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AIAA Aviation Forum

作者： Hofsaess, Hannes Braunt, David Holzapfel, Florian Tech Univ Munich Inst Flight Syst Dynam D-85748 Garching Germany

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Traditional certification approaches for flight control software aim at maximizing the confidence that all design errors have been removed during design time. For the certification of novel and complex flight control laws, however, this approach becomes increasingly difficult. An alternative approach is to ensure safety of flight through online monitoring of the aircraft when controlled by the complex law. The monitor switches command authority to a backup controller if the complex law has failed to respond to its inputs in a safe way. This work constitutes the first step for the design and validation of a monitoring function that evaluates the command outputs of the nominal controller with respect to its dynamic response requirements and the hazards for system safety. Thereby, we focus on the backup controllers capability of preserving safety after it is engaged by the monitoring function. We present a structured approach for approximation of the backup controllers safety set that bases on flight-physical assessment of the considered hazard for safety and incorporates set-based maneuverability requirements of the nominal controller. Furthermore, we suggest a counter optimization-based worst-case validation procedure that can be used early in the system development phase to assess the monitoring system and thereby validate the performance of the nominal controller in the presence of safety constraints. Finally, we present validation results for a high-fidelity use-case considering the system dynamics of a vertical take off and landing aircraft in hover flight.

关键词： integrated flight control system flight control Law Vertical Take off and Landing Closed Loop system Optimization Method flight Dynamic Analysis Transport Aircraft Yaw flight Envelope Protection Handling Qualities

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X-31A system identification using single-surface excitation at high angles of attack

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JOURNAL OF AIRCRAFT 1996年第3期33卷 485-490页

作者： Weiss, S Friehmelt, H Plaetschke, E Rohlf, D DLR German Aerospace Research Establishment D-38022 Brunswick Germany

Parameter identification of the X-31A experimental aircraft was conducted throughout the envelope expansion using mainly pilot input maneuvers, The quality of the identification results, especially in the high-angle-of-attack regime, suffered from high correlations between the aircraft controls and states as well as from insufficient sideslip excitation. These problems are caused by the high feedback gains used in the flight control system to control the basically unstable airplane, Therefore, in 1994-1995 a dedicated Right test program using single surface excitation for parameter identification at high angles of attack was conducted, The results prove that identification of highly augmented aircraft benefits considerably from this technique, This article presents the realization of the single-surface excitation using the X-31A flutter test box, Also, the Eight test program, the applied evaluation methods, and the identification models are discussed. Selected identification results from the single-surface excitation tests are presented and compared to those obtained from the pilot input maneuvers.

关键词： Angle of Attack system Identification Pilot flight Test Programme integrated flight control system Angle of Sideslip Experimental Aircraft Aircraft control control Surfaces Trailing Edge Flap

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Rotor-State Feedback control to Alleviate Pilot Workload for Helicopter Shipboard Operations

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JOURNAL OF GUIDANCE control AND DYNAMICS 2017年第12期40卷 3088-3099页

作者： Ji, Honglei Chen, Renliang Li, Pan Nanjing Univ Aeronaut & Astronaut Natl Key Lab Sci & Technol Rotorcraft Aeromech Nanjing 210016 Jiangsu Peoples R China

This paper presents an integrated flight control system with rotor-state feedback for helicopter approaching to the ship deck. First, a high-order nonlinear flight dynamics model coupled with the reconstructed ship airwake turbulence is developed. Then, a rotor-state feedback control law is developed and integrated into the baseline explicit model-following control system to form an integrated control system. The feedback gains of body and rotor states are designed together to improve the disturbance rejection over the ship airwake frequencies (1 to 12 rad/s). A feedforward compensator is introduced to improve aircraft response bandwidth. Furthermore, a method to adjust the command model is developed for further improvement of the response bandwidth. Finally, the effectiveness of the integrated control system is demonstrated with linear analysis, and pilot workload is evaluated with nonlinear simulation. In comparison to the baseline control system, the integrated control system improves both the disturbance rejection over the ship airwake frequencies and attitude response bandwidths of rolling and pitching motions. The pilot workload for the roll and pitch attitude regulation in ship airwake turbulence is reduced by 45 and 26%, respectively.

关键词： Helicopter Shipboard Operations Pilot Rotor State Feedback control systems Closed Loop Transfer Function integrated flight control system flight Dynamics Freestream Conditions Flap Angle Feedback Loop

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integrated guidance and control of moving-mass actuated kinetic warheads

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JOURNAL OF GUIDANCE control AND DYNAMICS 2004年第1期27卷 118-126页

作者： Menon, PK Sweriduk, GD Ohlmeyer, EJ Malyevac, DS Optimal Synth Inc Palo Alto CA 94303 USA USN Ctr Surface Warfare Missile Syst Div Dahlgren VA 22448 USA

Modeling, simulation, and integrated guidance control of a kinetic warhead utilizing moving-mass actuators are discussed. Moving masses can be used in any speed range both in the atmosphere as well as outside it, as long as there is a force, either aerodynamic or propulsive, acting on the vehicle. The moving-mass actuation technique offers significant advantages over conventional aerodynamic control surfaces and reaction-control systems because the actuators are contained entirely within the airframe geometric envelope and produce no plumes. The present research develops a nine-degree-of-freedom simulation model of a kinetic warhead with three moving-mass actuators. This simulation model is used for actuator sizing and in the development of flight-control systems. A software package for performing numerical feedback linearization is employed for the design of nonlinear flight control systems. Interception of nonmaneuvering and weaving targets in both endoatmospheric and exoatmospheric conditions is demonstrated.

关键词： Warheads integrated flight control system Actuators Feedback Linearization control Surfaces Reaction control system Airframes Angle of Attack Aerodynamic Coefficients Autopilot

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DESIGN OF A TOTAL ENERGY control AUTOPILOT USING CONSTRAINED PARAMETER OPTIMIZATION

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JOURNAL OF GUIDANCE control AND DYNAMICS 1991年第5期14卷 927-935页

作者： VOTH, C LY, UL UNIV WASHINGTON DEPT AERONAUT & ASTRONAUTSEATTLEWA 98195

The application of a multivariable control design method based on constrained parameter optimization to the design of a multiloop aircraft flight control system is described. Specifically, the design method is applied to the direct synthesis of a multivariable "inner-loop" feedback control system based on total energy control principles. The design procedure offers a structured approach for the determination of a set of controller gains that meet design specifications in closed-loop stability, command tracking performance, disturbance rejection, and limits on control activities. The presented approach may be applied to a broader class of multiloop flight control systems. Direct tradeoffs between many real design goals are rendered systematic by this method following proper formulation of the design objectives and constraints. Performance characteristics of the optimized design have been improved over the current autopilot design on the B737-100 Transport systems Research Vehicle at the landing approach and cruise conditions, particularly in the areas of closed-loop damping and control activity in the presence of turbulence.

关键词： Energy Distribution Autopilot Linear Time Invariant Feedback control system Transport systems Research Vehicle integrated flight control system Multivariable control Elevator Total Energy control system flight Path Angle

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MV-22B Short Takeoff and Minimum Run-On Landing Tests Aboard Nimitz-Class Ships

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JOURNAL OF AIRCRAFT 2022年第2期59卷 307-316页

作者： Gibson, James R. Mitchell, Virginia Embry Riddle Aeronaut Univ Decis Sci Daytona Beach FL 32114 USA Lockheed Martin Marietta GA 30060 USA

Tiltrotor aircraft ship suitability and envelope expansion testing aboard a U.S. Navy aircraft carrier is discussed. The purpose was to validate and expand day/night vertical launch and recovery wind envelopes, and the development of short takeoff and minimum run-on landing wind envelopes. The preparation phase incorporated a six-degree-of-freedom motion flight simulator to evaluate flight dynamics prior to on-shore testing using V-22 developmental and production aircraft. The short takeoff and minimum run-on landing testing totaled 12.3 flight hours with 33 takeoffs and 32 landings. The gross weights ranged from 51,000 to 57,000 lb with +/- 15deg of relative wind from 0 to 45 kt. The test pilots provided assessments of handling and flying qualities throughout the maneuvers using the deck interface pilot effort scale. Predictability tests were required to determine the pilot's ability to land within the defined touchdown zone and speeds for safely stopping within the braking zone. The results show the integrated nature of shipboard flight testing and the process of combining pilot workload ratings, control strategies, and aerodynamic analyses to field a needed capability.

关键词： flight Test Programme Crew Member Queen Elizabeth Class Aircraft Carrier Handling Qualities Tiltrotor Aircraft Six Degree of Freedom flight Simulators flight Dynamics integrated flight control system Helicopter Rotor

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Avionics: A "new" senior partner in aeronautics

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AIAA JOURNAL 1999年第11期37卷 1337-1354页

作者： Loewy, RG Georgia Inst Technol Sch Aerosp Engn Atlanta GA 30332 USA

The application of electronic devices to aviation, particularly to air vehicles, has given rise to the term avionics. This term is now widely understood. The extent to which the technology that it represents is pervading aeronautics, however, is much less so. Although avionics often refers only to mission equipment packages (MEPs), increasing use of the term vehicle management system (VMS) by practitioners indicates its broader usage, and bath MEP and VMS uses of avionics are considered in this paper. Several specific engineering developments that have made the influence of avionics so profound for aeronautics are summarized. It is noted that the earliest applications were in the form of equipment add-ons to existing vehicle types. However, the benefits of exploiting avionics and the increasing need to rely on them have now reached a revel that requires their capabilities to be accounted for at every stage of aeronautical vehicle system design. As a result, the integration of avionics into the aircraft development process is now a matter of primary concern. Further, with the power of present-day digital technology, the associated software has become as complex and crucial as hardware. After reviewing the growing number of functions for which the capabilities of avionics are being used, the additional impact of so called smart materials and structures is introduced, and the implications of avionics for aircraft designers and aerospace engineering educators are discussed.

关键词： Aeronautics Full Authority Digital Engine control Smart Materials and Structures Supersonic Transport Aircraft Aircraft Center of Gravity Aviation control Surfaces integrated flight control system Pilot Aerodynamic Stability

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FUNCTIONAL AGILITY METRICS AND OPTIMAL TRAJECTORY ANALYSIS

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JOURNAL OF GUIDANCE control AND DYNAMICS 1994年第6期17卷 1193-1197页

作者： RYAN, GW DOWNING, DR University of Kansas Lawrence Kansas 66044

This paper examines several functional fighter agility metrics using optimal and nonoptimal maneuvers for a generic F-18-type aircraft to investigate the sensitivity of these metrics to the control strategy used to test them. The maneuvers tested are 180 deg heading changes. The metrics tested are the combat cycle time, the dynamic speed turn agility plots, and the relative energy state metric. Significant improvements in the measured agility metrics are possible if an optimal control strategy is used to test them. For example, reductions in combat cycle time of 60% with subsequent reductions in speed bleed rate of 80% are possible if an optimal maneuver is flown instead of a typical night test maneuver. The specific agility improvements are vehicle airframe and control system dependent. However, the techniques used in this study are applicable to any aircraft and could provide insight into flight control system design and design tactics for maximizing performance during air combat engagements.

关键词： Angle of Attack Mach Number Trajectory Optimization integrated flight control system control systems Airframes flight Testing Knots True Airspeed Pilot Energy Efficiency

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DEVELOPMENT OF THE F/A-18A AUTOMATIC CARRIER LANDING system

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JOURNAL OF GUIDANCE control AND DYNAMICS 1985年第3期8卷 289-295页

作者： URNES, JM HESS, RK McDonnell Aircraft Company St. Louis Missouri

The F/A-18A Automatic Carrier Landing system integrates the aircraft flight control system, throttle control system, inertial navigation sensors, and shipboard SPN-42 tracking radar and computer system to achieve fully automatic approach control to the carrier deck in all weather conditions. Accurate touchdown position and sink rate must be achieved under varying conditions of visibility, deck motion, air turbulence, and ship air wake downdraft. Design analysis of this integrated digital control system is described, including digital synthesis methods used and projected performance under wind and deck motion conditions, two shipboard trials have verified the high touchdown accuracy potential of the system, resulting in along-deck touchdown dispersion of only 19 ft for 91 automatic landings. © 1985 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Automatic Carrier Landing system integrated flight control system Radar Tracking Inertial Navigation system Sensors Digital control system Approach control Computer systems flight Testing Autopilot

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