Development of passive temperature control coatings for use on the Apollo vehicle ablative thermal protection system Final report
Passive temperature control coatings for Apollo spacecraft ablative thermal protection system
TEMPERATURE CONTROL↗
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Results for “controller development”
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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Development of techniques for controlling warpage and residual stresses in welded structures Final report
Techniques for controlling warpage and residual stresses in welded aluminum alloy structures for Saturn project
Cole, D. Q.↗
Development and evaluation of controlled viscosity coatings for superalloys
Controlled viscosity glass based protective coatings for superalloys for turbine blade applications
Chapman, J. W.↗
The development of effective fracture control procedures for space shuttle
Structural fracture causes and control procedures for space shuttles
Tiffany, C. F.↗
Development of a digital control system for a spacecraft propulsion test facility
A digital computer control and abort system which is used at NASA-Lewis research center is described. The system was designed to control test operations such as rocket engine testing, structure testing, and wind tunnel tests. Because of the nature of spacecraft system testing, particularly rocket engine testing, the unique features of the system are, control function updating at a 20 millisecond rate, continuous abort monitoring and a software system designed for short duration tests rather than continuous on-line control. To accomplish these system requirements, special hardware was designed. The presentation includes a description of the computer system and special interface hardware as well as a general description of the software used.
Smalley, R. R.↗
Development of a digital control system for a spacecraft propulsion test facility.
A digital computer control and abort system which is used at NASA-Lewis Research Center's Plum Brook Test Facilities is described. The system was designed by NASA personnel to control test operations such as rocket engine testing, structure testing, and wind tunnel tests. Because of the nature of spacecraft system testing, particularly rocket engine testing, the unique features of the system are, control function updating at a 20 millisecond rate, continuous abort monitoring and a software system designed for short duration tests rather than continuous on-line control. To accomplish these system requirements, special hardware was designed. The presentation will include a description of the computer system including special interface hardware as well as a general description of the software used.
Smalley, R. R.↗
Development of a digital control system for a spacecraft propulsion test facility.
Description of a digital computer control and abort system designed by NASA personnel to control test operations such as rocket engine testing, structure testing, and wind tunnel tests. Because of the nature of spacecraft system testing, particularly rocket engine testing, the unique features of the system are, control function updating at a 20 millisecond rate, continuous abort monitoring, and a software system designed for short duration tests rather than continuous on-line control. The presentation includes a description of the computer system and special interface hardware as well as a general description of the software used.
Smalley, R. R.↗
The design and development of an automatic control system for the in-duct cancellation of spinning modes of sound
The reduction is discussed of the discrete tones generated by jet engines which is essential for jet aircraft to meet present and proposed noise standards. The discrete tones generated by the blades and vanes propagate in the inlet and exhaust duct in the form of spiraling acoustic waves, or spinning modes. The reduction of these spinning modes by the cancellation effect of the combination of two acoustic fields was investigated. The spinning mode synthesizer provided the means for effective study of this noise reduction scheme. Two sets of electrical-acoustical transducers located in an equally-spaced circular array simultaneously generate a specified spinning mode and the cancelling mode. Analysis of the wave equation for the synthesizer established the optimum cancelling array acoustic parameters for maximum sound pressure level reduction. The parameter dependence of the frequency ranges of propagation of single, specified circumferential modes generated by a single array, and of effective cancellation of the modes generated by two arrays, was determined. Substantial sound pressure level reduction was obtained for modes within these limits.
Harrington, W. W.↗
Development of the Apollo Control Network
Description of activities associated with photogrammetric reduction of photography and support data gathered by Apollo spacecraft in lunar orbit. The aim of these activities is to combine all data from Apollo 15, 16, and 17 missions for the purpose of forming a unified control system on the moon called the Apollo Control Network. The status of efforts at reduction of data from each of these missions is summarized along with a proposed scheme for combining the three missions in a simultaneous reduction. Plans to expand the network by use of Apollo oblique mapping photography are also discussed, and the results of an oblique triangulation test are evaluated.
Hassell, J. R.↗
Control and computation module development
Software development methods have been investigated and two test bed projects have been chosen to evaluate application techniques of the 8080A and support microcircuits which will satisfy DSN requirements. Final recommendations will reflect successful JPL applications experience.
Winkelstein, R. A.↗
Development of a standardized control module for dc-to-dc converters
The electrical performance of a power processor depends on the quality of its control system. Most of the existing control circuits suffer one or more of the following imperfections that tend to restrict their respective utility: (1) inability to perform different modes of duty cycle control; (2) lack of immunity to output filter parameter changes, and (3) lack of capability to provide power component stress limiting on an instantaneous basis. The three lagging aspects of existing control circuits have been used to define the major objectives of the current Standardized Control Module (SCM) Program. Detailed information on the SCM functional block diagram, its universality, and performance features, circuit description, test results, and modeling and analysis efforts are presented.
Yu, Y.↗
A Mathematical Model for Vertical Attitude Takeoff and Landing (VATOL) Aircraft Simulation: Model Description Application - Volume 1
A mathematical model of a high performance airplane capable of vertical attitude takeoff and landing (VATOL) was developed. An off line digital simulation program incorporating this model was developed to provide trim conditions and dynamic check runs for the piloted simulation studies and support dynamic analyses of proposed VATOL configuration and flight control concepts. Development details for the various simulation component models and the application of the off line simulation program, Vertical Attitude Take-Off and Landing Simulation (VATLAS), to develop a baseline control system for the Vought SF-121 VATOL airplane concept are described.
Fortenbaugh, R. L.↗
Research developing closed loop roll control for magnetic balance systems
Computer inputs were interfaced to the magnetic balance outputs to provide computer position control and data acquisition. The use of parameter identification of a means of determining dynamic characteristics was investigated. The thyraton and motor generator power supplies for the pitch and yaw degrees of freedom were repaired. Topics covered include: choice of a method for handling dynamic system data; applications to the magnetic balance; the computer interface; and wind tunnel tests, results, and error analysis.
Covert, E. E.↗
Development of a process control computer device for the adaptation of flexible wind tunnel walls
In wind tunnel tests, the problems arise of determining the wall pressure distribution, calculating the wall contour, and controlling adjustment of the walls. This report shows how these problems have been solved for the high speed wind tunnel of the Technical University of Berlin.
Barg, J.↗
Development of laminar flow control wing surface porous structure
It was concluded that the chordwise air collection method, which actually combines chordwise and spanwise air collection, is the best of the designs conceived up to this time for full chord laminar flow control (LFC). Its shallower ducting improved structural efficiency of the main wing box resulting in a reduction in wing weight, and it provided continuous support of the chordwise panel joints, better matching of suction and clearing airflow requirements, and simplified duct to suction source minifolding. Laminar flow control on both the upper and lower surfaces was previously reduced to LFC suction on the upper surface only, back to 85 percent chord. The study concludes that, in addition to reduced wing area and other practical advantages, this system would be lighter because of the increase in effective structural wing thickness.
Klotzsche, M.↗
Interface For Fault-Tolerant Control System
Interface unit and controller emulator developed for research on electronic helicopter-flight-control systems equipped with artificial intelligence. Interface unit interrupt-driven system designed to link microprocessor-based, quadruply-redundant, asynchronous, ultra-reliable, fault-tolerant control system (controller) with electronic servocontrol unit that controls set of hydraulic actuators. Receives digital feedforward messages from, and transmits digital feedback messages to, controller through differential signal lines or fiber-optic cables (thus far only differential signal lines have been used). Analog signals transmitted to and from servocontrol unit via coaxial cables.
Shaver, Charles↗
Further developments in modeling digital control systems with MA-prefiltered measurements
State variable representations are presented for a continuous-time plant driven by a zero-order-hold with multirate-sampled measurements prefiltered by multi-input/multi-output moving average (MA) processes. These representations have broad application, but are known to be useful in the aerospace field for modeling systems with star trackers and some state-of-the-art rate-gyroscopes and accelerometers.
Polites, Michael E.↗
Software development for avionics SSME control and diagnostics
A study was made of software to integrate data from about 500 sensors that monitor the Space Shuttle Main Engine (SSME) and to make decisions for real-time control. Such software is expected to be applicable to other distributed systems as well. This study investigated the use of pattern recognition and other techniques to detect trends that could lead to major damage to the SSME and which would allow an orderly shutdown of the SSME before such damage could occur.
Choudry, A.↗