检索结果-内蒙古大学图书馆

PRECISE FLIGHT-PATH control USING A PREDICTIVE ALGORITHM

JOURNAL OF GUIDANCE control AND DYNAMICS 1991年第5期14卷 936-942页

作者： JUNG, YC HESS, RA University of California Davis Davis California 95616

Generalized predictive control describes an algorithm for the control of dynamic systems in which a control input is generated that minimizes a quadratic cost function consisting of a weighted sum of errors between desired and predicted future system output and future predicted control increments. The output predictions are obtained from an internal model of the plant dynamics. A design technique is discussed for applying the single-input/single-output generalized predictive control algorithm to a problem of longitudinal/vertical terrain-following flight of a rotocraft. By using the generalized predictive control technique to provide inputs to a classically designed stability and control augmentation system, it is demonstrated that a robust flight-path control system can be created that exhibits excellent tracking performance.

关键词： Precise Flight Path control stability and control augmentation system Single Input Single Output Rotorcrafts control Algorithm Airspeed Closed Loop Transfer Function Flight control system Optimal control Feedback Loop

来源：评论

学校读者我要写书评

暂无评论

FLIGHT TEST OF THE JAPANESE UPPER SURFACE BLOWING STOL EXPERIMENTAL AIRCRAFT ASKA

引用

JOURNAL OF AIRCRAFT 1991年第10期28卷 630-637页

作者： YAMATO, H OKADA, N BANDO, T University of Tokyo Tokyo Japan National Aerospace Laboratory Tokyo Japan

The Upper Surface Blowing STOL aircraft named ASKA was developed and flight tested by the National Aerospace Laboratory of Japan between 1977-1989. The aircraft was a conversion of the Kawasaki C-1 medium transport, with four newly developed FJR710/600S turbofan engines on the wing. The short takeoff and landing performance, including the stability and control augmentation system and boundary-layer control, was intensively examined by the flight test. Flight-test data were obtained at altitude and converted to the standard sea level conditions to compare with the design data. From the viewpoint of the lift-and-drag and related performances, the design STOL capability was proven by the flight-test program.

关键词： Flight Test Programme STOL Experimental Aircraft stability and control augmentation system National Aerospace Laboratory of Japan Boundary Layer control Turbofan Engines Angle of Attack Flight Path Angle Yaw Damper

来源：评论

学校读者我要写书评

暂无评论

GROUND-SIMULATION INVESTIGATION OF VTOL AIRWORTHINESS CRITERIA FOR TERMINAL AREA OPERATIONS

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 1985年第6期8卷 761-767页

作者： LEBACQZ, JV SCOTT, BC FED AVIAT ADM MOFFET FIELDCA

A two-part ground simulation investigation of variables that affect VTOL terminal area operations was conducted. The baseline vehicle selected was a generalized tilt-rotor aircraft. Experimental variables included the manner in which conversion from airborne to thrust-borne flight is effected, the coupling between conversion and aircraft pitch and heave control, and the allowable range of airspeeds at given thrust inclination angles. Four pilots conducted over 200 piloted evaluations of combinations of these variables for representative VTOL terminal area tasks. Among the results shown are that, for visual approaches, the conversion profile had minimal influence on the aircraft's acceptability but, for instrument approaches, desired performance could be achieved only if all the the conversion was performed prior to acquiring the glide slope, or if additional automation and display assistance was provided.

关键词： Terminal Area Operations Airworthiness Instrument Approach Tiltrotor Aircraft Rate of Climb Aircraft Configurations Pilot stability and control augmentation system Blade Loading Distance Measuring Equipment

来源：评论

学校读者我要写书评

暂无评论

DYNAMICS AND control OF MANEUVERABLE TOWED FLIGHT VEHICLES

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 1992年第5期15卷 1245-1252页

作者： COCHRAN, JE INNOCENTI, M NO, TS THUKRAL, A Auburn University Auburn Alabama 36849

This paper considers the problems of dynamically modeling and automatically controlling the motion of a small maneuverable flight vehicle that is being lowed by a much larger one. Mathematical models of the components of the system, including the towing aircraft, tow cable reel mechanism, tow cable, and vehicle aerodynamics, are described. The development of an autopilot for stability augmentation and maneuvering of the towed vehicle is discussed. An overview of the implementation of the models in a digital computer simulation program is provided, and some typical results obtained using the program are presented. A comparison of theoretical and experimental results is also made.

关键词： Flight Vehicle stability and control augmentation system Aerodynamic Characteristics Autopilot Mathematical Models Digital Computers control Surfaces Elevator Deflection Earth Newton's Laws of Motion

来源：评论

学校读者我要写书评

暂无评论

Development and Conversion Flight Test of a Small Tiltrotor Unmanned Aerial Vehicle

引用

JOURNAL OF AIRCRAFT 2010年第2期47卷 730-732页

作者： Choi, Seongwook Kang, Youngshin Chang, Sungho Koo, Samok Kim, Jai Moo Korea Aerosp Res Inst Smart UAV Dev Ctr Taejon 305333 South Korea

Seongwook et al present a sizing and performance analysis of the downscaled tiltrotor for unmanned aerial vehicle (UAV), in which simple codes based on blade element and momentum theory were used. The conversion corridor of the tiltrotor was predicted and the nacelle tilt angle and air speed were compared with flight-test results. This small tiltrotor flight test is expected to reduce risks in flight test of the 5-m-span full-scale tiltrotor UAV called Smart UAV.

关键词： Flight Test Programme Tiltrotor UAV Airframes Aeroplane Aerodynamic Performance stability and control augmentation system Rotor systems Flight control system Flight control Computer

来源：评论

学校读者我要写书评

暂无评论

Dynamic modeling and fuzzy control for a small tiltrotor unmanned aerial vehicle

引用

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 2013年第9期227卷 1468-1487页

作者： Chang, Sungho Bang, Hyochoong Lee, Wonsuk Park, Bumjin Korea Adv Inst Sci & Technol Div Aerosp Engn Taejon South Korea Korea Aerosp Res Inst Taejon South Korea

Dynamic modeling and fuzzy control of a tiltrotor unmanned aerial vehicle are presented. In order to design a full-conversion flight controller for a tiltrotor unmanned aerial vehicle, the dynamic characteristics of a small tiltrotor unmanned aerial vehicle during helicopter-to-airplane conversion is investigated. A six-degree-of-freedom nonlinear equation of motion using powered wind tunnel test data is developed based on a Bell Model 301 tiltrotor research aircraft. The time-varying characteristics of the conversion maneuver, over which system dynamics change rapidly, are handled by a Takagi-Sugeno fuzzy control approach in both longitudinal and lateral axes. Simulation results indicate that a small tiltrotor unmanned aerial vehicle exhibits nacelle tilt during the backward conversion flight from airplane to helicopter mode.

关键词： Tiltrotor unmanned aerial vehicle dynamic modeling Takagi-Sugeno fuzzy control stability and control augmentation system conversion autopilot

来源：评论

学校读者我要写书评

暂无评论

Prediction and Simulator Verification of Roll/Lateral Adverse Aeroservoelastic Rotorcraft-Pilot Couplings

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2016年第1期39卷 42-60页

作者： Muscarello, Vincenzo Quaranta, Giuseppe Masarati, Pierangelo Lu, Linghai Jones, Michael Jump, Michael Politecn Milan Dipartimento Sci & Tecnol Aerosp I-20156 Milan Italy Univ Liverpool Sch Engn Flight Sci & Technol Liverpool L69 3BX Merseyside England

The involuntary interaction of a pilot with an aircraft can be described as pilot-assisted oscillations. Such phenomena are usually only addressed late in the design process when they manifest themselves during ground/flight testing. Methods to be able to predict such phenomena as early as possible are therefore useful. This work describes a technique to predict the adverse aeroservoelastic rotorcraft-pilot couplings, specifically between a rotorcraft's roll motion and the resultant involuntary pilot lateral cyclic motion. By coupling linear vehicle aeroservoelastic models and experimentally identified pilot biodynamic models, pilot-assisted oscillations and no-pilot-assisted oscillation conditions have been numerically predicted for a soft-in-plane hingeless helicopter with a lightly damped regressive lead-lag mode that strongly interacts with the roll mode at a frequency within the biodynamic band of the pilots. These predictions have then been verified using real-time flight-simulation experiments. The absence of any similar adverse couplings experienced while using only rigid-body models in the flight simulator verified that the observed phenomena were indeed aeroelastic in nature. The excellent agreement between the numerical predictions and the observed experimental results indicates that the techniques developed in this paper can be used to highlight the proneness of new or existing designs to pilot-assisted oscillations.

关键词： Rotary Wing Aircraft Test Pilots Articulated Rotor Flight Simulation Flight Testing stability and control augmentation system Airframes Collective Pitch control Nyquist stability Criterion Aerodynamic Coefficients

来源：评论

学校读者我要写书评

暂无评论

Multibody Simulation of Integrated Tiltrotor Flight Mechanics, Aeroelasticity, and control

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2012年第5期35卷 1391-1405页

作者： Mattaboni, Mattia Masarati, Pierangelo Quaranta, Giuseppe Mantegazza, Paolo Politecn Milan Dipartimento Ingn Aerosp I-20156 Milan Italy

This work describes the application of an adaptive control algorithm based on the generalized predictive control paradigm to a detailed nonlinear aeroelastic model of a tiltrotor aircraft that includes rigid-body degrees of freedom, restricted to the plane of symmetry. The analysis is based on an original multibody dynamics formulation. The model is augmented by an autopilot and a stability augmentation system;in relevant cases, a model of the passive biomechanics of the pilot is considered as well. The interaction of rigid-body and deformable degrees of freedom alters the aeroelastic behavior of the system compared with that of the clamped wing rotor, discussed in a previous work. The flutter mechanism, originally consisting in whirl flutter, changes after considering rigid-body degrees of freedom;the short-period flight mechanics mode now dominates high-speed stability. This issue is mainly addressed by the stability augmentation system, whereas the generalized predictive control is mainly used to reduce gust-induced wing loads, although its intervention for whirl-flutter suppression is still needed to extend the flight envelope at very high speed. The capability of the adaptive regulator RI reduce wing loads is assessed in hover and in highspeed forward flight. In the latter condition, the capability to suppress whirl flutter is assessed as well.

关键词： Flight Mechanics Aeroservoelastic systems Tiltrotor Aircraft Multibody Simulation stability and control augmentation system Autopilot Pilot Adaptive control Algorithm Flight Envelope Wing Loading

来源：评论

学校读者我要写书评

暂无评论

Development of an AFCS SIL twin for Autopilot Software Design and Integration

Development of an AFCS SIL twin for Autopilot Software Desig...

引用

AIAA Aviation Forum

作者： Demirer, Serkan Duran, Sabahat Yilmaz, Murat Turkish Aerosp Ind TR-06980 Ankara Turkiye

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

The recently popular digital twin concept is expected to provide a great convenience in reducing the effort and schedules of engineering programs. The Digital twin concept, which can be used in all areas of technology, also plays an important role in the aviation field. Although formal testing and certification credit is what first appears in mind when it comes to avionics software;years of development & integration efforts, numerous iterations of releases, and regression testing are the iterative effort behind the scenes. These efforts can lead to a prolongation of the software development process and a delay in the delivery time of the whole system. This study presents the current status, as well as ongoing development efforts, of a digital twin SIL environment in the scope of autopilot software development project for T625 helicopter program. By creating a digital copy of the Automatic Flight control system equipment and running these digital copies together in an integrated manner, as in the system Integration Laboratory, the digital twin of the system Integration Laboratory was realized. This digital twin serves as a virtual desktop laboratory for development testing, initial integration and regression testing environment for autopilot code. Outputs produced by the autopilot code and movement of the actuators in response to sets of the same inputs are compared, in order to assess the accuracy of the SIL digital twin as compared to the real (SIL, helicopter) equipment. Currently, the SIL digital twin is in use, contributing to the early detection of integration errors and developers' own-desktop testing, reducing the intensity of SIL usage. The environment also serves as the infrastructure for a continuous integration (CI) environment. The continuous checks include not only the nightly builds but also nightly functionality checks, that are SAS, ATT and IAS modes of the autopilot, as well as the comprehensive automated PFT test.

关键词： Avionics systems Automatic Flight control systems Actuators stability and control augmentation system Digital Twins Helicopters Regression Testing Indicated Airspeed Software Development Software Design

来源：评论

学校读者我要写书评

暂无评论

Structured μ-Synthesis of Robust Attitude control Laws for Quad-Tilt-Wing Unmanned Aerial Vehicle

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2020年第12期43卷 2258-2274页

作者： Panza, Simone Lovera, Marco Sato, Masayuki Muraoka, Koji Politecn Milan Dept Aerosp Sci & Technol Via La Masa 34 I-20156 Milan Italy Japan Aerosp Explorat Agcy Flight Res Ctr Mitaka Tokyo 1810015 Japan

The problem of designing the longitudinal flight controller for a quad-tilt-wing unmanned aerial vehicle to achieve robust performance under constraints on the controller structure is considered. An approach based on mu-synthesis is proposed, in which a nonparametric inverse multiplicative uncertainty description is employed to account for the uncertainties of the aircraft attitude dynamics at each operating condition, with specific reference to variations in the number of unstable modes. The resulting mu-synthesis problem with a frequency-dependent weighting function, the structure of which is defined a priori, is reformulated as a structured H infinity problem and solved by means of available MATLAB software. Simulation results are presented in order to show the effectiveness of the approach.

关键词： Attitude Dynamics UAV MATLAB stability and control augmentation system Closed Loop Transfer Function Aeroplane Pilot Frequency Response Functions Helicopters Multiple Input Multiple Output

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：