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Results for “modular concepts”

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 73 records · Page 4
All sourcesNASA NTRSDOE OSTI
NASA NTRS1975

Inlet performance of the integrated Langley scramjet module

The inlet concept for the Langley Scramjet Module has been developed and proven in Langley wind tunnels over a Mach number range from 2.3 to 6.0 (flight simulation of Mach 2.6 to 7.6). This modular engine concept is designed to integrate with the airframe, which results in precompression of the engine airflow by the vehicle bow shock and additional expansion of the nozzle exhaust gas by the afterbody of the vehicle. With these integration advantages, the inlet can be designed with modest contraction ratios and fixed geometry. Also, the module nozzle exit area can be equal to the capture area, which permits the cowl to be alined with the local flow producing minimum external drag. The inlet leading edges and planar compression surfaces are swept at 48 deg, which provides spillage at low Mach numbers for starting and which reduces the pressure gradient on the top surface to permit ingestion of the vehicle forebody boundary layer into the inlet without separating. Three fuel injection struts provide for the use of a short combustor having low internal cooling requirements. Schedules for mass capture ratio, contraction ratio, and total pressure recovery are well within the acceptable range for a good scramjet propulsion device. The fixed geometry, minimum external drag design has proven to be a practical, high-performance inlet concept.

Trexler, C. A.↗
NASA NTRS1975

Modular bus and payload designs for the Shuttle era

The Space Shuttle, in combination with the Interim Upper Stage, will provide an economical means of placing payloads in geostationary orbit in the 1980s. This paper summarizes a recent study of multidiscipline applications payloads for Shuttle-IUS launch. Various concepts for modular 'bus' spacecraft structures and payload groupings based on equipment commonality are considered. Several bus and payload configurations, ranging from 160 to 1600 kg, are developed. A typical payload is described in some detail. The payload consists of equipment at 400 MHz for search and rescue and data collection, at 1.5 and 15 GHz for aeronautical, maritime, and land mobile communications, at 40 and 90 GHz for millimeter wave communications, and at other bands for meteorological radiometry, electromagnetic environment measurements, and interferometry.

Durrani, S. H.↗
NASA NTRS1987

Orbital Spacecraft Consumables Resupply System (OSCRS). Volume 2: Study results

The objective was to establish an earth storable fluids tanker concept which satisfies the initial resupply requirements for the Gamma Ray Observatory (GRO) for reasonable front end (design, development, verification) cost while providing growth potential for foreseeable future earth storable resupply mission requirements. The achievement of these objectives becomes possible with the development of a modularized tanker concept which is a hybrid of a dedicated GRO tanker and a generic earth storable propellant tanker.

Source record↗
NASA NTRS1981

Modular antenna design study

The mechanical design of a modular antenna concept was developed sufficiently to allow manufacture of a working demonstration model of a module, to predict mass properties, and to make performance estimates for antenna reflectors composed of these modules. The primary features of this concept are: (1) each module is an autonomous structural element which can be attached to adjacent modules through a three point connection; (2) the upper surface is a folding hexagonal truss plate mechanism which serves as the supporting structure for a reflective surface; and (3) the entire truss and surface can be folded into a cylindrical envelope in which all truss elements are essentially parallel. The kinematic studies and engineering demonstration model fully verified the deployment kinematics, stowing philosophy, and deployment sequencing for large antenna modules. It was established that such modules can be stowed in packages as small as 25 cm in diameter, using 1.27 cm diameter structural tubes. The development activity indicates that this deployable modular approach towards building large structures in space will support erection of 450 m apertures for operation up to 3 GHz with a single space shuttle flight.

Ribble, J. W.↗
NASA NTRS1971

Hybrid redundancy system for improving reliability - A concept

System combines two concepts - triple modular redundancy (TMR) and spares (replacement system) redundancy. System has triplicated active unit core with associated bank of specifically arranged standby spare units. Curves plotted from characteristic equation show hybrid system is more reliable than conventional TMR systems.

Mathur, F. P.↗
NASA NTRS1975

Life-support systems for interplanetary spacecraft and space stations for long-term use

Integrated regenerative life support systems in which the by-products of one system become useful material for another are considered. Regeneration or reclamation of water and the principal atmospheric gases, and elimination or disposition of waste products are the principal functions of such systems. A modular system concept is described. Features of this system include: commonality (for spares reduction), maintainability, overall computer-monitored functioning, and onboard repair and replacement tasks in the event of failure.

Jones, W. L.↗
NASA NTRS1976

Launch Processing System

This paper presents a functional description of the Launch Processing System, which provides automatic ground checkout and control of the Space Shuttle launch site and airborne systems, with emphasis placed on the Checkout, Control, and Monitor Subsystem. Hardware and software modular design concepts for the distributed computer system are reviewed relative to performing system tests, launch operations control, and status monitoring during ground operations. The communication network design, which uses a Common Data Buffer interface to all computers to allow computer-to-computer communication, is discussed in detail.

Byrne, F.↗
NASA NTRS1977

Planning for Materials Processing in Space

A systems design study to describe the conceptual evolution, the institutional interrelationshiphs, and the basic physical requirements to implement materials processing in space was conducted. Planning for a processing era, rather than hardware design, was emphasized. Product development in space was examined in terms of fluid phenomena, phase separation, and heat and mass transfer. The effect of materials processing on the environment was studied. A concept for modular, unmanned orbiting facilities using the modified external tank of the space shuttle is presented. Organizational and finding structures which would provide for the efficient movement of materials from user to space are discussed.

Source record↗
NASA NTRS1979

Flight controls/avionics research - Impact on future civil helicopter operating efficiency and mission reliability

Operational efficiency and mission reliability are key capabilities which will impact the future use of helicopters in the civil segment and areas where flight control/avionics research can play a major role. The present paper reviews flight control/avionics system needs for each major area of civil helicopter use. Technology requirements to meet civil needs are discussed. The review points up the need for the development of all-weather flight control concepts and the validation of cost effective active control/fly-by-wire/fly-by-light system concepts with modular architecture which can be tailored to specific mission requirements.

Snyder, W. J.↗
NASA NTRS1982

Space Operations Center system analysis study extension. Volume 1: Executive summary

The analysis fo Space Operations Center (SOC) systems is summarized. Design considerations, configurations of the manned orbital space station, planned operational and research missions, and subsystem tradeoffs are considered. Integration into the space transportation system is discussed. A modular design concept permitting growth of the SOC as its functions are expanded is described. Additional considerations are special requirements for habitat modules, design modifications needed to operate in geosynchronous orbits, and use of the external tank for cryogenic propellant storage or as a pressurized hangar. A cost summary is presented.

Source record↗
NASA NTRS1987

Mariner Mark II - Spacecraft control for the 1990's and beyond

The Mariner Mark II reconfigurable modular spacecraft concept will incorporate a Spacecraft Attitude and Articulation Control System of novel design. Attention is presently given to key component technologies that will be used for the first time in the Mariner Mark II; these encompass CCD-based, target-referenced extended body tracking, fiber-optic rate sensing, and momentum compensation for dynamic isolation of payloads. An analysis of star and target body-tracking requirements is presented, together with an account of the precision-pointing platform disturbance rejection properties required.

Bell, Charles E.↗
NASA NTRS1990

Addressing hypertext design and conversion issues

Hypertext is a network of information units connected by relational links. A hypertext system is a configuration of hardware and software that presents a hypertext to users and allows them to manage and access the information that it contains. Hypertext is also a user interface concept that closely supports the ways that people use printed information. Hypertext concepts encourage modularity and the elimination of redundancy in data bases because information can be stored only once but viewed in any appropriate context. Hypertext is such a hot idea because it is an enabling technology in that workstations and personal computers finally provide enough local processing power for hypertext user interfaces.

Glusko, Robert J.↗
NASA NTRS1992

Low Earth Orbital Mission Aboard the Space Test Experiments Platform (STEP-3)

A discussion of the Space Active Modular Materials Experiments (SAMMES) is presented in vugraph form. The discussion is divided into three sections: (1) a description of SAMMES; (2) a SAMMES/STEP-3 mission overview; and (3) SAMMES follow on efforts. The SAMMES/STEP-3 mission objectives are as follows: assess LEO space environmental effects on SDIO materials; quantify orbital and local environments; and demonstrate the modular experiment concept.

Brinza, David E.↗
NASA NTRS1993

Alternate vehicles for engine/vehicle optimization

The space shuttle main engine, full flow staged combustion, integrated modular engine concept, split expander, and expander bleed rocket engine cycles were studied for use on Single-Stage-to-Orbit fully reusable vehicles. The vehicle uses vertical take-off and horizontal landing and liquid hydrogen rockets for propulsion. The PROPSIZE computer code was modified for use on the available computers. Vehicle sizing was done after trajectory optimization for various engine designs. The various rocket engine cycles were compared and it was found that the full flow staged combustion cycle had the lowest vehicle dry mass. The split expander cycle could have advantages in safety and cooling which could make it the preferred choice in some cases. Comparison to previous work with two-stage heavy-lift vehicles showed that the same ranking of the cycles was found for both vehicle concepts.

Venkatasubramanyam, G.↗