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  • Spacecraft Design, Testing and Performance  (3)
  • 2000-2004  (3)
  • 1995-1999
  • 1960-1964
  • 2000  (3)
  • 1
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    Formation Flying In Highly Elliptical Orbits Initializing the Formation (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In this paper several methods are examined for initializing formations in which all spacecraft start in a common elliptical orbit subsequent to separation from the launch vehicle. The tetrahedron formation used on missions such as the Magnetospheric Multiscale (MMS), Auroral Multiscale Midex (AMM), and Cluster is used as a test bed Such a formation provides full three degrees-of-freedom in the relative motion about the reference orbit and is germane to several missions. The type of maneuver strategy that can be employed depends on the specific initial conditions of each member of the formation. Single-impulse maneuvers based on a Gaussian variation-of-parameters (VOP) approach, while operationally simple and intuitively-based, work only in a limited sense for a special class of initial conditions. These 'tailored' initial conditions are characterized as having only a few of the Keplerian elements different from the reference orbit. Attempts to achieve more generic initial conditions exceed the capabilities of the single impulse VOP. For these cases, multiple-impulse implementations are always possible but are generally less intuitive than the single-impulse case. The four-impulse VOP formalism discussed by Schaub is examined but smaller delta-V costs are achieved in our test problem by optimizing a Lambert solution.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Space Flight Dynamics; Jun 01, 2000; Biarritz; France
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Optimal Configurations for Rotating Spacecraft Formations (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In this paper a new class of formations that maintain a constant shape as viewed from the Earth is introduced. An algorithm is developed to place n spacecraft in a constant shape formation spaced equally in time using the classical orbital elements. To first order, the dimensions of the formation are shown to be simple functions of orbit eccentricity and inclination. The performance of the formation is investigated over a Keplerian orbit using a performance measure based on a weighted average of the angular separations between spacecraft in formation. Analytic approximations are developed that yield optimum configurations for different values of n. The analytic approximations are shown to be in excellent agreement with the exact solutions.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Richard H. Battin Astrodynamics Symposium; Mar 20, 2000 - Mar 21, 2000; College Station, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Earth Entry Vehicle for Mars Sample Return (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The driving requirement for design of a Mars Sample return mission is assuring containment of the returned samples. The impact of this requirement on developmental costs, mass allocation, and design approach of the Earth Entry Vehicle is significant. A simple Earth entry vehicle is described which can meet these requirements and safely transport the Mars Sample Return mission's sample through the Earth's atmosphere to a recoverable location on the surface. Detailed analysis and test are combined with probabilistic risk assessment to design this entirely passive concept that circumvents the potential failure modes of a parachute terminal descent system. The design also possesses features that mitigate other risks during the entry, descent, landing and recovery phases. The results of a full-scale drop test are summarized.
    Keywords: Spacecraft Design, Testing and Performance
    Type: IAF-00-Q.3.04 , 51st International Astronautics Federation Congress; Oct 02, 2000 - Oct 06, 2000; Rio de Janeiro; Brazil
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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