Relevant bibliographies by topics / 090104 Aircraft Performance and Flight Control Systems

Academic literature on the topic '090104 Aircraft Performance and Flight Control Systems'

Author: Grafiati
Published: 10 December 2022
Last updated: 29 January 2023

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Journal articles on the topic "090104 Aircraft Performance and Flight Control Systems"

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Fielding, C., and M. Lodge. "Stability and control of STOVL aircraft: The design of longitudinal flight control laws." Aeronautical Journal 104, no. 1038 (August 2000): 383–89. http://dx.doi.org/10.1017/s0001924000064022.

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Abstract Over the past three decades, the UK aerospace industry has carried out significant research into the development of short take-off and vertical landing (STOVL) technology, to enhance the performance and operation of the Harrier aircraft, and for possible application to future aircraft such as those being developed under the Joint Strike Fighter (JSF) programme. Some of this research has focused on aircraft handling and flight control for the transition between wing-borne and jet-borne flight. Following on from internal research at British Aircraft Corporation/British Aerospace (now part of BAE Systems) in the mid to late 1970s, further development work has been carried out in the 1980s and 90s in support of the UK’s Vectored thrust Advanced Aircraft flight Control (VAAC) Harrier and Integrated Flight and Propulsion Control System (IFPCS) programmes. This paper contains a short review of STOVL aircraft longitudinal flight control law design, and how basic feedback control schemes can be used to influence the aircraft’s response and hence its handling qualities.
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Landy, R. J., W. A. Yonke, and J. F. Stewart. "Development of HIDEC Adaptive Engine Control Systems." Journal of Engineering for Gas Turbines and Power 109, no. 2 (April 1, 1987): 146–51. http://dx.doi.org/10.1115/1.3240017.

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The NASA Ames/Dryden Flight Research Facility is sponsoring a flight research program designated Highly Integrated Digital Electronic Control (HIDEC), whose purpose is to develop integrated flight-propulsion control modes and evaluate their benefits in flight on NASA F-15 test aircraft. The Adaptive Engine Control System (ADECS I) is one phase of the HIDEC program. ADECS I involves uptrimming the P&W Engine Model Derivative (EMD) PW1128 engines to operate at higher engine pressure ratios (EPR) and produce more thrust. In a follow-on phase, called ADECS II, a constant thrust mode will be developed which will significantly reduce turbine operating temperatures and improve thrust specific fuel consumption. A performance seeking control mode is scheduled to be developed. This mode features an onboard model of the engine that will be updated to reflect actual engine performance, accounting for deterioration and manufacturing differences. The onboard engine model, together with inlet and nozzle models, are used to determine optimum control settings for the engine, inlet, and nozzle that will maximize thrust at power settings of intermediate and above and minimize fuel flow at cruise. The HIDEC program phases are described in this paper with particular emphasis on the ADECS I system and its expected performance benefits. The ADECS II and performance seeking control concepts and the plans for implementing these modes in a flight demonstration test aircraft are also described. The potential payoffs for these HIDEC modes as well as other integrated control modes are also discussed.
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Köthe, Alexander, and Robert Luckner. "Applying Eigenstructure Assignment to Inner-Loop Flight Control Laws for a Multibody Aircraft." CEAS Aeronautical Journal 13, no. 1 (December 21, 2021): 33–43. http://dx.doi.org/10.1007/s13272-021-00549-z.

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AbstractUnmanned aircraft used as high-altitude platform system has been studied in research and industry as alternative technologies to satellites. Regarding actual operation and flight performance of such systems, multibody aircraft seems to be a promising aircraft configuration. In terms of flight dynamics, this aircraft strongly differs from classical rigid-body and flexible aircraft, because a strong interference between flight mechanic and formation modes occurs. For unmanned operation in the stratosphere, flight control laws are required. While control theory generally provides a number of approaches, the specific flight physics characteristics can be only partially considered. This paper addresses a flight control law approach based on a physically exact target model of the multibody aircraft dynamics rather than conventionally considering the system dynamics only. In the target model, hypothetical spring and damping elements at the joints are included into the equations of motion to transfer the configuration of a highly flexible multibody aircraft into one similar to a classical rigid-body aircraft. The differences between both types of aircraft are reflected in the eigenvalues and eigenvectors. Using the eigenstructure assignment, the desired damping and stiffness are established by the inner-loop flight control law. In contrast to other methods, this procedure allows a straightforward control law design for a multibody aircraft based on a physical reference model.
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STEPAN, Anca, Georges GHAZI, and Ruxandra Mihaela BOTEZ. "Development of an Adaptive Aero-Propulsive Performance Model in Cruise Flight – Application to the Cessna Citation X." INCAS BULLETIN 14, no. 4 (December 2, 2022): 167–81. http://dx.doi.org/10.13111/2066-8201.2022.14.4.14.

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To accurately predict the amount of fuel needed by an aircraft for a given flight, a performance model must account for engine and airframe degradation. This paper presents a methodology to identify an aero-propulsive model to predict the fuel flow of an aircraft in cruise, while considering initial modeling uncertainties and performance variation over time due to degradation. Starting from performance data obtained from a Research Aircraft Flight Simulator, an initial aero-propulsive model was identified using different estimation methods. The estimation methods studied in this paper were polynomial interpolation, thin-plate splines, and neural networks. The aero-propulsive model was then structured using two lookup tables: one lookup table reflecting the aerodynamic performance, and another table reflecting the propulsive performance. Subsequently, an adaptative technique was developed to locally and then globally, adapt the lookup tables defining the aero-propulsive model using flight data. The methodology was applied to the Cessna Citation X business jet aircraft, for which a highly qualified level D research aircraft flight simulator was available. The results demonstrated that by using the proposed aero-propulsive performance model, it was possible to predict the aerodynamic performance with an average relative error of 0.99%, and the propulsive performance with an average relative error of 3.38%. These results were obtained using the neural network estimation method.
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Tromboni, Pier Domenico, and Giovanni B. Palmerini. "Navigation Aids Performance Evaluation for Precision Approaches." International Journal of Aerospace Engineering 2010 (2010): 1–10. http://dx.doi.org/10.1155/2010/389832.

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The paper deals with the evaluation of the expected performance of aircraft approaches and landings operated with different navigation systems, both traditional and satellite-based. Flight dynamics characteristics and control authority of the approaching aircraft are considered in order to obtain an overall manoeuvre evaluation. The technique from the presented analysis applies to different operative conditions, taking into account aircraft requirements, navigation systems features, and environmental constraints. The aim is to offer a tool to be used in the very preliminary design phase for system performance analysis in different scenarios, such as airport ground systems adoption and air traffic control requirements compliance; later, the same tool can be tuned to complement and direct the required real flight trials to validate an already fielded solution. A numerical code referring to the presented analytical model has been implemented and some applications concerning the system's performance evaluation and planning are proposed to illustrate the algorithm capabilities. The tool and the proposed analysis technique indeed are successful in providing a quantitative assessment of the differences among several possible approaches.
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Lee, A. W., and J. K. Hedrick. "Application of Approximate I/O Linearization to Aircraft Flight Control." Journal of Dynamic Systems, Measurement, and Control 116, no. 3 (September 1, 1994): 429–36. http://dx.doi.org/10.1115/1.2899238.

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This paper examines the performance enhancement of a statically unstable aircraft subject to the input and state constraints. Under control saturation, i/o linearizability is destroyed and the state trajectories may not be attracted to the sliding surface. If the reference signals are sufficiently large and the zero-dynamics is lightly damped, the i/o linearizing control may become unreasonably large in magnitude, making the closed-loop system susceptible to the damaging effects of control saturation. In addition to performance degradations such as increased tracking errors, control saturation can drive the closed-loop system to instability. In this paper, a new design method called approximate i/o linearization is presented to enhance the performance of the SISO longitudinal flight control problem under saturation. The new approximate i/o linearization law is obtained by solving a pointwise minimization problem. The function to be minimized consists of a surface whose relative degree is one, its derivative, and weighted square of the input u. The advantages of the approximate i/o linearization is that the adverse effects of control saturation can be minimized by properly selecting the weight on the usage of the control. The only requirement for the new technique is that the original plant be locally i/o linearizable. Thus approximate i/o linearization does not impose additional strict requirements on the plant. In the remaining sections of the paper, stability and bounded tracking properties of the approximate i/o linearization are proven. Finally, a longitudinal flight control problem is used to demonstrate the application of approximate i/o linearization.
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Ray, A., and J. Caplin. "Life extending control of aircraft: trade-off between flight performance and structural durability." Aeronautical Journal 104, no. 1039 (September 2000): 397–408. http://dx.doi.org/10.1017/s0001924000091843.

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Abstract The goal of life extending control (LEC) is to enhance the service life of complex mechanical systems, such as aircraft, spacecraft, and energy conversion devices, without any significant loss of performance, and can be achieved by making a trade-off between dynamic performance and structural durability. This paper presents the concept and a design methodology for robust life extending control of aircraft structures that are typically subjected to cyclic mechanical stresses. The controller design procedure relies on the specifications of flight performance and allowable fatigue crack damage at critical points of aircraft structures that serve as indicators of the effective service life. As an example, an aeroelastic model of the aircraft wings has been formulated and is incorporated into a nonlinear rigid-body model of the flight-dynamics. The H∞-based structured singular value (μ) synthesis method has been used to design robust life extending controllers based on a linearised model of the aircraft and a (nonlinear) state-space model of fatigue crack growth. The results of simulation experiments show significant savings in fatigue life of the wings while retaining the dynamic performance of the aircraft.
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Iyaghigba, Samuel David, Fakhre Ali, and Ian K. Jennions. "A Review of Diagnostic Methods for Hydraulically Powered Flight Control Actuation Systems." Machines 11, no. 2 (January 25, 2023): 165. http://dx.doi.org/10.3390/machines11020165.

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Aircraft systems are designed to perform functions that will aid the various missions of the aircraft. Their performance, when subjected to an unfamiliar condition of operation, imposes stress on them. The system components experience degradation due to fault which ultimately results in failure. Maintenance and monitoring mechanisms are put in place to ensure these systems are readily available when required. Thus, the sensing of parameters assists in providing conditions under which healthy and faulty scenarios can be indicated. To obtain parameter values, sensor data is processed, and the results are displayed so that the presence of faults may be known. Some faults are intermittent and incipient in nature. These are not discovered easily and can only be known through a display of unusual system performance by error code indication. Therefore, the assessed faults are transmitted to a maintenance crew by error codes. The results may be fault found (FF), no fault found (NFF), or cannot display (CND). However, the main classification of the faults and their origins may not be known in the system. This continues throughout the life cycle of the system or equipment. This paper reviews the diagnostic methods used for the hydraulically powered flight control actuation system (HPFCAS) of an aircraft and its interaction with other aircraft systems. The complexities of the subsystem’s integration are discussed, and different subsystems are identified. Approaches used for the diagnostics of faults, such as model-based, statistical mapping and classification, the use of algorithms, as well as parity checks are reviewed. These are integrated vehicle health management (IVHM) tools for systems diagnostics. The review shows that when a system is made up of several subsystems on the aircraft with dissimilar functions, the probability of fault existing in the system increases, as the subsystems are interconnected for resource sharing, space, and weight savings. Additionally, this review demonstrates that data-driven approaches for the fault diagnostics of components are good. However, they require large amounts of data for feature extraction. For a system such as the HPFCAS, flight-management data or aircraft maintenance records hold information on performance, health monitoring, diagnostics, and time scales during operation. These are needed for analysis. Here, a knowledge of training algorithms is used to interpret different fault scenarios from the record. Thus, such specific data are not readily available for use in a data-driven approach, since manufacturers, producers, and the end users of the system components or equipment do not readily distribute these verifiable data. This makes it difficult to perform diagnostics using a data-driven approach. In conclusion, this paper exposes the areas of interest, which constitute opportunities and challenges in the diagnostics and health monitoring of flight-control actuation systems on aircraft.
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Shim, Jong-Ik. "Improving Aircraft Database Performance for Flight Simulator." International Review of Aerospace Engineering (IREASE) 14, no. 1 (February 28, 2021): 28. http://dx.doi.org/10.15866/irease.v14i1.19310.

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Huang, Min, Zhong-wei Wang, Xing-Bao Yang, Zhen-yun Guo, and Yao-bin Niu. "Preliminary Validation of the Wind Tunnel Based Flight Control System Evaluation Method." MATEC Web of Conferences 179 (2018): 03021. http://dx.doi.org/10.1051/matecconf/201817903021.

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As mathematical models of aircraft aerodynamics and rudder loadings always have to be built in the hardware-in-the-loop simulation, wind tunnel based flight control system (FCS) evaluation methods were proposed in order to test and evaluate the flight control systems under real aerodynamic and rudder loading environment. To validate the evaluation method, a wind tunnel based flight control system test was performed in a hypersonic wind tunnel facility. As the aircraft support rig in the wind tunnel is static, the aircraft angle of attack cannot be changed in this test. During the test, the elevator response, the lift force and the pitching moment were measured. By analysing the measured data, the elevator control performance of the pitch control system was determined, and the pitch angle was successfully predicted, but the open-loop pitch control performance was not determined. These results validate the feasibility of evaluating the elevator control performance and predicting the pitch angle of a FCS by the wind tunnel based FCS evaluation method.
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Dissertations / Theses on the topic "090104 Aircraft Performance and Flight Control Systems"

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Collins, David C. (David Charles) 1969. "Adaptive model reference control of highly maneuverable high performance aircraft." Thesis, 1993. http://hdl.handle.net/1957/37416.

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This thesis presents an adaptive model reference controller for a highly maneuverable high performance aircraft, in particular, a modified F18. An adaptive controller is developed to maneuver an aircraft at a high angle of attack. Thus, the aircraft is required to fly over a highly nonlinear flight regime. The adaptive controller presented in this thesis can be viewed as a combination of a linear and a nonlinear controller. Around a fixed flight condition the adaptive controller converges to a linear controller; however, the controller remains a nonlinear controller during maneuvers. The contributions of this thesis lie in two areas. The first area is in control. A successful application of linear adaptive control is presented for a highly nonlinear system. A new method is used to generate the reference trajectory. The reference model uses output feedback to improve the reference trajectory. It is shown that this improvement is necessary because of the control limitations. This work is also important to the control of highly maneuverable high performance aircraft. A successful adaptive controller has been developed to rapidly maneuver an aircraft to a high angle of attack. The main focus of this thesis is adaptive control.
Graduation date: 1993
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(9762536), Shupeng Liu. "Sustainable Autonomous Solar UAV with Distributed Propulsion System." Thesis, 2021.

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Solar-powered Unmanned Aerial Vehicles (UAVs) solve the problem of loiter time as aircrafts can fly as long as sufficient illumination and reserve battery power is available. However, Solar-powered UAVs still face the problem of excessive wingspan to increase solar capture area, which detracts from maneuverability and portability. As a result, a feature of merit for solar UAVs has emerged that strives to reduce the wingspan of such UAVs. The purpose of this project is to improve energy use efficiency by applying a distributed propulsion system to reduce the wingspan of solar-powered UAVs and increase payload. The research focuses on optimizing a new design analysis method applied to the distributed propulsion system and further employs the novel application of solar arrays on both top and bottom of the wings. The design methodology will result in a 2.1-meter wingspan, which is the shortest at 2020, for a 24-hour duration solar-powered UAV.


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(8063924), Austin L. Nash. "Hierarchical Combined Plant and Control Design for Thermal Management Systems." Thesis, 2019.

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Over the last few decades, many factors, including increased electrification, have led to a critical need for fast and efficient transient cooling. Thermal management systems (TMSs) are typically designed using steady-state assumptions and to accommodate the most extreme operating conditions that could be encountered, such as maximum expected heat loads. Unfortunately, by designing systems in this manner, closed-loop transient performance is neglected and often constrained. If not constrained, conventional design approaches result in oversized systems that are less efficient under nominal operation. Therefore, it is imperative that \emph{transient} component modeling and subsystem interactions be considered at the design stage to avoid costly future redesigns. Simply put, as technological advances create the need for rapid transient cooling, a new design paradigm is needed to realize next generation systems to meet these demands.

In this thesis, I develop a new design approach for TMSs called hierarchical control co-design (HCCD). More specifically, I develop a HCCD algorithm aimed at optimizing high-fidelity design and control for a TMS across a system hierarchy. This is accomplished in part by integrating system level (SL) CCD with detailed component level (CL) design optimization. The lower-fidelity SL CCD algorithm incorporates feedback control into the design of a TMS to ensure controllability and robust transient response to exogenous disturbances, and the higher-fidelity CL design optimization algorithms provide a way of designing detailed components to achieve the desired performance needed at the SL. Key specifications are passed back and forth between levels of the hierarchy at each iteration to converge on an optimal design that is responsive to desired objectives at each level. The resulting HCCD algorithm permits the design and control of a TMS that is not only optimized for steady-state efficiency, but that can be designed for robustness to transient disturbances while achieving said disturbance rejection with minimal compromise to system efficiency. Several case studies are used to demonstrate the utility of the algorithm in designing systems with different objectives. Additionally, high-fidelity thermal modeling software is used to validate a solution to the proposed model-based design process.
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Books on the topic "090104 Aircraft Performance and Flight Control Systems"

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Navarro, Robert. Performance of an electro-hydrostatic actuator on the F-18 systems research aircraft. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1997.

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Navarro, Robert. Performance of an electro-hydrostatic actuator on the F-18 systems research aircraft. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1997.

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Murphy, Patrick C. Closed-loop system identification experience for flight control law and flying qualities evaluation of a high performance fighter aircraft. [Washington, D.C: National Aeronautics and Space Administration, 1996.

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C, Murphy Patrick. Closed-loop system identification experience for flight control law and flying qualities evaluation of a high performance fighter aircraft. [Washington, D.C: National Aeronautics and Space Administration, 1996.

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C, Murphy Patrick. Closed-loop system identification experience for flight control law and flying qualities evaluation of a high performance fighter aircraft. [Washington, D.C: National Aeronautics and Space Administration, 1996.

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Franklin, James A. Moving-base simulation evaluation of control/display integration issues for ASTOVL aircraft. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1997.

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Franklin, James A. Moving-base simulation evaluation of control/display integration issues for ASTOVL aircraft. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1997.

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Franklin, James A. Moving-base simulation evaluation of control/display integration issues for ASTOVL aircraft. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1997.

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Schmidt, D. K. Cooperative control theory and integrated flight and propulsion control: Final technical report for grant NAG3-575 covering the period 1994-1995. College Park, Md: Dept. of Aerospace Engineering, University of Maryland, 1995.

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Maine, Trindel A. A preliminary evaluation of an F100 engine parameter estimation process using flight data. Moffett Field, Calif: Ames Research Center, 1990.

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Book chapters on the topic "090104 Aircraft Performance and Flight Control Systems"

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Kemer, Emre, Hasan Başak, and Hayri Baytan Özmen. "Performance Improvement for Fighter Aircraft Using Fuzzy Switching LQI Controller." In Fuzzy Control Systems [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.107032.

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In this work, a switching linear quadratic integral (LQI) controller based on fuzzy logic is designed for the load-factor tracking problem of high-performance aircraft referred to as the Aero-Data Model in Research Environment (ADMIRE). ADMIRE is a new generation aircraft and has a wide flight operation envelope in terms of altitude and speed. Hence, it is difficult to design a flight controller to achieve a high tracking performance. First, the LQI controller is selected due to good tracking performance and robustness in the model dynamics. Combining switching LQI controller and fuzzy logic improves the transient performance of the closed-loop switched system. The results obtained with the fuzzy switching controller have been compared with the conventional LQI and the switching LQI in terms of robust demand tracking. The simulation results have demonstrated that the fuzzy switching controller is superior to the conventional LQI and switching LQI controllers due to better transient performance and robust stability.
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Conference papers on the topic "090104 Aircraft Performance and Flight Control Systems"

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CHIN, J., V. CHACON, and J. GERA. "X-29A flight control system performance during flight test." In Aircraft Design, Systems and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2878.

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Rice, Caleb, Yu Gu, Haiyang Chao, Trenton Larrabee, Srikanth Gururajan, Marcello Napolitano, Tanmay Mandal, and Matthew Rhudy. "Control performance analysis for autonomous close formation flight experiments." In 2014 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2014. http://dx.doi.org/10.1109/icuas.2014.6842372.

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Kim, Hyeongseok, Daejin Lim, and Kwanjung Yee. "Flight Control Simulation and Battery Performance Analysis of a Quadrotor under Wind Gust." In 2020 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2020. http://dx.doi.org/10.1109/icuas48674.2020.9214058.

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PORTER, B., A. MANGANAS, and T. MANGANAS. "Design of digital model-following flight-mode control systems for high-performance aircraft." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4116.

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Hair, Kenneth A. "Development of Fluidic Flight Control and Actuation Systems for High Performance Aircraft." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/871875.

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PORTER, B., and M. OTHMAN. "Design of adaptive digital model-following flight-mode control systems for high-performance aircraft." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-3495.

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Wu, Falin, Jiaqi He, Guopeng Zhou, Haolun Li, and Yushuang Liu. "Performance of Sliding Mode and Consensus-based Control Approaches for Quadrotor Leader-Follower Formation Flight." In 2021 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2021. http://dx.doi.org/10.1109/icuas51884.2021.9476782.

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"Synthesis of a reduced order model and design of a multivariable flight control system for a high performance helicopter." In Aircraft Design, Systems and Operations Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4501.

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PORTER, B., and T. MANGANAS. "Design of fast non-interacting digital flight-mode control systems for high-performance aircraft." In 7th Computational Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1903.

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Moguel, Israel, Hever Moncayo, Andres Perez, Mario Perhinschi, Dia Al Azzawi, and Adil Togayev. "Bio-Inspired Approach for Aircraft Health Assessment and Flight Envelope Estimation." In ASME 2014 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/dscc2014-5885.

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Based on the artificial immune system paradigm and a hierarchical multi-self strategy, a set of algorithms for aircraft sub-systems failure detection, identification, evaluation and flight envelope estimation have been developed and implemented. Data from a six degrees-of-freedom flight simulator were used to define a large set of 2-dimensional self/non-self projections as well as for the generation of antibodies and identifiers designated for health assessment of an aircraft under upset conditions. The methodology presented in this paper classifies and quantifies the type and severity of a broad number of aircraft actuators, sensors, engine and structural component failures. In addition, the impact of these upset conditions on the flight envelope is estimated using nominal test data. Based on immune negative and positive selection mechanisms, a heuristic selection of sub-selves and the formulation of a mapping-based algorithm capable of selectively capturing the dynamic fingerprint of upset conditions is implemented. The performance of the approach is assessed in terms of detection and identification rates, false alarms, and correct prediction of flight envelope reduction with respect to specific states.
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