检索结果-内蒙古大学图书馆

AIAA Atmospheric flight Mechanics Conference and Exhibit 2003

作者： Steer, A.J. Flight Dynamics and Simulation Group College of Aeronautics Cranfield University Cranfield Bedfordshire MK43 OAL United Kingdom

ISBN: (纸本)9781624100895

Concorde's unique low-speed handling qualities are acceptable when flown in a rigidly procedural manner by experienced pilots. However, to be commercially viable and environmentally acceptable more numerous second-generation supersonic transport (SST) aircraft would need to provide increased passenger carrying capacity, range and the flexibility to integrate with existing sub-sonic air traffic during terminal manoeuvres. Their much larger size, weight and inertia compared to Concorde's, combined with increasing levels of relaxed longitudinal stability to improve aerodynamic efficiency, results in unconventional dynamics and degraded handling qualities on the final approach, where precise manual flightpath control is required © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Supersonic aircraft

来源：评论

学校读者我要写书评

暂无评论

Pilot evaluation of a real-time free wake model in a navy rotorcraft fleet trainer 73

Pilot evaluation of a real-time free wake model in a navy ro...

引用

73rd American Helicopter Society International Annual Forum Special Sessions 2017

作者： Keller, Jeffrey D. Wachspress, Daniel A. Hoffler, Jacques C. Continuum Dynamics Inc. EwingNJ United States NAVAIR Flight Vehicle Modeling and Simulation Branch Patuxent RiverMD United States

ISBN: (纸本)9781510844070

Accurate modeling of rotorcraft aerodynamics and induced flow fields in real-time is important for high fidelity simulation and training. The challenge is heightened for naval rotorcraft flight trainers that must accurately represent the complex aerodynamic interactions between the aircraft and disturbances from the shipboard environment. To address this challenge, a high-fidelity free-wake induced velocity software module that can model coupled rotor wake/ ship airwake interactions has been developed, integrated, validated, and evaluated through analysis and piloted simulations. Use of the free wake model also has allowed vibration cues to be generated that reflect the underlying operating state of the rotor system as opposed to a simulation effect. The free wake induced velocity model was incorporated into a naval rotorcraft fleet trainer and compared with the baseline model during a pilot evaluation session. This paper describes the execution and results of this pilot evaluation. © 2017 by American Helicopter Society International.

关键词： Fleet operations

来源：评论

学校读者我要写书评

暂无评论

Problems in integration of artificial intelligence systems with real-time simulation

Problems in integration of artificial intelligence systems w...

引用

flight simulation Technologies Conference and Exhibit, 1990

作者： Teichgraeber, Richard D. Flight Simulation Laboratory General Dynamics Corporation Post Office Box 748 Mail Zone 5939 Fort WorthTX76101 United States

Artificial Intelligence (AI) systems, especially expert systems, have been or are being integrated with simulations. simulation integration of AI systems is a useful tool for exercising and debugging rule-based/knowledge-based AI systems. One might expect, for example, to find one or more intelligence components (in the form of an expert system) integrated into a real-time flight simulator. These intelligent components might be inserted as instructors in a training simulator or as tactical decision aids for a pilot operating in an advanced cockpit. The Pilot’s Associate program is a good example of proposed on-board use of several expert systems in an advanced cockpit, with staged testing in flight simulators. When such expert systems are initially integrated, problems may show up in the presence of the real-time simulation which did not appear during expert systems developmen. Advances in computer technology have enabled significant gains in AI technology. This cross-feed of technologies has been generally supportive of AI system integration. The integration of an AI system presents a special set of problems. If nothing else, the executive nature of the AI system is asynchronous with respect to the simulation and the input/output is symbolic. This paper discusses sources of problems that arise from AI system integration as well as progress towards solution of these problems. A few sources are, for example: comlexity of communication interfaces, time delays in response to AI system advisories, use of dissimilar computers (AI system host with respect to simulation) and use of different languages or versions of the same language. © 1990 General dynamics Corporation. All rights reserved.

关键词： flight simulators

来源：评论

学校读者我要写书评

暂无评论

S-97 RAIDER® genhel model development and correlation with flight test data 77

S-97 RAIDER® genhel model development and correlation with ...

引用

77th Annual Vertical flight Society Forum and Technology Display: The Future of Vertical flight, FORUM 2021

作者： Xin, Hong Zhang, Chi Black, Andrew Thorsen, Adam Luszcz, Matthew Smith, Todd Herrmann, Thomas Jaeger, Patricia Handling Qualities and Control Laws Sikorsky Lockheed Martin Company StratfordCT United States Flight Dynamics Simulation Fort WorthTX United States

ISBN: (纸本)9781713830016

flight dynamics models for engineering simulation are vital to rotorcraft design and testing. This paper focuses on a multi-year effort to develop and improve the S-97 RAIDER® flight dynamics model in State-Space GenHel and to correlate the model with flight test data. State-Space GenHel (SSGH) is an upgraded version of legacy GenHel with a series of new/enhanced modeling capabilities. The S-97 model has been used to support conceptual, preliminary, and detailed air vehicle design, control laws (CLAWS) design and tuning, handling qualities evaluation, flight loads development, system integration lab (SIL) testing, flight testing, and test pilot training. During the ongoing flight test program, the SSGH model has been continuously updated to improve correlation with the test data. The correlation spans a wide range of flight conditions including hover, low speed flight, level flight, chirp tests at different speeds, and various maneuvers. A series of reduced-order models and corrections were implemented in SSGH to capture the complicated physics missed in the baseline model. High-fidelity analytical tools and component test data were used to derive the parameters for these reduced-order models and corrections, with which the model-data correlation has been significantly improved. The paper also discusses the challenges in tip clearance prediction and in modeling the rotor on propeller interference. This study shows that an engineering model, continuously improved using appropriate methods, can capture the flight dynamics characteristics of a high-speed compound helicopter with sufficient accuracy for supporting CLAWS design and flight test. © 2021 by the Vertical flight Society. All rights reserved.

关键词： Compound helicopters

来源：评论

学校读者我要写书评

暂无评论

Relative navigation and control of satellites using monocular model-based vision

引用

Journal of Spacecraft Technology 2016年第1期27卷 1-12页

作者： Kumar, Vinod Hablani, Hari B. Pandiyan, R. Control Dynamics and Simulation Group ISRO Satellite Centre Department of Space Bangalore560017 India Formerly at Aerospace Engineering Department IIT Bombay Powai Mumbai India Department of Mechanical Engineering IIT Gandhinagar Ahmedabad382424 India Flight Dynamics Group ISRO Satellite Centre Department of Space Bangalore560017 India

A technique of navigation of formation flying satellites at geostationary altitudes using monocular model-based vision is presented. The uniqueness of this method is in that it utilizes the circular model features on the co-operative satellite in the formation. Though there are several research articles based on the point and/ or line features, no known article addresses the application of the circular features with regard to co-operative formation flying. In this paper, this novel circular feature-based technique is applied for determination of the 3-D relative position of a satellite in the formation. The Hills-Clohessey-Wiltshire (HCW) equations are employed to model the dynamics of the satellites in formation. Even though HCW equations have inherent inaccuracies, this study uses them to establish the vision algorithm. It is well known that periodic relative motions in local-vertical-localhorizontal reference frame are an in-plane ellipse and an out-of plane circle. When perturbations are included, these periodic motions cannot be maintained without control. The controlled relative motion of two spacecraft in the presence of solar radiation pressure is simulated, using the relative position information obtained from the model-based vision sensor.

关键词： Geostationary satellites

来源：评论

学校读者我要写书评

暂无评论

Formal scenario definition language for aviation: Aircraft landing case study

Formal scenario definition language for aviation: Aircraft l...

引用

AIAA Modeling and simulation Technologies Conference, 2016

作者： Jafer, Shafagh Chhaya, Bharvi Durak, Umut Gerlach, Torsten Embry-Riddle Aeronautical University 600 S Clyde Morris Blvd Daytona BeachFL32114-3900 United States Institute of Flight Systems Flight Dynamics and Simulation Lilienthalplatz 7 Braunschweig38108 Germany

ISBN: (数字)9781624104299

ISBN: (纸本)9781624104299

Although the importance of scenarios in modeling and simulation has long been well known, there still exists a lack of common understanding and standardized practices in simulation scenario development. This paper proposes a Domain-Specific Language (DLS) to provide a standard scenario specification that will lead to a common mechanism for verifying and executing aviation scenarios, effective sharing of scenarios among various simulation environments, improve the consistency among different simulators and simulations, and even enable the reuse of scenario specifications. Following DSL design practices, the proposed Aviation Scenario Definition Language (ASDL) will provide a well-structured definition language to formally specify complete aircraft landing scenarios. In order to capture the necessary constructs for a simulation scenario, simulation Interoperability Standards Organization (SISO) Base Object Model (BOM) is adopted as the baseline metamodel. This baseline is extended using the fundamentals of aircraft landing that cover all the domain-related concepts and terminology as constructs. By taking a formal approach in defining aviation scenarios, ASDL aims at providing consistency and completeness checking, and model-to-text transformations capabilities for various targets in the aviation scenario definition domain. The results of this work will be used to develop a graphical modeling environment and automatic means to transform scenario models into executable scenario scripts. The work presented here is the first stepping stone in formal scenario definition in aviation domain. © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Specifications

来源：评论

学校读者我要写书评

暂无评论

Real time free wake and ship airwake model for rotorcraft flight training applications

Real time free wake and ship airwake model for rotorcraft fl...

引用

71st American Helicopter Society International Annual Forum 2015

作者： Keller, Jeffrey D. Wachspress, Daniel A. Hoffler, Jacques C. Continuum Dynamics Inc EwingNJ United States NAVAIR Flight Vehicle Modeling and Simulation Branch Patuxent RiverMD United States

Accurate modeling of rotorcraft aerodynamics and induced flow fields is important for high fidelity flight dynamics simulation and pilot training applications. A real-time, free-wake rotor induced velocity software module has been developed and integrated with a Navy helicopter flight dynamics simulation for testing in multiple pilot evaluations. The model provides a physically-based approach for simulation of rotorcraft aerodynamic phenomena identified by strong vortex wake interactional effects. Such phenomena include wake interactions between the main rotor, tail rotor, fuselage and empennage vertical descent through vortex ring state;and rotor wake/ship air wake interactions. This paper provides an overview of the wake model and flight dynamics simulation integration. Comparison of the coupled free wake aerodynamics and flight dynamics model with flight test data for an MH-60S helicopter was performed, focusing on vertical descent and shipboard operations. A summary of findings from pilot evaluations within the NAVAIR Manned flight Simulator facility is also given. © 2015 by the American Helicopter Society International, Inc.

关键词： flight dynamics

来源：评论

学校读者我要写书评

暂无评论

Real time free wake and ship airwake model for rotorcraft flight training applications

Real time free wake and ship airwake model for rotorcraft fl...

引用

ISBN: (纸本)9781510803787

Accurate modeling of rotorcraft aerodynamics and induced flow fields is important for high fidelity flight dynamics simulation and pilot training applications. A real-time, free-wake rotor induced velocity software module has been developed and integrated with a Navy helicopter flight dynamics simulation for testing in multiple pilot evaluations. The model provides a physically-based approach for simulation of rotorcraft aerodynamic phenomena identified by strong vortex wake interactional effects. Such phenomena include wake interactions between the main rotor, tail rotor, fuselage and empennage;vertical descent through vortex ring state;and rotor wake/ship air wake interactions. This paper provides an overview of the wake model and flight dynamics simulation integration. Comparison of the coupled free wake aerodynamics and flight dynamics model with flight test data for an MH-60S helicopter was performed, focusing on vertical descent and shipboard operations. A summary of findings from pilot evaluations within the NAVAIR Manned flight Simulator facility is also given. © 2015 by the American Helicopter Society International, Inc.

关键词： flight dynamics

来源：评论

学校读者我要写书评

暂无评论

Development of a three-state rotor interference model and application to coaxial rotor inflow modeling 5

Development of a three-state rotor interference model and ap...

引用

5th Decennial AHS Aeromechanics Specialists' Conference 2014: Current Challenges and Future Directions in Rotorcraft Aeromechanics

作者： Xin, Hong Goss, Jennifer Parkes, Chris Handling Qualities and Control Laws Analysis Sikorsky Aircraft Corporation Fort WorthTX United States Flight Dynamics Simulation Sikorsky Aircraft Corporation StratfordCT United States

ISBN: (纸本)9781634391788

A three-state rotor interference model has been developed to model the rotor off-disk interference velocity. This approach uses the same model structure as the Pitt-Peters three-state dynamic inflow model. The influence coefficient matrices and time constants are obtained numerically using high-fidelity free wake models such as CHARM. The resulting L and M matrices are then stored in data tables as functions of wake skew state and disk loading. During real-time simulation the L-matrix elements are obtained via a lookup table. The newly developed model has been successfully integrated into a flight dynamics simulation and applied to coaxial rotor inflow modeling. The model is able to correlate well with flight test data measured on a Sikorsky designed coaxial rotor compound helicopter. Copyright @ 2014 by the American Helicopter Society, International. All rights reserved.

关键词： Wakes

来源：评论

学校读者我要写书评

暂无评论

Using a dual-eyepoint visual scene generation system to present both the pilot’s and ground threat views

Using a dual-eyepoint visual scene generation system to pres...

引用

flight simulation Technologies Conference and Exhibit, 1989

作者： Fleury, Frederick B. Smart, Donald D. Flight Simulation Laboratory Fort Worth Division General Dynamics Corporation P. O. Box 748 MZ 5939 Fort WorthTX76101 United States

Two critical issues of the Close Air Support Study required the Engineering flight simulation Laboratory (FSL) at General dynamics Fort Worth Division to configure a dual-eyepoint visual scene generation system to present both the pilot’s and ground threat operator’s scenes. The first issue the simulation facility had to solve was how to present the visual cues that would allow the pilot to locate and deliver weapons against an assigned target set. This issue involved the visual scene presentation, the amount of clutter, visual effects, and the pilot’s field of view. First, visual scene presentation had to balance best scene resolution against the field of view the projection system provided to the pilot. Second, since a visual scene generation system cannot present real-world clutter, the system had to be tuned to provide the best scene without overloading. Third, visual effects representing battlefield conditions had to be analyzed and incorporated in the scene. Last, with the above parameters driving the requirements, a cockpit station was selected with a projection system whose field of view would accommodate the aircraft maneuver limits. © American Institute of Aeronautics and Astronautics, Inc., 1989. All rights reserved.

关键词： flight simulators

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：