USA flag logo/image

An Official Website of the United States Government

Hybrid Vibration Isolation System for Whole-Spacecraft Launch Protection

Award Information

Agency:
Department of Defense
Branch:
Missile Defense Agency
Award ID:
64311
Program Year/Program:
2003 / SBIR
Agency Tracking Number:
031-1409
Solicitation Year:
N/A
Solicitation Topic Code:
N/A
Solicitation Number:
N/A
Small Business Information
ATA Engineering, Inc
13290 EVENING CREEK DRIVE SOUTH Suite 250 San Diego, CA 92128
View profile »
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No
 
Phase 1
Fiscal Year: 2003
Title: Hybrid Vibration Isolation System for Whole-Spacecraft Launch Protection
Agency / Branch: DOD / MDA
Contract: F2960103M0289
Award Amount: $69,063.00
 

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.

Principal Investigator:

Kevin L. Napolitano
Project Engineer
8587203030
Kevin.Napolitano@ata-e.com

Business Contact:

David L. Hunt
Vice President,Business D
8587923995
dave.hunt@ata-e.com
Small Business Information at Submission:

ATA ENGINEERING, INC.
11995 El Camino Real, Suite 200 San Diego, CA 92130

EIN/Tax ID: 330900801
DUNS: N/A
Number of Employees:
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No