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Roman Ya. Kezerashvili - One of the best experts on this subject based on the ideXlab platform.

  • Extrasolar space exploration by a solar sail accelerated via thermal desorption of coating
    Advances in Space Research, 2019
    Co-Authors: Elena Ancona, Roman Ya. Kezerashvili
    Abstract:

    Abstract For extrasolar space exploration it might be very convenient to take advantage of space environmental effects such as solar radiation heating to accelerate a solar sail coated by materials that undergo thermal desorption at a particular temperature. Thermal desorption can provide additional thrust as heating liberates atoms, embedded on the surface of the solar sail. We are considering orbital dynamics of a solar sail coated with materials that undergo thermal desorption at a specific temperature, as a result of heating by solar radiation at a particular heliocentric distance, and focus on two scenarios that only differ in the way the sail approaches the Sun. For each scenario once the perihelion is reached, the sail coat undergoes thermal desorption. When the desorption process ends, the sail then escapes the Solar System having the conventional acceleration due to solar radiation pressure. We study the dependence of a cruise speed of a solar sail on perihelion of the orbit where the solar sail is deployed. The following scenarios are considered and analyzed: (1) Hohmann Transfer plus thermal desorption. In this scenario the sail would be carried as a payload to the perihelion with a conventional propulsion system by a Hohmann Transfer from Earth’s orbit to an orbit very close to the Sun and then be deployed. Our calculations show that the cruise speed of the solar sail varies from 173 km/s to 325 km/s that corresponds to perihelion 0.3 AU and 0.1 AU, respectively. (2) Elliptical Transfer plus Slingshot plus thermal desorption. In this scenario the Transfer occurs from Earth’s orbit to Jupiter’s orbit; then a Jupiter’s fly-by leads to the orbit close to the Sun, where the sail is deployed and thermal desorption comes active. In this case the cruise speed of the solar sail varies from 187 km/s to 331 km/s depending on the perihelion of the orbit. Our study analyses and compares the different scenarios in which thermal desorption comes beside traditional propulsion systems for extrasolar space exploration.

  • Orbital dynamics of a solar sail accelerated by thermal desorption of coatings
    arXiv: Space Physics, 2016
    Co-Authors: Elena Ancona, Roman Ya. Kezerashvili
    Abstract:

    In this study we considered a solar sail coated with materials that undergo thermal desorption at a specific temperature, as a result of heating by solar radiation at a particular heliocentric distance. Three different scenarios, that only differ in the way the sail approaches the Sun, were analyzed and compared. In every case once the perihelion is reached, the sail coat undergoes thermal desorption. When the desorption process ends, the sail then escapes the Solar System having the conventional acceleration due to solar radiation pressure. Thermal desorption here comes as an additional source of solar sail acceleration beside traditional propulsion systems for extrasolar space exploration. The compared scenarios are the following: i. Hohmann Transfer plus thermal desorption. In this scenario the sail would be carried as a payload to the perihelion with a conventional propulsion system by an Hohmann Transfer from Earth's orbit to an orbit very close to the Sun (almost at 0.1 AU) and then be deployed there. ii. Elliptical Transfer plus Slingshot plus thermal desorption. In this scenario the Transfer occurs from Earth's orbit to Jupiter's orbit. A Jupiter's fly-by leads to the orbit close to the Sun, where the sail is deployed. iii. Two stage acceleration of the solar sail through thermal desorption. The proposed sail has two coats of the materials that undergo thermal desorption at different temperatures depending on the heliocentric distance. The first desorption occurs at the Earth orbit and provides the thrust needed to propel the solar sail toward the Sun. The second desorption is equivalent to that of the other scenarios.

  • Orbital dynamics of a solar sail accelerated by thermal desorption of coatings
    2016
    Co-Authors: Ancona Elena, Roman Ya. Kezerashvili
    Abstract:

    In this study we considered a solar sail coated with materials that undergo thermal desorption at a specific temperature, as a result of heating by solar radiation at a particular heliocentric distance. Three different scenarios, that only differ in the way the sail approaches the Sun, were analyzed and compared. In every case once the perihelion is reached, the sail coat undergoes thermal desorption. When the desorption process ends, the sail then escapes the Solar System having the conventional acceleration due to solar radiation pressure. Thermal desorption here comes as an additional source of solar sail acceleration beside traditional propulsion systems for extrasolar space exploration. The compared scenarios are the following: i. Hohmann Transfer plus thermal desorption. In this scenario the sail would be carried as a payload to the perihelion with a conventional propulsion system by an Hohmann Transfer from Earth's orbit to an orbit very close to the Sun (almost at 0.1 AU) and then be deployed there. ii. Elliptical Transfer plus Slingshot plus thermal desorption. In this scenario the Transfer occurs from Earth's orbit to Jupiter's orbit. A Jupiter's fly-by leads to the orbit close to the Sun, where the sail is deployed. iii. Two stage acceleration of the solar sail through thermal desorption. The proposed sail has two coats of the materials that undergo thermal desorption at different temperatures depending on the heliocentric distance. The first desorption occurs at the Earth orbit and provides the thrust needed to propel the solar sail toward the Sun. The second desorption is equivalent to that of the other scenarios.Comment: 12 pages, 7 figure

Panagiotis Tsiotras - One of the best experts on this subject based on the ideXlab platform.

  • Hohmann-Hohmann AND Hohmann-PHASING COOPERATIVE RENDEZVOUS MANEUVERS
    2015
    Co-Authors: Atri Dutta, Panagiotis Tsiotras
    Abstract:

    We consider the problem of cooperative rendezvous between two satellites in cir-cular orbits, given a fixed time for the rendezvous to be completed, and assuming a circular rendezvous orbit. We investigate two types of cooperative maneuvers for which analytical solutions can be obtained. One is the case of two Hohmann trans-fers, while the other, referred to as HPCM, is the case of a Hohmann Transfer and a Phasing maneuver. For the latter case we derive conditions on the phasing angle that makes a HPCM rendezvous cheaper than a cooperative rendezvous on an orbit that is different than either the original orbits of the two participating satellites. It is shown that minimizing fuel expenditure is equivalent to minimizing a weighted sum of the ΔV s of the two orbital Transfers, the weights being determined by the mass and engine characteristics of the satellites. Our results show that, if the time of rendezvous allows for a Hohmann Transfer between the orbits of the satellites, the optimal rendezvous is either a non-cooperative Hohmann Transfer or a Hohmann-Phasing cooperative maneuver. In both these cases, the maneuver costs are deter-mined analytically. A numerical example verifies these observations. Finally, we demonstrate the utility of this study for Peer-to-Peer (P2P) refueling of satellites in two different circular orbits

  • Hohmann-Hohmann and Hohmann-Phasing Cooperative Rendezvous Maneuvers
    The Journal of the Astronautical Sciences, 2009
    Co-Authors: Atri Dutta, Panagiotis Tsiotras
    Abstract:

    We consider the problem of cooperative rendezvous between two satellites in circular orbits, given a fixed time for the rendezvous to be completed, and assuming a circular rendezvous orbit. We investigate two types of cooperative maneuvers for which analytical solutions can be obtained. One is the case of two Hohmann Transfers, henceforth referred to as HHCM, while the other, henceforth referred to as HPCM, is the case of a Hohmann Transfer and a phasing maneuver. For the latter case we derive conditions on the phasing angle that make a HPCM rendezvous cheaper than a cooperative rendezvous on an orbit that is different than either the original orbits of the two participating satellites. It is shown that minimizing the fuel expenditure is equivalent to minimizing a weighted sum of the Δ V s of the two orbital Transfers, the weights being determined by the mass and engine characteristics of the satellites. Our results show that, if the time of rendezvous allows for a Hohmann Transfer between the orbits of the satellites, the optimal rendezvous is either a noncooperative Hohmann Transfer or a Hohmann-phasing cooperative maneuver. In both of these cases, the maneuver costs are determined analytically. A numerical example verifies these observations. Finally, we demonstrate the utility of this study for Peer-to-Peer (P2P) refueling of satellites residing in two different circular orbits.

Wang Wei-ping - One of the best experts on this subject based on the ideXlab platform.

  • Satellite Orbit Maneuver Simulation Application Based on HLA
    Computer Simulation, 2008
    Co-Authors: Wang Wei-ping
    Abstract:

    To deal with real-time interoperability deficiency of STK (Satellite Tool Kit) in war game simulation, a new flexible simulation design method based on HLA (High Level Architecture) was proposed. Hohmann Transfer between two circular coplanar orbits, single-impulse and double-impulse Transfers between two circular non-planar orbits algorithms were studied and modeled. Then a multi-view visualization module and Simulation Object Model (SOM) were elaborated. The results in comparison with STK show the feasibility of the method and the effectiveness of the models.

Tryshanda Moton - One of the best experts on this subject based on the ideXlab platform.

  • Phobos/Deimos sample return via solar sail.
    Annals of the New York Academy of Sciences, 2005
    Co-Authors: Gregory L. Matloff, Travis Taylor, Conley Powell, Tryshanda Moton
    Abstract:

    A sample-return mission to the Martian satellites using a con-temporary solar sail for all post-Earth-escape propulsion is proposed. The 0.015 kg/m(2) areal mass-thickness sail unfurls after launch and injection onto a Mars-bound Hohmann-Transfer ellipse. Structure and payload increase spacecraft areal mass thickness to 0.028 kg/m(2). During the Mars encounter, the sail functions as a parachute in the outer atmosphere of Mars to accomplish aerocapture. On-board thrusters or the sail maneuver the spacecraft into an orbit with periapsis near Mars and apoapsis near Phobos. The orbit is circularized for Phobos-rendezvous; surface samples are collected. The sail then raises the orbit for Deimos-rendezvous and sample collection. The sail next places the spacecraft on an Earth-bound Hohmann-Transfer ellipse. During Earth encounter, the sail accomplishes Earth-aerocapture or partially decelerates the sample container for entry into the Earth's atmosphere. Mission mass budget is about 218 grams and mission duration is less than five years.

Atri Dutta - One of the best experts on this subject based on the ideXlab platform.

  • Hohmann-Hohmann AND Hohmann-PHASING COOPERATIVE RENDEZVOUS MANEUVERS
    2015
    Co-Authors: Atri Dutta, Panagiotis Tsiotras
    Abstract:

    We consider the problem of cooperative rendezvous between two satellites in cir-cular orbits, given a fixed time for the rendezvous to be completed, and assuming a circular rendezvous orbit. We investigate two types of cooperative maneuvers for which analytical solutions can be obtained. One is the case of two Hohmann trans-fers, while the other, referred to as HPCM, is the case of a Hohmann Transfer and a Phasing maneuver. For the latter case we derive conditions on the phasing angle that makes a HPCM rendezvous cheaper than a cooperative rendezvous on an orbit that is different than either the original orbits of the two participating satellites. It is shown that minimizing fuel expenditure is equivalent to minimizing a weighted sum of the ΔV s of the two orbital Transfers, the weights being determined by the mass and engine characteristics of the satellites. Our results show that, if the time of rendezvous allows for a Hohmann Transfer between the orbits of the satellites, the optimal rendezvous is either a non-cooperative Hohmann Transfer or a Hohmann-Phasing cooperative maneuver. In both these cases, the maneuver costs are deter-mined analytically. A numerical example verifies these observations. Finally, we demonstrate the utility of this study for Peer-to-Peer (P2P) refueling of satellites in two different circular orbits

  • Hohmann-Hohmann and Hohmann-Phasing Cooperative Rendezvous Maneuvers
    The Journal of the Astronautical Sciences, 2009
    Co-Authors: Atri Dutta, Panagiotis Tsiotras
    Abstract:

    We consider the problem of cooperative rendezvous between two satellites in circular orbits, given a fixed time for the rendezvous to be completed, and assuming a circular rendezvous orbit. We investigate two types of cooperative maneuvers for which analytical solutions can be obtained. One is the case of two Hohmann Transfers, henceforth referred to as HHCM, while the other, henceforth referred to as HPCM, is the case of a Hohmann Transfer and a phasing maneuver. For the latter case we derive conditions on the phasing angle that make a HPCM rendezvous cheaper than a cooperative rendezvous on an orbit that is different than either the original orbits of the two participating satellites. It is shown that minimizing the fuel expenditure is equivalent to minimizing a weighted sum of the Δ V s of the two orbital Transfers, the weights being determined by the mass and engine characteristics of the satellites. Our results show that, if the time of rendezvous allows for a Hohmann Transfer between the orbits of the satellites, the optimal rendezvous is either a noncooperative Hohmann Transfer or a Hohmann-phasing cooperative maneuver. In both of these cases, the maneuver costs are determined analytically. A numerical example verifies these observations. Finally, we demonstrate the utility of this study for Peer-to-Peer (P2P) refueling of satellites residing in two different circular orbits.