by National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility in Edwards, Calif .
Written in English
|Statement||Leslie Gong, William L. Ko, and Robert D. Quinn|
|Series||NASA technical memorandum -- 85907|
|Contributions||Ko, William L, Quinn, Robert D, Ames Research Center|
|The Physical Object|
Get this from a library! Thermal response of space shuttle wing during reentry heating. [Leslie Gong; William L Ko; Robert D Quinn; Ames Research Center.]. computer program was used in the reentry heat transfer analysis of the space shuttle. Two typical wing cross sections and a midfuselage cross section were selected for mately 40° during the early phase of reentry). The space shuttle skins are construc- a preflight reentry heating thermal analysis of . The Space Shuttle thermal protection system (TPS) is the barrier that protected the Space Shuttle Orbiter during the searing 1, °C (3, °F) heat of atmospheric reentry.A secondary goal was to protect from the heat and cold of space while in orbit. Atmospheric entry is the movement of an object from outer space into and through the gases of an atmosphere of a planet, dwarf planet, or natural are two main types of atmospheric entry: uncontrolled entry, such as the entry of astronomical objects, space debris, or bolides; and controlled entry (or reentry) of a spacecraft capable of being navigated or following a.
A structural performance and resizing (SPAR) finite element thermal analysis computer program was used in the heat transfer analysis of the Space Shuttle Orbiter that was subjected to reentry. The shuttle's main fuel tank was covered in thermal insulation foam intended to prevent ice from forming when the tank is full of liquid hydrogen and ice could damage the shuttle if shed during lift-off. Mission STS was the th Space Shuttle launch. Planned to begin on Janu , the mission was delayed 18 times and eventually launched on Janu , following Location: Over Texas and Louisiana. This report deals with hypothetical reentry thermostructural performance of the Space Shuttle orbiter with missing or eroded thermal protection system (TPS) tiles. The original STS-5 heating (normal transition at sec) and the modified STS-5 heating (premature transition at sec) were used as . In this paper we deal with the aero-heating analysis of a reentry flight demonstrator helpful to the research activities for the design and development of a possible winged Reusable Launch Vehicle. In fact, to reduce risks in the development of next generation reusable launch vehicles, as first step it is suitable to gain deep design knowledge by means of extensive numerical computations, in.
Why does a space shuttle get hotter on reentry than on liftoff? We now know that the space shuttle Columbia burned up when it reentered Earth's . HOUSTON – Despite clearing another hurdle in efforts to prove the integrity of the shuttle Discovery’s heat shield, mission managers are still studying a puffed-up thermal blanket to ensure it. The Shuttle’s Thermal Protection System (TPS) By Dennis R. Jenkins. During the original studies of lifting-reentry vehicles during the late s and s, there had been a great debate over the relative merits of active cooling systems versus passive systems for the vehicle structure. The Space Shuttle was a partially reusable low Earth orbital spacecraft system that was operated from to by the National Aeronautics and Space Administration (NASA) as part of the Space Shuttle official program name was Space Transportation System (STS), taken from a plan for a system of reusable spacecraft of which it was the only item funded for flight: Ap