urn:nasa:pds:context:instrument_host:spacecraft.gp 1.1 1.15.0.0 Product_Context 2021-02-24 1.1 Changed inst LIDs from u:n:p:c:i:instID.scID to u:n:p:c:i:scID.instID And per "Guide toPDS4 Context Products" v1.7, changed all lidvid_reference to lid_reference 2016-10-01 1.0 extracted metadata from PDS3 catalog and modified to comply with PDS4 Information Model urn:nasa:pds:context:investigation:mission.galileo instrument_host_to_investigation urn:nasa:pds:context:instrument:gp.asi instrument_host_to_instrument urn:nasa:pds:context:instrument:gp.dwe instrument_host_to_instrument urn:nasa:pds:context:instrument:gp.epi instrument_host_to_instrument urn:nasa:pds:context:instrument:gp.gpms instrument_host_to_instrument urn:nasa:pds:context:instrument:gp.had instrument_host_to_instrument urn:nasa:pds:context:instrument:gp.lrd instrument_host_to_instrument urn:nasa:pds:context:instrument:gp.nep instrument_host_to_instrument urn:nasa:pds:context:instrument:gp.nfr instrument_host_to_instrument urn:nasa:pds:context:target:planet.jupiter instrument_host_to_target Yeates, C.M., T.V. Johnson, L. Colin, F.P. Fanale, L. Frank, and D.M. Hunten, Galileo: Exploration of Jupiter's System, NASA SP-479 (REPLACED BY YEATESETAL1985), 1985. reference.GLL1985 D'Amario, L.A., L.E. Bright, and A.A. Wolf, Space Science Reviews, Volume 60 Numbers 1-4, 1992, The Galileo Mission, Kluwer Academic Publishers, 1992. reference.SSR1992 GALILEO PROBE Spacecraft GP Instrument Host Overview ======================== The Galileo spacecraft consists of two parts, an orbiter (SPACECRAFT_ID = 'GO') and a probe (SPACECRAFT_ID = 'GP'). Spacecraft power is provided by two radioisotope thermoelectric generators. Propulsion is accomplished via a bipropellant system of twelve 10- newton thrusters and one 400 newton engine. The command and data subsystem consists of multiple microprocesors and a high-speed data bus. The Galileo atmospheric probe will be deployed from the orbiter 150 days prior to Jupiter encounter. The probe consists of a deceleration module and a descent module. It weighs about 331 kilograms, half of which is the heat shield. After entering the Jovian atmosphere and slowing its descent, the descent module deploys a 2.5 meter parachute and begins transmitting data from its instruments at a rate of 128 bits per second. (Refer to Yeates, et al, 1985; Johnson, et al, 1992.) Platform Description -------------------- Platform PROBE DESCENT MODULE The atmospheric descent module contains seven scientific instruments: the atmospheric structure instrument (ASI), the neutral mass spectrometer (NMS), the helium abundance detector (HAD), the nephelometer (NEP), the net-flux radiometer (NFR), the lightning and radio emissions detector (LRD), and the energetic particles instrument (EPI). The instruments are contained in hermetically sealed housings designed to withstand a pressure of 20 bars. The instrument data are transmitted to the orbiter over two simultaneously operating channels in the L band. (Refer to Yeates, et al, 1985; Johnson, et al, 1992.)