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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 469 records · Page 26
All sourcesNASA NTRSDOE OSTI
NASA NTRS1971

The Unified S-band Ground System.

This paper describes how the design of the Unified S-band Ground System evolved from the technology available in the NASA's Deep Space Network and Scientific Satellite Network as well as the Manned Space Flight Network to fulfill the requirements of the Apollo program. The project organization established for this program proved to be an effective management technique for controlling the widely dispersed activities and maintaining the necessary liaison with other organizations involved in the overall program. The Manned Space Flight Network includes systems at three locations employing 26 meter antennas to support the lunar phases of the mission and a number of systems at other locations employing 9 meter antennas for support of the near earth phases of the mission. The tradeoffs of mission requirements and technical capability established the equipment parameters and the network configuration. An extensive checkout program which included the use of aircraft and spacecraft provided a thorough evaluation of the system prior to its commitment to operational support of the missions.

Varson, W. P.↗
NASA NTRS1972

LSI computer fabrication - SUMC/DV.

The SUMC/DV (Space Ultrareliable Modular Computer Demonstration Vehicle), which required the design and fabrication of ten different array types, was designed, partitioned, assembled, tested, and made completely operational in less than one year. This paper describes the assembly, the physical and electrical characteristics, and the basic electrical testing procedures used on SUMC/DV. The paper includes a description of the packaging concepts, the physical assembly, the fabrication and testing of the various components including the LSI/CMOS arrays, the hierarchy of the memory complement, the clock generation and distribution scheme, additional system testing techniques, and the procedure employed in the electrical checkout of the system.

Feller, A.↗
NASA NTRS1973

The Launch Processing System for Space Shuttle.

In order to reduce costs and accelerate vehicle turnaround, a single automated system will be developed to support shuttle launch site operations, replacing a multiplicity of systems used in previous programs. The Launch Processing System will provide real-time control, data analysis, and information display for the checkout, servicing, launch, landing, and refurbishment of the launch vehicles, payloads, and all ground support systems. It will also provide real-time and historical data retrieval for management and sustaining engineering (test records and procedures, logistics, configuration control, scheduling, etc.).

Springer, D. A.↗
NASA NTRS1973

Orbiting Astronomical Observatory heat pipe flight performance data.

The paper describes preflight and inflight performance checkout of the three isothermalizer heat pipes onboard the OAO-C spacecraft. The three pipes are: an axially grooved pipe, a pedestal artery pipe, and a self-priming spiral artery pipe. All pipes are 1/2-inch diameter tube rolled into a 48-inch diameter hoop. They are constructed of aluminum and use ammonia as working fluid. Periodic inflight performance checks have been made since launch in August 1972. No degradation in performance of any of the pipes has been detected. The flight data are in excellent agreement with ground test data.

Harwell, W.↗
NASA NTRS1973

Some considerations for Space Tug launch site support operations.

The study reported was undertaken to investigate the requirements placed on the Space Tug by the ground operations. On the basis of the results obtained, it will be possible to consider in future Tug systems studies the full spectrum of both ground and flight operations requirements in defining selected Tug configurations. The central core of the study consists of a functional analysis of ground operations during the Tug turnaround. Electronic system studies were initiated concurrently with the functional analysis study phase to evaluate interrelationships between ground and vehicle checkout and fault isolation capability.

Heald, D. A.↗
NASA NTRS1973

Payloads.

Approaches to payload definition, design, and planning adopted in the Space Shuttle Program are described. The Space Shuttle offers many new modes of operation featuring reuse of spacecraft, on-orbit checkout and maintenance, sortie experiment missions, and opportunities to trade launch weight and volume for cost savings. In order to take advantage of these new approaches and to accommodate the varying missions, new payload elements have been identified, and new low-cost design approaches are being developed to utilize standardized components and modularized subassemblies that reduce spacecraft buildup and maintenance costs. A new payload planning technique makes use of the computer to provide large-scale planning, scheduling, and costing required for various program options.

Marshall, W. R.↗
NASA NTRS1973

Skylab SO71/SO72 circadian periodicity experiment

The circadian rhythm hardware activities from 1965 through 1973 are considered. A brief history of the programs leading to the development of the combined Skylab SO71/SO72 Circadian Periodicity Experiment (CPE) is given. SO71 is the Skylab experiment number designating the pocket mouse circadian experiment, and SO72 designates the vinegar gnat circadian experiment. Final design modifications and checkout of the CPE, integration testing with the Apollo service module CSM 117 and the launch preparation and support tasks at Kennedy Space Center are reported.

Fairchild, M. K.↗
NASA NTRS1973

Ground Operations Aerospace Language (GOAL). Volume 3: Data bank

The GOAL (Ground Operations Aerospace Language) test programming language was developed for use in ground checkout operations in a space vehicle launch environment. To insure compatibility with a maximum number of applications, a systematic and error-free method of referencing command/response (analog and digital) hardware measurements is a principle feature of the language. Central to the concept of requiring the test language to be independent of launch complex equipment and terminology is that of addressing measurements via symbolic names that have meaning directly in the hardware units being tested. To form the link from test program through test system interfaces to the units being tested the concept of a data bank has been introduced. The data bank is actually a large cross-reference table that provides pertinent hardware data such as interface unit addresses, data bus routings, or any other system values required to locate and access measurements.

Source record↗
NASA NTRS1973

Shuttle mission simulator requirements report, volume 1, revision C

The contractor tasks required to produce a shuttle mission simulator for training crew members and ground personnel are discussed. The tasks will consist of the design, development, production, installation, checkout, and field support of a simulator with two separate crew stations. The tasks include the following: (1) review of spacecraft changes and incorporation of appropriate changes in simulator hardware and software design, and (2) the generation of documentation of design, configuration management, and training used by maintenance and instructor personnel after acceptance for each of the crew stations.

Burke, J. F.↗
NASA NTRS1974

Spacelab data management subsystem phase B study

The Spacelab data management system is described. The data management subsystem (DMS) integrates the avionics equipment into an operational system by providing the computations, logic, signal flow, and interfaces needed to effectively command, control, monitor, and check out the experiment and subsystem hardware. Also, the DMS collects/retrieves experiment data and other information by recording and by command of the data relay link to ground. The major elements of the DMS are the computer subsystem, data acquisition and distribution subsystem, controls and display subsystem, onboard checkout subsystem, and software. The results of the DMS portion of the Spacelab Phase B Concept Definition Study are analyzed.

Source record↗
NASA NTRS1973

Liquid rocket valve assemblies

The design and operating characteristics of valve assemblies used in liquid propellant rocket engines are discussed. The subjects considered are as follows: (1) valve selection parameters, (2) major design aspects, (3) design integration of valve subassemblies, and (4) assembly of components and functional tests. Information is provided on engine, stage, and spacecraft checkout procedures.

Source record↗
NASA NTRS1974

Multi-kw dc power distribution system study program

The first phase of the Multi-kw dc Power Distribution Technology Program is reported and involves the test and evaluation of a technology breadboard in a specifically designed test facility according to design concepts developed in a previous study on space vehicle electrical power processing, distribution, and control. The static and dynamic performance, fault isolation, reliability, electromagnetic interference characterisitics, and operability factors of high distribution systems were studied in order to gain a technology base for the use of high voltage dc systems in future aerospace vehicles. Detailed technical descriptions are presented and include data for the following: (1) dynamic interactions due to operation of solid state and electromechanical switchgear; (2) multiplexed and computer controlled supervision and checkout methods; (3) pulse width modulator design; and (4) cable design factors.

Berkery, E. A.↗
NASA NTRS1974

The use of an aircraft test stand for VTOL handling qualities studies

The VTOL flight tests stand for testing control concepts on the X-14B VSS aircraft in hover, is described. This stand permits realistic and safe piloted evaluation and checkout of various control systems and of parameter variations within each system to determine acceptability to the pilot. Pilots can use it as a practical training tool to practice procedures and flying techniques and become familiar with the aircraft characteristics. Some examples of test experience are given. The test stand allows the X14B to maneuver in hover from centered position + or - 9.7 deg in roll and + or - 9.3 deg in pitch, about + or - 6 deg in yaw, and + or - 15 cm in vertical translation. The unique vertical free flight freedom enables study of liftoffs and landings with power conditions duplicated. The response on the stand agrees well with that measured in free hovering flight, and pilot comments confirm this.

Pauli, F. A.↗
NASA NTRS1974

Users guide for information retrieval using APL

A Programming Language (APL) is a precise, concise, and powerful computer programming language. Several features make APL useful to managers and other potential computer users. APL is interactive; therefore, the user can communicate with his program or data base in near real-time. This, coupled with the fact that APL has excellent debugging features, reduces program checkout time to minutes or hours rather than days or months. Of particular importance is the fact that APL can be utilized as a management science tool using such techniques as operations research, statistical analysis, and forecasting. The gap between the scientist and the manager could be narrowed by showing how APL can be used to do what the scientists and the manager each need to do, retrieve information. Sometimes, the information needs to be retrieved rapidly. In this case APL is ideally suited for this challenge.

Shapiro, A.↗
NASA NTRS1974

Skylab thruster attitude control system

Preflight activities and the Skylab mission support effort for the thruster attitude control system (TACS) are documented. The preflight activities include a description of problems and their solutions encountered in the development, qualification, and flight checkout test programs. Mission support effort is presented as it relates to system performance assessment, real-time problem solving, flight anomalies, and the daily system evaluation. Finally, the detailed flight evaluation is presented for each phase of the mission using system telemetry data. Data assert that the TACS met or exceeded design requirements and fulfilled its assigned mission objectives.

Wilmer, G. E., Jr.↗
NASA NTRS1974

Asymmetrical booster ascent guidance and control system design study. Volume 2: SSFS math models - Ascent

The engineering equations and mathematical models developed for use in the space shuttle functional simulator (SSFS) are presented, and include extensive revisions and additions to earlier documentation. Definitions of coordinate systems used by the SSFS models and coordinate tranformations are given, along with documentation of the flexible body mathematical models. The models were incorporated in the SSFS and are in the checkout stage.

Williams, F. E.↗
NASA NTRS1974

Analyses of the dynamic docking test system for advanced mission docking system test programs

Results are given of analytical studies performed in support of the design, implementation, checkout and use of NASA's dynamic docking test system (DDTS). Included are analyses of simulator components, a list of detailed operational test procedures, a summary of simulator performance, and an analysis and comparison of docking dynamics and loads obtained by test and analysis.

Gates, R. M.↗