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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.

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At least 721 records · Page 40
All sourcesNASA NTRSDOE OSTI
NASA NTRS1980

Safety of liquid propulsion systems for STS payloads

STS payload safety requirements for Earth-storable liquid propulsion systems are reviewed with respect to applicable safety documents. The effect of normal flight and emergency landing/abort launch profiles on propulsion system design is delineated. Spacecraft studied include Earth satellites, interplanetary spacecraft, and orbit transfer vehicles. Safety considerations for monopropellant (hydrazine), bipropellant (nitrogen tetroxide/monomethyl hydrazine), and ion (mercury) propulsion systems are described. Safety requirements for specific components of propulsion systems are reported. Analysis techniques for STS payload fracture control requirements for pressure vessels and critical support structure are discussed.

Lewis, J. C.↗
NASA NTRS1981

Payload retention latches for the shuttle orbiter

Two latches were designed to mount payloads in the shuttle orbiter bay. Multiple retention latches attach a payload to the sill longerons and another latch device attaches it to the keel. Requirements for each actuator are defined and drive mechanisms are described. Other design aspects discussed include: switch mechanisms, motors, gearboxes, redundancy provisions, structural materials, and lubricants. A preliminary dry lubricant test program is also reviewed and results presented.

Renken, R. D.↗
NASA NTRS1981

A new payload integration method

This paper introduces a new payload integration method. The system equations of motion are derived in terms of interface-restrained booster and payload modes. These system equations are directly integrated, avoiding the solution of an expensive eigenvalue problem. A modified Newmark-Chan-Beta numerical scheme is used to perform this integration. Due to the unique form of the system equations it is possible to achieve significant savings. A similar savings is feasible for the computation of the internal loads. This new approach does not involve approximations. Although completely general, the presented technique is most effective when the number of interface degrees of freedom is relatively small. Both determinate and indeterminate interfaces are allowed.

Engels, R. C.↗
NASA NTRS1980

Applications of Spacelab Payload Standard Modular Electronics /SPSME/

The NASA sponsored Spacelab Payload Standard Modular Electronics program has been designed with the basic objective of providing a space-qualified set of standardized modular electronics to support investigations identified for Spacelab payloads. These units are reusable, have functional, physical, and interface characteristics which allow them to be conveniently assembled in a multitude of configurations, and functionally interchangeable with their ground-based equivalents. The interfacing and control modules are described and typical hardware applications are presented.

Wilkinson, D. D.↗
NASA NTRS1981

Effects of the specular Orbiter forward radiators on a typical Spacelab payload thermal environment

Orbiter radiators, having a specular reflection, must be considered when determining the design environment for payloads which can view the forward deployed radiators. Unlike most surfaces on the Orbiter, which reflect energy diffusely, the radiators are covered with a highly specular silverized Teflon material, with high emissivity, and have a concave contour, producing a local concentration of reflected energy towards the region of angle incidence. The combined effects of radiator specularity and geometry were analyzed using the Thermal Radiation Analysis System (TRASYS II), a specialized ray trace program, and a generalized Monte-Carlo-based thermal radiation program. Data given for a 0 deg payload inclination angle at orbital noon at 3.454 m indicate that the maximum total flux and average flux can increase 173% and 63%, respectively, when compared to diffuse radiators.

Turner, L. D.↗
NASA NTRS1982

Dynamic environments for space shuttle payloads

Payload bay dynamic data from the first two space shuttle flights are summarized and evaluated. Development of dynamic environment design and test criteria for shuttle payloads from measured flight data is discussed. Factors that must be considered are flight to flight variations, spatial variations, temporal variations, measurement bias errors and the degree of confidence desired that a predicted environment will not be exceeded in flight. Summary and conclusion reports will be published after STS-4 and at appropriate intervals thereafter. The nature of these future reports and their impact on the user community is discussed.

Kern, D. L.↗
NASA NTRS1982

An evaluation of Space Shuttle STS-1 payload bay acoustic data and comparison with predictions

During the first launch (STS-1) of the Space Shuttle orbiter vehicle, sound pressure levels were measured at several locations in the payload bay of the vehicle and on the exterior surface. The data were obtained in order to provide validation for prediction procedures for interior and exterior sound pressure levels and to determine, independently, the acoustic environment in the payload bay during actual launch conditions.

Wilby, J. F.↗
NASA NTRS1982

OSTA-1 - The Space Shuttle's first scientific payload

The capabilities of the first Space Shuttle scientific payload for remote sensing observations of the earth are evaluated, and the instruments used are from the Office of Space and Terrestrial Applications (OSTA-1). The payload gathered 10 million square kilometers of data over the earth's oceans, 6 million square kilometers of data over land masses, and global atmospheric data on carbon monoxide concentration. Shuttle imaging radar collected data over a 10,000 km sweep from Spain to Australia, a Shuttle multispectral infrared radiometer obtained 400,000 ten-channel spectra in clear weather conditions over four continents, and the Ocean Color Experiment detected water color for interpretation of major water constituents. The mission is considered to be a success based on the amount of data collected, and scientific and technical insight gained for the development of Shuttle flight instruments.

Moore, J. W.↗
NASA NTRS1982

Far ultraviolet wide field imaging with a SPARTAN /Experiment of Opportunity/ Payload

A wide-field electrographic Schmidt camera, sensitive in the far UV (1230-2000 A), has been developed and utilized in three sounding rocket flights. It is now being prepared for Shuttle flight as an Experiment of Opportunity Payload (EOP) (recently renamed as the SPARTAN program). In this paper, we discuss (1) design of the instrument and payload, particularly as influenced by our experience in rocket flights; (2) special problems of EOP in comparison to sounding rocket missions; (3) relationship of this experiment to, and special capabilities in comparison to, other space astronomy instruments such as Space Telescope; and (4) a tentative observing plan for an EOP mission.

Carruthers, G. R.↗
NASA NTRS1982

Development and flight tests of a new middle atmosphere electric field payload

There has been a marked increase of scientific interest in middle atmosphere electrodynamics in recent years. This region, which encompasses the stratosphere and mesosphere, has generally been considered relatively passive, electrically. Attempts at in-situ electric field measurements throughout this region can only be accomplished by the use of sounding rockets. A series of middle atmosphere electrodynamic rocket flights have been conducted using a new electric field subpayload. This new payload is capable of measuring all three components of the vector electric field using the symmetric double probe technique. In six flight attempts, the subpayload has performed well and obtained E-field data on five flights. It has been successfully utilized in a mother-daughter configuration and as a stand-alone payload. The flight results have established the existence of large mesospheric electric fields, supporting previous results from single axis measurements.

Gurkin, L. W.↗
NASA NTRS1982

GAS Verification Payload - From concept through flight

The GAS Verification Payload (GVP), successfully flown on STS-3, was the forerunner of the Get Away Special class of payloads. Intended to provide GAS experiments with flight environmental information, it also served to shape out the GAS support systems and establish areas of programmatic understanding between the GSFC, JSC, and KSC. Originally envisaged as using a sounding rocket build-it, test-it, fly-it approach with minimum paperwork, this naivete dissipated when faced with the manned space flight world of JSC. What evolved was an understanding by both disciplines that safety and reliability could be achieved at lower cost without compromise.

Hudgins, J. I.↗
NASA NTRS1982

Mission analysis techniques for attached Shuttle payloads

Visibility times, i.e., times which desired targets are visible to a payload, are examined for attached Shuttle payloads. These times are affected by a number of constraints. Some constraints are examined along with mathematical or computer modeling techniques used to determine their effects. The constraints include: occultation of the earth, moon, and sun, and limb avoidance angles of each; orbit parameters such as inclination and ascending node, along with sensitivity to changes in each; TDRSS acquisition; South Atlantic Anomaly (SAA) avoidance, nighttime viewing only; bright earth avoidance angles; the field of view; Shuttle attitude, and Orbiter operational constraints. All of this information is integrated and, with computer programs, a schedule of observations and Shuttle attitudes is obtained.

Lambros, S.↗
NASA NTRS1981

Structural dynamics payload loads estimates

The development of a full scale payload integration method which reduces the cost of a load cycle and is capable of land long very large systems is discussed. The method solves the coupled booster/payload system equations and does not involve additional approximations as compared to the standard transient analysis. The method is cost effective and directly applicable to the shuttle payload design case.

Engels, R. C.↗
NASA NTRS1982

Evaluation of Space Transportation System (STS) OV-102 orbiter payload bay acoustic environment

This report presents the results of a statistical analysis and evaluation performed by the Mechanical Engineering Branch (Code 731) on the payload bay internal acoustic data measured on the STS-1 through STS-4 flights. The results are used as a basis for developing the required baseline acoustic environment specification to be used in establishing design and test criteria for STS payloads and components.

On, F. J.↗
NASA NTRS1982

LANDSAT-D accelerated payload correction subsystem output computer compatible tape format

The NASA GSFC LANDSAT-D Ground Segment (GS) is developing an Accelerated Payload Correction Subsystem (APCS) to provide Thematic Mapper (TM) image correction data to be used outside the GS. This correction data is computed from a subset of the TM Payload Correction Data (PCD), which is downlinked from the spacecraft in a 32 Kbps data stream, and mirror scan correction data (MSCD), which is extracted from the wideband video data. This correction data is generated in the GS Thematic Mapper Mission Management Facility (MMF-T), and is recorded on a 9-track 1600 bit per inch computer compatible tape (CCT). This CCT is known as a APCS Output CCT (AOT). The AOT follows standardized corrections with respect to data formats, record construction and record identification. Applicable documents are delineated; common conventions which are used in further defining the structure, format and content of the AOT are defined; and the structure and content of the AOT are described.

Source record↗
NASA NTRS1981

LANDSAT-D data format control book. Volume 5: (Payload)

The LANDSAT-D flight segment payload is the thematic mapper and the multispectral scanner. Narrative and visual descriptions of the LANDSAT-D payload data handling hardware and data flow paths from the sensing instruments through to the GSFC LANDSAT-D data management system are provided. Key subsystems are examined.

Andrew, H.↗