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Space Shuttle: Difference between revisions
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The [http://ntrs.nasa.gov NASA technical reports server] supplies a large base of wind tunnel and in-situ performance data of both the mated launch vehicle and the orbiter, and the aerodynamics of the simulated shuttle is based on these documents. The authoritive source for procedures for trajectory management, instrumentation, limits and energency procedures is the [https://www.nasa.gov/centers/johnson/pdf/390651main_shuttle_crew_operations_manual.pdf Space Shuttle Crew Operations Manual] and currently a normal mission, i.e. ascent, orbital insertion, de-orbit, entry, terminal area energy management and landing can be flown largely 'by the book', i.e. following the real procedure for CSS. As of May 2015, this does not yet hold for emergency procedures. | The [http://ntrs.nasa.gov NASA technical reports server] supplies a large base of wind tunnel and in-situ performance data of both the mated launch vehicle and the orbiter, and the aerodynamics of the simulated shuttle is based on these documents. The authoritive source for procedures for trajectory management, instrumentation, limits and energency procedures is the [https://www.nasa.gov/centers/johnson/pdf/390651main_shuttle_crew_operations_manual.pdf Space Shuttle Crew Operations Manual] and currently a normal mission, i.e. ascent, orbital insertion, de-orbit, entry, terminal area energy management and landing can be flown largely 'by the book', i.e. following the real procedure for CSS. As of May 2015, this does not yet hold for emergency procedures. | ||
== The mated launch vehicle == | |||
At liftoff, thrust for the shuttle is provided by its three main engines (SSMEs) and the two SRBs. The assembled launch configuration has a height of 184.2 ft (56.1 m) and a mass of about 4,470,000 lb or 2.030 tons (in addition to payload), over 90% of this being propellant. The main engines would at this point be incapable of lifting the launch stack. | |||
The SRBs burn an ammonium perchlorate composite fuel with a relatively low ISP of 268 s in vacuum, supplying 2,800,000 lbf of liftoff thrust each, this is supplemented by the SSME burning liquid hydrogen/oxygen with an ISP of 455 s, supplying an additional total liftoff thrust of 1,180,000 lbf. At liftoff, the shuttle hence reaches a thrust/weight ratio over 1.6, i.e. it leaves the launch pad rapidly. | |||
== Glossary of acronyms == | |||
CSS: control stick steering <p> | |||
DAP: digital autopilot <p> | |||
ET: external tank <p> | |||
ISP: specific impulse<p> | |||
OV: orbiter vehicle<p> | |||
SRB: solid rocket booster<p> | |||
SSME: Space Shuttle main engine<p> | |||
== Latest development snapshot == | |||
The latest development version (possibly unstable) is found in a dedicated [https://sourceforge.net/projects/fgspaceshuttledev/ repository] on SourceForge. | |||
== Gallery == | == Gallery == | ||