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  • 1
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    A Comparison of Trajectory Optimization Methods for the Impulsive Minimum Fuel Rendezvous Problem (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: In this paper we present a comparison of optimization approaches to the minimum fuel rendezvous problem. Both indirect and direct methods are compared for a variety of test cases. The indirect approach is based on primer vector theory. The direct approaches are implemented numerically and include Sequential Quadratic Programming (SQP), Quasi-Newton, Simplex, Genetic Algorithms, and Simulated Annealing. Each method is applied to a variety of test cases including, circular to circular coplanar orbits, LEO to GEO, and orbit phasing in highly elliptic orbits. We also compare different constrained optimization routines on complex orbit rendezvous problems with complicated, highly nonlinear constraints.
    Keywords: Spacecraft Propulsion and Power
    Type: 26th Annual Guidance and Control Conference; Feb 01, 2003 - Feb 28, 2003; Breckenridge, CO; United States
    Format: text
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  • 2
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    A Preliminary Formation Flying Orbit Dynamics Analysis for Leonardo-BRDF (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Leonardo-BRDF is a NASA mission concept proposed to allow the investigation of radiative transfer and its effect on the Earth's climate and atmospheric phenomenon. Enabled by the recent developments in small-satellite and formation flying technology, the mission is envisioned to be composed of an array of spacecraft in carefully designed orbits. The different perspectives provided by a distributed array of spacecraft offer a unique advantage to study the Earth's albedo. This paper presents the orbit dynamics analysis performed in the context of the Leonardo-BRDF science requirements. First, the albedo integral is investigated and the effect of viewing geometry on science return is studied. The method used in this paper, based on Gauss quadrature, provides the optimal formation geometry to ensure that the value of the integral is accurately approximated. An orbit design approach is presented to achieve specific relative orbit geometries while simultaneously satisfying orbit dynamics constraints to reduce formation-keeping fuel expenditure. The relative geometry afforded by the design is discussed in terms of mission requirements. An optimal two-burn initialization scheme is presented with the required delta-V to distribute all spacecraft from a common parking orbit into their appropriate orbits in the formation. Finally, formation-keeping strategies are developed and the associated delta-V's are calculated to maintain the formation in the presence of perturbations.
    Keywords: Astrodynamics
    Type: 2001 Flight Mechanics Symposium; 131; NASA/CP-2001-209986
    Format: text
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  • 3
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    Calipso's Mission Design: Sun-Glint Avoidance Strategies (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: CALIPSO will fly in formation with the Aqua spacecraft to obtain a coincident image of a portion of the Aqua/MODIS swath. Since MODIS pixels suffering sun-glint degradation are not processed, it is essential that CALIPSO only co- image the glint h e portion of the MODIS instrument swath. This paper presents sun-glint avoidance strategies for the CALIPSO mission. First, we introduce the Aqua sun-glint geometry and its relation to the CALIPSO-Aqua formation flying parameters. Then, we detail our implementation of the computation and perform a cross-track trade-space analysis. Finally, we analyze the impact of the sun-glint avoidance strategy on the spacecraft power and delta-V budget over the mission lifetime.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AAS-04-114 , AAS/AIAA Space Flight Mechanics Conference; Feb 08, 2004 - Feb 12, 2004; Maui, HI; United States
    Format: application/pdf
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  • 4
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    A Comparison of Trajectory Optimization Methods for the Impulsive Minimum Fuel Rendezvous Problem (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In this paper we present, a comparison of trajectory optimization approaches for the minimum fuel rendezvous problem. Both indirect and direct methods are compared for a variety of test cases. The indirect approach is based on primer vector theory. The direct approaches are implemented numerically and include Sequential Quadratic Programming (SQP). Quasi- Newton and Nelder-Meade Simplex. Several cost function parameterizations are considered for the direct approach. We choose one direct approach that appears to be the most flexible. Both the direct and indirect methods are applied to a variety of test cases which are chosen to demonstrate the performance of each method in different flight regimes. The first test case is a simple circular-to-circular coplanar rendezvous. The second test case is an elliptic-to-elliptic line of apsides rotation. The final test case is an orbit phasing maneuver sequence in a highly elliptic orbit. For each test case we present a comparison of the performance of all methods we consider in this paper.
    Keywords: Spacecraft Propulsion and Power
    Type: 26th Annual Guidance and Control Conference; Feb 01, 2003 - Feb 28, 2003; Breckenridge, CO.; United States
    Format: application/pdf
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  • 5
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    A Preliminary Formation Flying Orbit Dynamics Analysis for Leonardo-BRDF (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Leonardo-BRDF is a new NASA mission concept proposed to allow the investigation of radiative transfer and its effect on the Earth's climate and atmospheric phenomenon. Enabled by the recent developments in small-satellite and formation flying technology, the mission is envisioned to be composed of an array of spacecraft in carefully designed orbits. The different perspectives provided by a distributed array of spacecraft offer a unique advantage to study the Earth's albedo. This paper presents the flight dynamics analysis performed in the context of the Leonardo-BRDF science requirements. First, the albedo integral is investigated and the effect of viewing geometry on science return is studied. The method used in this paper, based on Gauss quadrature, provides the optimal formation geometry to ensure that the value of the integral is accurately approximated. An orbit design approach is presented to achieve specific relative orbit geometries while simultaneously satisfying orbit dynamics constraints to reduce formation-keeping fuel expenditure. The relative geometry afforded by the design is discussed in terms of mission requirements. An optimal Lambert initialization scheme is presented with the required DeltaV to distribute all spacecraft from a common parking orbit into their appropriate orbits in the formation. Finally, formation-keeping strategies are developed and the associated DeltaV's are calculated to maintain the formation in the presence of perturbations.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 2001 IEEE Aerospace Conference; Mar 10, 2001 - Mar 17, 2001; Big Sky, MT; United States
    Format: application/pdf
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