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  • Other Sources  (171)
  • Spacecraft Design, Testing and Performance  (171)
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  • 2008  (171)
  • 1
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    Orion -- Crew Exploration Vehicle (CEV) Project Overview (2008)
    In:  Other Sources
    Details
    Publication Date: 2018-06-06
    Description: NASA explores for answers that power our future by building a new space exploration vehicle that will become America s human spacecraft workhorse after the shuttle is retired in 2010. The new spacecraft is called Orion. Orion is part of the Constellation Program to send human explorers back to the Moon and beyond
    Keywords: Spacecraft Design, Testing and Performance
    Type: 2007 NASA Seal/Secondary Air System Workshop; 25-39; NASA/CP-2008-215263/VOL1
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Sample Manipulation System for Sample Analysis at Mars (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Sample Analysis at Mars (SAM) instrument will analyze Martian samples collected by the Mars Science Laboratory Rover with a suite of spectrometers. This paper discusses the driving requirements, design, and lessons learned in the development of the Sample Manipulation System (SMS) within SAM. The SMS stores and manipulates 74 sample cups to be used for solid sample pyrolysis experiments. Focus is given to the unique mechanism architecture developed to deliver a high packing density of sample cups in a reliable, fault tolerant manner while minimizing system mass and control complexity. Lessons learned are presented on contamination control, launch restraint mechanisms for fragile sample cups, and mechanism test data.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 39th Aerospace Mechanisms Symposium; 303-316; NASA/CP-2008-215252
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    NASA TECHNICAL REPORTS
  • 3
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    JPL Fault Protection Experiences - Case Studies (2008)
    In:  Other Sources
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    Publication Date: 2018-06-11
    Description: This slide presentation shows several case studies for fault protection. The cases involve a discovery-class mission to excavate material from a comet, rendezvous with two asteroids and develop a prototype system for a next-generation Deep Space Network consisting of ndca large array of small antennas.
    Keywords: Spacecraft Design, Testing and Performance
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    SAMPEX Spin Stabilized Mode (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The Solar, Anomalous, and Magnetospheric Particle Explorer (SAMPEX), the first of the Small Explorer series of spacecraft, was launched on July 3, 1992 into an 82' inclination orbit with an apogee of 670 km and a perigee of 520 km and a mission lifetime goal of 3 years. After more than 15 years of continuous operation, the reaction wheel began to fail on August 18,2007. With a set of three magnetic torquer bars being the only remaining attitude actuator, the SAMPEX recovery team decided to deviate from its original attitude control system design and put the spacecraft into a spin stabilized mode. The necessary operations had not been used for many years, which posed a challenge. However, on September 25, 2007, the spacecraft was successfully spun up to 1.0 rpm about its pitch axis, which points at the sun. This paper describes the diagnosis of the anomaly, the analysis of flight data, the simulation of the spacecraft dynamics, and the procedures used to recover the spacecraft to spin stabilized mode.
    Keywords: Spacecraft Design, Testing and Performance
    Format: application/pdf
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  • 5
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    A Covert Disruptive Technology: Test and Development of the Corona Satellite (2008)
    In:  Other Sources
    Details
    Publication Date: 2018-06-06
    Description: The launching by the Soviet Union of the Sputnik satellite in 19457 was an impetuous to the United States. The Intercontinental ballistic Missile (ICBM) that launched the Earth's first satellite, could have been armed with a nuclear warhead, that could destroy an American city. The primary intelligence requirement that the US had was to determine the actual size of the Soviet missile program. To this end, a covert, high-risk photoreconnaissance satellite was developed. The code name of this program was "Corona." This article describes the trials and eventual successes of the Corona program.
    Keywords: Spacecraft Design, Testing and Performance
    Type: ITEA Journal; Volume 28; No. 4; 135-137
    Format: text
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  • 6
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    A High Performance Command and Data Handling System for NASA's Lunar Reconnaissance Orbiter (2008)
    In:  CASI
    Details
    Publication Date: 2018-08-10
    Description: A high performance, modular and state-of-the-art Command and Data Handling (C&DH) system has been developed for use on the Lunar Reconnaissance Orbiter (LRO) mission. This paper addresses the hardware architecture, the operational performance, and the fabrication technology.
    Keywords: Spacecraft Design, Testing and Performance
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  • 7
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    Apollo 13 Case Study Part 1 and 2 (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-11
    Description: Objectives: a) Describe the Service Module Electrical Power System hardware; b) Describe the circumstances which led to the Apollo 13 accident c) Summarize the Mission Control and crew reaction.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Apollo 13 Blu Ray DVD
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    SDO FlatSat Facility (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The goal of the Solar Dynamics Observatory (SDO) is to understand and, ideally, predict the solar variations that influence life and society. It's instruments will measure the properties of the Sun and will take hifh definition images of the Sun every few seconds, all day every day. The FlatSat is a high fidelity electrical and functional representation of the SDO spacecraft bus. It is a high fidelity test bed for Integration & Test (I & T), flight software, and flight operations. For I & T purposes FlatSat will be a driver to development and dry run electrical integration procedures, STOL test procedures, page displays, and the command and telemetry database. FlatSat will also serve as a platform for flight software acceptance and systems testing for the flight software system component including the spacecraft main processors, power supply electronics, attitude control electronic, gimbal control electrons and the S-band communications card. FlatSat will also benefit the flight operations team through post-launch flight software code and table update development and verification and verification of new and updated flight operations products. This document highlights the benefits of FlatSat; describes the building of FlatSat; provides FlatSat facility requirements, access roles and responsibilities; and, and discusses FlatSat mechanical and electrical integration and functional testing.
    Keywords: Spacecraft Design, Testing and Performance
    Format: application/pdf
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  • 9
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    Parameter Estimation of Lateral Spacecraft Fuel Slosh (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-11
    Description: Predicting the effect of fuel slosh on the attitude control system of a spacecraft or launch vehicle is a very important and challenging task. Whether the spacecraft is spinning or moving laterally, the dynamic effect of the fuel slosh helps determine whether the spacecraft will remain on its intended trajectory. Three categories of slosh can be caused by launch vehicle or spacecraft maneuvers when the fuel is in the presence of an acceleration field. These are bulk-fluid motion, subsurface wave motion (currents), and free-surface slosh. Each of these slosh types has a periodic component defined by either a spinning or a lateral motion. For spinning spacecraft, all three types of slosh can greatly affect stability. Bulk-fluid motion and free-surface slosh can affect the lateral-slosh characteristics. For either condition, an unpredicted coupled resonance between the spacecraft and its onboard fuel could threaten a mission. This ongoing research effort seeks to improve the accuracy and efficiency of modeling techniques used to predict these types of fluid motions for lateral motion. Particular efforts focus on analyzing the effects of viscoelastic diaphragms on slosh dynamics.
    Keywords: Spacecraft Design, Testing and Performance
    Type: John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report; 84-85; NASA/TM-2008-214740
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Descent Assisted Split Habitat Lunar Lander Concept (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-11
    Description: The Descent Assisted Split Habitat (DASH) lunar lander concept utilizes a disposable braking stage for descent and a minimally sized pressurized volume for crew transport to and from the lunar surface. The lander can also be configured to perform autonomous cargo missions. Although a braking-stage approach represents a significantly different operational concept compared with a traditional two-stage lander, the DASH lander offers many important benefits. These benefits include improved crew egress/ingress and large-cargo unloading; excellent surface visibility during landing; elimination of the need for deep-throttling descent engines; potentially reduced plume-surface interactions and lower vertical touchdown velocity; and reduced lander gross mass through efficient mass staging and volume segmentation. This paper documents the conceptual study on various aspects of the design, including development of sortie and outpost lander configurations and a mission concept of operations; the initial descent trajectory design; the initial spacecraft sizing estimates and subsystem design; and the identification of technology needs
    Keywords: Spacecraft Design, Testing and Performance
    Format: application/pdf
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