The simultaneous generation of sensitivity functions
Simultaneous generation of sensitivity functions for linear automatic control system with known characteristic differential equation
Kulas, C. E.↗
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Performance verification of the lunar descent program - P66 auto, task E-72C
Results of simulated runs to evaluate lunar module descent performance of P66 automatic control and guidance system
Dwivedi, N. P.↗
Automatic fatigue test temperature programmer Patent
Automatic controlled thermal fatigue testing apparatus
Corbin, P. L.↗
Automated tracking data analysis
Computer controlled automatic tracking data analysis with graphic display
Schmid, P. E.↗
Design, development, and fabrication of a water electrolysis system for a 90-day manned test Final report
Design, fabrication, and testing of circulating electrolyte type water electrolysis system for automatic control of spacecraft total pressure and oxygen partial pressure
Greenough, B. M.↗
Identification of a linear system from sampled noisy data, part C Final project report
Step input linear system modeling from nonlinear system sampled noisy data based on method of perturbation or quasilinearization of automatic control system data
Luckinbill, D. L.↗
Boring bar drive mechanism Patent
Automatic controlled drive mechanism for portable boring bar
Miller, J. L.↗
Performance of a direct current power supply for the 2- to 15-kilowatt Brayton cycle system
Performance tests on Brayton cycle direct current power supply circuit for automatic control
Vrancik, J. E.↗
A turbojet simulator for Mach numbers up to 2.0
A turbojet simulator was designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and termperature. Overall aerodynamic design, compressor operating conditions, automatic controls, turbine aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data.
Steffen, F. W.↗
A proposed criterion for aircraft flight in turbulence
A proposed criterion for aircraft flight in turbulent conditions is presented. Subjects discussed are: (1) the problem of flight safety in turbulence, (2) new criterion for turbulence flight where existing ones seem adequate, and (3) computational problems associated with new criterion. Primary emphasis is placed on catastrophic occurrences in subsonic cruise with the aircraft under automatic control. A Monte Carlo simulation is used in the formulation and evaluation of probabilities of survival of an encounter with turbulence.
Porter, R. F.↗
Signal coherence studies in multiaperture arrays
A two-element array was constructed to measure the gain improvement that can be realized while tracking spacecraft. Measurements were made at VHF and S band. An automatically controlled time delay correction system was developed and tested for this program.
Deerkoski, L. F.↗
An analytical study of airplane-autopilot response to atmospheric turbulence
An analytical study has shown that, with proper selection of feedback gains, an automatic control system can reduce excursions in altitude of a jet transport flying in turbulence without increasing structural loads. The control system uses feedback of attitude-angle and pitch-rate signals to the elevator and uses feedback of altitude and altitude-rate signals to the throttle.
Oehman, W. I.↗
Flight test of an erectable spacecraft used for decelerator testing at simulated Mars entry conditions
A 55 foot diameter disk-gap-band parachute was deployed behind an expandable 15 foot diameter, 120 deg blunted-cone simulated spacecraft. The spacecraft was carried to altitude in the folded condition. An automatic control system kept the folded spacecraft pointing in the desired direction after booster separation. The aeroshell was then erected at the desired conditions by ground command. When the desired parachute test conditions were reached, another ground command deployed the test parachute. The test Mach number and dynamic pressure obtained at the parachute peak load were 2.62 and 19.4 pounds per square foot respectively. A large disturbance after aeroshell erection caused a large angle of attack to exist at parachute deployment. Methods of preventing this disturbance are discussed.
Henning, A. B.↗
Space shuttle ascent flight turbulence response
A totally reusable space shuttle configuration has been analyzed during ascent flight to determine its response to atmospheric turbulence. Responses in the form of booster and orbiter body accelerations and booster wing root shear, bending moment and turque were obtained due to random and quasi-square-wave discrete turbulence. The configuration was also analyzed with booster aerodynamic surfaces removed to simulate an expendable booster. Symmetric and antisymmetric analyses were performed. Propellant sloshing, gust penetration, and automatic control system effects were included. It was found that the symmetric responses were generally higher than the antisymmetric ones. The stability augmentation system tended to lower the booster accelerations in the symmetric case, while increasing the orbiter accelerations.
Source record↗
Water electrolysis system refurbishment and testing
The electrolytic oxygen generator for the back-up water electrolysis system in a 90-day manned test was refurbished, improved and subjected to a 182-day bench test. The performance of the system during the test demonstrated the soundness of the basic electrolysis concept, the high development status of the automatic controls which allowed completely hands-off operation, and the capability for orbital operation. Some design improvements are indicated.
Greenough, B. M.↗
An Exercise Prescription Intervention Program with Periodic Ergometric Grading
A long term exercise prescription type of physical conditioning program has been available to executive personnel of the NASA Manned Spacecraft Center for the past two years. Periodic ergometric testing with a heart rate controlled, automatically programmed, bicycle ergometer is used to follow the individual's progress and appropriately alter his exercise prescription from time to time. Such a program appears feasible, and acceptance is excellent, dropout rates small and periodic testing participation good. Subjects training diligently can maintain satisfactory levels of conditioning.
Owen, C. A.↗
Molecular solid-state inverter-converter system
A modular approach for aerospace electrical systems has been developed, using lightweight high efficiency pulse width modulation techniques. With the modular approach, a required system is obtained by paralleling modules. The modular system includes the inverters and converters, a paralleling system, and an automatic control and fault-sensing protection system with a visual annunciator. The output is 150 V dc, or a low distortion three phase sine wave at 120 V, 400 Hz. Input power is unregulated 56 V dc. Each module is rated 2.5 kW or 3.6 kVA at 0.7 power factor.
Birchenough, A. G.↗
Design, fabrication, testing and delivery of a feasibility model laminated ferrite memory
The effect of using multiword addressing with laminated ferrite arrays was made. Both a reduction in the number of components, and a reduction in power consumption was obtained for memory capacities between one million bits and one million words. An investigation into the effect of variations in the processing steps resulted in a number of process modifications that improved the quality of the arrays. A feasibility model laminated ferrite memory system was constructed by modifying a commercial plated wire memory system to operate with laminated ferrite arrays. To provide flexibility for the testing of the laminated ferrite memory, an exerciser has been constructed to automatically control the loading and recirculation of arbitrary size checkerboard patterns of one's and zero's and to display the patterns of stored information on a CRT screen.
Heckler, H. C.↗