High speed phase detector Patent
High speed phase detector design indicating phase relationship between two square wave input signals
Parker, G. L.↗
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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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Handbook of human engineering design data for reduced gravity conditions
A Handbook is presented for the use of engineers, designers, and human factors specialists during the developmental and detailed design phases of manned spacecraft programs. Detailed and diverse quantified data on man's capabilities and tolerances for survival and productive effort in the extraterrestrial environment are provided. Quantified data and information on the space environment as well as the characteristics of the vehicular or residential environment required to support man in outer space are also given.
Marton, T.↗
Choice of an ion engine for the Communications Technology Satellite.
The purpose of the spacecraft is to space qualify a number of components for the next generation of communications satellites. The state of development of ion thrusters has reached a point where at least three types of engine may be considered for integration on spacecraft. The proposed methods of stationkeeping require that the thruster operate with a duty cycle of somewhat less than 12 hours in a 24 hour period. Several possible mounting positions for the thrusters were considered during the conceptual design phase. It is concluded that an experimental ion thruster subsystem may be incorporated in the communication satellite and used to demonstrate, at a minimum, north-south stationkeeping of the spacecraft in synchronous orbit.
Payne, W. F.↗
Space station prototype environmental/thermal control and life system - A current overview.
The Environmental Thermal Control and Life Support System (ETC/LSS) for a space station has progressed through the design phase into the fabrication of hardware. An overview of the current status of this program is presented with emphasis on the impact and implementation of commonality and maintainability concepts as well as the interface with an on-board checkout system. The programmatic techniques and procedural modifications employed and anticipated are treated.
Willis, N. C., Jr.↗
EOS image data processing system definition study
The Image Processing System (IPS) requirements and configuration are defined for NASA-sponsored advanced technology Earth Observatory System (EOS). The scope included investigation and definition of IPS operational, functional, and product requirements considering overall system constraints and interfaces (sensor, etc.) The scope also included investigation of the technical feasibility and definition of a point design reflecting system requirements. The design phase required a survey of present and projected technology related to general and special-purpose processors, high-density digital tape recorders, and image recorders.
Gilbert, J.↗
Evaluation of advanced lift concepts and fuel conservative short-haul aircraft, volume 1
The performance and economics of a twin-engine augmentor wing airplane were evaluated in two phases. Design aspects of the over-the-wing/internally blown flap hybrid, augmentor wing, and mechanical flap aircraft were investigated for 910 m. field length with parametric extension to other field lengths. Fuel savings achievable by application of advanced lift concepts to short-haul aircraft were evaluated and the effect of different field lengths, cruise requirements, and noise levels on fuel consumption and airplane economics at higher fuel prices were determined. Conclusions and recommendations are presented.
Renshaw, J. H.↗
A mass spectrometer concept for identifying planetary atmosphere composition
The design and use of mass spectrometers to measure and identify atmospheric gas compositions of planets are discussed. Special emphasis during the design phase was given to dynamic range that the instrument must have, mass range the instrument must cover, and precision of the measurements that are necessary, for example to confirm isotope ratios. Some problems encountered in the use of the instrument are illustrated using data from the Pioneer-Venus program.
Spencer, N. W.↗
Multiple docking adapter window for the S-190 experiment
Martin Marietta/NASA subcontracted the design, fabrication, testing, and installation of the multiple docking adapter S-190 experiment window assembly to Actron. In this paper, we primarily treat the thermal-optical analysis aspect of the design phase. The window is a pane of BK 7 glass 59.18 cm by 44.91 cm by 4.06 cm. Though it must meet many mechanical specifications, the optical requirements, dictated by the high acuity, distortion-free S-190 multiband camera system, are the most severe. Under operating conditions over any 7.6-cm circular area, the maximum rms deviation from the best-fitting plane must be less than 12.0 nm, and from the reference plane through the entire window, 60.0 nm.
Gimlett, J. I.↗
Skylab EVA system development
EVA hardware design is traced from initial conceptual development to final flight configuration. Major concepts considered during design evolution are identified, and reasons for the acceptance or rejection of these concepts are discussed. An iterative approach to simulations and testing was found useful. Early conceptual efforts concentrated on analyses and normal gravity, low-cost, low-fidelity mockups; later design phases combined normal gravity and neutral buoyancy simulations of increasing fidelity. Restudying after each change consistently drove EVA hardware toward operational and mechanical simplicity.-
Heckman, R. T.↗
Transonic flow about airfoils
Program analyzes airfoils that permit transonic flow for subsonic free-stream mach numbers. Transonic refers to aircraft speeds less than speed of sound, but close enough so that top of wing, where airflow is fastest, mach number becomes greater than 1. Program should aid design phase of new airfoil and in analysis of existing airfoils.
Bauer, F.↗
Compressible laminar boundary-layer flow
Program computes compressible laminar boundary-layer flow over yawed infinite wing including distributed suction. Computations are useful in efforts to implement boundary-layer suction on wing to maintain laminar flow in order to reduce net drag. Program contains number of approximations to simplify analysis; yet results are accurate enough to be useful, particularly in preliminary design phase.
Carter, J. E.↗
NASA/Navy lift/cruise fan cost reduction studies
Cost reduction studies were performed for the LCF459 turbotip fan for application with the YJ97-GE-100 gas generator in a multimission V/STOL research and technology aircraft. A 20 percent cost reduction of the research configuration based on the original preliminary design was achieved. The trade studies performed and the results in the area of cost reduction and weight are covered. A fan configuration is defined for continuation of the program through the detailed design phase.
Source record↗
Application of active controls to civil transport aircraft
The impact of active controls on civil transport aircraft and some of the complex problems involved are described. The approach taken by NASA as part of the Active Control Technology Program is discussed to integrate active controls in the conceptual design phase. It is shown that when handled correctly, active controls improve aircraft performance.
Taylor, L. W., Jr.↗
Vortex lattice prediction of subsonic aerodynamics of hypersonic vehicle concepts
The vortex lattice method introduced by Lamar and Gloss (1975) was applied to the prediction of subsonic aerodynamic characteristics of hypersonic body-wing configurations. The reliability of the method was assessed through comparison of the calculated and observed aerodynamic performances of two National Hypersonic Flight Research Facility craft at Mach 0.2. The investigation indicated that a vortex lattice model involving 120 or more panel elements can give good results for the lift and induced drag coefficients of the craft, as well as for the pitching moment at angles of attack below 10 to 15 deg. Automated processes for calculating the local slopes of mean-camber surfaces may also render the method suitable for use in preliminary design phases.
Pittman, J. L.↗
GEMPAK: An arbitrary aircraft geometry generator
A computer program, GEMPAK, has been developed to aid in the generation of detailed configuration geometry. The program was written to allow the user as much flexibility as possible in his choices of configurations and the detail of description desired and at the same time keep input requirements and program turnaround and cost to a minimum. The program consists of routines that generate fuselage and planar-surface (winglike) geometry and a routine that will determine the true intersection of all components with the fuselage. This paper describes the methods by which the various geometries are generated and provides input description with sample input and output. Also included are descriptions of the primary program variables and functions performed by the various routines. The FORTRAN program GEMPAK has been used extensively in conjunction with interfaces to several aerodynamic and plotting computer programs and has proven to be an effective aid in the preliminary design phase of aircraft configurations.
Stack, S. H.↗
Evaluation of materials for high performance solar arrays
A program has been underway to evaluate materials for advanced solar arrays which are required to provide power to weight ratios up to 100 W/kg. Severe mission environments together with the lack of knowledge of space environmental materials degradation rates require the generation of irradiation and outgassing engineering data for use in the initial design phase of the flight solar arrays. Therefore, approximately 25 candidate array materials were subjected to selected mission environments of vacuum, UV, and particle irradiation, and their mechanical and/or optical properties were determined where appropriate.
Whitaker, A. F.↗
Active controls technology to maximize structural efficiency
The implication of the dependence on active controls technology during the design phase of transport structures is considered. Critical loading conditions are discussed along with probable ways of alleviating these loads. Why fatigue requirements may be critical and can only be partially alleviated is explained. The significance of certain flutter suppression system criteria is examined.
Hoy, J. M.↗
Application of the equilibrium spin technique to a typical low-wing general aviation design
A graphical implementation of the equilibrium technique for obtaining spin modes from rotary balance data is presented. Using this technique, spin modes were computed for the NASA Low-Wing General Aviation Aircraft. The computed angles of attack are within 10 degrees of the NASA spin tunnel results. The method also provides information on the dynamic nature of spin modes. This technique offers the capability of providing a great deal of information on spin modes and recovery, using data from a single experimental installation. Such a technique could be utilized in the preliminary design phase in order to provide basic information on aircraft spin and recovery characteristics. Results, advantages and limitations of the application of this technique are discussed.
Tischler, M. B.↗