FORMOSAT-3/COSMIC Structural Dynamic Test Verification
- Paper number
IAC-06-C2.3.02
- Author
Dr. Ming-Chih Cheng, National Space Organization, Taiwan, China
- Coauthor
Mr. J.C. Kuo, National Space Organization, Taiwan, China
- Coauthor
Mr. C.W. Chou, National Space Organization, Taiwan, China
- Coauthor
Dr. Chiuder Hsiao, National Space Organization, Taiwan, China
- Year
2006
- Abstract
This paper describes the development of structural dynamic test strategy, the execution, and results of the test verification activities of FORMOSAT-3/COSMIC (Constellation Observing System for Meteorology/Ionosphere and Climate) satellite. The satellite system is developed under collaboration between Taiwan and the US. The satellite system is a constellation of six spacecraft. Major mission is to collect meteorological sounding data through receiving signals transmitted by the 24 US GPS satellites. The satellite system in launch configuration is a stack of these six spacecraft, and they will be launched in one rocket of US Air Force’s OSP (Orbital/Sub-orbital Program)/Minotaur. Then after arriving at parking orbit, the six spacecraft will be deployed and each will separately drift to reach six different orbits at an altitude of 700~800 kilometers. For the space segment, National Space Organization (NSPO) is responsible for the System Integration and System Test Verification. FORMOSAT-3/COSMIC dynamic test program includes Vibration, Acoustic, and Shock to simulate the launch environment. Due to the six spacecraft are identical in configuration, single spacecraft and the stack can be considered in developing the test strategy in order to optimize the schedule, cost, and technical risks. Final program consists of: (1.) minimum-workmanship level random vibration tests on single spacecraft, (2.) proto-flight level random vibration test on stacked satellite, and (3.) acceptance level acoustic test on stacked satellite. Force limiting technique is applied in the random vibration tests. Rationale embedded in developing the test plan is detailed in this paper. During the execution of the testing in NSPO, insights into the design of deployable parts are explored. The deployable parts include one payload antenna boom and two solar array panels. These insights, they are documented as lessons learned, are valuable in improving the design and installation procedure. As the system verification consists of single spacecraft and stacked satellite, the uniqueness of the program lies in the effort to correlate the structural modes between single spacecraft and the stack of six spacecraft. This test-analysis correlation is presented in this paper in detail.
- Abstract document