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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. | ||
=== Limit and failure modeling === | |||
The project contains code to simulate the various structural and aerodynamical limits as well as component failures based on sections 4 and 6 of the Space Shuttle crew manual. | |||
The general philosophy on limit modeling is that they can be treated dependent on a user setting as 'soft', 'hard' and 'realistic'. Where applicable, warnings when the state of the orbiter is getting dangerously close to a limit are called out in addition to a recommendation how to deal with the situation. Dependent on the trajectory of the orbiter, there may or may not be sufficient time to redeem the situation. | |||
<b>soft:</b> Limit violations are called out, but their violation has no consequences for aerodynamics or component failures. | |||
<b>hard:</b> Any limit violation immediately ends the simulation. | |||
<b>realistic:</b> In reality, components do not necessarily fail immediately if used outside their design specs. This option applies a probabilistic failure model in which the chance for a component to fail grows with the degree of limit violation. The failure may or may not be immediately visible, e.g. too much qbar upon ascent may damage the heat shield, but this may not be apparent (unless specifically checked) until the heat shield fails upon atmospheric entry. | |||
Component failure is modeled gradually where applicable - while a tire can only blow or not blow, an airfoil or a thruster for instance may lose a certain percentage of its efficiency. | |||
== The mated launch vehicle == | == The mated launch vehicle == | ||