2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)最新文献

{"title":"StarTram: a new approach for low-cost Earth-to-orbit transport","authors":"J. Powell, G. Maise, J. Paniagua, J. Rather","doi":"10.1109/AERO.2001.931219","DOIUrl":"https://doi.org/10.1109/AERO.2001.931219","url":null,"abstract":"StarTram is a revolutionary concept for low-cost, high volume Earth-to-Orbit transport of passengers and/or cargo. StarTram is an evacuated launch tube that is magnetically levitated above the Earth's surface, up to a maximum altitude of /spl sim/18 km above the local terrain. Although the concept is advanced, it is within the limits of existing technology. The launch tube is levitated by the magnetic repulsive force between a set of superconducting (SC) cables attached to the tube and a set of SC cables on the ground beneath. A total current of 14 mega-amps in the levitated cables and an oppositely directed current of 280 mega-amps in the ground cables, produces a repulsive force of 4 tonnes/m at an altitude of 22 km above sea level (18 km above local ground level). These forces levitate a robust 7 meter diameter launch tube with an adequate margin of safety. The launch tube is stabilized, both vertically and horizontally, against the net upwards magnetic force and wind forces, by an array of high tensile strength (e.g., Kevlar) tethers that are anchored to the ground. Traveling inside the launch tube is a reusable StarTram Space Vehicle (SSV) that is magnetically levitated and accelerated to near orbital velocity in an evacuated tunnel at ground level. The SSV carries a set of lightweight SC magnets that inductively interact with a guideway of simple normal aluminum loops that operate at ambient temperature to stably levitate the moving vehicle. A separate AC current winding in the guideway pushes on the SSV's SC magnets, accelerating it. After the SSV reaches 8 km/sec at the end of its 1280 km long acceleration tunnel, it transitions into the ascending, magnetically levitated 220 km long launch tube, in which it coasts upwards to the launch point at an altitude of /spl sim/22 km The SSV then enters the upper atmosphere at a launch angle of 5 degrees. A subsequent 0.34 km/sec /spl Delta/V burn by a conventional LOX-kerosine rocket engine on the SSV inserts it into orbit. For a high-traffic system, StarTram can deliver payloads into orbit at a projected cost of $30 per kilogram This includes amortization of the launch complex, vehicle, and energy costs.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122115506","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}

{"title":"Dynamic inversion-based adaptive/reconfigurable control of the X-33 on ascent","authors":"D. Doman, A. Ngo","doi":"10.1109/AERO.2001.931289","DOIUrl":"https://doi.org/10.1109/AERO.2001.931289","url":null,"abstract":"A quaternion-based attitude control system is developed for the X-33 in the ascent flight phase. A nonlinear control law commands body-axis rotation rates that align the angular velocity vector with an Euler-axis defining the axis of rotation that takes the body-axis system into a desired-axis system. The magnitudes of the commanded body rates are determined by the magnitude of the rotation error The commanded body rates form the input to a dynamic inversion-based adaptive/reconfigurable control law. The indirect adaptive control portion uses online system identification to estimate the current control effectiveness matrix to update a control allocation module. The control allocation nominally operates in a minimum deflection mode; however, if a fault is detected, it can operate in a null-space injection mode that excites and decorrelates the effecters without degrading the vehicle response in order to enable online system identification. The overall system is designed to provide fault and damage tolerance for the X-33 on ascent. The baseline control law supports full envelope operation and eliminates trajectory dependent gain-scheduling that is typically found on this type of vehicle. Preliminary results are shown to demonstrate the feasibility of the approach.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"120 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114079787","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}

{"title":"A 94 GHz spaceborne cloud profiling radar antenna system","authors":"S. Spitz, A. Prata, J. Harrell, R. Perez, W. Veruttipong","doi":"10.1109/AERO.2001.931248","DOIUrl":"https://doi.org/10.1109/AERO.2001.931248","url":null,"abstract":"The CloudSat spacecraft, scheduled to launch in 2003, will carry a 94 GHz cloud profiling radar. The electrical design of its antenna system has been completed and is presented here. It consists of a quasi-optical transmission line that performs signal relaying and duplexing (using a Faraday rotator), and a collimating antenna that provides the required gain and spatial resolution. A shaped open Cassegrain collimating antenna is used because of its clear aperture, which allows for accurate electrical modeling, good performance, and significant reduction in implementation time and cost. The complete antenna system (horns to free space) has a worst case predicted gain of 63.1 dBi (59% efficiency) and exceeds the sidelobe envelope requirement of 50 dB below the peak gain at angles from boresight greater than 7 degrees.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"60 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122796520","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}

{"title":"Networking intelligent components to create intelligent spacecraft","authors":"R. Hammett","doi":"10.1109/AERO.2001.931178","DOIUrl":"https://doi.org/10.1109/AERO.2001.931178","url":null,"abstract":"Spacecraft utilize complex digital electronic controls to perform their missions. Although these systems have benefited from the availability of ever-faster computers and miniaturized electronics, overall control system architectures have changed little, utilizing a shared, centralized computer programmed to service many subsystems. These centralized systems perform well, but are a challenge to design and integrate, requiring complex custom software, custom I/O electronics and extensive vehicle wiring. The availability of microprocessors, memories and serial data terminals small and rugged enough to be embedded directly into subsystem mechanical components has opened the door to revolutionary new distributed architectures. These so-called \"smart\" or intelligent components can be interconnected into a network to form a distributed architecture. This paper discusses work done to define these distributed architectures and to construct prototype components. Important issues addressed include the physical network required to distribute data and power to components, highly reliable, fault-tolerant operation, the importance of industry standards and a discussion of packaging and installation considerations.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"58 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126198849","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}

{"title":"NOAA solar sail programs","authors":"P. Mulligan","doi":"10.1109/AERO.2001.931439","DOIUrl":"https://doi.org/10.1109/AERO.2001.931439","url":null,"abstract":"This panel will discuss plans and programs for enabling the development of Gossamer Spacecraft, that is, a new class of ultralight spacecraft which encompass: 1) massive solar sails with areal densities of less than a gram per square meter which could be used for low cost propulsion; 2) massive telescopes with apertures having areal densities of less than a kilogram per square meter; 3) very large lightweight solar solar power concentrators, and 4) large antennas. There is interest in such spacecraft in NASA, NOAA and DoD, and there are ongoing technology programs to enable these spacecraft. The challenges are massive. For example, while the limits of the areal density of glass telescopes in space is about 5 kglm2, gossamer telescopes are foreseen with areal densities of 1 kg/m2. To enable such telescopes, solar sails, etc, will require technology development in materials, structures, control, deployment, adaptive systems, high precision metrology, and so on. This panel consists of seven people who manage these technology programs. Each will present a brief description of their program's goals and content, and then discussion will be opened up to all present.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130183337","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}

{"title":"The passive sensor subsystem for DITP-current status and projected performance","authors":"P. Levan, J. Lyke, J. Waterman, J. R. Duffey, B. Paulsen","doi":"10.1109/AERO.2001.931167","DOIUrl":"https://doi.org/10.1109/AERO.2001.931167","url":null,"abstract":"The passive sensor subsystem (PSS) is under development as part of the DITP, which is a BMDO and tri-service flight demonstration of advanced interceptor technologies. We describe the PSS in terms of its three basic constituents the LWIR focal plane array (FPA), the flight cryostat assembly, and the malleable signal processor. We first review each of these basic constituents. We then describe how these constituents relate in the overall system, including the FPA in the operating environment provided by the flight cryostat assembly; the operation of, and data acquisition from, the FPA by the malleable signal processor; and the optical configuration used to achieve the desired pixel and FPA fields of view in both flight and ground-test embodiments.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129236172","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}

{"title":"An integrated diagnostics virtual test bench for life cycle support","authors":"K. Cavanaugh","doi":"10.1109/AERO.2001.931400","DOIUrl":"https://doi.org/10.1109/AERO.2001.931400","url":null,"abstract":"Qualtech Systems, Inc. (QSI) has developed an architecture that utilizes the existing TEAMS (Testability Engineering and Maintenance Systems) integrated tool set as the foundation to a computing environment for modeling and rigorous design analysis. This architecture is called a Virtual Test Bench (VTB) for Integrated Diagnostics. The VTB approach addresses design for testability, safety, and risk reduction because it provides an engineering environment to develop/provide: 1. Accurate, comprehensive, and graphical model based failure mode, effects and diagnostic analysis to understand failure modes, their propagation, effects, and ability of diagnostics to address these failure modes. 2. Optimization of diagnostic methods and test sequencing supporting the development of an effective mix of diagnostic methods. 3. Seamless integration from analysis, to run-time implementation, to maintenance process and life cycle support. undetected fault lists, ambiguity group lists, and optimized diagnostic trees. 4. A collaborative, widely distributed engineering environment to \"ring-out\" the design before it is built and flown. The VTB architecture offers an innovative solution in a COTS package for system/component modeling, design for safety, failure mode/effect analysis, testability engineering, and rigorous integration/testing of the IVHM (Integrated Vehicle Health Management) function with the rest of the vehicle. The VTB approach described in this paper will use the TEAMS software tool to generate detailed, accurate \"failure\" models of the design, assess the propagation of the failure mode effects, and determine the impact on safety, mission and support costs. It will generate FMECA, mission reliability assessments, incorporate the diagnostic and prognostic test designs, and perform testability analysis. Diagnostic functions of the VTB include fault detection and isolation metrics undetected fault lists, ambiguity group lists, and optimized diagnostic trees.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129285096","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}

{"title":"Gamma-ray induced responses in an erbium doped fiber laser","authors":"R. Bussjager, M. Hayduk, S. Johns, E. Taylor","doi":"10.1109/AERO.2001.931377","DOIUrl":"https://doi.org/10.1109/AERO.2001.931377","url":null,"abstract":"Many people are investigating photonic analog-to-digital converters (ADCs) for use in a digital receiver as a plausible solution to increase the bandwidth and resolution over that currently offered by electronic ADCs. A key component of a photonic ADC is a mode-locked fiber laser. A preliminary evaluation of the capability of utilizing this type of laser in space based ionizing environments and applications is required. This paper explains the effects of exposing an erbium-doped fiber laser (EDFL) to a total gamma-ray dose of 1 Mrad (Si). The performance of the laser is characterized in a passive fashion, i.e. before and after the irradiation. Predictions are offered to the extent of radiation induced damage that the fiber laser can endure before breaking down. The results of the evaluation will allow for further optimization of the EDFL for use in space-based architectures and applications.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128509463","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}

{"title":"Flight testing of the F/A-18E/F automatic carrier landing system","authors":"A. Prickett, C.J. Parkes","doi":"10.1109/AERO.2001.931220","DOIUrl":"https://doi.org/10.1109/AERO.2001.931220","url":null,"abstract":"The F/A-18E/F is the U.S. Navy's premier strike fighter aircraft, manufactured by the Boeing Company. The F/A-18E/F aircraft, while maintaining a high degree of commonality with the F/A-18C/D aircraft, has a lengthened fuselage, larger wing and control surfaces, strengthened landing gear, an improved propulsion system including a growth version of the General Electric F404 engine designated the F414-GE-400, and larger high performance inlets. This paper concentrates on the development, test, and evaluation of the F/A-18E/F Automatic Carrier Landing System (ACLS) up to and including the Third Sea Trials, upon which the aircraft was initially qualified for Mode I, totally automatic, approaches and landings to the aircraft carrier. The paper briefly describes the key components of the F/A-18E/F's ACLS, including cockpit displays and controls, antennas, autothrottles and flight control implementation, and interface with the shipboard AN/SPN-46(V) ACLS. Test procedures and methodology are presented as well as test results and interpretation. Finally, lessons learned are presented and recommendations are made for future aircraft ACLS developmental test and evaluation efforts.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128656189","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}

{"title":"Pattern synthesis for TechSat21-a distributed spacebased radar system","authors":"H. Steyskal, J. Schindler, P. Franchi, R. Mailloux","doi":"10.1109/AERO.2001.931252","DOIUrl":"https://doi.org/10.1109/AERO.2001.931252","url":null,"abstract":"The TechSat21 space-based radar employs a cluster of free-floating satellites, each of which transmits its own orthogonal signal and receives all reflected signals. The satellites operate coherently at X-band. The cluster forms essentially a multi-element interferometer with a concomitant large number of grating lobes and significant ground clutter. A novel technique for pattern synthesis in angle-frequency space is proposed, which exploits the double periodicities of the grating lobes in the angular domain and of the radar pulses in the frequency domain, and allows substantial gains in clutter suppression. Gains from 7 to 17 dB relative to the normal random, sparse array appear feasible.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"222 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121301095","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}