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  • 11
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    Unknown
    In:  CASI
    Publication Date: 2019-07-12
    Description: The objectives of this slide presentation are: to describe the Command Service Module (CSM) plane change task, the prelaunch phase lunar module (LM) activities, and the prelaunch phase CSM activities.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: JSC-17237-18
    Format: application/pdf
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  • 12
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    Unknown
    In:  CASI
    Publication Date: 2019-07-12
    Description: Objectives include: a) Become familiar with the Saturn V Stage I (S-IC) major structural components: Forward Skirt, Oxidizer Tank, Intertank, Fuel Tank, and Thrust Structure. b) Gain a general understanding of the Stage I subsystems: Fuel, Oxidizer, Instrumentation, Flight Control, Environmental Control, Electrical, Control Pressure, and Ordinance.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-17237-24
    Format: application/pdf
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  • 13
    Publication Date: 2019-07-12
    Description: This slide presentation reviews the design and redesign considerations of the Apollo lunar module electrical power system. Included in the work are graphics showing the lunar module power system. It describes the in-flight failures, and the lessons learned from these failures.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-17237-13
    Format: application/pdf
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  • 14
    Publication Date: 2019-07-12
    Description: This slide presentation describes the propulsion system for the Apollo Lunar Module (LM). It defines they systems for the LM propulsion and the control system. It lists the times during the mission at which each system was used. It describes the basic components and the operation of the Descent and Ascent Propulsion systems. It also describes LM reaction control system.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-17237-14
    Format: application/pdf
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  • 15
    Publication Date: 2019-07-12
    Description: The objectives of this slide presentation are to: review the basic design criteria for fuel cells (FC's), review design considerations during developmental phase that affected Block I and Block II vehicles, summarize the conditions that led to the failure of components in the FC's, and state the solution implemented for each failure. It reviews the location of the fuel cells, the fuel cell theory the design criteria going into development phase and coming from the development phase, failures and solutions of Block I and II, and the lessons learned.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-17237-16
    Format: application/pdf
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  • 16
    Publication Date: 2019-07-12
    Description: Objectives include: a) Describe LM Electrical System original specifications; b) Describe the decision to change from fuel cells to batteries and other changes; c) Describe the Electrical system; and d) Describe the Apollo 13 failure from the LM perspective.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-17237-17
    Format: application/pdf
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  • 17
    Publication Date: 2019-07-12
    Description: This slide presentation reviews the considerations for the design of wiring for the Lunar Module. Included are a review of the choice of conductors and insulations, the wire splicing (i.e., crimping, and soldering), the wire connectors, and the fabrication of the wire harnesses. The problems in fabrication include the wires being the wrong length, the damage due to the sharp edges, the requried use of temproary protective covers and inadequate training. The problems in the wire harness installation include damge from sharp eges, work on adjacent harnesses, connector damage, and breaking wires. Engineering suggestions from the Apollo-era in reference to the conductors that are reviewed include: the use of plated conductors, and the use of alloys for stronger wiring. In refernce to insulation, the suggestions from Apollo era include the use of polymer tape-wrap wire insulation due to the light weight, however, other types of modern insulation might be more cost-effective. In reference to wire splices and terminal boards the suggestions from the Apollo Era include the use of crimp splices as superior to solder splices, joining multiple wire to a common point using modular plug-ins might be more reliable, but are heavier than crimp splicing. For connectors, the lessons from the Apollo era indicate that a rear environmental seal that does not require additional potting is preferred, and pins should be crimped or welded to the incoming wires and be removable from the rear of the connector.
    Keywords: Electronics and Electrical Engineering
    Type: JSC-17237-15
    Format: application/pdf
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  • 18
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    Unknown
    In:  CASI
    Publication Date: 2019-07-12
    Description: This viewgraph presentation reviews basic navigation concepts, describes coordinate systems and identifies attitude determination techniques including Primary Guidance, Navigation and Control System (PGNCS) IMU management and Command and Service Module Stabilization and Control System/Lunar Module (LM) Abort Guidance System (AGS) attitude management. The presentation also identifies state vector determination techniques, including PGNCS coasting flight navigation, PGNCS powered flight navigation and LM AGS navigation.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: JSC-17237-3
    Format: application/pdf
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  • 19
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    Unknown
    In:  CASI
    Publication Date: 2019-07-12
    Description: This viewgraph presentation examines Command and Service Module (CSM) Communications. The communication system's capabilities are defined, including CSM-Earth, CSM-Lunar Module and CSM-Extravehicular crewman communications. An overview is provided for S-band communications, including data transmission and receiving rates, operating frequencies and major system components (pre-modulation processors, unified S-band electronics, S-band power amplifier and S-band antennas). Additionally, data transmission rates, operating frequencies and the capabilities of VHF communications are described. Major VHF components, including transmitters and receivers, and the VHF multiplexer and antennas are also highlighted. Finally, communications during pre-launch, ascent, in-flight and entry are discussed. Overall, the CSM communication system was rated highly by flight controllers and crew. The system was mostly autonomous for both crew and flight controllers and no major issues were encountered during flight.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: JSC-17237-5
    Format: application/pdf
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  • 20
    Publication Date: 2019-07-12
    Description: Design considerations and failure modes for the Lunar Module (LM) Environmental Control System (ECS) are described. An overview of the the oxygen supply and cabin pressurization, atmosphere revitalization, water management and heat transport systems are provided. Design considerations including reliability, flight instrumentation, modularization and the change to the use of batteries instead of fuel cells are discussed. A summary is provided for the LM ECS general testing regime.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-17237-12 , Apollo 13 Blu Ray DVD and BD Live Server comment, January 2009
    Format: application/pdf
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