2 edition of Predictions of entry heating for lower surface of shuttle orbiter found in the catalog.
Predictions of entry heating for lower surface of shuttle orbiter
C. L. W Edwards
by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
Written in English
|Statement||C.L.W. Edwards and Stanley R. Cole|
|Series||NASA technical memorandum -- 84624|
|Contributions||Cole, Stanley R, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch|
|The Physical Object|
|Pagination||95 p. :|
|Number of Pages||95|
Experimental assessment of a computer program used in space shuttle orbiter entry heating analyses (NASA technical memorandum) [Wells, William L] on *FREE* shipping on qualifying offers. Experimental assessment of a computer program used in space shuttle orbiter entry heating analyses (NASA technical memorandum)Author: William L Wells. The following is an excerpt from the new book NASA Space Shuttle Owners’ Workshop Manual. Chapter 3: Anatomy of the Space Shuttle Author David Baker worked with .
The orbiter reentered the atmosphere as a blunt body by having a very high (40°) angle of attack, with its broad lower surface facing the direction of flight. Over 80% of the heating the orbiter experiences during reentry is caused by compression of the air ahead of the hypersonic vehicle, in accordance with the basic thermodynamic relation between pressure and temperature. The air density is very low because re-entry occurs many miles above the earth's surface. Strong shock waves are generated on the lower surface of the spacecraft. The only manned aircraft to currently fly in this regime are the American Space Shuttle, the Russian Soyuz spacecraft, and the Chinese Shenzhou spacecraft.
The facilities used at NASA Langley were the in. Mach 6, the in, Mach 6, the in. Mach 10 and the in. Mach 6 CF4 facility. The paper focuses on the high Mach, high altitude portion of the first entry of the Shuttle where the vehicle exhibited a nose-up pitching moment relative to pre-flight prediction of (Delta C(sub m)) = The facilities used at NASA Langley were the in. Mach 6, the in, Mach 6, the in. Mach 10 and the in. Mach 6 CF4 facility. The paper focuses on the high Mach, high altitude portion of the first entry of the Shuttle where the vehicle exhibited a nose-up pitching moment relative to pre-flight prediction of (Delta C(sub m)) = 0
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Surface of the Shuttle orbiter for both trajectories, and the lower-surface center line results were compared both with aerodynamic-heating design data and with flight values from the STS-1 and STS-2 trajectories. The peak laminar-heating values from the aerodynamic-heating design-data book were generally 40 to 60 percent higher than.
Averaged data from phase change paint tests compared favorably with thermocouple data for predicting heating rates. Laminar and turbulent radiation equilibrium heating rates were computed on the lower surface of the Shuttle orbiter for both trajectories, and the lower surface center line results were compared both with aerodynamic heating design data and with flight values from the Author: C.
Edwards and S. Cole. Results are presented from predictions of aerothermodynamic heating rates, temperatures, and pressures on the surface of the Shuttle Entry Air Data System (SEADS) nosecap during Orbiter reentry. These results are compared with data obtained by the first actual flight of the SEADS system aboard STSC.
The data also used to predict heating rates and surface temperatures for a. Engineering predictions of boundary layer transition and numerical simulations of the orbiter flow field were confirmed. The data tended to substantiate preflight predictions of surface catalysis phenomena.
The thermal response of the thermal protection system was as expected. Full text of "Space Shuttle orbiter entry heating and TPS response: STS-1 predictions and flight data" See other formats ^/ SPACE SHUTTLE ORBITER ENTRY HEATING AND TPS RESPONSE: STS-1 PREDICTIONS AND FLIGHT DATA Robert C.
Rled, Winston D. Goodrich, Chien P. Li, Carl D. Scott, Stephen M. Derry, and Robert J. Maraia NASA Lyndon B. Johnson Space Center Houston r Texas. SPACE SHUTTLE ORBITER THERMAL PROTECTION SYSTEM DESIGN AND FLIGHT EXPERIENCE Donald M. Curry NASNJohnson Space Center Houston, TX ABSTRACT The Space Shuttle Orbiter Thermal Protection System materials, design approaches associated with each material, and the operationalpedorm_ce experiencedduring fifty-five successful flights aredescribed.
on heating to the spacecraft’s surface during flight. This information is used in the design of the Thermal Protection System that shields the underlying structure from excessive temperatures. The design of the shuttle employed state-of-the-art aerodynamic and aerothermodynamic prediction techniques of the day and subsequently expanded them.
Full text of "Aerodynamic design of the space shuttle orbiter" The body flap also shields the exposed main engine nozzles from aerodynamic heating during entry. edge-up) control deflections, the movement of the control surface has_little effect on the boundary layer on the lower surface of the Orbiter, and consequently, the effect of M.
Shuttle Wing Loads—Testing and Modification Led to Greater Capacity Orbiter wing loads demonstrated the importance of anchoring the prediction or grounding the analysis with flight data in assuring a successful flight. The right wing of Columbia was instrumented with.
The Space Shuttle orbiter is the spaceplane component of the Space Shuttle, a partially reusable orbital spacecraft system that was part of the Space Shuttle ed by NASA, the U.S.
space agency, this vehicle could carry astronauts and payloads into low Earth orbit, perform in-space operations, then re-enter the atmosphere and land as a glider, returning its crew and any on-board Applications: Crew and cargo spaceplane.
The surface heat inputs to the thermal models were obtained from The space shuttle orbiter is designed to be used for at least missions. During each flight cycle, it must withstand the vibrations of lift-off and survive severe on the lower surface and 5 layers on the upper surface.
Both the lower. Get this from a library. Predictions of entry heating for lower surface of shuttle orbiter. [C L W Edwards; Stanley R Cole; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.].
Orbiter, the Reynolds numbers (associated with the high heating portion of atmospheric entry) are low enough to permit laminar flow if the configuration is properly controlled (ref. 16). Discontinuous surface radii of curvature are to be avoided (ref.
17). Once the. eﬀects from highly catalytic surfaces that may be present on the Orbiter TPS during atmospheric re-entry. In the event that the Orbiter becomes damaged and must re-enter the atmosphere with TPS damage exposure or repair sites, a quick surface heating analysis must be performed to determine if aerothermal heating will become problematic.
Results are presented from predictions of aerothermodynamic heating rates, temperatures, and pressures on the surface of the Shuttle Entry Air Data System (SEADS) nosecap during Orbiter reentry.
These results are compared with data obtained by the first actual flight of the SEADS system aboard STSC. Critical Hypersonic Aerothermodynamic Phenomena John J. Bertin 1, 2 pitching moment, and control surface effectiveness). The peak heat-transfer rate and the heating load, which is the heating rate integrated over time, are mapped over The demise of the Space Shuttle Orbiter Columbia during its reentry from orbit on February 1, was File Size: KB.
Near nominal heating was predicted on the remainder of the side fuselage with some lower than nominal heating on the front surface of the OMS pod. These results for missing RCC panel 9 are consistent with data from the STS re-entry where the heating augmentation was observed to move off the side fuselage and OMS pod sensors at later times.
SHUTTLE ENtrY GUIDANCE Jon C. Harpold Claude A. Graves, Jr. INTRODUCTION This paper describes the design of the entry guidance for the Space Shuttle Orbiter. This guidance provides the steering commands for trajectory control from initial penetration of the Earth's atmosphere until the terminal area guidance is activated at an Earth-relative.
of heating environments on windward surfaces of the Orbiter. On the nose cap and wing leading edge, however, the heating was even more extreme. In response, a coated carbon-carbon composite material was developed to Engineering Innovations While the re-entry surface heating of the Orbiter was predominantly convective, sufficient energy in.
shuttle orbiter re-enters the Earth’s at-mosphere, it is traveling in excess of 17, mph. To slow down to landing speed, fric-tion with the atmosphere produces exter-nal surface temperatures as high as 3, degrees Fahrenheit – well above the melting point of steel.
Special thermal shields are required to protect the vehicle and its oc. Shuttle Reference Manual The Shuttle Reference Manual, most recently revised inis an indepth technical guide to space shuttle equipment and operations. It was accurate in and while most of the information provided here from the manual .of a low-speed deployable canard to be used for approach and landing only [Ref.
1]. Two hour wind tunnel tests were conducted in a 7' X I1' low-speed wind tunnel with a scale model of the current Orbiter employing some suitable devices.
Canards at two longitudinal stations, X0=" and.RCC Plug Repair Thermal Tools for Shuttle Mission Support To utilize the thermal model for flight analyses, accurate predictions of protuberance heating were required.
Wind on the wing leading edge on the Panel 8 lower surface. The temperature and heating environments are shown in Figure 3.