Water recovery study- electrolytic purification of urine contractor report, jul. 7 - oct. 10, 1964
Design parameter study for urine electrolysis module
EQUIPMENT SPECIFICATIONS↗
SEARCH · Search NASA
Results for “EQUIPMENT SPECIFICATIONS”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
AROD design feasibility report, volume I and II Final report
System analysis, system design, and equipment implementation for Airborne Range and Orbit determination /AROD/
SYSTEMS DESIGN↗
Commerical application of rocket engine turbopump technology
This paper describes how commercial pump technology was modified for rocket engine application by trading long life for low weight. The component life of typical turbopump components is presented, and the modes of failure will be discussed. A comparison of the basic commercial and rocket engine pump requirements such as flow, pressure, etc. is made. It is concluded that rocket engine pump technology can be applied directly only if similar basic requirements exist in emergency or stand-by equipment. The specific design requirements for rocket engine turbopumps are presented and the need for high speeds is explained by the weight-speed relationship and the optimum NPSH of the tank and pump system. The trend of required rocket engine pump discharge pressure and future operational requirements is predicted. The need for inducers and boost pumps in rocket engines is explained, and the results of the flat-plate-inducer cavitation therein are briefly presented. Design solutions and material selections for high-pressure pump housings, ultra-high tip speed impellers, and pump packaging are demonstrated. As a typical example of utilizing rocket engine technology for commercial application, a helicopter stand-by engine i shown. This standby engine is designed from existing rocket engine components, using JATO rockets as the prime energy source.
Turbopump↗
Voyager spacecraft system. Preliminary design, volume C - 1971 operational support equipment design
Operational support equipment design for Voyager spacecraft - system test and launch complex equipment
LAUNCH COMPLEX↗
Human engineering data and concepts for handling advanced nuclear systems in space Research and technology implications report
System and equipment descriptions of manned orbital research laboratory, and interplanetary and lunar ferry vehicles
INTERPLANETARY SPACECRAFT↗
Design, proof test and delivery program of TE-372-3 Pyrogen for TE-29 Recruit rocket motor Final report
Design modifications, proof test, and delivery program of igniters for Recruit rocket engines
IGNITION SYSTEM↗
Evaluation of various lubrication methods at orbital conditions for space vehicles.
Space vehicle lubrication methods, noting design and construction of test apparatus
SPACECRAFT MECHANISM LUBRICATION↗
Proceedings of the 3rd Aerospace Mechanisms Symposium
Conference on mechanical engineering aspects of satellite systems - dynamic structural analyses and developments of control mechanisms, design specifications, and equipment components
Source record↗
The icing problem - Current status of NACA techniques and research
This paper summarizes some of the techniques used in N.A.C.A. research programs, in flight and in tunnels, to solve aircraft icing problems and it indicates the scope of the data avail-able for the design of aircraft icing protection systems. Sufficient data have been obtained, generalized where possible, and techniques have been established whereby icing -protection requirements for most aircraft components can be determined sufficiently accurately for engineering purposes. The Appendices discuss the icing facilities at the N.A.C.A. Lewis laboratory in detail, specific test equipment and techniques used in conducting tests in icing wind tunnels, and several icing instruments.
Uwe H von Glahn↗
Controlled flow assembly
Incorporation of isolation valves in high pressure oxygen supply system prevents occurrence of shock ignition when valves are opened. Specifications of equipment show flow rates, pressure ratings, and service life. Illustration of equipment is provided.
Cohen, A. E.↗
The interplanetary Pioneers. Volume 2: System design and development
The Pioneer systems, subsystems, and ground support activities are described. Details are given on the launch trajectory and solar orbit plans, spacecraft design approach and evolution, scientific instrument, test and ground support equipment, Delta launch vehicle, tracking and communication, and data processing equipment. Pioneer specifications, and reliability and quality assurance are also included.
Corliss, W. R.↗
Proceedings of the Fourth Precise Time and Time Interval Planning Meeting
The proceedings of a conference on Precise Time and Time Interval Planning are presented. The subjects discussed include the following: (1) satellite timing techniques, precision frequency sources, and very long baseline interferometry, (2) frequency stabilities and communications, and (3) very low frequency and ultrahigh frequency propagation and use. Emphasis is placed on the accuracy of time discrimination obtained with time measuring equipment and specific applications of time measurement to military operations and civilian research projects.
Acrivos, H. N.↗
Fluid dynamic aspects of jet noise generation
Jet engine noise generation and noise propagation was investigated by studying supersonic nozzle flow of various nozzle configurations in an experimental test facility. The experimental facility was constructed to provide a coaxial axisymmetric jet flow of unheated air. In the test setup, an inner primary flow exhausted from a 7 in. exit diameter convergent--divergent nozzle at Mach 2, while a secondary flow had a 10 in. outside diameter and was sonic at the exit. The large dimensions of the jets permitted probes to be placed inside the jet core without significantly disturbing the flow. Static pressure fluctuations were measured for the flows. The nozzles were designed for shock free (balanced) flow at Mach 2. Data processing techniques and experimental procedures were developed in order to study induced disturbances at the edge of the supersonic flows, and the propagation of those disturbances throughout the flows. Equipment used (specifications are given) to record acoustic levels (far field noise) is described. Results and conclusions are presented and discussed. Diagrams of the jet flow fields are included along with photographs of the test stand.
Barra, V.↗
SMM parallel battery operation in orbit
A parallel battery system for the SMM spacecraft is described. The battery system performance as a function of lifetime over orbit was evaluated. The following equipment performance specifications were examined during a typical orbit: battery current and discharges, voltage limitations, battery temperature variations, and current sensor performance. Tabulated battery performance data is also included.
Broderick, R.↗
Enviropod handbook: A guide to preparation and use of the Environmental Protection Agency's light-weight aerial camera system
The use of the Environmental Protection Agency (EPA) Enviropod camera system is detailed in this handbook which contains a step-by-step guide for mission planning, flights, film processing, indexing, and documentation. Information regarding Enviropod equipment and specifications is included.
Brower, S. J.↗
Internal contamination in the space station
Atmosphere trace contaminant control systems used in the past (Lunar Module and Skylab) and present (nuclear submarines and Shuttle) are discussed. Recommendations are made for the future Space Station contaminant control system. The prevention and control methods used are judicious material selection, detection, and specific removal equipment. Sources and effects of contamination relating to crew and equipment are also discussed.
Poythress, C.↗
Guidance studies for curved, descending approaches using the Microwave Landing System (MLS)
Results for the Microwave Landing System (MLS) guidance algorithm development conducted under the Advance Transport Operating System (ATOPS) Technology Studies (NAS1-16202) are documented. The study consisted of evaluating guidance law for vertical and lateral path control, as well as speed control, for approaches not possible with the present Instrument Landing System (ILS) equipment. Several specific approaches were simulated using the MD-80 aircraft simulation program, including curved, descending (segmented glide slope), and decelerating paths. Emphasis was placed on development of guidance algorithms specifically for approaches at Burbank, where proposed flight demonstrations are planned. Results of this simulation phase are suitable for use in future fixed base simulator evaluations employing actual hardware (autopilot and a performance management system).
Feather, J. B.↗
A digital beacon receiver
A digital satellite beacon receiver is described which provides measurement information down to a carrier/noise density ratio approximately 15 dB below that required by a conventional (phase locked loop) design. When the beacon signal fades, accuracy degrades gracefully, and is restored immediately (without hysteresis) on signal recovery, even if the signal has faded into the noise. Benefits of the digital processing approach used include the minimization of operator adjustments, stability of the phase measuring circuits with time, repeatability between units, and compatibility with equipment not specifically designed for propagation measuring. The receiver has been developed for the European Olympus satellite which has continuous wave (CW) beacons at 12.5 and 29.7 GHz, and a switched polarization beacon at 19.8 GHz approximately, but the system can be reconfigured for CW and polarization-switched beacons at other frequencies.
Ransome, Peter D.↗