Computer Science – Performance
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.931l&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Computer Science
Performance
Scientific paper
Within the frame of the Ariane 5 Plus programme, Europe is developing a new cryogenic upper stage ESC. In order to maintain the ARIANE 5 international competitive edge, Europe decided to enhance the payload capacity of its new workhorse by adding a cryogenic upper stage enabling up to 12 tons to be delivered into a Geostationary Transfer Orbit. A two-step approach was decided in order to meet the near future and long-term market demand. The first step consists of developing an intermediate version named ESC- A utilising the propulsion system components and engine from the Ariane 4 launcher vehicle 3rd (cryogenic) stage within a new structure. In the second step the B-version will follow based on ESC-A but utilising a new propulsion system and a new expander cycle engine. This paper describes the definition and performance characteristics of ESC-A and presents the qualification philosophy applied for the Ariane 4 reused equipment and also for the new equipment and substructures under the stringent schedule constraints. The qualification test phase is well under way with the first flight of ESC-A scheduled second half of 2002. On stage level two qualification test items are built and tested: one stage for mechanical qualification, and a second stage for qualifying the ground/launcher interface and thermal system during filling and draining of the stage. On subsystem level the mechanical qualification (stiffness and strength) for the new LH2-Tank, the Interstage Structure, and the stage internal structures are performed. Functional qualification of ESCA is performed without a hot firing test. The propulsion system and engine are already qualified for Ariane 4 - H10; therefore only complementary qualification for ESC-A environment is necessary (increased firing time, different dynamic and thermal environment). This is supported by specific functional tests, for example pressurisation loop tests, LH2 feeding system test, LH2 and LOX sloshing tests, LOX draining tests, and engine hot firing tests under the ESC-A conditions. An overview of these qualification tests is given resulting in a qualified stage ready for the first flight.
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