Computer Science – Performance
Scientific paper
Jan 2004
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004adspr..33.1806b&link_type=abstract
Advances in Space Research, Volume 33, Issue 10, p. 1806-1811.
Computer Science
Performance
Scientific Ballooning, Hasi Instrument, Sicily 2002 Balloon Flight Campaign
Scientific paper
A mock-up of the probe descending in the Titan atmosphere as part of the Huygens Cassini Mission was successfully launched and recovered on 30th May 2002 after a stratospheric balloon launch from the Italian Space Agency Base ``Luigi Broglio'' in Trapani, Sicily. To simulate the Huygens mission at Titan, the probe was lifted to an altitude of 32 km and then released to perform a 45 min parachute decelerated descent. The probe was hosting spares of HASI instruments, housekeeping sensors and other dedicated sensors, Beagle II UV Sensors and Huygens Tilt Sensor, for a total of 76 acquired sensor channels and sampled during the ascent, drift and descent phase. An integrated data acquisition and instrument control system was developed, based on PC architecture and soft-real-time application. Sensors channels were sampled at the nominal HASI data rates, with a max rate of 1 kHz. Software was developed for data acquisition, onboard storage and telemetry transmission satisfying all requests for real-time monitoring, diagnostic and redundancy. The main goal of this flight was to verify sensor performance and perform a realistic functional test for HASI hardware in dynamical and environmental conditions similar to those of the Titan atmosphere as well as the impact detection sequence of HASI accelerometer and HASI during ground landing. Aerodynamic study of the probe has contributed in achieving descent velocity and spin rate profiles close to the ones envisioned for the Huygens Titan descent. Profiles have been calculated by solving a system of ODE describing the translational and rotational motion of the probe through the Earth's atmosphere during parachute aided descent. Results of these calculations have driven the choice of an appropriate angle of attack of the blades in the bottom of the probe and ballast weight during flight.
Passive thermal control of the probe has also been designed and implemented in order to guarantee proper temperature ranges on critical components and instrument during all mission phases. Preliminary results of main instruments are also presented in this work.
Aboudan Alessio
Angrilli Francesco
Antonello Marco
Bastianello S.
Bettanini Carlo
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