The Optimization of Electric Propulsion Mission in the Earth-Moon System

Materova Irina ; Starinova Olga

doi:10.4156/jmmt.vol1.issue1.2

Angular motion control of electric propulsion spacecraft transfers between L1 and L2 libration points of the Earth-Moon system

10.1063/1.5081548 ◽

2018 ◽

Author(s):

Maksim Fain ◽

Olga Starinova ◽

Irina Chernyakina

Keyword(s):

Motion Control ◽

Electric Propulsion ◽

Libration Points ◽

Angular Motion ◽

Moon System ◽

The Earth ◽

L1 And L2

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Destiny+ Dust Analyzer – Campaign & timeline preparation for interplanetary & interstellar dust observation during the 4-year transfer phase from Earth to Phaethon

10.5194/epsc2020-342 ◽

2020 ◽

Author(s):

Maximilian Sommer ◽

Harald Krüger ◽

Ralf Srama ◽

Takayuki Hirai ◽

Masanori Kobayashi ◽

...

Keyword(s):

Electric Propulsion ◽

Interstellar Dust ◽

Impact Ionization ◽

Interplanetary Space ◽

Dust Cloud ◽

Dust Particles ◽

Transfer Phase ◽

Moon System ◽

The Earth ◽

The Impact

The Destiny+ mission (Demonstration and Experiment of Space Technology for Interplanetary voyage Phaethon fLyby and dUst Science) has been selected as part of its M-class Space Science Program by the Japanese space agency JAXA/ISAS and is set to launch in 2023/2024. The mission target is the active asteroid (3200) Phaethon with a projected flyby in early 2028. The scientific payload consists of two cameras (the Telescopic Camera for Phaethon, TCAP, and the Multi-band Camera for Phaethon, MCAP), and the Destiny+ Dust Analyzer (DDA). DDA is the technological successor to the Cosmic Dust Analyzer (CDA) aboard Cassini-Huygens, which prominently investigated the dust environment of the Saturnian system. The DDA sensor is designed as a combination of impact ionization time-of-flight mass spectrometer and trajectory sensor, which will allow for the analysis of sub-micron and micron sized dust particles with respect to their composition (mass resolution m/&#916;m &#8776; 100-150), mass, electrical charge, velocity (about 10% accuracy), and impact direction (about 10&#176; accuracy). Besides attempting to sample the impact-generated dust cloud around Phaethon during the flyby, DDA will be actively observing the interplanetary & interstellar dust environment over the roughly four years spanning cruise phase from the Earth-Moon system through interplanetary space. After launch into a GTO-like orbit, Destiny+ will first employ its solar-electric propulsion system to spiral up to the lunar orbit within about 18 months, followed by a series of lunar swingbys and interim coasting phases in distant cislunar space, accumulating momentum to leave the Earth-Moon system at high excess velocity. The subsequent roughly 2-year interplanetary transfer to intercept Phaethon will be characterized by moderate orbital eccentricity of up to 0.1 and largely unpowered coasting phases. During these four years, the DDA sensor will benefit from a maximum pointing coverage range enabled by its dual-axis pointing mechanism and spacecraft attitude flexibility (during times of unpowered flight). This will allow for exhaustive mapping and analysis of the different interplanetary dust populations, as well as interstellar dust encountered in the region between 0.9-1.1 AU. Here, we give a progress report on the science planning efforts for the 4-year transfer phase. We present a tentative observation timeline that assigns scientific campaigns to different phases of the mission, taking into account results of various dust models, as well as operational and technical constraints.

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Motion Control of Electric Propulsion Spacecraft Transfers between the Libration Points L1 and L2 of the Earth–Moon System

Proceedings of Higher Educational Institutions Маchine Building ◽

10.18698/0536-1044-2019-11-66-74 ◽

2019 ◽

pp. 66-74

Author(s):

M.K. Fain ◽

O.L. Starinova

Keyword(s):

Electric Propulsion ◽

Optimal Solution ◽

Libration Points ◽

Coordinate Frame ◽

Control Laws ◽

Moon System ◽

The Earth ◽

Nonlinear Motion ◽

Sequential Linearization ◽

L1 And L2

This article presents a study of nonlinear motion of an electric propulsion spacecraft. Spacecraft transfers between the libration points L1 and L2 of the Earth-Moon system are analyzed. The influence of the shaded areas and gravitational effects of the Earth, the Moon and the Sun is taken into account. The mathematical model of the transfers is described within the barycentric coordinate frame. The exact optimal solution of the problem is obtained using Pontryagin’s maximum principle formalism and the numerical solution of the boundary value problem. The method of optimizing the parameters and controls of interplanetary trajectories of the spacecraft based on the optimization of dynamic system components and on Fedorenko’s method of sequential linearization is applied in this study. This method allows limitations on composite functions with Fréchet derivatives. As the results of the simulation, the control laws and corresponding trajectories are obtained.

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Halo-orbit formation in the Earth-Moon system by the electric propulsion spacecraft

10.1063/1.5081579 ◽

2018 ◽

Author(s):

Olga Starinova ◽

Vyacheslav Kupczov ◽

Changsheng Gao ◽

Yudon Hu ◽

Maksim Fain ◽

...

Keyword(s):

Electric Propulsion ◽

Halo Orbit ◽

Moon System ◽

The Earth

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Rendez vous with Saturn's rings

International Astronomical Union Colloquium ◽

10.1017/s0252921100101885 ◽

1984 ◽

Vol 75 ◽

pp. 743-759 ◽

Cited By ~ 2

Author(s):

Kerry T. Nock

Keyword(s):

Solar Energy ◽

Electric Propulsion ◽

Power Source ◽

Propulsion System ◽

Low Thrust ◽

Ring Plane ◽

The Earth ◽

Total Impulse ◽

Saturn's Rings

ABSTRACTA mission to rendezvous with the rings of Saturn is studied with regard to science rationale and instrumentation and engineering feasibility and design. Future detailedin situexploration of the rings of Saturn will require spacecraft systems with enormous propulsive capability. NASA is currently studying the critical technologies for just such a system, called Nuclear Electric Propulsion (NEP). Electric propulsion is the only technology which can effectively provide the required total impulse for this demanding mission. Furthermore, the power source must be nuclear because the solar energy reaching Saturn is only 1% of that at the Earth. An important aspect of this mission is the ability of the low thrust propulsion system to continuously boost the spacecraft above the ring plane as it spirals in toward Saturn, thus enabling scientific measurements of ring particles from only a few kilometers.

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