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1NASA Technical Reports Server (NTRS) 19900000774: Modeling And Control System Design And Analysis Tools For Flexible Structures

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Described here are Boeing software tools used for the development of control laws of flexible structures. The Boeing Company has developed a software tool called Modern Control Software Package (MPAC). MPAC provides the environment necessary for linear model development, analysis, and controller design for large models of flexible structures. There are two features of MPAC which are particularly appropriate for use with large models: (1) numerical accuracy and (2) label-driven nature. With the first feature MPAC uses double precision arithmetic for all numerical operations and relies on EISPAC and LINPACK for the numerical foundation. With the second feature, all MPAC model inputs, outputs, and states are referenced by user-defined labels. This feature allows model modification while maintaining the same state, input, and output names. In addition, there is no need for the user to keep track of a model variable's matrix row and colunm locations. There is a wide range of model manipulation, analysis, and design features within the numerically robust and flexible environment provided by MPAC. Models can be built or modified using either state space or transfer function representations. Existing models can be combined via parallel, series, and feedback connections; and loops of a closed-loop model may be broken for analysis.

“NASA Technical Reports Server (NTRS) 19900000774: Modeling And Control System Design And Analysis Tools For Flexible Structures” Metadata:

  • Title: ➤  NASA Technical Reports Server (NTRS) 19900000774: Modeling And Control System Design And Analysis Tools For Flexible Structures
  • Author: ➤  
  • Language: English

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2Control System Analysis And Design

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Described here are Boeing software tools used for the development of control laws of flexible structures. The Boeing Company has developed a software tool called Modern Control Software Package (MPAC). MPAC provides the environment necessary for linear model development, analysis, and controller design for large models of flexible structures. There are two features of MPAC which are particularly appropriate for use with large models: (1) numerical accuracy and (2) label-driven nature. With the first feature MPAC uses double precision arithmetic for all numerical operations and relies on EISPAC and LINPACK for the numerical foundation. With the second feature, all MPAC model inputs, outputs, and states are referenced by user-defined labels. This feature allows model modification while maintaining the same state, input, and output names. In addition, there is no need for the user to keep track of a model variable's matrix row and colunm locations. There is a wide range of model manipulation, analysis, and design features within the numerically robust and flexible environment provided by MPAC. Models can be built or modified using either state space or transfer function representations. Existing models can be combined via parallel, series, and feedback connections; and loops of a closed-loop model may be broken for analysis.

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  • Title: ➤  Control System Analysis And Design
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3NASA Technical Reports Server (NTRS) 19760021169: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration. [performance Tests Of Remote Control Equipment For Roving Vehicles

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Problems related to the design and control of an autonomous rover for the purpose of unmanned exploration of the planets were considered. Building on the basis of prior studies, a four wheeled rover of unusual mobility and maneuverability was further refined and tested under both laboratory and field conditions. A second major effort was made to develop autonomous guidance. Path selection systems capable of dealing with relatively formidable hazard and terrains involving various short range (1.0-3.0 meters), hazard detection systems using a triangulation detection concept were simulated and evaluated. The mechanical/electronic systems required to implement such a scheme were constructed and tested. These systems include: laser transmitter, photodetectors, the necessary data handling/controlling systems and a scanning mast. In addition, a telemetry system to interface the vehicle, the off-board computer and a remote control module for operator intervention were developed. Software for the autonomous control concept was written. All of the systems required for complete autonomous control were shown to be satisfactory except for that portion of the software relating to the handling of interrupt commands.

“NASA Technical Reports Server (NTRS) 19760021169: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration. [performance Tests Of Remote Control Equipment For Roving Vehicles” Metadata:

  • Title: ➤  NASA Technical Reports Server (NTRS) 19760021169: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration. [performance Tests Of Remote Control Equipment For Roving Vehicles
  • Author: ➤  
  • Language: English

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4DTIC ADA1039221: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

By

In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

“DTIC ADA1039221: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.” Metadata:

  • Title: ➤  DTIC ADA1039221: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.
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  • Language: English

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5NASA Technical Reports Server (NTRS) 19750013563: Research Study On Stabilization And Control. Modern Sampled-data Control Theory. Analysis And Design Of The Digital Large Space Telescope System

By

Dynamic modeling of a low cost single axis LST system and the pointing stability of that system are investigated. The effects of nonlinear friction of the bearings of the reaction wheels, quantization, and sensor noise on the pointing error are covered. In addition, data are given on self sustained oscillations of the system induced by quantization and methods of evaluating attitude error of the digital LST.

“NASA Technical Reports Server (NTRS) 19750013563: Research Study On Stabilization And Control. Modern Sampled-data Control Theory. Analysis And Design Of The Digital Large Space Telescope System” Metadata:

  • Title: ➤  NASA Technical Reports Server (NTRS) 19750013563: Research Study On Stabilization And Control. Modern Sampled-data Control Theory. Analysis And Design Of The Digital Large Space Telescope System
  • Author: ➤  
  • Language: English

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6NASA Technical Reports Server (NTRS) 19720013168: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration

By

Investigation of problems related to control of a mobile planetary vehicle according to a systematic plan for the exploration of Mars has been undertaken. Problem areas receiving attention include: (1) overall systems analysis; (2) vehicle configuration and dynamics; (3) toroidal wheel design and evaluation; (4) on-board navigation systems; (5) satellite-vehicle navigation systems; (6) obstacle detection systems; (7) terrain sensing, interpretation and modeling; (8) computer simulation of terrain sensor-path selection systems; and (9) chromatographic systems design concept studies. The specific tasks which have been undertaken are defined and the progress which has been achieved during the period July 1, 1971 to December 31, 1971 is summarized.

“NASA Technical Reports Server (NTRS) 19720013168: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration” Metadata:

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7Detail Design And Analysis Of An Access Control System For A Multi-backend Database System.

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This thesis describes the design and analysis of an access control mechanism for a multi-backend database system (MDBS). MDBS utilizes a minicomputer as the controller and a number of minicomputers and their disk systems as the backends. The database is distributed over the dedicated disk systems of the backends. The operations on the database are performed by the backends in parallel. Thus, the performance gain of the system is dependent on the number of backends in the system. Each backend performs its own access control operations using duplicated access control information.

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  • Title: ➤  Detail Design And Analysis Of An Access Control System For A Multi-backend Database System.
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8NASA Technical Reports Server (NTRS) 19950014144: Preliminary Control System Design And Analysis For The Space Station Furnace Facility Thermal Control System

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This report presents the Space Station Furnace Facility (SSFF) thermal control system (TCS) preliminary control system design and analysis. The SSFF provides the necessary core systems to operate various materials processing furnaces. The TCS is defined as one of the core systems, and its function is to collect excess heat from furnaces and to provide precise cold temperature control of components and of certain furnace zones. Physical interconnection of parallel thermal control subsystems through a common pump implies the description of the TCS by coupled nonlinear differential equations in pressure and flow. This report formulates the system equations and develops the controllers that cause the interconnected subsystems to satisfy flow rate tracking requirements. Extensive digital simulation results are presented to show the flow rate tracking performance.

“NASA Technical Reports Server (NTRS) 19950014144: Preliminary Control System Design And Analysis For The Space Station Furnace Facility Thermal Control System” Metadata:

  • Title: ➤  NASA Technical Reports Server (NTRS) 19950014144: Preliminary Control System Design And Analysis For The Space Station Furnace Facility Thermal Control System
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  • Language: English

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9The Use Of A Microcomputer System As An Aid To Classical And Digital Control System Design And Analysis.

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This report presents the Space Station Furnace Facility (SSFF) thermal control system (TCS) preliminary control system design and analysis. The SSFF provides the necessary core systems to operate various materials processing furnaces. The TCS is defined as one of the core systems, and its function is to collect excess heat from furnaces and to provide precise cold temperature control of components and of certain furnace zones. Physical interconnection of parallel thermal control subsystems through a common pump implies the description of the TCS by coupled nonlinear differential equations in pressure and flow. This report formulates the system equations and develops the controllers that cause the interconnected subsystems to satisfy flow rate tracking requirements. Extensive digital simulation results are presented to show the flow rate tracking performance.

“The Use Of A Microcomputer System As An Aid To Classical And Digital Control System Design And Analysis.” Metadata:

  • Title: ➤  The Use Of A Microcomputer System As An Aid To Classical And Digital Control System Design And Analysis.
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  • Language: en_US

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10DTIC ADA1008082: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.

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This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

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  • Title: ➤  DTIC ADA1008082: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.
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  • Language: English

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11NASA Technical Reports Server (NTRS) 19740024189: Asymmetrical Booster Ascent Guidance And Control System Design Study. Volume 4: Sampled Data Stability Analysis Program (SADSAP) User's Guide. [space Shuttle Development

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A users guide to the Sampled Data Stability Analysis Program (SADSAP) is provided. This program is a general purpose sampled data Stability Analysis Program capable of providing frequency response on root locus data.

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  • Title: ➤  NASA Technical Reports Server (NTRS) 19740024189: Asymmetrical Booster Ascent Guidance And Control System Design Study. Volume 4: Sampled Data Stability Analysis Program (SADSAP) User's Guide. [space Shuttle Development
  • Author: ➤  
  • Language: English

“NASA Technical Reports Server (NTRS) 19740024189: Asymmetrical Booster Ascent Guidance And Control System Design Study. Volume 4: Sampled Data Stability Analysis Program (SADSAP) User's Guide. [space Shuttle Development” Subjects and Themes:

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12NASA Technical Reports Server (NTRS) 19730013098: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration

By

Investigation of problems related to the design and control of a mobile planetary vehicle to implement a systematic plan for the exploration of Mars has been undertaken. Problem areas receiving attention include: vehicle configuration, control, dynamics, systems and propulsion; systems analysis; terrain modeling and path selection; and chemical analysis of specimens. The following specific tasks have been under study: vehicle model design, mathematical modeling of a dynamic vehicle, experimental vehicle dynamics, obstacle negotiation, electromechanical controls, collapsibility and deployment, construction of a wheel tester, wheel analysis, payload design, system design optimization, effect of design assumptions, accessory optimal design, on-board computer sybsystem, laser range measurement, discrete obstacle detection, obstacle detection systems, terrain modeling, path selection system simulation and evaluation, gas chromatograph/mass spectrometer system concepts, chromatograph model evaluation and improvement.

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  • Title: ➤  NASA Technical Reports Server (NTRS) 19730013098: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration
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13DTIC ADA251641: Homotopy Methods In Control System Design And Analysis

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The primary objective of this research is to extend and develop homotopy algorithms for a variety of computational problems in control. In addition, these problems are being examined in the context of the algebraic and differential geometry on which the homotopy methods are based. This will enable the classification of solutions to a particular problem and consequently will allow the analyst or designer to extract the most desirable solution.

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14DTIC ADA331630: Analysis And Design Of The Adsorbent Sample Temperature Control In The Volumetric Isotherm System

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The propagation of error in the volumetric isotherm apparatus used at Guild Associates, Inc. is discussed as well as modifications to the apparatus to reduce errors. Investigators found that errors in temperature measurement and/or control may affect vapor-phase and adsorbed-phase concentrations in a complex but predictable manner. Changes to the isotherm apparatus to increase the accuracy of temperature measurements and improve the stability of the temperature control are documented.

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15DTIC ADA1039223: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

By

In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

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  • Title: ➤  DTIC ADA1039223: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.
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  • Language: English

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The book is available for download in "texts" format, the size of the file-s is: 54.13 Mbs, the file-s for this book were downloaded 64 times, the file-s went public at Sun Apr 05 2020.

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16DTIC ADA073342: Design And Analysis Of 777 'Fly-by-Wire' Control System.

By

This document describes the design and implementation of the 'fly-by-wire' despin control system for Program 777. Two designs for the ground loop controller are considered - one using proportional control only and one using proportional plus rate control. It is recommended that the spacecraft be operated at the lower RPM's. Also, recommended are counter limits to minimize transient overshoots to large torque disturbances. (Author)

“DTIC ADA073342: Design And Analysis Of 777 'Fly-by-Wire' Control System.” Metadata:

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  • Language: English

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17DTIC ADA1008084: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.

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This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

“DTIC ADA1008084: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.” Metadata:

  • Title: ➤  DTIC ADA1008084: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.
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18The Use Of A Microcomputer System As An Aid To Classical And Digital Control System Design And Analysis.

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ADA132945

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19DTIC ADA1039220: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

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In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

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20DTIC ADA1039222: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

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In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

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21DTIC ADA1008088: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.

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This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

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22DTIC ADA1039227: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

By

In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

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23NASA Technical Paper 1397... Design And Analysis Of An Active Jet Control System For Helicopter Sling Loads... Science And Technical Information Office, National Aeronautics & Space Administration... January 1979

By

NAS 1.60:1397 Digitized from IA1177308-02-0050 .

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24DTIC ADA100808: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.

By

This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

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25Analysis And Design Of A New Control System For Aerodrome

This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

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26DTIC ADA1008081: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.

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This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

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27Linear Control System Analysis And Design: Conventional And Modern

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Includes bibliographical references

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28NASA Technical Reports Server (NTRS) 20140008284: Design And Analysis Of Morpheus Lander Flight Control System

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The Morpheus Lander is a vertical takeoff and landing test bed vehicle developed to demonstrate the system performance of the Guidance, Navigation and Control (GN&C) system capability for the integrated autonomous landing and hazard avoidance system hardware and software. The Morpheus flight control system design must be robust to various mission profiles. This paper presents a design methodology for employing numerical optimization to develop the Morpheus flight control system. The design objectives include attitude tracking accuracy and robust stability with respect to rigid body dynamics and propellant slosh. Under the assumption that the Morpheus time-varying dynamics and control system can be frozen over a short period of time, the flight controllers are designed to stabilize all selected frozen-time control systems in the presence of parametric uncertainty. Both control gains in the inner attitude control loop and guidance gains in the outer position control loop are designed to maximize the vehicle performance while ensuring robustness. The flight control system designs provided herein have been demonstrated to provide stable control systems in both Draper Ares Stability Analysis Tool (ASAT) and the NASA/JSC Trick-based Morpheus time domain simulation.

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29MATLAB Tools For Control System Analysis And Design

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The Morpheus Lander is a vertical takeoff and landing test bed vehicle developed to demonstrate the system performance of the Guidance, Navigation and Control (GN&C) system capability for the integrated autonomous landing and hazard avoidance system hardware and software. The Morpheus flight control system design must be robust to various mission profiles. This paper presents a design methodology for employing numerical optimization to develop the Morpheus flight control system. The design objectives include attitude tracking accuracy and robust stability with respect to rigid body dynamics and propellant slosh. Under the assumption that the Morpheus time-varying dynamics and control system can be frozen over a short period of time, the flight controllers are designed to stabilize all selected frozen-time control systems in the presence of parametric uncertainty. Both control gains in the inner attitude control loop and guidance gains in the outer position control loop are designed to maximize the vehicle performance while ensuring robustness. The flight control system designs provided herein have been demonstrated to provide stable control systems in both Draper Ares Stability Analysis Tool (ASAT) and the NASA/JSC Trick-based Morpheus time domain simulation.

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30NASA Technical Reports Server (NTRS) 19740019611: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration

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A number of problems related to the design, construction and evaluation of an autonomous roving planetary vehicle and its control and operating systems intended for an unmanned exploration of Mars are studied. Vehicle configuration, dynamics, control, systems and propulsion; systems analysis; terrain sensing and modeling and path selection; and chemical analysis of samples are included.

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31The Design And Analysis Of An Automatic Frequency Control System

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No Abstract Available

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32DTIC ADA1008089: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.

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This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

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33Digital Control System Analysis And Design Global

digital control

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34DTIC ADA1039224: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

By

In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

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35Design And Analysis Of A Robust Accurate Speed Control System By Applying A Digital Compensator

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Abstract: This paper provides further advancement of the D-Partitioning analysis applied to nonlinear digital control system with variable parameters. As a case study, a nonlinear control system for accurate speed control of a dc motor is considered. The Bilinear Tustin Transform method is employed as one of the most precise facilities for systems discretization, where also the Euler's approximation is taken into account. A robust controller design is accomplished by a number of successive steps. Based on the difference equations of its stages, the robust controller can be realized by microcontrollers. The research is a further development of the author’s work on the D-Partitioning analysis and design of nonlinear digital control systems with variable parameters. The suggested tool for analysis is essential and beneficial for the further development of control theory in this area. Keywords: Wheatstone Speed-to-Voltage Converter, Speed Control, Nonlinear, Bilinear approximation, Discretization, D-Partitioning Stability Analysis, Digital Control Systems; http://www.icgst.com/paper.aspx?pid=P1111610484 @ARTICLE { P1111610484, author= "Prof. Kamen M. Yanev", title= "Design and Analysis of a Robust Accurate Speed Control System by Applying a Digital Compensator", journal= "Automatic Control and System Engineering  ACSE", year= "2016", month= "4", volume= "16", number= "1", pages= "27--36" }

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36Control Design And Analysis Of A Stochastic Network Control System

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A Network Control System (NCS) consists of control components that interact with the plant over a shared network. The system dynamics of a NCS could be subject to noise arising from randomness in the times at which the data is transmitted over the network, corruption of the transmitted data by the communication network, and external disturbances that might affect the plant. A question of interest is to understand how the statistics of the data transmission times affects the system dynamics, and under what conditions the system is stable. Another related issue is designing a controller that meets desired performance specifications (e.g., a specific mean and variance of the system state). Here, we consider a minimal NCS that consists of a plant and a controller, and it is subject to random transmission times, channel corruption and external disturbances. We derive exact dynamics of the first two moments of the system, and use them to derive the stability conditions of the system. We further design a control law that steers the system to a desired mean and variance. Finally, we demonstrate our results using different examples, and show that under some specific conditions, randomness in the data transmission times can even reduce the variability contributed from disturbance.

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37NASA Technical Reports Server (NTRS) 19740018657: Analysis And Design Of A Capsule Landing System And Surface Vehicle Control System For Mars Exploration

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The following tasks related to the design, construction, and evaluation of a mobile planetary vehicle for unmanned exploration of Mars are discussed: (1) design and construction of a 0.5 scale dynamic vehicle; (2) mathematical modeling of vehicle dynamics; (3) experimental 0.4 scale vehicle dynamics measurements and interpretation; (4) vehicle electro-mechanical control systems; (5) remote control systems; (6) collapsibility and deployment concepts and hardware; (7) design, construction and evaluation of a wheel with increased lateral stiffness, (8) system design optimization; (9) design of an on-board computer; (10) design and construction of a laser range finder; (11) measurement of reflectivity of terrain surfaces; (12) obstacle perception by edge detection; (13) terrain modeling based on gradients; (14) laser scan systems; (15) path selection system simulation and evaluation; (16) gas chromatograph system concepts; (17) experimental chromatograph separation measurements and chromatograph model improvement and evaluation.

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38NASA Technical Reports Server (NTRS) 19740074600: Proceedings Of Nuclear Propulsion Conference The Nuclear Rocket Program Criticality And Nuclear Characteristics Of The Kiwi-A Series Of Nuclear Propulsion Test Reactors Neutronic Calculations Of Temperature Effects On Kiwi Reactors Rover Reactor Control Element Worth Calculations Leakage Radiation Fields From The Kiwi-B-1A Design Computations For A Nuclear Rocket Shadow Shield Calculations Of Neutron Activation Dose Rates In Nuclear Rocket Vehicles And Test Facilities Nuclear Heating Of TORY-2-C Hafnium Control Rods Neutron And Gamma Angular Leakage Calculation Of A Kiwi-B Reactor Novel Radiation Calculations On Rocket Reactors Transport Calculations Of The Kiwi-B Neutron Environment Radiation Induced Conversion Of Orthohydrogen To Parahydrogen On The Rift Propellant Tank Startup Studies Of A Nuclear Rocket Reactor. Part 3: Startup Philosophy Control Systems For A Liquid-hydrogen-cooled Kiwi-B Reactor Design And Evaluation Of Electropneumatic Servo Actuators For The NERVA Engine Control And Telemetry Transducer Requirements For Nuclear Powered Vehicles Summary Of Nuclear Radiation Heating Analysis And Cooling System Design Of A Kiwi-B Prototype Rotary Electropneumatic Control Actuator Kiwi-B-1A Power And Temperature Control Systems Re-entry Of Nuclear Rockets Into Earth's Atmosphere Nuclear Rocket Destruct System Requirements Rover Reactor Power Transient Calculations Nuclear Rockets: Safety Problems And Safety Programs Nuclear Safety And Hazards Aspects Of RIFT Flight Operations Transient Reactor Experiments On NERVA Fuel Material Effects Of Liquid Propellant Explosions On Nuclear Rocket Engines The Los Alamos Scientific Laboratory Rover Flight Safety Program A Destruct System For The NERVA Engine E-MAD Facility Design Concept The Kiwi-B-1A Full Power Test Kiwi-B-1A Temperature-reactivity Effects Kiwi-A Prime Disassembly Design Considerations In The Development Of The Liquid Hydrogen Feedsystem For Kiwi-B The Nuclear Rocket Program Criticality And Nuclear Characteristics Of The Kiwi-A Series Of Nuclear Propulsion Test Reactors Neutronics Of Kiwi-B Nuclear Propulsion Reactors Neutronic Calculations Of Temperature Effects On Kiwi Reactors Rover Reactor Control Element Worth Calculations Leakage Radiation Fields From The Kiwi-B-1A Design Computations For A Nuclear Rocket Shadow Shield Calculations Of Neutron Activation Dose Rates In Nuclear Rocket Vehicles And Test Facilities Nuclear Heating Of TORY-2-C Hafnium Control Rods Neutron And Gamma Angular Leakage Calculation Of A Kiwi-B Reactor Novel Radiation Calculations On Rocket Reactors Transport Calculations Of The Kiwi-B Neutron Environment Radiation Induced Conversion Of Orthohydrogen To Parahydrogen On The Rift Propellant Tank Startup Studies Of A Nuclear Rocket Reactor. Part 3: Startup Philosophy Control Systems For A Liquid-hydrogen-cooled Kiwi-B Reactor Design And Evaluation Of Electropneumatic Servo Actuators For The NERVA Engine Control And Telemetry Transducer Requirements For Nuclear Powered Vehicles Summary Of Nuclear Radiation Heating Analysis And Cooling System Design Of A Kiwi-B Prototype Rotary Electropneumatic Control Actuator Kiwi-B-1A Power And Temperature Control Systems Re-entry Of Nuclear Rockets Into Earth's Atmosphere Nuclear Rocket Destruct System Requirements Rover Reactor Power Transient Calculations Nuclear Rockets: Safety Problems And Safety Programs Nuclear Safety And Hazards Aspects Of RIFT Flight Operations Transient Reactor Experiments On NERVA Fuel Material Effects Of Liquid Propellant Explosions On Nuclear Rocket Engines The Los Alamos Scientific Laboratory Rover Flight Safety Program A Destruct System For The NERVA Engine E-MAD Facility Design Concept The Kiwi-B-1A Full Power Test Kiwi-B-1A Temperature-reactivity Effects Kiwi-A Prime Disassembly Design Considerations In The Development Of The Liquid Hydrogen Feedsystem For Kiwi-B

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“NASA Technical Reports Server (NTRS) 19740074600: Proceedings Of Nuclear Propulsion Conference The Nuclear Rocket Program Criticality And Nuclear Characteristics Of The Kiwi-A Series Of Nuclear Propulsion Test Reactors Neutronic Calculations Of Temperature Effects On Kiwi Reactors Rover Reactor Control Element Worth Calculations Leakage Radiation Fields From The Kiwi-B-1A Design Computations For A Nuclear Rocket Shadow Shield Calculations Of Neutron Activation Dose Rates In Nuclear Rocket Vehicles And Test Facilities Nuclear Heating Of TORY-2-C Hafnium Control Rods Neutron And Gamma Angular Leakage Calculation Of A Kiwi-B Reactor Novel Radiation Calculations On Rocket Reactors Transport Calculations Of The Kiwi-B Neutron Environment Radiation Induced Conversion Of Orthohydrogen To Parahydrogen On The Rift Propellant Tank Startup Studies Of A Nuclear Rocket Reactor. Part 3: Startup Philosophy Control Systems For A Liquid-hydrogen-cooled Kiwi-B Reactor Design And Evaluation Of Electropneumatic Servo Actuators For The NERVA Engine Control And Telemetry Transducer Requirements For Nuclear Powered Vehicles Summary Of Nuclear Radiation Heating Analysis And Cooling System Design Of A Kiwi-B Prototype Rotary Electropneumatic Control Actuator Kiwi-B-1A Power And Temperature Control Systems Re-entry Of Nuclear Rockets Into Earth's Atmosphere Nuclear Rocket Destruct System Requirements Rover Reactor Power Transient Calculations Nuclear Rockets: Safety Problems And Safety Programs Nuclear Safety And Hazards Aspects Of RIFT Flight Operations Transient Reactor Experiments On NERVA Fuel Material Effects Of Liquid Propellant Explosions On Nuclear Rocket Engines The Los Alamos Scientific Laboratory Rover Flight Safety Program A Destruct System For The NERVA Engine E-MAD Facility Design Concept The Kiwi-B-1A Full Power Test Kiwi-B-1A Temperature-reactivity Effects Kiwi-A Prime Disassembly Design Considerations In The Development Of The Liquid Hydrogen Feedsystem For Kiwi-B The Nuclear Rocket Program Criticality And Nuclear Characteristics Of The Kiwi-A Series Of Nuclear Propulsion Test Reactors Neutronics Of Kiwi-B Nuclear Propulsion Reactors Neutronic Calculations Of Temperature Effects On Kiwi Reactors Rover Reactor Control Element Worth Calculations Leakage Radiation Fields From The Kiwi-B-1A Design Computations For A Nuclear Rocket Shadow Shield Calculations Of Neutron Activation Dose Rates In Nuclear Rocket Vehicles And Test Facilities Nuclear Heating Of TORY-2-C Hafnium Control Rods Neutron And Gamma Angular Leakage Calculation Of A Kiwi-B Reactor Novel Radiation Calculations On Rocket Reactors Transport Calculations Of The Kiwi-B Neutron Environment Radiation Induced Conversion Of Orthohydrogen To Parahydrogen On The Rift Propellant Tank Startup Studies Of A Nuclear Rocket Reactor. Part 3: Startup Philosophy Control Systems For A Liquid-hydrogen-cooled Kiwi-B Reactor Design And Evaluation Of Electropneumatic Servo Actuators For The NERVA Engine Control And Telemetry Transducer Requirements For Nuclear Powered Vehicles Summary Of Nuclear Radiation Heating Analysis And Cooling System Design Of A Kiwi-B Prototype Rotary Electropneumatic Control Actuator Kiwi-B-1A Power And Temperature Control Systems Re-entry Of Nuclear Rockets Into Earth's Atmosphere Nuclear Rocket Destruct System Requirements Rover Reactor Power Transient Calculations Nuclear Rockets: Safety Problems And Safety Programs Nuclear Safety And Hazards Aspects Of RIFT Flight Operations Transient Reactor Experiments On NERVA Fuel Material Effects Of Liquid Propellant Explosions On Nuclear Rocket Engines The Los Alamos Scientific Laboratory Rover Flight Safety Program A Destruct System For The NERVA Engine E-MAD Facility Design Concept The Kiwi-B-1A Full Power Test Kiwi-B-1A Temperature-reactivity Effects Kiwi-A Prime Disassembly Design Considerations In The Development Of The Liquid Hydrogen Feedsystem For Kiwi-B” Metadata:

  • Title: ➤  NASA Technical Reports Server (NTRS) 19740074600: Proceedings Of Nuclear Propulsion Conference The Nuclear Rocket Program Criticality And Nuclear Characteristics Of The Kiwi-A Series Of Nuclear Propulsion Test Reactors Neutronic Calculations Of Temperature Effects On Kiwi Reactors Rover Reactor Control Element Worth Calculations Leakage Radiation Fields From The Kiwi-B-1A Design Computations For A Nuclear Rocket Shadow Shield Calculations Of Neutron Activation Dose Rates In Nuclear Rocket Vehicles And Test Facilities Nuclear Heating Of TORY-2-C Hafnium Control Rods Neutron And Gamma Angular Leakage Calculation Of A Kiwi-B Reactor Novel Radiation Calculations On Rocket Reactors Transport Calculations Of The Kiwi-B Neutron Environment Radiation Induced Conversion Of Orthohydrogen To Parahydrogen On The Rift Propellant Tank Startup Studies Of A Nuclear Rocket Reactor. Part 3: Startup Philosophy Control Systems For A Liquid-hydrogen-cooled Kiwi-B Reactor Design And Evaluation Of Electropneumatic Servo Actuators For The NERVA Engine Control And Telemetry Transducer Requirements For Nuclear Powered Vehicles Summary Of Nuclear Radiation Heating Analysis And Cooling System Design Of A Kiwi-B Prototype Rotary Electropneumatic Control Actuator Kiwi-B-1A Power And Temperature Control Systems Re-entry Of Nuclear Rockets Into Earth's Atmosphere Nuclear Rocket Destruct System Requirements Rover Reactor Power Transient Calculations Nuclear Rockets: Safety Problems And Safety Programs Nuclear Safety And Hazards Aspects Of RIFT Flight Operations Transient Reactor Experiments On NERVA Fuel Material Effects Of Liquid Propellant Explosions On Nuclear Rocket Engines The Los Alamos Scientific Laboratory Rover Flight Safety Program A Destruct System For The NERVA Engine E-MAD Facility Design Concept The Kiwi-B-1A Full Power Test Kiwi-B-1A Temperature-reactivity Effects Kiwi-A Prime Disassembly Design Considerations In The Development Of The Liquid Hydrogen Feedsystem For Kiwi-B The Nuclear Rocket Program Criticality And Nuclear Characteristics Of The Kiwi-A Series Of Nuclear Propulsion Test Reactors Neutronics Of Kiwi-B Nuclear Propulsion Reactors Neutronic Calculations Of Temperature Effects On Kiwi Reactors Rover Reactor Control Element Worth Calculations Leakage Radiation Fields From The Kiwi-B-1A Design Computations For A Nuclear Rocket Shadow Shield Calculations Of Neutron Activation Dose Rates In Nuclear Rocket Vehicles And Test Facilities Nuclear Heating Of TORY-2-C Hafnium Control Rods Neutron And Gamma Angular Leakage Calculation Of A Kiwi-B Reactor Novel Radiation Calculations On Rocket Reactors Transport Calculations Of The Kiwi-B Neutron Environment Radiation Induced Conversion Of Orthohydrogen To Parahydrogen On The Rift Propellant Tank Startup Studies Of A Nuclear Rocket Reactor. Part 3: Startup Philosophy Control Systems For A Liquid-hydrogen-cooled Kiwi-B Reactor Design And Evaluation Of Electropneumatic Servo Actuators For The NERVA Engine Control And Telemetry Transducer Requirements For Nuclear Powered Vehicles Summary Of Nuclear Radiation Heating Analysis And Cooling System Design Of A Kiwi-B Prototype Rotary Electropneumatic Control Actuator Kiwi-B-1A Power And Temperature Control Systems Re-entry Of Nuclear Rockets Into Earth's Atmosphere Nuclear Rocket Destruct System Requirements Rover Reactor Power Transient Calculations Nuclear Rockets: Safety Problems And Safety Programs Nuclear Safety And Hazards Aspects Of RIFT Flight Operations Transient Reactor Experiments On NERVA Fuel Material Effects Of Liquid Propellant Explosions On Nuclear Rocket Engines The Los Alamos Scientific Laboratory Rover Flight Safety Program A Destruct System For The NERVA Engine E-MAD Facility Design Concept The Kiwi-B-1A Full Power Test Kiwi-B-1A Temperature-reactivity Effects Kiwi-A Prime Disassembly Design Considerations In The Development Of The Liquid Hydrogen Feedsystem For Kiwi-B
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“NASA Technical Reports Server (NTRS) 19740074600: Proceedings Of Nuclear Propulsion Conference The Nuclear Rocket Program Criticality And Nuclear Characteristics Of The Kiwi-A Series Of Nuclear Propulsion Test Reactors Neutronic Calculations Of Temperature Effects On Kiwi Reactors Rover Reactor Control Element Worth Calculations Leakage Radiation Fields From The Kiwi-B-1A Design Computations For A Nuclear Rocket Shadow Shield Calculations Of Neutron Activation Dose Rates In Nuclear Rocket Vehicles And Test Facilities Nuclear Heating Of TORY-2-C Hafnium Control Rods Neutron And Gamma Angular Leakage Calculation Of A Kiwi-B Reactor Novel Radiation Calculations On Rocket Reactors Transport Calculations Of The Kiwi-B Neutron Environment Radiation Induced Conversion Of Orthohydrogen To Parahydrogen On The Rift Propellant Tank Startup Studies Of A Nuclear Rocket Reactor. Part 3: Startup Philosophy Control Systems For A Liquid-hydrogen-cooled Kiwi-B Reactor Design And Evaluation Of Electropneumatic Servo Actuators For The NERVA Engine Control And Telemetry Transducer Requirements For Nuclear Powered Vehicles Summary Of Nuclear Radiation Heating Analysis And Cooling System Design Of A Kiwi-B Prototype Rotary Electropneumatic Control Actuator Kiwi-B-1A Power And Temperature Control Systems Re-entry Of Nuclear Rockets Into Earth's Atmosphere Nuclear Rocket Destruct System Requirements Rover Reactor Power Transient Calculations Nuclear Rockets: Safety Problems And Safety Programs Nuclear Safety And Hazards Aspects Of RIFT Flight Operations Transient Reactor Experiments On NERVA Fuel Material Effects Of Liquid Propellant Explosions On Nuclear Rocket Engines The Los Alamos Scientific Laboratory Rover Flight Safety Program A Destruct System For The NERVA Engine E-MAD Facility Design Concept The Kiwi-B-1A Full Power Test Kiwi-B-1A Temperature-reactivity Effects Kiwi-A Prime Disassembly Design Considerations In The Development Of The Liquid Hydrogen Feedsystem For Kiwi-B The Nuclear Rocket Program Criticality And Nuclear Characteristics Of The Kiwi-A Series Of Nuclear Propulsion Test Reactors Neutronics Of Kiwi-B Nuclear Propulsion Reactors Neutronic Calculations Of Temperature Effects On Kiwi Reactors Rover Reactor Control Element Worth Calculations Leakage Radiation Fields From The Kiwi-B-1A Design Computations For A Nuclear Rocket Shadow Shield Calculations Of Neutron Activation Dose Rates In Nuclear Rocket Vehicles And Test Facilities Nuclear Heating Of TORY-2-C Hafnium Control Rods Neutron And Gamma Angular Leakage Calculation Of A Kiwi-B Reactor Novel Radiation Calculations On Rocket Reactors Transport Calculations Of The Kiwi-B Neutron Environment Radiation Induced Conversion Of Orthohydrogen To Parahydrogen On The Rift Propellant Tank Startup Studies Of A Nuclear Rocket Reactor. Part 3: Startup Philosophy Control Systems For A Liquid-hydrogen-cooled Kiwi-B Reactor Design And Evaluation Of Electropneumatic Servo Actuators For The NERVA Engine Control And Telemetry Transducer Requirements For Nuclear Powered Vehicles Summary Of Nuclear Radiation Heating Analysis And Cooling System Design Of A Kiwi-B Prototype Rotary Electropneumatic Control Actuator Kiwi-B-1A Power And Temperature Control Systems Re-entry Of Nuclear Rockets Into Earth's Atmosphere Nuclear Rocket Destruct System Requirements Rover Reactor Power Transient Calculations Nuclear Rockets: Safety Problems And Safety Programs Nuclear Safety And Hazards Aspects Of RIFT Flight Operations Transient Reactor Experiments On NERVA Fuel Material Effects Of Liquid Propellant Explosions On Nuclear Rocket Engines The Los Alamos Scientific Laboratory Rover Flight Safety Program A Destruct System For The NERVA Engine E-MAD Facility Design Concept The Kiwi-B-1A Full Power Test Kiwi-B-1A Temperature-reactivity Effects Kiwi-A Prime Disassembly Design Considerations In The Development Of The Liquid Hydrogen Feedsystem For Kiwi-B” Subjects and Themes:

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39NASA Technical Reports Server (NTRS) 19820021477: Development Of Preliminary Design Concept For Multifunction Display And Control System For Orbiter Crew Station. Task 3: Concept Analysis

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The access schema developed to access both individual switch functions as well as automated or semiautomated procedures for the orbital maneuvering system and electrical power and distribution and control system discussed and the operation of the system is described. Feasibility tests and analyses used to define display parameters and to select applicable hardware choices for use in such a system are presented and the results are discussed.

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40Linear Control System Analysis And Design: Conventional And Modern

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The access schema developed to access both individual switch functions as well as automated or semiautomated procedures for the orbital maneuvering system and electrical power and distribution and control system discussed and the operation of the system is described. Feasibility tests and analyses used to define display parameters and to select applicable hardware choices for use in such a system are presented and the results are discussed.

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41DTIC ADA103922: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

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In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

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42DTIC ADA1039229: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

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In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

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43DTIC ADA1008083: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.

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This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

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44DTIC ADA1008080: Flight Control System Analysis And Design For A Remotely Piloted Vehicle With Thrust Vectoring Unit.

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This study investigated the stability and control of a remotely piloted vehicle (RPV) with a thrust vectoring unit attached. All geometric and aerodynamic data was generated and used to analyze the RPV. Specific handling qualities were developed and compared with the RPV characteristics. This comparison indicated that the RPV was too oscillatory in both the phugoid and dutch roll modes. Also, the RPV displayed a dominant spiral mode. A flight control system was synthesized to eliminate these traits. Evaluation of this flight control system was conducted through the use of three different sensitivity studies and a nonlinear simulation. In addition, a model matching application was examined for this RPV. Model matching entails using design procedures to synthesize an expanded flight control system so that the RPV has dynamic characteristics similar to the F-15. (Author)

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45Assessment Of Control And Monitoring System Design Security Using The Attack Security Tree Analysis Method

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Because of the efficiency of the system and the fact that it successfully completed the tasks that were given to it under specific conditions, we are compelled to look for a way to measure these requirements according to the conditions and guidelines that were established by the people who make use of the system. Conduct an investigation into the many techniques that are available for use in analysis in light of the following conditions: i) sufficient time to detect the mistake, ii) time to maintenance, iii) the total number of constituents involved in the analytical process, and iv) an explanation of the level of complexity provided to the user. In this article, we will provide a concise overview of a number of different approaches, along with our recommendations for the most effective ones based on the issues raised earlier.

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46DTIC ADA162036: Design And Analysis Of Control Laws For The Vertical Seeking Seat And The MICRAD (Microwave Radiometric) Attitude Reference System

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The Maximum Performance Ejection Seat (MPES) or Vertical Seeking Seat (VSS) escape system requires a vertical reference to provide commands for the control system. Previous tests of the MPES/VSS system performed using a strap- down vertical reference system which was initialized at the planned 'launch' attitude. Although this attitude hand-off is satisfactory for initial tests, the operational system should use an autonomous reference system such as the Microwave Radiometric (MICRAD) Attitude Reference System (MARS). One problem with using MARS to provide error signals to the VSS control system is that the MARS outputs vary significantly depending on whether the local earth's surface is land or water. This variation changes the control system gain resulting in degraded performance. As a result, efforts were initiated to develop alternatives and/or improvements to control laws studied previously at the Naval Weapons Center. An alternate control law was developed and evaluated using a digital simulation. Results indicated that this control law provided good performance and adequately compensated for variations in the MARS outputs.

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47DTIC ADA136758: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase 1. Requirements Analysis And Preliminary Design. Phase 2. Detailed Design

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The Air Force Wright Aeronautical Laboratories (AFWAL) Aero Propulsion Laboratory has been sponsoring research and development programs directed toward applying advanced solid state power switching and computer control technology to aircraft electrical power systems. Development of components and subsystems utilizing solid state power switching and microprocessor-based computer technology has progressed rapidly. Multiplexing techniques have been developed for transmission and processing of electrical system control data. This data usually consists of a large number of discrete (on/off) signals and information for solving control logic equations. Multiplex hardware and software designs have been optimized for electrical system control applications such as the B-1 E-Mux system. This, however, results in high initial development, integration and logistics costs. On large aircraft the amount of signal processing and data transfer may justify the use of a separate and optimized multiplex system for electrical system control; however, in the case of smaller aircraft this may not be the most cost effective solution.

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48DTIC ADA1039226: Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Requirements Analysis And Conceptual Design.

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In Task 1, the requirements for the electrical power system and the integrated power system control were defined. In Task 2, three conceptual designs for the electrical power system were prepared. Each design incorporated a different data bus architecture, integrated, hierarchical, and non-integrated dedicated. The three designs were evaluated for application to a two engine tactical aircraft. Processor and data bus loading were examined for each architecture. Based on the evaluation, the conceptual design based on the integrated architecture is recommended for preliminary design in Task 3, Phase I. (Author)

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49DTIC AD0919769: Drone Control And Data Retrieval System (DCDRS). Preliminary Design Study Final Report. Volume 3. Trade Studies And Analyses. Part 2. Man-Machine Interface Analysis

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Contents: Analysis and Technical Approach; Functional and Technical Characteristics; Mission and Flight Planning and Replanning; Orientation and Briefing; Checkout and Maintenance; Reporting; Launch; Handoffs; Enroute Vehicle and Mode Control; Situation Monitoring; Status Monitoring; Mission Execution; Target Acquisition and Cueing Aids; Vehicle Control During Weapon Delivery; Bomb Damage Assessment; Recovery; Specific Areas of Investigation; and Conclusions WITH Recommendations.

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50Fuzzy Logic-based Energy Management System For A Microgrid With Hybrid Energy Storage: Design, Control, And Comparative Analysis

This paper presents a fuzzy logic-based energy management controller for a microgrid with a hybrid energy storage system. The microgrid integrates intermittent renewable energy sources. To provide high quality, reliable and sustainable power, the microgrid depends on energy storage devices. The proposed fuzzy logic-based energy management controller controls the energy storage system’s power electronic converters by generating switching pulses based on the generation availability, load requirement, SOCs of battery, and supercapacitor. Additionally, a fuzzy logic-based energy management system is planned in such a way that high power needs are satisfied by supercapacitors and high energy needs are satisfied by batteries. To highlight the key benefits of utilizing a fuzzy logic-controlled hybrid energy storage system over PI -a controller-based cascaded dual loop energy management system, a comparative study is carried out. The results of the same is discussed elaborately in this paper. These studies were simulated using the MATLAB/Simulink software package.

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