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AIAA Modeling and simulation Technologies Conference, 2018

作者： Gotschlich, Jürgen Jones, Michael Institute of Flight Systems Flight Dynamics and Simulation Lilienthalplatz 7 Braunschweig38108 Germany Institute of Flight Systems Rotorcraft Department Lilienthalplatz 7 Braunschweig38108 Germany

ISBN: (纸本)9781624105289

Real-time simulation requires the definition of scenarios, which may be defined on the ground or in the air. In-flight scenarios usually begin in a trimmed flight condition, so that the simulation model is in a steady state. At the German Aerospace Center (DLR), the Air Vehicle Simulator (AVES) is operated for flight research and simulator studies. Research simulators require a high degree of flexibility to modify scenarios. Moreover, the flexibility to modify the simulation model poses a challenge to both the user interface and the trim procedure. Therefore, an adjustable user interface is required to allow the user to run the trim calculation online for immediate operation in a simulation run. This paper presents an implementation of a generic approach to trim flight dynamic models for use in research flight simulators. This implies both the implementation of a graphical user interface as well as the trim algorithm and their interaction. An example is demonstrated for a helicopter model used for research activities at DLR. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： flight simulators

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Dynamic analysis of rigid-flexible coupling spacecraft based on Euler parameters

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Scientific Reports 2025年第1期15卷 1-12页

作者： Ji, Yi Zhang, Huan School of Astronautics Harbin Institute of Technology Harbin 150001 China Frontier Science Center for Interaction between Space Environment and Matter Harbin 150001 China National Key Laboratory of Modeling and Simulation for Complex Systems Harbin 150001 China MOE Key Laboratory of Dynamics and Control of Flight Vehicle Beijing Institute of Technology Beijing 100081 China

With the development of aerospace technology, rigid-flexible coupling spacecraft with strong nonlinearity dominates, bringing huge challenges for numerical tools. This paper aims to accurately and quickly analyze the dynamic behavior of rigid-flexible coupling spacecraft. In our work, rigid body and flexible body are both described by Euler parameters for avoiding singular angles. Then, for this type of strong nonlinear dynamic system, the BN-stable method that is unconditionally stable for nonlinear initial value problems proposed by the first author is introduced to solve the transient responses. To keep the accuracy of the numerical rotation matrix, the relation between the angular velocity and Euler parameters, and the constraint in the level of velocity, are introduced to reformulate the original BN-stable method. Through the dynamic analysis for rigid satellite bodies and flexible solar wings, we find that the proposed strategy can effectively simulate the dynamic responses of spacecraft, and compared to the currently popular strategy, our strategy enjoys considerable advantages in accuracy, stability, and dissipation. © The Author(s) 2025.

关键词： BN-stability Dynamic analysis Euler parameters Rigid-flexible coupling Rotation matrix

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Wake encounter severity assessment based on validated aerodynamic interaction models

Wake encounter severity assessment based on validated aerody...

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AIAA Atmospheric and Space Environments Conference 2010

作者： Schwarz, Carsten W. Hahn, Klaus-Uwe Fischenberg, Dietrich German Aerospace Center DLR Institute of Flight Systems Department Flight Dynamics and Simulation 38108 Braunschweig Germany DLR Institute of Flight Systems Department Flight Dynamics and Simulation Germany

ISBN: (纸本)9781617823350

Wake encounter severity criteria based on validated models are of great importance for any wake vortex related severity assessment. The aerodynamic interaction model "strip method" describes the vortex-induced aircraft reaction. The model quality is validated with wake encounter flight test data. Model shortcomings are improved with dedicated refinements. A simplified hazard area approach is developed employing validated simulation models. With one simple criterion, the roll control ratio, safe and undisturbed flight operations can be ensured. A limit value for manually flown (non fly-by-wire) aircraft is derived from piloted trials. With the simplified hazard area prediction method, this can be universally applied for wake vortex advisory systems like DLR's wake vortex prediction and monitoring system. © 2010 by Her Majesty the Queen in Right of Canada.

关键词： Wakes

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CONSIDERATIONS IN LEVEL OF FIDELITY IN REAL-TIME AVIONIC SYSTEM simulationS.

CONSIDERATIONS IN LEVEL OF FIDELITY IN REAL-TIME AVIONIC SYS...

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AIAA/AHS/ASEE Aircraft Design Systems and Operations Meeting.

作者： Teichgraeber, Richard D. General Dynamics Corp Flight Simulation Lab Fort Worth TX USA General Dynamics Corp Flight Simulation Lab Fort Worth TX USA

Many real-time digital simulations have mixed levels of fidelity within them, particularly within the avionic system models. In most cases, there are reasons why the varying levels of modeling detail are acceptable in the simulation. In particular, as the simulation continues to be used, a change involving new avionic systems and requirements may require an upgrade in the level of model detail in order to support the requirement. Considerations affecting the level of fidelity for these simulations are discussed. Examples are presented to illustrate the difficulties with lack of fidelity in the area of interest.

关键词： AIRCRAFT

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Adapting scenario definition language for formalizing uas concept of operations

Adapting scenario definition language for formalizing uas co...

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AIAA Modeling and simulation Technologies Conference, 2018

作者： Torens, Christoph Durak, Umut Nikodem, Florian Dauer, Johann Adolf, Florian-Michael Dittrich, Joerg Institute of Flight Systems Braunschweig Germany Flight Dynamics and Simulation Safety Critical Systems and Systems Engineering

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

Recent regulatory efforts from EASA introduced the new concept of a specific category that allows a stepwise adaptation of certification requirements. Based on a specific operation risk assessment, this category enables new aircraft system architectures and mission designs. The concept allows for operational restrictions, defined in the concept of operations, to maintain overall operation safety. Therefore, the description of the concept of operations is one of the key elements for the approval of a UAS operation. This description will be used by pilots, operators, certification authorities and possibly additional stakeholders, e.g., for publishing operation into databases. Standardization of this document seems mandatory. In addition to this, we discuss the formalization of this document for easy distribution amongst stakeholders and establishment of tool support. To support this, we use recent developments regarding standardization of simulation modeling. The American Institute of Aeronautics and Astronautics Modeling and simulation Technical Committee recently launched a working group towards the development of a standard scenario definition language for aviation. In this paper, we extend this language specification in order to define specific operation safety boundaries of a system. Thereby, we aim at creating a dialect of the simulation scenario definition language that can be used to describe safe scenarios for a particular system of interest. We further discuss the challenges and benefits of such a formalization of the concept of operations by adapting the simulation scenario definition language. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Standardization

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Simulating the unexpected: Challenge-centric simulator scenario design for advanced flight crew training

Simulating the unexpected: Challenge-centric simulator scena...

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AIAA Modeling and simulation Technologies Conference, 2018

作者： Niedermeier, Dominik Buch, Jan-Philipp Durak, Umut Mohrmann, Frederik Braunschweig38108 Germany Amsterdam1059 CM Netherlands Flight Dynamics and Simulation Institute of Flight Systems

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

In 2013 the International Civil Aviation Organization (ICAO) published a report on the implementation of Evidence-Based Training (EBT). EBT aims at improving the overall capabilities of a pilot trainee in certain competencies such as decision-making, communication, situational awareness and others. This results in a shift in training focus from maneuvers to the training of competencies, which in turn sets different requirements for the desired simulator training scenarios. This paper presents a training scenario design approach being driven by the expected impact on the crew rather than focusing on specific maneuvers or system failures. The so-called "Challenge-Centric" design approach was applied in the EU project Man4Gen. It forms the basis for the development of a scenario design kit that shall facilitate the design of training scenarios for Evidence-based Training. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Decision making

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A new flight training device for modern lightweight gyroplanes

A new flight training device for modern lightweight gyroplan...

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AIAA Modeling and simulation Technologies Conference 2011

作者： Pruter, I. Duda, H. Department of Flight Dynamics and Simulation German Aerospace Center DLR Institute of Flight Systems Braunschweig 38108 Germany

ISBN: (纸本)9781624101540

Subject of this paper is the design of a training device for a modern lightweight gyroplane. A simulation model which comprises all relevant characteristics of a gyroplane and which is capable of real time simulation is developed. The gyroplane body and its rotor are considered as two individual masses. The pitch and roll stick forces are the input signals to the simulation instead of the commonly used stick deflections. flight tests with an instrumented gyroplane of type MTOsport were conducted to estimate the unknown parameters of the simulation model and to validate it. The flight maneuvers were defined according to ICAO requirements. Simultaneously a basic training device for pilot training was built at DLR. Preliminary results whether this training device is able to improve training efficiency are shown. © 2011 by the authors.

关键词： flight simulators

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Automated maneuvering control of a conventional tactical aircraft enhanced with thrust vectoring controls

Automated maneuvering control of a conventional tactical air...

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AIAA Guidance, Navigation and Control Conference 2011

作者： Atesoglu, Özgür Kemal Özgören, M. Institute of Flight Systems Department of Flight Dynamics and Simulation 38108 Braunschweig Germany METU Ankara 06531 Turkey

ISBN: (纸本)9781600869525

Regarding the enhanced technical capabilities of today's tactical aircraft, high-agility maneuvering always draws attention. Agility should ensure enhanced controllability and maneuverability of the aircraft which generally necessitates redirection of the thrust by means of thrust vectoring control. The enhancement of airframe agility also entails assurance of on-board safety and improvements of mission effectiveness. Hence, automated maneuvering assistance can be proposed to assist the cockpit crew in achieving highly-agile maneuvers under emergency or combat circumstances. This study focuses on automated maneuvering controller design for a tactical aircraft equipped with thrust vectoring controls. It specifically concentrates on automated controllability and maneuverability demonstration by design of body pointing and velocity vector pointing maneuver controllers. The modeling and the design of the controllers are presented in detail and their performance and implementation alternatives are demonstrated with synthetic simulations. An automatic tailchase acquisition maneuver is implemented using the designed nose pointing controller. Also, with the proposed velocity vector pointing controller, an automatic velocity vector roll maneuver is implemented. © 2011 by the American Institute of Aeronautics and American Institute of Aeronautics and Astronautics.

关键词： Controllers

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Wake encounter flight control assistance based on forward-looking measurement processing

Wake encounter flight control assistance based on forward-lo...

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AIAA Atmospheric and Space Environments Conference 2010

作者： Hahn, Klaus-Uwe Fischenberg, Dietrich Niedermeier, Dominik Horn, Christian German Aerospace Center DLR Institute of Flight Systems Department Flight Dynamics and Simulation Lilienthalplatz 7 38176 Braunschweig Germany

ISBN: (纸本)9781617823350

Weather dependent delays, incidents and even accidents play an important role in aircraft operation. Any airplane is subject to air motion. Thus, turbulence is an important parameter in aeronautics. The phenomena which are summarized as gusts and turbulence strongly affect the passenger comfort and the safety of aircraft. Especially the turbulence caused by the wake of other aircraft can cause undesired motions mainly roll and vertical displacements. Active control technology can be applied to alleviate wake vortex effects on aircraft and support the pilot to carry out his control task. With the aid of specific controllers such vortices can be safely encountered even if the required control power temporarily exceeds the available capacity. Aircraft equipped with such a controller will be less affected by unforeseen wake vortex encounters or even will be able to follow another aircraft closer than authorized by the current separation distances without any compromise concerning safety. A very promising concept for wake vortex disturbance alleviation is the feed-forward disturbance compensation. The application of such an approach requires the accurate determination of the flow disturbance to calculate the necessary counter measures in terms of required control activities. Thus, the disturbance flow determination plays an important role and needs to be investigated thoroughly. Modern LIDAR technology has the potential to measure the flow filed in front of the aircraft and to provide the required disturbance information in advance before it affects the aircraft. The final goal of the DLR approach is the development of an Integrated Ride and Loads Improvement System (IRLIS) which is able to cope with the whole frequency range of atmospheric flow disturbances relevant for aircraft operation. The presented paper will summarize the status of the work performed during the last years and the current activities. © 2010 by Her Majesty the Queen in Right of Canada.

关键词： Wakes

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Verification of a flying wing handling qualities analysis by means of in-flight simulation

Verification of a flying wing handling qualities analysis by...

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AIAA Atmospheric flight Mechanics Conference 2011

作者： Ehlers, Jana Niedermeier, Dominik Leißling, Dirk German Aerospace Center DLR Institute of Flight Systems Department Flight Dynamics and Simulation Lilienthalplatz 7 38108 Braunschweig Germany

ISBN: (纸本)9781624101533

The assurance of appropriate handling qualities represents a critical aspect for the development of a flying wing. This paper presents an analysis and evaluation of the handling qualities of a flying wing configuration for 750 passengers. Its flying qualities are evaluated by applying analytical handing qualities criteria. These criteria are however developed for conventional airplanes and imply that the longitudinal and lateral motion of the aircraft can approximately be considered as separate motions. As the considered flying wing configuration does not fulfill the prerequisite of an approximately decoupled lateral and longitudinal motion the applicability of the analytical criteria is not guaranteed and the additional evaluation of the handling qualities by pilots is absolutely required for such an aircraft. For this purpose an in-flight simulation is carried out with the DLR research aircraft ATTAS which is able to simulate other airplane configurations during flight. It allows analyzing the flight dynamics of the flying wing under real flight conditions and an evaluation of its handling qualities by test pilots. The flight tests are performed with the original baseline-configuration of the flying wing and a modified configuration with active control which is examined to evaluate the potential of flight control augmentation to improve the handling qualities. The maneuvers of the flight tests focus on the examination of the dynamics of the flying wing during turns. Thanks to the means of in-flight simulation it is possible to evaluate the unusual coupling of the lateral and longitudinal motion of the aircraft. The analyses permit to point out some major deficiencies in the handling qualities of the considered flying wing. © 2011 by the authors.

关键词： Quality control

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