Liquid Flyback Booster Pre-phase a Study Assessment ... Nasa-tm-104801-vol-1 ... Oct. 28, 1998 PDF Download
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781731269508
Category : Science
Languages : en
Pages : 138
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Book Description
Mw concept of a flyback booster has been around since early in the Shuttle program. The original two-stage Shuttle concepts used a manned flyback booster. These boosters were eliminated from the program for funding and size reasons. The current Shuttle uses two Redesigned Solid Rocket Motors (RSRMs), which are recovered and refurbished after each flight; this is one of the major cost factors of the program. Replacement options have been studied over the past ten years. The conclusion reached by the most recent study is that the liquid flyback booster (LFBB) is the only competitive option from a life-cycle cost perspective. The purpose of this study was to assess the feasibility and practicality of LFBBs. The study provides an expansion of the recommendations made during the during the aforementioned study. The primary benefits are the potential for enhanced reusability and a reuction of recurring costs. The potential savings in vehicle turnaround could offset the up-front costs. Development of LFBBs requires a commitment to the Shuttle program for 20 to 30 years. LFBBs also offer enhanced safety and abort capabilities. Currently, any failure of an RSRM can be considered catastrophic since them we no intact abort capabilities during the burn of the RSRMS. The performance goal of the LFBBs was to lift a fully loaded Orbiter under optimal conditions, so as not to be the limiting factor of the performance capability of the Shuttle. In addition, a final benefit is the availability of growth paths for applications other than the Shuttle. Peterson, W. and Ankney, W. and Bell, J. and Berning, M. and Bryant, L. and Bufkin, A. and Cain, L. and Caram, J. and Cockrell, B. and Curry, D. and Diegelman, T. and Gomez, R. and Hong, A. and Jih, D. and Labbe, S. and Le, M. and Leblanc, M. and Lunney, B. and Masciarelli, J. and Musler, J. Johnson Space Center LIFE CYCLE COSTS; SOLID PROPELLANT ROCKET ENGINES; SPACE SHUTTLES; COST ANALYSIS; ENGINE FAILURE; SPACE SHUTTLE BOOSTERS; BOOSTE...
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Category :
Languages : en
Pages : 138
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Author: United States. National Aeronautics and Space Administration
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722617301
Category :
Languages : en
Pages : 64
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The purpose of this study was to determine the feasibility of Liquid Rocket Boosters (LRBs) replacing Solid Rocket Boosters on the Space Shuttle program. The major findings are given. The most significant conclusion is that LRBs offer significantly safety and performance advantages over the SRBs currently used by the STS without major impact to the ongoing program. Unspecified Center...
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724281784
Category :
Languages : en
Pages : 224
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This Preliminary Project Implementation Plan (PPIP) was used to examine the feasibility of replacing the current Solid Rocket Boosters on the Space Shuttle with Liquid Rocket Boosters (LRBs). The need has determined the implications of integrating the LRB with the Space Transportation System as the earliest practical date. The purpose was to identify and define all elements required in a full scale development program for the LRB. This will be a reference guide for management of the LRB program, addressing such requirement as design and development, configuration management, performance measurement, manufacturing, product assurance and verification, launch operations, and mission operations support. Unspecified Center NASA-CR-183602, NAS 1.26:183602 NAS8-37137...
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781729367841
Category :
Languages : en
Pages : 56
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The feasibility of replacing the Space Transportation System (STS) Solid Rocket Boosters (SRBs) with Liquid Rocket Boosters (LRBs) was studied. Feasibility required acceptable technical risk, program costs, and a program plan which supports STS requirements. Three major goals were identified to direct booster design and operation: increased STS safety and reliability; STS/LRB integration with minimum impact; and increased STS performance. Two booster engine designs were studied. The first engine design was a turbopump-fed engine with state-of-the-art design, and the second was a pressure-fed engine which might provide a lower cost alternative to the pump-fed concept. Both booster concepts were carried through to completion of conceptual design and all system impacts and program costs were identified. Applications for LRB use in the Advanced Launch System (ALS) program were studied using the pump-fed LRB baseline concept and variations on the baseline concept. Support for the Pressure-Fed Booster Test Bed (PFBTB) included test program planning and costs and technical support. Unspecified Center...
Author: United States. National Aeronautics and Space Administration
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Category :
Languages : en
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