The unguided solid rocket for aerodynamic testing.
Operational problems and costs of staged solid- propellant rocket vehicles for atmosphere only, noting aerodynamic stabilization, spin motors, stage separation, jet plume, etc
ECONOMICS↗
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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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Electronic devices for hydrogen leak and fire detection.
Electronic hydrogen leak and fire detector systems installed on Saturn S-IVB static test firing stands, discussing installation and operational problems
STATIC TESTING↗
Factors in the operation of manned space chambers, symposium presented at the fifth pacific area national meeting, american society for testing and materials, seattle, wash., oct. 31-nov. 5, 1965. /astm special technical publication no. 398/.
Need, facility requirements, operational problems, and biomedical and physiological aspects associated with certification of simulated space environmental chambers for human occupancy
LIFE SUPPORT SYSTEM↗
Study of flight management requirements during SST low visibility approach and landing operations Final summary report
Flight management operational problems and task requirements for low visibility approach and landing of supersonic transports
Gartner, W. B.↗
VSTOL terminal area instrument flight research.
V/STOL instrument flight handling and operating problems, discussing pilot information requirements, flight displays and terminal facilities
Reeder, J. P.↗
Handbook of Astronautics
Soviet handbook of astronautics covering spacecraft and operating problems of near-earth spaceflight
Kondratev, N. YA.↗
High voltage solar array study Final report
Analysis of operating problems of high voltage solar array in earth orbit
Oman, H.↗
Low pressure oxygen-hydrogen auxiliary propulsion subsystems
Operational problem and technological requirement of low pressure oxygen hydrogen auxiliary subsystem of space shuttle propulsion
Kohrs, L. F.↗
Experiment T002: Manual navigation sightings
Navigation-type measurements through the window of the stabilized Gemini 12 spacecraft by the use of a hand-held sextant are reported. The major objectives were as follows: (1) to evaluate the ability of the crewmen to make accurate navigational measurements by the use of simple instruments in an authentic space flight environment; (2) to evaluate the operational feasibility of the measurement techniques by the use of the pressure suit with the helmet off and with the helmet on and the visor closed; (3) to evaluate operational problems associated with the spacecraft environment; and (4) to validate ground based simulation techniques by comparison of the inflight results with base line data obtained by the pilot by the use of simulators and celestial targets from ground based observatories.
Smith, D.↗
Design study of shaft face seal with self-acting lift augmentation. 5: Performance in simulated gas turbine engine operation
The feasibility and the noncontact operation of the self-acting seal was demonstrated over a range of simulated gas turbine engine conditions from 200 to 500 ft/sec sliding speed. Sealed pressure differentials were 50 to 300 psi and sealed temperatures were 150 to 1200 F. Low leakage (about 1/10 that of conventional labyrinth seals) was exhibited in two endurance runs (200 and 338 hr) at 400 ft/sec, 200 psi and 1000 F (gas temperature). For these endurance runs, the self-acting pad wear was less than 3.8 micrometers (0.00015 in.); this low wear was attributed to the noncontact operation of the primary seal. Operating problems identified were fretting wear of the secondary seal and erosion of the primary seal by hard particles.
Ludwig, L. P.↗
Study of a heat rejection system using capillary pumping
Results of an analytical study investigating the application of capillary pumping to the heat rejection loop of an advanced Rankine cycle power conversion system are presented. The feasibility of the concept of capillary pumping as an alternate to electromagnetic pumping is analytically demonstrated. Capillary pumping is shown to provide a potential for weight and electrical power saving and reliability through the use of redundant systems. A screen wick pump design with arterial feed lines was analytically developed. Advantages of this design are high thermodynamic and hydrodynamic efficiency, which provide a lightweight easily packaged system. Operational problems were identified which must be solved for successful application of capillary pumping. The most important are the development of start up and shutdown procedures, and development of a means of keeping noncondensibles from the system and of earth-bound testing procedures.
Neal, L. G.↗
Booster recovery following premature space shuttle stage separation
Abort criteria necessary to satisfy space shuttle program requirements to include intact vehicle abort capability are discussed. Intact abort implies the ability of the booster and orbiter to separate and both continue flight to a safe landing, with a full payload aboard the orbiter. Obviously, the requirement to separate early along the ascent trajectory presupposes critical operational problems that are probably booster problems and may preclude booster recovery. On the other hand, some critical problems while mated can become manageable when separated and should result in full booster recovery. All critical orbiter problems fall into this category; since stage separation without orbiter thrust is a capability of some separation system concepts, booster stage recovery following separation is a requirement.
Hurley, M. J.↗
A flight evaluation of a vectored thrust jet V/STOL airplane during simulated instrument approaches using the Kestrel (XV-6A) airplane
An in-flight investigation was made to determine the terminal-area operating problems of a vectored-thrust-jet vertical and short take-off landing (V/STOL) airplane under simulated instrument conditions. Handling-qualities data pertinent to the terminal-area approach and landing task are presented in the text, and additional documentation is included in the appendixes. Problems dealing with the cruise letdown to localizer capture, conversion to powered-lift flight, precise control of the glide slope, approach velocity or deceleration schedule, hover, and landing are discussed.
Morello, S. A.↗
Modifications and additions to NASTRAN at Marshall Space Flight Center, 1969 - 1972
Modifications to NASTRAN code which result from the location, identification, and correction of errors or operational problem areas are reviewed. Addition of improved capability which is structural, executive system oriented, or utility in nature is also considered. NASTRAN efficiencies and inefficiencies are studied.
Jordon, A. J., Jr.↗
NaK loop testing of thermoelectric converter modules (SNAP program)
The history of testing of compact tubular modules in flowing NaK loops is summarized. Test procedures, data handling, and instrument calibration are discussed. Also included is descriptive information of the test facilities, operational problems encountered, and some recommendations for testing.
Johnson, J. L.↗
Liquid rocket engine fluid-cooled combustion chambers
A monograph on the design and development of fluid cooled combustion chambers for liquid propellant rocket engines is presented. The subjects discussed are (1) regenerative cooling, (2) transpiration cooling, (3) film cooling, (4) structural analysis, (5) chamber reinforcement, and (6) operational problems.
Source record↗
Reactivity change in a fast-spectrum space power reactor due to a 328-meter-per-second (1075-ft/sec) impact
Application of nuclear reactors in space will present operational problems. One such problem is the possibility of an earth impact at velocities in excess of 305 m/sec (1000 ft/sec). This report shows the results of an impact against concrete at 328 m/sec (1075 ft/sec) and examines the deformed core to estimate the range of activity inserted as a result of the impact. The results of this examination are that the deformation of the reactor core within the containment vessel left only an estimated 2.7 percent void in the core and that the reactivity inserted due to this impact deformation could be from 4.0 to 10.25 dollars.
Peoples, J. A., Jr.↗
Third Level Air Carrier Service
A proposed Civil Aviation Board approach to regulating commuter air transportation services is discussed. Operating problems of specific air lines are used as examples. Inadequacies in the present service for short haul commuter air transportation are defined. Methods by which improvements in the commuter air transport service are proposed.
Eads, G. C.↗