3 edition of Thermal response of space shuttle wing during reentry heating found in the catalog.
Thermal response of space shuttle wing during reentry heating
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|
The shuttle’s color had little relevance to managing re-entry heat. The white tiles were a lightweight ceramic of silica and aluminum dioxide. They were designed to be white for the same reason the Apollo spacecraft were covered with reflective co. This image of the gouge to heat shield tiles on the space shuttle Endeavour was taken Aug. 12, using a camera on an extension boom during a focused inspection by the orbiter's crew.
Thermal Images of Shuttle Reentry Captured. shows heating patterns during the “boundary layer transition” (BLT) experiment, when NASA Author: Tudor Vieru. The shuttle orbiter was unique, in that it was protected from reentry heating not by ablative shielding, but by insulation. The ceramic tiles got all the attention (by conspicuously falling off, receiving damage, and leading to the loss of Columbi.
The Space Shuttle thermal protection system is rated for temperatures of up to °C. There's a boundary layer of air just above the TPS, outside that temperatures can reach °C. NASA used HYTHIRM to make thermal images of the orbiter during reentry. Gong, Leslie, Ko, William L., Quinn, Robert D., "Thermal Response of Space Shuttle Wing During Reentry Heating", NASA TM, June Thermal Protection Systems Expert and Material Property Database (TPSX), Web Edition Version 3, NASA Ames Research Center,
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Title: Thermal Response of Space Shuttle Wing During Reentry Heating Author: Leslie Gong, William L. Ko, and Robert D. Quinn Subject: NASA TM THERMAL RESPONSE OF SPACE SHUTTLE WING DURING REENTRY HEATING Leslie Gong,* William L.
KO,** and Robert D. Quinnt NASA Ames Research Center Dryden Flight Research Facility Edwards, California Abstract A structural performance and resizing (SPAR) finite element thermal analysis computer program. 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 Januthe mission was delayed 18 times and eventually launched on Janufollowing 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 Ovo je članak o svemirskoj letjelici, za članak o istoimenom svemirskom programu vidi Program Space Shuttle.
Space Shuttle, službeno nazvan Space Transportation System ili STS (Svemirski transportni sistem), svemirska je letjelica koju je kroz svemirsku agenciju NASA koristila vlada Sjedinjenih Država za svemirske letove s ljudskom posadom.
Prvi letovi obavljeni sua povučen je iz. Reinforced Carbon-Carbon (RCC) as in the Space Shuttle case. However, it is known that conduction-assisted radiative-cooling is an adequate thermal protection in reentry only if the heating rates are relatively low. This implies that the vehicle wing loading (W/S r) must be kept Size: 1MB.
Impacts of space shuttle thermal protection system tile on an F aircraft vertical tail [microform] / Finite-element reentry heat-transfer analysis of space shuttle orbiter [microform] / William L. Ko, Robe Thermal response of space shuttle wing during reentry heating [microform] / Leslie Gong, William L.
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA That deceleration will very gradually settle you into your seat for the reentry phase. Good-bye, free fall. Flying the space shuttle, roughly 40 minutes later, we were on the ground. The heat shield protects the cabin from nearly all reentry heating.
Under my orange launch and entry suit, I wore a water-cooled set of long johns that kept me cool. Space Shuttle [speɪs ˈʃʌtl] (engl.: svemirski čunak), službeno nazvan Space Transportation System (akr.
STS; engl.: svemirski transportni sistem), je svemirska letjelica koju kroz svemirsku agenciju NASA trenutno koristi vlada Sjedinjenih Država za svemirske letove s ljudskom posadom. Prvi letovi obavljeni sudok je predviđen za povlačenje iz upotrebe godine.
The following 14 facilities were identified in as being associated with the Space Shuttle Program: Low Turbulence Pressure Tunnel Complex; Testing on reentry vehicles began in the early s. In the s, tests performed at the facility supported the development of the Space Shuttle Orbiter, wing design and configuration details.the Space Shuttle Solid Rocket Booster) and for re-entry vehicle nose tips.
The thermal conductivity of a particular TPS material is usually proportional to the material's phenolic is a very effective ablative material, but also has high density which is undesirable. If the heat flux.When a spacecraft such as the Space Shuttle leaves orbit and reenters the atmosphere as it travels to a landing site, there is a critical period of time when all communications between the spacecraft and ground are lost.
This phenomenon is due to the tremendous heating experienced by the craft during reentry and is termed 'reentry blackout'.