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Sparse Flow Sensor Placement Optimization for Flight-by-Feel Control of 2D Airfoils

AIAA JOURNAL 2024年第10期62卷 3803-3812页

作者： Hollenbeck, Alex C. Grandhi, Ramana Hansen, John H. Pankonien, Alexander M. US Air Force Dept Aeronaut & Astronaut Inst Technol Wright Patterson AFB OH 45433 USA US Air Force Aerosp Syst Directorate Res Lab Wright Patterson AFB OH 45433 USA

This research introduces the Sparse Sensor Placement Optimization for Prediction algorithm and explores its use in bioinspired flight-by-feel control system design. Flying animals have velocity-sensing structures on their wings and are capable of highly agile flight in unsteady conditions, a proof-of-concept that artificial flight-by-feel control systems may be effective. Constrained by size, weight, and power, a flight-by-feel sensory system should have the fewest optimally placed sensors which capture enough information to predict the flight state. Flow datasets, such as from computational fluid dynamics, are discrete, often highly discontinuous, and ill-suited for conventional sensor placement optimization techniques. The data-driven Sparse Sensor Placement Optimization for Prediction approach reduces high-dimensional flow data to a low-dimensional sparse approximation containing nearly all of the original information, thereby identifying a near-optimal placement for any number of sensors. For two or more airflow velocity magnitude sensors, this algorithm finds a placement solution (design point) which predicts angle of attack of airfoils to within 0.10 degrees and ranks within the top 1% of all possible design points validated by combinatorial search. The scalability and adaptability of this algorithm is demonstrated on several 2D model variations in clean and noisy data, and model sensitivities are evaluated and compared against conventional optimization techniques. Applications for this sensor placement algorithm are explored for aircraft design, flight control, and beyond.

关键词： Tactile Sensors Aircraft Flight Control System Aerodynamic Performance Control System Design Aircraft Design Computational Fluid Dynamics algorithms and data structures Optimization Algorithm Bio Inspired Aircraft

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Fluid-Structure Interactions of a Fin over a Compliant Panel in Supersonic Flow

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AIAA JOURNAL 2024年第12期62卷 4574-4588页

作者： Mills, John G. Dutton, J. Craig Ehrhardt, David A. Elliott, Greg Univ Illinois 104 S Wright St Urbana IL 61801 USA

The fluid-structure interactions of a blunt fin mounted over a compliant panel in Mach 2 flow were investigated. The test geometry consisted of a thin, flexible panel fixed on all edges with a blunt fin with a hemispherically rounded leading edge mounted in a manner that the leading edge of the fin overhung the panel. The blunt fin was also pivoted to several angles of attack with respect to the oncoming flow. This allowed for the study of the dynamic system created by the interactions between the compliant panel and the blunt fin geometries. Both rigid and compliant panel models were used in order to provide a comparison between the flow with and without the dynamics of the compliant panel. High-speed schlieren and surface oil flow visualizations showed that the time-averaged flow remained almost entirely unchanged between the rigid and compliant panels. The instantaneous flow fields, however, showed a highly dynamic system where the compliant panel induced oscillatory shock waves that were both stationary and freely moving. Simultaneous high-speed schlieren visualization and stereo digital-image correlation showed a strong linkage between the motion of the shock waves and the deformation of the panel. This was demonstrated through frequency analysis and modal decomposition of the panel deformation and shock motions.

关键词： Fluid Structure Interaction Separated Flows Shock Waves Unsteady Reynolds Averaged Navier Stokes Structural Kinematics and Dynamics algorithms and data structures Wind Tunnel Tests Dynamic Fluid Structure Interaction Supersonic Flow over a Flat Plate Shock Wave Interaction

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Numerical Investigation of the Dynamic Instability of a Reentry Capsule in Transonic Flow

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AIAA JOURNAL 2024年第2期62卷 449-459页

作者： Han, Seoeum Lee, Bok Jik Furudate, Michiko Ahn Nagai, Hiroki Seoul Natl Univ Dept Aerosp Engn Seoul 08826 South Korea Chungnam Natl Univ Dept Mechatron Engn Daejeon 34134 South Korea Tohoku Univ Dept Aerosp Engn Sendai Miyagi 9808579 Japan

This study presents a numerical investigation of transonic flow characteristics over a reentry capsule at Mach 1.05, employing a detached eddy simulation. The simulated flowfields demonstrate that the recompression shock wave oscillates back and forth at a Strouhal number of the order of 0.01. Frequency analysis of fluctuations in the drag coefficient and base pressure reveals that these fluctuations can be predominantly attributed to oscillations in the recompression shock wave. While the recompression shock wave propagates upstream, local shock waves occur alternately in the upper and lower free-shear layers, with a Strouhal number of the order 0.1, due to the instability of free-shear layers. The repeated occurrence of these local shock waves causes the recirculation region to shrink, resulting in a decrease in the base pressure. Conversely, while the recompression shock wave propagates downstream, no local shock wave occurs and the recirculation region expands, leading to an increase in the base pressure. These results suggest that the interactions among the recompression shock wave, local shock wave, and free shear layer give rise to fluctuations in the base pressure of the capsule, which in turn can affect its dynamic instability.

关键词： Numerical Investigation Compressible Flow Shock Waves Boundary Layers Strouhal Number Freestream Conditions Improved Delayed Detached Eddy Simulation Fluid Flow Properties algorithms and data structures Reynolds Averaged Navier Stokes

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Unified Control of Flight Dynamics and Actuators Using Local Accelerations

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2024年第9期47卷 1920-1938页

作者： Meyer-Bruegel, Wolfram Silvestre, Flavio J. Tech Univ Berlin Chair Flight Mech Flight Control & Aeroelast Marchstr 12 D-10587 Berlin Germany

Control surface actuators usually come with their own servo control algorithm, which ensures that the deflection commanded by the flight control laws is quickly achieved. Therefore, flight control and servo control together form a cascaded control structure. Traditionally, the flight control laws (outer loop) and servo control laws (inner loop) are designed independently. However, recent applications demand an increasingly dynamic design of flight control, with actuator dynamics becoming a limiting factor. In this paper, a unified control design for actuators and flight dynamics is investigated. The local acceleration at the lifting surface (empennages and wing), close to the actuator, is fed back within an inner actuator control loop, allowing for faster compensation. The theoretical properties of the suggested control structure are discussed analytically first. Later, the concept is applied to a linear model for longitudinal aircraft motion. A classical state controller serves as a reference for comparison of the proposed strategy against the standard one with the actuator internal control law. Both controllers are designed using eigenstructure assignment, and the pole locations are numerically optimized. The closed-loop behavior is assessed in the time and frequency domains. The results promise significant improvements in terms of disturbance rejection and robustness.

关键词： Flight Path Angle Actuators Aircraft Flight Control System Closed Loop Transfer Function algorithms and data structures Flight Control Law Signal Processing Aircraft Components and Structure Flight Control Surfaces Aerodynamic Coefficients

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Numerical Investigations on Phase Cancelation of Interaction Noise for Counter-Rotating Propellers

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AIAA JOURNAL 2024年第5期62卷 1826-1839页

作者： Lyu, Changhao Liu, Peiqing Hu, Tianxiang Qu, Qiulin Geng, Xin Sun, Tao Guo, Hao Akkermans, Rinie A. D. Beihang Univ Sch Aeronaut Sci & Engn Key Lab Aeroacoust Minist Ind & Informat TechnolLu Shijia Lab Beijing 100191 Peoples R China Beihang Univ Sch Aeronaut Sci & Engn Key Lab Fluid Mech Minist Educ Beijing 100191 Peoples R China Hamburg Univ Appl Sci Dept Automot & Aeronaut Engn D-20099 Hamburg Germany

The large interaction tonal noise of counter-rotating propellers significantly restricts their application in civil aviation. A pair of counter-rotating propellers was simulated by the lattice Boltzmann method, and the far-field noise was predicted by the Ffowcs Williams and Hawkings analogy. Dynamic mode decomposition was introduced to analyze the surface pressure contribution to far-field noise and to provide insights on the cancellation mechanism of the noise source distribution for the interaction tone. It was found that the cancellation effect is closely related to the relative position between the front blade wake and rear blade element. By adjusting the rear blade sweep and, hence, changing the relative position, the interaction tone can be reduced effectively.

关键词： Counter Rotating Propellers algorithms and data structures Thermal Lattice Boltzmann Method Civil Aviation Vortex Dynamics Overall Sound Pressure Level Frequency Domain Beamforming Aerodynamic Center Tracking and Positioning Systems China Aerodynamics Research and Development Center

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Cooperative Enclosing Control for Networked Unmanned Aerial Vehicles to Faster Target

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2024年第2期47卷 366-374页

作者： Chen, Lin Duan, Haibin Beihang Univ Sch Autonomous Sci & Elect Engn Beijing 100083 Peoples R China

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data-Driven Control-Oriented Modeling for Response of Fluidic Thrust Vectoring

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AIAA JOURNAL 2024年第10期62卷 3789-3802页

作者： Zhou, Kaiwen Cheng, Changming Wen, Xin Shanghai Jiao Tong Univ Gas Turbine Res Inst Sch Mech Engn Key Lab Educ Minist Power Machinery & Engn 800 Dongchuan Rd Shanghai 200240 Peoples R China

Response to control input is of significance to the application of real-time active flow control (AFC). In this paper, a novel data-driven framework is used to discover the underlying physics of the dynamic response process of fluidic thrust vectoring (FTV), a typical application of AFC. In the proposed framework, sparse identification of a nonlinear dynamics (SINDy) algorithm is used to identify the governing equations of the flow control responses of sets of noisy measurement data. The clustering algorithm is then used to seek the generalized coefficients of basis functions for different sets of data, which improve the robustness of the model to noisy measurement data. First, a simulated mechanical system is used to validate the effect of the framework. To simplify the modeling, control performance and characteristics are investigated in a detailed manner. Then a dimensionless parameter Delta Cp based on the pressure coefficient is found to exhibit a linear relationship with the vector angle under different working conditions. This parameter is introduced in the proposed framework to model the dynamic process of response to control input. The obtained governing equations can describe the dynamic process accurately based on the validation of testing data. The form of the governing equation is rewritten and analyzed based on the control theory, revealing the physics of this process, which is significant to practical AFC implementation.

关键词： Active Flow Control State Estimation algorithms and data structures Fluid Dynamics

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Low-Thrust Trajectory Optimization with Averaged Dynamics Using Analytical Switching Detection

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2024年第6期47卷 1135-1149页

作者： Wu, Di Cheng, Lin Gong, Shengping Baoyin, Hexi Tsinghua Univ Sch Aerosp Engn Beijing 100084 Peoples R China Beihang Univ Sch Astronaut Beihang 102206 Peoples R China

This paper presents an efficient indirect optimization method for the time- and fuel-optimal low-thrust many-revolution transfers with averaged dynamics. Compared with the previous indirect method, the proposed method involves a new set of variables and several near-optimal control laws to formulate the two-point boundary value problem based on three practical assumptions. Then, the costate transformations between two reference frames are first derived with respect to the the corresponding Eulerian angles, such that the switching function can be expressed with a six-degree polynomial function and the number of parameters used to determine the energy-optimal solutions is reduced to 6. Finally, a neural network is trained to generated the initial guesses, and the solution algorithms for solving the time- and fuel-optimal problem are formulated. Numerical simulations demonstrate that the convergence ratio of initial guesses is higher than 98%, the proposed assumptions are reasonable for guaranteeing the near optimality, and the presented method can obtain convergent solutions within tenths of a second for the Earth- and moon-centered external/interior transfers considering the shadow J2 and third-body perturbations.

关键词： Pontryagin's Maximum Principle Solar System Moons Planets algorithms and data structures Artificial Neural Network Boundary Element Method Numerical Simulation Optimization Algorithm Propellant Geostationary Transfer Orbit

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Online Identification and Detection of Manual Control Adaptation with Recursive Time Series

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2025年第5期48卷 1112-1123页

作者： Plaetinck, Wouter Pool, Daan M. van Paassen, Marinus M. Mulder, Max Delft Univ Technol Fac Aerosp Engn NL-2600 GB Delft Netherlands Delft Univ Technol Fac Aerosp Engn Control & Simulat NL-2600 GB Delft Netherlands

An online pilot manual control behavior identification method, based on recursive low-order time-series model estimation, is presented and validated using experimental data. Eight participants performed compensatory tracking tasks with time-varying vehicle dynamics, where, at an unpredictable moment during a run, a sudden degradation in dynamics could occur. They were instructed to push a button when they detected a change in dynamics. Two methods to automatically detect the moment when pilot adaptation occurs from online estimated parameter traces are discussed. Results show that pilots are more accurate in detecting changes than either algorithm. But when the algorithms are correct, they are often quicker to detect pilot adaptation than pilots themselves. The presented techniques have potential but need improvements.

关键词： Describing Function Human Machine Interaction algorithms and data structures

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Angles-Only Cooperative Local Catalog Maintenance of Close-Proximity Satellite Systems

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2024年第12期47卷 2573-2586页

作者： Hays, Christopher W. Henderson, Troy Miller, Kristina Phillips, Sean Soderlund, Alexander Embry Riddle Aeronaut Univ Aerosp Engn Dept 1 Aerosp Blvd Daytona Beach FL 32114 USA Univ Illinois Elect & Comp Engn Dept 1308 W Main St Urbana Urbana IL 61801 USA USAF Res Lab Space Control Branch Kirtland AFB NM 87123 USA

In space mission sets like on-orbit servicing and manufacturing, agents in close proximity may operate too close to yield resolved localization solutions to operators. This requires that the system maintain a catalog of its local neighborhood;however, this imposes a large burden on each agent to update its catalog. This paper considers the case of multiple satellites each maintaining their catalog. Specifically, this paper considers the case of numerous noncooperative objects and a collection of agents operating in the same local environment. The goal of each agent is to maintain their catalog of all bodies (objects and agents) within this neighborhood through onboard angles-only measurements and cooperative communication with the other agents. A central supervisor selects the target body for each agent, a local controller tracks the selected target body for each agent, and a local estimator coalesces both an agent's measurements and state estimates provided by neighboring agents within the communication graph. Numerical results are provided to demonstrate the supervisor's ability to select an appropriate target subject to an uncertainty threshold, the controller's ability to track the selected target, and the estimator's ability to maintain an accurate and precise estimate of each of the bodies in the local environment.

关键词： Linear Time Invariant System algorithms and data structures Collaborative Decision Making Extended Kalman Filter State Estimation Distributed Control System Spacecraft Autonomous Operations Spacecraft Attitude Control Spacecraft Guidance and Control Autonomous Formation Flying System

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