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    NASA is currently building the Space Launch System (SLS) Block-1 launch vehicle for the Artemis I test flight. Design of the Artemis II mission, which will use theBlock-1 vehicle to take astronauts around the moon for the first time in decades, is also underway. The Guidance, Navigation, and Controls (GN&C) algorithms will be largely similar for the two missions. However, the extensive simulation and testing campaign for Artemis I has revealed opportunities for improvements in the GN&C algorithms, allowing more effective use of the capabilities of the SLS vehicle, and enhancing safety for the astronauts aboard. This paper will de-scribe several planned algorithm updates for the Artemis II mission. The updates enhance the Powered Explicit Guidance (PEG) algorithm and auxiliary guidance algorithms.
    Space launch
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    A broad-based Advanced Development Program is being conducted to modernize the technological base and support the systems design of the National Launch System. While the principal concentration of efforts has been in propulsion, significant work is being accomplished in all of the disciplinary areas associated with space launch. Tasks are selected that offer reduced costs, increased reliability, and enhanced operability with anticipated task completion times which are consistent with NLS development.
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    The paper discusses launch operations from a program perspective. Launch operations cost is a significant part of program cost. New approaches to launch operations, integrated with lessons learned, have the potential to increase safety and reliability as well as reduce cost. Operational efficiency must be an initial program goal. Design technology and management philosophy must be implemented early to ensure operational cost goals. Manufacturing cost and launch cost are related to operational efficiency. True program savings can be realized through implementation of launch operations cost saving approaches which do not correspondingly increase cost in other program areas such as manufacturing and software development and maintenance. Launch rate is a key factor in the cost/flight analysis and the determination of launch operations efficiency goals.
    Operational efficiency
    Cost driver
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    For over thirty years, large launch vehicles such as Saturn, Delta, Atlas, and Titan have successfully provided the world with access to space. The emphasis of each of those programs was focused on maximizing launch vehicle performance. More recently, in the Space Shuttle program, this traditional emphasis was widened to include the achievement of cost and schedule goals. Future launch vehicle programs, such as the National Launch System (NLS) and the Single Stage to Orbit (SSTO); will need to satisfy even more stringent requirements. Low life cycle costs, high launch rates, demanding surge capacities, short turnaround times, and continuous program evolution and growth considerations will shape the next generation space launch vehicle programs. More than ever, efficient ground operations will play an important role in meeting the requirements of these new programs.
    Space launch
    Space program
    Booster (rocketry)
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    Future launch vehicle programs for automated space missions, discussing higher launch velocities and economics
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    The main objective of the Advanced Launch System (ALS) program is to realize a substantial reduction in recurring launch costs over present launch systems. A methodology is presented for assessing the impact of the reliability of the avionics suite on the recurring launch cost of the ALS. The methodology is illustrated by focusing on two architectures. The first is a distillation of a typical architecture for this type of application. The second is a simplified implementation of the Advanced Information Processing System (AIPS) technology developed at the Charles Stark Draper Laboratory, Inc. Both architectures utilize redundancy of hardware to tolerate faults. the key contributors to the cost of unreliability are identified and modeled utilizing Markov modeling techniques for each of the two architectures. The results are presented along with the more traditional costs for these avionics suites.
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    In order to reduce costs and accelerate vehicle turnaround, a single automated system will be developed to support shuttle launch site operations, replacing a multiplicity of systems used in previous programs. The Launch Processing System will provide real-time control, data analysis, and information display for the checkout, servicing, launch, landing, and refurbishment of the launch vehicles, payloads, and all ground support systems. It will also provide real-time and historical data retrieval for management and sustaining engineering (test records and procedures, logistics, configuration control, scheduling, etc.).
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