Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332970
M. Ritchie
Cockpit displays have been described by name and by pictures or diagrams in which each indicator element is named. The names of the elements themselves are frequently not precisely defined. Within a single display and among the several displays on a panel it has been difficult to identify redundancy and equivalence of information. This paper presents a system of definitions and notation of display information elements. The system is based on a synthesis of (1) engineering definitions related to equations of motion and (2) human performance data which relate equivalence and sufficiency of displayed parameters.<>
{"title":"The information content of cockpit displays","authors":"M. Ritchie","doi":"10.1109/NAECON.1994.332970","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332970","url":null,"abstract":"Cockpit displays have been described by name and by pictures or diagrams in which each indicator element is named. The names of the elements themselves are frequently not precisely defined. Within a single display and among the several displays on a panel it has been difficult to identify redundancy and equivalence of information. This paper presents a system of definitions and notation of display information elements. The system is based on a synthesis of (1) engineering definitions related to equations of motion and (2) human performance data which relate equivalence and sufficiency of displayed parameters.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"3 12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124738881","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332939
R. Paschall, J. Layne
This paper presents the design and analysis of integrating global positioning system (GPS), inertial navigation system (INS), and synthetic aperture radar (SAR). The intent of this research is to predict the performance of the proposed targeting system. The analysis presented here is based on a well-tuned, full-order extended Kalman filter. The targeting aspects of the integrated INS, GPS, and SAR are investigated for both "relative" and "absolute" targeting. The simulation results indicate a theoretical possibility of obtaining absolute target position with a CEP of 10 ft.<>
{"title":"Design and analysis of an integrated targeting system","authors":"R. Paschall, J. Layne","doi":"10.1109/NAECON.1994.332939","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332939","url":null,"abstract":"This paper presents the design and analysis of integrating global positioning system (GPS), inertial navigation system (INS), and synthetic aperture radar (SAR). The intent of this research is to predict the performance of the proposed targeting system. The analysis presented here is based on a well-tuned, full-order extended Kalman filter. The targeting aspects of the integrated INS, GPS, and SAR are investigated for both \"relative\" and \"absolute\" targeting. The simulation results indicate a theoretical possibility of obtaining absolute target position with a CEP of 10 ft.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125094768","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332858
K. R. Babu, I. Sarma, K. Swamy
Two new guidance laws for short range homing missiles are developed by invoking the sliding mode control (SMC) theory. Guidance law 1 as structured around the basic proportional navigation (PN), with an additive switching term, which is a function of the line of sight (LOS) rate alone. An adaptive procedure is suggested to select the gain of the switching term, in order to reduce chattering. This guidance law is nearly as simple to implement as the PN itself and does not require any explicit target maneuver estimation. Guidance law 2, based on a first order sliding surface, is designed such that it results in a continuous acceleration law, thereby reducing the chattering problem. While explicitly taking into account the effect of aerodynamic drag, it requires the second derivatives of LOS angle and range, which are not directly measured. An estimation scheme, again based on sliding mode theory, is presented to estimate these quantities. Simulation results clearly demonstrate the superior performance of these schemes.<>
{"title":"Two robust homing missile guidance laws based on sliding mode control theory","authors":"K. R. Babu, I. Sarma, K. Swamy","doi":"10.1109/NAECON.1994.332858","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332858","url":null,"abstract":"Two new guidance laws for short range homing missiles are developed by invoking the sliding mode control (SMC) theory. Guidance law 1 as structured around the basic proportional navigation (PN), with an additive switching term, which is a function of the line of sight (LOS) rate alone. An adaptive procedure is suggested to select the gain of the switching term, in order to reduce chattering. This guidance law is nearly as simple to implement as the PN itself and does not require any explicit target maneuver estimation. Guidance law 2, based on a first order sliding surface, is designed such that it results in a continuous acceleration law, thereby reducing the chattering problem. While explicitly taking into account the effect of aerodynamic drag, it requires the second derivatives of LOS angle and range, which are not directly measured. An estimation scheme, again based on sliding mode theory, is presented to estimate these quantities. Simulation results clearly demonstrate the superior performance of these schemes.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130240671","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332903
Amanda D. Roe
This paper discusses the cost ground rules, assumptions, and methodology of the Joint Direct Attack Munition (JDAM) Cost Operational Effectiveness Analysis (COEA) for a Demonstration and Validation (Dem/Val) decision, Milestone 1. This was the first COEA performed for JDAM with the Milestone 0 having occurred on 8 June 1992. JDAM is a Joint Air Force/Navy Program (under Air Force Leadership) to develop and procure precision munitions capable of autonomous guidance from on or off-axis deliveries against fixed or relocatable targets under adverse environmental conditions. JDAM is an Acquisition Category (ACAT) I program. The delivery aircraft used in the COEA were the B-1B, B-2, F-15E, F-16, F-18 and the A-6. The munition alternatives analyzed were the unguided general purpose MK-82 (500 lb warhead), MK-83 (1000 lb warhead), MK-84 (2000 lb warhead) and BLU-109 (improved 2000 lb warhead), the Guided Bomb Unit (GBU)-24 (with a 2000 lb warhead) and the Air-to-Ground Missiles (AGM)-65 and 130 precision-guided bomb (with a 2000 lb warhead). The Measures of Effectiveness (MOE) were based on the "kill" of an array of targets suitable for the MK series of munitions and the aircraft attrition probability. This paper examines how the cost analysis was accomplished and merged with the measures of effectiveness, what cost data was obtained, and how this data was normalized and used in the results. Limitations, issues and risk areas were addressed and the sensitivities of cost and effectiveness were analyzed.<>
{"title":"Cost methodology for the Joint Direct Attack Munition COEA","authors":"Amanda D. Roe","doi":"10.1109/NAECON.1994.332903","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332903","url":null,"abstract":"This paper discusses the cost ground rules, assumptions, and methodology of the Joint Direct Attack Munition (JDAM) Cost Operational Effectiveness Analysis (COEA) for a Demonstration and Validation (Dem/Val) decision, Milestone 1. This was the first COEA performed for JDAM with the Milestone 0 having occurred on 8 June 1992. JDAM is a Joint Air Force/Navy Program (under Air Force Leadership) to develop and procure precision munitions capable of autonomous guidance from on or off-axis deliveries against fixed or relocatable targets under adverse environmental conditions. JDAM is an Acquisition Category (ACAT) I program. The delivery aircraft used in the COEA were the B-1B, B-2, F-15E, F-16, F-18 and the A-6. The munition alternatives analyzed were the unguided general purpose MK-82 (500 lb warhead), MK-83 (1000 lb warhead), MK-84 (2000 lb warhead) and BLU-109 (improved 2000 lb warhead), the Guided Bomb Unit (GBU)-24 (with a 2000 lb warhead) and the Air-to-Ground Missiles (AGM)-65 and 130 precision-guided bomb (with a 2000 lb warhead). The Measures of Effectiveness (MOE) were based on the \"kill\" of an array of targets suitable for the MK series of munitions and the aircraft attrition probability. This paper examines how the cost analysis was accomplished and merged with the measures of effectiveness, what cost data was obtained, and how this data was normalized and used in the results. Limitations, issues and risk areas were addressed and the sensitivities of cost and effectiveness were analyzed.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"157 2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128782251","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332987
Victor, Bright, E. Kolesar, Neal, T., Hauschild
The sensitivity, selectivity, and reversibility of a CHEMFET gas microsensor were investigated as a function of several physical operating parameters. The CHEMFET's responses were expressed based upon the changes generated by modulating the electrical conductivity of the microsensor's thin-film, metal-doped, phthalocyanine-coated interdigitated gate electrode when exposed to a family of challenge gases. Copper phthalocyanine (CuPc) and lead phthalocyanine (PbPc) were used as the chemically-sensitive thin-films which ranged in thicknesses from 250 /spl Aring/ to 1100 /spl Aring/. The challenge gases included: nitrogen dioxide (NO/sub 2/), dimethyl methylphosphonate (C/sub 3/H/sub 9/PO/sub 3/), boron trifluoride (BF/sub 3/), methanol (CH/sub 3/OH), carbon monoxide (CO), vinyl chloride (CH/sub 2/CHCl), and trichloroethylene (C/sub 2/HCl/sub 3/). The concentrations of the gases ranged from 10 parts-per-billion (ppb) to 50 parts-per-million (ppm). Tests performed at at 22/spl deg/C and 110/spl deg/C (70/spl deg/C for the latter four gases) revealed that CuPc was more sensitive to C/sub 3/H/sub 9/PO/sub 3/ and BF/sub 3/, whereas PbPc was more sensitive to NO/sub 2/, CH/sub 3/OH, CO, CH/sub 2/CHCl, and C/sub 2/HCl/sub 3/. The CHEMFET was also moderately selective when challenged with several binary challenge gas mixtures. The metal-doped phthalocyanine thin films were most selective to NO/sub 2/, followed by C/sub 3/H/sub 9/PO/sub 3/. The CHEMFET was not as selective for BF/sub 3/ when combined with several other challenge gases. The CHEMFET was totally reversible for both thin-film candidates and all challenge gases.<>
{"title":"Investigation of the sensitivity, selectivity, and reversibility of the chemically-sensitive field-effect transistor (CHEMFET) to detect NO/sub 2/, C/sub 3/H/sub 9/PO/sub 3/, and BF/sub 3/","authors":"Victor, Bright, E. Kolesar, Neal, T., Hauschild","doi":"10.1109/NAECON.1994.332987","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332987","url":null,"abstract":"The sensitivity, selectivity, and reversibility of a CHEMFET gas microsensor were investigated as a function of several physical operating parameters. The CHEMFET's responses were expressed based upon the changes generated by modulating the electrical conductivity of the microsensor's thin-film, metal-doped, phthalocyanine-coated interdigitated gate electrode when exposed to a family of challenge gases. Copper phthalocyanine (CuPc) and lead phthalocyanine (PbPc) were used as the chemically-sensitive thin-films which ranged in thicknesses from 250 /spl Aring/ to 1100 /spl Aring/. The challenge gases included: nitrogen dioxide (NO/sub 2/), dimethyl methylphosphonate (C/sub 3/H/sub 9/PO/sub 3/), boron trifluoride (BF/sub 3/), methanol (CH/sub 3/OH), carbon monoxide (CO), vinyl chloride (CH/sub 2/CHCl), and trichloroethylene (C/sub 2/HCl/sub 3/). The concentrations of the gases ranged from 10 parts-per-billion (ppb) to 50 parts-per-million (ppm). Tests performed at at 22/spl deg/C and 110/spl deg/C (70/spl deg/C for the latter four gases) revealed that CuPc was more sensitive to C/sub 3/H/sub 9/PO/sub 3/ and BF/sub 3/, whereas PbPc was more sensitive to NO/sub 2/, CH/sub 3/OH, CO, CH/sub 2/CHCl, and C/sub 2/HCl/sub 3/. The CHEMFET was also moderately selective when challenged with several binary challenge gas mixtures. The metal-doped phthalocyanine thin films were most selective to NO/sub 2/, followed by C/sub 3/H/sub 9/PO/sub 3/. The CHEMFET was not as selective for BF/sub 3/ when combined with several other challenge gases. The CHEMFET was totally reversible for both thin-film candidates and all challenge gases.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129293350","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332857
N. Wu, Tijian Chen
This paper is concerned with the design of reconfigurable flight control systems furnished with aerodynamic redundancy. Our focus is directed towards dealing with the aircraft surface impairment such as locked, float, or missing surfaces. We propose a control design criterion that facilitates the detection of failures without compromising the required performance robustness. Details are carried out for the design of the pitch axis controller of an experimental highly maneuverable aircraft, where redundancy in the control authority is provided by both the elevens and the canards. The goal is to explain our design procedure and to demonstrate enhanced overall system fault tolerance. The design effort is focused on the selection of controllers that can differentiate their effects on failures that require a control reconfiguration from the effects on other uncertainties that do not require a control reconfiguration. The key idea for achieving such differentiation is to examine the FDI (failure detection and isolation) performance index of controllers from a parameterized set that attains a certain control performance index. The scenario with a loss of surface effectiveness is simulated for the aircraft model. The deviation in the control law designed variance of the residual signal is shown to be most neglected in the processe of failures.<>
{"title":"Failure sensitivity and robustness in reconfigurable flight control systems","authors":"N. Wu, Tijian Chen","doi":"10.1109/NAECON.1994.332857","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332857","url":null,"abstract":"This paper is concerned with the design of reconfigurable flight control systems furnished with aerodynamic redundancy. Our focus is directed towards dealing with the aircraft surface impairment such as locked, float, or missing surfaces. We propose a control design criterion that facilitates the detection of failures without compromising the required performance robustness. Details are carried out for the design of the pitch axis controller of an experimental highly maneuverable aircraft, where redundancy in the control authority is provided by both the elevens and the canards. The goal is to explain our design procedure and to demonstrate enhanced overall system fault tolerance. The design effort is focused on the selection of controllers that can differentiate their effects on failures that require a control reconfiguration from the effects on other uncertainties that do not require a control reconfiguration. The key idea for achieving such differentiation is to examine the FDI (failure detection and isolation) performance index of controllers from a parameterized set that attains a certain control performance index. The scenario with a loss of surface effectiveness is simulated for the aircraft model. The deviation in the control law designed variance of the residual signal is shown to be most neglected in the processe of failures.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127692826","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332904
J. Sackett
One of the most difficult problems in a Cost and Operational Effectiveness Analysis (COEA) is the combination of the cost and effectiveness data and the corresponding presentation of this information to the decision maker in an integrated manner that allows him/her to select the best alternative from the competing weapons systems. The combination of cost and effectiveness is necessary because the wartime field commander wants to maximize weapon system effectiveness regardless of fiscal costs, while the peacetime financial manager wants to minimize costs while providing acceptable weapon system effectiveness. The difficulty of combining cost and effectiveness arises because the operational effectiveness analysis usually presents the performance of each alternative with respect to several measures of effectiveness (MOE). When examining this data, it is unusual to have a clear winner among the competing alternatives. And when the cost data is considered with the effectiveness data, the problem of selecting the "best" alternative is further complicated. However, unless the COEA is able to integrate the cost and effectiveness data into a coherent product, the analysis has not helped the decision maker solve his/her problem-selecting the preferred alternative. There are several potential methods that can be used to integrate the cost and effectiveness data for presentation to decision makers. This paper briefly discusses each method, provides an example of each method, and identifies its associated advantages and disadvantages.<>
{"title":"Cost and effectiveness integration","authors":"J. Sackett","doi":"10.1109/NAECON.1994.332904","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332904","url":null,"abstract":"One of the most difficult problems in a Cost and Operational Effectiveness Analysis (COEA) is the combination of the cost and effectiveness data and the corresponding presentation of this information to the decision maker in an integrated manner that allows him/her to select the best alternative from the competing weapons systems. The combination of cost and effectiveness is necessary because the wartime field commander wants to maximize weapon system effectiveness regardless of fiscal costs, while the peacetime financial manager wants to minimize costs while providing acceptable weapon system effectiveness. The difficulty of combining cost and effectiveness arises because the operational effectiveness analysis usually presents the performance of each alternative with respect to several measures of effectiveness (MOE). When examining this data, it is unusual to have a clear winner among the competing alternatives. And when the cost data is considered with the effectiveness data, the problem of selecting the \"best\" alternative is further complicated. However, unless the COEA is able to integrate the cost and effectiveness data into a coherent product, the analysis has not helped the decision maker solve his/her problem-selecting the preferred alternative. There are several potential methods that can be used to integrate the cost and effectiveness data for presentation to decision makers. This paper briefly discusses each method, provides an example of each method, and identifies its associated advantages and disadvantages.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129947377","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.333000
J. O'Brien, H. Fullman, H. Holt, L. Orwig
The validation of a radar system for making topographic measurements is described. The system is an interferometric SAR radar flown by Norden Systems in late 1992 and early 1993 under an ARPA-sponsored program. Both absolute and relative height measurements were made, with aircraft position referenced to an INS/GPS and a separate differential GPS. An initial accuracy prediction was obtained from a complete system error analysis. Confirmation of this prediction was a non-trivial task, which consisted of making comparisons with truth models obtained using photogrammetric surveys, using over-water measurements, and using radar data collected from orthogonal night directions. A photogrammetric survey was performed over a 5 km square area, with residual photogrammetric height errors estimated at less than 1 foot. The size of the survey area was considered large enough that radar system stability could be assessed. The inclusion of four-way corner reflectors in the surveyed scene permitted radar measurements to be tied to the photo-surveyed points so that the image scale factor could be determined. Radar system stability was also assessed by mapping the ocean surface. Both phenomenological and system limitations in accuracy are addressed.<>
{"title":"Accuracy validation of the IFSARE radar system","authors":"J. O'Brien, H. Fullman, H. Holt, L. Orwig","doi":"10.1109/NAECON.1994.333000","DOIUrl":"https://doi.org/10.1109/NAECON.1994.333000","url":null,"abstract":"The validation of a radar system for making topographic measurements is described. The system is an interferometric SAR radar flown by Norden Systems in late 1992 and early 1993 under an ARPA-sponsored program. Both absolute and relative height measurements were made, with aircraft position referenced to an INS/GPS and a separate differential GPS. An initial accuracy prediction was obtained from a complete system error analysis. Confirmation of this prediction was a non-trivial task, which consisted of making comparisons with truth models obtained using photogrammetric surveys, using over-water measurements, and using radar data collected from orthogonal night directions. A photogrammetric survey was performed over a 5 km square area, with residual photogrammetric height errors estimated at less than 1 foot. The size of the survey area was considered large enough that radar system stability could be assessed. The inclusion of four-way corner reflectors in the surveyed scene permitted radar measurements to be tied to the photo-surveyed points so that the image scale factor could be determined. Radar system stability was also assessed by mapping the ocean surface. Both phenomenological and system limitations in accuracy are addressed.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129806102","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332940
J. Newport
System developers use a variety of benchmarks to evaluate the performance of a new system, as well as mature the hardware and software. A computer system, in this context, includes the processing hardware as well as the Ada Run Time System. The integration of these elements is incremental and the system matures as software applications of different types run an the computer. Therefore, a wide spectrum of components must comprise a test suite. Many of the classic benchmarks are of the "toy" variety, which means that: they are unrealistic in several ways. This may be a lack of Input/Output (I/O), absence of interrupts during execution, small program size that does not break cache memory, or other factors. These benchmarks are important starting points, but a designer must not rely on such test to fully characterize and debug a new design. The proposed test is a more realistic program that addresses these issues. It is a "single board" version of system tests previously reported. The presentation updates its status as a proposed System Performance Evaluation Corporation candidate, and provides some candidate results.<>
{"title":"A proposed real-time ADA test","authors":"J. Newport","doi":"10.1109/NAECON.1994.332940","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332940","url":null,"abstract":"System developers use a variety of benchmarks to evaluate the performance of a new system, as well as mature the hardware and software. A computer system, in this context, includes the processing hardware as well as the Ada Run Time System. The integration of these elements is incremental and the system matures as software applications of different types run an the computer. Therefore, a wide spectrum of components must comprise a test suite. Many of the classic benchmarks are of the \"toy\" variety, which means that: they are unrealistic in several ways. This may be a lack of Input/Output (I/O), absence of interrupts during execution, small program size that does not break cache memory, or other factors. These benchmarks are important starting points, but a designer must not rely on such test to fully characterize and debug a new design. The proposed test is a more realistic program that addresses these issues. It is a \"single board\" version of system tests previously reported. The presentation updates its status as a proposed System Performance Evaluation Corporation candidate, and provides some candidate results.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"224 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121120227","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1994-05-23DOI: 10.1109/NAECON.1994.332887
R. Burton, K.I. Collier
MIL-STD-499B "Systems Engineering" defines a disciplined design and verification process for developing new systems. It's iterative and balanced approach results in systems that meet all of their intended needs and satisfy all of their intended customers. Mature systems with well defined designs, established specifications, limited requirements traceability, and existing design and manufacturing processes are faced with a dilemma when addressing modifications and upgrades. Full implementation of MIL-STD-499B cannot be cost justified, while the absence of implementation results in stagnation of the program and a weakened competitive position. McDonnell Douglas Aerospace (MDA) is implementing MIL-STD-499B across the enterprise, including mature systems such as the F-15 weapon system. MDA has developed a systems engineering manual as a guideline for the implementation of MIL-STD-499B. The F-15 program has taken the system engineering manual and tailored it to support new development activity. The F-15 program expects to improve product reliability and maintainability, develop performance upgrades, and improve the producibility of the F-15 weapon system by applying a disciplined systems engineering process to selected elements of the system. The F-15 program is expanding its system engineering approach as part of its integrated product development organization. This paper describes MDA's system engineering process, the tailored F-15 program implementation approach, progress to date and lessons learned.<>
{"title":"Implementing MIL-STD-499B Systems Engineering on a mature program","authors":"R. Burton, K.I. Collier","doi":"10.1109/NAECON.1994.332887","DOIUrl":"https://doi.org/10.1109/NAECON.1994.332887","url":null,"abstract":"MIL-STD-499B \"Systems Engineering\" defines a disciplined design and verification process for developing new systems. It's iterative and balanced approach results in systems that meet all of their intended needs and satisfy all of their intended customers. Mature systems with well defined designs, established specifications, limited requirements traceability, and existing design and manufacturing processes are faced with a dilemma when addressing modifications and upgrades. Full implementation of MIL-STD-499B cannot be cost justified, while the absence of implementation results in stagnation of the program and a weakened competitive position. McDonnell Douglas Aerospace (MDA) is implementing MIL-STD-499B across the enterprise, including mature systems such as the F-15 weapon system. MDA has developed a systems engineering manual as a guideline for the implementation of MIL-STD-499B. The F-15 program has taken the system engineering manual and tailored it to support new development activity. The F-15 program expects to improve product reliability and maintainability, develop performance upgrades, and improve the producibility of the F-15 weapon system by applying a disciplined systems engineering process to selected elements of the system. The F-15 program is expanding its system engineering approach as part of its integrated product development organization. This paper describes MDA's system engineering process, the tailored F-15 program implementation approach, progress to date and lessons learned.<<ETX>>","PeriodicalId":281754,"journal":{"name":"Proceedings of National Aerospace and Electronics Conference (NAECON'94)","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-05-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124037253","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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