Use of analog computer for the equalization of electromagnetic shakers in transient testing
Analog computer to perform open-loop equalization for multishaker environmental vibration testing
Trubert, M. R.↗
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Stability of linear time-invariant systems.
Stability conditions for multiple input-output linear time invariant feedback systems, noting open loop system impulse response characteristics
Desoer, C. A.↗
An apparent adaptive notch filter for thrust vector control.
Hydraulic controller possessing property of automatic tracking notch filter for open loop thrust engine control
Hung, J. C.↗
Suboptimal controls that maximize the probability of entering a target manifold.
Open loop suboptimal control for linear time dependent tradeoff between energy expenditure and probability of target set entry
Luh, J. Y. S.↗
Precision full-wave rectifier
Simplified circuit uses one operational amplifier and two precision resistors. The amplifier is operated open loop for switching and closed loop for linear gain, both simultaneously.
Deboo, G. J.↗
Flueric-controller pneumatic stepping motor system
Nutating stepping motor consists of an output rotating gear and a nutating gear. A flueric logic circuit controls the nutating motor. The complete system constitutes a reliable, open loop actuator system with inherently high output stiffness, reasonable slewing speeds and small step size.
Dustin, M. O.↗
Post Flight Dynamic Analysis Simulation
Digital six-degrees-of-freedom, open loop Saturn 5 first stage flight evaluation simulation program obtains post flight simulation of the launch vehicle using actual flight data as input. Results are compared with measured data. For preflight analysis, the program uses predicted flight data as input.
Gregory, B. R.↗
Two-channel feed system - A dual channel circularly polarized system. II
Dual channel circularly polarized feed of monopulse tracking antenna system, noting axial ratio and gain and open loop mode autotracking
Chadwick, G. G.↗
Adaptive stochastic control for linear systems. I - Solution method
Linear discrete time stochastic system with unknown gain parameters, interpreting open loop feedback optimal control identifier and controller equations
Athans, M.↗
Reactor simulator runs with thermionic diode kinetics experiment
Open loop transient analysis of thermionic diode kinetics experiment with analog computer nuclear reactor simulator
Gronroos, H. G.↗
Frequency domain stability criteria for stochastic systems
Frequency domain stability criteria for dynamical systems with random parameters, considering open loop stability, stochastic gain element rms value and linear element effective bandwidth
Blankenship, G. L.↗
Loudness (annoyance), prediction procedure for steady sounds
Method has been devised to predict loudness level of any steady sound solely from its measured power spectrum level. Method is based on assumption that, with respect to loudness sensation, the human auditory system acts as open-loop transmission system with transmittance function determined from measured tone curves.
Howes, W. L.↗
Characteristics of hingeless rotors with hub moment feedback controls including experimental rotor frequency response, Volume 1
Wind tunnel tests to determine the dynamic characteristics of hingeless rotors with hub moment feedback controls and to acquire experimental hingeless rotor transfer functions are discussed. Rotor transfer functions were calculated from data acquired during open loop frequency response tests. The transfer functions are linear and present the rotor longitudinal and lateral frequency responses to collective pitch, longitudinal cyclic pitch, and lateral cyclic pitch. The theoretical analysis was based on the rigid blade flapping model coupled with appropriate control system and cyclic pitch actuator equations of motion.
Kuczynski, W. A.↗
Control of an artificial infrared environment to simulate complex, time varying orbital conditions
A computer-controlled infrared simulation system has recently been developed for thermal vacuum ground testing of spacecraft in the Space Environment Simulation Laboratory of the NASA Manned Spacecraft Center. The system can simultaneously follow as many as 30 separate time-varying intensity profiles for irradiation of different areas of a test spacecraft, producing an environment that more closely resembles the changing conditions experienced by an orbiting spacecraft. A description of the hardware is included, but emphasis is placed upon computer techniques that have been developed to maximize the capabilities of the control system within the constraints imposed by a limited computer capability. Among the topics discussed are open-loop control, closed-loop control, manual alteration of profiles, compensation for slow response of the radiation source, and compensation for interacting control zones. Examples of typical results obtained using the control system are also presented.
Dewey, R. L.↗
Singular perturbations in the state regulator problem
Most of the results of singular perturbation theory have been concerned with initial value problems whereas optimal control problems are of two-point boundary value type. The portions of this theory applicable to the open loop state regulator problem are reviewed. For obtaining approximate solutions to the state regulator problem the method of matched asymptotic expansions is employed. This method has been developed in connection with certain fluid mechanics problems and is applicable to nonlinear as well as linear problems. It has been found in the past to be advantageous not to formulate this method generally but to apply it to each individual problem and this approach is adopted here. A general recipe for the method is given and its application is illustrated by using the method to obtain an approximate solution to a simple, specific state regulator problem.
Ardema, M. D.↗
Frequency response of a vaporization process to distorted acoustic disturbances
The open-loop response properties expressed as the mass vaporized in phase and out of phase with the pressure oscillations were numerically evaluated for a vaporizing n-heptane droplet. The evaluation includes the frequency dependence introduced by periodic oscillation in droplet mass and temperature. A given response was achieved over a much broader range of frequency with harmonically distorted disturbances than with sinusoidal disturbances. The results infer that distortion increases the probability of incurring spontaneous and triggered instability in any rocket engine combustor by broadening the frequency range over which the vaporization process can support an instability.
Heidmann, M. F.↗
Feasibility study of a bidirectional jet flap device for application to helicopter rotor blades. Phase 2: Lift controller development
A bidirectional jet flap device called the variable deflection thruster (VDT) has been investigated for possible application to helicopter rotors. This investigation included the development and testing of a fluidic lift control system for the VDT-blade model making use of the test result that VDT-blade lift can be sensed from the differential pressure at midchord. This study constitutes a long-range program to develop blown control techniques for stabilizing the higher harmonic modes of helicopter rotors. Wind tunnel tests were conducted using a three-sectioned, two-dimensional VDT-blade model having individually controlled VDT jet flaps in each section. Steady-state tests were conducted without the fluidic lift controller (open loop) for both full-span blowing and for the model center section blowing only. Steady-state tests were conducted with the center section blowing only using the fluidic lift controller (close-loop) to control the lift on the model center section. Dynamic tests were conducted using the complete model with the VDT jet in the model center section oscillating at various frequencies and also using the model center section alone on a single endplate to obtain finite-aspect-ratio effects. Fair agreement was obtained between theory and experimental results.
Rose, R. E.↗
Control system estimation and design for aerospace vehicles with time delay
The problems of estimation and control of discrete, linear, time-varying systems are considered. Previous solutions to these problems involved either approximate techniques, open-loop control solutions, or results which required excessive computation. The estimation problem is solved by two different methods, both of which yield the identical algorithm for determining the optimal filter. The partitioned results achieve a substantial reduction in computation time and storage requirements over the expanded solution, however. The results reduce to the Kalman filter when no delays are present in the system. The control problem is also solved by two different methods, both of which yield identical algorithms for determining the optimal control gains. The stochastic control is shown to be identical to the deterministic control, thus extending the separation principle to time delay systems. The results obtained reduce to the familiar optimal control solution when no time delays are present in the system.
Allgaier, G. R.↗