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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 631 records · Page 35
All sourcesNASA NTRSDOE OSTI
NASA NTRS1982

KSC ground support operations and equipment for the space transportation system

A significant element of the Kennedy Space Center's ground support equipment for the Space Shuttle is the Launch Processing System, which provides a high level of automation for all operations, including the checkout of the Orbiter, Solid Rocket Boosters, and External Tank. Other direct support elements of the Ground Support Equipment accomplish environmental conditioning, provide and control power, gases, and fluids, and supply vehicle facility and personnel fire protection. Attention is given to the prelaunch functions of the Launch Control Center's Firing Rooms, which contain minicomputers, a data recording area, the Hardware Interface Modules, a Common Data Buffer, and Front End Processors.

Utsman, T. E.↗
NASA NTRS1982

STS cargo processing at the Kennedy Space Center

Space Shuttle-related payload processing operations at the Kennedy Space Center have resulted in a major increase in the number of items being simultaneously processed, with two or more intermediate spacecraft being prepared, along with several smaller payload items, for launch on the same mission. When full operational status is achieved, some elements of three or more Space Shuttle flight cargoes will undergo processing at the Center simultaneously. It is also expected that long lead time items will often arrive earlier than those requiring a shorter checkout span. These and other complications due to the progressive increase in the scale of operations have prompted facility modifications, new operational procedures, and advance planning.

Rock, W. H.↗
NASA NTRS1984

A review of recent developments in flight test techniques at the Ames Research Center, Dryden Flight Research Facility

New flight test techniques in use at Ames Dryden are reviewed. The use of the pilot in combination with ground and airborne computational capabilities to maximize data return is discussed, including the remotely piloted research vehicle technique for high-risk testing, the remotely augmented vehicle technique for handling qualities research, and use of ground computed flight director information to fly unique profiles such as constant Reynolds number profiles through the transonic flight regime. Techniques used for checkout and design verification of systems-oriented aircraft are discussed, including descriptions of the various simulations, iron bird setups, and vehicle tests. Some newly developed techniques to support the aeronautical research disciplines are discussed, including a new approach to position-error determination, and the use of a large skin friction balance for the measurement of drag caused by various excrescencies.

Layton, G. P.↗
NASA NTRS1984

Operational modules for space station construction

Identification of an effective space construction concept is a current objective of NASA studies. One concept, described in this memorandum, consists of repetitive use of operational modules, which minimizes on-orbit stay time for the shuttle. A space station constructed of operational modules may benefit from fabrication and system checkout in ground-based facilities, and since the modules are the primary structure of the space station, a minimum of additional structure, and trips and on-orbit stay time of the shuttle are required.

Jackson, L. R.↗
NASA NTRS1984

Operational experience with the National Transonic Facility

Construction of the National Transonic Facility was completed in September 1982. The checkout of all systems required about one year. The facility operated to the design point of 120 million Reynolds number based on a 0.25 meter chord at a Mach number of 1.0. Performance of all systems was basically as expected. Setup for the detailed aerodynamic calibration begins late in 1983, and the calibration is expected to be complete by the last quarter of 1984.

Mckinney, L. W.↗
NASA NTRS1983

Flat-plate solar array project: Experimental process system development unit for producing semiconductor-grade silicon using the silane-to-silicon process

The process technology for the manufacture of semiconductor-grade silicon in a large commercial plant by 1986, at a price less than $14 per kilogram of silicon based on 1975 dollars is discussed. The engineering design, installation, checkout, and operation of an Experimental Process System Development unit was discussed. Quality control of scaling-up the process and an economic analysis of product and production costs are discussed.

Source record↗
NASA NTRS1984

Reflight certification software design specifications

The PDSS/IMC Software Design Specification for the Payload Development Support System (PDSS)/Image Motion Compensator (IMC) is contained. The PDSS/IMC is to be used for checkout and verification of the IMC flight hardware and software by NASA/MSFC.

Source record↗
NASA NTRS1984

Computer Aided Modeling and Post Processing with NASTRAN Analysis

Computer aided engineering systems are invaluable tools in performing NASTRAN finite element analysis. These techniques are implemented in both the pre-processing and post-processing phases of the NASTRAN analysis. The finite element model development, or pre-processing phase, was automated with a computer aided modeling program called Supertabl, and the review and interpretation of the results of the NASTRAN analysis, or post-processing phase, was automated with a computer aided plotting program called Output Display. An intermediate program, Nasplot, which was developed in-house, has also helped to cut down on the model checkout time and reduce errors in the model. An interface has been established between the finite element computer aided engineering system and the Learjet computer aided design system whereby data can be transferred back and forth between the two. These systems have significantly improved productivity and the ability to perform NASTRAN analysis in response to product development requests.

Boroughs, R. R.↗
NASA NTRS1983

Automated control and data acquisition for a tunable diode laser heterodyne spectrometer

This paper describes the hardware and software design, development, and implementation of the control and data electronics of a laser heterodyne spectrometer instrument being built at NASA Langley Research Center for a technology demonstration. Functional partitioning, applied at all levels of hardware and software, has been found to provide expedient design, development, and testing of the instrument. The instrument is composed of distributed microprocessor-based units. A master/slave protocol is presented which can be simulated by a terminal for unit checkout. All but one of the units are implemented using a set of core boards, plus unique boards where necessary. This design has led to reduced hardware development, reduced parts inventory, and replication of software modules, while providing the flexibility needed for a development instrument. The development tools and documentation guidelines are discussed.

Shull, T. S.↗
NASA NTRS1983

Payload/cargo processing at the launch site

Payload processing at Kennedy Space Center is described, with emphasis on payload contamination control. Support requirements are established after documentation of the payload. The processing facilities feature enclosed, environmentally controlled conditions, with account taken of the weather conditions, door openings, accessing the payload, industrial activities, and energy conservation. Apparatus are also available for purges after Orbiter landing. The payloads are divided into horizontal, vertical, mixed, and life sciences and Getaway Special categories, which determines the processing route through the facilities. A canister/transport system features sealed containers for moving payloads from one facility building to another. All payloads are exposed to complete Orbiter bay interface checkouts in a simulator before actually being mounted in the bay.

Ragusa, J. M.↗
NASA NTRS1983

Launch processing for Spacelab 1

The final integration of Spacelab payloads with the Shuttle is described. Attention is given to launch processing planning, schedules, quality control, and problem reports and configuration maintenance. Also covered are the integration and checkout of individual and combined experiments, mounting the end cones, attachment of the transfer tunnel, and inclusion of an extra experiments pallet. The entire Spacelab module was subjected to a full systems simulation before deliverance to the Orbiter bay. Modular parts that were transferred from building-to-building were placed in sealed containers filled with a purged atmosphere during transport.

Mcbrayer, R. O.↗
NASA NTRS1983

Launch operations of the SSME

The mission profile, performance over the first eight flights, and inspection and repair procedures for the Shuttle main engines (SSME) are outlined. The Orbiter has three SSMEs, each delivering 470,000 lb thrust at rated level and 512,000 lb thrust at full power level. The engines each have a design lifetime of 55 launches and 27,000 sec operating life. After eight STS flights the SSME maintenance requirements and part replacements have generally followed those experiences during ground tests, i.e., routine checkout of some items are performed every flight, some after a few flights, and replacements are made as needed or scheduled. Hot-fire tests are performed only if a generic defect has been recognized and corrective action taken. Attention is also given to engine sensors to verify functioning status. Details of the inspection procedures, unscheduled maintenance, and inspection tools and instruments are provided.

Klatt, F. P.↗
NASA NTRS1983

Development of the Space Shuttle main engine

The history of the development, certification, and launch operations of the Space Shuttle Main Engine is described. Development problems and their solutions are discussed. Ground testing at both rated and full power levels involving four engines and eight certification test cycles totalling more than 40,000 seconds of hot-fire testing, which qualified both Columbia's and Challenger's engines for flight, are discussed. Ground checkout and flight performance of Columbia's and Challenger's engines are revealed. Future plans for the Space Shuttle Main Engine are outlined including flight certification testing to verify a life of 40 flights and 20,000 seconds operation before overhaul.

Klatt, F. P.↗
NASA NTRS1982

Development of satellite position location system for aircraft and boat distress beacons

An international satellite system for the detection and location of distress beacons carried on aircraft and vessels is in its technical checkout phase. User demonstration and evaluation (D&E) will start in early 1983 and continue for two years. The D&E phase and a subsequent transition period will form the basis for improved search and rescue operations for the 1980's and beyond. The system, called COSPAS/SARSAT, has international participation involving the U.S., Canada, and France as SARSAT members and joint participation with the Soviet Union's COSPAS Project. Norway and the U.K. have recently joined as investigators. Average position location error of the satellite aided processing is expected to be from 10-20KM for the existing 121.5/243 MHz distress beacons and from 2-5KM for experimental beacons transmitting in the 406 MHz band.

Kahle, D. R.↗
NASA NTRS1984

Initial research program for the National Transonic Facility

The construction and checkout of the National Transonic Facility (NTF) have been completed, and detailed calibration is now in progress. The initial NTF research program covers a wide range of study areas falling into three major elements: (1) the assessment of Reynolds number sensitivities for a broad range of configurations and flow phenomena; (2) validation of the ability of NTF to simulate full-scale aerodynamics; and (3) the development of test techniques for improved test simulations in existing wind tunnels. This paper, therefore, is a status report on these various elements of the initial NTF research program.

Gloss, B. B.↗
NASA NTRS1983

Measurement of reach envelopes with a four-camera Selective Spot Recognition (SELSPOT) system

The basic Selective Spot Recognition (SELSPOT) system is essentially a system which uses infrared LEDs and a 'camera' with an infrared-sensitive photodetector, a focusing lens, and some A/D electronics to produce a digital output representing an X and Y coordinate for each LED for each camera. When the data are synthesized across all cameras with appropriate calibrations, an XYZ set of coordinates is obtained for each LED at a given point in time. Attention is given to the operating modes, a system checkout, and reach envelopes and software. The Video Recording Adapter (VRA) represents the main addition to the basic SELSPOT system. The VRA contains a microprocessor and other electronics which permit user selection of several options and some interaction with the system.

Stramler, J. H., Jr.↗
NASA NTRS1985

Shuttle avionics software trials, tribulations and success

The early problems and the solutions developed to provide the required quality software needed to support the space shuttle engine development program are described. The decision to use a programmable digital control system on the space shuttle engine was primarily based upon the need for a flexible control system capable of supporting the total engine mission on a large complex pump fed engine. The mission definition included all control phases from ground checkout through post shutdown propellant dumping. The flexibility of the controller through reprogrammable software allowed the system to respond to the technical challenges and innovation required to develop both the engine and controller hardware. This same flexibility, however, placed a severe strain on the capability of the software development and verification organization. The overall development program required that the software facility accommodate significant growth in both the software requirements and the number of software packages delivered. This challenge was met by reorganization and evolution in the process of developing and verifying software.

Henderson, O. L.↗
NASA NTRS1985

Shuttle avionics software development trials: Tribulations and successes, the backup flight system

The development and verification of the Backup Flight System software (BFS) is discussed. The approach taken for the BFS was to develop a very simple and straightforward software program and then test it in every conceivable manner. The result was a program that contained approximately 12,000 full words including ground checkout and the built in test program for the computer. To perform verification, a series of tests was defined using the actual flight type hardware and simulated flight conditions. Then simulated flights were flown and detailed performance analysis was conducted. The intent of most BFS tests was to demonstrate that a stable flightpath could be obtained after engagement from an anomalous initial condition. The extention of the BFS to meet the requirements of the orbital flight test phase is also described.

Chevers, E. S.↗