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6th International Conference on Astrodynamics Tools and Techniques (ICATT)

14–17 Mar 2016
Darmstadtium
Europe/Amsterdam timezone
"Orbiting Towards the Future"

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Session

Loitering / Orbiting (I)

15 Mar 2016, 08:20
Darmstadtium

Darmstadtium

Schloßgraben 1, 64283 Darmstadt, Germany

Description

Low Earth Orbits (LEO), Medium Earth Orbits (MEO), High Earth Orbits (HEO), Geostationary Orbits (GEO); station-keeping; optimization of loitering arcs; computation of drag-free orbits; circular and elliptical orbits around planets and Moons; resonant orbits and fuel efficient trajectories

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  1. 39. An efficient code to solve the Kepler equation for elliptic and hyperbolic orbits
    Ms Virginia Raposo Pulido (SDG-UPM)
    15/03/2016, 08:20
    02: Loitering / Orbiting
    Oral presentation at the conference
    The Kepler equation for the elliptical motion, *y − e* sin *y* − *x* = $0$, involves a nonlinear function depending on three parameters: the eccentric anomaly *y* = E, the eccentricity e and the mean anomaly *x* = M. For given e and x values the numerical solution of the Kepler equation becomes one of the goals of orbit propagation to provide the position of the object orbiting around a...
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  2. 16. A fast and efficient algorithm for onboard LEO intermediary propagation
    Dr Martin Lara (Space Dynamics Group, Polytechnic University of Madrid, and GRUCACI, University of La Rioja)
    15/03/2016, 08:40
    02: Loitering / Orbiting
    Oral presentation at the conference
    Usual onboard orbit propagators are provided as navigation maintenance aids for earth orbiting satellites. These programs should be able to forecast satellite ephemeris within a reasonable accuracy for short time periods, which may range from minutes, as in the case of momentary lack of GPS signal, to several satellite orbits. In these brief intervals the accumulation of second order effects...
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  3. 21. SIRIUS-DV: The new Flight Dynamics algorithms for the future CNES missions
    Mr IVÁN LLAMAS (GMV)
    15/03/2016, 09:00
    02: Loitering / Orbiting
    Oral presentation at the conference
    The SIRIUS project aims to develop a set of Flight Dynamics products that will be used operationally in the control centers of the upcoming CNES missions. It mainly covers three different layers: the mathematical low level libraries (PATRIUS), intended to be used either in an operational environment or in expert studies; the flight dynamics algorithms, implementing the operational...
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  4. 151. A semi-analytical orbit propagator program for Highly Elliptical Orbits
    Dr Juan Félix San-Juan (Scientific Computing Group (GRUCACI), University of La Rioja)
    15/03/2016, 09:20
    02: Loitering / Orbiting
    Oral presentation at the conference
    A semi-analytical orbit propagator to study the long-term evolution of spacecraft in Highly Elliptical Orbits is presented. The perturbation model taken into account includes the gravitational effects produced by the first nine zonal harmonics and the main tesseral harmonics affecting to the 2:1 resonance, which has an impact on Molniya orbit-types, of Earth’s gravitational potential, the...
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  5. 17. DESEO Design Engineering Suite for Earth Observation
    Mr Federico Letterio (Deimos Space)
    15/03/2016, 09:40
    02: Loitering / Orbiting
    Oral presentation at the conference
    The Design Engineering Suite for Earth Observation (DESEO) is a software toolkit to support mission analysis and preliminary system/subsystem design activities for all phases of Earth observation missions. DESEO has been designed to be used by mission and system engineers throughout all phases of an Earth Observation mission (from Phase 0 to Phase E), whenever they need accurate and fast...
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