Shuttle interaction study extension

NASA Technical Reports Server (NTRS)

1982-01-01

The following areas of Space Shuttle technology were discussed: variable altitude strategy, spacecraft servicing, propellant storage, orbiter plume impingement, space based design, mating (docking and berthing), shuttle fleet utilization, and mission/traffic model.

Radar cross section measurements of a scale model of the space shuttle orbiter vehicle

NASA Technical Reports Server (NTRS)

Yates, W. T.

1978-01-01

A series of microwave measurements was conducted to determine the radar cross section of the Space Shuttle Orbiter vehicle at a frequency and at aspect angles applicable to re-entry radar acquisition and tracking. The measurements were performed in a microwave anechoic chamber using a 1/15th scale model and a frequency applicable to C-band tracking radars. The data were digitally recorded and processed to yield statistical descriptions useful for prediction of orbiter re-entry detection and tracking ranges.

Space Shuttle Orbiter Crew Hatch Jettison Test using a 0.0405-scale model (16-0) in the Texas A/M low speed wind tunnel (OA362). Space Shuttle aerothermodynamic data report

NASA Technical Reports Server (NTRS)

Mitchell, C. E.

1992-01-01

This report contains post-test information for the Space Shuttle Orbiter Crew Hatch Jettison Test OA362 which was conducted in the Texas A&M Low Speed Wind Tunnel from 6/15/87 to 6/22/87. The test objective was to verify that the crew hatch, once jettisoned, would clear the orbiter under various simulated flight conditions. Several model hatches were used with the 0.0405-scale orbiter (Model 16-0). The model's angle of attack was set at 10, 15, and 20 degrees while the sideslip had values of minus 5, 0, and plus 5 degrees. The full scale Qbars that were simulated were 105, 128, 160, and 210 psf. In the hatch jettison mechanism itself, the plunger pressure was varied to achieve horizontal velocities of 3, 5, 7, and 20.1 feet per second model scale, and the plunger location was varied to achieve a variety of rotational velocities. The orbiter model was subjected to 122 runs with 13 different hatches. Of these, 60 were good runs.

Results of an external tank separation test in AEDC/VKF tunnel B on 0.010-scale replica of space shuttle vehicle model 52-OT(IA17A), Volume 1

NASA Technical Reports Server (NTRS)

Spangler, R. H.; Daileda, J. J.

1975-01-01

Tests were conducted on scale models of the space shuttle orbiter and external tank (ET) to determine the aerodynamic interactions during a return to launch site abort separation. The orbiter model was built to vehicle 3 configuration lines (139B) and the ET model approximated the vehicle 5 configurations with protuberances and attach hardware. For these investigations the orbiter was mounted on the primary support system and the external tank was mounted on the captive trajectory system. Six-component data were obtained for each vehicle at various orbiter angles of attack and sideslip for a range of relative angular and linear displacements of the ET from the orbiter.

Flow-field measurements in the windward surface shock layer of space shuttle orbiter configurations at Mach number 8. [wind tunnel tests of scale models

NASA Technical Reports Server (NTRS)

Martindale, W. R.; Carter, L. D.

1975-01-01

Pitot pressure and total-temperature measurements were made in the windward surface shock layer of two 0.0175-scale space shuttle orbiter models at simulated re-entry conditions. Corresponding surface static pressure measurements were also made. Flow properties at the edge of the model boundary layer were derived from these measurements and compared with values calculated using conventional methods.

Results of oil flow visualization tests of an 0.010-scale model (52-OT) of the space shuttle orbiter-tank mated and orbiter configurations in the AEDC VKF tunnel B (IA17B)

NASA Technical Reports Server (NTRS)

Daileda, J. J.

1975-01-01

An 0.010-scale model of the space shuttle (orbiter-tank mated and orbiter configurations) was tested in the AEDC VKF Tunnel B to investigate aerodynamic flow patterns. The tests utilized oil flow techniques to visualize the flow patterns. Tunnel free stream Mach number was 7.95 and nominal unit Reynolds number was 3.7 million per foot. Model angle of attack was varied from -5 deg through 10 deg and angle of sideslip was 0 deg and 2 deg. Photographs of resulting oil flow patterns are presented.

Results of tests of a Rockwell International space shuttle orbiter (-139 configuration) 0.0175-scale model (no. 29-0) in AEDC tunnel F to determine hypersonic heating effects (OH11)

NASA Technical Reports Server (NTRS)

Quan, M.

1975-01-01

Results from wind tunnel tests to determine hypersonic aerodynamic heating rates on a NASA/Rockwell Space Shuttle Orbiter are reported. The tests were to determine Mach number effects, if any, and to obtain overall heating rate data at high Mach numbers from 10.5 to 16. The model used was a 0.0175-scale model built to Rockwell Orbiter lines VL70-000139. The model identity number is 29-0. These tests, designated OH11, were conducted in the AEDC Tunnel F.

Pressure loads and aerodynamic force information for the -89A space shuttle orbiter configuration, volume 2

NASA Technical Reports Server (NTRS)

Mennell, R. C.

1973-01-01

Experimental aerodynamic investigations were conducted in a low speed wind tunnel on an 0.0405 scale representation of the 89A light weight Space Shuttle Orbiter to obtain pressure loads data in the presence of the ground for orbiter structural strength analysis. The model and the facility are described, and data reduction is outlined. Tables are included for data set/run number collation, data set/component collation, model component description, and pressure tap locations by series number. Tabulated force and pressure source data are presented.

CFD Analysis of Tile-Repair Augers for the Shuttle Orbiter Re-Entry Aeroheating

NASA Technical Reports Server (NTRS)

Mazaheri, Ali R.

2007-01-01

A three-dimensional aerothermodynamic model of the shuttle orbiter's tile overlay repair (TOR) sub-assembly is presented. This sub-assembly, which is an overlay that covers the damaged tiles, is modeled as a protuberance with a constant thickness. The washers and augers that serve as the overlay fasteners are modeled as cylindrical protuberances with constant thicknesses. Entry aerothermodynamic cases are studied to provide necessary inputs for future thermal analyses and to support the space-shuttle return-to-flight effort. The NASA Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA) is used to calculate heat transfer rate on the surfaces of the tile overlay repair and augers. Gas flow is modeled as non-equilibrium, five species air in thermal equilibrium. Heat transfer rate and surface temperatures are analyzed and studied for a shuttle orbiter trajectory point at Mach 17.85. Computational results show that the average heat transfer rate normalized with respect to its value at body point 1800 is about BF=1.9 for the auger head. It is also shown that the average BF for the auger and washer heads is about BF=2.0.

Effect of reaction control system jet-flow field interactions on a 0.015 scale model space shuttle orbiter aerodynamic characteristics

NASA Technical Reports Server (NTRS)

Monta, W. J.; Rausch, J. R.

1973-01-01

The effects of the reaction control system (RCS) jet-flow field interactions on the space shuttle orbiter system during entry are discussed. The primary objective of the test program was to obtain data for the shuttle orbiter configuration to determine control amplification factors resulting from jet interaction between the RCS plumes and the external flow over the vehicle. A secondary objective was to provide data for comparison and improvement of analytic jet interaction prediction techniques. The test program was divided into two phases; (1) force and moment measurements were made with and without RCS blowing, investigating environment parameters (R sub e, Alpha, Beta), RCS plume parameters (Jet pressure ratio, momentum ratio and thrust level), and geometry parameters (RCS pod locations) on the orbiter model, (2) oil flow visualization tests were conducted on a dummy balance at the end of the test.

STS-40 orbital acceleration research experiment flight results during a typical sleep period

NASA Technical Reports Server (NTRS)

Blanchard, Robert C.; Nicholson, John Y.; Ritter, James R.

1992-01-01

The Orbital Acceleration Research Experiment (OARE), an electrostatic accelerometer package with complete on-orbit calibration capabilities was flown aboard Shuttle on STS-40. The instrument is designed to measure and record the Shuttle aerodynamic acceleration environment from the free molecule flow regime through the rarefied flow transition into the hypersonic continuum regime. Because of its sensitivity, the OARE instrument detects aerodynamic behavior of the Shuttle while in low-earth orbit. A 2-h orbital time period on day seven of the mission, when the crew was asleep and other spacecraft activities were at a minimum, was examined. Examination of the model with the flight data shows the instrument to be sensitive to all major expected low-frequency acceleration phenomena; however, some erratic instrument bias behavior persists in two axes. In these axes, the OARE data can be made to match a comprehensive atmospheric-aerodynamic model by making bias adjustments and slight liner corrections for drift.

NASA Shuttle Orbiter Reinforced Carbon Carbon (RCC) Crack Repair Arc-Jet Testing

NASA Technical Reports Server (NTRS)

Clark, ShawnDella; Larin, Max; Rochelle, Bill

2007-01-01

This NASA study demonstrates the capability for testing NOAX-repaired RCC crack models in high temperature environments representative of Shuttle Orbiter during reentry. Analysis methods have provided correlation of test data with flight predictions. NOAX repair material for RCC is flown on every STS flight in the event such a repair is needed. Two final test reports are being generated on arc-jet results (both calibration model runs and repaired models runs).

Flutter tests (IS4) of the 0.0125-scale shuttle reflection plane model 30-OTS in the Langley Research Center 26-inch transonic blowdown tunnel test no. 547

NASA Technical Reports Server (NTRS)

Kotch, M. A.

1974-01-01

A series of slab wing flutter models with rigid orbiter fuselage, external tank, and SRB models of the space shuttle were tested, in a reflection plane arrangement, in the NASA Langley Research Center's 26-inch Transonic Blowdown Tunnel. Model flutter boundaries were obtained for both a wing-alone configuration and a wing-with-orbiter, tank and SRB configuration. Additional test points were taken of the wing-with-orbiter configuration, as a correlation with the wing-alone condition. A description of the wind tunnel models and test procedures utilized in the experiment are provided.

Aerodynamic and base heating studies on space shuttle configurations

NASA Technical Reports Server (NTRS)

1974-01-01

Heating rate and pressure measurements were obtained on a 25-O space shuttle model in a vacuum chamber. Correlation data on windward laminar and turbulent boundary layers and leeside surfaces of the space shuttle orbiter are included.

STS-40 orbital acceleration research experiment flight results during a typical sleep period

NASA Technical Reports Server (NTRS)

Blanchard, R. C.; Nicholson, J. Y.; Ritter, J. R.

1992-01-01

The Orbital Acceleration Research Experiment (OARE), an electrostatic accelerometer package with complete on-orbit calibration capabilities, was flown for the first time aboard the Space Shuttle on STS-40. This is also the first time an accelerometer package with nano-g sensitivity and a calibration facility has flown aboard the Space Shuttle. The instrument is designed to measure and record the Space Shuttle aerodynamic acceleration environment from the free molecule flow regime through the rarified flow transition into the hypersonic continuum regime. Because of its sensitivity, the OARE instrument defects aerodynamic behavior of the Space Shuttle while in low-earth orbit. A 2-hour orbital time period on day seven of the mission, when the crew was asleep and other spacecraft activities were at a minimum, was examined. During the flight, a 'trimmed-mean' filter was used to produce high quality, low frequency data which was successfully stored aboard the Space Shuttle in the OARE data storage system. Initial review of the data indicated that, although the expected precision was achieved, some equipment problems occurred resulting in uncertain accuracy. An acceleration model which includes aerodynamic, gravity-gradient, and rotational effects was constructed and compared with flight data. Examination of the model with the flight data shows the instrument to be sensitive to all major expected low frequency acceleration phenomena; however, some erratic instrument bias behavior persists in two axes. In these axes, the OARE data can be made to match a comprehensive atmospheric-aerodynamic model by making bias adjustments and slight linear corrections for drift. The other axis does not exhibit these difficulties and gives good agreement with the acceleration model.

Shuttle Return To Flight Experimental Results: Cavity Effects on Boundary Layer Transition

NASA Technical Reports Server (NTRS)

Liechty, Derek S.; Horvath, Thomas J.; Berry, Scott A.

2006-01-01

The effect of an isolated rectangular cavity on hypersonic boundary layer transition of the windward surface of the Shuttle Orbiter has been experimentally examined in the Langley Aerothermodynamics Laboratory in support of an agency-wide effort to prepare the Shuttle Orbiter for return to flight. This experimental study was initiated to provide a cavity effects database for developing hypersonic transition criteria to support on-orbit decisions to repair a damaged thermal protection system. Boundary layer transition results were obtained using 0.0075-scale Orbiter models with simulated tile damage (rectangular cavities) of varying length, width, and depth. The database contained within this report will be used to formulate cavity-induced transition correlations using predicted boundary layer edge parameters.

Hypersonic rarefied-flow aerodynamics inferred from Shuttle Orbiter acceleration measurements

NASA Technical Reports Server (NTRS)

Blanchard, R. C.; Hinson, E. W.

1989-01-01

Data obtained from multiple flights of sensitive accelerometers on the Space Shuttle Orbiter during reentry have been used to develop an improved aerodynamic model for the Orbiter normal- and axial-force coefficients in hypersonic rarefied flow. The lack of simultaneous atmospheric density measurements was overcome in part by using the ratio of normal-to-axial acceleration, in which density cancels, as a constraint. Differences between the preflight model and the flight-acceleration-derived model in the continuum regime are attributed primarily to real gas effects. New insights are gained into the variation of the force coefficients in the transition between the continuum regime and free molecule flow.

Results from investigations in three NASA/LaRC hypersonic wind tunnels on a .004 scale model space shuttle orbiter (model 13P-O) to determine real gas effects (LA78, LA87, LA88)

NASA Technical Reports Server (NTRS)

Ball, J. W.; Klug, G. W.

1976-01-01

Results from tests in the NASA/CF4, 20 inch Mach 6 and the 22 inch Helium Tunnel consist of pressure measurements on the lower surfaces of the Rockwell Space Shuttle Orbiter. All data are in absolute pressures. Data were recorded with the model at a Mach number of 6 and 20 at angles of 10 deg to 30 deg.

Results of tests in the AEDC VKF Tunnel B using the phase change paint technique on 0.04 scale 50 percent forebody models (82-0) of the Rockwell space shuttle orbiter (OH50A)

NASA Technical Reports Server (NTRS)

Quan, M.

1976-01-01

Model information and data from wind tunnel tests conducted on 0.04 scale 50 percent forebody models of the Space Shuttle Orbiter were presented. These tests were conducted using the phase change paint technique to determine aerodynamic heating rates due to various proturberances and recessions. Angles of attack from 20 deg through 45 deg were investigated at Mach 8.

Abort staging characteristics of an external oxygen tank separating from the space shuttle 040-A orbiter (.006 scale model) at Mach numbers of 0.6, 2.0, and 4.0

NASA Technical Reports Server (NTRS)

Fossler, I. H.; Cole, P.

1972-01-01

Experimental aerodynamic investigations were conducted on a .006 scale model of the space shuttle 040-A orbiter and its external fuel tank utilizing the NASA/MFSC dual sting support system in the MFSC 14 x 14 inch Trisonic Wind Tunnel. Normal force, pitching moment and axial force components were recorded simultaneously on the orbiter and the tank at selected tank field positions beneath the orbiter as both models were pitched through an angle of attack range of -5 deg to 20 deg. Incidence angles between orbiter and tank of 0 deg, 5 deg, 10 deg and 15 deg were investigated. During these tests Mach number was set at 0.6, 2.0 and 4.0.

Ku-band system design study and TDRSS interface analysis

NASA Technical Reports Server (NTRS)

Lindsey, W. C.; Mckenzie, T. M.; Choi, H. J.; Tsang, C. S.; An, S. H.

1983-01-01

The capabilities of the Shuttle/TDRSS link simulation program (LinCsim) were expanded to account for radio frequency interference (RFI) effects on the Shuttle S-band links, the channel models were updated to reflect the RFI related hardware changes, the ESTL hardware modeling of the TDRS communication payload was reviewed and evaluated, in LinCsim the Shuttle/TDRSS signal acquisition was modeled, LinCsim was upgraded, and possible Shuttle on-orbit navigation techniques was evaluated.

An analysis of the booster plume impingement environment during the space shuttle nominal staging maneuver

NASA Technical Reports Server (NTRS)

Wojciechowski, C. J.; Penny, M. M.; Greenwood, T. F.; Fossler, I. H.

1972-01-01

An experimental study of the plume impingement heating on the space shuttle booster afterbody resulting from the space shuttle orbiter engine plumes was conducted. The 1/100-scale model tests consisted of one and two orbiter engine firings on a flat plate, a flat plate with a fin, and a cylinder model. The plume impingement heating rates on these surfaces were measured using thin film heat transfer gages. Results indicate the engine simulation is a reasonable approximation to the two engine configuration, but more tests are needed to verify the plume model of the main engine configuration. For impingment, results show models experienced laminar boundary layer convective heating. Therefore, tests at higher Reynolds numbers are needed to determine impingment heating.

Space-Shuttle Emulator Software

NASA Technical Reports Server (NTRS)

Arnold, Scott; Askew, Bill; Barry, Matthew R.; Leigh, Agnes; Mermelstein, Scott; Owens, James; Payne, Dan; Pemble, Jim; Sollinger, John; Thompson, Hiram;

Shuttle optical environment; Proceedings of the Meeting, Washington, DC, April 23, 24, 1981

NASA Technical Reports Server (NTRS)

Miller, E. R. (Editor); Fazio, G. G.

1982-01-01

The numerical modeling, instrumentation, identification, and procedures to characterize and/or control contamination hazards to equipment used on the Shuttle are discussed. On-orbit pollutants include molecular offgassing and outgassing, particulate material, and substances from thrusters, vents, and leaks. Clean-rooms are being implemented in ground assembly and integration facilities. Attention is given to an upgraded SPACE program for numerically modeling contamination pathways and appropriate procedures to protect instrumentation from film and particulate deposition. Finally, attention is given to military cryogenic IR detectors being employed to quantify the Shuttle thermal and solid pollutant environment on-orbit as a prelude to future operational IR sensors.

Investigation of electrodynamic stabilization and control of long orbiting tethers

NASA Technical Reports Server (NTRS)

Colombo, G.; Arnold, D.

1984-01-01

The state-of-the-art in tether modelling among participants in the Tethered Satellite System (TSS) Program, the slack tether and its behavior, and certain advanced applications of the tether to problems in orbital mechanics are identified. The features and applications of the TSS software set are reviewed. Modelling the slack tether analytically with as many as 50 mass points and the application of this new model to a study of the behavior of a broken tether near the Shuttle are described. A reel control algorithm developed by SAO and examples of its use are described, including an example which also demonstrates the use of the tether in transferring a heavy payload from a low-orbiting Shuttle to a high circular orbit. Capture of a low-orbiting payload by a Space Station in high circular orbit is described. Energy transfer within a dumbbell-type spacecraft by cyclical reeling operations or gravitational effects on the natural elasticity of the connecting tether, it is shown, can circularize the orbit of the spacecraft.

Heat transfer tests on a 0.01-scale Rockwell configuration 3 space shuttle orbiter and tank (37-OT) in the Calspan 48-inch hypersonic shock tunnel (OH12/IH21), volume 1

NASA Technical Reports Server (NTRS)

Kotch, M.

1975-01-01

Model information and data are presented from wind tunnel tests conducted on 0.01-scale models of the space shuttle orbiter and external tank. These tests were conducted in a hypersonic shock tunnel to determine heating rates on ascent and reentry configurations at various Reynolds numbers, Mach numbers, and angles of attack.

Direct Simulation Monte Carlo Calculations in Support of the Columbia Shuttle Orbiter Accident Investigation

NASA Technical Reports Server (NTRS)

Gallis, Michael A.; LeBeau, Gerald J.; Boyles, Katie A.

2003-01-01

The Direct Simulation Monte Carlo method was used to provide 3-D simulations of the early entry phase of the Shuttle Orbiter. Undamaged and damaged scenarios were modeled to provide calibration points for engineering "bridging function" type of analysis. Currently the simulation technology (software and hardware) are mature enough to allow realistic simulations of three dimensional vehicles.

Results of a space shuttle vehicle ferry configuration afterbody fairing optimization study using a 140A/B 0.0405-scale model orbiter (43-0) in the Rockwell International 7.75 by 11.0 ft low speed wind tunnel (OA124)

NASA Technical Reports Server (NTRS)

Houlihan, S. R.

1975-01-01

Experimental aerodynamic investigations were conducted on a dual-strut mounted 0.0405-scale representation of the 140A/B outer mold line space shuttle orbiter vehicle. The tests, conducted from 11 Oct., 1974 through 22 Oct., 1974, were primarily to investigate aerodynamic stability and control characteristics of the space shuttle orbiter ferry configuration. Four afterbody fairing configurations and various additions to them in the form of horizontal and ventral fins strakes and other aerodynamic protuberances were tested. Base line data on the basic orbiter with MPS nozzles and bodyflap were recorded. The drag of the optimum ferry configuration was increased to the level of the basic orbiter for possible flight test configurations by the addition of two sizes of perforated speed brakes on the tail cone surface.

Aerodynamic results of a support system interference effects test conducted at NASA/LaRC UPWT using an 0.015-scale model of the configuration 140A/B SSV orbiter (0A20B)

NASA Technical Reports Server (NTRS)

Campbell, J. H., II; Embury, W. R.

1974-01-01

An experimental aerodynamic investigation was conducted to determine the interference effects of a wind tunnel support system. The test article was a 0.015 scale model of the space shuttle orbiter. The primary objective of the test was to determine the extent that aerodynamic simulation of the space shuttle orbiter is affected by base mounting the model, without nozzles, on a straight sting. Two support systems were tested. The characteristics of the support systems are described. Data from the tests are presented in the form of graphs and tables.

Results of tests on a Rockwell International space shuttle orbiter (-139 configuration) 0.0175-scale model (no. 29-0) in AEDC tunnel B to determine boundary layer characteristics

NASA Technical Reports Server (NTRS)

Quan, M.

1975-01-01

Results of wind tunnel tests were conducted to determine boundary layer characteristics on the lower surface of a space shuttle orbiter. Total pressure and temperature profile data at various model stations were obtained using a movable, four-degree-of-freedom probe mechanism and static pressure taps on the model surface. During a typical run, the probe was located over a preselected model location, then driven down through the bondary layer until contact was made with the model surface.

Design of a space shuttle structural dynamics model

NASA Technical Reports Server (NTRS)

1972-01-01

A 1/8 scale structural dynamics model of a parallel burn space shuttle has been designed. Basic objectives were to represent the significant low frequency structural dynamic characteristics while keeping the fabrication costs low. The model was derived from the proposed Grumman Design 619 space shuttle. The design includes an orbiter, two solid rocket motors (SRM) and an external tank (ET). The ET consists of a monocoque LO2 tank an interbank skirt with three frames to accept SRM attachment members, an LH2 tank with 10 frames of which 3 provide for orbiter attachment members, and an aft skirt with on frame to provide for aft SRM attachment members. The frames designed for the SRM attachments are fitted with transverse struts to take symmetric loads.

Shuttle derived atmospheric density model. Part 2: STS atmospheric implications for AOTV trajectory analysis, a proposed GRAM perturbation density model

NASA Technical Reports Server (NTRS)

Findlay, J. T.; Kelly, G. M.; Troutman, P. A.

1984-01-01

A perturbation model to the Marshall Space Flight Center (MSFC) Global Reference Atmosphere Model (GRAM) was developed for use in the Aeroassist Orbital Transfer Vehicle (AOTV) trajectory and analysis. The model reflects NASA Space Shuttle experience over the first twelve entry flights. The GRAM was selected over the Air Force 1978 Reference Model because of its more general formulation and wider use throughout NASA. The add-on model, a simple scaling with altitude to reflect density structure encountered by the Shuttle Orbiter was selected principally to simplify implementation. Perturbations, by season, can be utilized to minimize the number of required simulations, however, exact Shuttle flight history can be exercised using the same model if desired. Such a perturbation model, though not meteorologically motivated, enables inclusion of High Resolution Accelerometer Package (HiRAP) results in the thermosphere. Provision is made to incorporate differing perturbations during the AOTV entry and exit phases of the aero-asist maneuver to account for trajectory displacement (geographic) along the ground track.

The 0.040-scale space shuttle orbiter base heating model tests in the Lewis Research Center space power facility

NASA Technical Reports Server (NTRS)

Dezelick, R. A.

1976-01-01

Space shuttle base heating tests were conducted using a 0.040-scale model in the Plum Brook Space Power Facility of The NASA Lewis Research Center. The tests measured heat transfer rates, pressure distributions, and gas recovery temperatures on the orbiter vehicle 2A base configuration resulting from engine plume impingement. One hundred and sixty-eight hydrogen-oxygen engine firings were made at simulated flight altitudes ranging from 120,000 to 360,000 feet.

Space shuttle: Aerodynamic heating tests of the MDAC delta wing orbiter and canard booster

NASA Technical Reports Server (NTRS)

Andresen, T. L.

1972-01-01

Design of an efficient thermal protection system for the space shuttle orbiter and booster is discussed, based on knowledge of the thermal environment to be experienced by the vehicles in all flight phases. The complex configurations of these vehicles limit the level of confidence which can be associated with purely analytical thermal environment predictions. Tests were conducted during April and May 1971 using an orbiter and booster model at a 96-in. hypersonic shock tunnel. Both models were tested separately as well as together. A sufficiently large range in Reynolds number was covered so that laminar, transitional, and turbulent data could be obtained.

Experimental and theoretical study of shuttle lee-side heat transfer rates

NASA Technical Reports Server (NTRS)

Mruk, G. K.; Bertin, J.; Lamb, J. P.

1975-01-01

The experimental program which was conducted in the Calspan 96-inch hypersonic shock tunnel to investigate what effect the windward surface temperature had on the heat transfer to the leeward surface of the space shuttle orbiter is discussed. Heat-transfer distributions, surface-pressure distributions, and schlieren photographs were obtained for an 0.01-scale model of the 139 configuration space shuttle orbiter at angles-of-attack of 30 and 40 deg. Similar data were obtained for an 0.01 scale wingless model of the 139 configuration at angles-of-attack of 30 and 90 deg. Data were obtained for Mach numbers from Reynolds numbers, and surface temperatures and compared with theoretical results.

Results of investigations (OA20C) on an 0.015-scale configuration 140A/B space shuttle vehicle orbiter model (49-0) in the NASA/Langley Research Center Unitary Plan Wind Tunnel

NASA Technical Reports Server (NTRS)

Nichols, M. E.

1974-01-01

Data obtained from the wind tunnel tests of a scale model of the space shuttle orbiter configuration 140 A/B are presented. The test was conducted at Mach numbers of 2.5, 3.9, and 4.6 with Reynolds numbers from 1.25 million per foot to 5.0 million per foot. Various control surface settings were used ranging from an angle of attack range from minus 4 to plus 42 degrees at zero angle of yaw. Longitudinal stability and control characteristics of the space shuttle configuration were analyzed.

STS-99 Shuttle Radar Topography Mission Stability and Control

NASA Technical Reports Server (NTRS)

Hamelin, Jennifer L.; Jackson, Mark C.; Kirchwey, Christopher B.; Pileggi, Roberto A.

2001-01-01

The Shuttle Radar Topography Mission (SRTM) flew aboard Space Shuttle Endeavor February 2000 and used interferometry to map 80% of the Earth's landmass. SRTM employed a 200-foot deployable mast structure to extend a second antenna away from the main antenna located in the Shuttle payload bay. Mapping requirements demanded precision pointing and orbital trajectories from the Shuttle on-orbit Flight Control System (PCS). Mast structural dynamics interaction with the FCS impacted stability and performance of the autopilot for attitude maneuvers and pointing during mapping operations. A damper system added to ensure that mast tip motion remained with in the limits of the outboard antenna tracking system while mapping also helped to mitigate structural dynamic interaction with the FCS autopilot. Late changes made to the payload damper system, which actually failed on-orbit, required a redesign and verification of the FCS autopilot filtering schemes necessary to ensure rotational control stability. In-flight measurements using three sensors were used to validate models and gauge the accuracy and robustness of the pre-mission notch filter design.

Mated aerodynamic characteristics investigation for the 0.04 scale model TE 1065 (Boeing 747-100) of the 747 CAM and the 0.0405 scale model (43-0) of the space shuttle orbiter in the NASA Langley V/STOL transition research wind tunnel (CA8), volume 1

NASA Technical Reports Server (NTRS)

1976-01-01

Aerodynamic force data are presented in tables and graphs for the NASA Langley V/STOL Transition Research Wind Tunnel tests on a 0.04 scale model of the 747 with a 0.0405 scale Orbiter space shuttle. The investigation included the effects of flap setting, stabilizer angle, elevator angle, ground proximity, and Orbiter tailcone fairing. Data were obtained in the pitch plane only. The test was run at M = 0.15, with a dynamic pressure of 35 psf. Six static pressures were measured on each side of the 747 CAM nose to determine the effects of the Orbiter on the 747 airspeed and altitude indicators.

The NASA Dryden 747 Shuttle Carrier Aircraft crew poses in an engine inlet

NASA Technical Reports Server (NTRS)

2000-01-01

The NASA Dryden 747 Shuttle Carrier Aircraft crew poses in an engine inlet; Standing L to R - aircraft mechanic John Goleno and SCA Team Leader Pete Seidl; Kneeling L to R - aircraft mechanics Todd Weston and Arvid Knutson, and avionics technician Jim Bedard NASA uses two modified Boeing 747 jetliners, originally manufactured for commercial use, as Space Shuttle Carrier Aircraft (SCA). One is a 747-100 model, while the other is designated a 747-100SR (short range). The two aircraft are identical in appearance and in their performance as Shuttle Carrier Aircraft. The 747 series of aircraft are four-engine intercontinental-range swept-wing 'jumbo jets' that entered commercial service in 1969. The SCAs are used to ferry space shuttle orbiters from landing sites back to the launch complex at the Kennedy Space Center, and also to and from other locations too distant for the orbiters to be delivered by ground transportation. The orbiters are placed atop the SCAs by Mate-Demate Devices, large gantry-like structures which hoist the orbiters off the ground for post-flight servicing, and then mate them with the SCAs for ferry flights.

The NASA Dryden 747 Shuttle Carrier Aircraft crew poses in an engine inlet

NASA Image and Video Library

2000-02-03

The NASA Dryden 747 Shuttle Carrier Aircraft crew poses in an engine inlet; Standing L to R - aircraft mechanic John Goleno and SCA Team Leader Pete Seidl; Kneeling L to R - aircraft mechanics Todd Weston and Arvid Knutson, and avionics technician Jim Bedard NASA uses two modified Boeing 747 jetliners, originally manufactured for commercial use, as Space Shuttle Carrier Aircraft (SCA). One is a 747-100 model, while the other is designated a 747-100SR (short range). The two aircraft are identical in appearance and in their performance as Shuttle Carrier Aircraft. The 747 series of aircraft are four-engine intercontinental-range swept-wing "jumbo jets" that entered commercial service in 1969. The SCAs are used to ferry space shuttle orbiters from landing sites back to the launch complex at the Kennedy Space Center, and also to and from other locations too distant for the orbiters to be delivered by ground transportation. The orbiters are placed atop the SCAs by Mate-Demate Devices, large gantry-like structures which hoist the orbiters off the ground for post-flight servicing, and then mate them with the SCAs for ferry flights.

Experimental investigations of an 0.0405 scale space shuttle configuration 3 orbiter to determine subsonic stability characteristics (OA21A/OA21B), volume 2

NASA Technical Reports Server (NTRS)

Cameron, B. W.; Ritschel, A. J.

1974-01-01

Aerodynamic investigations were conducted in a low speed wind tunnel from June 18 through June 25, 1973 on a 0.0405 scale -139B model Space Shuttle Vehicle orbiter. The purpose of the test was to investigate the longitudinal and lateral-directional subsonic aerodynamic characteristics of the proposed PRR Space Shuttle Orbiter. Emphasis was placed on component buildup effects, elevon, rudder, body flaps, rudder flare effectiveness, and canard and speed brake development. Angles of attack from -4 to 24 and angles of sideslip of -10 to 10 were tested. Static pressures were recorded on the base. The aerodynamic force balance results are presented in plotted and tabular form.

Pressure distributions obtained on a 0.10-scale model of the Space Shuttle Orbiter's forebody in the Ames Unitary Plan Wind Tunnel

NASA Technical Reports Server (NTRS)

Siemers, P. M., III; Henry, M. W.

1986-01-01

Pressure distribution test data obtained on a 0.10-scale model of the forward fuselage of the Space Shuttle Orbiter are presented without analysis. The tests were completed in the Ames Unitary Wind Tunnel (UPWT). The UPWT tests were conducted in two different test sections operating in the continuous mode, the 8 x 7 feet and 9 x 7 feet test sections. Each test section has its own Mach number range, 1.6 to 2.5 and 2.5 to 3.5 for the 9 x 7 feet and 8 x 7 feet test section, respectively. The test Reynolds number ranged from 1.6 to 2.5 x 10 to the 6th power ft and 0.6 to 2.0 x 10 to the 6th power ft, respectively. The tests were conducted in support of the development of the Shuttle Entry Air Data System (SEADS). In addition to modeling the 20 SEADS orifices, the wind-tunnel model was also instrumented with orifices to match Development Flight Instrumentation (DFI) port locations that existed on the Space Shuttle Columbia (OV-102) during the Orbiter Flight test program. This DFI simulation has provided a means for comparisons between reentry flight pressure data and wind-tunnel and computational data.

Heat transfer tests of an 0.006-scale thin skin space shuttle thermocouple model (41-0) in the Langley Research Center variable density tunnel at M equals 8 (OH13)

NASA Technical Reports Server (NTRS)

Walstad, D. G.

1974-01-01

Orbiter entry heating distributions were obtained, and phase change paint data was correlated with thermocouple data during a program of heat transfer testing on a 0.006 scale space shuttle orbiter vehicle. The orbiter was tested at 0, 30, and 35 degrees angle of attack at Reynolds numbers of 1, 2, 3, 4, and 6 million per foot. Temperature data were obtained from a total of 57 thermocouples.

Shuttle Return To Flight Experimental Results: Protuberance Effects on Boundary Layer Transition

NASA Technical Reports Server (NTRS)

Liechty, Derek S.; Berry, Scott A.; Horvath, Thomas J.

2006-01-01

The effect of isolated roughness elements on the windward boundary layer of the Shuttle Orbiter has been experimentally examined in the Langley Aerothermodynamic Laboratory in support of an agency-wide effort to prepare the Shuttle Orbiter for return to flight. This experimental effort was initiated to provide a roughness effects database for developing transition criteria to support on-orbit decisions to repair damage to the thermal protection system. Boundary layer transition results were obtained using trips of varying heights and locations along the centerline and attachment lines of 0.0075-scale models. Global heat transfer images using phosphor thermography of the Orbiter windward surface and the corresponding heating distributions were used to infer the state of the boundary layer (laminar, transitional, or turbulent). The database contained within this report will be used to formulate protuberance-induced transition correlations using predicted boundary layer edge parameters.

Cornering and wear behavior of the Space Shuttle Orbiter main gear tire

NASA Technical Reports Server (NTRS)

Daugherty, Robert H.; Stubbs, Sandy M.

1987-01-01

One of the factors needed to describe the handling characteristics of the Space Shuttle Orbiter during the landing rollout is the response of the vehicle's tires to variations in load and yaw angle. An experimental investigation of the cornering characteristics of the Orbiter main gear tires was conducted at the NASA Langley Research Center Aircraft Landing Dynamics Facility. This investigation compliments earlier work done to define the Orbiter nose tire cornering characteristics. In the investigation, the effects of load and yaw angle were evaluated by measuring parameters such as side load and drag load, and obtaining measurements of aligning torque. Because the tire must operate on an extremely rough runway at the Shuttle Landing Facility at Kennedy Space Center (KSC), tests were also conducted to describe the wear behavior of the tire under various conditions on a simulated KSC runway surface. Mathematical models for both the cornering and the wear behavior are discussed.

Space shuttle phase B wind tunnel model and test information. Volume 2: Orbiter configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a data base and are available for applying to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Data Base is structured by vehicle component and configuration type. Basic components include the booster, the orbiter, and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retro-glide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks, and double delta wings. Launch configuration types include booster and orbiter components in various stacked and tandem combinations.

Supersonic dynamic stability characteristics of a space shuttle orbiter. [wind tunnel tests of scale models

NASA Technical Reports Server (NTRS)

Freeman, D. C., Jr.; Boyden, R. P.; Davenport, E. E.

1976-01-01

Supersonic forced-oscillation tests of a 0.0165-scale model of a modified 089B Rockwell International shuttle orbiter were conducted in a wind tunnel for several configurations over a Mach range from 1.6 to 4.63. The tests covered angles of attack up to 30 deg. The period and damping of the basic unaugmented vehicle were calculated along the entry trajectory using the measured damping results. Some parameter analysis was made with the measured dynamic derivatives. Photographs of the test configurations and test equipment are shown.

Heat transfer phase change paint tests of 0.0175-scale models (nos. 21-0 and 46-0) of the Rockwell International space shuttle orbiter in the AEDC tunnel B hypersonic wind tunnel (test OH25A)

NASA Technical Reports Server (NTRS)

Dye, W. H.

1975-01-01

Tests were conducted in a hypersonic wind tunnel using various truncated space shuttle orbiter configurations in an attempt to establish the optimum model size for other tests examining body shock-wing leading edge interference effects. The tests were conducted at Mach number 8 using the phase change paint technique. A test description, tabulated data, and tracings of isotherms made from photographs taken during the test are presented.

Results of dynamic stability tests conducted on a .012 scale model modified 089 B shuttle orbiter in the AEDC-VKF tunnel B at a Mach number of 8.0 (LA42)

NASA Technical Reports Server (NTRS)

Vaughn, J. E.; Daviet, J. T.

1975-01-01

Experimental aerodynamic investigations were conducted on a .012 scale model of a NASA/Langley modified version of the Rockwell 089B Space Shuttle Orbiter. Using the forced oscillation test technique, dynamic stability derivatives were measured in the pitch, yaw and roll planes at a Mach number of 8 over an angle of attack range from -4 deg to 28 deg. Plotted and tabulated results are presented.

Static and dynamic stability analysis of the space shuttle vehicle-orbiter

NASA Technical Reports Server (NTRS)

Chyu, W. J.; Cavin, R. K.; Erickson, L. L.

1978-01-01

The longitudinal static and dynamic stability of a Space Shuttle Vehicle-Orbiter (SSV Orbiter) model is analyzed using the FLEXSTAB computer program. Nonlinear effects are accounted for by application of a correction technique in the FLEXSTAB system; the technique incorporates experimental force and pressure data into the linear aerodynamic theory. A flexible Orbiter model is treated in the static stability analysis for the flight conditions of Mach number 0.9 for rectilinear flight (1 g) and for a pull-up maneuver (2.5 g) at an altitude of 15.24 km. Static stability parameters and structural deformations of the Orbiter are calculated at trim conditions for the dynamic stability analysis, and the characteristics of damping in pitch are investigated for a Mach number range of 0.3 to 1.2. The calculated results for both the static and dynamic stabilities are compared with the available experimental data.

Crew appliance computer program manual, volume 1

NASA Technical Reports Server (NTRS)

Russell, D. J.

1975-01-01

Trade studies of numerous appliance concepts for advanced spacecraft galley, personal hygiene, housekeeping, and other areas were made to determine which best satisfy the space shuttle orbiter and modular space station mission requirements. Analytical models of selected appliance concepts not currently included in the G-189A Generalized Environmental/Thermal Control and Life Support Systems (ETCLSS) Computer Program subroutine library were developed. The new appliance subroutines are given along with complete analytical model descriptions, solution methods, user's input instructions, and validation run results. The appliance components modeled were integrated with G-189A ETCLSS models for shuttle orbiter and modular space station, and results from computer runs of these systems are presented.

Shuttle Atlantis in Mate-Demate Device Being Loaded onto SCA-747 for Return to Kennedy Space Center

NASA Technical Reports Server (NTRS)

1996-01-01

This photo shows a night view of the orbiter Atlantis being loaded onto one of NASA's Boeing 747 Shuttle Carrier Aircraft (SCA) at the Dryden Flight Research Center, Edwards, California. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

KENNEDY SPACE CENTER, FLA. -- From left, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik, United Space Alliance (USA) Director of Orbiter Operations Patty Stratton, and NASA Space Shuttle Program Manager William Parsons view the underside of Shuttle Discovery in Orbiter Processing Facility Bay 3. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

NASA Image and Video Library

2003-12-19

KENNEDY SPACE CENTER, FLA. -- From left, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik, United Space Alliance (USA) Director of Orbiter Operations Patty Stratton, and NASA Space Shuttle Program Manager William Parsons view the underside of Shuttle Discovery in Orbiter Processing Facility Bay 3. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

Observing orbital debris using space-based telescopes. I - Mission orbit considerations

NASA Technical Reports Server (NTRS)

Reynolds, Robert C.; Talent, David L.; Vilas, Faith

1989-01-01

In this paper, mission orbit considerations are addressed for using the Space Shuttle as a telescope platform for observing man-made orbital debris. Computer modeling of various electrooptical systems predicts that such a space-borne system will be able to detect particles as small as 1-mm diameter. The research is meant to support the development of debris- collision warning sensors through the acquisition of spatial distribution and spectral characteristics for debris and testing of detector combinations on a shuttle-borne telescopic experiment. The technique can also be applied to low-earth-orbit-debris environment monitoring systems. It is shown how the choice of mission orbit, season of launch, and time of day of launch may be employed to provide extended periods of favorable observing conditions.

Space shuttle orbiter trimmed center-of-gravity extension study. Volume 3: Impact of retrofits for center-of-gravity extension on orbiter thermal-protection system

NASA Technical Reports Server (NTRS)

Dunavant, J. C.

1979-01-01

Heat transfer studies were conducted at Mach 10.3 on space shuttle orbiter models with the S-2 fillet and C-4 canard retrofit moldlines which were generated in aerodynamic and system design studies to increase the allowable c.g. range of the orbiter. Areas of orbiter most strongly affected were the sides where a shear layer which separated along the wing leading edge impinged. Analytical studies of the heating effect on the thermal-protection system were made which indicated that scar weight on the orbiter sides due to allowances for retrofits of the S-2 fillet and C-4 canard is small (less than about 90 kg (200 lbs) in comparison to the total weight of the retrofit).

Development of an external ceramic insulation for the space shuttle orbiter

NASA Technical Reports Server (NTRS)

Tanzilli, R. A. (Editor)

1972-01-01

The development and evaluation of a family of reusable external insulation systems for use on the space shuttle orbiter is discussed. The material development and evaluation activities are described. Additional information is provided on the development of an analytical micromechanical model of the reusable insulation and the development of techniques for reducing the heat transfer. Design data on reusable insulation systems and test techniques used for design data generation are included.

Shuttle Enterprise Mated to 747 SCA for Delivery to Smithsonian

NASA Technical Reports Server (NTRS)

1983-01-01

The Space Shuttle Enterprise atop the NASA 747 Shuttle Carrier Aircraft as it leaves NASA's Dryden Flight Research Center, Edwards, California. The Enterprise, first orbiter built, was not spaceflight rated and was used in 1977 to verify the landing, approach, and glide characteristics of the orbiters. It was also used for engineering fit-checks at the shuttle launch facilities. Following approach and landing tests in 1977 and its use as an engineering vehicle, Enterprise was donated to the National Air and Space Museum in Washington, D.C. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Simulation of Hypervelocity Impact Effects on Reinforced Carbon-Carbon. Chapter 6

NASA Technical Reports Server (NTRS)

Park, Young-Keun; Fahrenthold, Eric P.

2004-01-01

Spacecraft operating in low earth orbit face a significant orbital debris impact hazard. Of particular concern, in the case of the Space Shuttle, are impacts on critical components of the thermal protection system. Recent research has formulated a new material model of reinforced carbon-carbon, for use in the analysis of hypervelocity impact effects on the Space Shuttle wing leading edge. The material model has been validated in simulations of published impact experiments and applied to model orbital debris impacts at velocities beyond the range of current experimental methods. The results suggest that momentum scaling may be used to extrapolate the available experimental data base, in order to predict the size of wing leading edge perforations at impact velocities as high as 13 km/s.

Results of investigations on a 0.0405 scale model PRR version of the NR-SSV orbiter in the North American Aeronautical Laboratory low speed wind tunnel

NASA Technical Reports Server (NTRS)

Kingsland, R. B.; Vaughn, J. E.; Singellton, R.

1973-01-01

Experimental aerodynamic investigations were conducted in a low speed wind tunnel on a scale model space shuttle vehicle (SSV) orbiter. The purpose of the test was to investigate the longitudinal and lateral-directional aerodynamic characteristics of the space shuttle orbiter. Emphasis was placed on model component, wing-glove, and wing-body fairing effects, as well as elevon, aileron, and rudder control effectiveness. Angles of attack from - 5 deg to + 30 deg and angles of sideslip of - 5 deg, 0 deg, and + 5 deg were tested. Static pressures were recorded on base, fuselage, and wing surfaces. Tufts and talc-kerosene flow visualization techniques were also utilized. The aerodynamic force balance results are presented in plotted and tabular form.

Modal coupling procedures adapted to NASTRAN analysis of the 1/8-scale shuttle structural dynamics model. Volume 1: Technical report

NASA Technical Reports Server (NTRS)

Zalesak, J.

1975-01-01

A dynamic substructuring analysis, utilizing the component modes technique, of the 1/8 scale space shuttle orbiter finite element model is presented. The analysis was accomplished in 3 phases, using NASTRAN RIGID FORMAT 3, with appropriate Alters, on the IBM 360-370. The orbiter was divided into 5 substructures, each of which was reduced to interface degrees of freedom and generalized normal modes. The reduced substructures were coupled to yield the first 23 symmetric free-free orbiter modes, and the eigenvectors in the original grid point degree of freedom lineup were recovered. A comparison was made with an analysis which was performed with the same model using the direct coordinate elimination approach. Eigenvalues were extracted using the inverse power method.

Transition heating rates obtained on a matted and isolated 0.006 scale model (41-OT) space shuttle orbiter and external tank in the NASA/LaRC variable density hypersonic tunnel (IH17)

NASA Technical Reports Server (NTRS)

Cummings, J.

1976-01-01

Model information and data obtained from wind tunnel tests performed on a 0.006 scale model of the Rockwell International space shuttle orbiter and external tank in the 18 inch Variable Density Hypersonic Wind Tunnel (VDHT) at NASA Langley Research Center are presented. Tests were performed at a Mach number of 8.0 over a Reynolds Number range from 0.1 to 10.0 million per foot at 0 deg and -5 deg angle of attack and 0 deg sideslip angle. Transition heating rates were determined using thin skin thermocouples located at various locations on the orbiter and ET. The test was conducted in three stages: orbiter plus external tank (mated configuration); orbiter alone, and external tank alone. The effects of boundary layer trips were also included in the test sequence. The plotted results presented show the effect of configuration interference on the orbiter lower surface and on the ET. Tabulated data are given.

Experimental investigations of an 0.0405 scale Space Shuttle Configuration 3 orbiter to determine subsonic stability characteristics. Volume 1: OA21A

NASA Technical Reports Server (NTRS)

Cameron, B. W.; Ritschel, A. J.

1973-01-01

Experimental aerodynamic investigations were conducted in a low speed wind tunnel from May 21 through June 4 and from June 18 through June 25, 1973 on a 0.0405 scale -139B model Space Shuttle Vehicle (SSV) orbiter. The purpose of the test was to investigate the longitudinal and lateral-directional subsonic aerodynamic characteristics of the proposed PRR Space Shuttle orbiter. Emphasis was placed on component buildup effects, elevon, rudder, body flaps, rudder flare effectiveness, and canard and speed brake development. Angles of attack from -4 deg. to 24 deg. and angles of sideslip of -10 deg. to 10 deg. were tested. Static pressures were recorded on the base. The aerodynamic force balance results are presented in plotted and tabular form.

Space Shuttle orbiter modifications to support Space Station Freedom

NASA Technical Reports Server (NTRS)

Segert, Randall; Lichtenfels, Allyson

1992-01-01

The Space Shuttle will be the primary vehicle to support the launch, assembly, and maintenance of the Space Station Freedom (SSF). In order to accommodate this function, the Space Shuttle orbiter will require significant modifications. These modifications are currently in development in the Space Shuttle Program. The requirements for the planned modifications to the Space Shuttle orbiter are dependent on the design of the SSF. Therefore, extensive coordination is required with the Space Station Freedom Program (SSFP) in order to identify requirements and resolve integration issues. This paper describes the modifications to the Space Shuttle orbiter required to support SSF assembly and operations.

Early Program Development

NASA Image and Video Library

1989-01-01

This 1989 artist's rendering shows how a Shuttle-C would look during launch. As envisioned by Marshall Space Flight Center plarners, the Shuttle-C would be an unmanned heavy-lift cargo vehicle derived from Space Shuttle elements. The vehicle would utilize the basic Shuttle propulsion units (Solid Rocket Boosters, Space Shuttle Main Engine, External Tank), but would replace the Orbiter with an unmanned Shuttle-C Cargo Element (SCE). The SCE would have a payload bay lenght of eighty-two feet, compared to sixty feet for the Orbiter cargo bay, and would be able to deliver 170,000 pound payloads to low Earth orbit, more than three times the Orbiter's capacity.

Influence of orbital-maneuvering-system fairings and rudder flare on the transonic aerodynamic characteristics of a space shuttle orbiter

NASA Technical Reports Server (NTRS)

Ellison, J. C.

1975-01-01

An investigation was conducted in the Langley 8-foot transonic pressure tunnel to determine the influence of orbital-maneuvering-system fairings and a flared rudder on the aerodynamic characteristics of a space shuttle-orbiter configuration. Tests were made at Mach numbers from 0.4 to 1.2, at angles of attack from -1 deg to 24 deg, at angles of sideslip of 0 deg and 5 deg, and at a Reynolds number, based on model length, of 4 million. The model with the orbital-maneuvering-system fairings had a minimum untrimmed lift-drag ratio from 7.4 to 3.4 at Mach numbers from 0.4 to 1.2 and a maximum trimmed lift-drag ratio of about 3.55 at Mach 0.8 with the rudder flared 30 deg. The directional stability was increased at Mach 0.8 and 1.2 by addition of the orbital-maneuvering-system fairings and at Mach 1.2 by flaring the rudder.

Pressure and heat flux results from the space shuttle/external fuel tank interaction test at Mach numbers 16 and 19

NASA Technical Reports Server (NTRS)

Brewer, E. B.; Haberman, D. R.

1974-01-01

Heat transfer rates and pressures were measured on a 0.0175-scale model of the space shuttle external tank (ET), model MCR0200. Tests were conducted with the ET model separately and while mated with a 0.0175-scale model of the orbiter, model 21-OT (Grumman). The tests were conducted in the AEDC-VKF Hypervelocity Wind Tunnel (F) at Mach numbers 16 and 19. The primary data consisted of the interaction heating rates experienced by the ET while mated with the orbiter in the flight configuration. Data were taken for a range of Reynolds numbers from 50,000 to 65,000 under laminar flow conditions.

Enterprise - First Tailcone Off Free Flight

NASA Technical Reports Server (NTRS)

1977-01-01

The Space Shuttle prototype Enterprise flies free after being released from NASA's 747 Shuttle Carrier Aircraft (SCA) to begin a powerless glide flight back to NASA's Dryden Flight Research Center, Edwards, California, on its fourth of the five free flights in the Shuttle program's Approach and Landing Tests (ALT), 12 October 1977. The tests were carried out at Dryden to verify the aerodynamic and control characteristics of the orbiters in preperation for the first space mission with the orbiter Columbia in April 1981. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Composite Overwrapped Pressure Vessels (COPV): Developing Flight Rationale for the Space Shuttle Program

NASA Technical Reports Server (NTRS)

Kezirian, Michael T.

2010-01-01

Introducing composite vessels into the Space Shuttle Program represented a significant technical achievement. Each Orbiter vehicle contains 24 (nominally) Kevlar tanks for storage of pressurized helium (for propulsion) and nitrogen (for life support). The use of composite cylinders saved 752 pounds per Orbiter vehicle compared with all-metal tanks. The weight savings is significant considering each Shuttle flight can deliver 54,000 pounds of payload to the International Space Station. In the wake of the Columbia accident and the ensuing Return to Flight activities, the Space Shuttle Program, in 2005, re-examined COPV hardware certification. Incorporating COPV data that had been generated over the last 30 years and recognizing differences between initial Shuttle Program requirements and current operation, a new failure mode was identified, as composite stress rupture was deemed credible. The Orbiter Project undertook a comprehensive investigation to quantify and mitigate this risk. First, the engineering team considered and later deemed as unfeasible the option to replace existing all flight tanks. Second, operational improvements to flight procedures were instituted to reduce the flight risk and the danger to personnel. Third, an Orbiter reliability model was developed to quantify flight risk. Laser profilometry inspection of several flight COPVs identified deep (up to 20 mil) depressions on the tank interior. A comprehensive analysis was performed and it confirmed that these observed depressions were far less than the criterion which was established as necessary to lead to liner buckling. Existing fleet vessels were exonerated from this failure mechanism. Because full validation of the Orbiter Reliability Model was not possible given limited hardware resources, an Accelerated Stress Rupture Test of a flown flight vessel was performed to provide increased confidence. A Bayesian statistical approach was developed to evaluate possible test results with respect to the model credibility and thus flight rationale for continued operation of the Space Shuttle with existing flight hardware. A non-destructive evaluation (NDE) technique utilizing Raman Spectroscopy was developed to directly measure the overwrap residual stress state. Preliminary results provide optimistic results that patterns of fluctuation in fiber elastic strains over the outside vessel surface could be directly correlated with increased fiber stress ratios and thus reduced reliability.

Effect of Protuberance Shape and Orientation on Space Shuttle Orbiter Boundary-Layer Transition

NASA Technical Reports Server (NTRS)

King, RUdolph A.; Berry, Scott A.; Kegerise, Michael A.

2008-01-01

This document describes an experimental study conducted to examine the effects of protuberances on hypersonic boundary-layer transition. The experiment was conducted in the Langley 20-Inch Mach 6 Tunnel on a series of 0.9%-scale Shuttle Orbiter models. The data were acquired to complement the existing ground-based boundary-layer transition database that was used to develop Version 1.0 of the boundary-layer transition RTF (return-to-flight) tool. The existing ground-based data were all acquired on 0.75%-scale Orbiter models using diamond-shaped ( pizza-box ) trips. The larger model scale facilitated in manufacturing higher fidelity protuberances. The end use of this experimental database will be to develop a technical basis (in the form of a boundary-layer transition correlation) to assess representative protrusion shapes, e.g., gap fillers and protrusions resulting from possible tile repair concepts. The primary objective of this study is to investigate the effects of protuberance-trip location and geometry on Shuttle Orbiter boundary-layer transition. Secondary goals are to assess the effects of gap-filler orientation and other protrusion shapes on boundary-layer transition. Global heat-transfer images using phosphor thermography of the Orbiter windward surface and the corresponding streamwise and spanwise heating distributions were used to infer the state of the boundary layer, i.e., laminar, transitional, or turbulent.

STS Challenger Mated to 747 SCA for Initial Delivery to Florida

NASA Technical Reports Server (NTRS)

1982-01-01

The Space Shuttle orbiter Challenger atop NASA's Boeing 747 Shuttle Carrier Aircraft (SCA), NASA 905, after leaving the Dryden Flight Research Center, Edwards, California, for the ferry flight that took the orbiter to the Kennedy Space Center in Florida for its first launch. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Safety in earth orbit study. Volume 1: Technical summary

NASA Technical Reports Server (NTRS)

1972-01-01

A summary of the technical results and conclusions is presented of the hazards analyses of earth orbital operations in conjunction with the space shuttle program. The space shuttle orbiter and a variety of manned and unmanned payloads delivered to orbit by the shuttle are considered. The specific safety areas examined are hazardous payloads, docking, on-orbit survivability, tumbling spacecraft, and escape and rescue.

Shuttle Endeavour Mated to 747 SCA Taxi to Runway for Delivery to Kennedy Space Center, Florida

NASA Technical Reports Server (NTRS)

1991-01-01

NASA's 747 Shuttle Carrier Aircraft No. 911, with the space shuttle orbiter Endeavour securely mounted atop its fuselage, taxies to the runway to begin the ferry flight from Rockwell's Plant 42 at Palmdale, California, where the orbiter was built, to the Kennedy Space Center, Florida. At Kennedy, the space vehicle was processed and launched on orbital mission STS-49, which landed at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, 16 May 1992. NASA 911, the second modified 747 that went into service in November 1990, has special support struts atop the fuselage and internal strengthening to accommodate the added weight of the orbiters. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Endeavour Mated to 747 SCA Takeoff for Delivery to Kennedy Space Center, Florida

NASA Technical Reports Server (NTRS)

1991-01-01

NASA's 747 Shuttle Carrier Aircraft No. 911, with the space shuttle orbiter Endeavour securely mounted atop its fuselage, begins the ferry flight from Rockwell's Plant 42 at Palmdale, California, where the orbiter was built, to the Kennedy Space Center, Florida. At Kennedy, the space vehicle was processed and launched on orbital mission STS-49, which landed at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, 16 May 1992. NASA 911, the second modified 747 that went into service in November 1990, has special support struts atop the fuselage and internal strengthening to accommodate the added weight of the orbiters. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Discovery Mated to 747 SCA

NASA Technical Reports Server (NTRS)

1983-01-01

The Space Shuttle Discovery rides atop '905,' NASA's 747 Shuttle Carrier Aircraft, on its delivery flight from California to the Kennedy Space Center, Florida, where it was prepared for its first orbital mission for 30 August to 5 September 1984. The NASA 747, obtained in 1974, has special support struts atop the fuselage and internal strengthening to accommodate the additional weight of the orbiters. Small vertical fins have also been added to the tips of the horizontal stabilizers for additional stability due to air turbulence on the control surfaces caused by the orbiters. A second modified 747, no. 911, went in to service in November 1990 and is also used to ferry orbiters to destinations where ground transportation is not practical. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Discovery Landing at Palmdale, California, Maintenance Facility

NASA Technical Reports Server (NTRS)

1995-01-01

NASA Dryden Flight Research Center pilot Tom McMurtry lands NASA's Shuttle Carrier Aircraft with Space Shuttle Discovery attached at Rockwell Aerospace's Palmdale, California, facility about 1:00 p.m. Pacific Daylight Time (PDT). There for nine months of scheduled maintenance, Discovery and the 747 were completing a two-day flight from Kennedy Space Center, Florida, that began at 7:04 a.m. Eastern Standard Time on 27 September and included an overnight stop at Salt Lake City International Airport, Utah. At the conclusion of this mission, Discovery had flown 21 shuttle missions, totaling more than 142 days in orbit. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Discovery Being Unloaded from SCA-747 at Palmdale, California, Maintenance Facility

NASA Technical Reports Server (NTRS)

1995-01-01

Space Shuttle Discovery being unloaded from NASA's Boeing 747 Shuttle Carrier Aircraft (SCA) at Rockwell Aerospace's Palmdale facility for nine months of scheduled maintenance. Discovery and the 747 were completing a two-day flight from Kennedy Space Center, Florida, that began at 7:04 a.m. Eastern Standard Time on 27 September and included an overnight stop at Salt Lake City International Airport, Utah. At the conclusion of this mission, Discovery had flown 21 shuttle missions, totaling more than 142 days in orbit. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

A Preliminary Data Model for Orbital Flight Dynamics in Shuttle Mission Control

NASA Technical Reports Server (NTRS)

ONeill, John; Shalin, Valerie L.

2000-01-01

The Orbital Flight Dynamics group in Shuttle Mission Control is investigating new user interfaces in a project called RIOTS [RIOTS 2000]. Traditionally, the individual functions of hardware and software guide the design of displays, which results in an aggregated, if not integrated interface. The human work system has then been designed and trained to navigate, operate and integrate the processors and displays. The aim of RIOTS is to reduce the cognitive demands of the flight controllers by redesigning the user interface to support the work of the flight controller. This document supports the RIOTS project by defining a preliminary data model for Orbital Flight Dynamics. Section 2 defines an information-centric perspective. An information-centric approach aims to reduce the cognitive workload of the flight controllers by reducing the need for manual integration of information across processors and displays. Section 3 describes the Orbital Flight Dynamics domain. Section 4 defines the preliminary data model for Orbital Flight Dynamics. Section 5 examines the implications of mapping the data model to Orbital Flight Dynamics current information systems. Two recurring patterns are identified in the Orbital Flight Dynamics work the iteration/rework cycle and the decision-making/information integration/mirroring role relationship. Section 6 identifies new requirements on Orbital Flight Dynamics work and makes recommendations based on changing the information environment, changing the implementation of the data model, and changing the two recurring patterns.

Data report for tests on the heat transfer effects of the 0.0175 scale Rockwell International Space Shuttle Vehicle model 22-OT in the AEDC 50 inch B wind tunnel (0H4B), volume 1

NASA Technical Reports Server (NTRS)

Foster, T. F.; Grifall, W. J.; Martindale, W.

1975-01-01

Results of wind tunnel heat transfer tests of 0.0175-scale Rockwell International Space Shuttle Vehicle configurations for orbiter alone, tank alone, and orbiter plus external tank are presented. Body flap shielding of SSME's during simulated entry was investigated. The tests were conducted at Mach 8 for thirteen Reynolds number.

Transition Induced by Fence Geometrics on Shuttle Orbiter at Mach 10

NASA Technical Reports Server (NTRS)

Everhart, Joel L.

2010-01-01

Fence-induced transition data simulating a raised gap filler have been acquired on the wing lower surface of a Shuttle Orbiter model in the Langley 31-Inch Mach 10 Tunnel to compare with the Shuttle Boundary Layer Transition Flight and HYTHIRM Experiments, and to provide additional correlation data for the Boundary Layer Transition Tool. In a qualitative assessment, the data exhibit the expected response to all parameter variations; however, it is unclear whether fully effective tripping at the fence was ever realized at any test condition with the present model hardware. A preliminary, qualitative comparison of the ground-based transition measurements with those obtained from the STS-128 HYTHIRM imagery at Mach 15 reveal similar transition-wake response characteristics in terms of the spreading and the path along the vehicle surface.

Experiment module concepts study. Volume 5 book 1, appendix A: Shuttle only task

NASA Technical Reports Server (NTRS)

1970-01-01

Results of a preliminary investigation of the effect on the candidate experiment program implementation of experiment module operations in the absence of an orbiting space station and with the availability of the space shuttle orbiter vehicle only are presented. The fundamental hardware elements for shuttle-only operation of the program are: (1) integrated common experiment modules CM-1, CM-3, and CM-4, together with the propulsion slice; (2) support modules capable of supplying on-orbit crew life support, power, data management, and other services normally provided by a space station; (3) dormancy kits to enable normally attached modules to remain in orbit while shuttle returns to earth; and (4) shuttle orbiter. Preliminary cost estimates for 30 day on-orbit and 5 day on-orbit capabilities for a four year implementation period are $4.2 billion and $2.1 billion, respectively.

Optimum element density studies for finite-element thermal analysis of hypersonic aircraft structures

NASA Technical Reports Server (NTRS)

Ko, William L.; Olona, Timothy; Muramoto, Kyle M.

1990-01-01

Different finite element models previously set up for thermal analysis of the space shuttle orbiter structure are discussed and their shortcomings identified. Element density criteria are established for the finite element thermal modelings of space shuttle orbiter-type large, hypersonic aircraft structures. These criteria are based on rigorous studies on solution accuracies using different finite element models having different element densities set up for one cell of the orbiter wing. Also, a method for optimization of the transient thermal analysis computer central processing unit (CPU) time is discussed. Based on the newly established element density criteria, the orbiter wing midspan segment was modeled for the examination of thermal analysis solution accuracies and the extent of computation CPU time requirements. The results showed that the distributions of the structural temperatures and the thermal stresses obtained from this wing segment model were satisfactory and the computation CPU time was at the acceptable level. The studies offered the hope that modeling the large, hypersonic aircraft structures using high-density elements for transient thermal analysis is possible if a CPU optimization technique was used.

KENNEDY SPACE CENTER, FLA. -- In Orbiter Processing Facility Bay 1, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (left) and United Space Alliance (USA) Vice President and Space Shuttle Program Manager Howard DeCastro (right) are briefed by a USA technician (center) on Shuttle processing in the payload bay of orbiter Atlantis. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

NASA Image and Video Library

2003-12-19

KENNEDY SPACE CENTER, FLA. -- In Orbiter Processing Facility Bay 1, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (left) and United Space Alliance (USA) Vice President and Space Shuttle Program Manager Howard DeCastro (right) are briefed by a USA technician (center) on Shuttle processing in the payload bay of orbiter Atlantis. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

Shuttle in Mate-Demate Device being Loaded onto SCA-747

NASA Technical Reports Server (NTRS)

1991-01-01

At NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, technicians begin the task of mounting the Space Shuttle Atlantis atop NASA's 747 Shuttle Carrier Aircraft (NASA #911) for the ferry flight back to the Kennedy Space Center, Florida, following its STS-44 flight 24 November - 1 December 1991. Post-flight servicing of the orbiters, and the mating operation, is carried out at Dryden at the Mate-Demate Device (MDD), the large gantry-like structure that hoists the spacecraft to various levels during post-space flight processing and attachment to the 747. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Parking Lot and Public Viewing Area for STS-4 Landing

NASA Technical Reports Server (NTRS)

1982-01-01

This aerial photo shows the large crowd of people and vehicles that assembled to watch the landing of STS-4 at Edwards Air Force Base in California in July 1982. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Early Program Development

NASA Image and Video Library

1971-01-01

This 1971 artist's concept shows a Nuclear Shuttle and an early Space Shuttle docked with an Orbital Propellant Depot. As envisioned by Marshall Space Flight Center Program Development persornel, an orbital modular propellant storage depot, supplied periodically by the Space Shuttle or Earth-to-orbit fuel tankers, would be critical in making available large amounts of fuel to various orbital vehicles and spacecraft.

Supersonic aerodynamic characteristics of the North American Rockwell ATP shuttle orbiter

NASA Technical Reports Server (NTRS)

Ware, G. M.; Pencer, B., Jr.; Founier, R. H.

1973-01-01

A wind tunnel study to determine the supersonic aerodynamic characteristics of a 0.01925-scale model of the space shuttle orbiter configuration is reported. The model consisted of a low-finess-ratio body with a blended 50 swept delta wing forming an ogee planform and a center-line-mounted vertical tail. Tests were made at Mach numbers from 1.90 to 4.63, at angles of attack from -6 to 30, at angles of sideslip of 0 and 3, and at a Reynolds number, based on body length, of 5.3x 1 million.

Transonic control effectiveness for full and partial span elevon configurations on a 0.0165 scale model space shuttle orbiter tested in the LaRC 8-foot transonic wind tunnel (LA48)

NASA Technical Reports Server (NTRS)

1977-01-01

A transonic pressure tunnel test is reported on an early version of the space shuttle orbiter (designated 089B-139) 0.0165 scale model to systematically determine both longitudinal and lateral control effectiveness associated with various combinations of inboard, outboard, and full span wing trailing edge controls. The test was conducted over a Mach number range from 0.6 to 1.08 at angles of attack from -2 deg to 23 deg at 0 deg sideslip.

Use of MSC/NASTRAN for the thermal analysis of the Space Shuttle Orbiter braking system

NASA Technical Reports Server (NTRS)

Shu, James; Mccann, David

1987-01-01

A description is given of the thermal modeling and analysis effort being conducted to investigate the transient temperature and thermal stress characteristics of the Space Shuttle Orbiter brake components and subsystems. Models are constructed of the brake stator as well as of the entire brake assembly to analyze the temperature distribution and thermal stress during the landing and braking process. These investigations are carried out on a UNIVAC computer system with MSC/NASTRAN Version 63. Analytical results and solution methods are presented and comparisons are made with SINDA results.

Shuttle Carrier Aircraft (SCA) Fleet Photo

NASA Technical Reports Server (NTRS)

1995-01-01

NASA's two Boeing 747 Shuttle Carrier Aircraft (SCA) are seen here nose to nose at Dryden Flight Research Center, Edwards, California. The front mounting attachment for the Shuttle can just be seen on top of each. The SCAs are used to ferry Space Shuttle orbiters from landing sites back to the launch complex at the Kennedy Space Center, and also to and from other locations too distant for the orbiters to be delivered by ground transportation. The orbiters are placed atop the SCAs by Mate-Demate Devices, large gantry-like structures which hoist the orbiters off the ground for post-flight servicing, and then mate them with the SCAs for ferry flights. Features which distinguish the two SCAs from standard 747 jetliners are; three struts, with associated interior structural strengthening, protruding from the top of the fuselage (two aft, one forward) on which the orbiter is attached, and two additional vertical stabilizers, one on each end of the standard horizontal stabilizer, to enhance directional stability. The two SCAs are under the operational control of NASA's Johnson Space Center, Houston, Texas. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Effect of element size on the solution accuracies of finite-element heat transfer and thermal stress analyses of space shuttle orbiter

NASA Technical Reports Server (NTRS)

Ko, William L.; Olona, Timothy

1987-01-01

The effect of element size on the solution accuracies of finite-element heat transfer and thermal stress analyses of space shuttle orbiter was investigated. Several structural performance and resizing (SPAR) thermal models and NASA structural analysis (NASTRAN) structural models were set up for the orbiter wing midspan bay 3. The thermal model was found to be the one that determines the limit of finite-element fineness because of the limitation of computational core space required for the radiation view factor calculations. The thermal stresses were found to be extremely sensitive to a slight variation of structural temperature distributions. The minimum degree of element fineness required for the thermal model to yield reasonably accurate solutions was established. The radiation view factor computation time was found to be insignificant compared with the total computer time required for the SPAR transient heat transfer analysis.

Results of phase change paint heat transfer tests utilizing 0.040 scale 50% forebody models (No. 82-0) of the Rockwell International space shuttle orbiter in AEDC VKF hypersonic tunnel B (test OH54A)

NASA Technical Reports Server (NTRS)

Dye, W. H.

1976-01-01

Results of aerodynamic heating tests conducted in October 1974 on a space shuttle orbiter model using the phase change paint technique are presented. The model was a 0.040 scale representation of the forward 50 percent of the orbiter. Surface roughness effects on boundary layer transition were investigated. Roughness was simulated by using steel balls varying in diameter from 0 (no balls) to 0.039 inch with 0.040 inch wide by 0.080 inch deep gaps. A nominal Mach number of 8 was tested with Reynolds number varying from 0.75 through 3.5 million per foot. Angle of attack was varied from 20 deg to 40 deg.

Modeling and analysis of the space shuttle nose-gear tire with semianalytic finite elements

NASA Technical Reports Server (NTRS)

Kim, Kyun O.; Noor, Ahmed K.; Tanner, John A.

1990-01-01

A computational procedure is presented for the geometrically nonlinear analysis of aircraft tires. The Space Shuttle Orbiter nose gear tire was modeled by using a two-dimensional laminated anisotropic shell theory with the effects of variation in material and geometric parameters included. The four key elements of the procedure are: (1) semianalytic finite elements in which the shell variables are represented by Fourier series in the circumferential direction and piecewise polynominals in the meridional direction; (2) a mixed formulation with the fundamental unknowns consisting of strain parameters, stress-resultant parameters, and generalized displacements; (3) multilevel operator splitting to effect successive simplifications, and to uncouple the equations associated with different Fourier harmonics; and (4) multilevel iterative procedures and reduction techniques to generate the response of the shell. Numerical results of the Space Shuttle Orbiter nose gear tire model are compared with experimental measurements of the tire subjected to inflation loading.

STS-35 Leaves Dryden on 747 Shuttle Carrier Aircraft (SCA) Bound for Kennedy Space Center

NASA Technical Reports Server (NTRS)

1990-01-01

The first rays of the morning sun light up the side of NASA's Boeing 747 Shuttle Carrier Aircraft (SCA) as it departs for the Kennedy Space Center, Florida, with the orbiter from STS-35 attached to its back. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Simulation of Micron-Sized Debris Populations in Low Earth Orbit

NASA Technical Reports Server (NTRS)

Xu, Y.-L.; Hyde, J. L.; Prior, T.; Matney, Mark

2010-01-01

The update of ORDEM2000, the NASA Orbital Debris Engineering Model, to its new version ORDEM2010, is nearly complete. As a part of the ORDEM upgrade, this paper addresses the simulation of micro-debris (greater than 10 m and smaller than 1 mm in size) populations in low Earth orbit. The principal data used in the modeling of the micron-sized debris populations are in-situ hypervelocity impact records, accumulated in post-flight damage surveys on the space-exposed surfaces of returned spacecrafts. The development of the micro-debris model populations follows the general approach to deriving other ORDEM2010-required input populations for various components and types of debris. This paper describes the key elements and major steps in the statistical inference of the ORDEM2010 micro-debris populations. A crucial step is the construction of a degradation/ejecta source model to provide prior information on the micron-sized objects (such as orbital and object-size distributions). Another critical step is to link model populations with data, which is rather involved. It demands detailed information on area-time/directionality for all the space-exposed elements of a shuttle orbiter and damage laws, which relate impact damage with the physical properties of a projectile and impact conditions such as impact angle and velocity. Also needed are model-predicted debris fluxes as a function of object size and impact velocity from all possible directions. In spite of the very limited quantity of the available shuttle impact data, the population-derivation process is satisfactorily stable. Final modeling results obtained from shuttle window and radiator impact data are reasonably convergent and consistent, especially for the debris populations with object-size thresholds at 10 and 100 m.

Simulation of Micron-Sized Debris Populations in Low Earth Orbit

NASA Technical Reports Server (NTRS)

Xu, Y.-L.; Matney, M.; Liou, J.-C.; Hyde, J. L.; Prior, T. G.

2010-01-01

The update of ORDEM2000, the NASA Orbital Debris Engineering Model, to its new version . ORDEM2010, is nearly complete. As a part of the ORDEM upgrade, this paper addresses the simulation of micro-debris (greater than 10 micron and smaller than 1 mm in size) populations in low Earth orbit. The principal data used in the modeling of the micron-sized debris populations are in-situ hypervelocity impact records, accumulated in post-flight damage surveys on the space-exposed surfaces of returned spacecrafts. The development of the micro-debris model populations follows the general approach to deriving other ORDEM2010-required input populations for various components and types of debris. This paper describes the key elements and major steps in the statistical inference of the ORDEM2010 micro-debris populations. A crucial step is the construction of a degradation/ejecta source model to provide prior information on the micron-sized objects (such as orbital and object-size distributions). Another critical step is to link model populations with data, which is rather involved. It demands detailed information on area-time/directionality for all the space-exposed elements of a shuttle orbiter and damage laws, which relate impact damage with the physical properties of a projectile and impact conditions such as impact angle and velocity. Also needed are model-predicted debris fluxes as a function of object size and impact velocity from all possible directions. In spite of the very limited quantity of the available shuttle impact data, the population-derivation process is satisfactorily stable. Final modeling results obtained from shuttle window and radiator impact data are reasonably convergent and consistent, especially for the debris populations with object-size thresholds at 10 and 100 micron.

Shuttle Columbia Mated to 747 SCA with Crew

NASA Technical Reports Server (NTRS)

1981-01-01

The crew of NASA's 747 Shuttle Carrier Aircraft (SCA), seen mated with the Space Shuttle Columbia behind them, are from viewers left: Tom McMurtry, pilot; Vic Horton, flight engineer; Fitz Fulton, command pilot; and Ray Young, flight engineer. The SCA is used to ferry the shuttle between California and the Kennedy Space Center, Florida, and other destinations where ground transportation is not practical. The NASA 747 has special support struts atop the fuselage and internal strengthening to accommodate the additional weight of the orbiters. Small vertical fins have also been added to the tips of the horizontal stabilizers for additional stability due to air turbulence on the control surfaces caused by the orbiters. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Free Enterprise: Contributions of the Approach and Landing Test (ALT) Program to the Development of the Space Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Merlin, Peter W.

2006-01-01

The space shuttle orbiter was the first spacecraft designed with the aerodynamic characteristics and in-atmosphere handling qualities of a conventional airplane. In order to evaluate the orbiter's flight control systems and subsonic handling characteristics, a series of flight tests were undertaken at NASA Dryden Flight Research Center in 1977. A modified Boeing 747 Shuttle Carrier Aircraft carried the Enterprise, a prototype orbiter, during eight captive tests to determine how well the two vehicles flew together and to test some of the orbiter s systems. The free-flight phase of the ALT program allowed shuttle pilots to explore the orbiter's low-speed flight and landing characteristics. The Enterprise provided realistic, in-flight simulations of how subsequent space shuttles would be flown at the end of an orbital mission. The fifth free flight, with the Enterprise landing on a concrete runway for the first time, revealed a problem with the space shuttle flight control system that made it susceptible to pilot-induced oscillation, a potentially dangerous control problem. Further research using various aircraft, particularly NASA Dryden's F-8 Digital-Fly-By-Wire testbed, led to correction of the problem before the first Orbital Test Flight.

Flight Results of the Chandra X-ray Observatory Inertial Upper Stage Space Mission

NASA Technical Reports Server (NTRS)

Tillotson, R.; Walter, R.

2000-01-01

Under contract to NASA, a specially configured version of the Boeing developed Inertial Upper Stage (IUS) booster was provided by Boeing to deliver NASA's 1.5 billion dollar Chandra X-Ray Observatory satellite into a highly elliptical transfer orbit from a Shuttle provided circular park orbit. Subsequently, the final orbit of the Chandra satellite was to be achieved using the Chandra Integral Propulsion System (IPS) through a series of IPS burns. On 23 July 1999 the Shuttle Columbia (STS-93) was launched with the IUS/Chandra stack in the Shuttle payload bay. Unfortunately, the Shuttle Orbiter was unexpectantly inserted into an off-nominal park orbit due to a Shuttle propulsion anomaly occurring during ascent. Following the IUS/Chandra on-orbit deployment from the Shuttle, at seven hours from liftoff, the flight proven IUS GN&C system successfully injected Chandra into the targeted transfer orbit, in spite of the off-nominal park orbit. This paper describes the IUS GN&C system, discusses the specific IUS GN&C mission data load development, analyses and testing for the Chandra mission, and concludes with a summary of flight results for the IUS part of the Chandra mission.

Space shuttle phase B wind tunnel model and test information. Volume 3: Launch configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel data acquired in the Phase B development have been compiled into a data base and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include booster, orbiter and launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbital configuration types include straight and delta wings, lifting body, drop tanks and double delta wings. This is Volume 3 (Part 2) of the report -- Launch Configuration -- which includes booster and orbiter components in various stacked and tandem combinations.

Investigation of high temperature antennas for space shuttle

NASA Technical Reports Server (NTRS)

Kuhlman, E. A.

1973-01-01

The design and development of high temperature antennas for the space shuttle orbiter are discussed. The antenna designs were based on three antenna types, an annular slot (L-Band), a linear slot (C-Band), and a horn (C-Band). The design approach was based on combining an RF window, which provides thermal protection, with an off-the-shelf antenna. Available antenna window materials were reviewed and compared, and the materials most compatible with the design requirements were selected. Two antenna window design approaches were considered: one employed a high temperature dielectric material and a low density insulation material, and the other an insulation material usable for the orbiter thermal protection system. Preliminary designs were formulated and integrated into the orbiter structure. Simple electrical models, with a series of window configurations, were constructed and tested. The results of tests and analyses for the final antenna system designs are given and show that high temperature antenna systems consisting of off-the-shelf antennas thermally protected by RF windows can be designed for the Space Shuttle Orbiter.

An Inviscid Computational Study of the Space Shuttle Orbiter and Several Damaged Configurations

NASA Technical Reports Server (NTRS)

Prabhu, Ramadas K.; Merski, N. Ronald (Technical Monitor)

2004-01-01

Inviscid aerodynamic characteristics of the Space Shuttle Orbiter were computed in support of the Columbia Accident Investigation. The unstructured grid software FELISA was used and computations were done using freestream conditions corresponding to those in the NASA Langley 20-Inch Mach 6 CF4 tunnel test section. The angle of attack was held constant at 40 degrees. The baseline (undamaged) configuration and a large number of damaged configurations of the Orbiter were studied. Most of the computations were done on a half model. However, one set of computations was done using the full-model to study the effect of sideslip. The differences in the aerodynamic coefficients for the damaged and the baseline configurations were computed. Simultaneously with the computation reported here, tests were being done on a scale model of the Orbiter in the 20-Inch Mach 6 CF4 tunnel to measure the deltas . The present computations complemented the CF4 tunnel test, and provided aerodynamic coefficients of the Orbiter as well as its components. Further, they also provided details of the flow field.

Design analysis and computer-aided performance evaluation of shuttle orbiter electrical power system. Volume 2: SYSTID user's guide

NASA Technical Reports Server (NTRS)

1974-01-01

The manual for the use of the computer program SYSTID under the Univac operating system is presented. The computer program is used in the simulation and evaluation of the space shuttle orbiter electric power supply. The models described in the handbook are those which were available in the original versions of SYSTID. The subjects discussed are: (1) program description, (2) input language, (3) node typing, (4) problem submission, and (5) basic and power system SYSTID libraries.

An integral equation formulation for predicting radiation patterns of a space shuttle annular slot antenna

NASA Technical Reports Server (NTRS)

Jones, J. E.; Richmond, J. H.

1974-01-01

An integral equation formulation is applied to predict pitch- and roll-plane radiation patterns of a thin VHF/UHF (very high frequency/ultra high frequency) annular slot communications antenna operating at several locations in the nose region of the space shuttle orbiter. Digital computer programs used to compute radiation patterns are given and the use of the programs is illustrated. Experimental verification of computed patterns is given from measurements made on 1/35-scale models of the orbiter.

Space Shuttle Projects

NASA Image and Video Library

1985-04-01

In this photograph the SYNCOM IV-3, also known as LEASAT 3, satellite moves away from the Space Shuttle Orbiter Discovery. SYNCOM (Hughes Geosynchronous Communication Satellite) provides communication services from geosynchronous orbit, principally to the U.S. Government. The satellite was launched on April 12, 1985, aboard the Space Shuttle Orbiter Discovery.

Shuttle Columbia Post-landing Tow - with Reflection in Water

NASA Technical Reports Server (NTRS)

1982-01-01

A rare rain allowed this reflection of the Space Shuttle Columbia as it was towed 16 Nov. 1982, to the Shuttle Processing Area at NASA's Ames-Dryden Flight Research Facility (from 1976 to 1981 and after 1994, the Dryden Flight Research Center), Edwards, California, following its fifth flight in space. Columbia was launched on mission STS-5 11 Nov. 1982, and landed at Edwards Air Force Base on concrete runway 22. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines withtwo solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. MartinMarietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-134 Orbit 2 flight controllers on consoles

NASA Image and Video Library

2011-05-17

JSC2011-E-045472 (17 May 2011) --- A scale model of HM Bark Endeavour, namesake for the space shuttle currently making its final flight, adorns a console in the space shuttle flight control room in Mission Control in Houston. This model was first displayed in 1992 in the old shuttle control room during STS-49, the inaugural flight of the shuttle Endeavour. It was built by Dan Willett of JSC's Information Resources Directorate. The original sailing ship Endeavour was commanded by Lt. James Cook on a scientific voyage to the South Pacific, Australia and New Zealand from 1768 to 1771. Photo credit: NASA

A spectroscopic experimental and computer-assisted empirical model for the production and energetics of excited oxygen molecules formed by atom recombination on shuttle tile surfaces

NASA Technical Reports Server (NTRS)

Owan, D. A.

1981-01-01

A visible emission spectroscopic method was developed. The amounts of excited singlet and triplet oxygen molecules produced by recombination on the Space Shuttle Orbiter thermal protective tiles at elevated temperatures are determined. Rate constants and energetics of the extremely exothermic reaction are evaluated in terms of a chemical and mathematical model. Implications for potential contribution to Shuttle surface reentry heating fluxes are outlined.

Space shuttle: Static aerodynamic characteristics characteristics and control effectiveness for McDonnell-Douglas orbiter configuration for Mach number range of 0.4 to 5.0

NASA Technical Reports Server (NTRS)

Ellis, R. R.

1971-01-01

An experimental aerodynamic wind tunnel investigation was conducted employing a 0.00325 scale model of the McDonnell-Douglas space shuttle orbiter configuration. This investigation was conducted in the NASA/Marshall Space Flight Center 14- by 14- inch trisonic wind tunnel. The investigation was to determine the aerodynamic characteristics of the orbiter over the Mach number range of 0.4 to 5.0, an angle of attack variation from -4 degrees to 50 degrees, and -6 degrees to 9 degrees angle of sideslip. Control surface effectiveness was investigated for elevator, aileron, and rudder deflections.

Debris Dispersion Model Using Java 3D

NASA Technical Reports Server (NTRS)

Thirumalainambi, Rajkumar; Bardina, Jorge

2004-01-01

This paper describes web based simulation of Shuttle launch operations and debris dispersion. Java 3D graphics provides geometric and visual content with suitable mathematical model and behaviors of Shuttle launch. Because the model is so heterogeneous and interrelated with various factors, 3D graphics combined with physical models provides mechanisms to understand the complexity of launch and range operations. The main focus in the modeling and simulation covers orbital dynamics and range safety. Range safety areas include destruct limit lines, telemetry and tracking and population risk near range. If there is an explosion of Shuttle during launch, debris dispersion is explained. The shuttle launch and range operations in this paper are discussed based on the operations from Kennedy Space Center, Florida, USA.

MCC level C formulation requirements. Shuttle TAEM guidance and flight control, STS-1 baseline

NASA Technical Reports Server (NTRS)

Carman, G. L.; Montez, M. N.

1980-01-01

The TAEM guidance and body rotational dynamics models required for the MCC simulation of the TAEM mission phase are defined. This simulation begins at the end of the entry phase and terminates at TAEM autoland interface. The logic presented is the required configuration for the first shuttle orbital flight (STS-1). The TAEM guidance is simulated in detail. The rotational dynamics simulation is a simplified model that assumes that the commanded rotational rates can be achieved in the integration interval. Thus, the rotational dynamics simulation is essentially a simulation of the autopilot commanded rates and integration of these rates to determine orbiter attitude. The rotational dynamics simulation also includes a simulation of the speedbrake deflection. The body flap and elevon deflections are computed in the orbiter aerodynamic simulation.

Investigations on an 0.030-scale space shuttle vehicle configuration 140A/B orbiter model in the Ames Research Center unitary plan 8 by 7-foot supersonic wind tunnel (0A53C)

NASA Technical Reports Server (NTRS)

Nichols, M. E.

1974-01-01

A wind tunnel test was conducted of an 0.030 scale model of the space shuttle orbiter in a supersonic wind tunnel. Tests were conducted at Mach numbers of 2.5, 3.0, and 3.5. Reynolds numbers ranged from 0.75 million per foot to 4.00 million per foot. The objective of the test was to establish and verify longitudinal and lateral-directional aerodynamic performance, stability, and control characteristics for the configuration 140 A/B SSV Orbiter. Six-component force and moment data, base and cavity pressures, body-flap, elevon, speedbrake, and rudder hinge moments, and vertical tail forces and moments were measured.

Investigations to the space shuttle orbiter 2A configuration 0.015-scale model in the NASA Ames Research Center 3.5-foot hypersonic wind tunnel at Mach numbers 5, 7 and 10 (OA11B)

NASA Technical Reports Server (NTRS)

Mellenthin, J. A.; Cleary, J. W.; Nichols, M. E.; Milam, M. D.

1974-01-01

The results of a wind tunnel test to determine the force, moment, and hinge-moment characteristics of the Configuration 2A Space Shuttle Vehicle Orbiter at Mach numbers 5, 7 and 10 are presented. The model was an 0.015-scale representation of the Orbiter Configuration 2A used in test 0A11A and later tests. Six-component aerodynamic force and moment data were recorded from a 1.50-inch internal strain-gage balance, and base pressures were taken for axial and drag force corrections. Hinge-moment data were obtained for the rudder and the inboard and outboard elevon panels of the starboard wing.

Space shuttle orbiter test flight series

NASA Technical Reports Server (NTRS)

Garrett, D.; Gordon, R.; Jackson, R. B.

1977-01-01

The proposed studies on the space shuttle orbiter test taxi runs and captive flight tests were set forth. The orbiter test flights, the approach and landing tests (ALT), and the ground vibration tests were cited. Free flight plans, the space shuttle ALT crews, and 747 carrier aircraft crew were considered.

STS-68 747 SCA Ferry Flight Takeoff for Delivery to Kennedy Space Center, Florida

NASA Technical Reports Server (NTRS)

1994-01-01

The Space Shuttle Columbia, atop NASA's 747 Shuttle Carrier Aircraft (SCA), taking off for the Kennedy Space Center shortly after its landing on 12 October 1994, at Edwards, California, to complete mission STS-68. Columbia was being ferried from the Kennedy Space Center, Florida, to Air Force Plant 42, Palmdale, California, where it will undergo six months of inspections, modifications, and systems upgrades. The STS-68 11-day mission was devoted to radar imaging of Earth's geological features with the Space Radar Laboratory. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Boeing 747 jet modified to carry shuttle flying over Rocky Mountains

NASA Technical Reports Server (NTRS)

1977-01-01

A Boeing 747 jet aircraft, modified for use by NASA for the Space Shuttle Orbiter Approach and Landing Tests (ALTs), is seen in flight over the Rocky Mountains. Note the added structural supports atop the huge aircraft. The Shuttle Orbiter will ride 'piggy-back' atop the NASA 747 for the ALTs. The NASA 747 will be used also to transport Orbiters to the Space Shuttle launch sites.

KSC-2011-2879

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- Shuttle Atlantis' three main engines take center stage to the banners commemorating the orbiters that served the Space Shuttle Program. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

Hypersonic aeroheating test of space shuttle vehicle: Configuration 3 (model 22 OTS) in the NASA-Ames 3.5-foot hypersonic wind tunnel (IH20), volume 2

NASA Technical Reports Server (NTRS)

Kingsland, R. B.; Lockman, W. K.

1975-01-01

The model tested was an 0.0175-scale version of the vehicle 3 space shuttle configuration. Temperature measurements were made on the launch configuration, orbiter plus tank, orbiter alone, tank alone, and solid rocket booster (SRB) alone to provide heat transfer data. The test was conducted at free stream Mach numbers of 5.3 and 7.3 and at free stream Reynolds numbers of 1.5, 3.7, 5.0, and 7.0 million per foot. The model was tested at angles of attack from -5 deg to 20 deg and side slip angles of -5 deg and 0 deg.

Shuttle Discovery Overflight of Edwards Enroute to Palmdale, California, Maintenance Facility

NASA Technical Reports Server (NTRS)

1995-01-01

Space Shuttle Discovery overflies the Rogers Dry Lakebed, California, on 28 September 1995, at 12:50 p.m. Pacific Daylight Time (PDT) atop NASA's 747 Shuttle Carrier Aircraft (SCA). On its way to Rockwell Aerospace's Palmdale facility for nine months of scheduled maintenance, Discovery and the 747 were completing a two-day flight from Kennedy Space Center, Florida, that began at 7:04 a.m. Eastern Standard Time on 27 September and included an overnight stop at Salt Lake City International Airport, Utah. At the conclusion of this mission, Discovery had flown 21 shuttle missions, totaling more than 142 days in orbit. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Enterprise Mated to 747 SCA in Flight

NASA Technical Reports Server (NTRS)

1983-01-01

The Space Shuttle Enterprise, the nation's prototype space shuttle orbiter, departed NASA's Dryden Flight Research Center, Edwards, California, at 11:00 a.m., 16 May 1983, on the first leg of its trek to the Paris Air Show at Le Bourget Airport, Paris, France. Carried by the huge 747 Shuttle Carrier Aircraft (SCA), the first stop for the Enterprise was Peterson AFB, Colorado Springs, Colorado. Piloting the 747 on the Europe trip were Joe Algranti, Johnson Space Center Chief Pilot, Astronaut Dick Scobee, and NASA Dryden Chief Pilot Tom McMurtry. Flight engineers for that portion of the flight were Dryden's Ray Young and Johnson Space Center's Skip Guidry. The Enterprise, named after the spacecraft of Star Trek fame, was originally carried and launched by the 747 during the Approach and Landing Tests (ALT) at Dryden Flight Research Center. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Enterprise Mated to 747 SCA on Ramp

NASA Technical Reports Server (NTRS)

1982-01-01

The Space Shuttle Enterprise, the nation's prototype space shuttle orbiter, before departing NASA's Dryden Flight Research Center, Edwards, California, at 11:00 a.m., 16 May 1983, on the first leg of its trek to the Paris Air Show at Le Bourget Airport, Paris, France. Seen here atop the huge 747 Shuttle Carrier Aircraft (SCA), the first stop for the Enterprise was Peterson AFB, Colorado Springs, Colorado. Piloting the 747 on the Europe trip were Joe Algranti, Johnson Space Center Chief Pilot, Astronaut Dick Scobee, and NASA Dryden Chief Pilot Tom McMurtry. Flight engineers for that portion of the flight were Dryden's Ray Young and Johnson Space Center's Skip Guidry. The Enterprise, named after the spacecraft of Star Trek fame, was originally carried and launched by the 747 during the Approach and Landing Tests (ALT) at Dryden Flight Research Center. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Space shuttle orbiter digital data processing system timing sensitivity analysis OFT ascent phase

NASA Technical Reports Server (NTRS)

Lagas, J. J.; Peterka, J. J.; Becker, D. A.

1977-01-01

Dynamic loads were investigated to provide simulation and analysis of the space shuttle orbiter digital data processing system (DDPS). Segments of the ascent test (OFT) configuration were modeled utilizing the information management system interpretive model (IMSIM) in a computerized simulation modeling of the OFT hardware and software workload. System requirements for simulation of the OFT configuration were defined, and sensitivity analyses determined areas of potential data flow problems in DDPS operation. Based on the defined system requirements and these sensitivity analyses, a test design was developed for adapting, parameterizing, and executing IMSIM, using varying load and stress conditions for model execution. Analyses of the computer simulation runs are documented, including results, conclusions, and recommendations for DDPS improvements.

Investigation of the McDonnell-Douglas orbiter and booster shuttle models in proximity at Mach numbers 2.0 to 6.0. Volume 7: Proximity data at Mach 4 and 6, interference free and launch vehicle data

NASA Technical Reports Server (NTRS)

Trimmer, L. L.; Love, D. A.; Decker, J. P.; Blackwell, K. L.; Strike, W. T.; Rampy, J. M.

1972-01-01

Aerodynamic data obtained from a space shuttle abort stage separation wind tunnel test are presented. The .00556 scale models of the orbiter and booster configuration were tested in close proximity using dual balances during the time period of April 21 to April 27 1971. Data were obtained for both booster and orbiter over an angle of attack range from -10 to 10 deg for zero degree sideslip angle. The models were tested at several relative incidence angles and separation distances and power conditions. Plug nozzles utilizing air were used to simulate booster and orbiter plumes at various altitudes along a nominal ascent trajectory. Powered conditions were 100, 50, 25 and 0 percent of full power for the orbiter and 100, 50 and 0 percent of full power for the booster. Pitch control effectiveness data were obtained for both booster and orbiter with power on and off. In addition, launch vehicle data with and without booster power were obtained utilizing a single balance in the booster model. Data were also obtained with the booster canard off in close proximity and for the launch configuration.

Probabilistic risk assessment of the Space Shuttle. Phase 3: A study of the potential of losing the vehicle during nominal operation. Volume 4: System models and data analysis

NASA Technical Reports Server (NTRS)

Fragola, Joseph R.; Maggio, Gaspare; Frank, Michael V.; Gerez, Luis; Mcfadden, Richard H.; Collins, Erin P.; Ballesio, Jorge; Appignani, Peter L.; Karns, James J.

1995-01-01

In this volume, volume 4 (of five volumes), the discussion is focussed on the system models and related data references and has the following subsections: space shuttle main engine, integrated solid rocket booster, orbiter auxiliary power units/hydraulics, and electrical power system.

Results of an aerodynamic investigation of a space shuttle orbiter/747 carrier flight test configuration to determine separation characteristics utilizing 0.0125-scale models (48-0/AX1318I-1) in the LTV 4 x 4 foot high speed wind tunnel (CA26), volume 1

NASA Technical Reports Server (NTRS)

Gillins, R. L.

1976-01-01

Results of tests conducted on a 0.0125-scale model of the Space Shuttle Orbiter and a 0.0125-scale model of the 747 CAM configuration in a 4 x 4-foot High Speed Wind Tunnel were presented. Force and moment data were obtained for each vehicle separately at a Mach number of 0.6 and for each vehicle in proximity to the other at Mach numbers of 0.3, 0.5, 0.6 and 0.7. The proximity effects of each vehicle on the other at separation distances (from the mated configuration) ranging from 1.5 feet to 75 feet were presented; 747 Carrier angles of attack from 0 deg to 6 deg and angles of sideslip of 0 deg and -5 deg were tested. Model variables included orbiter elevon, aileron and body flap deflections, orbiter tailcone on and off, and 747 stabilizer and rudder deflections.

Experiment definition phase shuttle laboratory (LDRL-10.6 experiment): Shuttle sortie to elliptical orbit satellite

NASA Technical Reports Server (NTRS)

Goodwin, F. E.; Nussmeier, T. A.; Stokes, L. S.; Vourgourakis, E. J.

1976-01-01

The following topics were reviewed: (1) design options for shuttle terminal, (2) elliptical orbit satellite design options, (3) shuttle terminal details, (4) technology status and development requirements, (5) transmitter technology, and (6) carbon dioxide laser life studies.

STS-68 on Runway with 747 SCA/Columbia Ferry Flyby

NASA Technical Reports Server (NTRS)

1994-01-01

The space shuttle Endeavour receives a high-flying salute from its sister shuttle, Columbia, atop NASA's Shuttle Carrier Aircraft, shortly after Endeavor's landing 12 October 1994, at Edwards, California, to complete mission STS-68. Columbia was being ferried from the Kennedy Space Center, Florida, to Air Force Plant 42, Palmdale, California, where it will undergo six months of inspections, modifications, and systems upgrades. The STS-68 11-day mission was devoted to radar imaging of Earth's geological features with the Space Radar Laboratory. The orbiter is surrounded by equipment and personnel that make up the ground support convoy that services the space vehicles as soon as they land. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-68 on Runway with 747 SCA - Columbia Ferry Flyby

NASA Technical Reports Server (NTRS)

1994-01-01

The space shuttle Endeavour receives a high-flying salute from its sister shuttle, Columbia, atop NASA's Shuttle Carrier Aircraft, shortly after Endeavor's landing 12 October 1994, at Edwards, California, to complete mission STS-68. Columbia was being ferried from the Kennedy Space Center, Florida, to Air Force Plant 42, Palmdale, California, where it will undergo six months of inspections, modifications, and systems upgrades. The STS-68 11-day mission was devoted to radar imaging of Earth's geological features with the Space Radar Laboratory. The orbiter is surrounded by equipment and personnel that make up the ground support convoy that services the space vehicles as soon as they land. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle in Mate-Demate Device being Loaded onto SCA-747 - Rear View

NASA Technical Reports Server (NTRS)

1991-01-01

Evening light begins to fade at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, as technicians begin the task of mounting the Space Shuttle Atlantis atop NASA's 747 Shuttle Carrier Aircraft (NASA 911) for the ferry flight back to the Kennedy Space Center, Fla., following its STS-44 flight 24 November-1 December 1991. Post-flight servicing of the orbiters, and the mating operation is carried out at Dryden at the Mate-Demate Device, the large gantry-like structure that hoists the spacecraft to various levels during post-spaceflight processing and attachment to the 747. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle in Mate-Demate Device being Loaded onto SCA-747 - Side View

NASA Technical Reports Server (NTRS)

1991-01-01

Evening light begins to fade at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, as technicians begin the task of mounting the Space Shuttle Atlantis atop NASA's 747 Shuttle Carrier Aircraft (NASA #911) for the ferry flight back to the Kennedy Space Center, Fla., following its STS-44 flight 24 November-1 December 1991. Post-flight servicing of the orbiters, and the mating operation, is carried out at Dryden at the Mate-Demate Device (MDD), the large gantry-like structure that hoists the spacecraft to various levels during post-space flight processing and attachment to the 747. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Feasibility analysis of cislunar flight using the Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Haynes, Davy A.

1991-01-01

A first order orbital mechanics analysis was conducted to examine the possibility of utilizing the Space Shuttle Orbiter to perform payload delivery missions to lunar orbit. In the analysis, the earth orbit of departure was constrained to be that of Space Station Freedom. Furthermore, no enhancements of the Orbiter's thermal protection system were assumed. Therefore, earth orbit insertion maneuvers were constrained to be all propulsive. Only minimal constraints were placed on the lunar orbits and no consideration was given to possible landing sites for lunar surface payloads. The various phases and maneuvers of the mission are discussed for both a conventional (Apollo type) and an unconventional mission profile. The velocity impulses needed, and the propellant masses required are presented for all of the mission maneuvers. Maximum payload capabilities were determined for both of the mission profiles examined. In addition, other issues relating to the feasibility of such lunar shuttle missions are discussed. The results of the analysis indicate that the Shuttle Orbiter would be a poor vehicle for payload delivery missions to lunar orbit.

Early Program Development

NASA Image and Video Library

1971-01-01

In this 1971 artist's concept, the Nuclear Shuttle is shown in various space-based applications. As envisioned by Marshall Space Flight Center Program Development persornel, the Nuclear Shuttle would deliver payloads to geosychronous Earth orbits or lunar orbits then return to low Earth orbit for refueling. A cluster of Nuclear Shuttle units could form the basis for planetary missions.

Early Program Development

NASA Image and Video Library

1970-01-01

This artist's concept from 1970 shows a Nuclear Shuttle docked to an Orbital Propellant Depot and an early Space Shuttle. As envisioned by Marshall Space Flight Center Program Development plarners, the Nuclear Shuttle, in either manned or unmanned mode, would deliver payloads to lunar orbit or other destinations then return to Earth orbit for refueling and additonal missions.

Use of microgravity sensors for quantification of space shuttle orbiter vernier reaction control system induced environments

NASA Technical Reports Server (NTRS)

Friend, Robert B.

1998-01-01

In the modeling of spacecraft dynamics it is important to accurately characterize the environment in which the vehicle operates, including the environments induced by the vehicle itself. On the Space Shuttle these induced environmental factors include reaction control system plume. Knowledge of these environments is necessary for performance of control systems and loads analyses, estimation of disturbances due to thruster firings, and accurate state vector propagation. During the STS-71 mission, while the Orbiter was performing attitude control for the mated Orbiter/Mir stack, it was noted that the autopilot was limit cycling at a rate higher than expected from pre-flight simulations. Investigations during the mission resulted in the conjecture that an unmodelled plume impingement force was acting upon the orbiter elevons. The in-flight investigations were not successful in determining the actual magnitude of the impingement, resulting in several sequential post-flight investigations. Efforts performed to better quantify the vernier reaction control system induced plume impingement environment of the Space Shuttle orbiter are described in this paper, and background detailing circumstances which required the more detailed knowledge of the RCS self impingement forces, as well as a description of the resulting investigations and their results is presented. The investigations described in this paper applied microgravity acceleration data from two shuttle borne microgravity experiments, SAMS and OARE, to the solution of this particular problem. This solution, now used by shuttle analysts and mission planners, results in more accurate propellant consumption and attitude limit cycle estimates in preflight analyses, which are critical for pending International Space Station missions.

Low supersonic stability and control characteristics of .015-scale (remotely controlled elevon) model 44-0 of space shuttle orbiter tests in NASA/LaRC 4-ft UPWT (leg 1) (LA63A). [wind tunnel stability tests

NASA Technical Reports Server (NTRS)

Gamble, J. D.

1975-01-01

A Langley-built 0.015-scale Space Shuttle Orbiter model with remote independently operated left and right elevon surfaces was tested. The objective of the test was to generate a detailed aerodynamic data base for the current shuttle orbiter configuration. Special attention was directed to definition of nonlinear aerodynamic characteristics by taking data at small increments in angle of attack, angle of sideslip, and elevon position. Six-component aerodynamic force and moment and elevon position data were recorded over an angle of attack range from -2 deg to 20 deg at angles of sideslip of 0 deg and plus or minus 2 deg. Additional tests were made over an angle of range from -6 deg to 8 deg at selected angles of attack. The test Mach numbers were 1.5 and 2.0 while the Reynolds number held at a constant two million per foot. Photographs of the test configuration are shown.

Early Program Development

NASA Image and Video Library

1989-01-01

In this 1989 artist's concept, the Shuttle-C floats in space with its cargo bay doors open. As envisioned by Marshall Space Flight Center plarners, the Shuttle-C would be an unmanned heavy lift cargo vehicle derived from Space Shuttle elements. The vehicle would utilize the basic Shuttle propulsion units (Solid Rocket Boosters, Space Shuttle Main Engine, External Tank), but would replace the Oribiter with an unmanned Shuttle-C Cargo Element (SCE). The SCE would have a payload bay length of eighty-two feet, compared to sixty feet for the Orbiter cargo bay, and would be able to deliver 170,000 pound payloads to low Earth orbit, more than three times the Orbiter's capacity.

KSC-2011-2877

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- Kennedy Center Director Bob Cabana addresses the audience after the announcement that revealed the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-2859

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- Shuttle Atlantis' three main engines take center stage to the banners commemorating the orbiters that served the Space Shuttle Program. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

Shuttle Systems 3-D Applications: Application of 3-D Graphics in Engineering Training for Shuttle Ground Processing

NASA Technical Reports Server (NTRS)

Godfrey, Gary S.

2003-01-01

This project illustrates an animation of the orbiter mate to the external tank, an animation of the OMS POD installation to the orbiter, and a simulation of the landing gear mechanism at the Kennedy Space Center. A detailed storyboard was created to reflect each animation or simulation. Solid models were collected and translated into Pro/Engineer's prt and asm formats. These solid models included computer files of the: orbiter, external tank, solid rocket booster, mobile launch platform, transporter, vehicle assembly building, OMS POD fixture, and landing gear. A depository of the above solid models was established. These solid models were translated into several formats. This depository contained the following files: stl for sterolithography, stp for neutral file work, shrinkwrap for compression, tiff for photoshop work, jpeg for Internet use, and prt and asm for Pro/Engineer use. Solid models were created of the material handling sling, bay 3 platforms, and orbiter contact points. Animations were developed using mechanisms to reflect each storyboard. Every effort was made to build all models technically correct for engineering use. The result was an animated routine that could be used by NASA for training material handlers and uncovering engineering safety issues.

Results of tests CS4 and CS5 to investigate dynamic loads and pressures on 0.03-scale models (Ax1319-3/4 and 45-0) of mated 747 cam and space shuttle orbiter in the Boeing transonic wind tunnel

NASA Technical Reports Server (NTRS)

1976-01-01

A 0.03-scale model of the 747 CAM/Orbiter was tested in an 8 x 12 foot transonic wind tunnel. Dynamic loads, pressure, and empennage flow field data were obtained using pressure transducers, strain gages, and a split film anemometer. The test variables included Mach number, angle of attack, sideslip angle, orbiter tailcone on and off, orbiter partial tailcone, orbiter nozzle air scoops, orbiter body flap angle, and orbiter elevon angle.

KSC-2011-2872

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- Mike Parrish, space shuttle Endeavour's vehicle manager with United Space Alliance addresses the audience after the announcement that revealed the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

Hollow cathodes as electron emitting plasma contactors Theory and computer modeling

NASA Technical Reports Server (NTRS)

Davis, V. A.; Katz, I.; Mandell, M. J.; Parks, D. E.

1987-01-01

Several researchers have suggested using hollow cathodes as plasma contactors for electrodynamic tethers, particularly to prevent the Shuttle Orbiter from charging to large negative potentials. Previous studies have shown that fluid models with anomalous scattering can describe the electron transport in hollow cathode generated plasmas. An improved theory of the hollow cathode plasmas is developed and computational results using the theory are compared with laboratory experiments. Numerical predictions for a hollow cathode plasma source of the type considered for use on the Shuttle are presented, as are three-dimensional NASCAP/LEO calculations of the emitted ion trajectories and the resulting potentials in the vicinity of the Orbiter. The computer calculations show that the hollow cathode plasma source makes vastly superior contact with the ionospheric plasma compared with either an electron gun or passive ion collection by the Orbiter.

Data report for tests on the heat transfer effects of the 0.0175-scale Rockwell International Space Shuttle Vehicle model 22-OT in the AEDC 50-inch B wind tunnel (OH4B), volume 3

NASA Technical Reports Server (NTRS)

Foster, T. F.; Grifall, W. J.; Martindale, W.

1975-01-01

Results of wind tunnel heat transfer tests of 0.0175-scale Rockwell International Space Shuttle Vehicle configurations for orbiter alone, tank alone, and orbiter plus external tank are presented. Body flap shielding of SSME's during simulated entry was also investigated. The tests were conducted at Mach 8 for thirteen Reynolds number per foot values ranging from 0.5 million to 3.72 million.

Results of transonic/supersonic static stability wind tunnel tests of an 0.004-scale space shuttle orbiter model (0A49)

NASA Technical Reports Server (NTRS)

Allen, E.

1974-01-01

Experimental aerodynamic investigations of the configuration 4 space shuttle orbiter were conducted in the 14-inch trisonic wind tunnel during November and December 1973. Elevon, aileron, bodyflap, speedbrake, rudder effectiveness, and effects of ventral fins were investigated at angles of attack from -10 deg to 40 deg, angles of sideslip from -10 deg to +10 deg, and Mach numbers from 0.6 to 4.96. Resulting six-component static stability data and associated test information are presented.

Results of an aerodynamic force and moment investigation of an 0.015-scale configuration 3 space shuttle orbiter in the NASA/ARC 3.5-foot hypersonic wind tunnel (OA58)

NASA Technical Reports Server (NTRS)

Dziubala, T. J.; Cleary, J. W.

1974-01-01

The primary objective of the test was to obtain stability and control data for the basic configuration and an alternate configuration for the Space Shuttle Orbiter. Pitch runs were made with 0 deg of sideslip at Mach numbers of 5.3, 7.3 and 10.3. Six-component force data and fuselage base pressures were recorded for each run. Shadowgraph pictures were taken at selected points. Model 420 was used for the tests.

Results of investigation on an 0.004-scale 140c modified configuration space shuttle vehicle orbiter model (74-0) in the NASA/Langley Research Center hypersonic nitrogen tunnel (OA89)

NASA Technical Reports Server (NTRS)

Hawthorne, P. J.

1975-01-01

Wind tunnel test data for the modified space shuttle vehicle orbiter is documented. Tests were made at various elevon settings and additionally in wing off/bodyflap off configuration at angles of attack from -5 to 42.5 degrees at zero yaw. Data obtained on high hypersonic longitudinal and lateral directional stability and control characteristics of the updated SSV configuration in an initially diatomic medium are included.

Space Shuttle Orbiter trimmed center-of-gravity extension study. Volume 4: Effects of configuration modifications on the aerodynamic characteristics of the 139B orbiter at Mach 20.3

NASA Technical Reports Server (NTRS)

Scallion, W. I.; Stone, D. R.

1978-01-01

Force tests were conducted at Mach 20.3 to determine the effect of several forebody, wing-fillet, and canard modifications on the hypersonic trim capability of a 139B Space Shuttle Orbiter model. Force and moment data were obtained at angles of attack of 10 deg to 54 deg at zero sideslip angle and at a Reynolds number of 1,900,000 based on body length. The results indicated that wing-fillet and canard modifications would increase the allowable forward trimmed center-of-gravity capability by as much as 3.0 percent of the body length.

The calibration and flight test performance of the space shuttle orbiter air data system

NASA Technical Reports Server (NTRS)

Dean, A. S.; Mena, A. L.

1983-01-01

The Space Shuttle air data system (ADS) is used by the guidance, navigation and control system (GN&C) to guide the vehicle to a safe landing. In addition, postflight aerodynamic analysis requires a precise knowledge of flight conditions. Since the orbiter is essentially an unpowered vehicle, the conventional methods of obtaining the ADS calibration were not available; therefore, the calibration was derived using a unique and extensive wind tunnel test program. This test program included subsonic tests with a 0.36-scale orbiter model, transonic and supersonic tests with a smaller 0.2-scale model, and numerous ADS probe-alone tests. The wind tunnel calibration was further refined with subsonic results from the approach and landing test (ALT) program, thus producing the ADS calibration for the orbital flight test (OFT) program. The calibration of the Space Shuttle ADS and its performance during flight are discussed in this paper. A brief description of the system is followed by a discussion of the calibration methodology, and then by a review of the wind tunnel and flight test programs. Finally, the flight results are presented, including an evaluation of the system performance for on-board systems use and a description of the calibration refinements developed to provide the best possible air data for postflight analysis work.

Transonic wind tunnel tests of A.015 scale space shuttle orbiter model, volume 1

NASA Technical Reports Server (NTRS)

Struzynski, N. A.

1975-01-01

Transonic wind tunnel tests were run on a 0.015 scale model of the Space Shuttle Orbiter Vehicle in an eight-foot tunnel during August 1975. The purpose of the program was to obtain basic shuttle aerodynamic data through a full range of elevon and aileron deflections, verification of data obtained at other facilities, and effects of Reynolds numbers. The first part of a discussion of test procedures and results in both tabular and graphical form were presented. Tests were performed at Mach numbers from 0.35 to 1.20, and at Reynolds numbers for 3.5 million to 8.2 million per foot. The angle of attack was varied from -1 to +20 degrees at sideslip angles of -2, 0, +2 degrees. Sideslip was varied from -6 to +8 degrees at constant angles of attack from 0 to +20 degrees. Various aileron and ailevon settings were tested for various angles of attack.

Transonic wind tunnel tests of a .015 scale space shuttle orbiter model, volume 2

NASA Technical Reports Server (NTRS)

Struzynski, N. A.

1975-01-01

Transonic wind tunnel tests were run on a 0.015 scale model of the Space Shuttle Orbiter Vehicle in an eight-foot tunnel during August 1975. The purpose of the program was to obtain basic shuttle aerodynamic data through a full range of elevon and aileron deflections, verification of data obtained at other facilities, and effects of Reynolds numbers. The second part of a discussion of test procedures and results in both tabular and graphical form were presented. Tests were performed at Mach numbers from 0.35 to 1.20, and at Reynolds numbers from 3.5 million to 8.2 million per foot. The angle of attack was varied from -2 to +20 degrees at sideslip angles of -2, 0, +2 degrees. Sideslip was varied from -6 to +8 degrees at constant angles of attack from 0 to +20 degrees. Various aileron and ailevon settings were tested for various angles of attack.

STS-49 Landing at Edwards with First Drag Chute Landing

NASA Technical Reports Server (NTRS)

1992-01-01

The Space Shuttle Endeavour concludes mission STS-49 at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, with a 1:57 p.m. (PDT) landing 16 May on Edward's concrete runway 22. The planned 7-day mission, which began with a launch from Kennedy Space Center, Florida, at 4:41 p.m. (PFT), 7 May, was extended two days to allow extra time to rescue the Intelsat VI satellite and complete Space Station assembly techniques originally planned. After a perfect rendezvous in orbit and numerous attempts to grab the satellite, space walking astronauts Pierre Thuot, Rick Hieb and Tom Akers successfully rescued it by hand on the third space walk with the support of mission specialists Kathy Thornton and Bruce Melnick. The three astronauts, on a record space walk, took hold of the satellite and directed it to the shuttle where a booster motor was attached to launch it to its proper orbit. Commander Dan Brandenstein and Pilot Kevin Chilton brought Endeavours's record setting maiden voyage to a perfect landing at Edwards AFB with the first deployment of a drag chute on a shuttle mission. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-49 Landing at Edwards with First Drag Chute Landing

NASA Technical Reports Server (NTRS)

1992-01-01

The Space Shuttle Endeavour concludes mission STS-49 at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, with a 1:57 p.m. (PDT) landing May 16 on Edward's concrete runway 22. The planned 7-day mission, which began with a launch from Kennedy Space Center, Florida, at 4:41 p.m. (PFT), 7 May, was extended two days to allow extra time to rescue the Intelsat VI satellite and complete Space Station assembly techniques originally planned. After a perfect rendezvous in orbit and numerous attempts to grab the satellite, space walking astronauts Pierre Thuot, Rick Hieb and Tom Akers successfully rescued it by hand on the third space walk with the support of mission specialists Kathy Thornton and Bruce Melnick. The three astronauts, on a record space walk, took hold of the satellite and directed it to the shuttle where a booster motor was attached to launch it to its proper orbit. Commander Dan Brandenstein and Pilot Kevin Chilton brought Endeavours's record setting maiden voyage to a perfect landing at Edwards with the first deployment of a drag chute on a shuttle mission. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-76 Landing - Space Shuttle Atlantis Lands at Edwards Air Force Base, Drag Chute Deploy

NASA Technical Reports Server (NTRS)

1996-01-01

The space shuttle Atlantis touches down on the runway at Edwards, California, at approximately 5:29 a.m. Pacific Standard Time after completing the highly successful STS-76 mission to deliver Astronaut Shannon Lucid to the Russian Space Station Mir. She was the first American woman to serve as a Mir station researcher. Atlantis was originally scheduled to land at Kennedy Space Center, Florida, but bad weather there both 30 and 31 March necessitated a landing at the backup site at Edwards. This photo shows the drag chute deployed to help the shuttle roll to a stop. Mission commander for STS-76 was Kevin P. Chilton, and Richard A. Searfoss was the pilot. Ronald M. Sega was payload commander and mission specialist-1. Mission specialists were Richard Clifford, Linda Godwin and Shannon Lucid. The mission also featured a spacewalk while Atlantis was docked to Mir and experiments aboard the SPACEHAB module. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Orbiter/payload contamination control assessment support

NASA Technical Reports Server (NTRS)

Rantanen, R. O.; Strange, D. A.; Hetrick, M. A.

1978-01-01

The development and integration of 16 payload bay liner filters into the existing shuttle/payload contamination evaluation (SPACE) computer program is discussed as well as an initial mission profile model. As part of the mission profile model, a thermal conversion program, a temperature cycling routine, a flexible plot routine and a mission simulation of orbital flight test 3 are presented.

Effects of damping on mode shapes, volume 2

NASA Technical Reports Server (NTRS)

Gates, R. M.; Merchant, D. H.; Arnquist, J. L.

1977-01-01

Displacement, velocity, and acceleration admittances were calculated for a realistic NASTRAN structural model of space shuttle for three conditions: liftoff, maximum dynamic pressure and end of solid rocket booster burn. The realistic model of the orbiter, external tank, and solid rocket motors included the representation of structural joint transmissibilities by finite stiffness and damping elements. Data values for the finite damping elements were assigned to duplicate overall low-frequency modal damping values taken from tests of similar vehicles. For comparison with the calculated admittances, position and rate gains were computed for a conventional shuttle model for the liftoff condition. Dynamic characteristics and admittances for the space shuttle model are presented.

Photography by KSC Space Shuttle Orbiter Enterprise mated to an external fuel tank and two solid

NASA Technical Reports Server (NTRS)

1980-01-01

Photography by KSC Space Shuttle Orbiter Enterprise mated to an external fuel tank and two solid rocket boosters on top of a Mobil Launcher Platform, undergoes fit and function checks at the launch site for the first Space Shuttle at Launch Complex 39's Pad A. The dummy Space Shuttle was assembled in the Vehicle Assembly Building and rolled out to the launch site on May 1 as part of an exercise to make certain shuttle elements are compatible with the Spaceport's assembly and launch facilities and ground support equipment, and help clear the way for the launch of the Space Shuttle Orbiter Columbia.

PHOTOGRAPHY BY KSC SPACE SHUTTLE ORBITER ENTERPRISE MATED TO AN EXTERNAL FUEL TANK AND TWO SOLID

NASA Technical Reports Server (NTRS)

1980-01-01

PHOTOGRAPHY BY KSC SPACE SHUTTLE ORBITER ENTERPRISE MATED TO AN EXTERNAL FUEL TANK AND TWO SOLID ROCKET BOOSTERS ON TOP OF A MOBIL LAUNCHER PLATFORM, UNDERGOES FIT AND FUNCTION CHECKS AT THE LAUNCH SITE FOR THE FIRST SPACE SHUTTLE AT LAUNCH COMPLEX 39'S PAD A. THE DUMMY SPACE SHUTTLE WAS ASSEMBLED IN THE VEHICLE ASSEMBLY BUILDING AND ROLLED OUT TO THE LAUNCH SITE ON MAY 1 AS PART OF AN EXERCISE TO MAKE CERTAIN SHUTTLE ELEMENTS ARE COMPATIBLE WITH THE SPACEPORT'S ASSEMBLY AND LAUNCH FACILITIES AND GROUND SUPPORT EQUIPMENT, AND HELP CLEAR THE WAY FOR THE LAUNCH OF THE SPACE SHUTTLE ORBITER COLUMBIA.

The use of a block diagram simulation language for rapid model prototyping

NASA Technical Reports Server (NTRS)

Whitlow, Jonathan E.

1995-01-01

The research performed this summer focussed on the development of a predictive model for the loading of liquid oxygen (LO2) into the external tank (ET) of the shuttle prior to launch. A predictive model can greatly aid the operational personnel since instrumentation aboard the orbiter and ET is limited due to weight constraints. The model, which focuses primarily on the orbiter section of the system was developed using a block diagram based simulation language known as VisSim. Simulations were run on LO2 loading data for shuttle flights STS50 and STS55 and the model was demonstrated to accurately predict the sensor data recorded for these flights. As a consequence of the simulation results, it can be concluded that the software tool can be very useful for rapid prototyping of complex models.

Boeing 747 jet modified to carry shuttle en route to Dryden

NASA Technical Reports Server (NTRS)

1977-01-01

A Boeing 747 jet aircraft, modified for use by NASA for the Space Shuttle Orbiter Approach and Landing Tests (ALTs), is seen en route from the Boeing facility at Seattle, Washington, to the Dryden Flight Research Center in Southern California. Note the added structural supports atop the huge aircraft. The Shuttle Orbiter will ride 'piggy-back' atop the NASA 747 for the ALTs. The NASA 747 will be used also to transport Orbiters to the Space Shuttle launch sites.

Shuttle/GPSPAC experimentation study

NASA Technical Reports Server (NTRS)

Moses, J.; Flack, J. F.

1977-01-01

The utilization is discussed of the GPSPAC, which is presently being developed to be used on the low altitude host vehicle (LAHV), for possible use in the shuttle avionics system to evaluate shuttle/GPS navigation performance. Analysis and tradeoffs of the shuttle/GPS link, shuttle signal interface requirements, oscillator tradeoffs and GPSPAC mechanical modifications for shuttle are included. Only the on-orbit utilization of GPSPAC for the shuttle is discussed. Other phases are briefly touched upon. Recommendations are provided for using the present GPSPAC and the changes required to perform shuttle on-orbit navigation.

Space shuttle phase B wind tunnel model and test information. Volume 1: Booster configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include the booster, the orbiter, and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. This is Volume 1 (Part 2) of the report -- Booster Configuration.

Space shuttle phase B wind tunnel model and test information. Volume 1: Booster configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include the booster, the orbiter and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks, and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. This is Volume 1 (Part 1) of the report -- Booster Configuration.

Space shuttle phase B wind tunnel model and test information. Volume 3: Launch configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel test data are available for flyback booster or other alternate recoverable configuration as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle, including contractor data for an extensive variety of configurations with an array of wing and body planforms. The test data have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration. Basic components include booster, orbiter, and launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configurations include straight and delta wings, lifting body, drop tanks and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. The digital database consists of 220 files containing basic tunnel data. Database structure is documented in a series of reports which include configuration sketches for the various planforms tested. This is Volume 3 -- launch configurations.

On plasma disturbances caused by the motion of the Space Shuttle and small satellites - A comparison of in situ observations

NASA Technical Reports Server (NTRS)

Samir, U.; Stone, N. H.; Wright, K. H., Jr.

1986-01-01

Recent results regarding the interactions between a body and its environmental space plasma, made by charged particle probes mounted in the bay of the Space Shuttle Orbiter Columbia (STS 3 mission), are compared with earlier results, obtained from small ionospheric satellites, in an attempt to widen our scope of knowledge and understanding regarding such interactions. The objective is to work toward a unified model of body-space plasma interactions in the solar system covering a variety of plasma and body conditions. The comparisons focus mainly on (1) the (wake/ram) current ratio; (2) the generation of charged particle density fluctuations (indicative of plasma turbulence) around the body; and (3) the increase in electron temperature ahead and in the wake of the satellite. The main results of the comparison are that (1) the (wake/ram) current ratio (or current depletion in the wake) for the Orbiter is 1 to 2 orders of magnitude larger than the ratio for small ionospheric satellites; and (2) fluctuations in density (or turbulence) are observed for both 'large body' (Shuttle Orbiter) and 'smaller body' (standard ionospheric satellites). However, the cause of the turbulence may not be the same for both cases; (3) the results for the electronic temperature enhancement due to the Shuttle Orbiter are in contrast with measurements from smaller ionospheric satellites. A path to follow in future Shuttle experiments is suggested and caution that care be taken in interpreting local particle and field measurements.

STS-76 Landing - Space Shuttle Atlantis Lands at Edwards Air Force Base

NASA Technical Reports Server (NTRS)

1996-01-01

The space shuttle Atlantis touches down on the runway at Edwards, California, at approximately 5:29 a.m. Pacific Standard Time on 31 March 1996 after completing the highly successful STS-76 mission to deliver Astronaut Shannon Lucid to the Russian Space Station Mir. She was the first American woman to serve as a Mir station researcher. Atlantis was originally scheduled to land at Kennedy Space Center, Florida, but bad weather there both March 30 and March 31 necessitated a landing at the backup site at Edwards AFB. Mission commander for STS-76 was Kevin P. Chilton. Richard A. Searfoss was the pilot. Serving as payload commander and mission specialist-1 was Ronald M. Sega. Mission specialist-2 was Richard Clifford. Linda Godwin served as mission specialist-3, and Shannon Lucid was mission specialist-4. The mission also featured a spacewalk while Atlantis was docked to Mir and experiments aboard the SPACEHAB module. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-76 Landing - Space Shuttle Atlantis Lands at Edwards Air Force Base

NASA Technical Reports Server (NTRS)

1996-01-01

The space shuttle Atlantis prepares to touch down on the runway at Edwards, California, at approximately 5:29 a.m. Pacific Standard Time after completing the highly successful STS-76 mission to deliver Astronaut Shannon Lucid to the Russian Space Station Mir. Lucid was the first American woman to serve as a Mir station researcher. Atlantis was originally scheduled to land at Kennedy Space Center, Florida, but bad weather there both 30 March and 31 March necessitated a landing at the backup site at Edwards on the latter date. Mission commander for STS-76 was Kevin P. Chilton, and Richard A. Searfoss was the pilot. Ronald M. Sega was the payload commander and mission specialist-1. Other mission specialists were Richard Clifford, Linda Godwin, and Shannon Lucid. The mission also featured a spacewalk while Atlantis was docked to Mir and experiments aboard the SPACEHAB module. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-76 - Being Prepared for Delivery to Kennedy Space Center via SCA 747 Aircraft

NASA Technical Reports Server (NTRS)

1996-01-01

Moonrise over Atlantis: the space shuttle Atlantis receives post-flight servicing in the Mate-Demate Device (MDD), following its landing at NASA's Dryden Flight Research Center, Edwards, California, 31 March 1996. Once servicing was complete, one of NASA's two 747 Shuttle Carrier Aircraft, No. 905, was readied to ferry Atlantis back to the Kennedy Space Center, Florida. Delivery of Atlantis to Florida was delayed until 11 April 1996, due to an engine warning light that appeared shortly after take off on April 6. The SCA returned to Edwards only minutes after departure. The right inboard engine #3 was exchanged, and the 747 with Atlantis atop was able to depart 11 April for Davis-Monthan Air Force Base for a refueling stop. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-76 - SCA 747 Aircraft Takeoff for Delivery to Kennedy Space Center

NASA Technical Reports Server (NTRS)

1996-01-01

NASA's Boeing 747 Shuttle Carrier Aircraft leaves the runway with the Shuttle Atlantis on its back. Following the STS-76 dawn landing at NASA's Dryden Flight Research Center, Edwards, California, on 31 March 1996. NASA 905, one of two modified 747's, was prepared to ferry Atlantis back to the Kennedy Space Center, FL. Delivery of Altlantis to Florida was delayed until 11 April 1996, due to an engine warning light that appeared shortly after take off on 6 April. The SCA #905 returned to Edwards with Atlantis aboard only minutes after departure. The right inboard engine #3 was exchanged and the 747 with Atlantis atop was able to depart for Davis-Monthan Air Force Base for a refueling stop. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-66 Atlantis 747 SCA Ferry Flight Morning Takeoff for Delivery to Kennedy Space Center, Florida

NASA Technical Reports Server (NTRS)

1994-01-01

The space shuttle Atlantis atop NASA's 747 Shuttle Carrier Aircraft (SCA) during takeoff for a return ferry flight to the Kennedy Space Center from Edwards, California. The STS-66 mission was dedicated to the third flight of the Atmospheric Laboratory for Applications and Science-3 (ATLAS-3), part of NASA's Mission to Planet Earth program. The astronauts also deployed and retrieved a free-flying satellite designed to study the middle and lower thermospheres and perform a series of experiments covering life sciences research and microgravity processing. The landing was at 7:34 a.m. (PST) 14 November 1994, after being waved off from the Kennedy Space Center, Florida, due to adverse weather. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Discovery Landing at Edwards

NASA Technical Reports Server (NTRS)

1989-01-01

The STS-29 Space Shuttle Discovery mission lands at NASA's then Ames-Dryden Flight Research Facility, Edwards AFB, California, early Saturday morning, 18 March 1989. Touchdown was at 6:35:49 a.m. PST and wheel stop was at 6:36:40 a.m. on runway 22. Controllers chose the concrete runway for the landing in order to make tests of braking and nosewheel steering. The STS-29 mission was very successful, completing the launch of a Tracking and Data Relay communications satellite, as well as a range of scientific experiments. Discovery's five-man crew was led by Commander Michael L. Coats, and included pilot John E. Blaha and mission specialists James P. Bagian, Robert C. Springer, and James F. Buchli. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

An empirical method for computing leeside centerline heating on the Space Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Helms, V. T., III

1981-01-01

An empirical method is presented for computing top centerline heating on the Space Shuttle Orbiter at simulated reentry conditions. It is shown that the Shuttle's top centerline can be thought of as being under the influence of a swept cylinder flow field. The effective geometry of the flow field, as well as top centerline heating, are directly related to oil-flow patterns on the upper surface of the fuselage. An empirical turbulent swept cylinder heating method was developed based on these considerations. The method takes into account the effects of the vortex-dominated leeside flow field without actually having to compute the detailed properties of such a complex flow. The heating method closely predicts experimental heat-transfer values on the top centerline of a Shuttle model at Mach numbers of 6 and 10 over a wide range in Reynolds number and angle of attack.

Space Shuttle Projects

NASA Image and Video Library

1991-08-01

The free-flying Tracking and Data Relay Satellite-E (TDRS-E), still attached to an Inertial Upper Stage (IUS), was photographed by one of the crewmembers during the STS-43 mission. The TDRS-E was boosted by the IUS into geosynchronous orbit and positioned to remain stationary 22,400 miles above the Pacific Ocean southwest of Hawaii. The TDRS system provides almost uninterrupted communications with Earth-orbiting Shuttles and satellites, and had replaced the intermittent coverage provided by globe-encircling ground tracking stations used during the early space program. The TDRS can transmit and receive data, and track a user spacecraft in a low Earth orbit. The IUS is an unmarned transportation system designed to ferry payloads from low Earth orbit to higher orbits that are unattainable by the Shuttle. The Space Shuttle Orbiter Atlantis for the STS-43 mission was launched on August 2, 1991.

KSC-2011-2861

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- Kennedy Center Director Bob Cabana addresses the audience poised to hear which of the four institutions will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

KSC-2011-2864

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA officials, Florida representatives,Kennedy employees and media applaud the announcement that revealed the four institutions receiving shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

Early Program Development

NASA Image and Video Library

1970-01-01

In this 1970 artist's concept, the Nuclear Shuttle is shown in its lunar and geosynchronous orbit configuration and in its planetary mission configuration. As envisioned by Marshall Space Flight Center Program Development plarners, the Nuclear Shuttle would deliver payloads to lunar orbit or other destinations then return to Earth orbit for refueling. A cluster of Nuclear Shuttle units could form the basis for planetary missions.

Space Station on-orbit solar array loads during assembly

NASA Astrophysics Data System (ADS)

Ghofranian, S.; Fujii, E.; Larson, C. R.

This paper is concerned with the closed-loop dynamic analysis of on-orbit maneuvers when the Space Shuttle is fully mated to the Space Station Freedom. A flexible model of the Space Station in the form of component modes is attached to a rigid orbiter and on-orbit maneuvers are performed using the Shuttle Primary Reaction Control System jets. The traditional approach for this type of problems is to perform an open-loop analysis to determine the attitude control system jet profiles based on rigid vehicles and apply the resulting profile to a flexible Space Station. In this study a closed-loop Structure/Control model was developed in the Dynamic Analysis and Design System (DADS) program and the solar array loads were determined for single axis maneuvers with various delay times between jet firings. It is shown that the Digital Auto Pilot jet selection is affected by Space Station flexibility. It is also shown that for obtaining solar array loads the effect of high frequency modes cannot be ignored.

Dynamics Impact Tolerance of Shuttle RCC Leading Edge Panels Using LS-DYNA

NASA Technical Reports Server (NTRS)

Fasanella, Edwin L.; Jackson, Karen E.; Lyle, Karen H.; Jones, Lisa E.; Hardy, Robin C.; Spellman, Regina L.; Carney, Kelly S.; Melis, Matthew E.; Stockwell, Alan E.

2005-01-01

This paper describes a research program conducted to enable accurate prediction of the impact tolerance of the shuttle Orbiter leading-edge wing panels using physics-based codes such as LS-DYNA, a nonlinear, explicit transient dynamic finite element code. The shuttle leading-edge panels are constructed of Reinforced-Carbon-Carbon (RCC) composite material, which is used because of its thermal properties to protect the shuttle during reentry into the Earth's atmosphere. Accurate predictions of impact damage from insulating foam and other debris strikes that occur during launch required materials characterization of expected debris, including strain-rate effects. First, analytical models of individual foam and RCC materials were validated. Next, analytical models of foam cylinders impacting 6- in. x 6-in. RCC flat plates were developed and validated. LS-DYNA pre-test models of the RCC flat plate specimens established the impact velocity of the test for three damage levels: no-detectable damage, non-destructive evaluation (NDE) detectable damage, or visible damage such as a through crack or hole. Finally, the threshold of impact damage for RCC on representative Orbiter wing panels was predicted for both a small through crack and for NDE-detectable damage.

Dynamic Impact Tolerance of Shuttle RCC Leading Edge Panels using LS-DYNA

NASA Technical Reports Server (NTRS)

Fasanella, Edwin; Jackson, Karen E.; Lyle, Karen H.; Jones, Lisa E.; Hardy, Robin C.; Spellman, Regina L.; Carney, Kelly S.; Melis, Matthew E.; Stockwell, Alan E.

2008-01-01

This paper describes a research program conducted to enable accurate prediction of the impact tolerance of the shuttle Orbiter leading-edge wing panels using 'physics-based- codes such as LS-DYNA, a nonlinear, explicit transient dynamic finite element code. The shuttle leading-edge panels are constructed of Reinforced-Carbon-Carbon (RCC) composite material, which issued because of its thermal properties to protect the shuttle during re-entry into the Earth's atmosphere. Accurate predictions of impact damage from insulating foam and other debris strikes that occur during launch required materials characterization of expected debris, including strain-rate effects. First, analytical models of individual foam and RCC materials were validated. Next, analytical models of individual foam cylinders impacting 6-in. x 6-in. RCC flat plates were developed and validated. LS-DYNA pre-test models of the RCC flat plate specimens established the impact velocity of the test for three damage levels: no-detectable damage, non-destructive evaluation (NDE) detectable damage, or visible damage such as a through crack or hole. Finally, the threshold of impact damage for RCC on representative Orbiter wing panels was predicted for both a small through crack and for NDE-detectable damage.

KSC-2011-2880

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA officials, Florida representatives, Kennedy employees and media await the announcement that will reveal the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-2882

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA officials, Florida representatives, Kennedy employees and media stand to applaud the news that revealed the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-2876

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA officials, Florida representatives, Kennedy employees and media listen to the speakers after the announcement that revealed the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-2871

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA Astronaut and Director of Flight Crew Operations, Janet Kavandi addresses the audience after the announcement that revealed the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-2881

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA Administrator Charles Bolden and Kennedy Center Director Bob Cabana sit on the dias listening to other speakers prior to the announcement that will reveal the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-2870

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA Administrator Charles Bolden and Kennedy Center Director Bob Cabana sit on the dias listening to other speakers after the announcement that revealed the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-2873

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- STS-1 Pilot and former Kennedy Space Center Director Bob Crippen addresses the audience after the announcement that revealed the four institutions that will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

Space Shuttle Project

NASA Image and Video Library

1978-10-04

The Shuttle Orbiter Enterprise inside of Marshall Space Flight Center's Dynamic Test Stand for Mated Vertical Ground Vibration tests (MVGVT). The tests marked the first time ever that the entire shuttle complement including Orbiter, external tank, and solid rocket boosters were vertically mated.

Results of differential elevon/aileron deflection for lateral control optimization and elevon hinge moment investigations on an 0.015-scale model (49-0) of the space shuttle orbiter in the NASA/Langley Research Center 8 foot TPT (OA116)

NASA Technical Reports Server (NTRS)

Lindsey, A. I.; Milam, M. D.

1974-01-01

Aerodynamic investigations were conducted in a transonic pressure tunnel on an 0.015 scale model of the space shuttle orbiter. Major test objectives were to determine: (1) transonic differential elevon/aileron lateral control optimization; (2) transonic elevon hinge moments; (3) transonic effects of the baseline 6 inch elevon/elevon and elevon/fuselage gaps; and (4) transonic effects of the short OMS pods. Six-component aerodynamic force and moment, and elevon hinge moment data, were recorded over an angle-of-attack range form -2 to +22 degrees.

Numerical computation of complex multi-body Navier-Stokes flows with applications for the integrated Space Shuttle launch vehicle

NASA Technical Reports Server (NTRS)

Chan, William M.

1993-01-01

An enhanced grid system for the Space Shuttle Orbiter was built by integrating CAD definitions from several sources and then generating the surface and volume grids. The new grid system contains geometric components not modeled previously plus significant enhancements on geometry that has been modeled in the old grid system. The new orbiter grids were then integrated with new grids for the rest of the launch vehicle. Enhancements were made to the hyperbolic grid generator HYPGEN and new tools for grid projection, manipulation, and modification, Cartesian box grid and far field grid generation and post-processing of flow solver data were developed.

Gap heating with pressure gradients. [for Shuttle Orbiter thermal protection system tiles

NASA Technical Reports Server (NTRS)

Scott, C. D.; Maraia, R. J.

1979-01-01

The heating rate distribution and temperature response on the gap walls of insulating tiles is analyzed to determine significant phenomena and parameters in flows where there is an external surface pressure gradient. Convective heating due to gap flow, modeled as fully developed pipe flow, is coupled with a two-dimensional thermal model of the tiles that includes conduction and radiative heat transfer. To account for geometry and important environmental parameters, scale factors are obtained by curve-fitting measured temperatures to analytical solutions. These scale factors are then used to predict the time-dependent gap heat flux and temperature response of tile gaps on the Space Shuttle Orbiter during entry.

Thermal environments for Space Shuttle payloads

NASA Technical Reports Server (NTRS)

Fu, J. H.; Graves, G. R.

1985-01-01

The thermal environment of the Space Shuttle payload bay during the on-orbit phase of the STS flights is presented. The STS Thermal Flight Instrumentation System and various substructures of the Orbiter and the payload are described, as well as the various on-orbit attitudes encountered in the STS flights (the tail to sun, nose to sun, payload bay to sun, etc.). Included are the temperature profiles obtained during the on-orbit STS 1-5 flights (with the payload bay door open), recorded in various substructures of the Orbiter's midsection at different flight attitudes, as well as schematic illustrations of the Space Shuttle system, a typical mission profile, and the Orbiter's substructures.

STS-76 - Being Prepared for Delivery to Kennedy Space Center via SCA 747 Aircraft

NASA Technical Reports Server (NTRS)

1996-01-01

Moonrise over Atlantis: following the STS-76 dawn landing at NASA's Dryden Flight Research Center, Edwards, California, on 31 March 1996, NASA 905, one of two modified Boeing 747 Shuttle Carrier Aircraft, was prepared to ferry Atlantis back to the Kennedy Space Center, FL. Delivery of Altlantis to Florida was delayed until 11 April 1996, due to an engine warning light that appeared shortly after take off on April 6. The SCA #905 returned to Edwards only minutes after departure. The right inboard engine #3 was exchanged and the 747 with Atlantis atop was able to depart for Davis-Monthan Air Force Base for a refueling stop. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-76 - Being Prepared for Delivery to Kennedy Space Center via SCA 747 Aircraft

NASA Technical Reports Server (NTRS)

1996-01-01

Moonrise over Atlantis following the STS-76 dawn landing at NASA's Dryden Flight Research Center, Edwards, California, on 31 March 1996. NASA 905, one of two modified Boeing 747 Shuttle Carrier Aircraft (SCA), was readied to ferry Atlantis back to the Kennedy Space Center, Florida. Delivery of Atlantis to Florida was delayed until 11 April 1996, due to an engine warning light that appeared shortly after take off on 6 April. The SCA #905 returned to Edwards with Atlantis attached only minutes after departure. The right inboard engine #3 was exchanged and the 747 with Atlantis atop was able to depart for Davis-Monthan Air Force Base for a refueling stop. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-58 Landing at Edwards with Drag Chute

NASA Technical Reports Server (NTRS)

1993-01-01

A drag chute slows the space shuttle Columbia as it rolls to a perfect landing concluding NASA's longest mission at that time, STS-58, at the Ames-Dryden Flight Research Facility (later redesignated the Dryden Flight Research Center), Edwards, California, with a 8:06 a.m. (PST) touchdown 1 November 1993 on Edward's concrete runway 22. The planned 14 day mission, which began with a launch from Kennedy Space Center, Florida, at 7:53 a.m. (PDT), October 18, was the second spacelab flight dedicated to life sciences research. Seven Columbia crewmembers performed a series of experiments to gain more knowledge on how the human body adapts to the weightless environment of space. Crewmembers on this flight included: John Blaha, commander; Rick Searfoss, pilot; payload commander Rhea Seddon; mission specialists Bill MacArthur, David Wolf, and Shannon Lucid; and payload specialist Martin Fettman. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

STS-29 Landing Approach at Edwards

NASA Technical Reports Server (NTRS)

1989-01-01

The STS-29 Space Shuttle Discovery mission approaches for a landing at NASA's then Ames-Dryden Flight Research Facility, Edwards AFB, California, early Saturday morning, 18 March 1989. Touchdown was at 6:35:49 a.m. PST and wheel stop was at 6:36:40 a.m. on runway 22. Controllers chose the concrete runway for the landing in order to make tests of braking and nosewheel steering. The STS-29 mission was very successful, completing the launch a Tracking and Data Relay communications satellite, as well as a range of scientific experiments. Discovery's five man crew was led by Commander Michael L. Coats, and included pilot John E. Blaha and mission specialists James P. Bagian, Robert C. Springer, and James F. Buchli. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Composite Overwrapped Pressure Vessels (COPV): Flight Rationale for the Space Shuttle Program

NASA Technical Reports Server (NTRS)

Kezirian, Michael T.; Johnson, Kevin L.; Phoenix, Stuart L.

2011-01-01

Each Orbiter Vehicle (Space Shuttle Program) contains up to 24 Kevlar49/Epoxy Composite Overwrapped Pressure Vessels (COPV) for storage of pressurized gases. In the wake of the Columbia accident and the ensuing Return To Flight (RTF) activities, Orbiter engineers reexamined COPV flight certification. The original COPV design calculations were updated to include recently declassified Kevlar COPV test data from Lawrence Livermore National Laboratory (LLNL) and to incorporate changes in how the Space Shuttle was operated as opposed to orinigially envisioned. 2005 estimates for the probability of a catastrophic failure over the life of the program (from STS-1 through STS-107) were one-in-five. To address this unacceptable risk, the Orbiter Project Office (OPO) initiated a comprehensive investigation to understand and mitigate this risk. First, the team considered and eventually deemed unfeasible procuring and replacing all existing flight COPVs. OPO replaced the two vessels with the highest risk with existing flight spare units. Second, OPO instituted operational improvements in ground procedures to signficiantly reduce risk, without adversely affecting Shuttle capability. Third, OPO developed a comprehensive model to quantify the likelihood of occurrance. A fully-instrumented burst test (recording a lower burst pressure than expected) on a flight-certified vessel provided critical understanding of the behavior of Orbiter COPVs. A more accurate model was based on a newly-compiled comprehensive database of Kevlar data from LLNL and elsewhere. Considering hardware changes, operational improvements and reliability model refinements, the mean reliability was determined to be 0.998 for the remainder of the Shuttle Program (from 2007, for STS- 118 thru STS-135). Since limited hardware resources precluded full model validation through multiple tests, additional model confidence was sought through the first-ever Accelerated Stress Rupture Test (ASRT) of a flown flight article. A Bayesian statistical approach was developed to interpret possible test results. Since the lifetime observed in the ASRT exceeded initial estimates by one to two orders of magnitude, the Space Shuttle Program deemed there was significant conservatism in the model and accepted continued operation with existing flight hardware. Given the variability in tank-to-tank original prooftest response, a non-destructive evaluation (NDE) technique utilizing Raman Spectroscopy was developed to directly measure COPV residual stress state. Preliminary results showed that patterns of low fiber elastic strains over the outside vessel surface, together with measured permanent volume growth during proof, could be directly correlated to increased fiber stress ratios on the inside fibers adjacent to the liner, and thus reduced reliability.

Results of aerodynamic heat transfer tests of a 0.0175-scale model of the Rockwell International Space Shuttle Orbiter 139 (model number 22-0) in the NASA/Ames 3.5-foot hypersonic wind tunnel (test OH6)

NASA Technical Reports Server (NTRS)

Dye, W. H.; Lockman, W. K.

1975-01-01

The results of a hypersonic wind tunnel test program conducted using a 0.0175 scale thin-skin thermocouple model of the Space Shuttle Orbiter to obtain aerodynamic heat transfer data on the Orbiter under simulated reentry conditions were presented. The test program was conducted at a Mach number of 7.3 and a freestream Reynolds number ranging between 1.0 and 6.0 million/foot. The model was tested for angles of attack ranging between 10 deg and 30 deg and a sideslip angle of 0 deg. The model was constructed of 15-5 PH stainless steel with the instrumented areas machined to a nominal skin thickness of 0.030 in. The model instrumentation consisted of 288 iron-constantan thermocouples spot welded to the skin inner surface, but only 75 of these were used in this test program. A high-speed, analog-to-digital data acquisition system was used to record data on magnetic tape.

High Level Architecture Distributed Space System Simulation for Simulation Interoperability Standards Organization Simulation Smackdown

NASA Technical Reports Server (NTRS)

Li, Zuqun

2011-01-01

Modeling and Simulation plays a very important role in mission design. It not only reduces design cost, but also prepares astronauts for their mission tasks. The SISO Smackdown is a simulation event that facilitates modeling and simulation in academia. The scenario of this year s Smackdown was to simulate a lunar base supply mission. The mission objective was to transfer Earth supply cargo to a lunar base supply depot and retrieve He-3 to take back to Earth. Federates for this scenario include the environment federate, Earth-Moon transfer vehicle, lunar shuttle, lunar rover, supply depot, mobile ISRU plant, exploratory hopper, and communication satellite. These federates were built by teams from all around the world, including teams from MIT, JSC, University of Alabama in Huntsville, University of Bordeaux from France, and University of Genoa from Italy. This paper focuses on the lunar shuttle federate, which was programmed by the USRP intern team from NASA JSC. The shuttle was responsible for provide transportation between lunar orbit and the lunar surface. The lunar shuttle federate was built using the NASA standard simulation package called Trick, and it was extended with HLA functions using TrickHLA. HLA functions of the lunar shuttle federate include sending and receiving interaction, publishing and subscribing attributes, and packing and unpacking fixed record data. The dynamics model of the lunar shuttle was modeled with three degrees of freedom, and the state propagation was obeying the law of two body dynamics. The descending trajectory of the lunar shuttle was designed by first defining a unique descending orbit in 2D space, and then defining a unique orbit in 3D space with the assumption of a non-rotating moon. Finally this assumption was taken away to define the initial position of the lunar shuttle so that it will start descending a second after it joins the execution. VPN software from SonicWall was used to connect federates with RTI during testing and the Smackdown event. HLA software from Pitch Technology and MAK Technology were used to edit and extend FOM and provide HLA services for federation execution. The SISO Smackdown event for 2011 was held in Boston, Massachusetts. The federation execution lasted for one hour, and the event was very successful in catching the attention of university students and faculties.

Independent Orbiter Assessment (IOA): Analysis of the Orbiter Experiment (OEX) subsystem

NASA Technical Reports Server (NTRS)

Compton, J. M.

1987-01-01

The results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) are presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items. To preserve independence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. This report documents the independent analysis results corresponding to the Orbiter Experiments hardware. Each level of hardware was evaluated and analyzed for possible failure modes and effects. Criticality was assigned based upon the severity of the effect for each failure mode. The Orbiter Experiments (OEX) Program consists of a multiple set of experiments for the purpose of gathering environmental and aerodynamic data to develop more accurate ground models for Shuttle performance and to facilitate the design of future spacecraft. This assessment only addresses currently manifested experiments and their support systems. Specifically this list consists of: Shuttle Entry Air Data System (SEADS); Shuttle Upper Atmosphere Mass Spectrometer (SUMS); Forward Fuselage Support System for OEX (FFSSO); Shuttle Infrared Laced Temperature Sensor (SILTS); Aerodynamic Coefficient Identification Package (ACIP); and Support System for OEX (SSO). There are only two potential critical items for the OEX, since the experiments only gather data for analysis post mission and are totally independent systems except for power. Failure of any experiment component usually only causes a loss of experiment data and in no way jeopardizes the crew or mission.

Wings In Orbit: Scientific and Engineering Legacies of the Space Shuttle

NASA Technical Reports Server (NTRS)

Hale, N. Wayne (Editor); Lulla, Kamlesh (Editor); Lane, Helen W. (Editor); Chapline, Gail (Editor)

2010-01-01

This Space Shuttle book project reviews Wings In Orbit-scientific and engineering legacies of the Space Shuttle. The contents include: 1) Magnificent Flying Machine-A Cathedral to Technology; 2) The Historical Legacy; 3) The Shuttle and its Operations; 4) Engineering Innovations; 5) Major Scientific Discoveries; 6) Social, Cultural, and Educational Legacies; 7) Commercial Aerospace Industries and Spin-offs; and 8) The Shuttle continuum, Role of Human Spaceflight.

Development of Ku-band rendezvous radar tracking and acquisition simulation programs

NASA Technical Reports Server (NTRS)

1986-01-01

The fidelity of the Space Shuttle Radar tracking simulation model was improved. The data from the Shuttle Orbiter Radar Test and Evaluation (SORTE) program experiments performed at the White Sands Missile Range (WSMR) were reviewed and analyzed. The selected flight rendezvous radar data was evaluated. Problems with the Inertial Line-of-Sight (ILOS) angle rate tracker were evaluated using the improved fidelity angle rate tracker simulation model.

Space Shuttle Projects

NASA Image and Video Library

1991-08-01

The primary payload of the STS-43 mission, Tracking and Data Relay Satellite-E (TDRS-E) attached to an Inertial Upper Stage (IUS) was photographed at the moment of its release from the cargo bay of the Space Shuttle Orbiter Atlantis. The TDRS-E was boosted by the IUS into geosynchronous orbit and positioned to remain stationary 22,400 miles above the Pacific Ocean southwest of Hawaii. The TDRS system provides almost uninterrupted communications with Earth-orbiting Shuttles and satellites, and had replaced the intermittent coverage provided by globe-encircling ground tracking stations used during the early space program. The TDRS can transmit and receive data, and track a user spacecraft in a low Earth orbit. The IUS is an unmarned transportation system designed to ferry payloads from low Earth orbit to higher orbits that are unattainable by the Shuttle. The launch of STS-43 occurred on August 2, 1991.

STS-64 and 747-SCA Ferry Flight Takeoff

NASA Technical Reports Server (NTRS)

1994-01-01

The Space Shuttle Discovery, mated to NASA's 747 Shuttle Carrier Aircraft (SCA), takes to the air for its ferry flight back to the Kennedy Space Center in Florida. The spacecraft, with a crew of six, was launched into a 57-degree high inclination orbit from the Kennedy Space Center, Florida, at 3:23 p.m., 9 September 1994. The mission featured the study of clouds and the atmosphere with a laser beaming system called Lidar In-Space Technology Experiment (LITE), and the first untethered space walk in ten years. A Spartan satellite was also deployed and later retrieved in the study of the sun's corona and solar wind. The mission was scheduled to end Sunday, 18 September, but was extended one day to continue science work. Bad weather at the Kennedy Space Center on 19 September, forced a one-day delay to September 20, with a weather divert that day to Edwards. Mission commander was Richard Richards, the pilot Blaine Hammond, while mission specialists were Jerry Linenger, Susan Helms, Carl Meade, and Mark Lee. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Orbital Debris Shape and Orientation Effects on Impact Damage to Shuttle Tiles

NASA Technical Reports Server (NTRS)

Evans, Steven W.; Williamsen, Joel

2006-01-01

Taking the damage results from a previous paper as a guide, and using a tile model created for the STS-107 accident investigation, we used the SPHC hydrodynamic code to evaluate the probable worst-case impact effects of flat, rectangular, "flake-shaped," orbital debris particles on Space Shuttle thermal tiles. We compared the damage from flakes with that produced by spheres. The flakes and spheres were sized according to a "characteristic length" (Lc) derived from radar cross-section measurements, and embodied in the NASA Standard Breakup Model (SBM). Impacts were simulated at near-normal obliquity, at 12 km/sec. We modeled the worst-case flake orientation: a corner-on impact, an orientation we term a "Face A-B" impact. Results of our simulations indicate that flake impactors are less damaging than spheres of the same Lc. Since spherical impactors have been assumed in analyses of shuttle orbital debris impact risk, we find that these risks may have been overestimated. This work represents a preliminary second step, i.e., a follow-on to [1], in developing a sensitivity analysis for the expected range of effects on damage considering spherical vs. non-spherical impactors, as recommended by the Institute for Defense Analyses (IDA) report to the Columbia Accident Investigation Board.

Discrete Roughness Effects on Shuttle Orbiter at Mach 6

NASA Technical Reports Server (NTRS)

Berry, Scott A.; Hamilton, H. Harris, II

2002-01-01

Discrete roughness boundary layer transition results on a Shuttle Orbiter model in the NASA Langley Research Center 20-Inch Mach 6 Air Tunnel have been reanalyzed with new boundary layer calculations to provide consistency for comparison to other published results. The experimental results were previously obtained utilizing the phosphor thermography system to monitor the status of the boundary layer via global heat transfer images of the Orbiter windward surface. The size and location of discrete roughness elements were systematically varied along the centerline of the 0.0075-scale model at an angle of attack of 40 deg and the boundary layer response recorded. Various correlative approaches were attempted, with the roughness transition correlations based on edge properties providing the most reliable results. When a consistent computational method is used to compute edge conditions, transition datasets for different configurations at several angles of attack have been shown to collapse to a well-behaved correlation.

An investigation of drag reduction fairings on the space shuttle vehicle 5 configuration (model 74-OTS) in the MSFC 14 inch trisonic wind tunnel (FA14)

NASA Technical Reports Server (NTRS)

Ramsey, P. E.

1976-01-01

An experimental investigation was conducted in the MSFC 14-inch TWT (FA14, TWT 600) to determine the static stability and drag on a 0.004 scale model of the shuttle ascent configuration. The primary objective was to study the possibility of reducing the launch vehicle drag by using Orbiter/ET/SRB fairings, streamlined orbiter fore and aft attach structures, SRB and ET alternative nose configurations, and devices for modifying the flow between the orbiter and ET. The secondary objective was to determine the longitudinal and directional characteristics of the ascent configuration with the most promising of the drag reduction devices installed. Data were obtained for a Mach number range of 0.6 through 4.96 and angles of attack from -5 through 5 degrees at zero degrees side slip angle.

Space Shuttle Project

NASA Image and Video Library

1978-04-21

The Shuttle Orbiter Enterprise is lowered into the Dynamic Test Stand for Mated Vertical Ground Vibration tests (MVGVT) at the Marshall Space Flight Center. The tests marked the first time ever that the entire shuttle complement (including Orbiter, external tank, and solid rocket boosters) were mated vertically.

Space Shuttle Project

NASA Image and Video Library

1978-10-04

The Shuttle Orbiter Enterprise is being installed into liftoff configuration at Marshall Space Flight Center's Dynamic Test Stand for Mated Vertical Ground Vibration tests (MVGVT). The tests marked the first time ever that the entire shuttle complement (including Orbiter, external tank, and solid rocket boosters) were mated vertically.

Space platforms - A cost effective evolution of Spacelab operation

NASA Technical Reports Server (NTRS)

Stofan, A. J.

1981-01-01

The capabilities added to the Shuttle/Spacelab configuration by the addition of the Power Extension Package (PEP), the Power System (PS), and the Science and Applications Space Platforms (SASP) are reviewed with an emphasis on SASP. SASP are intended for placement in orbit by the Shuttle to test new instruments and systems, for clustering of instrumentation, and for servicing, refurbishment, repair, or augmentation by the Shuttle. The PEP permits extended stays in orbit (30 days), and the PS is an orbital solar array and energy storage system acting as a free flying spacecraft. The Shuttle can deliver payloads to the PS or attach to it for extension of the Spacelab operations. Applications of SASP for long term space-based biological experiments are outlined, and the fact that SASP do not increase the required Shuttle in-orbit time is stressed.

Aerodynamic characteristics of the North American Rockwell space shuttle delta-wing orbiter (110C) alone and with belly-mounted external oxygen/hydrogen tanks (M equals 0.6 to 5.0)

NASA Technical Reports Server (NTRS)

Allen, E. C.

1972-01-01

Experimental aerodynamic investigations were conducted at the MSFC 14 x 14 inch trisonic wind tunnel on a .0044 scale model of the space shuttle orbiter, 110C. The test configurations included the orbiter alone and with external oxygen/hydrogen belly tanks. The six component aerodynamic force and moment data obtained cover a Mach number range from 0.6 to 4.96 at angles of attack from 10 to 60 deg at 0 deg sideslip angle and -10 to 10 deg at -6 deg sideslip angle. Reynolds number per unit length varied somewhat with Mach number but was a nominal 6.8 million per foot.

Spin-up studies of the Space Shuttle Orbiter main gear tire

NASA Technical Reports Server (NTRS)

Daugherty, Robert H.; Stubbs, Sandy M.

1988-01-01

One of the factors needed to describe the wear behavior of the Space Shuttle Orbiter main gear tires is their behavior during the spin-up process. An experimental investigation of tire spin-up processes was conducted at the NASA Langley Research Center's Aircraft Landing Dynamics Facility. During the investigation, the influence of various parameters such as forward speed and sink speed on tire spin-up forces were evaluated. A mathematical model was developed to estimate drag forces and spin-up times and is presented. The effect of prerotation was explored and is discussed. Also included is a means of determining the sink speed of the orbiter at touchdown based upon the appearance of the rubber deposits left on the runway during spinup.

Orbital Debris: A Chronology

NASA Technical Reports Server (NTRS)

Portree, Davis S. F. (Editor); Loftus, Joseph P., Jr. (Editor)

1999-01-01

This chronology covers the 37-year history of orbital debris concerns. It tracks orbital debris hazard creation, research, observation, experimentation, management, mitigation, protection, and policy. Included are debris-producing, events; U.N. orbital debris treaties, Space Shuttle and space station orbital debris issues; ASAT tests; milestones in theory and modeling; uncontrolled reentries; detection system development; shielding development; geosynchronous debris issues, including reboost policies: returned surfaces studies, seminar papers reports, conferences, and studies; the increasing effect of space activities on astronomy; and growing international awareness of the near-Earth environment.

A Review of Microgravity Levels on Ten OARE Shuttle Missions

NASA Technical Reports Server (NTRS)

McPherson, Kevin M.

1998-01-01

The Orbital Acceleration Research Experiment (OARE) is an accelerometer package with nano-g sensitivity and on-orbit bias calibration capabilities. The OARE consists of a three axis miniature electrostatic accelerometer (MESA), a full in-flight bias and scale factor calibration station, and an on-board microprocessor for experiment control and data storage. Originally designed to measure and record the aerodynamic acceleration environment of the NASA Space Shuttles during re-entry, the OARE has been used on ten shuttle missions to measure the quasi-steady acceleration environment (<1 Hz) of the Orbiter while in low-Earth orbit. The effects on the quasi-steady acceleration environment from Orbiter systems, Orbiter attitude, Orbiter altitude, and crew activity are well understood as a result of these ten shuttle missions. This knowledge of the quasi-steady acceleration realm has direct application to understanding the quasi-steady acceleration environment expected for the International Space Station (ISS). This paper will summarize the more salient aspects of this quasi-steady acceleration knowledge base.

Feasibility and tradeoff study of an aeromaneuvering orbit-to-orbit shuttle (AMOOS)

NASA Technical Reports Server (NTRS)

White, J.

1974-01-01

This study establishes that configurations satisfying the aeromaneuvering orbit-to-orbit shuttle (AMOOS) requirements can be designed with performance capabilities in excess of the purely propulsive space tug. In view of this improved potential of the AMOOS vehicle over the propulsive space tug concept it is recommended that the AMOOS studies be advanced to a stage comparable to those performed for the space tug. This advancement is needed in particular in areas that are either peculiar to AMOOS or not addressed in sufficient detail in these studies to date. These areas include the thermodynamics problems, navigation and guidance, operations and economics analyses, subsystems and interfaces. The aeromaneuvering orbit-to-orbit shuttle (AMOOS) is evaluated as a candidate reusable third stage to the two-stage earth-to-orbit shuttle (EOS). AMOOS has the potential for increased payload capability over the purely propulsive space tug by trading a savings in consumables for an increase in structural and thermal protection system (TPS) mass.

Friction evaluation of unpaved, gypsum-surface runways at Northrup Strip, White Sands Missile Range, in support of Space Shuttle Orbiter landing and retrieval operations

NASA Technical Reports Server (NTRS)

Yager, T. J.; Horne, W. B.

1980-01-01

Friction measurement results obtained on the gypsum surface runways at Northrup Strip, White Sands Missile Range, N. M., using an instrumented tire test vehicle and a diagonal braked vehicle, are presented. These runways were prepared to serve as backup landing and retrieval sites to the primary sites located at Dryden Flight Research Center for shuttle orbiter during initial test flights. Similar friction data obtained on paved and other unpaved surfaces was shown for comparison and to indicate that the friction capability measured on the dry gypsum surface runways is sufficient for operations with the shuttle orbiter and the Boeing 747 aircraft. Based on these ground vehicle friction measurements, estimates of shuttle orbiter and aircraft tire friction performance are presented and discussed. General observations concerning the gypsum surface characteristics are also included and several recommendations are made for improving and maintaining adequate surface friction capabilities prior to the first shuttle orbiter landing.

Thermal math model analysis of FRSI test article subjected to cold soak and entry environments. [Flexible Reuseable Surface Insulation in Space Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Gallegos, J. J.

1978-01-01

A multi-objective test program was conducted at the NASA/JSC Radiant Heat Test Facility in which an aluminum skin/stringer test panel insulated with FRSI (Flexible Reusable Surface Insulation) was subjected to 24 simulated Space Shuttle Orbiter ascent/entry heating cycles with a cold soak in between in the 10th and 20th cycles. A two-dimensional thermal math model was developed and utilized to predict the thermal performance of the FRSI. Results are presented which indicate that the modeling techniques and property values have been proven adequate in predicting peak structure temperatures and entry thermal responses from both an ambient and cold soak condition of an FRSI covered aluminum structure.

KSC-02pd1085

NASA Image and Video Library

2002-06-27

KENNEDY SPACE CENTER, FLA. -- United Space Alliance Chief Operating Officer Mike McCulley welcomes guests to the Landing Operations Facility and commissioning ceremony for the new Convoy Command Vehicle behind him. The new 40-foot vehicle is replacing a 15-year old model, and will be used following Shuttle landings as the prime vehicle to control critical communications between the orbiter, the crew and the Launch Control Center, to monitor the health of the Shuttle Orbiter systems and to direct convoy operations at the Shuttle Landing Facility. Upgrades and high-tech features incorporated into the design and development of this vehicle make it more reliable and efficient for the convoy crew. Seating capacity was increased from 4 to 12, and video recorders and television monitors were added to provide the convoy team with the maximum amount of visual information

Identification and status of design improvements to the NASA Shuttle EMU for International Space Station application.

PubMed

Wilde, R C; McBarron, J W; Faszcza, J J

1997-06-01

To meet the significant increase in EVA demand to support assembly and operations of the International Space Station (ISS), NASA and industry have improved the current Shuttle Extravehicular Mobility Unit (EMU), or "space suit", configuration to meet the unique and specific requirements of an orbital-based system. The current Shuttle EMU was designed to be maintained and serviced on the ground between frequent Shuttle flights. ISS will require the EMUs to meet increased EVAs out of the Shuttle Orbiter and to remain on orbit for up to 180 days without need for regular return to Earth for scheduled maintenance or refurbishment. Ongoing Shuttle EMU improvements have increased reliability, operational life and performance while minimizing ground and on-orbit maintenance cost and expendable inventory. Modifications to both the anthropomorphic mobility elements of the Space Suit Assembly (SSA) as well as to the Primary Life Support System (PLSS) are identified and discussed. This paper also addresses the status of on-going Shuttle EMU improvements and summarizes the approach for increasing interoperability of the U.S. and Russian space suits to be utilized aboard the ISS.

Analytical studies of the Space Shuttle orbiter nose-gear tire

NASA Technical Reports Server (NTRS)

Noor, Ahmed K.; Tanner, John A.; Peters, Jeanne M.; Robinson, Martha P.

1991-01-01

A computational procedure is presented for evaluating the analytic sensitivity derivatives of the tire response with respect to material and geometrical properties of the tire. The tire is modeled by using a two-dimensional laminated anisotropic shell theory with the effects of variation in material and geometric parameters included. The computational procedure is applied to the case of the Space Shuttle orbiter nose-gear tire subjected to uniform inflation pressure. Numerical results are presented which show the sensitivity of the different tire response quantities to variations in the material characteristics of both the cord and rubber.

Space Shuttle Orbiter oxygen partial pressure sensing and control system improvements

NASA Technical Reports Server (NTRS)

Frampton, Robert F.; Hoy, Dennis M.; Kelly, Kevin J.; Walleshauser, James J.

1992-01-01

A program aimed at developing a new PPO2 oxygen sensor and a replacement amplifier for the Space Shuttle Orbiter is described. Experimental design methodologies used in the test and modeling process made it possible to enhance the effectiveness of the program and to reduce its cost. Significant cost savings are due to the increased lifetime of the basic sensor cell, the maximization of useful sensor life through an increased amplifier gain adjustment capability, the use of streamlined production processes for the manufacture of the assemblies, and the refurbishment capability of the replacement sensor.

Effects of surface cooling and of roughness on the heating (including transition) to the windward plane-of-symmetry of the shuttle orbiter

NASA Technical Reports Server (NTRS)

Bertin, J. J.; Idar, E. S., III; Galanski, S. R.

1977-01-01

The theoretical heat-transfer distributions are compared with experimental heat-transfer distributions obtained in Tunnel B at AEDC using a 0.0175 scale model of the space shuttle orbiter configuration for which the first 80% of the windward surface was roughened by a simulated tile misalignment. The theoretical solutions indicate that thinning the boundary layer by surface cooling increased the nondimensionalized value of the local heat-transfer coefficient. Tile misalignment did not significantly affect the heat-transfer rate in regions where the boundary layer was either laminar or turbulent.

Acquisition/expulsion system for earth orbital propulsion system study. Volume 2: Cryogenic design

NASA Technical Reports Server (NTRS)

1973-01-01

Detailed designs were made for three earth orbital propulsion systems; (1) the space shuttle (integrated) OMS/RCS, (2) the space shuttle (dedicated) OMS (LO2), and (3) the space tug. The preferred designs from the integrated OMS/RCS were used as the basis for the flight test article design. A plan was prepared that outlines the steps, cost, and schedule required to complete the development of the prototype DSL tank and feedline (LH2 and LO2) systems. Ground testing of a subscale model using LH2 verified the expulsion characteristics of the preferred DSL designs.

Endeavour Grand Opening Ceremony

NASA Image and Video Library

2012-10-30

A space shuttle main engine (SSME) is on display near the space shuttle Endeavour at the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, Tuesday, Oct. 30, 2012, in Los Angeles. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Photo Credit: (NASA/Bill Ingalls)

KSC-2011-2866

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- STS-1 Pilot and former Kennedy Space Center Director Bob Crippen addresses the audience after the announcement that revealed the four institutions receiving shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

KSC-2011-2869

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- Media interview STS-1 Pilot and former Kennedy Space Center Director Bob Crippen after the announcement that revealed the four institutions receiving shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

KSC-2011-2862

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- The Expedition 27 crew members from the International Space Station appear onscreen to address NASA officials, Florida representatives, Kennedy employees and media waiting to hear which of the four institutions will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

KSC-2011-2860

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA officials, Florida representatives, Kennedy employees and media await an announcement that will reveal which of the four institutions will receive shuttle orbiters for permanent display. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

Design analysis and computer-aided performance evaluation of shuttle orbiter electrical power system. Volume 1: Summary

NASA Technical Reports Server (NTRS)

1974-01-01

Studies were conducted to develop appropriate space shuttle electrical power distribution and control (EPDC) subsystem simulation models and to apply the computer simulations to systems analysis of the EPDC. A previously developed software program (SYSTID) was adapted for this purpose. The following objectives were attained: (1) significant enhancement of the SYSTID time domain simulation software, (2) generation of functionally useful shuttle EPDC element models, and (3) illustrative simulation results in the analysis of EPDC performance, under the conditions of fault, current pulse injection due to lightning, and circuit protection sizing and reaction times.

Payload/orbiter contamination control requirement study, volume 1, exhibit A

NASA Technical Reports Server (NTRS)

Bareiss, L. E.; Hooper, V. W.; Rantanen, R. O.; Ress, E. B.

1974-01-01

This study is to identify and quantify the expected molecular and particulate on orbit contaminant environment for selected shuttle payloads as a result of major spacelab and shuttle orbiter contaminant sources. This investigation reviews individual payload susceptibilities to contamination, identifies the combined induced environment, identifies the risk of spacelab/payload critical surface(s) degradation, and provides preliminary contamination recommendations. It also establishes limiting factors which may depend upon operational activities associated with the payloads, spacelab, and the shuttle orbiter interface or upon independent payload functional activities.

Dual-fuel propulsion - Why it works, possible engines, and results of vehicle studies. [on earth-to-orbit Space Shuttle flights

NASA Technical Reports Server (NTRS)

Martin, J. A.; Wilhite, A. W.

1979-01-01

The reasons why dual-fuel propulsion works are discussed. Various engine options are discussed, and vehicle mass and cost results are presented for earth-to-orbit vehicles. The results indicate that dual-fuel propulsion is attractive, particularly with the dual-expander engine. A unique orbit-transfer vehicle is described which uses dual-fuel propulsion. One Space Shuttle flight and one flight of a heavy-lift Shuttle derivative are used for each orbit-transfer vehicle flight, and the payload capability is quite attractive.

Shuttle considerations for the design of large space structures

NASA Technical Reports Server (NTRS)

Roebuck, J. A., Jr.

1980-01-01

Shuttle related considerations (constraints and guidelines) are compiled for use by designers of a potential class of large space structures which are transported to orbit and, deployed, fabricated or assembled in space using the Space Shuttle Orbiter. Considerations of all phases of shuttle operations from launch to ground turnaround operations are presented. Design of large space structures includes design of special construction fixtures and support equipment, special stowage cradles or pallets, special checkout maintenance, and monitoring equipment, and planning for packaging into the orbiter of all additional provisions and supplies chargeable to payload. Checklists of design issues, Shuttle capabilities constraints and guidelines, as well as general explanatory material and references to source documents are included.

SRTM is removed from Endeavour's payload bay to ease wiring inspections

NASA Technical Reports Server (NTRS)

1999-01-01

Inside orbiter Endeavour's payload bay, a crane lifts the Shuttle Radar Topography Mission (SRTM) for its transfer out of the orbiter to a payload canister. The payload on mission STS-99, SRTM is being removed to allow technicians access to the orbiter's midbody for planned wiring inspections. Endeavour is in the Orbiter Processing Facility. The entire fleet of orbiters is being inspected for wiring abrasions after the problem was first discovered in Columbia. Shuttle managers are reviewing several manifest options and could establish new target launch dates for the balance of 1999 next week. Shuttle Endeavour currently remains slated for launch in early October.

KSC-03PD-3240

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- From left, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik, United Space Alliance (USA) Director of Orbiter Operations Patty Stratton, and NASA Space Shuttle Program Manager William Parsons view the underside of Shuttle Discovery in Orbiter Processing Facility Bay 3. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

Space Shuttle wind tunnel testing program

NASA Technical Reports Server (NTRS)

Whitnah, A. M.; Hillje, E. R.

1984-01-01

A major phase of the Space Shuttle Vehicle (SSV) Development Program was the acquisition of data through the space shuttle wind tunnel testing program. It became obvious that the large number of configuration/environment combinations would necessitate an extremely large wind tunnel testing program. To make the most efficient use of available test facilities and to assist the prime contractor for orbiter design and space shuttle vehicle integration, a unique management plan was devised for the design and development phase. The space shuttle program is reviewed together with the evolutional development of the shuttle configuration. The wind tunnel testing rationale and the associated test program management plan and its overall results is reviewed. Information is given for the various facilities and models used within this program. A unique posttest documentation procedure and a summary of the types of test per disciplines, per facility, and per model are presented with detailed listing of the posttest documentation.

Nuclear Shuttle Logistics Configuration

NASA Technical Reports Server (NTRS)

1971-01-01

This 1971 artist's concept shows the Nuclear Shuttle in both its lunar logistics configuraton and geosynchronous station configuration. As envisioned by Marshall Space Flight Center Program Development persornel, the Nuclear Shuttle would deliver payloads to lunar orbits or other destinations then return to Earth orbit for refueling and additional missions.

Differential elevon effectiveness lateral control optimization and elevon hinge moment investigation on a 0.015 scale space shuttle orbiter model 49-0 (140A/B/C modified) in the AECD VKF wind tunnel A (0A115)

NASA Technical Reports Server (NTRS)

Esparza, V.

1975-01-01

Experimental aerodynamic investigations were conducted in the Arnold Engineering Development Center (AEDC) Von Karman Facility Tunnel A on a scale model of the space shuttle orbiter. The objectives of this test were: (1) determine supersonic differential elevon/aileron lateral control optimization, (2) determine supersonic elevon hinge moments, (3) determine the supersonic effects of the new baseline 6-inch elevon/elevon and elevon/fuselage gaps, and 4) determine the supersonic effects of the new short (VL70-008410) OMS pods. Six-component aerodynamic force, moment, and elevon hinge moment data were recorded.

Force and moment tests to determine the interaction effects of the reaction control system jet plumes on the space shuttle Orbiter aerodynamics at Mach Number 6 (Test OA352)

NASA Technical Reports Server (NTRS)

Cayse, Robert W.

1987-01-01

The purpose of this test was to expand the existing Space Shuttle aerodynamics and Reaction Control System (RCS) data base to support the Glide Return to Launch Site (GRTLS) abort trajectory and the new Digital Autopilot. An existing model of the orbiter was used to investigate the aerodynamic effects of several combinations of RCS thrusters and thruster momentum ratios at Mach number 6. Two separate model installations were used to achieve an angle-of-attack range of -11 to 46 deg. The test was conducted at a unit Reynolds number of 0.8 x 10 to the 6th per foot.

Hypersonic aeroheating test of space shuttle vehicle configuration 3 (model 22-OTS) in the NASA-Ames 3.5-foot hypersonic wind tunnel (IH20), volume 1

NASA Technical Reports Server (NTRS)

Kingsland, R. B.; Lockman, W. K.

1975-01-01

The results of hypersonic wind tunnel testing of an 0.0175 scale version of the vehicle 3 space shuttle configuration are presented. Temperature measurements were made on the launch configuration, orbiter plus tank, orbiter alone, tank alone, and solid rocket booster alone to provide heat transfer data. The test was conducted at free-stream Mach numbers of 5.3 and 7.3 and at free-stream Reynolds numbers of 1.5 million, 3.7 million, 5.0 million, and 7.0 million per foot. The model was tested at angles of attack from -5 deg to 20 deg and side slip angles of -5 deg and 0 deg.

STS_135_SAIL

NASA Image and Video Library

2011-07-12

JSC2011-E-067679 (12 July 2011) --- This is an overall view of the wiring for the simulated shuttle payload bay in the Shuttle Avionics Integration Laboratory (SAIL) at the Johnson Space Center in Houston on July 12, 2011. The laboratory is a skeletal avionics version of the shuttle that uses actual orbiter hardware and flight software. The facility even carries the official orbiter designation as Orbiter Vehicle 095. Photo credit: NASA Photo/Houston Chronicle, Smiley N. Pool

STS_135_SAIL

NASA Image and Video Library

2011-07-12

JSC2011-E-067680 (12 July 2011) --- This is an overall view of the wiring for the simulated shuttle payload bay in the Shuttle Avionics Integration Laboratory (SAIL) at the Johnson Space Center in Houston on July 12, 2011. The laboratory is a skeletal avionics version of the shuttle that uses actual orbiter hardware and flight software. The facility even carries the official orbiter designation as Orbiter Vehicle 095. Photo credit: NASA Photo/Houston Chronicle, Smiley N. Pool

Space Shuttle Projects

NASA Image and Video Library

1984-04-24

The official mission insignia for the 41-D Space Shuttle flight features the Discovery - NASA's third orbital vehicle - as it makes its maiden voyage. The ghost ship represents the orbiter's namesakes which have figured prominently in the history of exploration. The Space Shuttle Discovery heads for new horizons to extend that proud tradition. Surnames for the crewmembers of NASA's eleventh Space Shuttle mission encircle the red, white, and blue scene.

STS-80 Space Shuttle Mission Report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1997-01-01

The STS-80 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the eightieth flight of the Space Shuttle Program, the fifty-fifth flight since the return-to-flight, and the twenty-first flight of the Orbiter Columbia (OV-102).

STS-92 - Orbiter in Mate-Demate Device (MDD) - closeup view from front

NASA Image and Video Library

2000-10-29

The Space Shuttle Discovery is centered in the Mate-Demate Device (MDD) at NASA’s Dryden Flight Research Center at Edwards, California. The gantry-like MDD structure is used for servicing the shuttle orbiters in preparation for their ferry flight back to the Kennedy Space Center in Florida, including mounting the shuttle atop NASA’s modified Boeing 747 Shuttle Carrier Aircraft.

Shuttle on-orbit rendezvous targeting: Circular orbits

NASA Technical Reports Server (NTRS)

Bentley, E. L.

1972-01-01

The strategy and logic used in a space shuttle on-orbit rendezvous targeting program are described. The program generates ascent targeting conditions for boost to insertion into an intermediate parking orbit, and generates on-orbit targeting and timeline bases for each maneuver to effect rendezvous with a space station. Time of launch is determined so as to eliminate any plane change, and all work was performed for a near-circular space station orbit.

Heat transfer test of an 0.006-scale thin-skin thermocouple space shuttle model (50-0, 41-T) in the NASA-Ames Research Center 3.5-foot hypersonic wind tunnel at Mach 5.3 (IH28), volume 1

NASA Technical Reports Server (NTRS)

Cummings, J. W.; Foster, T. F.; Lockman, W. K.

1976-01-01

Data obtained from a heat transfer test conducted on an 0.006-scale space shuttle orbiter and external tank in the NASA-Ames Research Center 3.5-foot Hypersonic Wind Tunnel are presented. The purpose of this test was to obtain data under simulated return-to-launch-site abort conditions. Configurations tested were integrated orbiter and external tank, orbiter alone, and external tank alone at angles of attack of 0, + or - 30, + or - 60, + or - 90, and + or - 120 degrees. Runs were conducted at Mach numbers of 5.2 and 5.3 for Reynolds numbers of 1.0 and 4.0 million per foot, respectively. Heat transfer data were obtained from 75 orbiter and 75 external tank iron-constantan thermocouples.

Orbiter post-tire failure and skid testing results

NASA Technical Reports Server (NTRS)

Daugherty, Robert H.; Stubbs, Sandy M.

1989-01-01

An investigation was conducted at the NASA Langley Research Center's Aircraft Landing Dynamics Facility (ALDF) to define the post-tire failure drag characteristics of the Space Shuttle Orbiter main tire and wheel assembly. Skid tests on various materials were also conducted to define their friction and wear rate characteristics under higher speed and bearing pressures than any previous tests. The skid tests were conducted to support a feasibility study of adding a skid to the orbiter strut between the main tires to protect an intact tire from failure due to overload should one of the tires fail. Roll-on-rim tests were conducted to define the ability of a standard and a modified orbiter main wheel to roll without a tire. Results of the investigation are combined into a generic model of strut drag versus time under failure conditions for inclusion into rollout simulators used to train the shuttle astronauts.

Investigation of space shuttle vehicle 140C configuration orbiter (model 16-0) wheel well pressure loads in the Rockwell International 7.75 x 11 foot wind tunnel (OA143)

NASA Technical Reports Server (NTRS)

Mennell, R. C.

1975-01-01

Experimental aerodynamic investigations were conducted on a sting mounted .0405-scale representation of the 140C outer mold line space shuttle orbiter configuration in the Rockwell International 7.75 x 11.00 foot low speed wind tunnel. The primary test objectives were to define the orbiter wheel well pressure loading and its effects on landing gear thermal insulation and to investigate the pressure environment experienced by both the horizontal flight nose probe and air vent door probes. Steady state and dynamic pressure values were recorded in the orbiter nose gear well, left main landing gear well, horizontal flight nose probe, and both left and right air vent door probe. All steady state pressure levels were measured by Statham differential pressure transducers while dynamic pressure levels were recorded by Kulite high frequency response pressure sensors.

The effects of RCS jet firing on the isolated Orbiter and mated coast phases of the glide return to launch site maneuver at Mach number 6 (IA302B)

NASA Technical Reports Server (NTRS)

Garrett, L. V.; Buchanan, T. D.; Fryberger, P. E.

1988-01-01

An updated Space Shuttle aerodynamic data base was obtained in Tunnel B for two phases of the Glide Return to Launch Site (GRTLS) abort maneuver. One-and-a-quarter percent scale models of the Space Shuttle Orbiter and External Tank were used to measure the effects of various combinations of Reaction Control System (RCS) jet thrusters at Mach number 6. The angle-of-attack range for the isolated orbiter was -10 to 15 deg at sideslip angles from -5 to 10 deg during Phase 1 of testing. The angle-of-attack range for the mated orbiter and external tank was -5 to 15 deg with sideslip angles of -2 to 5 deg during Phase 2. The test was conducted at a unit Reynolds number of 0.75 million per foot.

KSC-2011-3012

NASA Image and Video Library

2011-04-21

CAPE CANAVERAL, Fla. -- Members of a visiting team from the Smithsonian's National Air and Space Museum examine the space shuttle's thermal protection system tile as they stand beneath shuttle Discovery in Orbiter Processing Facility-2 at NASA's Kennedy Space Center. NASA Administrator Charles Bolden announced April 12 the facilities where all four shuttle orbiters will be permanently displayed at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired in March after completing its 39th mission. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Photo credit: NASA/Cory Huston

KSC-2011-2874

NASA Image and Video Library

2011-04-12

In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-3011

NASA Image and Video Library

2011-04-21

CAPE CANAVERAL, Fla. -- Members of a visiting team from the Smithsonian's National Air and Space Museum discuss the application of the space shuttle's thermal protection system tile with shuttle technicians in Orbiter Processing Facility-2 at NASA's Kennedy Space Center. NASA Administrator Charles Bolden announced April 12 the facilities where all four shuttle orbiters will be permanently displayed at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired in March after completing its 39th mission. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Photo credit: NASA/Cory Huston

KSC-2011-2875

NASA Image and Video Library

2011-04-12

In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

KSC-2011-2883

NASA Image and Video Library

2011-04-12

In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

Landing pressure loads of the 140A/B space shuttle orbiter (model 43-0) determined in the Rockwell International low speed wind tunnel (OA69), volume 1. [wind tunnel tests

NASA Technical Reports Server (NTRS)

Soard, T. L.

1975-01-01

Wind tunnel tests of a 0.0405 scale model of the -1404A/B configuration of the Space Shuttle Vehicle Orbiter are presented. Pressure loads data were obtained from the orbiter in the landing configuration in the presence of the ground for structural strength analysis. This was accomplished by locating as many as 30 static pressure bugs at various locations on external model surfaces as each configuration was tested. A complete pressure loads survey was generated for each configuration by combining data from all bug locations, and these loads are described for the fuselage, wing, vertical tail, and landing gear doors. Aerodynamic force data was measured by a six component internal strain gage balance. This data was recorded to correct model angles of attack and sideslip for sting and balance deflections and to determine the aerodynamic effects of landing gear extension. All testing was conducted at a Mach number of 0.165 and a Reynolds number of 1.2 million per foot. Photographs of test configurations are shown.

Orbiter ECLSS support of Shuttle payloads

NASA Technical Reports Server (NTRS)

Jaax, J. R.; Morris, D. W.; Prince, R. N.

1974-01-01

The orbiter ECLSS (Environmental Control and Life Support System) provides the functions of atmosphere revitalization, crew life support, and active thermal control. This paper describes these functions as they relate to the support of Shuttle payloads, including automated spacecraft, Spacelab and Department of Defense missions. Functional and performance requirements for the orbiter ECLSS which affect payload support are presented for the atmosphere revitalization subsystem, the food, water and waste subsystem, and the active thermal control subsystem. Schematics for these subsystems are also described. Finally, based on the selected orbiter configuration, preliminary design and off-design thermodynamic data are presented to quantify the baseline orbiter capability; to quantify the payload chargeable penalties for increasing this support; and to identify the significant limits of orbiter ECLSS support available to Shuttle payloads.

Results of a landing gear loads test using a 0.0405-scale model (16-0) of the space shuttle orbiter in the Rockwell International NAAL wind tunnel (OA163), volume 1

NASA Technical Reports Server (NTRS)

Mennell, R. C.

1976-01-01

Experimental aerodynamic investigations were conducted on a sting mounted scale representation of the 140C outer mold line space shuttle orbiter configuration in the low speed wind tunnel. The primary test objectives were to define the orbiter landing gear system pressure loading and to record landing gear door and strut hingemoment levels. Secondary objectives included recording the aerodynamic influence of various landing gear configurations on orbiter force data as well as investigating 40 x 80 ft. Ames Wind Tunnel strut simulation effects on both orbiter landing gear loads and aerodynamic characteristics. Testing was conducted at a Mach number of 0.17, free stream dynamic pressure of 42.5 PSF, and Reynolds number per unit length of 1.2 million per foot. Angle of attack variation was 0 to 20 while yaw angles ranged from -10 to 10 deg.

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

The space shuttle Endeavour is seen as it traverses through Inglewood, Calif. on Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Carla Cioffi)

Space Shuttle flying qualities and flight control system assessment study, phase 2

NASA Technical Reports Server (NTRS)

Myers, T. T.; Johnston, D. E.; Mcruer, D. T.

1983-01-01

A program of flying qualities experiments as part of the Orbiter Experiments Program (OEX) is defined. Phase 1, published as CR-170391, reviewed flying qualities criteria and shuttle data. The review of applicable experimental and shuttle data to further define the OEX plan is continued. An unconventional feature of this approach is the use of pilot strategy model identification to relate flight and simulator results. Instrumentation, software, and data analysis techniques for pilot model measurements are examined. The relationship between shuttle characteristics and superaugmented aircraft is established. STS flights 1 through 4 are reviewed from the point of view of flying qualities. A preliminary plan for a coordinated program of inflight and simulator research is presented.

Habitability study shuttle orbiter

NASA Technical Reports Server (NTRS)

1972-01-01

Studies of the habitability of the space shuttle orbiter are briefly summarized. Selected illustrations and descriptions are presented for: crew compartment, hygiene facilities, food system and galley, and storage systems.

Early Program Development

NASA Image and Video Library

1970-01-01

This artist's concept from 1970 shows a Nuclear Shuttle taking on fuel from an orbiting Liquid Hydrogen Depot. As envisioned by Marshall Space Flight Center Program Development persornel, the Nuclear Shuttle would deliver payloads to lunar orbit or other destinations then return to Earth orbit for refueling and additional missions.

Russian Docking Module is lowered

NASA Technical Reports Server (NTRS)

1995-01-01

The Russian-built Docking Module (DM) is lowered for installation into the payload bay of the Space Shuttle Orbiter Atlantis while the spaceplane is in Orbiter Processing Facility bay 2. The module will fly as a primary payload on the second Space Shuttle/Mir space station docking mission, STS-74, which is now scheduled for liftoff in the fall of 1995. During the mission, the module will first be attached with the orbiter's robot arm to the Orbiter Docking System (ODS) in the payload bay of the orbiter Atlantis and then be docked with the Mir. When Atlantis undocks from the Mir, it will leave the new docking module permanently attached to the space station for use during future Shuttle Mir docking missions. The new module will simplify future Shuttle linkups with Mir by improving orbiter clearances when it serves as a bridge between the two space vehicles. The white structures attached to the module's sides are solar panels that will be attached to the Mir after the conclusion of the STS-74 mission.

Space Station Freedom assembly and operation at a 51.6 degree inclination orbit

NASA Technical Reports Server (NTRS)

Troutman, Patrick A.; Brewer, Laura M.; Heck, Michael L.; Kumar, Renjith R.

1993-01-01

This study examines the implications of assembling and operating Space Station Freedom at a 51.6 degree inclination orbit utilizing an enhanced lift Space Shuttle. Freedom assembly is currently baselined at a 220 nautical mile high, 28.5 degree inclination orbit. Some of the reasons for increasing the orbital inclination are (1) increased ground coverage for Earth observations, (2) greater accessibility from Russian and other international launch sites, and (3) increased number of Assured Crew Return Vehicle (ACRV) landing sites. Previous studies have looked at assembling Freedom at a higher inclination using both medium and heavy lift expendable launch vehicles (such as Shuttle-C and Energia). The study assumes that the shuttle is used exclusively for delivering the station to orbit and that it can gain additional payload capability from design changes such as a lighter external tank that somewhat offsets the performance decrease that occurs when the shuttle is launched to a 51.6 degree inclination orbit.

Russian RSC Energia employees attach trunnions to DM

NASA Technical Reports Server (NTRS)

1995-01-01

Employees of the Russian aerospace company RSC Energia attach trunnions to the Russian-built docking module in the Space Station Processing Facility at KSC so that it can be mounted in the payload bay of the Space Shuttle orbiter Atlantis. The module will fly as a primary payload on the second Space Shuttle/Mir space station docking mission, STS-74, which is now scheduled for liftoff in the fall of 1995. During the mission, the module will first be attached with the orbiter's robot arm to the Orbiter Docking System (ODS) in the payload bay of the orbiter Atlantis and then be docked with the Mir. When Atlantis undocks from the Mir, it will leave the new docking module permanently attached to the space station for use during future Shuttle Mir docking missions. The new module will simplify future Shuttle linkups with Mir by improving orbiter clearances when it serves as a bridge between the two space vehicles.

Space shuttle: Static stability and control investigation of NR/GD delta wing booster (B-20) and delta wing orbiter (134D), volume 4

NASA Technical Reports Server (NTRS)

Allen, E. C., Jr.; Eder, F. W.

1972-01-01

Test results of booster and orbiter models of various component buildup configurations are reported. Dataset Collation Sheets, which give a complete summary of the configurations, are presented along with a description of the test facility. Data reduction procedures are described.

Modelling and simulation of Space Station Freedom berthing dynamics and control

NASA Technical Reports Server (NTRS)

Cooper, Paul A.; Garrison, James L., Jr.; Montgomery, Raymond C.; Wu, Shih-Chin; Stockwell, Alan E.; Demeo, Martha E.

1994-01-01

A large-angle, flexible, multibody, dynamic modeling capability has been developed to help validate numerical simulations of the dynamic motion and control forces which occur during berthing of Space Station Freedom to the Shuttle Orbiter in the early assembly flights. This paper outlines the dynamics and control of the station, the attached Shuttle Remote Manipulator System, and the orbiter. The simulation tool developed for the analysis is described and the results of two simulations are presented. The first is a simulated maneuver from a gravity-gradient attitude to a torque equilibrium attitude using the station reaction control jets. The second simulation is the berthing of the station to the orbiter with the station control moment gyros actively maintaining an estimated torque equilibrium attitude. The influence of the elastic dynamic behavior of the station and of the Remote Manipulator System on the attitude control of the station/orbiter system during each maneuver was investigated. The flexibility of the station and the arm were found to have only a minor influence on the attitude control of the system during the maneuvers.

Heat transfer tests of a 0.006-scale thin skin space shuttle model (50-0, 41-T) in the Langley Research Center nitrogen tunnel at Mach 19 (IH19)

NASA Technical Reports Server (NTRS)

Walstad, D. G.

1975-01-01

Data are presented from heat transfer tests on an 0.0006-scale space shuttle vehicle in the Langley Research Center Nitrogen Tunnel. The purpose of this test was to obtain ascent heating data at a high hypersonic Mach number. Configurations tested were integrated orbiter and external tank, orbiter alone, and external tank alone. All configurations were tested with and without boundary layer transition. Testing was conducted at a Mach number of 19, a Reynolds number of 0.5 million per foot, and angles of attack of 0, + or - 5, and + or - 10 degrees. Heat transfer data was obtained from 77 orbiter and 90 external tank iron-constantan thermocouples.

Effect of ELEVON gap configurations on the longitudinal stability and control effectiveness of the 43-0 space shuttle orbiter (OA118)

NASA Technical Reports Server (NTRS)

Hughes, T.; Mennell, R.

1974-01-01

Experimental aerodynamic investigations were conducted on a stingmounted 0.0405-scale representation of the 140A/B space shuttle orbiter in a 7.75 by 11-Foot low speed wind tunnel from April 24 to April 26, 1974. Differential inboard/outboard elevon panel deflections with the 6-inch gap were investigated to determine outboard panel aileron effectiveness. The elevons were deflected from +20 degrees to -40 degrees in various combinations. Aerodynamic force and moment data for the orbiter were measured in the body axis system by an internally mounted, six-component strain gage balance. The model was sting mounted with the center of rotation located at F.S. 60.172. The angle of attack range was from -10 degrees to +24 degrees.

Shuttle flight data and in-flight anomaly list. STS-1 through STS-50, and STS-52 through STS-56. Revision T

NASA Technical Reports Server (NTRS)

1993-01-01

This report contains mission data for space shuttle flights and consists of three sections. The first section is a listing of shuttle flight data for flights STS-1 through STS-55 gathered during the mission evaluation process. The second section is a listing of all orbiter in-flight anomalies arranged in order by affected Work Unit Codes of the failed items from shuttle flights STS-1 through STS-50 and STS-52 through STS-56. The third section consists of data derived from the as-flown orbiter attitude timelines and crew activity plans for each mission. The data are presented in chart form and show the progression of the mission from launch to entry interface with the varying orbiter attitudes (roll, pitch, and yaw) and the time duration in each attitude. The chart also shows the orbiter's velocity vector, i.e., which of the orbiter's body axes is pointing forward along the orbital path. The Beta angle, the angle between the sun vector and the orbital plane, is also shown for each 12-hour period of the mission.

KSC-2011-2878

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- Kennedy Center Director Bob Cabana appears pleased that Kennedy was awarded shuttle Atlantis to be displayed permanently in Florida. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. The event also commemorated the 30th anniversary of the first space shuttle launch with the launch of shuttle Columbia. Photo credit: NASA/Kim Shiflett

STS-81 Mission Highlights Resource Tape

NASA Technical Reports Server (NTRS)

1997-01-01

The flight crew of the STS-81 Space Shuttle Orbiter Atlantis Commander Michael A. Baker, Pilot Brent W. Jett Jr., and Mission Specialists, John M. Grunsfeld, Marsha S. Ivins, Peter J.K. Wisoff, and John M. Linenger present an overview of their mission. Video footage includes the following: prelaunch and launch activities, the crew eating breakfast, shuttle launch, on orbit activities, rendezvous with Mir, Shuttle/Mir joint activities, undocking, and the shuttle landing.

Investigation of sonic boom for the Space Shuttle: Low cross-range orbiter

NASA Technical Reports Server (NTRS)

Levy, Lionel L., Jr.; Hicks, Raymond M.; Mendoza, Joel P.

1993-01-01

It is desired that the Space Shuttle Orbiter be capable of landing at airports equipped to handle present-day jet transports. Since the majority of such airports are located near heavily populated areas, an investigation has been undertaken to determine whether or not the sonic boom generated during reentry of Space Shuttle Orbiters is potentially a serious problem. The investigation was concerned with the low cross-range orbiter and reentry concept proposed by Faget of the Manned Spacecraft Center (MSC). This report describes the approach used and presents the results obtained to date.

SRTM is removed from Endeavour's payload bay to ease wiring inspections

NASA Technical Reports Server (NTRS)

1999-01-01

In the Orbiter Processing Facility, workers observe as an overhead crane lowers the Shuttle Radar Topography Mission (SRTM) into a payload canister. The payload on mission STS-99, SRTM was removed from orbiter Endeavour's payload bay to allow technicians access to the orbiter's midbody for planned wiring inspections. The entire fleet of orbiters is being inspected for wiring abrasions after the problem was first discovered in Columbia. Shuttle managers are reviewing several manifest options and could establish new target launch dates for the balance of 1999 next week. Shuttle Endeavour currently remains slated for launch in early October.

Achieving Space Shuttle Abort-to-Orbit Using the Five-Segment Booster

NASA Technical Reports Server (NTRS)

Craft, Joe; Ess, Robert; Sauvageau, Don

2003-01-01

The Five-Segment Booster design concept was evaluated by a team that determined the concept to be feasible and capable of achieving the desired abort-to-orbit capability when used in conjunction with increased Space Shuttle main engine throttle capability. The team (NASA Johnson Space Center, NASA Marshall Space Flight Center, ATK Thiokol Propulsion, United Space Alliance, Lockheed-Martin Space Systems, and Boeing) selected the concept that provided abort-to-orbit capability while: 1) minimizing Shuttle system impacts by maintaining the current interface requirements with the orbiter, external tank, and ground operation systems; 2) minimizing changes to the flight-proven design, materials, and processes of the current four-segment Shuttle booster; 3) maximizing use of existing booster hardware; and 4) taking advantage of demonstrated Shuttle main engine throttle capability. The added capability can also provide Shuttle mission planning flexibility. Additional performance could be used to: enable implementation of more desirable Shuttle safety improvements like crew escape, while maintaining current payload capability; compensate for off nominal performance in no-fail missions; and support missions to high altitudes and inclinations. This concept is a low-cost, low-risk approach to meeting Shuttle safety upgrade objectives. The Five-Segment Booster also has the potential to support future heavy-lift missions.

Study of structural active cooling and heat sink systems for space shuttle

NASA Technical Reports Server (NTRS)

1972-01-01

This technology investigation was conducted to evaluate the feasibility of a number of thermal protection systems (TPS) concepts which are alternate candidates to the space shuttle baseline TPS. Four independent tasks were performed. Task 1 consisted of an in-depth evaluation of active structural cooling of the space shuttle orbiter. In Task 2, heat sink concepts for the booster were studied to identify and postulate solutions for design problems unique to heat sink TPS. Task 3 consisted of a feasibility demonstration test of a phase change material (PCM) incorporated into a reusable surface insulation (RSI) thermal protection system for the shuttle orbiter. In Task 4 the feasibility of heat pipes for stagnation region cooling was studied for the booster and the orbiter. Designs were developed for the orbiter leading edge and used in trade studies of leading edge concepts. At the time this program was initiated, a 2-stage fully reusable shuttle system was envisioned; therefore, the majority of the tasks were focused on the fully reusable system environments. Subsequently, a number of alternate shuttle system approaches, with potential for reduced shuttle system development funding requirements, were proposed. Where practicable, appropriate shifts in emphasis and task scoping were made to reflect these changes.

Closed loop performance of a brushless dc motor powered electromechanical actuator for flight control applications. [computerized simulation for Shuttle Orbiter applications

NASA Technical Reports Server (NTRS)

Demerdash, N. A.; Nehl, T. W.

1980-01-01

A comprehensive digital model for the analysis and possible optimization of the closed loop dynamic (instantaneous) performance of a power conditioner fed, brushless dc motor powered, electromechanical actuator system (EMA) is presented. This model was developed for the simulation of the dynamic performance of an actual prototype EMA built for NASA-JSC as a possible alternative to hydraulic actuators for consideration in Space Shuttle Orbiter applications. Excellent correlation was achieved between numerical model simulation and experimental test results obtained from the actual hardware. These results include: various current and voltage waveforms in the machine-power conditioner (MPC) unit, flap position as well as other control loop variables in response to step commands of change of flap position. These results with consequent conclusions are detailed in the paper.

KSC-02pd1086

NASA Image and Video Library

2002-06-27

KENNEDY SPACE CENTER, FLA. -- At the podium, Center Director Roy Bridges Jr. offers remarks at the commissioning ceremony for the new Convoy Command Vehicle behind him. At left is Mike McCulley, chief operating officer, United Space Alliance. The new 40-foot vehicle is replacing a 15-year old model, and will be used following Shuttle landings as the prime vehicle to control critical communications between the orbiter, the crew and the Launch Control Center, to monitor the health of the Shuttle Orbiter systems and to direct convoy operations at the Shuttle Landing Facility. Upgrades and high-tech features incorporated into the design and development of this vehicle make it more reliable and efficient for the convoy crew. Seating capacity was increased from 4 to 12, and video recorders and television monitors were added to provide the convoy team with the maximum amount of visual information

KSC-02pd1087

NASA Image and Video Library

2002-06-27

KENNEDY SPACE CENTER, FLA. -- At the podium, Center Director Roy Bridges Jr. offers remarks at the commissioning ceremony for the new Convoy Command Vehicle behind him. At left is Mike McCulley, chief operating officer, United Space Alliance. The new 40-foot vehicle is replacing a 15-year old model, and will be used following Shuttle landings as the prime vehicle to control critical communications between the orbiter, the crew and the Launch Control Center, to monitor the health of the Shuttle Orbiter systems and to direct convoy operations at the Shuttle Landing Facility. Upgrades and high-tech features incorporated into the design and development of this vehicle make it more reliable and efficient for the convoy crew. Seating capacity was increased from 4 to 12, and video recorders and television monitors were added to provide the convoy team with the maximum amount of visual information

Phase change paint tests on Rockwell orbiter/tank and orbiter alone configurations (OH3A/OH3B)

NASA Technical Reports Server (NTRS)

Quan, M.; Craig, C.

1974-01-01

Wind tunnel tests were conducted on scale models of the space shuttle orbiter and external tank. The tests were designed to determine the basic heating rate and interference effects on the orbiter-tank configuration and to analyze the effectiveness of the thermal protective system on the reentry vehicle. The phase change paint techniques were used to determine areodynamic heating rates. Oil flow and schlieren photographs were used for flow visualization.

Space Shuttle Project

NASA Image and Video Library

1978-04-21

This is an interior ground level view of the Shuttle Orbiter Enterprise being lowered for mating to External Tank (ET) inside Marshall Space Flight Center's Dynamic Test Stand for Mated Vertical Ground Vibration tests (MVGVT). The tests marked the first time ever that the entire shuttle complement (including Orbiter, external tank, and solid rocket boosters) were mated vertically.

Shuttle cryogenics supply system. Optimization study. Volume 5 B-4: Programmers manual for space shuttle orbit injection analysis (SOPSA)

NASA Technical Reports Server (NTRS)

1973-01-01

A computer program for space shuttle orbit injection propulsion system analysis (SOPSA) is described to show the operational characteristics and the computer system requirements. The program was developed as an analytical tool to aid in the preliminary design of propellant feed systems for the space shuttle orbiter main engines. The primary purpose of the program is to evaluate the propellant tank ullage pressure requirements imposed by the need to accelerate propellants rapidly during the engine start sequence. The SOPSA program will generate parametric feed system pressure histories and weight data for a range of nominal feedline sizes.

Probabilistic risk assessment of the Space Shuttle. Phase 3: A study of the potential of losing the vehicle during nominal operation. Volume 2: Integrated loss of vehicle model

NASA Technical Reports Server (NTRS)

Fragola, Joseph R.; Maggio, Gaspare; Frank, Michael V.; Gerez, Luis; Mcfadden, Richard H.; Collins, Erin P.; Ballesio, Jorge; Appignani, Peter L.; Karns, James J.

1995-01-01

The application of the probabilistic risk assessment methodology to a Space Shuttle environment, particularly to the potential of losing the Shuttle during nominal operation is addressed. The different related concerns are identified and combined to determine overall program risks. A fault tree model is used to allocate system probabilities to the subsystem level. The loss of the vehicle due to failure to contain energetic gas and debris, to maintain proper propulsion and configuration is analyzed, along with the loss due to Orbiter, external tank failure, and landing failure or error.

Development of the reentry flight dynamics simulator for evaluation of space shuttle orbiter entry systems

NASA Technical Reports Server (NTRS)

Rowell, L. F.; Powell, R. W.; Stone, H. W., Jr.

1980-01-01

A nonlinear, six degree of freedom, digital computer simulation of a vehicle which has constant mass properties and whose attitudes are controlled by both aerodynamic surfaces and reaction control system thrusters was developed. A rotating, oblate Earth model was used to describe the gravitational forces which affect long duration Earth entry trajectories. The program is executed in a nonreal time mode or connected to a simulation cockpit to conduct piloted and autopilot studies. The program guidance and control software used by the space shuttle orbiter for its descent from approximately 121.9 km to touchdown on the runway.

STS_135_SAIL

NASA Image and Video Library

2011-07-12

JSC2011-E-067674 (12 July 2011) --- Chris St. Julian, left, a Prairie View A&M electrical engineering major who is interning at NASA for the summer, pilots the shuttle for a simulated landing in the Shuttle Avionics Integration Laboratory (SAIL) at the Johnson Space Center in Houston, July 12, 2011. The laboratory is a skeletal avionics version of the shuttle that uses actual orbiter hardware and flight software. The facility bears the orbiter designation of Orbiter Vehicle 095. Photo credit: NASA Photo/Houston Chronicle, Smiley N. Pool

Second Shuttle Join NASA's STS Fleet: Challenger Launches First New Tracking Satellite

NASA Technical Reports Server (NTRS)

1983-01-01

NASA made a major stride in readying a second delivery vehicle for its Space Transportation System (STS) fleet with the perfect landing of Shuttle Orbiter Challenger at Edwards Air Force Base, California, April 9, 1983. Besides being the first flight test of Challenger's performance, the mission marked the orbiting of the first spacecraft in NASA's new Tracking and Data Relay Satellite System (TDRSS). The new family of orbiting space communications platforms is essential to serve future Shuttle missions. Although the Inertial Upper Stage (IUS) second stage engine firing failed to place TDRS in its final 35,888 kilometer (22,300 mile) geosynchronous orbit, its release from the orbiter cargo bay went as planned. Launch officials were confident they can achieve its planned orbit in a matter of weeks.

KSC-2012-5801

NASA Image and Video Library

2012-10-16

CAPE CANAVERAL, Fla. – The nose gear of space shuttle Atlantis retracts as the shuttle sits on the orbiter transporter vehicle in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida. The shuttle is being prepared for its move from the OPF to the Vehicle Assembly Building during transition and retirement work. Later, the shuttle will be taken to the Kennedy Space Center Visitor Complex where it will go on public display. Photo credit: NASA/Jim Grossmann

KSC-2012-5802

NASA Image and Video Library

2012-10-16

CAPE CANAVERAL, Fla. – The nose gear of space shuttle Atlantis retracts as the shuttle sits on the orbiter transporter vehicle in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida. The shuttle is being prepared for its move from the OPF to the Vehicle Assembly Building during transition and retirement work. Later, the shuttle will be taken to the Kennedy Space Center Visitor Complex where it will go on public display. Photo credit: NASA/Jim Grossmann

The use of the Space Shuttle for land remote sensing

NASA Technical Reports Server (NTRS)

Thome, P. G.

1982-01-01

The use of the Space Shuttle for land remote sensing will grow significantly during the 1980's. The main use will be for general land cover and geological mapping purposes by worldwide users employing specialized sensors such as: high resolution film systems, synthetic aperture radars, and multispectral visible/IR electronic linear array scanners. Because these type sensors have low Space Shuttle load factors, the user's preference will be for shared flights. With this strong preference and given the present prognosis for Space Shuttle flight frequency as a function of orbit inclination, the strongest demand will be for 57 deg orbits. However, significant use will be made of lower inclination orbits. Compared with freeflying satellites, Space Shuttle mission investment requirements will be significantly lower. The use of the Space Shuttle for testing R and D land remote sensors will replace the free-flying satellites for most test programs.

STS-38 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Camp, David W.; Germany, D. M.; Nicholson, Leonard S.

1991-01-01

The STS-38 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities on this thirty-seventh flight of the Space Shuttle and the seventh flight of the Orbiter vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-40/LWT-33), three Space Shuttle main engines (SSME's) (serial numbers 2019, 2022, 2027), and two Solid Rocket Boosters (SRB's), designated as BI-039. The STS-38 mission was a classified Department of Defense mission, and as much, the classified portions of the mission are not presented in this report. The sequence of events for this mission is shown. The significant problems that occurred in the Space Shuttle Orbiter subsystem during the mission are summarized and the official problem tracking list is presented. In addition, each Space Shuttle Orbiter problem is cited in the subsystem discussion.

A study of aerodynamic heating distributions on a tip-fin controller installed on a Space Shuttle Orbiter model

NASA Technical Reports Server (NTRS)

Wittliff, C. E.

1982-01-01

The aerodynamic heating of a tip-fin controller mounted on a Space Shuttle Orbiter model was studied experimentally in the Calspan Advanced Technology Center 96 inch Hypersonic Shock Tunnel. A 0.0175 scale model was tested at Mach numbers from 10 to 17.5 at angles of attack typical of a shuttle entry. The study was conducted in two phases. In phase 1 testing a thermographic phosphor technique was used to qualitatively determine the areas of high heat-transfer rates. Based on the results of this phase, the model was instrumented with 40 thin-film resistance thermometers to obtain quantitative measurements of the aerodynamic heating. The results of the phase 2 testing indicate that the highest heating rates, which occur on the leading edge of the tip-fin controller, are very sensitive to angle of attack for alpha or = 30 deg. The shock wave from the leading edge of the orbiter wing impinges on the leading edge of the tip-fin controller resulting in peak values of h/h(Ref) in the range from 1.5 to 2.0. Away from the leading edge, the heat-transfer rates never exceed h/h(Ref) = 0.25 when the control surface, is not deflected. With the control surface deflected 20 deg, the heat-transfer rates had a maximum value of h/h(Ref) = 0.3. The heating rates are quite nonuniform over the outboard surface and are sensitive to angle of attack.

KSC-2011-2863

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

KSC-2011-3009

NASA Image and Video Library

2011-04-21

CAPE CANAVERAL, Fla. -- NASA's Stephanie Stilson (facing camera), flow director for space shuttle Discovery, discusses Discovery's thermal protection system with members of a visiting team from the Smithsonian's National Air and Space Museum in Orbiter Processing Facility-2 at NASA's Kennedy Space Center. NASA Administrator Charles Bolden announced April 12 the facilities where all four shuttle orbiters will be permanently displayed at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired in March after completing its 39th mission. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Photo credit: NASA/Cory Huston

KSC-2011-3010

NASA Image and Video Library

2011-04-21

CAPE CANAVERAL, Fla. -- Members of a visiting team from the Smithsonian's National Air and Space Museum receive a briefing on the application of the space shuttle's thermal protection system tile in Orbiter Processing Facility-2 at NASA's Kennedy Space Center. NASA Administrator Charles Bolden announced April 12 the facilities where all four shuttle orbiters will be permanently displayed at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired in March after completing its 39th mission. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Photo credit: NASA/Cory Huston

KSC-2011-2865

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

KSC-2011-3008

NASA Image and Video Library

2011-04-21

CAPE CANAVERAL, Fla. -- Members of a visiting team from the Smithsonian's National Air and Space Museum inspect the aft-end of space shuttle Discovery in Orbiter Processing Facility-2 at NASA's Kennedy Space Center. NASA Administrator Charles Bolden announced April 12 the facilities where all four shuttle orbiters will be permanently displayed at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired in March after completing its 39th mission. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Photo credit: NASA/Cory Huston

KSC-2011-7775

NASA Image and Video Library

2011-11-15

CAPE CANAVERAL, Fla. – Inside Orbiter Processing Facility-1 at NASA’s Kennedy Space Center in Florida, technicians install the shuttle orbiter repackaged galley (SORG) in the middeck of space shuttle Discovery. After Discovery’s final mission, STS-133, the SORG was removed and sent to a United Space Alliance lab in Houston where it was cleaned and deserviced. Water in the microbial check valve and the orbiter water system was drained and dried. The SORG was returned to Kennedy Space Center. The work is part of the Space Shuttle Program’s transition and retirement processing of shuttle Discovery, which is being prepared for display at Smithsonian’s National Air and Space Museum, Steven F. Udvar-Hazy Center in Chantilly, Va. For more information, visit http://www.nasa.gov/shuttle. Photo credit: NASA/Dimitri Gerondidakis

KSC-2011-7772

NASA Image and Video Library

2011-11-15

CAPE CANAVERAL, Fla. – Inside Orbiter Processing Facility-1 at NASA’s Kennedy Space Center in Florida, technicians prepare to install the shuttle orbiter repackaged galley (SORG) in the middeck of space shuttle Discovery. After Discovery’s final mission, STS-133, the SORG was removed and sent to a United Space Alliance lab in Houston where it was cleaned and deserviced. Water in the microbial check valve and the orbiter water system was drained and dried. The SORG was returned to Kennedy Space Center. The work is part of the Space Shuttle Program’s transition and retirement processing of shuttle Discovery, which is being prepared for display at Smithsonian’s National Air and Space Museum, Steven F. Udvar-Hazy Center in Chantilly, Va. For more information, visit http://www.nasa.gov/shuttle. Photo credit: NASA/Dimitri Gerondidakis

KSC-2011-7776

NASA Image and Video Library

2011-11-15

CAPE CANAVERAL, Fla. – Inside Orbiter Processing Facility-1 at NASA’s Kennedy Space Center in Florida, the shuttle orbiter repackaged galley (SORG) is installed in the middeck of space shuttle Discovery. After Discovery’s final mission, STS-133, the SORG was removed and sent to a United Space Alliance lab in Houston where it was cleaned and deserviced. Water in the microbial check valve and the orbiter water system was drained and dried. The SORG was returned to Kennedy Space Center. The work is part of the Space Shuttle Program’s transition and retirement processing of shuttle Discovery, which is being prepared for display at Smithsonian’s National Air and Space Museum, Steven F. Udvar-Hazy Center in Chantilly, Va. For more information, visit http://www.nasa.gov/shuttle. Photo credit: NASA/Dimitri Gerondidakis

KSC-2011-7771

NASA Image and Video Library

2011-11-15

CAPE CANAVERAL, Fla. – Inside Orbiter Processing Facility-1 at NASA’s Kennedy Space Center in Florida, the shuttle orbiter repackaged galley (SORG) is being installed in the middeck of space shuttle Discovery. After Discovery’s final mission, STS-133, the SORG was removed and sent to a United Space Alliance lab in Houston where it was cleaned and deserviced. Water in the microbial check valve and the orbiter water system was drained and dried. The SORG was returned to Kennedy Space Center. The work is part of the Space Shuttle Program’s transition and retirement processing of shuttle Discovery, which is being prepared for display at Smithsonian’s National Air and Space Museum, Steven F. Udvar-Hazy Center in Chantilly, Va. For more information, visit http://www.nasa.gov/shuttle. Photo credit: NASA/Dimitri Gerondidakis

KSC-2011-7773

NASA Image and Video Library

2011-11-15

CAPE CANAVERAL, Fla. – Inside Orbiter Processing Facility-1 at NASA’s Kennedy Space Center in Florida, technicians prepare to install the shuttle orbiter repackaged galley (SORG) in the middeck of space shuttle Discovery. After Discovery’s final mission, STS-133, the SORG was removed and sent to a United Space Alliance lab in Houston where it was cleaned and deserviced. Water in the microbial check valve and the orbiter water system was drained and dried. The SORG was returned to Kennedy Space Center. The work is part of the Space Shuttle Program’s transition and retirement processing of shuttle Discovery, which is being prepared for display at Smithsonian’s National Air and Space Museum, Steven F. Udvar-Hazy Center in Chantilly, Va. For more information, visit http://www.nasa.gov/shuttle. Photo credit: NASA/Dimitri Gerondidakis

KSC-2011-7774

NASA Image and Video Library

2011-11-15

CAPE CANAVERAL, Fla. – Inside Orbiter Processing Facility-1 at NASA’s Kennedy Space Center in Florida, technicians install the shuttle orbiter repackaged galley (SORG) in the middeck of space shuttle Discovery. After Discovery’s final mission, STS-133, the SORG was removed and sent to a United Space Alliance lab in Houston where it was cleaned and deserviced. Water in the microbial check valve and the orbiter water system was drained and dried. The SORG was returned to Kennedy Space Center. The work is part of the Space Shuttle Program’s transition and retirement processing of shuttle Discovery, which is being prepared for display at Smithsonian’s National Air and Space Museum, Steven F. Udvar-Hazy Center in Chantilly, Va. For more information, visit http://www.nasa.gov/shuttle. Photo credit: NASA/Dimitri Gerondidakis

Prediction of force and acceleration control spectra for Space Shuttle orbiter sidewall-mounted payloads

NASA Technical Reports Server (NTRS)

Hipol, Philip J.

1990-01-01

The development of force and acceleration control spectra for vibration testing of Space Shuttle (STS) orbiter sidewall-mounted payloads requiresreliable estimates of the sidewall apparent weight and free (i.e. unloaded) vibration during lift-off. The feasibility of analytically predicting these quantities has been investigated through the development and analysis of a finite element model of the STS cargo bay. Analytical predictions of the sidewall apparent weight were compared with apparent weight measurements made on OV-101, and analytical predictions of the sidewall free vibration response during lift-off were compared with flight measurements obtained from STS-3 and STS-4. These analysis suggest that the cargo bay finite element model has potential application for the estimation of force and acceleration control spectra for STS sidewall-mounted payloads.

Results of investigations conducted in the LaRC 8-foot transonic pressure tunnel using the 0.010-scale 72-OTS model of the space shuttle integrated vehicle (IA93)

NASA Technical Reports Server (NTRS)

Nichols, M. E.

1976-01-01

Test procedures, history, and data from the wind tunnel test are presented. Aero-loads were investigated on the updated configuration-5 space shuttle launch vehicle at Mach numbers from 0.600 to 1.205. Six-component vehicle forces and moments, base and sting-cavity pressures, elevon hinge moments, wing-root bending and torsion moments, and normal shear force data were obtained. Full simulation of updated vehicle protuberances and attach hardware was employed. Various elevon deflection angles were tested with two different forward orbiter-to-external-tank attach-strut configurations. The entire model was supported by means of a balance mounted in the orbiter through its base and suspended from a sting.

Solution accuracies of finite element reentry heat transfer and thermal stress analyses of Space Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Ko, William L.

1988-01-01

Accuracies of solutions (structural temperatures and thermal stresses) obtained from different thermal and structural FEMs set up for the Space Shuttle Orbiter (SSO) are compared and discussed. For studying the effect of element size on the solution accuracies of heat-transfer and thermal-stress analyses of the SSO, five SPAR thermal models and five NASTRAN structural models were set up for wing midspan bay 3. The structural temperature distribution over the wing skin (lower and upper) surface of one bay was dome shaped and induced more severe thermal stresses in the chordwise direction than in the spanwise direction. The induced thermal stresses were extremely sensitive to slight variation in structural temperature distributions. Both internal convention and internal radiation were found to have equal effects on the SSO.

Results of investigations conducted in the LaRC 4-foot unitary plan wind tunnel leg no. 1 using the 0.010-scale 72-OTS model of the space shuttle integrated vehicle (IA94A)

NASA Technical Reports Server (NTRS)

Nichols, M. E.

1976-01-01

Aero-loads investigations were conducted on the updated configuration-5 space shuttle launch vehicle at Mach numbers 2.50, 3.50, and 4.50. Six-component vehicle forces and moments, base and sting-cavity pressures, elevon hinge moments, wing-root bending and torsion moments, and normal shear force data were obtained. Full simulation of updated vehicle protuberances and attach hardware was employed. Various elevon deflection angles were tested, with two different forward orbiter-to-external-tank attach-strut configurations. The entire vehicle model 72-OTS was supported by means of a balance mounted in the orbiter through its base and suspended from an appropriate sting for the specific tunnel.

Orbiter CIU/IUS communications hardware evaluation

NASA Technical Reports Server (NTRS)

Huth, G. K.

1979-01-01

The DOD and NASA inertial upper stage communication system design, hardware specifications and interfaces were analyzed to determine their compatibility with the Orbiter payload communications equipment (Payload Interrogator, Payload Signal Processors, Communications Interface Unit, and the Orbiter operational communications equipment (the S-Band and Ku-band systems). Topics covered include (1) IUS/shuttle Orbiter communications interface definition; (2) Orbiter avionics equipment serving the IUS; (3) IUS communication equipment; (4) IUS/shuttle Orbiter RF links; (5) STDN/TDRS S-band related activities; and (6) communication interface unit/Orbiter interface issues. A test requirement plan overview is included.

STS-71 Mission Highlights Resources Tape

NASA Technical Reports Server (NTRS)

1997-01-01

The flight crew of the STS-71 Space Shuttle Orbiter Atlantis Commander Robert L. Gibson, Pilot Charles J. Precourt, Mission Specialists, Ellen S. Baker, Bonnie J. Dunbar, Gregory J. Harbaugh, and Payload Specialists, Norman E. Thagard, Vladimir Dezhurov, and Gennadiy Strekalov present an overview of their mission. It's primary objective is the first Mir docking with a space shuttle and crew transfer. Video footage includes the following: prelaunch and launch activities; the crew eating breakfast; shuttle launch; on orbit activities; rendezvous with Mir; Shuttle/Mir joint activities; undocking; and the shuttle landing.

KSC-2012-1863

NASA Image and Video Library

2012-02-17

Space Shuttle Payloads: Kennedy Space Center was the hub for the final preparation and launch of the space shuttle and its payloads. The shuttle carried a wide variety of payloads into Earth orbit. Not all payloads were installed in the shuttle's cargo bay. In-cabin payloads were carried in the shuttle's middeck. Cargo bay payloads were typically large payloads which did not require a pressurized environment, such as interplanetary space probes, earth-orbiting satellites, scientific laboratories and International Space Station trusses and components. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA

Endeavour Lands at LAX

NASA Image and Video Library

2012-09-21

Space shuttle Endeavour, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) performs a low flyby at Los Angeles International Airport, Friday, Sept. 21, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers.Photo Credit: (NASA/Bill Ingalls)

Endeavour Lands at LAX

NASA Image and Video Library

2012-09-21

Space shuttle Endeavour, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) lands at Los Angeles International Airport, Friday, Sept. 21, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers.Photo Credit: (NASA/Bill Ingalls)

High supersonic stability and control characteristics of a 0.015-scale (remotely controlled elevon) model 44-0 space shuttle orbiter tested in the NASA/LaRC 4-foot UPWT (LEG 2) (LA75), volume 1

NASA Technical Reports Server (NTRS)

Ball, J. W.

1976-01-01

Wind tunnel tests are reported on a 0.015-scale SSV orbiter model with remote independently operated left and right elevon surfaces. Special attention was directed to definition of nonlinear aerodynamic characteristics by taking data at small increments. Six component aerodynamic force and moment and elevon position data were recorded for the space shuttle orbiter with various elevon, aileron rudder and speed brake deflection combinations over an angle of attack range from -4 deg to 32 deg at angles of sideslip of 0 deg and 3 deg. Additional tests were made over an angle of sideslip range from -6 deg to 8 deg at selected angles of attack. Test Mach numbers were 2.86, 2.90, 3.90 and 4.60 with Reynolds numbers held at a constant 2.0 x 1 million per foot.

Results of investigations on a 0.010-scale model of the configuration 3 space shuttle orbiter and external tank in the NASA/Ames Research Center 3.5-foot hypersonic wind tunnel (IA15)

NASA Technical Reports Server (NTRS)

Petrozzi, M. T.; Milam, M. D.; Mellenthin, J. A.

1974-01-01

Experimental aerodynamic investigations were conducted in a 3.5-foot hypersonic wind tunnel. The model used for this test was a 0.010-scale of the Configuration 2 Space Shuttle Orbiter and the External Tank. Six-component aerodynamic force and moment data were recorded over an angle of attack range from -8 deg to +30 deg at 0 deg and 5 deg angles of sideslip. Data was also recorded during beta sweeps of -8 deg to +10 deg at angles of attack of -10 deg, 0 deg, and 30 deg. All testing was done at Mach 7.3. Various elevon, rudder and orbiter to external tank attaching structures and fairings were tested to determine longitudinal and lateral-directional stability characteristics. Non-metric exhaust plumes were installed during a portion of the testing to determine the effects of the main propulsion system rocket plumes.

Space Shuttle Projects

NASA Image and Video Library

2001-01-01

The Space Shuttle represented an entirely new generation of space vehicles, the world's first reusable spacecraft. Unlike earlier expendable rockets, the Shuttle was designed to be launched over and over again and would serve as a system for ferrying payloads and persornel to and from Earth orbit. The Shuttle's major components are the orbiter spacecraft; the three main engines, with a combined thrust of more than 1.2 million pounds; the huge external tank (ET) that feeds the liquid hydrogen fuel and liquid oxygen oxidizer to the three main engines; and the two solid rocket boosters (SRB's), with their combined thrust of some 5.8 million pounds, that provide most of the power for the first two minutes of flight. Crucially involved with the Space Shuttle program virtually from its inception, the Marshall Space Flight Center (MSFC) played a leading role in the design, development, testing, and fabrication of many major Shuttle propulsion components. The MSFC was assigned responsibility for developing the Shuttle orbiter's high-performance main engines, the most complex rocket engines ever built. The MSFC was also responsible for developing the Shuttle's massive ET and the solid rocket motors and boosters.

Space Shuttle Projects

NASA Image and Video Library

1975-01-01

The Space Shuttle represented an entirely new generation of space vehicle, the world's first reusable spacecraft. Unlike earlier expendable rockets, the Shuttle was designed to be launched over and over again and would serve as a system for ferrying payloads and persornel to and from Earth orbit. The Shuttle's major components are the orbiter spacecraft; the three main engines, with a combined thrust of more than 1.2 million pounds; the huge external tank (ET) that feeds the liquid hydrogen fuel and liquid oxygen oxidizer to the three main engines; and the two solid rocket boosters (SRB's), with their combined thrust of some 5.8 million pounds. The SRB's provide most of the power for the first two minutes of flight. Crucially involved with the Space Shuttle program virtually from its inception, the Marshall Space Flight Center (MSFC) played a leading role in the design, development, testing, and fabrication of many major Shuttle propulsion components. The MSFC was assigned responsibility for developing the Shuttle orbiter's high-performance main engines, the most complex rocket engines ever built. The MSFC was also responsible for developing the Shuttle's massive ET and the solid rocket motors and boosters.

Results of flutter test OS6 obtained using the 0.14-scale wing/elevon model (54-0) in the NASA LaRC 16-foot transonic dynamics wind tunnel

NASA Technical Reports Server (NTRS)

Berthold, C. L.

1977-01-01

A 0.14-scale dynamically scaled model of the space shuttle orbiter wing was tested in the Langley Research Center 16-Foot Transonic Dynamics Wind Tunnel to determine flutter, buffet, and elevon buzz boundaries. Mach numbers between 0.3 and 1.1 were investigated. Rockwell shuttle model 54-0 was utilized for this investigation. A description of the test procedure, hardware, and results of this test is presented.

Space shuttle. [a transportation system for low orbit space missions

NASA Technical Reports Server (NTRS)

1974-01-01

The space shuttle is discussed as a reusable space vehicle operated as a transportation system for space missions in low earth orbit. Space shuttle studies and operational capabilities are reported for potential missions indicating that about 38 percent are likely to be spacelab missions with the remainder being the replacement, revisit, or retrieval of automated spacecraft.

Astronomy sortie missions definition study. Volume 3, book 2: Appendix: Design analysis and trade studies

NASA Technical Reports Server (NTRS)

1972-01-01

Backup or supporting data for the design analyses and trade studies which defined the astronomy sortie missions are presented. The subjects discussed are: (1) configuration of space shuttle orbiter, (2) electronic subsystems, (3) electric power requirements, and (4) payload requirements. Mathematical models are developed to illustrate the orbital rendezvous capabilities.

Space shuttle: Heat transfer rate distributions on McDonnell-Douglas delta wing orbiter determined by phase-change paint technique for nominal Mach number of 8

NASA Technical Reports Server (NTRS)

Matthews, R. K.; Martindale, W. R.; Warmbrod, J. D.

1972-01-01

The results are reported of the phase-change paint tests conducted at Mach 8, to determine the aerodynamic heat transfer distributions on the McDonnell Douglas delta wing orbiter. Model details, test conditions, and reduced heat transfer data are presented.

High supersonic stability and control characteristics of a 0.015-scale (remotely controlled elevon) model 49-0 of the space shuttle orbiter tested in the NASA/LaRC 4-foot UPWT (LEG 2) (LA63B)

NASA Technical Reports Server (NTRS)

Gamble, J. D.

1976-01-01

The model tested was a Langley-built 0.015-scale SSV Orbiter model with remote independently operated left and right elevon surfaces. The objective of the test was to generate a detailed aerodynamic data base for the current Shuttle Orbiter Configuration. Special attention was directed to definition of nonlinear aerodynamic characteristics by taking data at small increments, angle of attack, angle of sideslip, and elevon position. Six-component aerodynamic force and moment and elevon position data were recorded over an angle-of-attack range from -4 deg to 45 deg, at angles of sideslip of 0 deg, + or - 2 deg, and + or - 4 deg. Additional tests were made over an angle of sideslip range from -6 deg to 8 deg at selected angles of attack. The test Mach numbers were 2.86, 3.90, and 4.60 with Reynolds number held at a constant two million per foot.

Shuttle antenna radome technology test program. Volume 2: Development of S-band antenna interface design

NASA Technical Reports Server (NTRS)

Kuhlman, E. A.; Baranowski, L. C.

1977-01-01

The effects of the Thermal Protection Subsystem (TPS) contamination on the space shuttle orbiter S band quad antenna due to multiple mission buildup are discussed. A test fixture was designed, fabricated and exposed to ten cycles of simulated ground and flight environments. Radiation pattern and impedance tests were performed to measure the effects of the contaminates. The degradation in antenna performance was attributed to the silicone waterproofing in the TPS tiles rather than exposure to the contaminating sources used in the test program. Validation of the accuracy of an analytical thermal model is discussed. Thermal vacuum tests with a test fixture and a representative S band quad antenna were conducted to evaluate the predictions of the analytical thermal model for two orbital heating conditions and entry from each orbit. The results show that the accuracy of predicting the test fixture thermal responses is largely dependent on the ability to define the boundary and ambient conditions. When the test conditions were accurately included in the analytical model, the predictions were in excellent agreement with measurements.

Subsonic stability and control characteristics of a 0.015-scale (remotely controlled elevon) model 44-0 of the space shuttle orbiter tested in the NASA/ARC 12-foot pressure tunnel (LA66)

NASA Technical Reports Server (NTRS)

Underwood, J. M.; Parrell, H.

1976-01-01

The investigation was conducted in the NASA/Ames Research Center 12-foot Pressure Tunnel. The model was a Langley-built 0.015-scale SSV orbiter model with remote independently operated left and right elevon surfaces. The objective of the test was to generate a detailed aerodynamic data base for the current shuttle orbiter configuration. Special attention was directed to definition of nonlinear aerodynamic characteristics by taking data at small increments in angle of attack, angle of sideslip, and elevon position. Six-component aerodynamic force and moment and elevon position data were recorded over an angle of attack range from -4 deg to 24 deg at angles of sideslip of 0 deg and + or - 4 deg. Additional tests were made over an angle of sideslip range from -6 deg to 6 deg at selected angles of attack. The test Mach numbers were 0.22 and 0.29 and the Reynolds number was varied from 2.0 to 8.5 million per foot.

KSC-03PD-1064

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employee Mike Cote installs Thermal Protection System tiles on a test panel. The test panel and sections of Space Shuttle orbiter Enterprise (OV-101) will be transferred to the Southwest Research Institute for testing after the tile installation is complete. The testing has been requested by the Columbia Accident Investigation Board. Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight.

Shuttle Endeavour Mated to 747 SCA Takeoff for Delivery to Kennedy Space Center, Florida

NASA Image and Video Library

1991-05-02

NASA's 747 Shuttle Carrier Aircraft No. 911, with the space shuttle orbiter Endeavour securely mounted atop its fuselage, begins the ferry flight from Rockwell's Plant 42 at Palmdale, California, where the orbiter was built, to the Kennedy Space Center, Florida. At Kennedy, the space vehicle was processed and launched on orbital mission STS-49, which landed at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, 16 May 1992. NASA 911, the second modified 747 that went into service in November 1990, has special support struts atop the fuselage and internal strengthening to accommodate the added weight of the orbiters.

KSC-03PD-1079

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employee Harrell Watts (right) installs Thermal Protection System tiles on a main landing gear door of Space Shuttle orbiter Enterprise (OV-101). Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight. After the tile installation is complete, the sections will be transferred to the Southwest Research Institute for testing requested by the Columbia Accident Investigation Board.

Analytical and experimental study of the effects of wing-body aerodynamic interaction on space shuttle subsonic flutter

NASA Technical Reports Server (NTRS)

Chipman, R. R.; Rauch, F. J.

1975-01-01

The effects on flutter of the aerodynamic interaction between the space shuttle bodies and wing, 1/80th-scale semispan models of the orbiter wing, the complete shuttle and intermediate component combinations were tested in the NASA Langley Research Center 26-inch Transonic Blowdown Wind Tunnel. Using the double lattice method combined with slender body theory to calculate unsteady aerodynamic forces, subsonic flutter speeds were computed for comparison. Using calculated complete vehicle modes, flutter speed trends were computed for the full scale vehicle at an altitude of 15,200 meters and a Mach number of 0.6. Consistent with findings of the model studies, analysis shows the shuttle to have the same flutter speed as an isolated cantilevered wing.

Parametric trade studies on a Shuttle 2 launch system architecture

NASA Technical Reports Server (NTRS)

Stanley, Douglas O.; Talay, Theodore A.; Lepsch, Roger A.; Morris, W. Douglas; Naftel, J. Christopher; Cruz, Christopher I.

1991-01-01

A series of trade studies are presented on a complementary architecture of launch vehicles as a part of a study often referred to as Shuttle-2. The results of the trade studies performed on the vehicles of a reference Shuttle-2 mixed fleet architecture have provided an increased understanding of the relative importance of each of the major vehicle parameters. As a result of trades on the reference booster-orbiter configuration with a methane booster, the study showed that 60 percent of the total liftoff thrust should be on the booster and 40 percent on the orbiter. It was also found that the liftoff thrust to weight ratio (T/W) on the booster-orbiter should be 1.3. This leads to a low dry weight and still provides enough thrust to allow the design of a heavy lift architecture. As a result of another trade study, the dry weight of the reference booster-orbiter was chosen for a variety of operational considerations. Other trade studies on the booster-orbiter demonstrate that the cross feeding of propellant during boost phase is desirable and that engine-out capability from launch to orbit is worth the performance penalty. Technology assumptions made during the Shuttle-2 design were shown to be approx. equivalent to a 25 percent across the board weight reduction over the Space Shuttle technology. The vehicles of the Shuttle-2 architecture were also sized for a wide variety of payloads and missions to different orbits. Many of these same parametric trades were also performed on completely liquid hydrogen fueled fully reusable concepts. If a booster-orbiter is designed using liquid hydrogen engines on both the booster and orbiter, the total vehicle dry weight is only 3.0 percent higher than the reference dual-fuel booster-orbiter, and the gross weight is 3.8 percent less. For this booster-orbiter vehicle, a liftoff T/W of 1.3, a thrust of about 60 percent on the booster, and a Mach staging number of 3 all proved to be desirable. This modest dry weight increase for a liquid hydrogen fueled Shuttle-2 system should be more than offset by the elimination of the entire hydrocarbon engine development program and the savings in operation cost realized by the elimination of an entire fuel type.

Safety in earth orbit study. Volume 5: Space shuttle payloads: Safety requirements and guidelines on-orbit phase

NASA Technical Reports Server (NTRS)

1972-01-01

Safety requirements and guidelines are listed for the sortie module, upper stage vehicle, and space station for the earth orbit operations of the space shuttle program. The requirements and guidelines are for vehicle design, safety devices, warning devices, operational procedures, and residual hazards.

DSMC simulations of the Shuttle Plume Impingement Flight EXperiment(SPIFEX)

NASA Technical Reports Server (NTRS)

Stewart, Benedicte; Lumpkin, Forrest

2017-01-01

During orbital maneuvers and proximity operations, a spacecraft fires its thrusters inducing plume impingement loads, heating and contamination to itself and to any other nearby spacecraft. These thruster firings are generally modeled using a combination of Computational Fluid Dynamics (CFD) and DSMC simulations. The Shuttle Plume Impingement Flight EXperiment(SPIFEX) produced data that can be compared to a high fidelity simulation. Due to the size of the Shuttle thrusters this problem was too resource intensive to be solved with DSMC when the experiment flew in 1994.

Automated biowaste sampling system feces monitoring system

NASA Technical Reports Server (NTRS)

Hunt, S. R.; Glanfield, E. J.

1979-01-01

The Feces Monitoring System (FMS) Program designed, fabricated, assembled and tested an engineering model waste collector system (WCS) to be used in support of life science and medical experiments related to Shuttle missions. The FMS design was patterned closely after the Shuttle WCS, including: interface provisions; mounting; configuration; and operating procedures. These similarities make it possible to eventually substitute an FMS for the Shuttle WCS of Orbiter. In addition, several advanced waste collection features, including the capability of real-time inertial fecal separation and fecal mass measurement and sampling were incorporated into the FMS design.

Shuttle program. MCC level C formulation requirements: Shuttle TAEM guidance and flight control

NASA Technical Reports Server (NTRS)

Carman, G. L.

1980-01-01

The Level C requirements for the shuttle orbiter terminal area energy management (TAEM) guidance and flight control functions to be incorporated into the Mission Control Center entry profile planning processor are defined. This processor will be used for preentry evaluation of the entry through landing maneuvers, and will include a simplified three degree-of-freedom model of the body rotational dynamics that is necessary to account for the effects of attitude response on the trajectory dynamics. This simulation terminates at TAEM-autoland interface.

Using the Shuttle In Situ Window and Radiator Data for Meteoroid Measurements

NASA Technical Reports Server (NTRS)

Matney, Mark

2015-01-01

Every time NASA's Space Shuttle flew in orbit, it was exposed to the natural meteoroid and artificial debris environment. NASA Johnson Space Center maintains a database of impact cratering data of 60 Shuttle missions flown since the mid-1990's that were inspected after flight. These represent a total net exposure time to the space environment of 2 years. Impact damage was recorded on the windows and radiators, and in many cases information on the impactor material was determined by later analysis of the crater residue. This information was used to segregate damage caused by natural meteoroids and artificial space debris. The windows represent a total area of 3.565 sq m, and were capable of resolving craters down to about 10 micrometers in size. The radiators represent a total area of 119.26 sq m, and saw damage from objects up to approximately 1 mm in diameter. These data were used extensively in the development of NASA's ORDEM 3.0 Orbital Debris Environment Model, and gives a continuous picture of the orbital debris environment in material type and size ranging from about 10 micrometers to 1 mm. However, the meteoroid data from the Shuttles have never been fully analyzed. For the orbital debris work, special "as flown" files were created that tracked the pointing of the surface elements and their shadowing by structure (such as the ISS during docking). Unfortunately, such files for the meteoroid environment have not yet been created. This talk will introduce these unique impact data and describe how they were used for orbital debris measurements. We will then discuss some simple first-order analyses of the meteoroid data, and point the way for future analyses.

Analytical and experimental investigation of a 1/8-scale dynamic model of the shuttle orbiter. Volume 3B: Supporting data

NASA Technical Reports Server (NTRS)

Mason, P. W.; Harris, H. G.; Zalesak, J.; Bernstein, M.

1974-01-01

The NASA Structural Analysis System (NASTRAN) Model 1 finite element idealization, input data, and detailed analytical results are presented. The data presented include: substructuring analysis for normal modes, plots of member data, plots of symmetric free-free modes, plots of antisymmetric free-free modes, analysis of the wing, analysis of the cargo doors, analysis of the payload, and analysis of the orbiter.

Space Shuttle Placement Announcement

NASA Image and Video Library

2011-04-12

The space shuttle Atlantis is seen in the Orbiter Processing Facility at an event where NASA Administrator Charles Bolden announced where four space shuttle orbiters will be permanently displayed at the conclusion of the Space Shuttle Program, Tuesday, April 12, 2011, at Kennedy Space Center in Cape Canaveral, Fla. The four orbiters, Enterprise, which currently is on display at the Smithsonian's Steven F. Udvar-Hazy Center near Washington Dulles International Airport, will move to the Intrepid Sea, Air & Space Museum in New York, Discovery will move to Udvar-Hazy, Endeavour will be displayed at the California Science Center in Los Angeles and Atlantis, will be displayed at the Kennedy Space Center Visitor’s Complex. Photo Credit: (NASA/Bill Ingalls)

Shuttle Orbiter Active Thermal Control Subsystem design and flight experience

NASA Technical Reports Server (NTRS)

Bond, Timothy A.; Metcalf, Jordan L.; Asuncion, Carmelo

1991-01-01

The paper examines the design of the Space Shuttle Orbiter Active Thermal Control Subsystem (ATCS) constructed for providing the vehicle and payload cooling during all phases of a mission and during ground turnaround operations. The operation of the Shuttle ATCS and some of the problems encountered during the first 39 flights of the Shuttle program are described, with special attention given to the major problems encountered with the degradation of the Freon flow rate on the Orbiter Columbia, the Flash Evaporator Subsystem mission anomalies which occurred on STS-26 and STS-34, and problems encountered with the Ammonia Boiler Subsystem. The causes and the resolutions of these problems are discussed.

KSC-95PC-1324

NASA Image and Video Library

1995-09-11

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, the Russian-built Docking Module is lowered for installation into the payload bay of the space shuttle Atlantis while it is in bay 2 of the Orbiter Processing Facility. The module will fly as a primary payload on the second Space Shuttle/Mir space station docking mission, STS-74. During the mission, the module will first be attached with the orbiter's robot arm to the Orbiter Docking System in the payload bay of the orbiter Atlantis and then be docked with the Mir. When Atlantis undocks from the Mir, it will leave the new docking module permanently attached to the space station for use during future shuttle Mir docking missions. The new module will simplify future Shuttle linkups with Mir by improving orbiter clearances when it serves as a bridge between the two spacecraft. The white structures attached to the module's sides are solar panels that will be attached to the Mir after the conclusion of the STS-74 mission. Photo Credit: NASA

KSC-02pd1089

NASA Image and Video Library

2002-06-27

KENNEDY SPACE CENTER, FLA. - After opening remarks at a commissioning ceremony for the new Convoy Command Vehicle, Center Director Roy Bridges Jr. (right) gets ready to open the door for a tour of the vehicle. At left is United Space Alliance Chief Operating Officer Mike McCulley. The new 40-foot vehicle is replacing a 15-year old model, and will be used following Shuttle landings as the prime vehicle to control critical communications between the orbiter, the crew and the Launch Control Center, to monitor the health of the Shuttle Orbiter systems and to direct convoy operations at the Shuttle Landing Facility. Upgrades and high-tech features incorporated into the design and development of this vehicle make it more reliable and efficient for the convoy crew. Seating capacity was increased from 4 to 12, and video recorders and television monitors were added to provide the convoy team with the maximum amount of visual information

KSC-02pd1088

NASA Image and Video Library

2002-06-27

KENNEDY SPACE CENTER, FLA. -- During a commissioning ceremony for the new Convoy Command Vehicle (background), Tony Shibly, project manager, United Space Alliance, offers a few remarks to guests. At left are USA Chief Operating Officer Mike McCulley and Center Director Roy Bridges Jr. The new 40-foot vehicle is replacing a 15-year old model, and will be used following Shuttle landings as the prime vehicle to control critical communications between the orbiter, the crew and the Launch Control Center, to monitor the health of the Shuttle Orbiter systems and to direct convoy operations at the Shuttle Landing Facility. Upgrades and high-tech features incorporated into the design and development of this vehicle make it more reliable and efficient for the convoy crew. Seating capacity was increased from 4 to 12, and video recorders and television monitors were added to provide the convoy team with the maximum amount of visual information

Space shuttle on-orbit flight control software requirements, preliminary version

NASA Technical Reports Server (NTRS)

1975-01-01

Software modules associated with various flight control functions for the space shuttle orbiter are described. Data flow, interface requirements, initialization requirements and module sequencing requirements are considered. Block diagrams and tables are included.

Analyses of shuttle orbiter approach and landing conditions

NASA Technical Reports Server (NTRS)

Teper, G. L.; Dimarco, R. J.; Ashkenas, I. L.; Hoh, R. H.

1981-01-01

A study of one shuttle orbiter approach and landing conditions are summarized. Causes of observed PIO like flight deficiencies are identified and potential cures are examined. Closed loop pilot/vehicle analyses are described and path/attitude stability boundaries defined. The latter novel technique proved of great value in delineating and illustrating the basic causes of this multiloop pilot control problem. The analytical results are shown to be consistent with flight test and fixed base simulation. Conclusions are drawn relating to possible improvements of the shuttle orbiter/digital flight control system.

Endeavour Grand Opening Ceremony

NASA Image and Video Library

2012-10-30

The space shuttle Endeavour is seen as workers prepare for the grand opening ceremony for the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, Tuesday, Oct. 30, 2012, in Los Angeles. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Photo Credit: (NASA/Bill Ingalls)

KENNEDY SPACE CENTER, FLA. -- NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (top) discusses the inner workings of Shuttle Atlantis in Orbiter Processing Facility Bay 1 with a United Space Alliance (USA) technician (bottom). NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

NASA Image and Video Library

2003-12-19

KENNEDY SPACE CENTER, FLA. -- NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (top) discusses the inner workings of Shuttle Atlantis in Orbiter Processing Facility Bay 1 with a United Space Alliance (USA) technician (bottom). NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

KENNEDY SPACE CENTER, FLA. -- NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (right) discusses a speed brake on Shuttle Discovery in Orbiter Processing Facility Bay 3 with a United Space Alliance (USA) technician (left). NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

NASA Image and Video Library

2003-12-19

KENNEDY SPACE CENTER, FLA. -- NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (right) discusses a speed brake on Shuttle Discovery in Orbiter Processing Facility Bay 3 with a United Space Alliance (USA) technician (left). NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

ARC-1980-AC80-0107-19

NASA Image and Video Library

1980-02-06

Space Shuttle Orbiter Enterprise mated to an external fuel tank and two solid rocket boosters on top of a Mobil Launcher Platform, undergoes fit and function checks at the launch site for the first Space Shuttle at Launch Complex 39's Pad A. The dummy Space Shuttle was assembled in the Vehicle Assembly Building and rolled out to the launch site on May 1 as part of an exercise to make certain shuttle elements are compatible with the Spaceport's assembly and launch facilities and ground support equipment, and help clear the way for the launch of the Space Shuttle Orbiter Columbia.

ARC-1980-AC80-0107-14

NASA Image and Video Library

1980-02-06

SPACE SHUTTLE ORBITER ENTERPRISE MATED TO AN EXTERNAL FUEL TANK AND TWO SOLID ROCKET BOOSTERS ON TOP OF A MOBIL LAUNCHER PLATFORM, UNDERGOES FIT AND FUNCTION CHECKS AT THE LAUNCH SITE FOR THE FIRST SPACE SHUTTLE AT LAUNCH COMPLEX 39'S PAD A. THE DUMMY SPACE SHUTTLE WAS ASSEMBLED IN THE VEHICLE ASSEMBLY BUILDING AND ROLLED OUT TO THE LAUNCH SITE ON MAY 1 AS PART OF AN EXERCISE TO MAKE CERTAIN SHUTTLE ELEMENTS ARE COMPATIBLE WITH THE SPACEPORT'S ASSEMBLY AND LAUNCH FACILITIES AND GROUND SUPPORT EQUIPMENT, AND HELP CLEAR THE WAY FOR THE LAUNCH OF THE SPACE SHUTTLE ORBITER COLUMBIA.

ARC-1980-AC80-0107-17

NASA Image and Video Library

1980-02-06

SPACE SHUTTLE ORBITER ENTERPRISE MATED TO AN EXTERNAL FUEL TANK AND TWO SOLID ROCKET BOOSTERS ON TOP OF A MOBIL LAUNCHER PLATFORM, UNDERGOES FIT AND FUNCTION CHECKS AT THE LAUNCH SITE FOR THE FIRST SPACE SHUTTLE AT LAUNCH COMPLEX 39'S PAD A. THE DUMMY SPACE SHUTTLE WAS ASSEMBLED IN THE VEHICLE ASSEMBLY BUILDING AND ROLLED OUT TO THE LAUNCH SITE ON MAY 1 AS PART OF AN EXERCISE TO MAKE CERTAIN SHUTTLE ELEMENTS ARE COMPATIBLE WITH THE SPACEPORT'S ASSEMBLY AND LAUNCH FACILITIES AND GROUND SUPPORT EQUIPMENT, AND HELP CLEAR THE WAY FOR THE LAUNCH OF THE SPACE SHUTTLE ORBITER COLUMBIA.

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

Spectators watch space shuttle Endeavour as it passes by on its way to its new home at the California Science Center in Los Angeles, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Carla Cioffi)

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

The space shuttle Endeavour is seen as it traverses through the streest of Los Angeles on its way to its new home at the California Science Center, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Carla Cioffi)

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

Spectators are seen as they watch space shuttle Endeavour as it passes by on its way to its new home at the California Science Center in Los Angeles, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Carla Cioffi)

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

A spectator photographs the space shuttle Endeavour as it passes by on its way to its new home at the California Science Center in Los Angeles, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Carla Cioffi)

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

A spectator is seen photographing the space shuttle Endeavour as it is moved to its new home at the California Science Center in Los Angeles, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC’s Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Bill Ingalls)

Endeavour Lands at LAX

NASA Image and Video Library

2012-09-21

Space shuttle Endeavour, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) performs a low flyby past the tower at Los Angeles International Airport, Friday, Sept. 21, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers.Photo Credit: (NASA/Bill Ingalls)

Endeavour Lands at LAX

NASA Image and Video Library

2012-09-21

Space shuttle Endeavour, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) performs a flyby of the Theme Building at Los Angeles International Airport, Friday, Sept. 21, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers.Photo Credit: (NASA/Scott Andrews)

Early Program Development

NASA Image and Video Library

1970-01-01

This 1970 artist's concept shows a Nuclear Shuttle in flight. As envisioned by Marshall Space Flight Center Program Development engineers, the Nuclear Shuttle would deliver payloads to lunar orbit or other destinations then return to Earth orbit for refueling and additional missions.

Results of an investigation of hypersonic viscous interaction effects of the space shuttle orbiter using a 0.010 scale model (51-0) in the AEDC-VKF tunnel F (OA160)

NASA Technical Reports Server (NTRS)

Elder, D. J.

1975-01-01

An experimental aerodynamic investigation was conducted in the AEDC-VKF Hypervelocity Wind Tunnel (Tunnel F) at a nomial Mach number of 19 to determine hypersonic viscous interaction effects on the space shuttle orbiter. The tests were conducted at an angle of attack of 30 degrees over a free-stream Reynolds number (based on fuselage length) variation from 0.1 to 0.4 million. Viscous interaction parameter was varied from 0.02 to 0.06. Six component static stability force and moment data were measured by an internally compensated internal strain gage balance. Resulting data are presented.

Space shuttle: Static stability and control investigation of NR/GD delta wing booster (B-20) and delta wing orbiter (134D), volume 1

NASA Technical Reports Server (NTRS)

Allen, E. C.; Eder, F. W.

1972-01-01

Experimental aerodynamic investigations have been made on a .0035 scale model North American Rockwell/General Dynamics version of the space shuttle. Static stability and control data were obtained on the delta wing booster alone (B-20) and with the delta wing orbiter (134D) mounted in various positions on the booster. Six component aerodynamic force and moment data were recorded over an angle of attack range from -10 deg to 24 deg at 0 deg and 6 deg sideslip angles and from -10 deg to +10 deg sideslip at 0 deg angle of attack. Mach number ranged from 0.6 to 4.96.

Supersonic and hypersonic aerodynamic characteristics of two shuttle-orbiter configurations designed for reduced length

NASA Technical Reports Server (NTRS)

Stone, H. W.

1974-01-01

Performance, stability, and control tests at supersonic and hypersonic speeds have been performed on two versions of a shuttle orbiter configuration designed for reduced length. One of the test configurations had twin dorsal fins rolled out 15 deg the other a centerline single dorsal fin. Effects of elevon and body deg flap deflection, rudder flare, planform fillet, and aileron deflection were examined. The supersonic tests were over the Mach number range from 1.6 to 4.63 at a Reynolds number based on model length of 4,300,000. The hypersonic tests were conducted at a Mach number of 10.3 and Reynolds number of 670,000.

Space power distribution system technology. Volume 1: Reference EPS design

NASA Technical Reports Server (NTRS)

Decker, D. K.; Cannady, M. D.; Cassinelli, J. E.; Farber, B. F.; Lurie, C.; Fleck, G. W.; Lepisto, J. W.; Massner, A.; Ritterman, P. F.

1983-01-01

The multihundred kilowatt electrical power aspects of a mannable space platform in low Earth orbit is analyzed from a cost and technology viewpoint. At the projected orbital altitudes, Shuttle launch and servicing are technically and economically viable. Power generation is specified as photovoltaic consistent with projected planning. The cost models and trades are based upon a zero interest rate (the government taxes concurrently as required), constant dollars (1980), and costs derived in the first half of 1980. Space platform utilization of up to 30 years is evaluated to fully understand the impact of resupply and replacement as satellite missions are extended. Such lifetimes are potentially realizable with Shuttle servicing capability and are economically desirable.

KSC-03PD-1065

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employees (from left) Harrell Watts, Lynn Wozniak, and Jason Levandusky install Thermal Protection System tiles on a main landing gear door of Space Shuttle orbiter Enterprise (OV-101). Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight. After the tile installation is complete, the sections will be transferred to the Southwest Research Institute for testing requested by the Columbia Accident Investigation Board.

KSC-03pd1065

NASA Image and Video Library

2003-04-11

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employees (from left) Harrell Watts, Lynn Wozniak, and Jason Levandusky install Thermal Protection System tiles on a main landing gear door of Space Shuttle orbiter Enterprise (OV-101). Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight. After the tile installation is complete, the sections will be transferred to the Southwest Research Institute for testing requested by the Columbia Accident Investigation Board.

KSC-03PD-1086

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employees (from left) Harrell Watts, Mike Cote, and Jason Levandusky install Thermal Protection System tiles on a main landing gear door of Space Shuttle orbiter Enterprise (OV-101). Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight. After the tile installation is complete, the sections will be transferred to the Southwest Research Institute for testing requested by the Columbia Accident Investigation Board.

Shuttle Endeavour Mated to 747 SCA Taxi to Runway for Delivery to Kennedy Space Center, Florida

NASA Image and Video Library

1991-05-02

NASA's 747 Shuttle Carrier Aircraft No. 911, with the space shuttle orbiter Endeavour securely mounted atop its fuselage, taxies to the runway to begin the ferry flight from Rockwell's Plant 42 at Palmdale, California, where the orbiter was built, to the Kennedy Space Center, Florida. At Kennedy, the space vehicle was processed and launched on orbital mission STS-49, which landed at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, 16 May 1992. NASA 911, the second modified 747 that went into service in November 1990, has special support struts atop the fuselage and internal strengthening to accommodate the added weight of the orbiters.

KSC-03PD-1080

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employees (from left) John Kuhn, Mike Cote, and Tom Baggitt discuss the installation of Thermal Protection System tiles on a main landing gear door of Space Shuttle orbiter Enterprise (OV-101). Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight. After the tile installation is complete, the sections will be transferred to the Southwest Research Institute for testing requested by the Columbia Accident Investigation Board.

KSC-03PD-1085

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employees (from left) Mike Cote, Tom Baggitt, and Jason Levandusky install Thermal Protection System tiles on a main landing gear door of Space Shuttle orbiter Enterprise (OV-101). Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight. After the tile installation is complete, the sections will be transferred to the Southwest Research Institute for testing requested by the Columbia Accident Investigation Board.

KSC-03PD-1084

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employee Dave Sanborn (left) conducts a bond verification test on Thermal Protection System tiles installed on a main landing gear door of Space Shuttle orbiter Enterprise (OV-101). Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight. After the tile installation is complete, the sections will be transferred to the Southwest Research Institute for testing requested by the Columbia Accident Investigation Board.

Space shuttle abort separation pressure investigation. Volume 1, Part A: Booster data at Mach 5

NASA Technical Reports Server (NTRS)

Trimmer, L. L.; Love, D. A.; Rampy, J. M.; Decker, J. P.; Blackwell, K. L.; Strike, W. T.

1972-01-01

Pressure data obtained from a joint Langley Research Center (LaRC)/Marshall Space Flight Center (MSFC) Space Shuttle about stage separation wind tunnel test are presented. The .00556 scale models of the McDonnell-Douglas orbiter and booster configurations were tested in proximity in Tunnel A of the Von Karman Facility (VKF), Arnold Engineering Development Center (AEDC). Mach numbers were 5.0, 3.0, and 2.0 and nominal Reynolds numbers were 1.09, 1.60, and 1.74 million per foot, respectively. Pressure data were obtained for the booster upper surface and orbiter lower surface at angles of attack of -10 deg, -5, 0, 5, and 10 deg for zero degrees sideslip. The models were tested at incidence angles of 0 and 5 deg for several separation distances and power conditions. Plug nozzles utilizing air were used to simulate booster and orbiter plumes at various altitudes along a nominal ascent trajectory. Powered conditions were 100, 50, and 0 percent of full power for the orbiter and 100, 50 and 0 percent of full power for the booster. Data were also obtained with the booster canard off in close proximity.

Geostationary platform systems concepts definition study. Volume 2: Technical, book 2

NASA Technical Reports Server (NTRS)

1980-01-01

A selected concept for a geostationary platform is defined in sufficient detail to identify requirements for supporting research and technology, space demonstrations, GFE interfaces, costs, and schedules. This system consists of six platforms in geostationary orbit (GEO) over the Western Hemisphere and six over the Atlantic, to satisfy the total payload set associated with the nominal traffic model. Each platform is delivered to low Earth orbit (LEO) in a single shuttle flight, already mated to its LEO to GEO transfer vehicle and ready for deployment and transfer to GEO. An alternative concept is looked at briefly for comparison of configuration and technology requirements. This alternative consists of two large platforms, one over the Western Hemisphere consisting of three docked modules, and one over the Atlantic (two docked modules), to satisfy a high traffic model. The modules are full length orbiter cargo bay payloads, mated at LEO to orbital transfer vehicles (OTVs) delivered in other shuttle flights, for transfer to GEO, rendezvous, and docking. A preliminary feasibility study of an experimental platform is also performed to demonstrate communications and platform technologies required for the operational platforms of the 1990s.

Experimental Space Shuttle Orbiter Studies to Acquire Data for Code and Flight Heating Model Validation

NASA Technical Reports Server (NTRS)

Wadhams, T. P.; Holden, M. S.; MacLean, M. G.; Campbell, Charles

2010-01-01

In an experimental study to obtain detailed heating data over the Space Shuttle Orbiter, CUBRC has completed an extensive matrix of experiments using three distinct models and two unique hypervelocity wind tunnel facilities. This detailed data will be employed to assess heating augmentation due to boundary layer transition on the Orbiter wing leading edge and wind side acreage with comparisons to computational methods and flight data obtained during the Orbiter Entry Boundary Layer Flight Experiment and HYTHIRM during STS-119 reentry. These comparisons will facilitate critical updates to be made to the engineering tools employed to make assessments about natural and tripped boundary layer transition during Orbiter reentry. To achieve the goals of this study data was obtained over a range of Mach numbers from 10 to 18, with flight scaled Reynolds numbers and model attitudes representing key points on the Orbiter reentry trajectory. The first of these studies were performed as an integral part of Return to Flight activities following the accident that occurred during the reentry of the Space Shuttle Columbia (STS-107) in February of 2003. This accident was caused by debris, which originated from the foam covering the external tank bipod fitting ramps, striking and damaging critical wing leading edge heating tiles that reside in the Orbiter bow shock/wing interaction region. During investigation of the accident aeroheating team members discovered that only a limited amount of experimental wing leading edge data existed in this critical peak heating area and a need arose to acquire a detailed dataset of heating in this region. This new dataset was acquired in three phases consisting of a risk mitigation phase employing a 1.8% scale Orbiter model with special temperature sensitive paint covering the wing leading edge, a 0.9% scale Orbiter model with high resolution thin-film instrumentation in the span direction, and the primary 1.8% scale Orbiter model with detailed thin-film resolution in both the span and chord direction in the area of peak heating. Additional objectives of this first study included: obtaining natural or tripped turbulent wing leading edge heating levels, assessing the effectiveness of protuberances and cavities placed at specified locations on the orbiter over a range of Mach numbers and Reynolds numbers to evaluate and compare to existing engineering and computational tools, obtaining cavity floor heating to aid in the verification of cavity heating correlations, acquiring control surface deflection heating data on both the main body flap and elevons, and obtain high speed schlieren videos of the interaction of the orbiter nose bow shock with the wing leading edge. To support these objectives, the stainless steel 1.8% scale orbiter model in addition to the sensors on the wing leading edge was instrumented down the windward centerline, over the wing acreage on the port side, and painted with temperature sensitive paint on the starboard side wing acreage. In all, the stainless steel 1.8% scale Orbiter model was instrumented with over three-hundred highly sensitive thin-film heating sensors, two-hundred of which were located in the wing leading edge shock interaction region. Further experimental studies will also be performed following the successful acquisition of flight data during the Orbiter Entry Boundary Layer Flight Experiment and HYTHIRM on STS-119 at specific data points simulating flight conditions and geometries. Additional instrumentation and a protuberance matching the layout present during the STS-119 boundary layer transition flight experiment were added with testing performed at Mach number and Reynolds number conditions simulating conditions experienced in flight. In addition to the experimental studies, CUBRC also performed a large amount of CFD analysis to confirm and validate not only the tunnel freestream conditions, but also 3D flows over the orbiter acreage, wing leading edge, and controlurfaces to assess data quality, shock interaction locations, and control surface separation regions. This analysis is a standard part of any experimental program at CUBRC, and this information was of key importance for post-test data quality analysis and understanding particular phenomena seen in the data. All work during this effort was sponsored and paid for by the NASA Space Shuttle Program Office at the Johnson Space Center in Houston, Texas.

Mathematical modeling of acute and chronic cardiovascular changes during Extended Duration Orbiter (EDO) flights

NASA Technical Reports Server (NTRS)

White, Ronald J.; Leonard, Joel I.; Srinivasan, R. Srini; Charles, John B.

1991-01-01

The purpose of NASA's Extended Duration Orbiter program is a gradual extension of the capabilities of the Space Shuttle Orbiter beyond its current 7-10 day limit on mission duration, as warranted by deepening understanding of the long-term physiological effects of weightlessness. Attention is being given to the cardiovascular problem of orthostatic tolerance loss due to its adverse effects on crew performance and health during reentry and initial readaptation to earth gravity. An account is given of the results of the application of proven mathematical models of circulatory and cardiovascular systems under microgravity conditions.

Orbital Debris Research in the United States

NASA Technical Reports Server (NTRS)

Stansbery, Gene

2009-01-01

The presentation includes information about growth of the satellite population, the U.S. Space Surveillance Network, tracking and catalog maintenance, Haystack and HAX radar observation, Goldstone radar, the Michigan Orbital Debris Survey Telescope (MODEST), spacecraft surface examinations and sample of space shuttle impacts. GEO/LEO observations from Kwajalein Atoll, NASA s Orbital Debris Engineering Model (ORDEM2008), a LEO-to-GEO Environment Debris Model (LEGEND), Debris Assessment Software (DAS) 2.0, the NASA/JSC BUMPER-II meteoroid/debris threat assessment code, satellite reentry risk assessment, optical size and shape determination, work on more complicated fragments, and spectral studies.

STS-51 Space Shuttle Mission Report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1993-01-01

The STS-51 Space Shuttle Program Mission Report summarizes the payloads as well as the orbiter, external tank (ET), solid rocket booster (SRB), redesigned solid rocket motor (RSRM), and the space shuttle main engine (SSME) systems performance during the fifty-seventh flight of the space shuttle program and seventeenth flight of the orbiter vehicle Discovery (OV-103). In addition to the orbiter, the flight vehicle consisted of an ET designated as ET-59; three SSME's, which were designated as serial numbers 2031, 2034, and 2029 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-060. The lightweight RSRM's that were installed in each SRB were designated as 360W033A for the left SRB and 360L033B for the right SRB.

STS-60 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1994-01-01

The STS-60 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixtieth flight of the Space Shuttle Program and eighteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET designated at ET-61 (Block 10); three SSME's which were designated as serial numbers 2012, 2034, and 2032 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-062. The RSRM's that were installed in each SRB were designated as 360L035A (lightweight) for the left SRB, and 360Q035B (quarterweight) for the right SRB. This STS-60 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume VIII, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of the STS-60 mission were to deploy and retrieve the Wake Shield Facility-1 (WSF-1), and to activate the Spacehab-2 payload and perform on-orbit experiments. Secondary objectives of this flight were to activate and command the Capillary Pumped Loop/Orbital Debris Radar Calibration Spheres/Breman Satellite Experiment/Getaway Special (GAS) Bridge Assembly (CAPL/ODERACS/BREMSAT/GBA) payload, the Auroral Photography Experiment-B (APE-B), and the Shuttle Amateur Radio Experiment-II (SAREX-II).

Crew appliance concepts. Volume 3, appendix B: Shuttle orbiter appliances supporting engineering data

NASA Technical Reports Server (NTRS)

Proctor, B. W.; Reysa, R. P.; Russell, D. J.

1975-01-01

Technical data collected for housekeeping, off-duty activities, and medical appliances considered for the shuttle orbiter are presented. Equipment cleaning, refuse management, garment/linen maintenance, entertainment, physical conditioning, sterilization, and physical monitoring were analyzed.

Endeavour Grand Opening Ceremony

NASA Image and Video Library

2012-10-30

California Governor Jerry Brown speaks from a podium underneath the space shuttle Endeavour during the grand opening ceremony for the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, Tuesday, Oct. 30, 2012, in Los Angeles. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Photo Credit: (NASA/Bill Ingalls)

Endeavour Grand Opening Ceremony

NASA Image and Video Library

2012-10-30

A police officer is seen underneath the wing of the space shuttle Endeavour during the grand opening ceremony for the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, Tuesday, Oct. 30, 2012, in Los Angeles. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Photo Credit: (NASA/Bill Ingalls)

STS-41D Mission Insignia

NASA Technical Reports Server (NTRS)

1984-01-01

The official mission insignia for the 41-D Space Shuttle flight features the Discovery - NASA's third orbital vehicle - as it makes its maiden voyage. The ghost ship represents the orbiter's namesakes which have figured prominently in the history of exploration. The Space Shuttle Discovery heads for new horizons to extend that proud tradition. Surnames for the crewmembers of NASA's eleventh Space Shuttle mission encircle the red, white, and blue scene.

KSC-05PD-0625

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Technicians photograph the exterior of Space Shuttle Discovery on its journey to Launch Pad 39B to support the Baseline Configuration Imaging (BCI) project. BCI will be collected on each orbiter prior to every mission, beginning with STS-114. The photos will be compiled into a database available for comparison, if the need arises, to photos taken on orbit from the Shuttle's Orbital Boom Sensor System (OBSS). The 50-foot-long OBSS attaches to the Remote Manipulator System, or Shuttle robotic arm, and is one of the new safety measures for Return to Flight, equipping the orbiter with cameras and laser systems to inspect the Shuttles Thermal Protection System while in space. Discovery was hard down on the pad at 1:16 a.m. EDT April 7. Launch of Discovery on its Return to Flight mission, STS-114, is targeted for May 15 with a launch window that extends to June 3. During its 12-day mission, Discoverys seven-member crew will test new hardware and techniques to improve Shuttle safety, as well as deliver supplies to the International Space Station.

KSC-05PD-0624

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Technicians photograph the exterior of Space Shuttle Discovery on its journey to Launch Pad 39B to support the Baseline Configuration Imaging (BCI) project. BCI will be collected on each orbiter prior to every mission, beginning with STS-114. The photos will be compiled into a database available for comparison, if the need arises, to photos taken on orbit from the Shuttle's Orbital Boom Sensor System (OBSS). The 50-foot-long OBSS attaches to the Remote Manipulator System, or Shuttle robotic arm, and is one of the new safety measures for Return to Flight, equipping the orbiter with cameras and laser systems to inspect the Shuttles Thermal Protection System while in space. Discovery was hard down on the pad at 1:16 a.m. EDT April 7. Launch of Discovery on its Return to Flight mission, STS-114, is targeted for May 15 with a launch window that extends to June 3. During its 12-day mission, Discoverys seven-member crew will test new hardware and techniques to improve Shuttle safety, as well as deliver supplies to the International Space Station.

KSC-2011-2867

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- Standing proudly in front of shuttle Atlantis' three main engines are, from left, STS-1 Pilot and former Kennedy Space Center Director Bob Crippen, NASA Administrator Charles Bolden, NASA Astronaut and Director of Flight Crew Operations Janet Kavandi, Kennedy Center Director Bob Cabana and Mike Parrish, space shuttle Endeavour's vehicle manager with United Space Alliance. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

Atmospheric turbulence simulation for Shuttle orbiter

NASA Technical Reports Server (NTRS)

Tatom, F. B.; Smith, S. R.

1979-01-01

An improved non-recursive model for atmospheric turbulence along the flight path of the Shuttle Orbiter is developed which provides for simulation of instantaneous vertical and horizontal gusts at the vehicle center-of-gravity, and also for simulation of instantaneous gust gradients. Based on this model the time series for both gusts and gust gradients are generated and stored on a series of magnetic tapes. Section 2 provides a description of the various technical considerations associated with the turbulence simulation model. Included in this section are descriptions of the digital filter simulation model, the von Karman spectra with finite upper limits, and the final non recursive turbulence simulation model which was used to generate the time series. Section 2 provides a description of the various technical considerations associated with the turbulence simulation model. Included in this section are descriptions of the digial filter simulation model, the von Karman spectra with finite upper limits, and the final non recursive turbulence simulation model which was used to generate the time series. Section 3 provides a description of the time series as currently recorded on magnetic tape. Conclusions and recommendations are presented in Section 4.

Space shuttle orbiter avionics software: Post review report for the entry FACI (First Article Configuration Inspection). [including orbital flight tests integrated system

NASA Technical Reports Server (NTRS)

Markos, H.

1978-01-01

Status of the computer programs dealing with space shuttle orbiter avionics is reported. Specific topics covered include: delivery status; SSW software; SM software; DL software; GNC software; level 3/4 testing; level 5 testing; performance analysis, SDL readiness for entry first article configuration inspection; and verification assessment.

HP-9810A calculator programs for plotting the 2-dimensional motion of cyclindrical payloads relative to the shuttle orbiter

NASA Technical Reports Server (NTRS)

Wilson, S. W.

1976-01-01

The HP-9810A calculator programs described provide the capability to generate HP-9862A plotter displays which depict the apparent motion of a free-flying cyclindrical payload relative to the shuttle orbiter body axes by projecting the payload geometry into the orbiter plane of symmetry at regular time intervals.

Internet Based Simulations of Debris Dispersion of Shuttle Launch

NASA Technical Reports Server (NTRS)

Bardina, Jorge; Thirumalainambi, Rajkumar

2004-01-01

The debris dispersion model (which dispersion model?) is so heterogeneous and interrelated with various factors, 3D graphics combined with physical models are useful in understanding the complexity of launch and range operations. Modeling and simulation in this area mainly focuses on orbital dynamics and range safety concepts, including destruct limits, telemetry and tracking, and population risk. Particle explosion modeling is the process of simulating an explosion by breaking the rocket into many pieces. The particles are scattered throughout their motion using the laws of physics eventually coming to rest. The size of the foot print explains the type of explosion and distribution of the particles. The shuttle launch and range operations in this paper are discussed based on the operations of the Kennedy Space Center, Florida, USA. Java 3D graphics provides geometric and visual content with suitable modeling behaviors of Shuttle launches.

KENNEDY SPACE CENTER, FLA. - This bird's-eye view of a high bay in the Orbiter Processing Facility (OPF) shows Space Shuttle Atlantis surrounded by the standard platforms and equipment required to process a Space Shuttle orbiter for flight. The high bay is 197 feet (60 meters) long, 150 feet (46 meters) wide, 95 feet (29 meters) high, and encompasses a 29,000-square-foot (2,694-meter) area. Platforms, a main access bridge, and two rolling bridges with trucks provide access to various parts of the orbiter. The next mission scheduled for Atlantis is STS-114, a utilization and logistics flight to the International Space Station.

NASA Image and Video Library

2003-09-03

KENNEDY SPACE CENTER, FLA. - This bird's-eye view of a high bay in the Orbiter Processing Facility (OPF) shows Space Shuttle Atlantis surrounded by the standard platforms and equipment required to process a Space Shuttle orbiter for flight. The high bay is 197 feet (60 meters) long, 150 feet (46 meters) wide, 95 feet (29 meters) high, and encompasses a 29,000-square-foot (2,694-meter) area. Platforms, a main access bridge, and two rolling bridges with trucks provide access to various parts of the orbiter. The next mission scheduled for Atlantis is STS-114, a utilization and logistics flight to the International Space Station.

Results of tests OA12 and IA9 in the Ames Research Center unitary plan wind tunnels on an 0.030-scale model of the space shuttle vehicle 2A to determine aerodynamic loads, volume 1

NASA Technical Reports Server (NTRS)

Spangler, R. H.

1973-01-01

Tests were conducted in unitary plan wind tunnels on an 0.030-scale replica of the space shuttle vehicle configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration and tests on the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from minus 8 deg to plus 8 deg. The isolated orbiter was tested at angles of attack from minus 15 deg to plus 40 deg and angles of sideslip from minus 10 deg to plus 10 deg are dictated by trajectory considerations. The effects of orbiter/external tank incidence and deflected control surfaces on aerodynamic loads were also investigated.

Effects of reaction control system jet simulation on the stability and control characteristics of a 0.015 scale space shuttle orbiter model tested in the Langley Research Center unitary plan wind tunnel

NASA Technical Reports Server (NTRS)

Daileda, J. J.; Marroquin, J.

1974-01-01

An experimental investigation was performed in the Langley Research Center Unitary Plan Wind Tunnel (Test 0A70) to obtain the detailed effects that RCS jet flow interactions with local orbiter flow field have on supersonic stability and control characteristics of the space shuttle orbiter. Six-component force data were obtained through an angle-of-attack range from 15 to 35 degrees at angles of sideslip of 0, +5, and -5 degrees. The test was conducted with yaw jet simulation at free-stream Mach numbers of 2.5 and 4.6, simulating SSV re-entry flight conditions at these Mach numbers. In addition to the basic force measurements, fuselage base pressures and pressures on the non-metric RCS pods were obtained.

Results of tests OA12 and IA9 in the Ames Research Center unitary plan wind tunnels on an 0.030 scale model of the space shuttle vehicle 2A to determine aerodynamic loads, volume 7

NASA Technical Reports Server (NTRS)

Spangler, R. H.

1973-01-01

Tests were conducted in wind tunnels during April and May 1973, on an 0.030-scale replica of the Space Shuttle Vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration and on the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from -8 deg. The isolated orbiter was tested at angles of attack from -15 deg to +40 deg and angles of sideslip from -10 deg to +10 deg as dictated by trajectory considerations. The effects of orbiter/external tank incidence angle and deflected control surfaces on aerodynamic loads were also investigated.

Space shuttle orbiter rear mounted reaction control system jet interaction study. [hypersonic wind tunnel tests

NASA Technical Reports Server (NTRS)

Rausch, J. R.

1977-01-01

The effect of interaction between the reaction control system (RCS) jets and the flow over the space shuttle orbiter in the atmosphere was investigated in the NASA Langley 31-inch continuous flow hypersonic tunnel at a nominal Mach number of 10.3 and in the AEDC continuous flow hypersonic tunnel B at a nominal Mach number of 6, using 0.01 and .0125 scale force models with aft RCS nozzles mounted both on the model and on the sting of the force model balance. The data show that RCS nozzle exit momentum ratio is the primary correlating parameter for effects where the plume impinges on an adjacent surface and mass flow ratio is the parameter when the plume interaction is primarily with the external stream. An analytic model of aft mounted RCS units was developed in which the total reaction control moments are the sum of thrust, impingement, interaction, and cross-coupling terms.

A low speed wind tunnel test of a 0.050 scale model of shuttle orbiter (model 089B) to investigate the longitudinal and lateral directional effects of canard and tail configurational modifications in the LTV LSWT (MA14)

NASA Technical Reports Server (NTRS)

Chambliss, E. B.

1976-01-01

A low speed wind tunnel test was conducted to determine the effects of 6 canard configurations on the 0.050 scale model of shuttle orbiter 089B. In addition, two horizontal tail configurations were tested at two positions on the model as were two wing configurations. Since this test was restricted to 103 runs, only a limited number of permutations of the configurational changes could be tested. The testing was done in the 15 by 20 foot section of the LSWT and consisted of pitch polars, one yawed polar and several yaw runs. The pitch polars encompassed an alpha range from 0 to 28 deg; the yawed polar was run at beta = +2 degrees and the yaw runs covered a beta range from -6 to +6 deg at angles-of-attack of 0, 4, 10, 16, and 20 deg.

Space shuttle: Aerodynamic stability, control effectiveness and drag characteristics of a shuttle orbiter configuration at Mach numbers from 0.6 to 4.96

NASA Technical Reports Server (NTRS)

Ramsey, P. E.

1972-01-01

Experimental aerodynamic investigations were conducted in the NASA/MSFC 14-inch Trisonic Wind Tunnel from Sept. 27 to Oct. 7, 1972 on a 0.004 scale model of the NR ATP baseline shuttle orbiter configuration. Six component aerodynamic force and moment data were recorded at 0 deg sideslip angle over an angle of attack range from 0 to 20 deg for Mach numbers of 0.6 to 4.96, 20 to 40 deg for Mach numbers of 0.6, 0.9, 2.99, and 4.96, and 40 to 60 deg for Mach numbers of 2.99 and 4.96. Data were obtained over a sideslip range of -10 to 10 deg at 0, 10, and 20 deg angles of attack over the Mach range and 30 and 50 deg at Mach numbers of 2.99 and 4.96. The purpose of the test was to define the buildup, performance, stability, and control characteristics of the orbiter configuration. The model parameters, were: body alone; body-wing; body-wing-tail; elevon deflections of 0, 10, -20, and -40 deg both full and split); aileron deflections of plus or minus 10 deg (full and split); rudder flares of 10 and 40 deg, and a rudder deflection of 15 deg about the 10 and 40 deg flare positions.

Generalized environmental control and life support system computer program (G189A) configuration control. [computer subroutine libraries for shuttle orbiter analyses

NASA Technical Reports Server (NTRS)

Blakely, R. L.

1973-01-01

A G189A simulation of the shuttle orbiter EC/lSS was prepared and used to study payload support capabilities. Two master program libraries of the G189A computer program were prepared for the NASA/JSC computer system. Several new component subroutines were added to the G189A program library and many existing subroutines were revised to improve their capabilities. A number of special analyses were performed in support of a NASA/JSC shuttle orbiter EC/LSS payload support capability study.

Mechanisms to deploy the two-stage IUS from the shuttle cargo bay

NASA Technical Reports Server (NTRS)

Haynie, H. T.

1980-01-01

The Inertial Upper Stage (IUS) is a two-stage or three-stage booster used to transport spacecraft from the space shuttle orbit to synchronous orbit or on an interplanetary trajectory. The mechanisms which were designed specifically to perform the two-stage IUS required functions while contained within the cargo bay of the space shuttle during the boost phase and while in a low Earth orbit are discussed. The requirements, configuration, and operation of the mechanisms are described, with particular emphasis on the tilt actuator and the mechanism for decoupling the actuators during boost to eliminate redundant load paths.

Analyses of Shuttle Orbiter approach and landing

NASA Technical Reports Server (NTRS)

Ashkenas, I. L.; Hoh, R. H.; Teper, G. L.

1982-01-01

A study of the Shuttle Orbiter approach and landing conditions is summarized. The causes of observed PIO-like flight deficiencies are listed, and possible corrective measures are examined. Closed-loop pilot/vehicle analyses are described, and a description is given of path-attitude stability boundaries. The latter novel approach is found to be of great value in delineating and illustrating the basic causes of this multiloop pilot control problem. It is shown that the analytical results are consistent with flight test and fixed-base simulation. Conclusions are drawn concerning possible improvements in the Shuttle Orbiter/Digital Flight Control System.

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility insert the liquid oxygen feedline for the 17-inch disconnect in the orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility insert the liquid oxygen feedline for the 17-inch disconnect in the orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers install the liquid oxygen feedline for the 17-inch disconnect on orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers install the liquid oxygen feedline for the 17-inch disconnect on orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers raise the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers raise the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers lift the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers lift the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers move the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers move the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

Space Operations Center - A concept analysis

NASA Technical Reports Server (NTRS)

1980-01-01

The Space Operations Center (SOC) which is a concept for a Shuttle serviced, permanent, manned facility in low earth orbit is viewed as a major candidate for the manned space flight following the completion of an operational Shuttle. The primary objectives of SOC are: (1) the construction, checkout, and transfer to operational orbit of large, complex space systems, (2) on-orbit assembly, launch, recovery, and servicing of manned and unmanned spacecraft, (3) managing operations of co-orbiting free-flying satellites, and (4) the development of reduced dependence on earth for control and resupply. The structure of SOC, a self-contained orbital facility containing several Shuttle launched modules, includes the service, habitation, and logistics modules as well as construction, and flight support facilities. A schedule is proposed for the development of SOC over ten years and costs for the yearly programs are estimated.

Space Shuttle processing - A case study in artificial intelligence

NASA Technical Reports Server (NTRS)

Mollikarimi, Cindy; Gargan, Robert; Zweben, Monte

1991-01-01

A scheduling system incorporating AI is described and applied to the automated processing of the Space Shuttle. The unique problem of addressing the temporal, resource, and orbiter-configuration requirements of shuttle processing is described with comparisons to traditional project management for manufacturing processes. The present scheduling system is developed to handle the late inputs and complex programs that characterize shuttle processing by incorporating fixed preemptive scheduling, constraint-based simulated annealing, and the characteristics of an 'anytime' algorithm. The Space-Shuttle processing environment is modeled with 500 activities broken down into 4000 subtasks and with 1600 temporal constraints, 8000 resource constraints, and 3900 state requirements. The algorithm is shown to scale to very large problems and maintain anytime characteristics suggesting that an automated scheduling process is achievable and potentially cost-effective.

Shuttle Hitchhiker Experiment Launcher System (SHELS)

NASA Technical Reports Server (NTRS)

Daelemans, Gerry

1999-01-01

NASA's Goddard Space Flight Center Shuttle Small Payloads Project (SSPP), in partnership with the United States Air Force and NASA's Explorer Program, is developing a Shuttle based launch system called SHELS (Shuttle Hitchhiker Experiment Launcher System), which shall be capable of launching up to a 400 pound spacecraft from the Shuttle cargo bay. SHELS consists of a Marman band clamp push-plate ejection system mounted to a launch structure; the launch structure is mounted to one Orbiter sidewall adapter beam. Avionics mounted to the adapter beam will interface with Orbiter electrical services and provide optional umbilical services and ejection circuitry. SHELS provides an array of manifesting possibilities to a wide range of satellites.

Space Shuttle Atlantis after its Final Landing

NASA Image and Video Library

2011-07-21

STS135-S-274 (21 July 2011) --- Space shuttle Atlantis is slowly towed from the Shuttle Landing Facility to an orbiter processing facility at NASA's Kennedy Space Center in Florida for the last time. Atlantis' final return from space at 5:57 a.m. (EDT) on July 21, 2011, secured the space shuttle fleet's place in history and brought a close to the America's Space Shuttle Program. STS-135 delivered spare parts, equipment and supplies to the International Space Station. STS-135 was the 33rd and final flight for Atlantis, which has spent 307 days in space, orbited Earth 4,848 times and traveled 125,935,769 miles. Photo credit: NASA

Space Shuttle Atlantis after its Final Landing

NASA Image and Video Library

2011-06-21

STS135-S-273 (21 July 2011) --- Space shuttle Atlantis is slowly towed from the Shuttle Landing Facility to an orbiter processing facility at NASA's Kennedy Space Center in Florida for the last time. Atlantis' final return from space at 5:57 a.m. (EDT) on July 21, 2011, secured the space shuttle fleet's place in history and brought a close to the America's Space Shuttle Program. STS-135 delivered spare parts, equipment and supplies to the International Space Station. STS-135 was the 33rd and final flight for Atlantis, which has spent 307 days in space, orbited Earth 4,848 times and traveled 125,935,769 miles. Photo credit: NASA

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

The driver of the Over Land Transporter is seen as he maneuvers the space shuttle Endeavour on the streets of Los Angeles as it heads to its new home at the California Science Center, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC’s Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Bill Ingalls)

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

The driver of the Over Land Transporter (OLT) is seen as he maneuvers the space shuttle Endeavour on the streets of Los Angeles as it heads to its new home at the California Science Center, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Carla Cioffi)

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

A spectator on the roof of a building photographs space shuttle Endeavour as it passes by on its way to its new home at the California Science Center in Los Angeles, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC’s Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Carla Cioffi)

Endeavour Lands at LAX

NASA Image and Video Library

2012-09-21

Space shuttle Endeavour, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) lands at Los Angeles International Airport, Friday, Sept. 21, 2012. The shadow of a NASA F-18 chase jet wing is shown in the foreground. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers.Photo Credit: (NASA/Bill Ingalls)

Space Shuttle Endeavour Move

NASA Image and Video Library

2012-10-12

The space shuttle Endeavour moves out of the Los Angeles International Airport and onto the streets of Los Angeles to make its way to its new home at the California Science Center, Friday, Oct. 12, 2012. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Beginning Oct. 30, the shuttle will be on display in the CSC's Samuel Oschin Space Shuttle Endeavour Display Pavilion, embarking on its new mission to commemorate past achievements in space and educate and inspire future generations of explorers. Photo Credit: (NASA/Carla Cioffi)

Space Shuttle Discovery DC Fly-Over

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA), flies over the Washington skyline as seen from a NASA T-38 aircraft, Tuesday, April 17, 2012. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Robert Markowitz)

Launch of space shuttle Challenger on the 41-C mission

NASA Image and Video Library

1984-04-06

41C-3029 (6 April 1984) --- The space shuttle Challenger and its five-member astronaut crew leave the launch pad at the Kennedy Space Center to begin a six-day stay in space. Astronaut John W. Young, a veteran of two shuttle missions and six spaceflights overall, recorded the image with a handheld 70mm camera from the shuttle training aircraft which he was using to monitor environmental conditions around Florida. This is the eighth mission on which Young photographed one of NASA's orbiter vehicles beginning its orbital stay. Photo credit: NASA

Space Shuttle Project

NASA Image and Video Library

1972-03-07

This early chart conceptualizes the use of two parallel Solid Rocket Motor Boosters in conjunction with three main engines to launch the proposed Space Shuttle to orbit. At approximately twenty-five miles altitude, the boosters would detach from the Orbiter and parachute back to Earth where they would be recovered and refurbished for future use. The Shuttle was designed as NASA's first reusable space vehicle, launching vertically like a spacecraft and landing on runways like conventional aircraft. Marshall Space Flight Center had management responsibility for the Shuttle's propulsion elements, including the Solid Rocket Boosters.

Experimental Design for the Evaluation of Detection Techniques of Hidden Corrosion Beneath the Thermal Protective System of the Space Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Kammerer, Catherine C.; Jacoby, Joseph A.; Lomness, Janice K.; Hintze, Paul E.; Russell, Richard W.

2007-01-01

The United States Space Operational Space Shuttle Fleet Consists of three shuttles with an average age of 19.7 years. Shuttles are exposed to corrosive conditions while undergoing final closeout for missions at the launch pad and extreme conditions during ascent, orbit, and descent that may accelerate the corrosion process. Structural corrosion under TPS could progress undetected (without tile removal) and eventually result in reduction in structural capability sufficient to create negative margins of . safety and ultimate loss of local structural capability.

Space Shuttle Discovery DC Fly-Over

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) flies near the U.S. Capitol, Tuesday, April 17, 2012, in Washington. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Michael Porterfield)

Shuttle Discovery Fly-Over

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) flies over the Steven F. Udvar-Hazy Center, Tuesday, April 17, 2012, in Washington. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Smithsonian Institution/Dane Penland)

Shuttle Discovery Is Demated From SCA

NASA Image and Video Library

2012-04-19

Workers monitor the lift of the space shuttle Discovery from the the NASA 747 Shuttle Carrier Aircraft (SCA) at Washington Dulles International Airport, Thursday, April 19, 2012, in Sterling, VA. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Bill Ingalls)

Space Shuttle Discovery DC Fly-Over

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) is seen as it flies near the U.S. Capitol, Tuesday, April 17, 2012, in Washington. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Smithsonian Institution/Harold Dorwin)

Shuttle Discovery Arrives at Udvar-Hazy

NASA Image and Video Library

2012-04-19

Space Shuttles Enterprise, left, and Discovery meet nose-to-nose during the a transfer ceremony at the Smithsonian's Steven F. Udvar-Hazy Center, Thursday, April 19, 2012, in Chantilly, Va. Space shuttle Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles will take the place of Enterprise at the center to commemorate past achievements in space and to educate and inspire future generations of explorers at the center. Photo Credit: (NASA/Carla Cioffi)

Space Shuttle Discovery Landing

NASA Image and Video Library

2012-04-17

Space Shuttle Discovery mounted atop a 747 Shuttle Carrier Aircraft (SCA) approaches the runway for landing at Washington Dulles International Airport, Tuesday April 17, 2012, in Sterling, Va. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Paul E. Alers)

Space Shuttle Discovery DC Fly-Over

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) flies over the Steven F. Udvar-Hazy Center, Tuesday, April 17, 2012, in Washington. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Robert Markowitz)

Space Shuttle Discovery Landing

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) taxis in front of the main terminal at Washington Dulles International Airport, Tuesday, April 17, 2012, in Sterling, Va. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Smithsonian Institution/Eric Long)

Shuttle Discovery Reagan Airport Fly-Over

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) makes its way past Ronald Reagan Washington National Airport, Tuesday, April 17, 2012, in Arlington, Va. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Bill Ingalls)

Space Shuttle Discovery Landing

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) lands at Washington Dulles International Airport, Tuesday, April 17, 2012, in Sterling, Va. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Smithsonian Institution/Eric Long)

Space Shuttle Discovery DC Fly-Over

NASA Image and Video Library

2012-04-16

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) flies near the U.S. Capitol, Tuesday, April 17, 2012, in Washington. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Rebecca Roth)

Space Shuttle Discovery Fly-By

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) flies over the Steven F. Udvar-Hazy Center, Tuesday, April 17, 2012, in Washington. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Smithsonian Institution/Eric Long)

Space Shuttle Discovery DC Fly-Over

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA) flies near the U.S. Capitol, Tuesday, April 17, 2012, in Washington. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Bill Ingalls)

The Shuttle Era

NASA Technical Reports Server (NTRS)

1981-01-01

An overview of the Space Shuttle Program is presented. The missions of the space shuttle orbiters, the boosters and main engine, and experimental equipment are described. Crew and passenger accommodations are discussed as well as the shuttle management teams.

The Ames-Lockheed orbiter processing scheduling system

NASA Technical Reports Server (NTRS)

Zweben, Monte; Gargan, Robert

1991-01-01

A general purpose scheduling system and its application to Space Shuttle Orbiter Processing at the Kennedy Space Center (KSC) are described. Orbiter processing entails all the inspection, testing, repair, and maintenance necessary to prepare the Shuttle for launch and takes place within the Orbiter Processing Facility (OPF) at KSC, the Vehicle Assembly Building (VAB), and on the launch pad. The problems are extremely combinatoric in that there are thousands of tasks, resources, and other temporal considerations that must be coordinated. Researchers are building a scheduling tool that they hope will be an integral part of automating the planning and scheduling process at KSC. The scheduling engine is domain independent and is also being applied to Space Shuttle cargo processing problems as well as wind tunnel scheduling problems.

KSC-03PD-1082

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, United Space Alliance employees (from left) Dave Sanborn, Butch Lato, and Bill Brooks conduct a bond verification test on Thermal Protection System tiles newly installed on a main landing gear door of Space Shuttle orbiter Enterprise (OV-101). Sections of Enterprise were borrowed from the Smithsonian Institution's Air and Space Museum where the orbiter is being stored at the Washington Dulles International Airport. Enterprise was the first orbiter built in the Shuttle fleet and was used to conduct the Approach and Landing Test Program before the first powered Shuttle flight. After the tile installation is complete, the sections will be transferred to the Southwest Research Institute for testing requested by the Columbia Accident Investigation Board.

Endeavour Grand Opening Ceremony

NASA Image and Video Library

2012-10-30

Vocalist James Ingram sings "I Believe I Can Fly" from underneath the space shuttle Endeavour during the grand opening ceremony for the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, Tuesday, Oct. 30, 2012, in Los Angeles. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Photo Credit: (NASA/Bill Ingalls)

Shuttle synthetic aperture radar implementation study, volume 1. [flight instrument and ground data processor system for collecting raw imaged radar data

NASA Technical Reports Server (NTRS)

Mehlis, J. G.

1976-01-01

Results of an implementation study for a synthetic aperture radar for the space shuttle orbiter are described. The overall effort was directed toward the determination of the feasibility and usefulness of a multifrequency, multipolarization imaging radar for the shuttle orbiter. The radar is intended for earth resource monitoring as well as oceanographic and marine studies.

Space Shuttle program orbital flight test program results and implications

NASA Technical Reports Server (NTRS)

Kohrs, R. H.

1982-01-01

The Space Shuttle System Orbital Flight Test (OFT) program results are described along with an overview of significant development issues and their resolution. In addition, an overall summary of the development status and the follow-on flight demonstrations of Shuttle improvements such as Lightweight External Tank, High Performance SRBs, Full Power Level (109%) Main Engine Operation, and the SRB Filament Wound Case (FWC) will be discussed.

KSC-2012-3327

NASA Image and Video Library

2012-06-12

CAPE CANAVERAL, Fla. – In Orbiter Processing Facility-1 at NASA’s Kennedy Space Center in Florida, an orbital maneuvering system, or OMS, pod is lifted from its transporter under the careful supervision of United Space Alliance technicians. The pod will be reinstalled on space shuttle Atlantis. The orbital maneuvering system provided the shuttle with thrust for orbit insertion, rendezvous and deorbit, and could provide up to 1,000 pounds of propellant to the aft reaction control system. The OMS is housed in two independent pods located on each side of the shuttle's aft fuselage. Each pod contains one OMS engine and the hardware needed to pressurize, store and distribute the propellants to perform the velocity maneuvers. Atlantis’ OMS pods were removed and sent to White Sands Test Facility in New Mexico to be cleaned of residual toxic propellant. The work is part of the Space Shuttle Program’s transition and retirement processing of the shuttle fleet. A groundbreaking was held Jan. 18 for Atlantis' future home, a 65,000-square-foot exhibit hall in Shuttle Plaza at the Kennedy Space Center Visitor Complex. Atlantis is scheduled to roll over to the visitor complex in November in preparation for the exhibit’s grand opening in July 2013. For more information, visit http://www.nasa.gov/transition. Photo credit: NASA/Kim Shiflett

Shuttle orbiter radar cross-sectional analysis

NASA Technical Reports Server (NTRS)

Cooper, D. W.; James, R.

1979-01-01

Theoretical and model simulation studies on signal to noise levels and shuttle radar cross section are described. Pre-mission system calibrations, system configuration, and postmission system calibration of the tracking radars are described. Conversion of target range, azimuth, and elevation into radar centered east north vertical position coordinates are evaluated. The location of the impinging rf energy with respect to the target vehicles body axis triad is calculated. Cross section correlation between the two radars is presented.

The role of the real-time simulation facility, SIMFAC, in the design, development and performance verification of the Shuttle Remote Manipulator System (SRMS) with man-in-the-loop

NASA Technical Reports Server (NTRS)

Mccllough, J. R.; Sharpe, A.; Doetsch, K. H.

1980-01-01

The SIMFAC has played a vital role in the design, development, and performance verification of the shuttle remote manipulator system (SRMS) to be installed in the space shuttle orbiter. The facility provides for realistic man-in-the-loop operation of the SRMS by an operator in the operator complex, a flightlike crew station patterned after the orbiter aft flight deck with all necessary man machine interface elements, including SRMS displays and controls and simulated out-of-the-window and CCTV scenes. The characteristics of the manipulator system, including arm and joint servo dynamics and control algorithms, are simulated by a comprehensive mathematical model within the simulation subsystem of the facility. Major studies carried out using SIMFAC include: SRMS parameter sensitivity evaluations; the development, evaluation, and verification of operating procedures; and malfunction simulation and analysis of malfunction performance. Among the most important and comprehensive man-in-the-loop simulations carried out to date on SIMFAC are those which support SRMS performance verification and certification when the SRMS is part of the integrated orbiter-manipulator system.

Rarefied flow past a flat plate at incidence

NASA Technical Reports Server (NTRS)

Dogra, Virendra K.; Moss, James N.; Price, Joseph M.

1988-01-01

Results of a numerical study using the direct simulation Monte Carlo (DSMC) method are presented for the transitional flow about a flat plate at 40 deg incidence. The plate has zero thickness and a length of 1.0 m. The flow conditions simulated are those experienced by the Shuttle Orbiter during reentry at 7.5 km/s. The range of freestream conditions are such that the freestream Knudsen number values are between 0.02 and 8.4, i.e., conditions that encompass most of the transitional flow regime. The DSMC simulations show that transitional effects are evident when compared with free molecule results for all cases considered. The calculated results demonstrate clearly the necessity of having a means of identifying the effects of transitional flow when making aerodynamic flight measurements as are currently being made with the Space Shuttle Orbiter vehicles. Previous flight data analyses have relied exclusively on adjustments in the gas-surface interaction models without accounting for the transitional effect which can be comparable in magnitude. The present calculations show that the transitional effect at 175 km would increase the Space Shuttle Orbiter lift-drag ratio by 90 percent over the free molecule value.

An axisymmetric analog two-layer convective heating procedure with application to the evaluation of Space Shuttle Orbiter wing leading edge and windward surface heating

NASA Technical Reports Server (NTRS)

Wang, K. C.

1994-01-01

A numerical procedure for predicting the convective heating rate of hypersonic reentry vehicles is described. The procedure, which is based on the axisymmetric analog, consists of obtaining the three-dimensional inviscid flowfield solution; then the surface streamlines and metrics are calculated using the inviscid velocity components on the surface; finally, an axisymmetric boundary layer code or approximate convective heating equations are used to evaluate heating rates. This approach yields heating predictions to general three-dimensional body shapes. The procedure has been applied to the prediction of the wing leading edge heating to the Space Shuttle Orbiter. The numerical results are compared with the results of heat transfer testing (OH66) of an 0.025 scale model of the Space Shuttle Orbiter configuration in the Calspan Hypersonic Shock Tunnel (HST) at Mach 10 and angles of attack of 30 and 40 degrees. Comparisons with STS-5 flight data at Mach 9.15 and angle of attack of 37.4 degrees and STS-2 flight data at Mach 12.86 and angle of attack of 39.7 degrees are also given.

NASA Contingency Shuttle Crew Support (CSCS) Medical Operations

NASA Technical Reports Server (NTRS)

Adams, Adrien

2010-01-01

The genesis of the space shuttle began in the 1930's when Eugene Sanger came up with the idea of a recyclable rocket plane that could carry a crew of people. The very first Shuttle to enter space was the Shuttle "Columbia" which launched on April 12 of 1981. Not only was "Columbia" the first Shuttle to be launched, but was also the first to utilize solid fuel rockets for U.S. manned flight. The primary objectives given to "Columbia" were to check out the overall Shuttle system, accomplish a safe ascent into orbit, and to return back to earth for a safe landing. Subsequent to its first flight Columbia flew 27 more missions but on February 1st, 2003 after a highly successful 16 day mission, the Columbia, STS-107 mission, ended in tragedy. With all Shuttle flight successes come failures such as the fatal in-flight accident of STS 107. As a result of the STS 107 accident, and other close-calls, the NASA Space Shuttle Program developed contingency procedures for a rescue mission by another Shuttle if an on-orbit repair was not possible. A rescue mission would be considered for a situation where a Shuttle and the crew were not in immediate danger, but, was unable to return to Earth or land safely. For Shuttle missions to the International Space Station (ISS), plans were developed so the Shuttle crew would remain on board ISS for an extended period of time until rescued by a "rescue" Shuttle. The damaged Shuttle would subsequently be de-orbited unmanned. During the period when the ISS Crew and Shuttle crew are on board simultaneously multiple issues would need to be worked including, but not limited to: crew diet, exercise, psychological support, workload, and ground contingency support

ACTS/TOS after release from Shuttle Discovery

NASA Technical Reports Server (NTRS)

1993-01-01

The Advanced Communications Technology Satellite (ACTS) with its Transfer Orbit Stage (TOS) is backdropped over the blue ocean following its release from the Earth-orbiting Space Shuttle Discovery. ACTS/TOS deploy was the first major task performed on the almost ten-day mission.

Design study of arresting gear system for recovery of space shuttle orbiters

NASA Technical Reports Server (NTRS)

1972-01-01

A plan is reported for the design, manufacture, development, test, and production of an emergency arrestment system for the recovery of shuttle orbiters. Time and cost estimates are included. System testing and several optional test programs are discussed.

KSC-04PD-2687

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. A shipping container transporting part of the new Orbiter Boom Sensor System (OBSS) is delivered by truck to the Remote Manipulator System lab in the Vehicle Assembly Building (VAB). Once the entire structure has arrived, the OBSS will be assembled and undergo final checkout and testing in the lab prior to being transferred to the Orbiter Processing Facility (OPF) for installation on Space Shuttle Discovery. The 50-foot-long OBSS will be attached to the Remote Manipulator System, or Shuttle arm, and is one of the new safety measures for Return to Flight, equipping the orbiter with cameras and laser systems to inspect the Shuttle's Thermal Protection System while in space. Discovery is slated to fly mission STS-114 once Space Shuttle launches resume. The launch planning window is May 12 to June 3, 2005.

STS-56 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1993-01-01

The STS-56 Space Shuttle Program Mission Report provides a summary of the Payloads, as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the fifty-fourth flight of the Space Shuttle Program and sixteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET (ET-54); three SSME's, which were designated as serial numbers 2024, 2033, and 2018 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-058. The lightweight RSRM's that were installed in each SRB were designated as 360L031A for the left SRB and 360L031B for the right SRB.

Reynolds number effects on hypersonic characteristics of a 0.010-scale model of the 139-B shuttle orbiter

NASA Technical Reports Server (NTRS)

Bernot, P. T.

1974-01-01

Longitudinal and lateral-directional stability characteristics of the 139-B orbiter (model 32-0) were obtained in a continuous flow hypersonic tunnel at Mach 10.3. Tests were made at Reynolds numbers of 1.04 million and 2.17 million (based on body length) over an angle of attack range of 12 deg to 36 deg at sideslip angles of 0 deg and minus 5 deg. Data were obtained at three elevon/body flap settings.

Results of investigations of an 0.010-scale 140A/B configuration (model 72-OTS) of the Rockwell International space shuttle orbiter in the NASA/Langley Research Center unitary plan wind tunnel

NASA Technical Reports Server (NTRS)

Petrozzi, M. T.; Milam, M. D.

1975-01-01

Experimental aerodynamic investigations were conducted in the NASA/Langley unitary plan wind tunnel on a sting mounted 0.010-scale outer mold line model of the 140A/B configuration of the Rockwell International Space Shuttle Vehicle. The primary test objectives were to obtain: (1) six component force and moment data for the mated vehicle at subsonic and transonic conditions, (2) effects of configuration build-up, (3) effects of protuberances, ET/orbiter fairings and attach structures, and (4) elevon deflection effects on wing bending moment. Six component aerodynamic force and moment data and base and balance cavity pressures were recorded over Mach numbers of 1.6, 2.0, 2.5, 2.86, 3.9, and 4.63 at a nominal Reynolds number of 20 to the 6th power per foot. Selected configurations were tested at angles of attack and sideslip from -10 deg to +10 deg. For all configurations involving the orbiter, wing bending, and torsion coefficients were measured on the right wing.

KENNEDY SPACE CENTER, FLA. -- From left, NASA Deputy Program Manager of the Space Shuttle Program Michael Wetmore, United Space Alliance (USA) Vice President and Space Shuttle Program Manager Howard DeCastro, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik, and a USA technician examine cold plates in Orbiter Processing Facility Bay 2. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

NASA Image and Video Library

2003-12-19

KENNEDY SPACE CENTER, FLA. -- From left, NASA Deputy Program Manager of the Space Shuttle Program Michael Wetmore, United Space Alliance (USA) Vice President and Space Shuttle Program Manager Howard DeCastro, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik, and a USA technician examine cold plates in Orbiter Processing Facility Bay 2. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

Instrument pointing system applicability and orbiter stabilization for EVAL missions. Application studies

NASA Technical Reports Server (NTRS)

Spector, V. A.

1977-01-01

Related aspect of the Earth Viewing Applications Laboratory (EVAL) shuttle missions were investigated. The applicability of the gimballed Instrument Pointing System (IPS) to EVAL missions by comparing the IPS capabilities with the EVAL requirements was evaluated, and a means of stabilizing the shuttle orbiter attitude in earth viewing orientations for prolonged periods without use of the orbiter gas reaction control system was assessed.

Shuttle Orbital Applications and Requirements, supplementary tasks (SOAR-IIS)

NASA Technical Reports Server (NTRS)

1973-01-01

Representative shuttle mission applications were studied. The interfaces analyses, and specific payloads are reported for the following types of missions: shuttle delivered automated spacecraft, shuttle/tug delivered spacecraft, man-tended automated spacecraft, and sortie missions.

The Space Shuttle Atlantis centered in the Mate-Demate Device (MDD) at NASA's Dryden Flight Research Center at Edwards, California

NASA Image and Video Library

2001-02-26

The Space Shuttle Atlantis is centered in the Mate-Demate Device (MDD) at NASA's Dryden Flight Research Center at Edwards, California. The gantry-like MDD structure is used for servicing the shuttle orbiters in preparation for their ferry flight back to the Kennedy Space Center in Florida, including mounting the shuttle atop NASA's modified Boeing 747 Shuttle Carrier Aircraft. Space Shuttle Atlantis landed at 12:33 p.m. February 20, 2001, on the runway at Edwards Air Force Base, California, where NASA's Dryden Flight Research Center is located. The mission, which began February 7, logged 5.3 million miles as the shuttle orbited earth while delivering the Destiny science laboratory to the International Space Station. Inclement weather conditions in Florida prompted the decision to land Atlantis at Edwards. The last time a space shuttle landed at Edwards was Oct. 24, 2000.

KENNEDY SPACE CENTER, FLA. -- NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (left) discusses some of the working parts inside the nose of Shuttle Discovery in Orbiter Processing Facility Bay 3 with a United Space Alliance (USA) technician (back to camera). NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

NASA Image and Video Library

2003-12-19

KENNEDY SPACE CENTER, FLA. -- NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (left) discusses some of the working parts inside the nose of Shuttle Discovery in Orbiter Processing Facility Bay 3 with a United Space Alliance (USA) technician (back to camera). NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

Lightning strikes in the distance as the Space Shuttle Discovery receives post-flight processing in the Mate-Demate Device, following its landing at NASA DFRC

NASA Image and Video Library

2005-08-14

Lightning strikes in the distance as the Space Shuttle Discovery receives post-flight processing in the Mate-Demate Device (MDD), following its landing at NASA's Dryden Flight Research Center in California. The gantry-like MDD structure is used for servicing the shuttle orbiters in preparation for their ferry flight back to the Kennedy Space Center in Florida, including mounting the shuttle atop NASA's modified Boeing 747 Shuttle Carrier Aircraft. Space Shuttle Discovery landed safely at NASA's Dryden Flight Research Center at Edwards Air Force Base in California at 5:11:22 a.m. PDT, August 9, 2005, following the very successful 14-day STS-114 return to flight mission. During their two weeks in space, Commander Eileen Collins and her six crewmates tested out new safety procedures and delivered supplies and equipment the International Space Station. Discovery spent two weeks in space, where the crew demonstrated new methods to inspect and repair the Shuttle in orbit. The crew also delivered supplies, outfitted and performed maintenance on the International Space Station. A number of these tasks were conducted during three spacewalks. In an unprecedented event, spacewalkers were called upon to remove protruding gap fillers from the heat shield on Discovery's underbelly. In other spacewalk activities, astronauts installed an external platform onto the Station's Quest Airlock and replaced one of the orbital outpost's Control Moment Gyroscopes. Inside the Station, the STS-114 crew conducted joint operations with the Expedition 11 crew. They unloaded fresh supplies from the Shuttle and the Raffaello Multi-Purpose Logistics Module. Before Discovery undocked, the crews filled Raffeallo with unneeded items and returned to Shuttle payload bay. Discovery launched on July 26 and spent almost 14 days on orbit.

A technician leaves the 'white room,' the access point for entering the Space Shuttle Discovery during post-flight processing at NASA DFRC in California

NASA Image and Video Library

2005-08-14

A technician leaves the 'white room', the access point for entering the Space Shuttle Discovery during post-flight processing in the Mate-Demate Device (MDD) at NASA's Dryden Flight Research Center in California. The gantry-like MDD structure is used for servicing the shuttle orbiters in preparation for their ferry flight back to the Kennedy Space Center in Florida, including mounting the shuttle atop NASA's modified Boeing 747 Shuttle Carrier Aircraft. Space Shuttle Discovery landed safely at NASA's Dryden Flight Research Center at Edwards Air Force Base in California at 5:11:22 a.m. PDT, August 9, 2005, following the very successful 14-day STS-114 return to flight mission. During their two weeks in space, Commander Eileen Collins and her six crewmates tested out new safety procedures and delivered supplies and equipment the International Space Station. Discovery spent two weeks in space, where the crew demonstrated new methods to inspect and repair the Shuttle in orbit. The crew also delivered supplies, outfitted and performed maintenance on the International Space Station. A number of these tasks were conducted during three spacewalks. In an unprecedented event, spacewalkers were called upon to remove protruding gap fillers from the heat shield on Discovery's underbelly. In other spacewalk activities, astronauts installed an external platform onto the Station's Quest Airlock and replaced one of the orbital outpost's Control Moment Gyroscopes. Inside the Station, the STS-114 crew conducted joint operations with the Expedition 11 crew. They unloaded fresh supplies from the Shuttle and the Raffaello Multi-Purpose Logistics Module. Before Discovery undocked, the crews filled Raffeallo with unneeded items and returned to Shuttle payload bay. Discovery launched on July 26 and spent almost 14 days on orbit.

The sun sets on the Space Shuttle Discovery during post-flight processing in the Mate-Demate Device (MDD), following its landing at NASA DFRC in California

NASA Image and Video Library

2005-08-14

The sun sets on the Space Shuttle Discovery during post-flight processing in the Mate-Demate Device (MDD), following its landing at NASA's Dryden Flight Research Center in California. The gantry-like MDD structure is used for servicing the shuttle orbiters in preparation for their ferry flight back to the Kennedy Space Center in Florida, including mounting the shuttle atop NASA's modified Boeing 747 Shuttle Carrier Aircraft. Space Shuttle Discovery landed safely at NASA's Dryden Flight Research Center at Edwards Air Force Base in California at 5:11:22 a.m. PDT, August 9, 2005, following the very successful 14-day STS-114 return to flight mission. During their two weeks in space, Commander Eileen Collins and her six crewmates tested out new safety procedures and delivered supplies and equipment the International Space Station. Discovery spent two weeks in space, where the crew demonstrated new methods to inspect and repair the Shuttle in orbit. The crew also delivered supplies, outfitted and performed maintenance on the International Space Station. A number of these tasks were conducted during three spacewalks. In an unprecedented event, spacewalkers were called upon to remove protruding gap fillers from the heat shield on Discovery's underbelly. In other spacewalk activities, astronauts installed an external platform onto the Station's Quest Airlock and replaced one of the orbital outpost's Control Moment Gyroscopes. Inside the Station, the STS-114 crew conducted joint operations with the Expedition 11 crew. They unloaded fresh supplies from the Shuttle and the Raffaello Multi-Purpose Logistics Module. Before Discovery undocked, the crews filled Raffeallo with unneeded items and returned to Shuttle payload bay. Discovery launched on July 26 and spent almost 14 days on orbit.

The Space Shuttle Discovery receives post-flight servicing in the Mate-Demate Device (MDD) at NASA's Dryden Flight Research Center, Edwards, California

NASA Image and Video Library

2005-08-11

The Space Shuttle Discovery receives post-flight servicing in the Mate-Demate Device (MDD), following its landing at NASA's Dryden Flight Research Center, Edwards, California, August 9, 2005. The gantry-like MDD structure is used for servicing the shuttle orbiters in preparation for their ferry flight back to the Kennedy Space Center in Florida, including mounting the shuttle atop NASA's modified Boeing 747 Shuttle Carrier Aircraft. Space Shuttle Discovery landed safely at NASA's Dryden Flight Research Center at Edwards Air Force Base in California at 5:11:22 a.m. PDT, August 9, 2005, following the very successful 14-day STS-114 return to flight mission. During their two weeks in space, Commander Eileen Collins and her six crewmates tested out new safety procedures and delivered supplies and equipment the International Space Station. Discovery spent two weeks in space, where the crew demonstrated new methods to inspect and repair the Shuttle in orbit. The crew also delivered supplies, outfitted and performed maintenance on the International Space Station. A number of these tasks were conducted during three spacewalks. In an unprecedented event, spacewalkers were called upon to remove protruding gap fillers from the heat shield on Discovery's underbelly. In other spacewalk activities, astronauts installed an external platform onto the Station's Quest Airlock and replaced one of the orbital outpost's Control Moment Gyroscopes. Inside the Station, the STS-114 crew conducted joint operations with the Expedition 11 crew. They unloaded fresh supplies from the Shuttle and the Raffaello Multi-Purpose Logistics Module. Before Discovery undocked, the crews filled Raffeallo with unneeded items and returned to Shuttle payload bay. Discovery launched on July 26 and spent almost 14 days on orbit.

The Space Shuttle Discovery receives post-flight servicing in the Mate-Demate Device (MDD) at NASA's Dryden Flight Research Center, Edwards, California

NASA Image and Video Library

2005-08-11

The Space Shuttle Discovery receives post-flight servicing in the Mate-Demate Device (MDD), following its landing at NASA's Dryden Flight Research Center, Edwards, California, August 9, 2005. The gantry-like MDD structure is used for servicing the shuttle orbiters in preparation for their ferry flight back to the Kennedy Space Center in Florida, including mounting the shuttle atop NASA's modified Boeing 747 Shuttle Carrier Aircraft. Space Shuttle Discovery landed safely at NASA's Dryden Flight Research Center at Edwards Air Force Base in California at 5:11:22 a.m. PDT this morning, following the very successful 14-day STS-114 return to flight mission. During their two weeks in space, Commander Eileen Collins and her six crewmates tested out new safety procedures and delivered supplies and equipment the International Space Station. Discovery spent two weeks in space, where the crew demonstrated new methods to inspect and repair the Shuttle in orbit. The crew also delivered supplies, outfitted and performed maintenance on the International Space Station. A number of these tasks were conducted during three spacewalks. In an unprecedented event, spacewalkers were called upon to remove protruding gap fillers from the heat shield on Discovery's underbelly. In other spacewalk activities, astronauts installed an external platform onto the Station's Quest Airlock and replaced one of the orbital outpost's Control Moment Gyroscopes. Inside the Station, the STS-114 crew conducted joint operations with the Expedition 11 crew. They unloaded fresh supplies from the Shuttle and the Raffaello Multi-Purpose Logistics Module. Before Discovery undocked, the crews filled Raffeallo with unneeded items and returned to Shuttle payload bay. Discovery launched on July 26 and spent almost 14 days on orbit.

STS-63 Space Shuttle report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1995-01-01

The STS-63 Space Shuttle Program Mission Report summarizes the Payload activities and provides detailed data on the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle Main Engine (SSME) systems performance during this sixty-seventh flight of the Space Shuttle Program, the forty-second since the return to flight, and twentieth flight of the Orbiter vehicle Discovery (OV-103). In addition to the OV-103 Orbiter vehicle, the flight vehicle consisted of an ET that was designated ET-68; three SSME's that were designated 2035, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-070. The RSRM's that were an integral part of the SRB's were designated 360Q042A for the left SRB and 360L042B for the right SRB. The STS-63 mission was planned as an 8-day duration mission with two contingency days available for weather avoidance or Orbiter contingency operations. The primary objectives of the STS-63 mission were to perform the Mir rendezvous operations, accomplish the Spacehab-3 experiments, and deploy and retrieve the Shuttle Pointed Autonomous Research Tool for Astronomy-204 (SPARTAN-204) payload. The secondary objectives were to perform the Cryogenic Systems Experiment (CSE)/Shuttle Glo-2 Experiment (GLO-2) Payload (CGP)/Orbital Debris Radar Calibration Spheres (ODERACS-2) (CGP/ODERACS-2) payload objectives, the Solid Surface Combustion Experiment (SSCE), and the Air Force Maui Optical Site Calibration Tests (AMOS). The objectives of the Mir rendezvous/flyby were to verify flight techniques, communication and navigation-aid sensor interfaces, and engineering analyses associated with Shuttle/Mir proximity operations in preparation for the STS-71 docking mission.

Analytical and experimental investigation of a 1/8-scale dynamic model of the shuttle orbiter. Volume 2: Technical report

NASA Technical Reports Server (NTRS)

Mason, P. W.; Harris, H. G.; Zalesak, J.; Bernstein, M.

1974-01-01

The methods and procedures used in the analysis and testing of the scale model are reported together with the correlation of the analytical and experimental results. The model, the NASTRAN finite element analysis, and results are discussed. Tests and analytical investigations are also reported.

Oxidation of Reinforced Carbon-Carbon Subjected to Hypervelocity Impact

NASA Technical Reports Server (NTRS)

Curry, Donald M.; Pham, Vuong T.; Norman, Ignacio; Chao, Dennis C.

2000-01-01

This paper presents results from arc jet tests conducted at the NASA Johnson Space Center on reinforced carbon-carbon (RCC) samples subjected to hypervelocity impact. The RCC test specimens are representative of RCC components used on the Space Shuttle Orbiter. The arc jet testing established the oxidation characteristics of RCC when hypervelocity projectiles, simulating meteoroid/orbital debris, impact the RCC material. In addition to developing correlations for use in trajectory simulations, we discuss analytical modeling of the increased material oxidation in the impacted area using measured hole growth data. Entry flight simulations are useful in assessing the increased Space Shuttle RCC component degradation as a result of impact damage and the hot gas flow through an enlarging hole into the wing leading-edge cavity.

Space shuttle: Static stability and control investigation of NR/GD delta wing booster (B-20) and delta wing orbiter (134-D), volume 3

NASA Technical Reports Server (NTRS)

Allen, E. C., Jr.; Eder, F. W.

1972-01-01

Experimental aerodynamic investigations have been made on a .0035 scale model North American Rockwell/General Dynamics version of the space shuttle in the NASA/MSFC 14 x 14 Inch Trisonic Wind Tunnel. Static stability and control data were obtained on the delta wing booster alone (B-20) and with the delta wing orbiter (134D) mounted in various positions on the booster. Six component aerodynamic force and moment data were recorded over an angle of attack range from -10 to 24 deg at 0 and 6 deg sideslip angles and from -10 to +10 deg sideslip at 0 deg angle of attack. Mach number ranged from 0.6 to 4.96.

Supersonic stability and control characteristics of a 0.015 scale model 69-0 of the space shuttle orbiter with forebody RSI modifications in the NASA/LaRC 4-foot UPWT (legs 1 and 2) (LA71A/B)

NASA Technical Reports Server (NTRS)

1977-01-01

Investigations are reported for the determination of aerodynamic effects of reducing the thickness of the reusable surface insulation located along the sides of the shuttle orbiter in order to allow weight reduction in the nose region. Six-component aerodynamic force and moment data were obtained at Mach numbers from 1.5 to 4.6 over an angle of attack range from about -1 deg to 28 deg. Additional tests were made over an angle of sideslip range from -6 deg to 6 deg at selected angles of attack. Test results are presented in graph and tables.

Early Program Development

NASA Image and Video Library

1971-01-01

This 1971 artist's concept shows the Nuclear Shuttle in both its lunar logistics configuraton and geosynchronous station configuration. As envisioned by Marshall Space Flight Center Program Development persornel, the Nuclear Shuttle would deliver payloads to lunar orbits or other destinations then return to Earth orbit for refueling and additional missions.

KSC-2011-2868

NASA Image and Video Library

2011-04-12

CAPE CANAVERAL, Fla. -- NASA Administrator Charles Bolden, left, speaks with Professor Sam Ting, Alpha Magnetic Spectrometer-2 principal investigator at the Massachusetts Institute of Technology, Kennedy Center Director Bob Cabana and STS-1 Pilot and former Kennedy Space Center Director Bob Crippen. In a ceremony held in front of Orbiter Processing Facility-1 at NASA's Kennedy Space Center in Florida, NASA Administrator Charles Bolden announced the facilities where four shuttle orbiters will be displayed permanently at the conclusion of the Space Shuttle Program. Shuttle Enterprise, the first orbiter built, will move from the Smithsonian's National Air and Space Museum Steven F. Udvar-Hazy Center in Virginia to the Intrepid Sea, Air & Space Museum in New York. The Udvar-Hazy Center will become the new home for shuttle Discovery, which retired after completing its 39th mission in March. Shuttle Endeavour, which is preparing for its final flight at the end of the month, will go to the California Science Center in Los Angeles. Atlantis, which will fly the last planned shuttle mission in June, will be displayed at the Kennedy Space Center Visitor Complex in Florida. Later, employees, their families and friends, will celebrate the 30th anniversary of the first shuttle launch at the visitor complex. Photo credit: NASA/Kim Shiflett

Program Predicts Nonlinear Inverter Performance

NASA Technical Reports Server (NTRS)

Al-Ayoubi, R. R.; Oepomo, T. S.

1985-01-01

Program developed for ac power distribution system on Shuttle orbiter predicts total load on inverters and node voltages at each of line replaceable units (LRU's). Mathematical model simulates inverter performance at each change of state in power distribution system.

n/a

NASA Image and Video Library

1975-10-10

This diagram illustrates the Space Shuttle mission sequence. The Space Shuttle was approved as a national program in 1972 and developed through the 1970s. Part spacecraft and part aircraft, the Space Shuttle orbiter, the brain and the heart of the Space Transportation System (STS), required several technological advances, including thousands of insulating tiles able to stand the heat of reentry over the course of many missions, as well as sophisticated engines that could be used again and again without being thrown away. The airplane-like orbiter has three main engines, that burn liquid hydrogen and oxygen stored in the large external tank, the single largest structure in the Shuttle. Attached to the tank are two solid rocket boosters that provide the vehecile with most of the thrust needed for liftoff. Two minutes into the flight, the spent solids drop into the ocean to be recovered and refurbished for reuse, while the orbiter engines continue burning until approximately 8 minutes into the flight. After the mission is completed, the orbiter lands on a runway like an airplane.

STS-35 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Camp, David W.; Germany, D. M.; Nicholson, Leonard S.

1991-01-01

The STS-35 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities during this thirty-eighth flight of the Space Shuttle and the tenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-35/LWT-28), three Space Shuttle main engines (SSME's) (serial numbers 2024, 2012, and 2028 in positions 1, 2, and 3, respectively), and two Solid Rocket Boosters (SRB's) designated as BI-038. The primary objectives of this flight were to successfully perform the planned operations of the Ultraviolet Astronomy (Astro-1) payload and the Broad-Band X-Ray Telescope (BBXRT) payload in a 190-nmi. circular orbit which had an inclination of 28.45 degrees. The sequence of events for this mission is shown in tablular form. Summarized are the significant problems that occurred in the Orbiter subsystems during the mission. The official problem tracking list is presented. In addition, each Orbiter subsystem problem is cited in the applicable subsystem discussion.

An automated data management/analysis system for space shuttle orbiter tiles. [stress analysis

NASA Technical Reports Server (NTRS)

Giles, G. L.; Ballas, M.

1982-01-01

An engineering data management system was combined with a nonlinear stress analysis program to provide a capability for analyzing a large number of tiles on the space shuttle orbiter. Tile geometry data and all data necessary of define the tile loads environment accessed automatically as needed for the analysis of a particular tile or a set of tiles. User documentation provided includes: (1) description of computer programs and data files contained in the system; (2) definitions of all engineering data stored in the data base; (3) characteristics of the tile anaytical model; (4) instructions for preparation of user input; and (5) a sample problem to illustrate use of the system. Description of data, computer programs, and analytical models of the tile are sufficiently detailed to guide extension of the system to include additional zones of tiles and/or additional types of analyses

Space shuttle: Aerodynamic stability and control characteristics of the NASA/MSC .006 scale 040-A delta wing orbiter

NASA Technical Reports Server (NTRS)

Click, P. L.; Michana, D. J.; Sarver, D. A.

1971-01-01

Experimental aerodynamic investigations were made on a .006 scale model 040-A delta wing space shuttle orbiter configuration. These tests were conducted to determine six-degree-of-freedom force and moment data for preliminary stability and control analysis. Data were obtained over a Mach number range from 0.6 to 4.96 at angles of attack from -10 deg to 50 deg at zero degrees sideslip and at angles of sideslip from -10 deg to 10 deg at constants angles of attack of 0 deg, 15 deg, 30 deg, and 45 deg. Various aileron, elevator, (elevon) rudder and rudder flare deflection angles were tested to establish the control effectiveness and vehicle stability. Model component buildup data were also obtained to provide a data base for future configuration modifications. Plotted data results are presented in both the body and stability axis system.

Results of tests in the NASA/LARC 31-inch CFHT on an 0.010-scale model (32-OT) of the space shuttle configuration 3 to determine the RCS jet flowfield interaction effects on aerodynamic characteristics (IA60/OA105), volume 1

NASA Technical Reports Server (NTRS)

Thornton, D. E.

1974-01-01

Tests were conducted in the NASA Langley Research Center 31-inch continuous Flow Hypersonic Wind Tunnel to determine RCS jet interaction effect on the hypersonic aerodynamic and stability and control characteristics prior to return to launch site (RTLS) abort separation. The model used was an 0.010-scale replica of the Space Shuttle Vehicle Configuration 3. Hypersonic stability data were obtained from tests at Mach 10.3 and dynamic pressure of 150 psf for the integrated Orbiter and external tank and the Orbiter alone. RCS modes of pitch, yaw, and roll at free flight dynamic pressure simulation of 7, 20, and 50 psf were investigated. The effects of speedbrake, bodyflap, elevon, and aileron deflections were also investigated.

A Feasibility Study on a Parallel Mechanism for Examining the Space Shuttle Orbiter Payload Bay Radiators

NASA Technical Reports Server (NTRS)

Roberts, Rodney G.; LopezdelCastillo, Eduardo

1996-01-01

The goal of the project was to develop the necessary analysis tools for a feasibility study of a cable suspended robot system for examining the space shuttle orbiter payload bay radiators These tools were developed to address design issues such as workspace size, tension requirements on the cable, the necessary accuracy and resolution requirements and the stiffness and movement requirements of the system. This report describes the mathematical models for studying the inverse kinematics, statics, and stiffness of the robot. Each model is described by a matrix. The manipulator Jacobian was also related to the stiffness matrix, which characterized the stiffness of the system. Analysis tools were then developed based on the singular value decomposition (SVD) of the corresponding matrices. It was demonstrated how the SVD can be used to quantify the robot's performance and to provide insight into different design issues.

Results of tests in the NASA/LaRC 31-inch CFHT on an 0.010-scale model (32-OT) of the space shuttle configuration 3 to determine the RCS jet flowfield interaction effects on aerodynamic characteristics (IA60/0A105), volume 1

NASA Technical Reports Server (NTRS)

Thornton, D. E.

1974-01-01

Tests were conducted in the 31-inch continuous Flow Hypersonic Wind Tunnel to determine RCS jet interaction effect on the hypersonic aerodynamic and stability and control characteristics prior to RTLS abort separation. The model used was an 0.010-scale replica of the Space Shuttle Vehicle Configuration 3. Hypersonic stability data were obtained from tests at Mach 10.3 and dynamic pressure of 150 psf for the integrated Orbiter and external tank and the Orbiter alone. RCS modes of pitch, yaw, and roll at free flight dynamic pressure simulation of 7, 20, and 50 psf were investigated. The effects of speedbrake, bodyflap, elevon, and airleron deflections were also investigated.

Results of tests in the NASA/LaRC 31-inch CFHT on an 0.010-scale model (32-OT) of the space shuttle configuration 3 to determine the RCS jet flowfield interaction effects on aerodynamic characteristics (IA60/0A105), volume 2

NASA Technical Reports Server (NTRS)

Thornton, D. E.

1974-01-01

Tests were conducted in the NASA Langley Research Center 31-inch continuous flow hypersonic wind tunnel from 14 February to 22 February 1974, to determine RCS jet interaction effect on the hypersonic aerodynamic and stability and control characteristics prior to RTLS abort separation. The model used was an 0.010-scale replica of the space shuttle vehicle configuration 3. Hypersonic stability data were obtained from tests at Mach 10.3 and dynamic pressure of 150 psf for the intergrated orbiter and external tank and the orbiter alone. RCS modes of pitch, yaw, and roll at free flight dynamic pressure simulation of 7, 20, and 50 psf were investigated. The effects of speedbrake, bodyflap, elevon, and aileron deflections were also investigated.

Results of an investigation to determine local flow characteristics at the air data probe locations using an 0.030-scale model (45-0) of the space shuttle vehicle orbiter configuration 140A/B (modified) in the NASA Ames Research Center unitary plan wind tunnel (OA161, A, B, C), volume 1

NASA Technical Reports Server (NTRS)

Nichols, M. E.

1976-01-01

Results are presented of wind tunnel test 0A161 of a 0.030-scale model 45-0 of the configuration 140A/B (modified) space shuttle vehicle orbiter in the NASA Ames Research Center Unitary Plan Wind Tunnel facilities. The purpose of this test was to determine local total and static pressure environments for the air data probe locations and relative effectiveness of alternate flight-test probe configurations. Testing was done in the Mach number range from 0.30 to 3.5. Angle of attack was varied from -8 to 25 degrees while sideslip varied between -8 and 8 degrees.

Quasi-Static 3-Point Reinforced Carbon-Carbon Bend Test and Analysis for Shuttle Orbiter Wing Leading Edge Impact Damage Thresholds

NASA Technical Reports Server (NTRS)

Fasanella, Edwin L.; Sotiris, Kellas

2006-01-01

Static 3-point bend tests of Reinforced Carbon-Carbon (RCC) were conducted to failure to provide data for additional validation of an LS-DYNA RCC model suitable for predicting the threshold of impact damage to shuttle orbiter wing leading edges. LS-DYNA predictions correlated well with the average RCC failure load, and were good in matching the load vs. deflection. However, correlating the detectable damage using NDE methods with the cumulative damage parameter in LS-DYNA material model 58 was not readily achievable. The difficulty of finding internal RCC damage with NDE and the high sensitivity of the mat58 damage parameter to the load near failure made the task very challenging. In addition, damage mechanisms for RCC due to dynamic impact of debris such as foam and ice and damage mechanisms due to a static loading were, as expected, not equivalent.

Endeavour Grand Opening Ceremony

NASA Image and Video Library

2012-10-30

David D. McBride, director of NASA's Dryden Flight Research Center, speaks from a podium underneath the space shuttle Endeavour during the grand opening ceremony for the California Science center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, Tuesday, Oct. 30, 2012, in Los Angeles. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Photo Credit: (NASA/Bill Ingalls)

Endeavour Grand Opening Ceremony

NASA Image and Video Library

2012-10-30

President and CEO of the California Science Center Jeffrey N. Rudolph speaks from a podium underneath the space shuttle Endeavour during the grand opening ceremony for the center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, Tuesday, Oct. 30, 2012, in Los Angeles. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Photo Credit: (NASA/Bill Ingalls)

Endeavour Grand Opening Ceremony

NASA Image and Video Library

2012-10-30

Chief Executive Officer of the Planetary Society, Bill Nye "The Science Guy", acts as emcee from a podium underneath the space shuttle Endeavour during the grand opening ceremony for the center's Samuel Oschin Space Shuttle Endeavour Display Pavilion, Tuesday, Oct. 30, 2012, in Los Angeles. Endeavour, built as a replacement for space shuttle Challenger, completed 25 missions, spent 299 days in orbit, and orbited Earth 4,671 times while traveling 122,883,151 miles. Photo Credit: (NASA/Bill Ingalls)

STS-57 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1993-01-01

The STS-57 Space Shuttle Program Mission Report provides a summary of the Payloads, as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the fifty-sixth flight of the Space Shuttle Program and fourth flight of the Orbiter vehicle Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET (ET-58); three SSME's which were designated as serial numbers 2019, 2034, and 2017 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-059. The lightweight RSRM's that were installed in each SRB were designated as 360L032A for the left SRB and 360W032B for the right SRB. The STS-57 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement, as documented in NSTS 07700, Volume 8, Appendix E. That document states that each major organizational element supporting the Program will report the results of their hardware evaluation and mission performance plus identify all related in-flight anomalies.

International Space Station (ISS) Oxygen High Pressure Storage Management

NASA Technical Reports Server (NTRS)

Lewis, John R.; Dake, Jason; Cover, John; Leonard, Dan; Bohannon, Carl

2004-01-01

High pressure oxygen onboard the ISS provides support for Extra Vehicular Activities (EVA) and contingency metabolic support for the crew. This high pressure 02 is brought to the ISS by the Space Shuttle and is transferred using the Oxygen Recharge Compressor Assembly (ORCA). There are several drivers that must be considered in managing the available high pressure 02 on the ISS. The amount of O2 the Shuttle can fly up is driven by manifest mass limitations, launch slips, and on orbit Shuttle power requirements. The amount of 02 that is used from the ISS high pressure gas tanks (HPGT) is driven by the number of Shuttle docked and undocked EVAs, the type of EVA prebreath protocol that is used and contingency use of O2 for metabolic support. Also, the use of the ORCA must be managed to optimize its life on orbit and assure that it will be available to transfer the planned amount of O2 from the Shuttle. Management of this resource has required long range planning and coordination between Shuttle manifest on orbit plans. To further optimize the situation hardware options have been pursued.

Space Shuttle Orbiter auxiliary power unit status

NASA Technical Reports Server (NTRS)

Reck, M.; Loken, G.; Horton, J.; Lukens, W.; Scott, W.; Baughman, J.; Bauch, T.

1991-01-01

An overview of the United States Space Shuttle Orbiter APU, which provides power to the Orbiter vehicle hydraulic system, is presented. Three complete APU systems, each with its own separate fuel system, supply power to three dedicated hydraulic systems. These in turn provide power to all Orbiter vehicle critical flight functions including launch, orbit, reentry, and landing. The basic APU logic diagram is presented. The APU includes a hydrazine-powered turbine that drives a hydraulic pump and various accessories through a high-speed gearbox. The APU also features a sophisticated thermal management system designed to ensure safe and reliable operation in the various launch, orbit, reentry, and landing environments.

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility oversee installation of the liquid oxygen feedline for the 17-inch disconnect on the orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility oversee installation of the liquid oxygen feedline for the 17-inch disconnect on the orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

Mounted Video Camera Captures Launch of STS-112, Shuttle Orbiter Atlantis

NASA Technical Reports Server (NTRS)

2002-01-01

A color video camera mounted to the top of the External Tank (ET) provided this spectacular never-before-seen view of the STS-112 mission as the Space Shuttle Orbiter Atlantis lifted off in the afternoon of October 7, 2002, The camera provided views as the the orbiter began its ascent until it reached near-orbital speed, about 56 miles above the Earth, including a view of the front and belly of the orbiter, a portion of the Solid Rocket Booster, and ET. The video was downlinked during flight to several NASA data-receiving sites, offering the STS-112 team an opportunity to monitor the shuttle's performance from a new angle. Atlantis carried the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart. The CETA is the first of two human-powered carts that will ride along the International Space Station's railway providing a mobile work platform for future extravehicular activities by astronauts. Landing on October 18, 2002, the Orbiter Atlantis ended its 11-day mission.

Mounted Video Camera Captures Launch of STS-112, Shuttle Orbiter Atlantis

NASA Technical Reports Server (NTRS)

2002-01-01

A color video camera mounted to the top of the External Tank (ET) provided this spectacular never-before-seen view of the STS-112 mission as the Space Shuttle Orbiter Atlantis lifted off in the afternoon of October 7, 2002. The camera provided views as the orbiter began its ascent until it reached near-orbital speed, about 56 miles above the Earth, including a view of the front and belly of the orbiter, a portion of the Solid Rocket Booster, and ET. The video was downlinked during flight to several NASA data-receiving sites, offering the STS-112 team an opportunity to monitor the shuttle's performance from a new angle. Atlantis carried the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart. The CETA is the first of two human-powered carts that will ride along the International Space Station's railway providing a mobile work platform for future extravehicular activities by astronauts. Landing on October 18, 2002, the Orbiter Atlantis ended its 11-day mission.

Shuttle orbiter - IUS/DSP satellite interface contamination study

NASA Technical Reports Server (NTRS)

Rantanen, R. O.; Strange, D. A.

1978-01-01

The results of a contamination analysis on the Defense Support Program (DSP) satellite during launch and deployment by the Space Transportation System (STS) are presented. Predicted contaminant deposition was also included on critical DSP surfaces during the period soon after launch when the DSP is in the shuttle orbiter bay with the doors closed, the bay doors open, and during initial deployment. Additionally, a six sided box was placed at the spacecraft position to obtain directional contaminant flux information for a general payload while in the bay and during deployment. The analysis included contamination sources from the shuttle orbiter, IUS and cradle, the DSP sensor and the DSP support package.

Determination of ASPS performance for large payloads in the shuttle orbiter disturbance environment. [digital simulation

NASA Technical Reports Server (NTRS)

Keckler, C. R.; Kibler, K. S.; Powell, L. F.

1979-01-01

A high fidelity simulation of the annular suspension and pointing system (ASPS), its payload, and the shuttle orbiter was used to define the worst case orientations of the ASPS and its payload for the various vehicle disturbances, and to determine the performance capability of the ASPS under these conditions. The most demanding and largest proposed payload, the Solar Optical Telescope was selected for study. It was found that, in all cases, the ASPS more than satisfied the payload's requirements. It is concluded that, to satisfy facility class payload requirements, the ASPS or a shuttle orbiter free-drift mode (control system off) should be utilized.

Space Shuttle Orbiter logistics - Managing in a dynamic environment

NASA Technical Reports Server (NTRS)

Renfroe, Michael B.; Bradshaw, Kimberly

1990-01-01

The importance and methods of monitoring logistics vital signs, logistics data sources and acquisition, and converting data into useful management information are presented. With the launch and landing site for the Shuttle Orbiter project at the Kennedy Space Center now totally responsible for its own supportability posture, it is imperative that logistics resource requirements and management be continually monitored and reassessed. Detailed graphs and data concerning various aspects of logistics activities including objectives, inventory operating levels, customer environment, and data sources are provided. Finally, some lessons learned from the Shuttle Orbiter project and logistics options which should be considered by other space programs are discussed.

Thermal control evaluation of a Shuttle Orbiter solar observatory using Skylab ATM backup hardware

NASA Technical Reports Server (NTRS)

Class, C. R.; Presta, G.; Trucks, H.

1975-01-01

A study under the sponsorship of Marshall Space Flight Center (MSFC) established the feasibility to utilize the Skylab Apollo Telescope Mount (ATM) backup hardware for early low cost Shuttle Orbiter solar observation missions. A solar inertial attitude and a seven-day, full sun exposure were baselined. As a portion of the study, a series of thermal control evaluations were performed to resolve the problems caused by the relocation of the ATM to the Shuttle Orbiter bay and resulting configuration changes. Thermal control requirements, problems, the use of solar shields, Spacelab supplied fluid cooling and component placement are discussed.