Pub Date : 1994-10-30DOI: 10.1109/DASC.1994.369443
J. Aplin
This paper traces the development of active noise control (ANC) from its origins in the University Research Laboratories, to its fulfilment in revenue service with airlines. It begins by identifying the need for ANC in terms of quietening the noise from turboprop or turbojet engines, and proceeds to develop the requirements for a viable ANC system. The algorithm used for controlling noise is described, especially its ability to control many independent tones and tones that fluctuate in frequency and amplitude. The system design is described, detailing those features included in the system to make it easy to use, followed by an outline of the hardware used to implement the system. The method of installing, calibrating, and trialling the system is detailed, concluding with the results from a recent set of flight trials.<>
{"title":"Active noise control-from research to reality","authors":"J. Aplin","doi":"10.1109/DASC.1994.369443","DOIUrl":"https://doi.org/10.1109/DASC.1994.369443","url":null,"abstract":"This paper traces the development of active noise control (ANC) from its origins in the University Research Laboratories, to its fulfilment in revenue service with airlines. It begins by identifying the need for ANC in terms of quietening the noise from turboprop or turbojet engines, and proceeds to develop the requirements for a viable ANC system. The algorithm used for controlling noise is described, especially its ability to control many independent tones and tones that fluctuate in frequency and amplitude. The system design is described, detailing those features included in the system to make it easy to use, followed by an outline of the hardware used to implement the system. The method of installing, calibrating, and trialling the system is detailed, concluding with the results from a recent set of flight trials.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115367667","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 : 1994-10-30DOI: 10.1109/DASC.1994.369461
J. Thoma, S. Dick
In 1993, the US Navy's COMSEACONTROLWINGLANT (Cecil Field, FL.) agreed to support a proof of concept (POC) demonstration with Norden's AN/APG-76 multimode radar system, carried in a cargo pod aboard an S-3 Viking aircraft. Norden has modified an S-3 pod, including installation of an F-4 radome, to carry the radar. This modified pod has successfully flown in a non-operational demonstration. Norden is installing a prototype demonstration for the S-3, including the modified pod and aircraft equipment.<>
{"title":"Gray Wolf S-3B demonstration of podded Norden AN/APG-76 radar system","authors":"J. Thoma, S. Dick","doi":"10.1109/DASC.1994.369461","DOIUrl":"https://doi.org/10.1109/DASC.1994.369461","url":null,"abstract":"In 1993, the US Navy's COMSEACONTROLWINGLANT (Cecil Field, FL.) agreed to support a proof of concept (POC) demonstration with Norden's AN/APG-76 multimode radar system, carried in a cargo pod aboard an S-3 Viking aircraft. Norden has modified an S-3 pod, including installation of an F-4 radome, to carry the radar. This modified pod has successfully flown in a non-operational demonstration. Norden is installing a prototype demonstration for the S-3, including the modified pod and aircraft equipment.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128903805","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 : 1994-10-30DOI: 10.1109/DASC.1994.369487
S. Liden
In the 12 years since Flight Management Systems first became standard equipment on commercial aircraft, this category of avionic equipment has experienced exceptional growth in features and functionality. There have also been significant differences between the various "species" of systems that were developed for different aircraft and for different aircraft manufacturers. This paper explores the reasons for the differences and describes what the main differences are. It also describes the numerous evolutionary changes that have taken place in each family of systems. Finally, how this trend is expected to continue into the future is discussed.<>
{"title":"The evolution of Flight Management Systems","authors":"S. Liden","doi":"10.1109/DASC.1994.369487","DOIUrl":"https://doi.org/10.1109/DASC.1994.369487","url":null,"abstract":"In the 12 years since Flight Management Systems first became standard equipment on commercial aircraft, this category of avionic equipment has experienced exceptional growth in features and functionality. There have also been significant differences between the various \"species\" of systems that were developed for different aircraft and for different aircraft manufacturers. This paper explores the reasons for the differences and describes what the main differences are. It also describes the numerous evolutionary changes that have taken place in each family of systems. Finally, how this trend is expected to continue into the future is discussed.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"22 2","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120912829","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 : 1994-10-30DOI: 10.1109/DASC.1994.369453
M. Jenkins
The use of multiprocessors for reducing risk in a system is called redundancy management. The software should be hardware independent, reliable, and reusable. These are key words in choosing Ada to implement the code. A set of common data to all CPUs may be updated by one CPU, called a master, while the others (called slaves) read the data and act on the results. The master controls the operation of the system, and the slaves continually check the validity of the master. The complexity in this code is that all CPUs must execute the same algorithm, but react in a different way. Each CPU must determine whether it can write data as the master, read data as a slave, or transition to master if the master is dysfunctional. One way to do this is to implement a rotating count scheme.<>
{"title":"Independent multiprocessor systems: a master/slave configuration implemented in Ada","authors":"M. Jenkins","doi":"10.1109/DASC.1994.369453","DOIUrl":"https://doi.org/10.1109/DASC.1994.369453","url":null,"abstract":"The use of multiprocessors for reducing risk in a system is called redundancy management. The software should be hardware independent, reliable, and reusable. These are key words in choosing Ada to implement the code. A set of common data to all CPUs may be updated by one CPU, called a master, while the others (called slaves) read the data and act on the results. The master controls the operation of the system, and the slaves continually check the validity of the master. The complexity in this code is that all CPUs must execute the same algorithm, but react in a different way. Each CPU must determine whether it can write data as the master, read data as a slave, or transition to master if the master is dysfunctional. One way to do this is to implement a rotating count scheme.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117065034","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 : 1994-10-30DOI: 10.1109/DASC.1994.369456
M. Dzwonczyk, E. Huff
A real-time helicopter transmission health monitor is being developed and evaluated at the NASA Ames Research Center in conjunction with the U.S. Army Aeroflightdynamics Directorate. This system uses non-real-time neural computing techniques to first learn the vibration signatures of faulty gearbox modes. Real-time capability is then achieved by faithful replication of the neural network processing model in an air-worthy integrated electronics architecture. The latter is based upon seminal work done at Draper Laboratory on INCA (Integrated Neural Computing Architecture). Prior work done by a number of organizations has substantiated the utility of neural computation for this kind of application in static laboratory environments. The present effort extends that basic research into dynamic flight by use of the FLITE (Flying Laboratory for Integrated Test and Evaluation) vehicle, which is an instrumented Cobra helicopter located at Moffett Field, CA.<>
{"title":"Helicopter transmission health monitoring using real-time neural computing methods","authors":"M. Dzwonczyk, E. Huff","doi":"10.1109/DASC.1994.369456","DOIUrl":"https://doi.org/10.1109/DASC.1994.369456","url":null,"abstract":"A real-time helicopter transmission health monitor is being developed and evaluated at the NASA Ames Research Center in conjunction with the U.S. Army Aeroflightdynamics Directorate. This system uses non-real-time neural computing techniques to first learn the vibration signatures of faulty gearbox modes. Real-time capability is then achieved by faithful replication of the neural network processing model in an air-worthy integrated electronics architecture. The latter is based upon seminal work done at Draper Laboratory on INCA (Integrated Neural Computing Architecture). Prior work done by a number of organizations has substantiated the utility of neural computation for this kind of application in static laboratory environments. The present effort extends that basic research into dynamic flight by use of the FLITE (Flying Laboratory for Integrated Test and Evaluation) vehicle, which is an instrumented Cobra helicopter located at Moffett Field, CA.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"126 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116204108","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 : 1994-10-30DOI: 10.1109/DASC.1994.369447
Xinggan Zhang, Zhaoda Zhu
In this paper, we describe a pulse compressor implementation with DSP for small time-bandwidth (TB) product linear frequency modulation (LFM) waveform. It contains the digital generation of the LFM waveform and the digital internally Hamming weighted compression filter. Two methods for suppression of time sidelobe of the digital pulse compressor are employed. First, the LFM waveform is modified using cubic phase predistortion for reducting the effect of Fresnel ripples in small TB product LFM waveform. Secondly, anti-aliasing filter is used before A/D converter for reducting spectrum skirt level of the returned LFM waveform. The parameters of the compression filter implemented with IMSA100 DSP are programmable. The experiments show that the peak time sidelobe level of the digital pulse compressor is not larger than -32 dB for TB product of 20.<>
{"title":"A pulse compression processor implementation with DSP for airborne pulse Doppler radar","authors":"Xinggan Zhang, Zhaoda Zhu","doi":"10.1109/DASC.1994.369447","DOIUrl":"https://doi.org/10.1109/DASC.1994.369447","url":null,"abstract":"In this paper, we describe a pulse compressor implementation with DSP for small time-bandwidth (TB) product linear frequency modulation (LFM) waveform. It contains the digital generation of the LFM waveform and the digital internally Hamming weighted compression filter. Two methods for suppression of time sidelobe of the digital pulse compressor are employed. First, the LFM waveform is modified using cubic phase predistortion for reducting the effect of Fresnel ripples in small TB product LFM waveform. Secondly, anti-aliasing filter is used before A/D converter for reducting spectrum skirt level of the returned LFM waveform. The parameters of the compression filter implemented with IMSA100 DSP are programmable. The experiments show that the peak time sidelobe level of the digital pulse compressor is not larger than -32 dB for TB product of 20.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"127 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122741885","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 : 1994-10-30DOI: 10.1109/DASC.1994.369419
R. J. LeFevre, J. C. Kirk, R. Durand
This paper describes a 94 GHz active radar system designed to generate an accurate, three dimensional representation of the terrain and obstacles in the flight path of a helicopter. The data is to be used to provide signals to the guidance and control systems for automatic Nap-of-the-Earth (ANOE) Flight. The heart of the radar is the digital signal processor. The developmental digital signal processor architecture is PC based and uses commercial off-the-shelf (COTS) processing elements. The design is extremely flexible. It utilizes a commercial software analysis package to implement a virtual radar control panel as well as provide a display of the processed signals. This approach allows for rapid reconfiguration to efficiently incorporate on-going test results.<>
{"title":"Obstacle avoidance sensors for automatic Nap-of-the-Earth flight","authors":"R. J. LeFevre, J. C. Kirk, R. Durand","doi":"10.1109/DASC.1994.369419","DOIUrl":"https://doi.org/10.1109/DASC.1994.369419","url":null,"abstract":"This paper describes a 94 GHz active radar system designed to generate an accurate, three dimensional representation of the terrain and obstacles in the flight path of a helicopter. The data is to be used to provide signals to the guidance and control systems for automatic Nap-of-the-Earth (ANOE) Flight. The heart of the radar is the digital signal processor. The developmental digital signal processor architecture is PC based and uses commercial off-the-shelf (COTS) processing elements. The design is extremely flexible. It utilizes a commercial software analysis package to implement a virtual radar control panel as well as provide a display of the processed signals. This approach allows for rapid reconfiguration to efficiently incorporate on-going test results.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127049427","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 : 1994-10-30DOI: 10.1109/DASC.1994.369452
Binfan Liu, Jennie Si
This paper is concerned with the problem of detecting and isolating faults. We provide a method to design a fault isolation filter such that multiple faults can be detected and isolated. This design procedure guarantees to isolate up to n faults, where n is the dimension of the system. In particular, we are interested in the application of the developed scheme to a d.c. motor driving a centrifugal pump driven. Extensive computer simulations demonstrate the detectability and isolability of faults by the detection filter in the occurrence of multiple faults in the motor-pump dynamic system.<>
{"title":"Fault isolation filter design for linear systems","authors":"Binfan Liu, Jennie Si","doi":"10.1109/DASC.1994.369452","DOIUrl":"https://doi.org/10.1109/DASC.1994.369452","url":null,"abstract":"This paper is concerned with the problem of detecting and isolating faults. We provide a method to design a fault isolation filter such that multiple faults can be detected and isolated. This design procedure guarantees to isolate up to n faults, where n is the dimension of the system. In particular, we are interested in the application of the developed scheme to a d.c. motor driving a centrifugal pump driven. Extensive computer simulations demonstrate the detectability and isolability of faults by the detection filter in the occurrence of multiple faults in the motor-pump dynamic system.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"196 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133730887","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 : 1994-10-30DOI: 10.1109/DASC.1994.369478
R. Gucciardo
Flight Inspection encompasses the verification of navigational aids (e.g. VOR's, ILS's, GPS) in the air to ensure that the guidance signals emanating from these ground/air facilities as received by the user (Aviation Community) are within specification. This paper provide a brief tutorial on flight inspection concepts, fundamental techniques utilized for measurement and a typical system configuration employed on many of today's flight inspection aircraft. The balance of the paper focuses on the attributes of the latest generation Flight Inspection System (FIS) currently being developed for the US FAA by Gull Electronics Systems Division (Gull) of Parker Hannifin Corporation. The system consisting of airborne and ground components, employs the latest receiver, display and computer technology capitalizing on many developments achieved by both commercial and military aviation. The adaptation of Color Active Matrix LCD's for operator displays, state-of-the-art GPS for improved positioning and DATALINK to enhance air/ground communications for routine deployment and emergency dispatch, will ensure the ultimate Flight Inspection platform leading into the 21th century.<>
{"title":"Flight inspection-the \"state of the art\"","authors":"R. Gucciardo","doi":"10.1109/DASC.1994.369478","DOIUrl":"https://doi.org/10.1109/DASC.1994.369478","url":null,"abstract":"Flight Inspection encompasses the verification of navigational aids (e.g. VOR's, ILS's, GPS) in the air to ensure that the guidance signals emanating from these ground/air facilities as received by the user (Aviation Community) are within specification. This paper provide a brief tutorial on flight inspection concepts, fundamental techniques utilized for measurement and a typical system configuration employed on many of today's flight inspection aircraft. The balance of the paper focuses on the attributes of the latest generation Flight Inspection System (FIS) currently being developed for the US FAA by Gull Electronics Systems Division (Gull) of Parker Hannifin Corporation. The system consisting of airborne and ground components, employs the latest receiver, display and computer technology capitalizing on many developments achieved by both commercial and military aviation. The adaptation of Color Active Matrix LCD's for operator displays, state-of-the-art GPS for improved positioning and DATALINK to enhance air/ground communications for routine deployment and emergency dispatch, will ensure the ultimate Flight Inspection platform leading into the 21th century.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133453242","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 : 1994-10-30DOI: 10.1109/DASC.1994.369409
K. Raymer, T. Weingartner
The Quiet Knight Technology Demonstration Program has developed an integrated avionics system that greatly enhances covert penetration capabilities of the C-130 aircraft. The system centers around an enhanced digital map called the Advanced Terrain Data Processor (ATDP). The ATDP enhances covert capability by fusing data from different sensors and sources. Aggressive terrain following is accomplished by blending Low Probability of Intercept (LPI) Radar, Ladar, and radar altimeter with Digital Terrain Elevation Data (DTED). Accurate navigation, required by terrain following, combines data from the INS, GPS, radar altimeter, and DTED. Threat avoidance is accomplished by merging on-board and over the horizon intelligence data with DTED culminating in an automatic replan. All three functions combine to provide excellent situational awareness that keeps the aircraft safe front terrain impact and enemy engagement.<>
{"title":"Advanced terrain data processor","authors":"K. Raymer, T. Weingartner","doi":"10.1109/DASC.1994.369409","DOIUrl":"https://doi.org/10.1109/DASC.1994.369409","url":null,"abstract":"The Quiet Knight Technology Demonstration Program has developed an integrated avionics system that greatly enhances covert penetration capabilities of the C-130 aircraft. The system centers around an enhanced digital map called the Advanced Terrain Data Processor (ATDP). The ATDP enhances covert capability by fusing data from different sensors and sources. Aggressive terrain following is accomplished by blending Low Probability of Intercept (LPI) Radar, Ladar, and radar altimeter with Digital Terrain Elevation Data (DTED). Accurate navigation, required by terrain following, combines data from the INS, GPS, radar altimeter, and DTED. Threat avoidance is accomplished by merging on-board and over the horizon intelligence data with DTED culminating in an automatic replan. All three functions combine to provide excellent situational awareness that keeps the aircraft safe front terrain impact and enemy engagement.<<ETX>>","PeriodicalId":246447,"journal":{"name":"AIAA/IEEE Digital Avionics Systems Conference. 13th DASC","volume":"135 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1994-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124205930","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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