Hydrogen Flare Stack Diffusion Flames - Low and High Flow Instabilities, Burning Rates, Dilution Limits, Temperatures, and Wind Effects
Combustion characteristics and safety factors for hydrogen diffusion flames in flare stack operations
Grumer, J.↗
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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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Nuclear power for surface effect vehicle and aircraft propulsion
Economic and safety factors of nuclear powered surface vehicles and aircraft in transoceanic commerce
Rom, F. E.↗
Systems simulation for an airport trailing vortex warning system
The approach, development, and limited system studies associated with a system simulation for an Airport Trailing Vortex Warning System are documented. The usefulness is shown of a systems engineering approach to the problem of developing a system, as dictated by aircraft vortices, which will increase air-traffic flow in the takeoff/landing corridors of busy airports while maintaining the required safety factor for each operation. The simulation program has been developed in a modular form which permits new, more sophisticated component models, when they become available and are required, to be incorporated into the program with a minimum of program modifications. This report documents a limited system study that has been performed using this Total System Simulation Model. The resulting preliminary system requirements, conclusions, and recommendations are given.
Jeffreys, H. B.↗
Technical report analysis and design: Study of solid rocket motors for a space shuttle booster, volume 2, book 1, supplement 1
An analysis and design effort was conducted as part of the study of solid rocket motor for a space shuttle booster. The 156-inch-diameter, parallel burn solid rocket motor was selected as its baseline because it is transportable and is the most cost-effective, reliable system that has been developed and demonstrated. The basic approach was to concentrate on the selected baseline design, and to draw from the baseline sufficient data to describe the alternate approaches also studied. The following conclusions were reached with respect to technical feasibility of the use of solid rocket booster motors for the space shuttle vehicle: (1) The 156-inch, parallel-burn baseline SRM design meets NASA's study requirements while incorporating conservative safety factors. (2) The solid rocket motor booster represents a cost-effective approach. (3) Baseline costs are conservative and are based on a demonstrated design. (4) Recovery and reuse are feasible and offer substantial cost savings. (5) Abort can be accomplished successfully. (6) Ecological effects are acceptable.
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Space shuttle auxiliary propulsion system design study. Executive summary
The development and characteristics of an auxiliary propulsion system for space shuttle applications are presented. The system design data necessary for selection of preferred system concepts and the requirements for complementing component design and test programs are analyzed. The use of cryogenic oxygen and hydrogen as a propellant combination is explained on the basis of high vehicle impulse requirements, safety factors, reuse, and logistics considerations. The final configurations for the alternate propellant system, with primary emphasis on earth storable propellants is described.
Kelly, P. J.↗
Radiative relaxation rates and intensities during outer planet entries
Gas properties which can affect outer planetary entry probe radiative heat transfer are reviewed in order to predict the effect of processes such as radiative relaxation, radiative cooling, and equilibrium radiation intensities on entry. These processes are quantified in order to avoid overestimating the radiative transfer by an over simplified approach to the problem. By reducing the uncertainties in the knowledge of these processes, the heatshield weight is minimized by reducing safety factors and performance limits.
Leibowitz, L.↗
Characteristics of oxygen
Oxygen reactivity and the design of special hardware to be used in oxygen service are discussed. Safety factors, passing mixing characteristics, and oxygen absorption by porous materials are considered. Special attention was given to system failure prevention and resulting hazards, costs, and time loss.
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Oxygen tank assemblies
Structural design considerations for O2 tank shells and suspension systems of ground based storage and mobile tank systems are outlined. Safety factors, chemical compatibility, liquid slosh strength, and cryogenic temperature properties are summarized. Finally, costs, quality control measures, and long life characteristics are examined.
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A generalized concept for cost-effective structural design
A generalized concept for cost-effective structural design is introduced. It is assumed that decisions affecting the cost effectiveness of aerospace structures fall into three basic categories: design, verification, and operation. Within these basic categories, certain decisions concerning items such as design configuration, safety factors, testing methods, and operational constraints are to be made. All or some of the variables affecting these decisions may be treated probabilistically. Bayesian statistical decision theory is used as the tool for determining the cost optimum decisions. A special case of the general problem is derived herein, and some very useful parametric curves are developed and applied to several sample structures.
Thomas, J. M.↗
The Airfloat HL project
A design study is described for a large low-cost rigid airship intended primarily for the movement of large indivisible loads (cargo) between industrial sites. A survey of the ship and its overall performance is followed by accounts of the operational procedures for the above function and for an alternative application to unit module transfer between fixed terminals. A final section indicates the estimated costs of construction and operation. Safety factors are also considered. Lifting devices such as winches, hoists are shown and described, and airship configurations are also shown.
Mowforth, E.↗
Analysis of UF6 breeder reactor power plants
Gaseous UF6 fueled breeder reactor design and technical applications of such concepts are summarized. Special attention was given to application in nuclear power plants and to reactor efficiency and safety factors.
Clement, J. D.↗
High purity silica reflective heat shield development
A hyperpure vitreous silica material is being developed for use as a reflective and ablative heat shield for planetary entry. Various purity grades and forms of raw materials were evaluated along with various processing methods. Slip casting of high purity grain was selected as the best processing method, resulting in a highly reflective material in the wavelength bands of interest (the visible and ultraviolet regions). The selected material was characterized with respect to optical, mechanical and physical properties using a limited number of specimens. The process has been scaled up to produce a one-half scale heat shield (18 in. dia.) (45.72 cm) for a Jupiter entry vehicle. This work is now being extended to improve the structural safety factor of the heat shield by making hyperpure silica material tougher through the addition of silica fibers.
Nachtscheim, P. R.↗
Progress Report on Project Mercury
Progress on Project Mercury, program for manned orbital space flight, is briefly reviewed. The original aims and concepts of the project are recounted. Various types of launch apparatus are mentioned along with safety factors.
Donlan, C. J.↗
Satellite Power System (SPS) concept development and evaluation program plan, July 1977 - August 1980
An overview of the program to evaluate the solar satellite power system concept is presented. Environmental, health, and safety factors are examined along with economic, international, and institutional issues.
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Liquid rocket engine axial-flow turbopumps
The axial pump is considered in terms of the total turbopump assembly. Stage hydrodynamic design, pump rotor assembly, pump materials for liquid hydrogen applications, and safety factors as utilized in state of the art pumps are among the topics discussed. Axial pump applications are included.
Scheer, D. D.↗
The 11th Annual Battery Workshop
The development, properties, and testing of nickel cadmium, metal hydrogen, and lithium systems are discussed, as well as their applications and related safety factors.
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First Spacelab flight - A status report of the joint ESA/NASA mission
A general overview of the first Spacelab flight is presented and a table is given listing the payload composition. An accommodation study is presented with emphasis on the configuration, mass status, timeline, and experiment interface specifications. Also considered are flight and ground operations, safety factors, and payload specialists training for the first flight.
Craft, H. G., Jr.↗
Space Shuttle autoland design
The Orbiter Autoland system is activated at 10,000 ft altitude and performs energy control through speedbrake modulation, vertical path tracking with acceleration commands to the pitch control system, lateral path tracking through bank angle commands to the roll control system, and brings the vehicle to main gear touchdown. A nominal 19 degree glide slope is flown down to 2000 ft, followed by a 1.5 deg path to flare and subsequent soft landing. The flight path is similar to that which a pilot would fly, a feature which increases safety factors should manual takeover be necessary during landing maneuvers. A block diagram of the autoland control interfaces is provided, and attention is given to the use of a reference trajectory, the guidance laws, lateral guidance, the speed control system, pitch rate control, and the rollout system. Conditions and instrument indications leading to pilot takeover are outlined.
Tsikalas, G. M.↗