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AIAA Aviation Forum

作者： Kelm, Benjamin Myschik, Stephan Niggemann, Oliver Helmut Schmidt Univ Inst Automat Technol Flight Mech & Flight Control Hamburg Germany Univ Bundeswehr Munchen Chair Flight Mech & Flight Control Neubiberg Germany

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Multirotor platforms are increasingly deployed for safety-critical tasks. To increase their safety and availability an automated fault handling is required. For severe faults, a mere fault accommodation with robust or adaptive control architectures is insufficient, requiring a reconfiguration of the controller structure. To make use of the explicit and analytical redundancies of the system in the reconfiguration process, an up-to-date dynamic model of the faulty system is required. In this paper we apply a sparse regression algorithm (SINDYc) to identify the system dynamics of a Redundant Multirotor Testbed (RMT), an octocopter in X8 configuration, to facilitate rapid online control reconfiguration after the sudden loss of one or multiple actuators. The control reconfiguration approach is implemented within a nonlinear simulation in MATLAB/Simulink.

关键词： Multicopter Closed Loop System Identification Unmanned Aerial Vehicle Actuators Simulink Dynamic Modelling Quadcopter flight control Computer Feedback Linearization flight control algorithms

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Increasing Operator Situational Awareness During Transition Procedures for Fixed-Wing VTOL UAV Operations

Increasing Operator Situational Awareness During Transition ...

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AIAA Science and Technology Forum and Exposition (AIAA SciTech Forum)

作者： Dollinger, Daniel Marvakov, Valentin A. Holzapfel, Florian Tech Univ Munich Inst Flight Syst Dynam D-85748 Garching Bavaria Germany

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

Situational awareness towards system automation's behavior in highly automated aircraft is a central requirement as a breakdown in the operator's situational awareness can lead to critical situations and hazardous flight states. In the case of any system failures, the arising decision-making process with faults can be more complex and time critical, hence requires more attention and adequate information representation. This paper implements an operator interaction concept, concerning the Human-Machine-Interface (HMI) to increase situational awareness during transition and re-transition procedures of an unmanned experimental fixed-wing VTOL aircraft. From a human operator point of view, requirements are placed towards the system automation's state observability and proper feedback mechanisms for the state information are selected, comprising intuitive indications. The HMI and operator interaction concept are verified in a closed-loop simulation environment, so called Model-in-the-Loop (MIL), showing that the HMI functions are correctly implemented. For validation purposes, a real-time Hardware-in-the-Loop (HIL) environment is setup. The validation demonstrates that the proposed HMI and operator interaction concept can increase situational awareness during transition procedures for the experimental unmanned fixed-wing VTOL aircraft.

关键词： VTOL Aircraft Closed Loop Propulsion System flight control algorithms Pilot Vertical Take off and Landing flight control System flight Phases Aerodynamic Lift Aircraft Operations

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Takeoff and Landing of a Wing-Tip-Connected Meta Aircraft with Feedback control

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JOURNAL OF AIRCRAFT 2021年第4期58卷 733-742页

作者： Cobar, Maxwell Montalvo, Carlos Univ S Alabama Mobile AL 36688 USA

This paper details the successful takeoff and landing of a wing-tip-connected meta aircraft prototype. The aircraft consisted of two commercial off-the-shelf high wing trainers connected wing tip to wing tip with three neodymium magnets. The flight controller on board each aircraft was a Raspberry Pi 3B complete with Navio2 flight controller. The software running on the aircraft was built using Emlid developer libraries with custom C++ wrappers for the inner-loop control system. The flight control algorithm reads state information and seeks to move the aircraft to a desired attitude depending on pilot inputs. The pilot commands both aircraft, and each flight controller responds independently to these inputs. No communication between aircraft was necessary to ensure stability. Simulation results are included to highlight successful performance of the controller with one aircraft and two connected aircraft.

关键词： Takeoff and Landing Wing Tip Transport Aircraft Pilot control Systems Feedback control flight control algorithms C++ Commercial off the Shelf control Surfaces

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Guidance and control of a Projectile with Reduced Sensor and Actuator Requirements

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JOURNAL OF GUIDANCE control AND DYNAMICS 2011年第6期34卷 1757-1766页

作者： Fresconi, Frank USA Res Lab Precis & Guided Flight Dynam Team Weap & Mat Res Directorate Aberdeen Proving Ground MD 21015 USA

Successfully guiding a projectile launched from a gun is an extremely challenging task. Striking a balance between performance and affordability requires innovative solutions. This paper introduces a unique guidance and control strategy that enables precision and trajectory shaping with reduced Sensor and actuator needs. The derivation of this guidance and control algorithm is based on flight dynamics. flight experiments were conducted to verify that the algorithm guided the projectile to the target and to demonstrate its application to different airframes. Features of the algorithm (such as expected precision, maneuver conservation, and trajectory shaping) were investigated through modeling and simulation. Position bias errors drove the precision;errors due to the guidance and control algorithm were on the order of 0.1 m. An analysis was conducted on the lateral acceleration available from the airframe, lateral acceleration required for this algorithm, and lateral acceleration required for classic proportional navigation. For control-authority-limited munitions proportional navigation was unable to intercept the target point, whereas the current guidance algorithm successfully hit the target. Trajectory shaping with this algorithm is demonstrated through simulation.

关键词： Spin Stabilized Projectiles Actuators Sensors Airframes Algorithm Performance Proportional Navigation flight Dynamics flight control algorithms Angle of Attack GPS

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Guided Entry Performance of Low Ballistic Coefficient Vehicles at Mars

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JOURNAL OF SPACECRAFT AND ROCKETS 2013年第5期50卷 1047-1059页

作者： Meginnis, Ian M. Putnam, Zachary R. Clark, Ian G. Braun, Robert D. Barton, Gregg H. Georgia Inst Technol Daniel Guggenheim Sch Aerosp Engn Atlanta GA 30332 USA Charles Stark Draper Lab Houston TX 77058 USA

Current Mars entry, descent, and landing technology is near its performance limit and may be unable to land payloads on the surface that exceed 1 metric ton. One option for increasing landed payload mass capability is decreasing the entry vehicle's hypersonic ballistic coefficient. A lower ballistic coefficient vehicle decelerates higher in the atmosphere, providing the additional timeline and altitude margin necessary to land more massive payloads. This study analyzed the guided entry performance of several low ballistic coefficient vehicle concepts on Mars. A terminal point controller guidance algorithm, based on the Apollo Final Phase algorithm, was used to provide precision targeting capability. Terminal accuracy, peak deceleration, peak heat rate, and integrated heat load were assessed and compared with a traditional Mars entry vehicle concept to determine the effects of lowering the vehicle ballistic coefficient on entry performance. Results indicate that, while terminal accuracy degrades slightly with decreasing ballistic coefficient, terminal accuracy rivals the performance of current entry systems for ballistic coefficients as low as 1 kg/m(2). These results demonstrate that guided entry vehicles with low ballistic coefficients (large diameters) may be feasible on Mars. Additionally, the flight performance determined by this investigation may be improved through the use of new guidance schemes designed specifically for low ballistic coefficient vehicles, as well as novel terminal descent systems designed around low ballistic coefficient trajectories.

关键词： Ballistic Coefficient flight control algorithms flight Performance Aerodynamic Coefficients Dynamic Pressure flight Path Angle Earth Monte Carlo Simulation Lift to Drag Ratio Angle of Attack

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Vertical Takeoff and Landing of Flexible Wing Kite Power Systems

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JOURNAL OF GUIDANCE control AND DYNAMICS 2018年第11期41卷 2386-2400页

作者： Rapp, Sebastian Schmehl, Roland Delft Univ Technol Fac Aerosp Engn Kluyverweg 1 NL-2629 HS Delft Netherlands

In this work, a novel vertical takeoff and landing methodology for flexible wing kite power systems is presented. Starting from a basic mast-based launching and landing concept, the operational envelope will be enlarged using the external assistance of a multicopter. The multicopter is used to drag the kite along a specified launching path until the operational altitude is reached, where the kite is detached and steered to its characteristic parking position while the multicopter lands. The landing of the kite will be conducted without multicopter assistance, and solely the winch will be used to pull the kite toward the ground station. For all maneuvers, flight control algorithms are presented, and the feasibility of the proposed methodology is analyzed using a developed simulation environment incorporating models for the kite, multicopter, ground station, and the tethers that connect the individual subsystems.

关键词： Flexible Wings Energy Density VTOL Multicopter Ground Station flight control algorithms Aerodynamic Properties Newton's Second Law Angle of Attack Wind Shear

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Guidance, Navigation, and control System Design for Tripropeller Vertical-Takeoff-and-Landing Unmanned Air Vehicle

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JOURNAL OF AIRCRAFT 2009年第6期46卷 1837-1856页

作者： Huang, Rui Liu, Yong Zhu, J. Jim Ohio Univ Sch Elect Engn & Comp Sci Athens OH 45701 USA

In this paper, we present the design and development of the guidance, navigation, and control system of a small vertical-takeoff-and-landing unmanned air vehicle based on a 6 degrees-of freedom nonlinear dynamic model. The vertical-takeoff-and-landing unmanned air vehicle is equipped with three propellers for vertical thrust. and thrust differential together with a set of yaw trim flaps are used for 3 degrees-of-freedom attitude and thrust control actuation. The focus is on the 6 degrees-of-freedom flight control algorithm design using the trajectory linearization control method, along with simulation verification and robustness tests. Hardware and software implementation of the flight controller and onboard navigation sensors are also briefly discussed.

关键词： Guidance, Navigation, and control Systems VTOL Aircraft Vertical Take off and Landing Roll control Reverse Pitch Propellers Position Sensors flight control algorithms Proportional Integral Derivative Attitude control System Euler Angles

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Validating Aircraft Models in the Gap Metric

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JOURNAL OF AIRCRAFT 2014年第6期51卷 1665-1672页

作者： Dorobantu, Andrei Balas, Gary J. Georgiou, Tryphon T. Univ Minnesota Dept Aerosp Engn & Mech Minneapolis MN 55455 USA Univ Minnesota Dept Elect & Comp Engn Minneapolis MN 55455 USA

A framework based on the gap metric is proposed to validate mathematical models of aircraft dynamics using flight data. The approach derives stability margin requirements, and hence is ideally suited to support model-based design and certification of flight control algorithms. This paper shows that the gap metric is an extension of the Theil inequality coefficient: a widely used metric for model validation. The approach is demonstrated on a case study with a small unmanned aircraft.

关键词： Aircrafts flight Data Linear Time Invariant Aircraft Dynamics flight control algorithms Mathematical Models flight Testing Elevator Frequency Domain Unmanned Aircraft System

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