Engineering Papers⌕ Search

SEARCH · Engineering Papers

Results for “repair”

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 973 records · Page 54
All sourcesNASA NTRSDOE OSTI
NASA NTRS1983

A development of logistics management models for the Space Transportation System

A new analytic queueing approach was described which relates stockage levels, repair level decisions, and the project network schedule of prelaunch operations directly to the probability distribution of the space transportation system launch delay. Finite source population and limited repair capability were additional factors included in this logistics management model developed specifically for STS maintenance requirements. Data presently available to support logistics decisions were based on a comparability study of heavy aircraft components. A two-phase program is recommended by which NASA would implement an integrated data collection system, assemble logistics data from previous STS flights, revise extant logistics planning and resource requirement parameters using Bayes-Lin techniques, and adjust for uncertainty surrounding logistics systems performance parameters. The implementation of these recommendations can be expected to deliver more cost-effective logistics support.

Carrillo, M. J.↗
NASA NTRS1984

The role of the Shuttle Engineering Simulator in the Solar Max rescue mission

Background information concerning the makeup of the SES, the role it traditionally plays in support of the Shuttle Program, its capabilities and the specific work performed on the simulator during the sixteen months proceedings the Solar Max repair mission is presented. The SES plays a significant role in the preparations for the STS 41-C Solar Max repair mission and during the mission in the development of the plan and procedures to retrieve the satellite after the MMU docking attempts failed. The development of the on orbit simulation capabilities required to support this mission is to a very large extent simply an expansion of the capabilities designed into the SES to support previous engineering simulation requirements for the Space Shuttle program.

St.john, R. H.↗
NASA NTRS1983

Space station: Policy, planning and utilization; Proceedings of the Symposium, Arlington, VA, July 18-20, 1983

The design, technology, and applications of the proposed Space Station (SS) are examined in contributions and discussions from the AIAA/NASA Symposium on the Space Station held on July 18-20, 1983. The role of man in space, the history of SS concepts, and the requirements of scientists, engineers, and commercial users are reviewed. Discussion is included on military space activities; the Solar Maximum Repair Mission; the role of the SS in earth sciences, life sciences, astronomy and astrophysics, and solar physics; pharmaceutical manufacturing on the SS, satellite and platform maintenance and repair from the SS; international utilization of the SS; SS architectures and user concerns; the SS as an element of the total space-system architecture; productivity on an evolutionary SS, SS information and communications systems; and environmental-control and life-support systems for the SS.

Gerard, M.↗
NASA NTRS1983

The role of man in space

The roles played by astronauts in space missions are discussed using illustrations from the Spacelab and STS experience, and the implications for the proposed space station are considered. Man's ability to perform successfully for relatively long periods in space is demonstrated, and capabilities in manipulation, EVA, equipment repair and compensation for equipment failure, earth observation, astronomy of sun and stars, and laboratory experimentation are characterized and illustrated with photographs. Space station activities planned include repairs (like that of the Solar Maximum Satellite), maintenance (of the Space Telescope), and construction and involve the use of a manned maneuvering unit, a teleoperator maneuvering system, and/or a manned or unmanned OTV.

Lousma, J. R.↗
NASA NTRS1983

Development and evaluation of a fault-tolerant multiprocessor (FTMP) computer. Volume 1: FTMP principles of operation

The basic organization of the fault tolerant multiprocessor, (FTMP) is that of a general purpose homogeneous multiprocessor. Three processors operate on a shared system (memory and I/O) bus. Replication and tight synchronization of all elements and hardware voting is employed to detect and correct any single fault. Reconfiguration is then employed to repair a fault. Multiple faults may be tolerated as a sequence of single faults with repair between fault occurrences.

Smith, T. B., Jr.↗
NASA NTRS1984

Space research in the era of the space station

The historical development of U.S. space technology is examined as a basis for future programs planned in the field of astrophysics, meteorological and land sciences, and planetary exploration. The background of the NASA space station project is described, as well as other current programs: Voyager II for Uranus and Neptune exploration, Galileo mission for sending probes into the Jovian atmosphere, Venus Radar Mapper, Mars Geochemistry and Climatology Orbiter, and the International Solar Polar mission. Recent advances in in-orbit assembly, refurbishment and repairs are discussed through the example of the Solar Maximum mission spacecraft repair in 1984 and the use of the RMS tool. The U.S. space observatory project with a 20-meter reflector telescope, currently in the early definition stage, is also discussed. Finally, the Soviet Salyut and Soyuz missions, together with the Soviet Union's study of long term flight conditions are mentioned as possible comparison with the NASA work.

Frost, K. J.↗
NASA NTRS1986

Hubble Space Telescope meteoroid-debris protection analysis

A system level failure could occur if the Hubble Space Telescope's (ST) capability to operate as a facility on-orbit is critically reduced or when a significant reduction in the quality of science data is registered. Failure could occur if a meteoroid/debris impact damages a component of a major support subsystem or if a meteoroid/debris penetration causes straylight contamination in the light shield, forward shell, aft shroud, or through the aperture door. The ST was analyzed to find the probability of no critical penetration. This probability value was found to be 92.25% for a two-year service life. A straylight leakage repair technique was recommended for the aft shroud, the region found most likely to be critically penetrated. Fozar tape and multilayer insulation blankets are suggested as posible repair materials.

Horn, J.↗
NASA NTRS1986

Point of view of the U.S. science community

A special task force was formed by the National Academy of Sciences to examine the applications of Manned Space Station (MSS) platforms, communications and information systems, MSS operations and satellite assembly and repair capabilities on seven areas of space research. The task force reached several conclusions, including comprehensive space science planning by NASA with the MSS being one element of the plan. The STS is to provide a test bed for space research technologies and its basic design should be studied for conversion to an extended duration flight vehicle. The MSS could be categorized as a national facility, and payloads should be developed which specifically take advantage of its capabilities. The repair and maintenance capabilities which the MSS will furnish are concluded to be a significant asset to any future space science activities, and participation in those activities by the international science community is to be encouraged.

Black, D. C.↗
NASA NTRS1986

Control of a free-flying robot manipulator system

The development of and test control strategies for self-contained, autonomous free flying space robots are discussed. Such a robot would perform operations in space similar to those currently handled by astronauts during extravehicular activity (EVA). Use of robots should reduce the expense and danger attending EVA both by providing assistance to astronauts and in many cases by eliminating altogether the need for human EVA, thus greatly enhancing the scope and flexibility of space assembly and repair activities. The focus of the work is to develop and carry out a program of research with a series of physical Satellite Robot Simulator Vehicles (SRSV's), two-dimensionally freely mobile laboratory models of autonomous free-flying space robots such as might perform extravehicular functions associated with operation of a space station or repair of orbiting satellites. It is planned, in a later phase, to extend the research to three dimensions by carrying out experiments in the Space Shuttle cargo bay.

Alexander, H.↗
NASA NTRS1985

Proceedings of the SMRM Degradation Study Workshop

This publication contains the proceedings of the Solar Maximum Repair Mission Degradation Study Workshop, held at the Goddard Space Flight Center in Greenbelt, Maryland on May 9-10, 1985. The main purpose of the workshop was to report on the results of tests and studies of the returned Solar Maximum Mission hardware and materials. Specifically, the workshop was concerned with studies of the effects of four years exposure to a low-earth orbital environment. A summary of the results reported at the workshop is included in this publication. To provide a background for the reported findings, the summary includes a short description of the Solar Maximum Mission and the Solar Maximum Repair Mission. Some of the papers contained in this publication have been submitted by the participating organizations after the presentations were made at the workshop and may not necessarily have the same title and author/presenter as in the workshop agenda.

Satellite Servicing Project↗
NASA NTRS1985

Failure analysis and performance evaluation of NASA inertial reference unit (DRIRU 2) after 50 months of orbital operation

The first production DRIRU 2 (NASA standard high performance inertial reference unit) system was launched as a subsystem of the Modular Attitude Control System for the Solar Maximum Mission (SMM) spacecraft in February 1980. This hardware was retrieved during the repair of the SMM during Shuttle Flight 41-C in April 1984 and returned to Teledyne Systems Company (manufacturer) for investigation and performance measurements as directed by Goddard Space Flight Center. A failure of one of the three gyro channels occurred approximately 6.5 months after launch. The built in redundancy functioned properly, the DRIRU 2 continued to provide the required attitude control function without performance degradation. Subsequent failure of other attitude control subsystems made the SMM a candidate for the first demonstration of the shuttle in-orbit repair capabilty. The in-orbit DRIRU 2 II failure scenario and the results of the analyses/tests conducted after retrieval are discussed. Comparison of this data with similar data prior to launch demonstates the excellent stability of performance parameters achieveable with DRIRU 2.

Green, K. N.↗
NASA NTRS1985

Solar maximum thermal surface assessment

The inflight repair of the Solar Maximum Spacecraft provided the first opportunity to make actual measurements of thermal control surfaces after 4 years exposure in low Earth orbit. Defective hardware was replaced by astronauts and returned to Earth while protected from reentry damage in the Shuttle Payload bay. A preliminary thermal surface assessment was made soon after retrieval in support of Space Telescope and other current spacecraft programs. This included visual examination and measurement of Kapton and Teflon film to determine change in thermal radiative properties after 4 years exposure to solar radiation and reaction with atomic oxygen. Comparative measurements were made with a portable solar reflectometer used for inspection of spacecraft hardware. Post flight measurements and observations reveal significant surface changes that further confirm Kapton mass loss predictions made prior to Solar Maximum repair. Details of thermal surface application, measurements and experimental results are presented and discussed.

Rhoads, G. D.↗
NASA NTRS1986

Comparison of solar hard X-ray and UV line and continuum bursts with high time resolution

The close temporal correlation between the ultraviolet line emission from OV (lambda 1371A) and hard X-rays above 30 keV has been previously established from a comparison of data sets from the Ultraviolet Spectrometer and Polarimeter (UVSP) and Hard X-Ray Burst Spectrometer (HXRBS) instruments on Solar Maximum Mission (SMM). Corresponding features were found to be coincident to within 1 s. Following the SMM repair, similar measurements were made for a flare occurring on May 20, 1984, at 0259 UT, this time with UVSP observing in the continuum near 1600A with much higher time resolution (75ms). The simultaneity of several features in this flare were established to better than 0.1 s, thus reinforcing the close relationship between hard X-ray and UV emission. Following the repair of the UVSP wavelength drive, similar measurements were repeated for a flare occurring at 0148 UT on April 24, 1985. This event was observed simultaneously in the OV line, the UV continuum and in hard X-rays by the same SMM instruments. Temporal comparisons of the three data sets show that, for a few selected features, simultaneity of the hard X-ray and UV emissions does exist. However, cross-correlation analyses of the entire data sets indicate that there is a trend for the fastest OV emission features to be delayed with respect to the hard X-rays by approx. 260 ms. On the other hand the fast OV and UV continuum features are simultaneous to within the instrumental uncertainty. The combined results have established the close relationship of the impulsive phase hard X-ray and UV continuum and OV line emissions. They lend support to the argument that both the hard X-ray and UV radiations originate low in the solar atmosphere.

Orwig, L. E.↗
NASA NTRS1987

Space station integrated wall design and penetration damage control

A methodology was developed to allow a designer to optimize the pressure wall, insulation, and meteoroid/debris shield system of a manned spacecraft for a given spacecraft configuration and threat environment. The threat environment consists of meteoroids and orbital debris, as specified for an arbitrary orbit and expected lifetime. An overall probability of no penetration is calculated, as well as contours of equal threat that take into account spacecraft geometry and orientation. Techniques, tools, and procedures for repairing an impacted and penetrated pressure wall were developed and tested. These techniques are applied from the spacecraft interior and account for the possibility of performing the repair in a vacuum. Hypervelocity impact testing was conducted to: (1) develop and refine appropriate penetration functions, and (2) determine the internal effects of a penetration on personnel and equipment.

Coronado, A. R.↗
NASA NTRS1986

U.S. experience in satellite servicing and linkage to the Space Station era

A history of on-orbit servicing and repair is given with emphasis placed on the Solar Maximum Repair Mission. The experience gained thus far in on-orbit servicing and the design of the Space Station's servicing capabilities impose the following requirements on users: (1) satellites must have a standard grapple for capture and a standard berthing interface, (2) Space Station safety requirements must meet to preclude damage to the Space Station or injury to the EVA crew, (3) sensitive instruments will need to implement remotely controlled protective devices to prevent damage, and (4) satellite thermal systems must be designed to maintain survival temperatures during transfer from orbit to the Space Station servicing facility.

Browning, R. K.↗
NASA NTRS1987

Shuttle/Centaur G-prime composite adapters damage tolerance/repair test program

The Space Shuttle/Centaur Composite Adapters Damage Tolerance/Repair Test program had as its goals the determination of probable and potentially critical defects or damages on the adapters' strength and stability, as well as the adequacy of repairs on significantly damaged areas and the generation of NDT data for the upgrading of acceptance criteria. Such rational accept/reject criteria and repair methods reduce both engineering liason costs and any unnecessary parts-scrapping. Successful 'damage tolerant' design ensures that degradations of strength and stability due to undetected defects or damage will not be catastrophic.

Sollars, Teresa A.↗
NASA NTRS1988

Space spider crane

A space spider crane for the movement, placement, and or assembly of various components on or in the vicinity of a space structure is described. As permanent space structures are utilized by the space program, a means will be required to transport cargo and perform various repair tasks. A space spider crane comprising a small central body with attached manipulators and legs fulfills this requirement. The manipulators may be equipped with constant pressure gripping end effectors or tools to accomplish various repair tasks. The legs are also equipped with constant pressure gripping end effectors to grip the space structure. Control of the space spider crane may be achieved either by computer software or a remotely situated human operator, who maintains visual contact via television cameras mounted on the space spider crane. One possible walking program consists of a parallel motion walking program whereby the small central body alternatively leans forward and backward relative to end effectors.

Macconochie, Ian O.↗
NASA NTRS1987

Vapor Compression Distillation Subsystem (VCDS) Component Enhancement, Testing and Expert Fault Diagnostics Development, Volume 2

A wide variety of Space Station functions will be managed via computerized controls. Many of these functions are at the same time very complex and very critical to the operation of the Space Station. The Environmental Control and Life Support System is one group of very complex and critical subsystems which directly affects the ability of the crew to perform their mission. Failure of the Environmental Control and Life Support Subsystems are to be avoided and, in the event of failure, repair must be effected as rapidly as possible. Due to the complex and diverse nature of the subsystems, it is not possible to train the Space Station crew to be experts in the operation of all of the subsystems. By applying the concepts of computer-based expert systems, it may be possible to provide the necessary expertise for these subsystems in dedicated controllers. In this way, an expert system could avoid failures and extend the operating time of the subsystems even in the event of failure of some components, and could reduce the time to repair by being able to pinpoint the cause of a failure when one cannot be avoided.

Mallinak, E. S.↗