This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
A Summary of the Cassini Spacecraft Thermal Performance from Launch Through Early Cruise
Annotation ability available
Sector:
Language:
English
Abstract
Cassini, NASA's mission to investigate the Saturnian system was launched successfully on October 15, 1997. The cruise period from launch until Saturn arrival takes the spacecraft through a wide range of solar/thermal environments (0.67 astronomical units [AU] to 10 AU). The thermal control approach, which consists of thermal design features and operational constraints, must therefore maintain hardware temperature limits throughout this wide range of environments.
The off-sun exposure flight experience with interplanetary spacecraft at relatively close heliocentric distance is very limited. Cassini's ability to perform off-sun maneuvers relies heavily on the large thermal capacitance of the spacecraft's central body and the relatively short off-sun durations required for these maneuvers. The post launch execution of the first trajectory correction maneuver (TCM-1) was the first opportunity to validate the spacecraft off-sun capability and to enhance the thermal math model simulation capability.
Authors
- Arturo Avila - Jet Propulsion Lab., California Institute of Technology
- Nazilla Rouse - Jet Propulsion Lab., California Institute of Technology
- Stuart Clark - Jet Propulsion Lab., California Institute of Technology
- Glenn Tsuyuki - Jet Propulsion Lab., California Institute of Technology
- Jerry Millard - Jet Propulsion Lab., California Institute of Technology
Topic
Citation
Avila, A., Rouse, N., Clark, S., Tsuyuki, G. et al., "A Summary of the Cassini Spacecraft Thermal Performance from Launch Through Early Cruise," SAE Technical Paper 981547, 1998, https://doi.org/10.4271/981547.Also In
References
- Reeve, R. “Thermal Redesign of the Galileo Spacecraft for a VEEGA Trajectory,” Journal of Spacecraft and Rockets 28 2 130 138 American Institute of Aeronautics and Astronautics Washington, D.C. March-April 1991
- Becker, R. “Functional Requirements, Mariner Jupiter/Saturn, Design Criteria for Temperature Control,” JPL Internal Document 618-205-3-210, Revision A November 1976
- Mireles, V. Tsuyuki, G. “A Summary of the Cassini System-Level Thermal Balance Test: Engineering Subsystems,” SAE Paper 97ES-287 July 1997
- Tsuyuki, G. Mireles, V. Lin, E. Avila, A. “A Summary of the Cassini System-Level Thermal Balance Test: Science Instruments,” SAE Paper 97ES-287 July 1997
- Tsuyuki, G. “Functional Requirements, Cassini Orbiter, Design Criteria for Temperature Control,” JPL Internal Document 699-205-3-210, Revision D October 1997
- Macias, J. “Flight Rules and Constraints,” JPL Internal Document 699-270, Revision C September 1997
- Avila, A. “Cassini Orbiter System Level Thermal Math Model Requirements,” JPL Internal Document D-13846, Revision A July 1997
- Juanero, K. Mireles, V. “Cassini Spacecraft System Level Solar Thermal Vacuum Test Report,” JPL Internal Document 699-255 April 1997