Hybrid Vibration Isolation System for Whole-Spacecraft Launch Protection

Award Information
Agency:
Department of Defense
Amount:
$69,063.00
Program:
SBIR
Contract:
F2960103M0289
Solitcitation Year:
N/A
Solicitation Number:
N/A
Branch:
Missile Defense Agency
Award Year:
2003
Phase:
Phase I
Agency Tracking Number:
031-1409
Solicitation Topic Code:
N/A
Small Business Information
ATA ENGINEERING, INC.
11995 El Camino Real, Suite 200, San Diego, CA, 92130
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
133709001
Principal Investigator
 Kevin Napolitano
 Project Engineer
 (858) 720-3030
 Kevin.Napolitano@ata-e.com
Business Contact
 David Hunt
Title: Vice President,Business D
Phone: (858) 792-3995
Email: dave.hunt@ata-e.com
Research Institution
N/A
Abstract
The proposal describes an active and passive system that will supplement a passive isolation system.The baseline passive isolation system consists of a graphite epoxy/honeycomb core laminate formed into an essentially flat plate. An integral low-bending-stiffness outer band provides the capability to tune the modal frequencies of the system to achievesignificant levels of payload isolation. Constrained layer damping is used to damp at the isolator vertical mode.Further reduction in response is possible if the passive isolation frequency is reduced. However, this is limited by concerns that rocking mode response is too high. Unfortunately, passive vertical stiffness of the diaphragm affects both vertical androcking frequencies.The opportunity here is to use active controls or other passive means to mitigate rocking mode response. Sensors will differentiate between rocking modes and the primary vertical mode. Actuators will be used to independently control either rocking orvertical motion. After rocking motion has been suppressed, the passive system is modified so that the vertical frequency near 30 Hz is lowered without subjecting the payload to increased lateral motion.The active system can also be used to add supplemental isolation in a critical frequency band and to minimize effects of initial loading. Fragile structures may be launched from ICBMs. Also, since increased payload isolation has the potential to save spacecraft structural weight, an active/passive hybrid isolation system may have a competitive advantage over traditional passive isolationsystems.

* information listed above is at the time of submission.

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