摘要 :
This report presents the aerodynamic characteristics of a proposed aerial tow target configured to meet the requirements of the Navy Standard Tow Target System for a large gunnery target. The Profile Fighter Tow Target will be bot...
展开
This report presents the aerodynamic characteristics of a proposed aerial tow target configured to meet the requirements of the Navy Standard Tow Target System for a large gunnery target. The Profile Fighter Tow Target will be both size and performance representative of potential enemy fighter airplanes. (Author)
收起
摘要 :
The purpose of this report is to determine the applicability of the QuantitativeFeedback Theory (QFT) approach to designing the control laws for a modern military flight control system. This report documents a portion of the QFT r...
展开
The purpose of this report is to determine the applicability of the QuantitativeFeedback Theory (QFT) approach to designing the control laws for a modern military flight control system. This report documents a portion of the QFT research program, specifically, the implementation of a QFT design on a manned simulation of the NF-16D Variable Stability Inflight Simulator Test Aircraft (VISTA F-16). The control law design addresses the subsonic flight envelope of the VISTA F-16 including changes in aircraft configuration. The design was accomplished as a SISO longitudinal loop and a MIMO lateral loop, and incorporates pilot handling qualities within the specifications. Imbedding handling qualities in the system through prudent choice of control variable ensured that the performance specifications were met. Flexibility in the prefilter design allowed the closed loop response to be shaped for proper feel. The handling qualities were evaluated in a high fidelity, manned simulation of the system. The QFT design provided level 1 handling qualities per the specifications in the pitch channel. It did not provide level 1 handling qualities in the lateral channel, but the design requires minor modification to meet level 1.
收起
摘要 :
The report analyzes the state of aeronautics research and the role of the Federal Government in supporting that research. Among its conclusions were that there are possible today monumental advances in aircraft performance. Due to...
展开
The report analyzes the state of aeronautics research and the role of the Federal Government in supporting that research. Among its conclusions were that there are possible today monumental advances in aircraft performance. Due to the nature of the benefits, both military and commercial, the Federal Government and industry must unite to realize that potential. The report addresses specific goals in three areas - subsonics, supersonics, and transatmospherics.
收起
摘要 :
An aircraft's response to control inputs varies widely throughout its flightenvelope. The aircraft configuration also impacts control response through variations in center of gravity and moments of inertia. Designing a flight cont...
展开
An aircraft's response to control inputs varies widely throughout its flightenvelope. The aircraft configuration also impacts control response through variations in center of gravity and moments of inertia. Designing a flight control system (FCS) to accommodate the full flight envelope and configuration set of an aircraft is clearly a complex undertaking. Quantitative feedback theory (QFT) is a design tool which enables the engineer to attack this task in an efficient way. Although QFT is a robust control design technique, it is an interactive algorithm allowing the engineer full control over compensator order and gain. In this research effort, a full subsonic flight envelope FCS is designed for the VISTA F-16 aircraft using QFT. Four aircraft configurations are considered. The strict control of the compensator order and gain allowed by QFT facilitates the attainment of desired performance while avoiding physical saturations. In addition, flying qualities are imbedded in the longitudinal design through the use of a control parameter which varies with the aircraft's energy state. This parameter is synthesized to closely reflect the actual control desires of the pilot throughout the aircraft flight envelope. Linear simulations with realistically large control inputs are used to validate the design.
收起
摘要 :
National Aeronautics and Space Administration Dryden Flight Research Center acquired a Gulfstream III (GIII) aircraft to serve as a testbed for aeronautics flight research experiments. The aircraft is referred to as SCRAT, which s...
展开
National Aeronautics and Space Administration Dryden Flight Research Center acquired a Gulfstream III (GIII) aircraft to serve as a testbed for aeronautics flight research experiments. The aircraft is referred to as SCRAT, which stands for SubsoniC Research Aircraft Testbed. The aircraft.s mission is to perform aeronautics research; more specifically raising the Technology Readiness Level (TRL) of advanced technologies through flight demonstrations and gathering high-quality research data suitable for verifying the technologies, and validating design and analysis tools. The SCRAT has the ability to conduct a range of flight research experiments throughout a transport class aircraft.s flight envelope. Experiments ranging from flight-testing of a new aircraft system or sensor to those requiring structural and aerodynamic modifications to the aircraft can be accomplished. The aircraft has been modified to include an instrumentation system and sensors necessary to conduct flight research experiments along with a telemetry capability. An instrumentation power distribution system was installed to accommodate the instrumentation system and future experiments. An engineering simulation of the SCRAT has been developed to aid in integrating research experiments. A series of baseline aircraft characterization flights has been flown that gathered flight data to aid in developing and integrating future research experiments. This paper describes the SCRAT's research systems and capabilities
收起
摘要 :
An overview is presented of the design codes developed in Australia that are directly applicable or related to the Aerodynamics of towed bodies. In view of the continuing need for increasingly sophisticated towed targets, often as...
展开
An overview is presented of the design codes developed in Australia that are directly applicable or related to the Aerodynamics of towed bodies. In view of the continuing need for increasingly sophisticated towed targets, often as an alternative to costly subscale targets, a collaborative activity was undertaken to: 1) review the availability and applicability of existing design codes for the free flight phase of deployed aerial tow bodies in the subsonic and supersonic flight regimes; and 2) recommend either an existing design approach or cooperative action to provide a satisfactory capability. In this report, an overview of the design codes developed in Australia that are directly applicable or related to the aerodynamics of towed bodies is presented.
收起
摘要 :
The study was conducted to validate military specification MIL-F-8785B(ASG), 'Flying Qualities of Piloted Airplanes,' dated 7 August 1969, Interim Amendment-1 (USAF), dated 31 March 1971, by performing a detail comparison of its r...
展开
The study was conducted to validate military specification MIL-F-8785B(ASG), 'Flying Qualities of Piloted Airplanes,' dated 7 August 1969, Interim Amendment-1 (USAF), dated 31 March 1971, by performing a detail comparison of its requirements with the known characteristics of the Lockheed C-5A and pilot comments on them. The comparison was based primarily on existing flight test data supplemented by analytical data as required for this evaluation process. Paragraph by paragraph validations of discrepancies are noted, resolution attempted if necessary, and any recommendations given. In addition, recommendations are made enumerating experimental and analytical investigations beyond the scope of this study which will provide data for further validation and updating of the requirements.
收起
摘要 :
This report is a part of the documentations which describe the complete development of an STTR Phase 2 effort entitled, Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. This report is one of four manuals that com...
展开
This report is a part of the documentations which describe the complete development of an STTR Phase 2 effort entitled, Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. This report is one of four manuals that comprise the final report. The remaining reports consist of the ZAERO Programmer's Manual (Volume 2), the ZAERO Applications Manual (Volume 3) and the ZAERO Theoretical Manual (Volume 4). ASTROS is the seamless integration of the ZAERO module into ASTROS. As an aerodynamic enhancement to ASTROS, ZAERO is the ZONA aerodynamic module, unified for all Mach number ranges. This manual assumes the reader is familiar with the ASTROS system (Version 10.0), its terminology and user interface. It provides the complete user interface to the ASTROS system required for preparation of input data. First, an overview of the ZAERO software is presented. Second, the executive control options are described. Third, a complete and comprehensive description of the bulk data input is presented. Fourth, ZAERO modeling guidelines are provided with detailed descriptions for proper aerodynamic, geometry and spline input. Finally, the output description of ZAERO is presented with output samples.
收起
