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7th International Conference on Astrodynamics Tools and Techniques (ICATT)

6–9 Nov 2018
DLR Oberpfaffenhofen, Germany
Europe/Amsterdam timezone

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Session

Low Thrust #3

9 Nov 2018, 13:00
103 and 105 combined

103 and 105 combined

Building 135

Conveners

Low Thrust #3

  • Lale Evrim Briese (German Aerospace Center (DLR))
  • Christina Jetzschmann (Airbus DS Bremen)
  • Juan Carlos Bastante (OHB System AG)

Presentation materials

There are no materials yet.

  1. 72. Efficient design of low lunar orbits based on Kaula recursions
    Dr Martin Lara (GRUCACI - University of La Rioja)
    09/11/2018, 13:00
    03: Low Thrust
    Oral presentation at the conference

    Preliminary design of artificial satellite missions commonly relays on the use of simplified models that comprise the bulk of the dynamics. In the case of the gravitational potential, the amplitude of long-term oscillations of the orbital parameters is roughly one order of magnitude larger than the short-period oscillations. Because of that, dealing with just the few more relevant zonal...

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  2. 8. MOLTO-OR: A Multi-Objective Low-Thrust Optimization Tool for Orbit Raising
    DAVID MORANTE (Universidad Carlos III ( Madrid ))
    09/11/2018, 13:30
    03: Low Thrust
    Oral presentation at the conference

    Commercial and scientific satellites located in Geostationary Equatorial Orbit (GEO) that are not placed there by the launch vehicle are often injected in a parking orbit. They are transferred therefrom to GEO using their own on-board propulsion system. The classical strategy relies either on Chemical Propulsion (CP) or Electrical Propulsion (EP). The former guarantees very short transfer...

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  3. 9. MOLTO-IT: A Multi-Objective Low-Thrust Optimization Tool for Interplanetary Trajectories
    DAVID MORANTE (Universidad Carlos III ( Madrid ))
    09/11/2018, 14:00
    03: Low Thrust
    Oral presentation at the conference

    Low-thrust propulsion and gravity assists maneuvers are both well known to provide sig- nificant benefits in terms of required propellant mass for interplanetary trajectories. However, the propellant reduction achieved with low-thrust engines, when compared to their chemical counterparts, comes at the cost of a higher transfer time.
    Therefore, the design and optimization of interplanetary...

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  4. 69. MARS SAMPLE RETURN: MISSION ANALYSIS FOR AN ESA EARTH RETURN ORBITER
    Eric Joffre (Airbus Defence and Space)
    09/11/2018, 14:30
    03: Low Thrust
    Oral presentation at the conference

    Bi-lateral discussions between NASA and the European
    Space Agency identified the orbiter element as a promising
    European-led contribution to a future international Mars Sample
    Return campaign. Airbus recently completed the Mars
    Sample Return Architecture Assessment Study on behalf of
    ESA, with the objective to identify and quantify candidate
    mission architectures. The paper describes the...

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  5. 34. Automated optimization of low-thrust trajectories
    Alexey Ivanyukhin (Research Institute of Applied Mechanics and Electrodynamics of the Moscow Aviation Institute (RIAME MAI)), Dr Vyacheslav Petukhov (Research Institute of Applied Mechanics and Electrodynamics of Moscow Aviation Institute)
    03: Low Thrust
    Oral presentation at the conference

    Modern space missions often require a large velocity increment, which leads to the need to use main electric propulsion systems with a high value of the specific impulse to reduce the mass of the active propellant and increase the mass of spacecraft in target orbits.
    To improve the efficiency of space transportation operations, optimization of the low-thrust trajectories is required....

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