Filament wound metal lined propellant tanks for future earth-to-orbit transports / lan O. MacConochie, Robert B. Davis, William T. Freeman, Jr.

Format:

Book

Government document

Author/Creator:

MacConochie, Ian O., author.

Davis, Robert B. (NASA Langley Research Center), author.

Freeman, William T. Jr., author.

Contributor:

Langley Research Center, issuing body.

Series:

NASA technical memorandum ; 100594.

NASA technical memorandum ; 100594

Language:

English

Subjects (All):

Honeycomb structures.

Genre:

Online resources.

Physical Description:

1 online resource (30 pages) : illustrations

Place of Publication:

Hampton, Virginia : National Aeronautics and Space Administration, Langley Research Center, October 1988.

Summary:

For future Earth-to-orbit transport vehicles, reusability and lighter weights are sought for the main propellant tanks. To achieve these goals, a filament wound tank with a metal liner and an intermediate layer of foam-filled honeycomb is proposed. A hydrogen tank is used as an example. To accommodate the mismatches in the expansion of liner and overwrap, a design is proposed wherein the liner is configured so that the extension of the liner under pressure matches the expected contraction of the same liner due to the presence of a cryogen. In operation, the liner is pressurized at a rate such that the pressure strain just matches the contraction due to the decrease in temperature. As an alternate design approach, a compressive pre-stress is placed in the liner such that the liner will not separate from the overwrap at operating conditions. A finite element program is used to show stresses in the liner and overwrap for various tank pressures for the pre-stressed liner concept. A fracture mechanics analysis is made of the liners to determine tank life. The tank concept shown has a similar unit weight to the Shuttle external hydrogen tank, but the filament wound tank is expected to be reusable. Various design considerations related to the integration of the propellant tanks into a future transport vehicle are discussed.

Contents:

Abstract

Introduction

Vehicle size and shape considerations

Tank and body shell designs

Ambient air effects on cryogenic tanks

Filament wound tank concept

Fracture mechanics analysis

Liner configuration alternatives

Why consider filament wound tanks

Design factors of safety

Summary remarks.

Notes:

"October 1988."

"Performing organization: NASA Langley Research Center"--Report documentation page

Includes bibliographical references (pages 13-14), and tables (pages 15-30).

Online resource; title from PDF title page (NASA, viewed December 6, 2016).

Other Format:

Microfiche version: MacConochie, Ian O. Filament wound metal lined propellant tanks for future earth-to-orbit transports

OCLC:

965383789