The Experts below are selected from a list of 36 Experts worldwide ranked by ideXlab platform

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

  • Multimission Modular Spacecraft Ground Support Software System (MMS/GSSS) state-of-the-art computer systems/ compatibility study
    2017
    Co-Authors: Nasa
    Abstract:

    The compatibility of the Multimission Modular Spacecraft (MMS) Ground Support Software System (GSSS), currently operational on a ModComp IV/35, with the VAX 11/780 system is discussed. The compatibility is examined in various key areas of the GSSS through the results of in depth testing performed on the VAX 11/780 and ModComp IV/35 systems. The compatibility of the GSSS with the ModComp CLASSIC is presented based upon projections from ModComp supplied literature.

  • Flight support system mechanisms
    2016
    Co-Authors: Nasa
    Abstract:

    The Flight Support System (FSS) which contains twelve mechanisms (six different types) which are used for retention and positioning of a Multimission Modular Spacecraft (MMS) within the Space Shuttle's cargo bay during launch, retrieval, and servicing missions is described. Retention latches were designed to provide the capability for structural support of the MMS during launch and retrieval, and during servicing operations the mechanisms on the Positioning Platform provide the capability for positioning the MMS in virtually any orientation necessary for the work to be performed. In addition, there are mechanisms for matching and demating umbilical connectors and a mechanism for locking the Positioning Platform during maneuvers. Each Mechanism is driven by a Common Drive Unit. Manual overrides were provided for those mechanisms that would present a safety hazard for the crew, if they should fail.

  • Severe storms observing satellite (STORMSAT)
    2013
    Co-Authors: Nasa
    Abstract:

    The primary payload for this satellite is the Advanced Atmospheric Sounding and Imaging Radiometer which will perform precise infrared temperature sounding and visible/infrared imaging from geostationary orbit. A secondary payload instrument which may be utilized on STORMSAT is the Microwave Atmospheric Sounding Radiometer which provides an independent set of temperature and humidity sounding in cloudy, meteorologically active regions. The study provides satellite designs and identifies mission-unique subsystems using the Multimission Modular Spacecraft using a Shuttle/Interim Upper Stage launch vehicle.

  • Servicer system demonstration plan and capability development
    2013
    Co-Authors: Nasa
    Abstract:

    An orbital maneuvering vehicle (OMV) front end kit is defined which is capable of performing in-situ fluid resupply and Modular maintenance of free flying Spacecraft based on the integrated orbital servicing system (IOSS) concept. The compatibility of the IOSS to perform gas and fluid umbilical connect and disconnect functions utilizing connect systems currently available or in development is addressed. A series of tasks involving on-orbit servicing and the engineering test unit (ETU) of the on-orbit service were studied. The objective is the advancement of orbital servicing by expanding the Spacecraft Servicing Demonstration Plan (SSDP) to include detail demonstration planning using the Multimission Modular Spacecraft (MMS) and upgrading the ETU control.

R. V. Welch - One of the best experts on this subject based on the ideXlab platform.

  • An augmented MMS MACS for the Topex/Poseidon mission and beyond
    2011
    Co-Authors: R. J. Williams, R. V. Welch, D. Lee, C. J. Dennehy
    Abstract:

    The augmented Modular Attitude Control Subsystem (MACS) is described, with emphasis on the significant hardware modifications that have been incorporated into the Landsat MMS (Multimission Modular Spacecraft) MACS design to satisfy the Topex/Poseidon mission attitude control and determination requirements. Particular attention is given to a modification consisting in the addition of an earth pointing safe hold mode utilizing yaw coarse sun sensors to provide a yaw-slew capability for maintaining adequate illumination of the solar array. The design utility of this augmented MACS module for future Spacecraft applications is pointed out.

  • Validation Approach for the Modular Attitude Determination Control Subsystem Implemented on Topex/Poseidon (T/P)
    IFAC Proceedings Volumes, 1992
    Co-Authors: R. V. Welch
    Abstract:

    Abstract The Modular Attitude Control Subsystem (MACS) was developed as part of the Multimission Modular Spacecraft for NASA Goddard Space Flight Center in the late 1970s. This subsystem has demonstrated performance on multiple low earth orbit scientific missions. Application on T/P is derived from the flight proven LANDSAT-5 design and represents the first Fairchild development of the MACS. Design and development are complete with final ground verification underway to support a July 1992 T/P launch. The philosophy of the ground verification process is described in detail. The discussion will provide the approach of subsystem verification from component level testing through ever increasing levels of subsystem and satellite integration. The role of analyses will be described and some on-orbit subsystem performance issues are presented. This work was performed for the Jet Propulsion Laboratory, California Institute of Technology, sponsored by the National Aeronautics and Space Administration.

Ernest Costogue - One of the best experts on this subject based on the ideXlab platform.

  • TOPEX electrical power system
    1991
    Co-Authors: P.r.k. Chetty, Lew Roufberg, Ernest Costogue
    Abstract:

    The TOPEX mission requirements which impact the power requirements and analyses are presented. A description of the electrical power system (EPS), including energy management and battery charging methods that were conceived and developed to meet the identified satellite requirements, is included. Analysis of the TOPEX EPS confirms that all of its electrical performance and reliability requirements have been met. The TOPEX EPS employs the flight-proven Modular power system (MPS) which is part of the Multimission Modular Spacecraft and provides high reliability, abbreviated development effort and schedule, and low cost. An energy balance equation, unique to TOPEX, has been derived to confirm that the batteries will be completely recharged following each eclipse, under worst-case conditions. TOPEX uses three NASA Standard 50AH Ni-Cd batteries, each with 22 cells in series. The MPS contains battery charge control and protection based on measurements of battery currents, voltages, temperatures, and computed depth-of-discharge. In case of impending battery depletion, the MPS automatically implements load shedding.

W. Reupke - One of the best experts on this subject based on the ideXlab platform.

  • A Multimission three-axis stabilized Spacecraft flight dynamics ground support system
    1993
    Co-Authors: J. Langston, K. Krack, W. Reupke
    Abstract:

    The Multimission Three-Axis Stabilized Spacecraft (MTASS) Flight Dynamics Support System (FDSS) has been developed in an effort to minimize the costs of ground support systems. Unlike single-purpose ground support systems, which attempt to reduce costs by reusing software specifically developed for previous missions, the Multimission support system is an intermediate step in the progression to a fully generalized mission support system in which numerous missions may be served by one general system. The benefits of Multimission attitude ground support systems extend not only to the software design and coding process, but to the entire system environment, from specification through testing, simulation, operations, and maintenance. This paper reports the application of an MTASS FDSS to multiple scientific satellite missions. The satellites are the Upper Atmosphere Research Satellite (UARS), the Extreme Ultraviolet Explorer (EUVE), and the Solar Anomalous Magnetospheric Particle Explorer (SAMPEX). Both UARS and EUVE use the Multimission Modular Spacecraft (MMS) concept. SAMPEX is part of the Small Explorer (SMEX) series and uses a much simpler set of attitude sensors. This paper centers on algorithm and design concepts for a Multimission system and discusses flight experience from UARS.

C. J. Dennehy - One of the best experts on this subject based on the ideXlab platform.

  • An augmented MMS MACS for the Topex/Poseidon mission and beyond
    2011
    Co-Authors: R. J. Williams, R. V. Welch, D. Lee, C. J. Dennehy
    Abstract:

    The augmented Modular Attitude Control Subsystem (MACS) is described, with emphasis on the significant hardware modifications that have been incorporated into the Landsat MMS (Multimission Modular Spacecraft) MACS design to satisfy the Topex/Poseidon mission attitude control and determination requirements. Particular attention is given to a modification consisting in the addition of an earth pointing safe hold mode utilizing yaw coarse sun sensors to provide a yaw-slew capability for maintaining adequate illumination of the solar array. The design utility of this augmented MACS module for future Spacecraft applications is pointed out.