The basic advantage of deployable structures, their compact stowed size relative to their final deployed size, presents a significant advantage to the aerospace designer. Extremely large structures that stow into very small volumes for launch are particularly feasible with one particular type of deployable, the inflated structure. However, it is difficult to advocate the use a purely inflated structure for an orbital mission because of the risk of micrometeor puncture. Rigidizing the structure in some fashion addresses this fragility issue. Design and operational issues with respect to foam- rigidized aerospace structures are investigated in this paper. The structures are fabricated from flexible Kapton film that is formed into a cylindrical shell. The shell is injected with a hardening urethane foam to form a composite strut. The results of both static and dynamic tests of four test coupons cut from foam rigidized struts are presented. The experimentally determined structural properties are then input into a finite-element model to gain insight into the dynamic behavior of a realistic inflated-rigidized structure. As with all structures touted for aerospace use, the survivability of foam-rigidized structures in the orbital environment is of interest. This issue is investigated by damaging the test coupons in a controlled fashion and then again experimentally evaluating the static and dynamic material properties. These properties are used for sections of the finite-element model to represent damage to the structure. An evaluation of the possibility of vibration-based damage assessment is included.
|Title of host publication||16th Biennial Conference on Mechanical Vibration and Noise|
|State||Published - 1997|
|Event||ASME 1997 Design Engineering Technical Conferences, DETC 1997 - Sacramento, United States|
Duration: Sep 14 1997 → Sep 17 1997
|Name||Proceedings of the ASME Design Engineering Technical Conference|
|Conference||ASME 1997 Design Engineering Technical Conferences, DETC 1997|
|Period||9/14/97 → 9/17/97|
Bibliographical noteFunding Information:
The authors gratefully acknowledge the support of NASA through the Advanced Concepts Research Program and technical monitor Whitt Brantley of Marshall Space Flight Center. The foam rigidized test coupons used in this study were generously provided by United Applied Technologies of Huntsville, Alabama, USA. Suzanne Smith's, Alex Chapman's and Patrick Hobbs' efforts are supported under a NSF Young Investigator award.
© 1997 American Society of Mechanical Engineers (ASME). All rights reserved.
- Compression stabilized
- Material characterization
- Material properties
ASJC Scopus subject areas
- Mechanical Engineering
- Computer Graphics and Computer-Aided Design
- Computer Science Applications
- Modeling and Simulation