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Results for “modularization”

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 271 records · Page 15
All sourcesNASA NTRSDOE OSTI
NASA NTRS1977

STS multimission modular spacecraft - A new horizon in social and industrial benefits

Economics and benefits of orbiting observatory Multi-mission Modular Spacecraft are discussed. The Space Shuttle can be used both to place these satellites in low-altitude workhorse orbits and to maintain their functioning in any of three ways - on-orbit service (by visiting the satellite with the Shuttle), Shuttle retrieval and ground refurbishment of the entire satellite, and replacement of a failed satellite with a new one. Individuals could receive information from these satellites either indirectly, by turning to a specialty television station, or directly, by calling up information on their television sets as needed. Such information, for example, might include reconnoitering interesting areas, following the weather, or locating migratory fish. Equipment and costs of the proposed Landsats and Seasats are discussed.

Cepollina, F. J.↗
NASA NTRS1977

Modular control subsystems for use in solar heating systems for multi-family dwellings

Progress in the development of solar heating modular control subsystems is reported. Circuit design, circuit drawings, and printed circuit board layout are discussed along with maintenance manuals, installation instructions, and verification and acceptance tests. Calculations made to determine the predicted performance of the differential thermostat are given including details and results of tests for the offset temperature, and boil and freeze protect points.

Source record↗
NASA NTRS1978

Analysis and design of the Multimission Modular Spacecraft hydrazine propulsion module

The translational velocity increment, stabilization and control requirements, vehicle weight, and geometric considerations of the Multimission Modular Spacecraft (MMS) provided the basic data on which to initiate the analysis and design of the hydrazine propulsion modules. The Landsat D was used as the mission model. Tradeoff studies were conducted on thrust level, thruster location, and clustering arrangement together with tankage volume and location. The impact of the use of single and dual seat thruster valves on plumbing configuration, reliability, and overall system cost was studied in detail. Conceptual designs of a recommended propulsion module configuration for both the Delta 3910 and Shuttle were prepared.

Etheridge, F. G.↗
NASA NTRS1978

NASA standard Multimission Modular Spacecraft for future space exploration

The design of the Multimission Modular Spacecraft (MMS) has evolved over the past seven years. The main objective concerning the design of the MMS has been related to aspects of cost effectiveness. Maximum use was to be made of NASA standard components. The basic concept has been to design a core spacecraft which has inherent flexibility to meet a range of mission needs without modification of its hardware elements. An overview is provided of the MMS performance capability and the current status of the MMS program. The MMS is the first NASA approved active control free-flying spacecraft to be designed to be Shuttle compatible. The design of the MMS is such that no single failure will preclude its retrieval by the Shuttle.

Bartlett, R. O.↗
NASA NTRS1979

Modular solar-heating system - design package

Compilation contains design, performance, and hardware specifications in sufficient detail to fabricate or procure materials and install, operate, and maintain complete modular solar heating and hot water system for single family size dwellings.

Sinton, D. S.↗
NASA NTRS1977

Study of Multimission Modular Spacecraft (MMS) propulsion requirements

The cost effectiveness of various propulsion technologies for shuttle-launched multimission modular spacecraft (MMS) missions was determined with special attention to the potential role of ion propulsion. The primary criterion chosen for comparison for the different types of propulsion technologies was the total propulsion related cost, including the Shuttle charges, propulsion module costs, upper stage costs, and propulsion module development. In addition to the cost comparison, other criteria such as reliability, risk, and STS compatibility are examined. Topics covered include MMS mission models, propulsion technology definition, trajectory/performance analysis, cost assessment, program evaluation, sensitivity analysis, and conclusions and recommendations.

Fischer, N. H.↗
NASA NTRS1977

Multimission modular spacecraft parallel battery tests

An engineering evaluation of the Multimission Modular Spacecraft power supply is presented. The spacecraft has one charger with eight commandable voltage versus temperature levels. Graphs are presented which represent: (1) cell voltage limits vs. temperature; (2) charge ratio vs. temperature; (3) effect of 0.0 percent impedance unbalance at 10 C; (4) shorted cell at 10 C; and (5) discharge voltage profile at 10 C.

Palandati, C.↗
NASA NTRS1978

A modular multiple use system for precise time and frequency measurement and distribution

A modular CAMAC based system is described which was developed to meet a variety of precise time and frequency measurement and distribution needs. The system was based on a generalization of the dual mixer concept. By using a 16 channel 100 ns event clock, the system can intercompare the phase of 16 frequency standards with subpicosecond resolution. The system has a noise floor of 26 fs and a long term stability on the order of 1 ps or better. The system also used a digitally controlled crystal oscillator in a control loop to provide an offsettable 5 MHz output with subpicosecond phase tracking capability. A detailed description of the system is given including theory of operation and performance. A method to improve the performance of the dual mixer technique is discussed when phase balancing of the two input ports cannot be accomplished.

Reinhardt, V. S.↗
NASA NTRS1978

Modular on-board adaptive imaging

Feature extraction involves the transformation of a raw video image to a more compact representation of the scene in which relevant information about objects of interest is retained. The task of the low-level processor is to extract object outlines and pass the data to the high-level process in a format that facilitates pattern recognition tasks. Due to the immense computational load caused by processing a 256x256 image, even a fast minicomputer requires a few seconds to complete this low-level processing. It is, therefore, necessary to consider hardware implementation of these low-level functions to achieve real-time processing speeds. The considered project had the objective to implement a system in which the continuous feature extraction process is not affected by the dynamic changes in the scene, varying lighting conditions, or object motion relative to the cameras. Due to the high bandwidth (3.5 MHz) and serial nature of the TV data, a pipeline processing scheme was adopted as the overall architecture of this system. Modularity in the system is achieved by designing circuits that are generic within the overall system.

Eskenazi, R.↗
NASA NTRS1978

Testing programs for the Multimission Modular Spacecraft

The Multimission Modular Spacecraft (MMS) provides a standard spacecraft bus to a user for a variety of space missions ranging from near-earth to synchronous orbits. The present paper describes the philosophy behind the MMS module test program and discusses the implementation of the test program. It is concluded that the MMS module test program provides an effective and comprehensive customer buy-off at the subsystem contractor's plant, is an optimum approach for checkout of the subsystems prior to use for on-orbit servicing in the Shuttle Cargo Bay, and is a cost-effective technique for environmental testing.

Greenwell, T. J.↗
NASA NTRS1981

Versatile modular scaffolds

Movable and fixed modular scaffolds can be tailored to most scaffolding needs by interconnecting only 4 basic structural elements: platforms, rails, vertical-support angles, and stiffener. Standard nuts and bolts are used to join elements, simplifying construction, and reducing costs. Scaffolds are rigid and can be made any length. They are stable on unlevel ground and can extend to well over 50 feet in height. Scaffolds allow for internal elevators and for wheels and air mounts so that same elements can be used for standing or movable scaffold.

Kerley, J.↗
NASA NTRS1980

Design of a modular digital computer system

A Central Control Element (CCE) module which controls the Automatically Reconfigurable Modular System (ARMS) and allows both redundant processing and multi-computing in the same computer with real time mode switching, is discussed. The same hardware is used for either reliability enhancement, speed enhancement, or for a combination of both.

Source record↗
NASA NTRS1982

Modular Engine Instrumentation System

System that provides information and measurements never obtained before in real time has been developed. System shows not only real-time measurements but also results of computations of key combustion parameters in meaningful and easily understood display. Standard commercially-available shaft encoder plus data from pressure transducer act as principal drivers to device. Eventually, modular system could be developed into onboard controller for automobile engines.

Rice, W. J.↗
NASA NTRS1980

Modular missile borne computers

The modular missile borne computer's architecture with emphasis on how that architecture evolved is discussed. A careful analysis is given of both the physical constraints and the processing requirements.

Ramseyer, R.↗
NASA NTRS1980

Modular space structures

The Extendable Tetrahedral Truss orbiting antenna concept, comprising the use of prefabricated, automatically deployable lattice structures and their subsequent assembly into larger structures suitable for microwave antenna use, is described. It is assumed that the Space Shuttle Orbiter payload bay will be able to accommodate only modular portions of the structural system required, and that the Space Shuttle crew will furnish the manual labor entailed by orbital assembly. It is concluded that a deployable beam module system may be a more elegant design solution than the alternative triangular-module system.

Vaughan, D. H.↗
NASA NTRS1981

Modular hardware synthesis using an HDL

Although hardware description languages (HDL) are becoming more and more necessary to automated design systems, their application is complicated due to the difficulty in translating the HDL description into an implementable format, nonfamiliarity of hardware designers with high-level language programming, nonuniform design methodologies and the time and costs involved in transfering HDL design software. Digital design language (DDL) suffers from all of the above problems and in addition can only by synthesized on a complete system and not on its subparts, making it unsuitable for synthesis using standard modules or prefabricated chips such as those required in LSI or VLSI circuits. The present paper presents a method by which the DDL translator can be made to generate modular equations that will allow the system to be synthesized as an interconnection of lower-level modules. The method involves the introduction of a new language construct called a Module which provides for the separate translation of all equations bounded by it.

Covington, J. A.↗
NASA NTRS1982

Attitude control of the space construction base: A modular approach

A planar model of a space base and one module is considered. For this simplified system, a feedback controller which is compatible with the modular construction method is described. The systems dynamics are decomposed into two parts corresponding to base and module. The information structure of the problem is non-classical in that not all system information is supplied to each controller. The base controller is designed to accommodate structural changes that occur as the module is added and the module controller is designed to regulate its own states and follow commands from the base. Overall stability of the system is checked by Liapunov analysis and controller effectiveness is verified by computer simulation.

Oconnor, D. A.↗