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Command and Control (C2) is an important eliminate to military operations. This is a concept that has been around for a long time and is recognized for its importance on military effectiveness. However, identifying the scope of C2 and the effectiveness as a component of a system is difficult. Differing opinion exists as to what really contributes to C2 and how to measure C2 performance. There is a significant need as new C2 concepts and systems are being developed for a systems approach to define and measure C2. It is helpful to define C2 in the context of a system and develop an approach to Metrics identification for evaluating C2 performance and effectiveness. The metrics must be dynamic to account for the different goals of C2 systems. This paper provides a recommended approach to help solve this problem by viewing C2 as a component of a system. Metrics need to help identify effectiveness and performance measures to help indicate C2 performance. Metrics can be used to help identify system requirements and testing and evaluation for the effectiveness of the C2 approach.

Lectures from the National Programme on Technology Enhanced Learning - Electrical Engineering - Advanced Control Systems

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Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 1992: Volume 206 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_1993_207_i4 . Next issue: sim_proceedings-institution-mechanical-engineers-i_1994_208_i1 .

At a time when many companies are under pressure to reduce "times-to-market" the management of product information from the early stages of design through assembly to manufacture and production has become increasingly important. Similarly in the construction of high energy physics devices the collection of (often evolving) engineering data is central to the subsequent physics analysis. Traditionally in industry design engineers have employed Engineering Data Management Systems (also called Product Data Management Systems) to coordinate and control access to documented versions of product designs. However, these systems provide control only at the collaborative design level and are seldom used beyond design. Workflow management systems, on the other hand, are employed in industry to coordinate and support the more complex and repeatable work processes of the production environment. Commercial workflow products cannot support the highly dynamic activities found both in the design stages of product development and in rapidly evolving workflow definitions. The integration of Product Data Management with Workflow Management can provide support for product development from initial CAD/CAM collaborative design through to the support and optimisation of production workflow activities. This paper investigates this integration and proposes a philosophy for the support of product data throughout the full development and production lifecycle and demonstrates its usefulness in the construction of CMS detectors.

At a time when many companies are under pressure to reduce "times-to-market" the management of product information from the early stages of design through assembly to manufacture and production has become increasingly important. Similarly in the construction of high energy physics devices the collection of (often evolving) engineering data is central to the subsequent physics analysis. Traditionally in industry design engineers have employed Engineering Data Management Systems (also called Product Data Management Systems) to coordinate and control access to documented versions of product designs. However, these systems provide control only at the collaborative design level and are seldom used beyond design. Workflow management systems, on the other hand, are employed in industry to coordinate and support the more complex and repeatable work processes of the production environment. Commercial workflow products cannot support the highly dynamic activities found both in the design stages of product development and in rapidly evolving workflow definitions. The integration of Product Data Management with Workflow Management can provide support for product development from initial CAD/CAM collaborative design through to the support and optimisation of production workflow activities. This paper investigates this integration and proposes a philosophy for the support of product data throughout the full development and production lifecycle and demonstrates its usefulness in the construction of CMS detectors.

Software sustainment costs continue to rise as the Army increases use of complex software-intensive systems to support military operations and associated business functions. Various studies have identified potential processes and procedures to help control software costs; however, no study has been undertaken to determine whether organizational changes to the Army Materiel Commands (AMC) software support centers can improve performance and reduce costs.

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No abstract available

In this research, an engineered process with a new approach to change control is presented and implemented on a complex space product. This approach involves using design constraint levels in a combination of two design structure matrix (DSM) structures and a systematic process for controlling changes. The system process includes the use of the system change evaluation code, how to create the transfer model, and the management evaluation of the requested change. While using similar existing methods in the literature, this paper provides a systematic approach to apply the knowledge of the designers of a space project to guide change control of large engineering projects, including managerial change control decisions and how to identify the best path for the change control process. Finally, a space orbiter has been selected for a brief implementation of a case study. The comparative results show the benefit of the proposed approach.

In this research, an engineered process with a new approach to change control is presented and implemented on a complex space product. This approach involves using design constraint levels in a combination of two design structure matrix (DSM) structures and a systematic process for controlling changes. The system process includes the use of the system change evaluation code, how to create the transfer model, and the management evaluation of the requested change. While using similar existing methods in the literature, this paper provides a systematic approach to apply the knowledge of the designers of a space project to guide change control of large engineering projects, including managerial change control decisions and how to identify the best path for the change control process. Finally, a space orbiter has been selected for a brief implementation of a case study. The comparative results show the benefit of the proposed approach.

In this research, an engineered process with a new approach to change control is presented and implemented on a complex space product. This approach involves using design constraint levels in a combination of two design structure matrix (DSM) structures and a systematic process for controlling changes. The system process includes the use of the system change evaluation code, how to create the transfer model, and the management evaluation of the requested change. While using similar existing methods in the literature, this paper provides a systematic approach to apply the knowledge of the designers of a space project to guide change control of large engineering projects, including managerial change control decisions and how to identify the best path for the change control process. Finally, a space orbiter has been selected for a brief implementation of a case study. The comparative results show the benefit of the proposed approach.

In this research, an engineered process with a new approach to change control is presented and implemented on a complex space product. This approach involves using design constraint levels in a combination of two design structure matrix (DSM) structures and a systematic process for controlling changes. The system process includes the use of the system change evaluation code, how to create the transfer model, and the management evaluation of the requested change. While using similar existing methods in the literature, this paper provides a systematic approach to apply the knowledge of the designers of a space project to guide change control of large engineering projects, including managerial change control decisions and how to identify the best path for the change control process. Finally, a space orbiter has been selected for a brief implementation of a case study. The comparative results show the benefit of the proposed approach.

In this research, an engineered process with a new approach to change control is presented and implemented on a complex space product. This approach involves using design constraint levels in a combination of two design structure matrix (DSM) structures and a systematic process for controlling changes. The system process includes the use of the system change evaluation code, how to create the transfer model, and the management evaluation of the requested change. While using similar existing methods in the literature, this paper provides a systematic approach to apply the knowledge of the designers of a space project to guide change control of large engineering projects, including managerial change control decisions and how to identify the best path for the change control process. Finally, a space orbiter has been selected for a brief implementation of a case study. The comparative results show the benefit of the proposed approach.

In this research, an engineered process with a new approach to change control is presented and implemented on a complex space product. This approach involves using design constraint levels in a combination of two design structure matrix (DSM) structures and a systematic process for controlling changes. The system process includes the use of the system change evaluation code, how to create the transfer model, and the management evaluation of the requested change. While using similar existing methods in the literature, this paper provides a systematic approach to apply the knowledge of the designers of a space project to guide change control of large engineering projects, including managerial change control decisions and how to identify the best path for the change control process. Finally, a space orbiter has been selected for a brief implementation of a case study. The comparative results show the benefit of the proposed approach.

From the bitsavers.org collection, a scanned-in computer-related document. autonetics :: fadac :: AMCP 706 329 Engineering Design Handbook Fire Control Series Section 3 Fire Control Computing Systems 197010

From the bitsavers.org collection, a scanned-in computer-related document. autonetics :: fadac :: AMCP 706 329 Engineering Design Handbook Fire Control Series Section 3 Fire Control Computing Systems 197010

Despite the growing popularity of unmanned systems being deployed in the military domain, limited research efforts have been dedicated to the progress of ground system developments. Dedicated efforts for unmanned ground vehicles (UGV) focused largely on operations in continental environments, places where vegetation is relatively sparse compared to a tropical jungle or plantation estate commonly found in Asia. This research explore methods for the development of an UGV that would be capable of operating autonomously in a densely cluttered environment such as that found in Asia. This thesis adopted a systems engineering approach to understand the pertinent parameters affecting the performance of the UGV in order to evaluate, design and develop the necessary guidance, navigation and control algorithms for the UGV. The thesis uses methodologies such as the pure pursuit method for path following and the vector field histogram method for obstacle avoidance as the main guidance and control algorithm governing the movement of the UGV. The thesis then considers the use of feature recognition method of image processing to form the basis of the target identification and tracking algorithm.

Despite the growing popularity of unmanned systems being deployed in the military domain, limited research efforts have been dedicated to the progress of ground system developments. Dedicated efforts for unmanned ground vehicles (UGV) focused largely on operations in continental environments, places where vegetation is relatively sparse compared to a tropical jungle or plantation estate commonly found in Asia. This research explore methods for the development of an UGV that would be capable of operating autonomously in a densely cluttered environment such as that found in Asia. This thesis adopted a systems engineering approach to understand the pertinent parameters affecting the performance of the UGV in order to evaluate, design and develop the necessary guidance, navigation and control algorithms for the UGV. The thesis uses methodologies such as the pure pursuit method for path following and the vector field histogram method for obstacle avoidance as the main guidance and control algorithm governing the movement of the UGV. The thesis then considers the use of feature recognition method of image processing to form the basis of the target identification and tracking algorithm.

Despite the growing popularity of unmanned systems being deployed in the military domain, limited research efforts have been dedicated to the progress of ground system developments. Dedicated efforts for unmanned ground vehicles (UGV) focused largely on operations in continental environments, places where vegetation is relatively sparse compared to a tropical jungle or plantation estate commonly found in Asia. This research explore methods for the development of an UGV that would be capable of operating autonomously in a densely cluttered environment such as that found in Asia. This thesis adopted a systems engineering approach to understand the pertinent parameters affecting the performance of the UGV in order to evaluate, design and develop the necessary guidance, navigation and control algorithms for the UGV. The thesis uses methodologies such as the pure pursuit method for path following and the vector field histogram method for obstacle avoidance as the main guidance and control algorithm governing the movement of the UGV. The thesis then considers the use of feature recognition method of image processing to form the basis of the target identification and tracking algorithm.

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 1994: Volume 208 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_1995_209_i4 . Next issue: sim_proceedings-institution-mechanical-engineers-i_1996_210_index .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 1994: Volume 208 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_1995_209_i4 . Next issue: sim_proceedings-institution-mechanical-engineers-i_1996_210_index .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 1994: Volume 208 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_1995_209_i4 . Next issue: sim_proceedings-institution-mechanical-engineers-i_1996_210_index .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 1994: Volume 208 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_1995_209_i4 . Next issue: sim_proceedings-institution-mechanical-engineers-i_1996_210_index .

ADA003543

The Space Launch System (SLS) Core Stage (CS) Thrust Vector Control (TVC)\nsystem is comprised of 8 mechanical feedback Shuttle heritage Type III TVC\nactuators and four RS-25 engines, each attached to a Shuttle heritage gimbal\nblock/bearing. Two actuators are used to move each engine in two planes perpendicular\nto one another (i.e., pitch and yaw). The TVC system design leverages\nhardware from the Space Shuttle program as well as new hardware designed\nspecifically for the Core Stage.\nThe Space Shuttle heritage hardware directly reused on SLS includes the Orbiter\nTVC hydraulic servo-actuators (with two slight design modifications), the\nOrbiter hydraulic circulation pumps, the Orbiter gimbal block/bearing, and the\nSolid Rocket Booster hydraulic pumps. The Core Auxiliary Power Unit (CAPU)\nis derived from the Orbiter Auxiliary Power Unit (APU). The Orbiter and Solid\nRocket Booster APU turbines are powered by hot gas produced by catalyzed hydrazine\ndecomposition. On the SLS Core Stage, the CAPU turbine is spun using\ncold gas tapped-off from the RS-25 to CS liquid hydrogen autogenous pressurization\nline.\nWhile direct reuse or slight modification of existing hardware may seem to be\na triple-win for a program in cost, schedule, and technical risk mitigation, those\nbenefits can only be realized when its degree of application in a new system is carefully\nand thoughtfully managed. The heritage hardware reuse should be prescribed\nwithin the heritage design capability and reuse environments must lie within the\nenvelope of heritage qualification testing. Despite the significant test and flight experience\nof the Shuttle heritage hardware components, successful integration with\nthe newly designed CS TVC components and incorporation into the stage design\nproved to be a challenge which required re-qualification of the heritage hardware\nas well as thorough integrated testing to support flight certification.\nExamples of the challenges that were overcome include: re-qualifying heritage\nhardware to survive new shock and vibration environments, certifying performance\nof extensively modified heritage hardware, regenerating design insight\ndue to lack of available heritage vendor data, showing compliance to modern structural\ndesign standards, translation of heritage requirements for analog avionics to\nmodern digital avionics, and interfacing heritage mechanical hardware with newly\ndesigned avionics. This paper is the second installment in a seven-paper series\nsurveying the design, engineering, test validation, and flight performance of the\nCore Stage Thrust Vector Control system. This paper will discuss several engineering\nchallenges encountered during the development process for SLS CS TVC\nand how they were successfully overcome to reach flight readiness.

The Space Launch System (SLS) Core Stage (CS) Thrust Vector Control (TVC)\nsystem is comprised of 8 mechanical feedback Shuttle heritage Type III TVC\nactuators and four RS-25 engines, each attached to a Shuttle heritage gimbal\nblock/bearing. Two actuators are used to move each engine in two planes perpendicular\nto one another (i.e., pitch and yaw). The TVC system design leverages\nhardware from the Space Shuttle program as well as new hardware designed\nspecifically for the Core Stage.\nThe Space Shuttle heritage hardware directly reused on SLS includes the Orbiter\nTVC hydraulic servo-actuators (with two slight design modifications), the\nOrbiter hydraulic circulation pumps, the Orbiter gimbal block/bearing, and the\nSolid Rocket Booster hydraulic pumps. The Core Auxiliary Power Unit (CAPU)\nis derived from the Orbiter Auxiliary Power Unit (APU). The Orbiter and Solid\nRocket Booster APU turbines are powered by hot gas produced by catalyzed hydrazine\ndecomposition. On the SLS Core Stage, the CAPU turbine is spun using\ncold gas tapped-off from the RS-25 to CS liquid hydrogen autogenous pressurization\nline.\nWhile direct reuse or slight modification of existing hardware may seem to be\na triple-win for a program in cost, schedule, and technical risk mitigation, those\nbenefits can only be realized when its degree of application in a new system is carefully\nand thoughtfully managed. The heritage hardware reuse should be prescribed\nwithin the heritage design capability and reuse environments must lie within the\nenvelope of heritage qualification testing. Despite the significant test and flight experience\nof the Shuttle heritage hardware components, successful integration with\nthe newly designed CS TVC components and incorporation into the stage design\nproved to be a challenge which required re-qualification of the heritage hardware\nas well as thorough integrated testing to support flight certification.\nExamples of the challenges that were overcome include: re-qualifying heritage\nhardware to survive new shock and vibration environments, certifying performance\nof extensively modified heritage hardware, regenerating design insight\ndue to lack of available heritage vendor data, showing compliance to modern structural\ndesign standards, translation of heritage requirements for analog avionics to\nmodern digital avionics, and interfacing heritage mechanical hardware with newly\ndesigned avionics. This paper is the second installment in a seven-paper series\nsurveying the design, engineering, test validation, and flight performance of the\nCore Stage Thrust Vector Control system. This paper will discuss several engineering\nchallenges encountered during the development process for SLS CS TVC\nand how they were successfully overcome to reach flight readiness.

The Space Launch System (SLS) Core Stage (CS) Thrust Vector Control (TVC)\nsystem is comprised of 8 mechanical feedback Shuttle heritage Type III TVC\nactuators and four RS-25 engines, each attached to a Shuttle heritage gimbal\nblock/bearing. Two actuators are used to move each engine in two planes perpendicular\nto one another (i.e., pitch and yaw). The TVC system design leverages\nhardware from the Space Shuttle program as well as new hardware designed\nspecifically for the Core Stage.\nThe Space Shuttle heritage hardware directly reused on SLS includes the Orbiter\nTVC hydraulic servo-actuators (with two slight design modifications), the\nOrbiter hydraulic circulation pumps, the Orbiter gimbal block/bearing, and the\nSolid Rocket Booster hydraulic pumps. The Core Auxiliary Power Unit (CAPU)\nis derived from the Orbiter Auxiliary Power Unit (APU). The Orbiter and Solid\nRocket Booster APU turbines are powered by hot gas produced by catalyzed hydrazine\ndecomposition. On the SLS Core Stage, the CAPU turbine is spun using\ncold gas tapped-off from the RS-25 to CS liquid hydrogen autogenous pressurization\nline.\nWhile direct reuse or slight modification of existing hardware may seem to be\na triple-win for a program in cost, schedule, and technical risk mitigation, those\nbenefits can only be realized when its degree of application in a new system is carefully\nand thoughtfully managed. The heritage hardware reuse should be prescribed\nwithin the heritage design capability and reuse environments must lie within the\nenvelope of heritage qualification testing. Despite the significant test and flight experience\nof the Shuttle heritage hardware components, successful integration with\nthe newly designed CS TVC components and incorporation into the stage design\nproved to be a challenge which required re-qualification of the heritage hardware\nas well as thorough integrated testing to support flight certification.\nExamples of the challenges that were overcome include: re-qualifying heritage\nhardware to survive new shock and vibration environments, certifying performance\nof extensively modified heritage hardware, regenerating design insight\ndue to lack of available heritage vendor data, showing compliance to modern structural\ndesign standards, translation of heritage requirements for analog avionics to\nmodern digital avionics, and interfacing heritage mechanical hardware with newly\ndesigned avionics. This paper is the second installment in a seven-paper series\nsurveying the design, engineering, test validation, and flight performance of the\nCore Stage Thrust Vector Control system. This paper will discuss several engineering\nchallenges encountered during the development process for SLS CS TVC\nand how they were successfully overcome to reach flight readiness.

Essential book to know how the data drive the decisions

Essential book to know how the data drive the decisions

Despite the growing popularity of unmanned systems being deployed in the military domain, limited research efforts have been dedicated to the progress of ground system developments. Dedicated efforts for unmanned ground vehicles (UGV) focused largely on operations in continental environments, places where vegetation is relatively sparse compared to a tropical jungle or plantation estate commonly found in Asia. This research explore methods for the development of an UGV that would be capable of operating autonomously in a densely cluttered environment such as that found in Asia. This thesis adopted a systems engineering approach to understand the pertinent parameters affecting the performance of the UGV in order to evaluate, design and develop the necessary guidance, navigation and control algorithms for the UGV. The thesis uses methodologies such as the pure pursuit method for path following and the vector field histogram method for obstacle avoidance as the main guidance and control algorithm governing the movement of the UGV. The thesis then considers the use of feature recognition method of image processing to form the basis of the target identification and tracking algorithm.

Despite the growing popularity of unmanned systems being deployed in the military domain, limited research efforts have been dedicated to the progress of ground system developments. Dedicated efforts for unmanned ground vehicles (UGV) focused largely on operations in continental environments, places where vegetation is relatively sparse compared to a tropical jungle or plantation estate commonly found in Asia. This research explore methods for the development of an UGV that would be capable of operating autonomously in a densely cluttered environment such as that found in Asia. This thesis adopted a systems engineering approach to understand the pertinent parameters affecting the performance of the UGV in order to evaluate, design and develop the necessary guidance, navigation and control algorithms for the UGV. The thesis uses methodologies such as the pure pursuit method for path following and the vector field histogram method for obstacle avoidance as the main guidance and control algorithm governing the movement of the UGV. The thesis then considers the use of feature recognition method of image processing to form the basis of the target identification and tracking algorithm.

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 1998: Volume 212 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_1997_211_i6 . Next issue: sim_proceedings-institution-mechanical-engineers-i_1998_212_i1 .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 2005: Volume 219 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_september-2004_218_i6 . Next issue: sim_proceedings-institution-mechanical-engineers-i_february-2005_219_i1 .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 2005: Volume 219 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_september-2004_218_i6 . Next issue: sim_proceedings-institution-mechanical-engineers-i_february-2005_219_i1 .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 2005: Volume 219 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_september-2004_218_i6 . Next issue: sim_proceedings-institution-mechanical-engineers-i_february-2005_219_i1 .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 2005: Volume 219 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_september-2004_218_i6 . Next issue: sim_proceedings-institution-mechanical-engineers-i_february-2005_219_i1 .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 2005: Volume 219 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_september-2004_218_i6 . Next issue: sim_proceedings-institution-mechanical-engineers-i_february-2005_219_i1 .

Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 2005: Volume 219 , Issue Index. Digitized from IA1631332-05 . Previous issue: sim_proceedings-institution-mechanical-engineers-i_september-2004_218_i6 . Next issue: sim_proceedings-institution-mechanical-engineers-i_february-2005_219_i1 .

Control system, OmAm. 

Control system, OmAm. 

Control system, OmAm. 

The Apollo Program experience from early 1962 to July 1969 with respect to the engineering-simulation support and the problems encountered is summarized in this report. Engineering simulation in support of the Apollo guidance and control system is discussed in terms of design analysis and verification, certification of hardware in closed-loop operation, verification of hardware/software compatibility, and verification of both software and procedures for each mission. The magnitude, time, and cost of the engineering simulations are described with respect to hardware availability, NASA and contractor facilities (for verification of the command module, the lunar module, and the primary guidance, navigation, and control system), and scheduling and planning considerations. Recommendations are made regarding implementation of similar, large-scale simulations for future programs.

Includes bibliographies

Includes bibliographies

Includes bibliographies

Includes bibliographies