Engineering Papers⌕ Search

SEARCH · Engineering Papers

Results for “STS”

Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 649 records · Page 36
All sourcesNASA NTRSDOE OSTI
NASA NTRS1984

Interpretation of STS-3/plasma diagnostics package results in terms of large space structure plasma interactions

The Plasma Diagnostics Package, which was flown aboard STS-3 recorded various chemical releases from the Orbiter. Changes in the plasma environment were observed to occur during Flash Evaporator System (FES) releases, water dumps and maneuvering thruster operations. During flash evaporator operations, broadband Orbiter-generated electro-static noise is enhanced and plasma density irregularity (delta n/N) is observed to increase by as much as 4 times and is strongly peaked below 6 Hz. In the case of water dumps, background electrostatic noise is enhanced or suppressed depending on frequency and Delta N/N is also seen to increase by as much as 4 times. Various changes in the plasma environment are effected by primary and vernier thruster operations. In addition, thruster activity stimulates electrostatic noise with a spectrum which is most intense at frequencies below 10 kHz.

Kurth, W. S.↗
NASA NTRS1984

Airborne measurements of launch vehicle effluent of STS-2 launch on November 12, 1981 at Cape Canaveral, Florida

The second Space Shuttle (STS-2) was launched from the John F. Kennedy Space Center at 1010 EST on November 12, 1981. An instrumented light airplane was used to measure the emitted concentration of Shuttle exhaust products produced during launch. The airplane accomplished 31 passes through and under the exhaust cloud in the 1 hr 45 min immediately following the launch. Measurements included the following: (1) particulate data in the form of a light scattering coefficient obtained from an integrating nephelometer, (2) particulate concentrations and mass concentrations obtained from a spectrometer probe, (3) gaseous HCl and total HCl concentrations obtained from a gas-filter-correlation instrument and a chemiluminescent instrument, respectively, and (4) outside-air temperature and dew-point temperature. These data are presented along with time, altitude, and position for each cloud pass. These data are within the range of values observed during similar measurements made during the first Space Shuttle launch on April 12, 1981.

Maddrea, G. L., Jr.↗
NASA NTRS1984

STS-9 BET products

The final products generated for the STS-9, which landed on December 8, 1983 are reported. The trajectory reconstruction utilized an anchor epoch of GMT corresponding to an initial altitude of h 356 kft, selected in view of the limited tracking coverage available. The final state utilized IMU2 measurements and was based on processing radar tracking from six C-bands and a single S-band station, plus six photo-theodolite cameras in the vicinity of Runway 17 at Edwards Air Force Base. The final atmosphere (FLAIR9/UN=581199C) was based on a composite of the remote measured data and the 1978 Air Force Reference Atmosphere model. The Extended BET is available as STS9BET/UN=274885C. The AEROBET and MMLE input files created are discussed. Plots of the more relevant parameters from the AEROBET (reel number NL0624) are included. Input parameters, final residual plots, a trajectory listing, and data archival information are defined.

Findlay, J. T.↗
NASA NTRS1983

Effects of chemical releases by the STS-3 Orbiter on the ionosphere

The Plasma Diagnostics Package, flown aboard STS-3 as part of the first Shuttle payload (OSS-1), recorded the effects of various chemical releases from the Orbiter. Changes in the plasma environment was observed during flash evaporator system releases, water dumps and maneuvering thruster operations. During flash evaporator operations, broadband Orbiter-generated electrostatic noise was enhanced and plasma density irregularities were observed to increase by 3 to 30 times with a spectrum which rose steeply and peaked below 6 Hz. In the case of water dumps, background electrostatic noise was enhanced at frequencies below about 3 kHz and suppressed at frequencies above 2 kHz. Thruster activity also stimulated electrostatic noise with a spectrum which peaked at approximately 0.5 kHz. In addition, ions with energies up to 1 keV were seen during some thruster events.

Pickett, J. S.↗
NASA NTRS1984

Final STS-11 (41-B) best estimate trajectory products: Development and results from the first Cape landing

The STS-11 (41-B) postflight data processing is completed and the results published. The final reconstructed entry trajectory is presented. The various atmospheric sources available for this flight are discussed. Aerodynamic Best Estimate of Trajectory BET generation and plots from this file are presented. A definition of the major maneuvers effected is given. Physical constants, including spacecraft mass properties; final residuals from the reconstruction process; trajectory parameter listings; and an archival section are included.

Kelly, G. M.↗
NASA NTRS1982

Flight data file: STS-4 crew activity plan

The STS-4 Crew Activity Plan contains the on-orbit timeline, which is a flight data file article. Various time scales such as Mission Elapsed Time (MET), Greenwich Mean Time (GMT), and time until deorbit ignition as well as crew activities, day/night, orbit position, ground tracking, communication coverage, attitude, and maneuvers are presented in chart form.

Pippert, E. B., Jr.↗
NASA NTRS1983

MEA/A-1 experiment 81F01 conducted on STS-7 flight, June 1983. Containerless processing of glass forming melts

The space processing of containerless, glassforming melts on board the space shuttle flight STS-7 is investigated. Objectives include; (1) obtain quantitative evidence for the supression of heterogeneous nucleation/crystallization, (2) study melt homogenization without gravity driven convection, (3) procedural development for bubble free, high purity homogeneous melts inmicro-g, (4) comparative analysis of melts on Earth and in micro g, and (5) assess the apparatus for processing multicomponent, glass forming melts in a low gravity environment.

Day, D. E.↗
NASA NTRS1984

Atomic beam system for laboratory simulation of upper atmosphere oxygen atom impact on STS surfaces

An atomic beam apparatus capable of producing a collimated beam of O atoms or other atmospheric species at the STS impact velocity of 8 km/s is described. A conventional ion beam charge transfer neutralization approach was adopted to produce the projectile beam. The prime considerations favoring this approach are: the ability to vary the velocity of the impacting species at will over a wide range on either side of the optimum required value of 8 km/s; and sample irradiation can be made with species other than O-atoms, such as O2, N, or N2.

Mahadevan, P.↗
NASA NTRS1984

LEO atomic oxygen effects on spacecraft materials: STS-5 results

Effects of low Earth orbit (LEO) atomic oxygen were measured on a variety of spacecraft materials which obtained exposure on STS-5. Material degradation dependency on temperature was found in one material. Of the five paints flown, only S13GLO was unaffected. Generally, the glossy paints became Lambertian and the diffuse coatings improved. Scanning electron microscope examinations indicated removal of urethane and epoxy paint binder materials. Reaction products were evident on the surfaces of Z302 paint and Mylar. Thin films showed thickness losses ranging from negligible loss in Teflon to considerable loss in Mylar and Kapton. Glossy films such as black Kapton and white Tedlar became diffused. Kevlar 29 rope lost tensile strength and silver solar cell interconnect material oxidized. Oxidation on the backside of an elevated specimen indicated that reflections of oxygen atoms were occurring and that reflecting surfaces, probably Kapton, were not fully accommodating the incident atoms.

Whitaker, A. F.↗
NASA NTRS1983

Measured thermal ion environment of STS-3

The Plasma Diagnostic Package (PDP) on the third Space Shuttle Flight (STS- 3) included a Bennett RF ion mass spectrometer which surveyed the positive ion composition in the vicinity of the vehicle. The ion measurements both within and exterior to the Shuttle cargo bay show the pervasive influence of the Shuttle's own gaseous emissions on its immediate plasma environment. Within the bay the ion spectrometer detected copius quantities of ions when the Shuttle was in daylight and when the gas pressure at the surface of the PDP was enhanced. In general few cases of ion detection occurred when the bay was facing toward the Shuttle wake. The plasma near the Shuttle consisted predominately of O+ (16AMU) ions and ions with atomic masses of 18, 30, 32 and 44 AMU corresponding to H2O+, NO+, O2+, and CO2+. All of these ions with the exception of H2O+ and CO2+ are expected ambient ions at the Shuttle's altitude of 240 km. During some thruster firings the 18 and 30 AMU ion concentrations detected within the bay increase by up to an order of magnitude within the 2.4 second sweep of the instrument. During these latter events the O+ distributions did not show a similar change.

Grebowsky, J. M.↗
NASA NTRS1983

Development of baseline random vibration criteria for STS pallet payloads

This paper presents a statistical evaluation of measured random vibration response data obtained from the Office of Space Science-1 (OSS-1) pallet payload. The data were measured during the acoustic test simulation (September 1980) and the ascent phase of the flight of STS-3, Orbiter 102 (launched from the Kennedy Space Center on March 22, 1982). Acoustic test efficiency factors are evaluated based on the Dynamic, Acoustic and Thermal Environments (DATE) instrumentation as the source of the measured vibration data. Test efficiency correction to test data is applied in the extrapolation of non-DATE acoustic test data to increase sample population size for improved statistical evaluation. For baseline criteria evaluation and development, data are grouped in accordance with the payload 'zone' in which the component is mounted.

On, F. J.↗
NASA NTRS1983

Base drag determination for STS flights 1-5

Predicting the base drag characteristics for blunt based vehicles such as the Space Shuttle orbiter in gliding flight is difficult, particularly at transonic speeds. Data from the first five flights (STS 1-5) of the orbiter Columbia have been utilized to obtain the interference-free, base drag characteristics. These base drag characteristics are compared to preflight predictions derived from wind tunnel tests. Base drag is shown to account for as much as 50 percent of the total orbiter drag at transonic speeds.

Phillips, W. P.↗
NASA NTRS1984

Wave emissions from dc and modulated electron beams on STS 3

During the third Space Shuttle Columbia flight (STS 3) in March 1982, investigations were conducted to assess the electrical, electromagnetic, and plasma environment of the orbiter and to diagnose wave emissions and related plasma effects due to the injection of an electron beam into the surrounding ionosphere. Attention is given to wave emissions and related plasma processes which were stimulated by the first electron beam emissions from the Space Shuttle. The on-orbit measurements are compared to measurements made in a space simulation chamber. Instrumentation and operations are considered along with the plasma effects of beam emissions, wave emissions from dc beams, wave emissions from VLF-modulated beams, and wave emissions from ELF-modulated beams.

Shawhan, S. D.↗
NASA NTRS1984

Observation of orbiting vehicle induced luminosities on the STS-8 mission

Image-intensified photographic observations of vehicle glow from the STS-8 Space Shuttle mission are discussed. An objective grating spectrometer preceding a camera was used to measure the intensity of the glow. It is found that glow intensity is dependent on the nature of the vehicle material. With limited resolution of the objective spectrum vehicle glow appeared as a continuum emission. The intensity of the glow from the tail of the vehicle became detectable at 4600 A and increased toward the red. Between 7000 and 8000 A, a slight decrease in the glow intensity is inferred. The absolute intensity of the obliquely viewed tail glow was measured at 450 Rayleighs per Angstrom at 7000 A and 1 MR in the range within the transmission band of the image intensifier camera. The spectral distribution is found to be in agreement with measurements taken from the atmospheric explorer satellite. Samples of the photographic data are provided.

Mende, S. B.↗
NASA NTRS1984

Growth and development of plants flown on the STS-3 Space Shuttle mission

Pre-germinated pine seedlings and germinating oat and mung bean seeds were flown on the STS-3 Space Shuttle mission. Overall, the seedlings grew and developed well in space. Some oat and mung bean roots, however, grew upward. Lignin content was slightly lower in flight tissues and protein content was higher.

Cowles, J. R.↗
NASA NTRS1984

Future scientific missions for STS

The present investigation is concerned with a number of astrophysics missions which are currently being studied by NASA. The missions will be initially flown on the Space Transportation System (STS) and subsequently could be conducted in connection with the utilization of a Space Station on Space Platform. One of the missions involves the use of a large antenna system designed to significantly extend the aperture synthesis technique of earth-based very long baseline interferometry technique (orbiting VLBI). It has been recommended that a space VLBI antenna be launched in low earth orbit during this decade. Another mission considered is related to the Advanced Solar Observatory (ASO). ASO is a long duration space observatory. It will consist of four major instrument groupings including a High Resolution Solar Telescope Cluster (HRSTC), a Pinhole Occulter Facility, a Solar High Energy Facility, and a Solar Low Frequency Radio Facility. Attention is also given to a new program entitled Capabilities for Opportunity Payload Experiments (COPE).

De Sanctis, C. E.↗
NASA NTRS1985

STS payload ground handling mechanism at John F. Kennedy Space Center

The payload ground handling mechanism (PGHM), which lifts payloads out of the payload canister that brings them to the launch pad, is described. The PGHM then loads the payloads into the orbiter through the open payload bay doors. The challenge was to provide this capability in time for space shuttle mission 31-A. Meeting this STS requirement was considerably more challenging than using the stacking method for loading payloads on top of expendable vehicles. The new mechanism and its main features are discussed.

Cassisi, V.↗
NASA NTRS1985

Space Transportation System (STS) propellant scavenging system study. Volume 1: Technical report

The objectives are to define the most efficient and cost effective methods for scavenging cryogenic and storable propellants and then define the requirements for these scavenging systems. For cryogenic propellants, scavenging is the transfer of propellants from the Shuttle orbiter external tank (ET) and/or main propulsion subsystems (MPS) propellant lines into storage tanks located in the orbiter payload bay for delivery to the user station by a space based transfer stage or the Space Transportation System (STS) by direct insertion. For storable propellants, scavenging is the direct transfer from the orbital maneuvering subsystem (OMS) and/or tankage in the payload bay to users in LEO as well as users in the vicinity of the Space Station.

Source record↗