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  • 1
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    LARES Mission: Separation and Retention Subsystem (2014)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: As part of the Lares (LAser RElativity Satellite) mission, an all-Italian scientific mission launched with the Vega maiden flight in February 2012, a mechanical separation and retention subsystem (SSEP) has been developed to retain the LARES satellite during launch and release it in the final orbit. The design flow was based on the identification of the driving requirements and critical areas to guide the trade-off, design, analysis and test activities. In particular, the SSEP had to face very high environmental loads and to minimize the contact areas with the satellite that had a spherical shape. The test activity overview is provided.
    Keywords: Mechanical Engineering; Launch Vehicles and Launch Operations; Spacecraft Design, Testing and Performance
    Type: The 42nd Aerospace Mechanism Symposium; 259-272; NASA/CP-2014-217519
    Format: application/pdf
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  • 2
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    Constraints on LISA Pathfinder's Self-Gravity: Design Requirements, Estimates and Testing Procedures (2016)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: LISA Pathfinder satellite was launched on 3 December 2015 toward the Sun Earth first Lagrangian point (L1) where the LISA Technology Package (LTP), which is the main science payload, will be tested. LTP achieves measurements of differential acceleration of free-falling test masses (TMs) with sensitivity below 3 x 10(exp -14) m s(exp -2) Hz(exp - 1/2) within the 130 mHz frequency band in one dimension. The spacecraft itself is responsible for the dominant differential gravitational field acting on the two TMs. Such a force interaction could contribute a significant amount of noise and thus threaten the achievement of the targeted free-fall level. We prevented this by balancing the gravitational forces to the sub nm s(exp -2) level, guided by a protocol based on measurements of the position and the mass of all parts that constitute the satellite, via finite element calculation tool estimates. In this paper, we will introduce the gravitational balance requirements and design, and then discuss our predictions for the balance that will be achieved in flight.
    Keywords: Astrophysics
    Type: GSFC-E-DAA-TN41786 , Classical and Quantum Gravity (ISSN 0264-9381) (e-ISSN 1361-6382); 33; 23; 235015
    Format: text
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