and ±10 km) were applied to each of them for the simulation.
  • As the current work considered very low altitude ranges on the Moon, the resultant orbits may be considerably affected by the nonspherical harmonics of the Moon. Among the eight different sets of candidate reference orbits, the lowest reference altitude condition was selected and analyzed for the effects of the different degree and order of nonspherical harmonics of the Moon on the SK strategy.
  • A total of eight different extremely low reference orbit sets for a circular polar orbit around the Moon, having four different reference altitudes above the mean lunar surface (20, 30, 40, and 50 km) and two different deadband sets (±5 and ±10 km) were applied to each of them for the simulation. As a result, characteristics of the SK maneuvers were successfully analyzed together with the effect of the selection of the degree and order of the lunar gravitational harmonics on the overall SK maneuver strategy. As expected, a considerable magnitude of delta-Vs, as well as the SK maneuver execution time were affected by these different selections.
  • Based on the delta-V results obtained together with the performance of a miniaturized propulsion system currently available, this subsection studies the feasibilities of maintaining such an extremely low altitude using a CubeSat. Due to the extensively growing interest in CubeSat applications, several propulsion systems have been rapidly developed with enhanced performance for use with CubeSats.
  • 30 m/s for the ±10 km deadband case. Based on the derived overall SK maneuver delta-Vs cost, the possibilities of performing a CubeSat mission were additionally analyzed with application of the current flightproven miniaturized propulsion system performances. It is concluded that a ~15 kg class CubeSat could maintain an orbit (30–50 km reference altitude having ±10 km deadband limits) around the Moon from 1–6 months.
  • Firstly, using a high-fidelity force model, the required SK maneuver delta-Vs for maintaining an extremely low lunar altitude are obtained. Based on the derived overall SK maneuver deltaVs cost, the possibilities of performing a CubeSat mission are analyzed by applying the current flight-proven miniaturized propulsion system performances. The remainder of this manuscript is organized as follows: A detailed targeting problem formulation using System Tool Kit (STK) Astrogator to maintain the nominal altitude, with given deadband limits, is explained in Section 2.
  • For root-finding, the Secant method was applied with the forward difference derivative calculation method. Finally, all maneuvers were assumed to be impulsive maneuvers to maintain the reference orbit within the deadband limit, and only the velocity component of the maneuver was controlled among the three components of the maneuver expressed in the velocity-normal-conormal (VNC) reference frame, as to focus on a preliminary analysis. In the VNC frame, it should be noted that the unit x-axis is defined as along the velocity vector, the unit y-axis is along the orbit normal, and the unit z-axis completes the orthogonal triad.
  • The main focus of the current work is to perform an early phase feasibility analysis of a CubeSat mission, particularly flying at an extremely low altitude on the Moon. Firstly, using a high-fidelity force model, the required SK maneuver delta-Vs for maintaining an extremely low lunar altitude are obtained.
  • The target sequence provides Astrogator with a powerful capability to solve very complex space flight dynamics by defining the maneuver and propagation components inside to achieve the final design goals. With high-fidelity force models (the detailed setup of which will be explained in the following subsection), three different OR logical stopping conditions were given to trigger the following sequential event inside the MCS.

대상 데이터

  • For each reference orbit, two different deadband sets (±5 and ±10 km) were considered; therefore, a total of 8 different reference orbit sets were considered for the simulation.

이론/모형

  • Within this algorithm, the maximum iteration limit for a single run was set as 100, with convergence criteria of the equality conditions within the tolerance. For root-finding, the Secant method was applied with the forward difference derivative calculation method. Finally, all maneuvers were assumed to be impulsive maneuvers to maintain the reference orbit within the deadband limit, and only the velocity component of the maneuver was controlled among the three components of the maneuver expressed in the velocity-normal-conormal (VNC) reference frame, as to focus on a preliminary analysis.
  • The associated SK problem at this low altitude was formulated using the STK Astrogator module by AGI, which has been used to design and operate many real flight missions. The targeting problem for the SK maneuvers was formulated by establishing a MCS with high-fidelity force model. A total of eight different extremely low reference orbit sets for a circular polar orbit around the Moon, having four different reference altitudes above the mean lunar surface (20, 30, 40, and 50 km) and two different deadband sets (±5 and ±10 km) were applied to each of them for the simulation.
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