检索结果-内蒙古大学图书馆

Optimal Input Design for aircraft stability and control Flight Testing

JOURNAL OF OPTIMIZATION THEORY AND APPLICATIONS 2021年第2-3期191卷 415-439页

作者： Morelli, Eugene A. NASA Langley Res Ctr Hampton VA 23666 USA

Flight testing to characterize aircraft stability and control is a complex and expensive task that involves restrictive practical constraints. Methods are examined for optimizing the inputs applied to aircraft controls during flight test maneuvers to produce informative flight data. Theory underpinning optimal input design for stability and control flight testing is explained. The merits and limitations of optimal inputs are discussed, along with optimization approaches and practical considerations involved in applying optimal inputs in a real flight test environment. Simulated and flight test case studies of optimal multiple-input design for aircraft stability and control flight testing are presented and discussed.

关键词： Optimal input design aircraft stability and control Flight testing Parameter estimation

来源：评论

学校读者我要写书评

暂无评论

Investigation of Reduced-Order Modeling for aircraft stability and control Prediction

Investigation of Reduced-Order Modeling for Aircraft Stabili...

引用

AIAA Science and Technology (SciTech) Forum and Exposition

作者： Frink, Neal T. Hiller, Brett R. Murphy, Patrick C. Cunningham, Kevin Shah, Gautam H. NASA Configurat Aerodynam Branch Langley Res Ctr Hampton VA 23681 USA NASA Dynam Syst & Control Branch Langley Res Ctr Hampton VA 23681 USA NASA Flight Dynam Branch Langley Res Ctr Hampton VA 23681 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

High-fidelity computational fluid dynamics tools offer the potential to approximate increments for ground-to-flight scaling effects, as well as to augment the dynamic damping derivative data for motion-based flight simulators. Unfortunately, the computational expense is currently prohibitive for populating a complete simulator database. This work investigates an existing surrogate-based, indicial response reduced-order model methodology as a means to efficiently augment a flight simulator database with high-fidelity nonlinear aerodynamic damping derivatives. Creation of the reduced-order model is based on the superposition integrals of the step response with the derivative of its corresponding input signal. Step responses are calculated using a computational grid motion approach that separates the effects of angle of attack and sideslip angle from angular rates, and rates from angle of attack and sideslip. It is demonstrated that the transients produced during the start of a forced-oscillation motion are captured by the reduced-order model to the level of fidelity of a comparable computational solution. Aerodynamic coefficients computed within minutes by the reduced-order model for an aircraft undergoing an 18-second half Lazy-8 maneuver and a 25-second Immelmann turn maneuver are compared with those from full computational flight solutions that required days to complete. Finally, a cost-benefit assessment is included that demonstrates a compelling advantage for this approach.

关键词： Step response Reduced order model SIDESLIP aircraft stability and control derived data flight simulators Reduced order modeling ANGLE OF ATTACK high fidelity

来源：评论

学校读者我要写书评

暂无评论

Validation of a Mid-Fidelity Approach for aircraft stability and control Characterization

Validation of a Mid-Fidelity Approach for Aircraft Stability...

引用

AIAA Aviation Forum

作者： Simmons, Benjamin M. Geuthert, Steven C. Ahuja, Vivek NASA Flight Dynam Branch Langley Res Ctr Hampton VA 23681 USA NASA Aeronaut Syst Engn Branch Langley Res Ctr Hampton VA 23681 USA Res Flight Austin TX 78750 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

This paper describes an efficient computational approach for aircraft aerodynamic model development intended for use in flight dynamics simulations. A commercial surface-vorticity flow solver called FlightStream((R)) is employed to predict performance, stability, and control characteristics for a NASA subscale electric vertical takeoff and landing aircraft in its isolatedairframe configuration. A framework is described to rapidly convert OpenVSP geometry into a form compatible with the FlightStream((R)) software. FlightStream((R)) predictions for the variation of aerodynamic force and moment coefficients with airflow angles and control surface deflection angles are compared to static wind-tunnel data to illustrate the process and assess the accuracy of FlightStream((R)) solutions. The results and approach presented in this paper are encouraging for use in rapid aerodynamic modeling and flight dynamics simulation development early in the aircraft design process.

关键词： Wind Tunnel Tests aircraft Configurations Aerodynamic Force Coefficients OpenVSP Flight Dynamics Vorticity NASA Vertical Takeoff and Landing aircraft Design Process aircraft stability and control

来源：评论

学校读者我要写书评

暂无评论

A Review of High-Speed aircraft stability and control Challenges

A Review of High-Speed Aircraft Stability and Control Challe...

引用

AIAA Aviation Forum

作者： Takahashi, Timothy T. Griffin, Jack A. Grandhi, Ramana, V Arizona State Univ Sch Engn Matter Transport & Energy Practice Aerosp Engn Tempe AZ 85281 USA Air Force Inst Technol Wright Patterson AFB OH 45433 USA Air Force Inst Technol Dept Aeronaut & Astronaut Wright Patterson AFB OH 45433 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

This paper identifies key stability and control screening parameters needed to design general-purpose high-supersonic and hypersonic aircraft. A review of ground test, computation and flight test data of the rocket propelled Bell X-2, North American X-15, Martin X-24A and Northrop HL-10 lifting bodies, the Lockheed YF-12 (SR-71) and North American XB-70 jet propelled aircraft as well as the Rockwell Space Shuttle Orbiter reveals a need for strong static directional stability. We glean from the relative success of the X-15 and YF-12 and the performance limitations of the others that lateral-directional stability and control needs special scrutiny during preliminary design. We show how adverse yaw can be so strong as to destabilize an otherwise "innocent" looking statically stable airframe like the Bell X-2. This document outlines sources for effective screening criteria that should be considered during high-speed vehicle development. They derive from the classic MIL-STD-8785C, MIL-STD-1797A, MIL-STD-1797B as well as in older AGARD reports.

关键词： aircraft stability and control Fly By Wire control Systems Scramjet Powered aircraft Flight Test Programme Airframes Space Shuttle Orbiter Hypersonic aircraft Lifting Body Rockets Hypersonic Aerodynamics

来源：评论

学校读者我要写书评

暂无评论

Assessment of Longitudinal stability-and-control Characteristics of Hybrid Wing Body aircraft in Conceptual Design

Assessment of Longitudinal Stability-and-Control Characteris...

引用

AIAA Aviation Forum and Exposition

作者： Cai, Yu Xie, Jiacheng Harrison, Evan D. Mavris, Dimitri N. Georgia Inst Technol Aerosp Syst Design Lab Daniel Guggenheim Sch Aerosp Engn Atlanta GA 30332 USA Georgia Tech ASDL Atlanta GA 30332 USA

ISBN: (数字)9781624106101

ISBN: (纸本)9781624106101

The conceptual design phase traditionally employs the "tail volume ratio" method to initially size the horizontal and vertical tails on tube-and-wing aircraft. Such method is no longer applicable for certain hybrid wing body (HWB) configurations where the use of elevons and the absence of a horizontal stabilizer yield strong coupling between mass properties, aerodynamics, and stability-and-control (S&C) characteristics, which should therefore be explicitly assessed in the conceptual design stage. Additionally, the lack of historical data for HWB calls for a physics-based approach to quantify the aircraft stability-and-control characteristics. Previous research has attempted to use static margin as a criterion to determine the static stability, yet the use of a stability augmentation system helps relax this constraint and may lead to more efficient design candidates which are statically unstable but dynamically stabilizable. This paper proposes a novel approach to facilitate the assessment of S&C characteristics during design space exploration at the conceptual phase, where a physics-based S&C analysis module is integrated into a conceptual modeling and simulation environment, trimmability, stability, controllability, and stabilizability constraints are identified and examined within the design space along with existing physical and operational constraints, and a constrained optimization is performed to highlight the impact of accounting for S&C constraints on vehicle sizing.

关键词： aircraft Conceptual Design Longitudinal stability control Surfaces Aerodynamic Efficiency Prandtl Glauert Transformation stability Augmentation Systems Space Exploration Horizontal Stabilizers aircraft stability and control Linear Time Invariant System

来源：评论

学校读者我要写书评

暂无评论

Stabilizing a Bio-Inspired Rotating Empennage Fighter aircraft in Multiple Trim Scenarios

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2025年第3期48卷 520-536页

作者： Moulton, Benjamin C. Harris, Matthew W. Hunsaker, Douglas F. Utah State Univ Mech & Aerospace Engn 4130 Old Main Hill Lehi UT 84322 USA

This paper considers the problem of stabilizing a bio-inspired fighter aircraft at its Air Combat Maneuver Condition in steady-level and coordinated-turning flight. The aircraft equations of motion are linearized, and an infinite-horizon linear quadratic regulator design is conducted. The open-loop system is unstable in the short-period and Dutch roll modes. This is mitigated in the closed-loop system, which is analyzed in the time and frequency domains. Included in the simulation dynamics are first-order actuator models, actuator deflection limits, and actuator rate limits. These are particularly important for this bio-inspired aircraft because control actuation requires rotation of the empennage, which has relatively large inertia. Simulation responses to initial condition dispersions, aerodynamic model error, and atmospheric turbulence are analyzed to characterize time-domain properties: settling time, region of attraction, control saturation, and robustness. Due to poor singular values for the throttle setting and rotating tail inputs, analysis is dedicated to control designs with these inputs fixed at trim values. Within the scope of these analyses, fixing the rotating tail at trim does not significantly degrade system performance.

关键词： Fighter aircraft Aileron Actuators aircraft Dynamic Modes Atmospheric Turbulence Bio Inspired aircraft aircraft stability and control Steady Flight Coordinated Flight

来源：评论

学校读者我要写书评

暂无评论

Switched Model-Predictive-control-Based Trajectory Tracking of Fixed-Wing aircraft for Payload Dropping

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2025年第3期48卷 679-688页

作者： Li, Yunpeng Zhang, Lixian Wu, Tong Han, Yuejiang Zhang, Yuxuan Harbin Inst Technol Sch Astronaut Harbin 150001 Peoples R China

来源：评论

学校读者我要写书评

暂无评论

Aerodynamics-Driven Morphing control and Flight Test for Compound Flexible Multibody aircraft

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2025年第5期48卷 991-1003页

作者： Zhu, Entong Zhou, Zhou Wang, Guichen Northwestern Polytech Univ Sch Aeronaut Xian 100065 Shaanxi Peoples R China

The compound multibody aircraft, created through flexible wingtip docking of multiple unit aircraft, not only capitalizes on high aerodynamic efficiency, but also holds the potential for in-flight reconfiguration. This study addresses the challenges of controlling the inherently unstable morphing process through aerodynamic surfaces, eliminating the need for additional driving mechanisms and offering advantages in structural simplicity. In-flight controllable morphing was achieved, significantly elevating the mission flexibility and environmental adaptability of the Compound Flexible Multibody aircraft. A multibody dynamics model with 10 degrees of freedom is developed, and a modified control allocation strategy is proposed to enhance morphing control capability. The control structure placing the configuration controller and the overall attitude controller in parallel is developed to simultaneously guarantee the morphing and trajectory control task. Finally, a successful morphing flight test is implied, in which the configuration commands are determined according to the attainable configuration envelope. This paper presents a control method for compound flexible multibody aircraft that accommodates varying numbers of connections and provides solutions for the stable flight and aerodynamic morphing of such aircraft, expanding their usage and offering insights for the control of more general flexible aircraft.

关键词： Flight Testing control Allocation Multibody Dynamics aircraft stability and control Compound aircraft Morphing aircraft

来源：评论

学校读者我要写书评

暂无评论

stability and control Derivative Estimation for the Bell-Shaped Lift Distribution

Stability and Control Derivative Estimation for the Bell-Sha...

引用

AIAA Science and Technology (SciTech) Forum and Exposition

作者： Newton, Loren J. NASA Armstrong Flight Res Ctr Edwards AFB CA 93523 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

Methodology and results are discussed for flight data analysis of the Prandtl-2 aircraft, a tailless research vehicle designed around an innovative lift distribution. Beyond its greater aerodynamic efficiency than the universally accepted elliptical lift distribution, this "bell-shaped" lift distribution bears significant ramifications upon fundamental aircraft stability and control: an aircraft designed with this lift distribution exhibits proverse yaw, is consequently stable in roll/yaw coupling, and thus does not require an auxiliary yaw control device. Data was collected from a series of flight tests;parameter estimation methods were then applied to determine the characteristic longitudinal and lateral stability and control derivatives of the vehicle. Parameter estimation iteratively tunes estimates of these derivatives such that the difference between a mathematical model of the aircraft's response and its realworld state time histories is minimized. User control over this procedure is focused upon manipulating weights attached to different state variables. Beyond creating scripts to efficiently run the estimation, a method was designed and successfully tested to algorithmically determine these weights to further facilitate the analysis procedure. One derivative's values, indicating yaw moment induced by aileron deflection, is presented as quantitative evidence of proverse yaw. Future development of this work centers on using regression maps of all of the stability and control derivatives to create a dynamic model of the Prandtl-2 vehicle, and in general further analyze the handling idiosyncrasies of such a tailless vehicle with a bell-shaped spanload.

关键词： lift distribution stability derivatives bell-shaped State variable aircraft yawing moments Statistical analysis lateral stability vehicle aircraft stability and control

来源：评论

学校读者我要写书评

暂无评论

Backup Plan Constrained Model Predictive control with Guaranteed stability

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2024年第2期47卷 233-246页

作者： Tao, Ran Kim, Hunmin Yoon, Hyung-Jin Wan, Wenbin Hovakimyan, Naira Sha, Lui Voulgaris, Petros Univ Illinois Dept Mech Sci & Engn Urbana IL 61801 USA Mercer Univ Dept Elect & Comp Engn Macon GA 31207 USA Tennessee Technol Univ Dept Mech Engn Cookeville TN 38505 USA Univ New Mexico Dept Mech Engn Albuquerque NM 87131 USA Univ Illinois Dept Comp Sci Urbana IL 61801 USA Univ Nevada Dept Mech Engn Reno NV 89557 USA

This paper proposes and evaluates a new safety concept called backup plan safety for path planning of autonomous vehicles under mission uncertainty using model predictive control (MPC). Backup plan safety is defined as the ability to complete an alternative mission when the primary mission is aborted. To include this new safety concept in control problems, we formulate a feasibility maximization problem aiming to maximize the feasibility of the primary and alternative missions. The feasibility maximization problem is based on multi-objective MPC, where each objective (cost function) is associated with a different mission and balanced by a weight vector. Furthermore, the feasibility maximization problem incorporates additional control input horizons toward the alternative missions on top of the control input horizon toward the primary mission, denoted as multihorizon inputs, to evaluate the cost for each mission. We develop the backup plan constrained MPC algorithm, which designs the weight vector that ensures asymptotic stability of the closed-loop system, and generates the optimal control input by solving the feasibility maximization problem with computational efficiency. The performance of the proposed algorithm is validated through simulations of an unmanned aerial vehicle path planning problem.

关键词： Stochastic Optimal control Optimal control Problem Unmanned Aerial Vehicle Emergency Landing Autonomous Systems Model Predictive control aircraft stability and control aircraft Safety Mission Abort

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：