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Evaluation of an L₁ Adaptive flight Control Law on Calspan's Variable-Stability Learjet

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2017年第4期40卷 1050-1059页

作者： Ackerman, Kasey A. Xargay, Enric Choe, Ronald Hovakimyan, Naira Cotting, M. Christopher Jeffrey, Robert B. Blackstun, Margaret P. Fulkerson, T. Paul Lau, Timothy R. Stephens, Shawn S. Univ Illinois Dept Mech Sci & Engn Urbana IL 61801 USA Univ Illinois Dept Mech Sci & Engn Urbana IL 61801 USA US Air Force Test Pilot Sch Flying Qual Edwards AFB CA 93524 USA US Air Force Test Pilot Sch Edwards AFB CA 93524 USA

A study presented flight-test results of a variable-stability Learjet aircraft augmented with an L1 adaptive flight control law. The flight tests were conducted by the US Air Force (USAF) test Pilot School (TPS) at Ed... 详细信息

A study presented flight-test results of a variable-stability Learjet aircraft augmented with an L₁ adaptive flight control law. The flight tests were conducted by the US Air Force (USAF) test Pilot School (TPS) at Edwards Air Force Base, California, in collaboration with the Calspan Corporation, and mark the first time an L₁ adaptive system was implemented and tested on a manned aircraft. The flight-test plan was designed by the team at the USAF TPS and included the assessment of the flying and handling qualities of the L₁-augmented Learjet, the determination of the stability margins of the L₁ flight control law, offset-to-landing tasks conducted at altitude, and straight-in, touch-and-go landings.

关键词： flight Control Law SAS Control Surfaces flight test programme test Pilots Handling Qualities Longitudinal Control Aerodynamic Stability Aircraft Dynamics Aircraft Configurations

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Adaptive Glide Slope Control for Parafoil and Payload Aircraft

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2013年第4期36卷 1019-1034页

作者： Ward, Michael Costello, Mark Georgia Inst Technol Guggenheim Sch Aerosp Engn Atlanta GA 30332 USA Georgia Inst Technol Guggenheim Sch Aerosp Engn Woodruff Sch Mech Engn Atlanta GA 30332 USA

The invention of the steerable, gliding, ram-air parafoil enabled the possibility of precision, autonomous aerial payload delivery. Research and development work on guided airdrop systems has focused primarily on evolutionary improvements to the guidance algorithm, although the navigation and control algorithms have changed little since the initial autonomous systems were developed. Recent work has demonstrated the potential for dramatic improvements in landing accuracy through the incorporation of canopy incidence variation to achieve glide slope control for parafoils. The current work presents the development of a control law to implement glide slope control on an autonomous airdrop system. Autonomous landings with the control law in both simulation and flight test demonstrate an improvement in landing accuracy by a factor of two, though the improvement can be even greater in especially windy conditions. Finally, the ability to perform in-flight system identification to adapt internal control mappings to match flight data and provide dramatic improvements in landing accuracy when there is a significant discrepancy between the assumed and actual flight characteristics is demonstrated in both simulation and flight test.

关键词： Parafoil Air Vehicle flight test programme Adaptive Control Algorithm Control Algorithm flight Software Navigation Algorithm Autonomous Systems Airspeed GPS

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BANK-TO-TURN MISSILE AUTOPILOT DESIGN USING LOOP TRANSFER RECOVERY

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1990年第1期13卷 145-152页

作者： WISE, KA SO ILLINOIS UNIV ELECT ENGNEDWARDSVILLEIL 62026

Linear quadratic Gaussian/loop transfer recovery control theory is used to design a bank-to-turn missile autopilot. This paper presents the steps of the design and analysis procedure and demonstrates them in designing a missile autopilot at a single flight condition. Autopilot design issues such as bandwidth, model uncertainty, and noise sensitivity are discussed using singular values of their respective matrix quantities.

关键词： Aerodynamic Stability Autopilot Missile Configurations Closed Loop Transfer Function Algebraic Riccati Equation Kalman Filter Gain flight Control Design Missile Defense Inertial Navigation flight test programme

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PRACTICAL flight test METHOD FOR DETERMINING RECIPROCATING-ENGINE COOLING REQUIREMENTS

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JOURNAL OF AIRCRAFT 1984年第12期21卷 936-942页

作者： WARD, DT MILEY, SJ Texas A&M University College Station Texas

A practical flight test procedure has been developed and verified for determining the cooling requirements for an installed air cooled reciprocating engine of any type The technique is based on a simple modification of the NACA cooling correlation method developed some 40 years ago for radial engines The modification involves replacing an empirically determined combustion gas temperature T_g with a measured exhaust gas temperature T_egt This latter parameter can be easily obtained utilizing cockpit instruments only The modification, therefore, reduces the need for extensive and expensive ground tests Data were collected in two separate flight test programs that verify the technique first with a rather completely instrumented airplane and later with minimal instrumentation and a minimal number of data points In both cases the data fits that comprise the correlation procedure were quite good Even the second tests with the sparse test matrix produced root mean square fit errors of less than 4% suggesting that the procedure provides consistent answers for practical flight test situations. © 1984 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： flight test programme Horizontally Opposed Engine Aeroplane Mass Flow Rate Air Cooled Engine Heat Transfer Landing Gear General Aviation Cockpit Instrumentation Airspeed

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COMPUTATIONAL REQUIREMENTS FOR HYPERSONIC flight PERFORMANCE ESTIMATES

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JOURNAL OF SPACECRAFT AND ROCKETS 1990年第2期27卷 103-112页

作者： MEHTA, UB NASA Ames Research Center Moffett Field California 94035

Among the many new hypervelocity vehicles being considered for development, the air breathing, single stage-to-orbit transatmospheric vehicles and aeroassisted orbital-transfer vehicles are going to be designed largely by computational fluid dynamics (CFD). (The nomenclature of CFD is used to encompass a range of related areas such as computational aerodynamics, combustion, rarified gas dynamics, and computational aerothermodynamics.) Errors in CFD, flight-performance estimates, and, consequently, in the specifications for these vehicles need to be sufficiently small to achieve the design goals set for the vehicles. At present, the credibility of the CFD technology, in general, is poor when different forms of the Navier-Stokes equations are used for estimating critical design-performance quantities. To improve this credibility, a procedure is presented. This procedure introduces the phrase “programmatic research,” the CFD design technology development triad and “code certification.” Programmatic research emphasizes performance estimates. In turn, performance estimation requirements largely determine the computational requirements. This triad uses the systems approach (a characteristic of programmatic research) to create a strong interaction between CFD, design, ground-based testing, and flight testing. Code certification can bring order into the process of establishing the credibility of computer codes by insuring compliance to specific requirements. These requirements are primarily set by design sensitivities, physical/chemical realities, and computational sensitivities. Ground-based experiments and flight tests principally help to establish the credibility of CFD results. However, risks are associated with CFD performance estimates mainly because of a lack of quality test data, inadequate modeling of physics and chemistry, and a lack of a satisfactory level of numerical accuracy. These risks need to be estimated with an uncertainty analysis. The preceding procedur

关键词： flight Performance CFD flight test programme Design Technology Aerodynamic Characteristics Conservation of Mass Navier Stokes Equations Aerothermodynamics Orbital Maneuvers Hypersonic Speed

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flight test OF THE JAPANESE UPPER SURFACE BLOWING STOL EXPERIMENTAL AIRCRAFT ASKA

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JOURNAL OF AIRCRAFT 1991年第10期28卷 630-637页

作者： YAMATO, H OKADA, N BANDO, T University of Tokyo Tokyo Japan National Aerospace Laboratory Tokyo Japan

The Upper Surface Blowing STOL aircraft named ASKA was developed and flight tested by the National Aerospace Laboratory of Japan between 1977-1989. The aircraft was a conversion of the Kawasaki C-1 medium transport, with four newly developed FJR710/600S turbofan engines on the wing. The short takeoff and landing performance, including the stability and control augmentation system and boundary-layer control, was intensively examined by the flight test. flight-test data were obtained at altitude and converted to the standard sea level conditions to compare with the design data. From the viewpoint of the lift-and-drag and related performances, the design STOL capability was proven by the flight-test program.

关键词： flight test programme STOL Experimental Aircraft Stability and Control Augmentation System National Aerospace Laboratory of Japan Boundary Layer Control Turbofan Engines Angle of Attack flight Path Angle Yaw Damper

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WIND PROFILE MEASUREMENT USING LIFTING SENSORS

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JOURNAL OF SPACECRAFT AND ROCKETS 1966年第3期3卷 365-&页

作者： STENGEL, RF Princeton University Princeton N. J.

A vertical profile of wind velocity for use in rocket prelaunch operations should be measured rapidly in order to minimize the space-time displacement between the measured profile and the ascent trajectory. A lifting wind sensor, a missile-like body with a large cruciform or annular wing, can measure the wind profile below 100,000 ft in 10 to 15 min. Using the linearized equations of motion to determine the wind response transfer function, a sample configuration is shown to have a maximum resolution more than an order of magnitude better than that of a drag wind sensor, e.g., balloon, chaff, or parachute, with the same fall velocity. Although the maximum resolution is set by the ratio 2m_e/C_LαS_ρ, the amplitude and phase fidelity largely depend on the moment stability derivatives. The response to arbitrary profiles, computed with a three-degree-of-freedom trajectory program, supports the linear analysis. By employing an iterative technique, the accuracy of the wind-profile estimate can be increased by at least an order of magnitude. Preliminary flight test data are briefly discussed. © 1966 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Sensors Aerodynamic Coefficients flight test programme Three Degrees of Freedom Meteorological Rocket Lift Coefficient Radiosondes Radar Data Earth Wind Shear

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REAL-TIME COMPARISON OF X-29A flight DATA AND SIMULATION DATA

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JOURNAL OF AIRCRAFT 1989年第2期26卷 117-123页

作者： BAUER, JE CRAWFORD, DB GERA, J ANDRISANI, D Purdue University West Lafayette Indiana NASA Ames Research Center Edwards California

This paper presents a technique for comparing, in real time, the flight-test time histories for X-29A aircraft with time histories computed from linearized mathematical models. Such a comparison allows the flight-test personnel to verify that the aircraft is performing as predicted, to determine regions of nonlinear behavior, and to increase the rate of envelope expansion. The types of mathematical modeling and equipment required, the procedure used, and actual flight-test results are discussed. © 1987 American Institute of Aeronautics and Astronautics, Inc.

关键词： Data Simulation flight test programme X 29A Aircraft Mathematical Models Digital flight Control System flight Data Pilot Control Derivatives Vector Processor Cathode Ray Tubes

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SCATTERING PROPERTIES OF ICE PARTICLES FORMED BY RELEASE OF H2O IN VACUUM

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JOURNAL OF SPACECRAFT AND ROCKETS 1974年第1期11卷 54-56页

作者： KASSAL, TT GRUMMAN AEROSP CORP BETHPAGENY 11714

The scattering characteristics of an aggregate of ice particles formed by injecting a stream of water into a vacuum tank were determined experimentally. Although the experiments were performed in the absence of solar radiation, the laboratory freezing conditions are similar to those encountered during the Apollo flights. The measured optical properties are believed to be identical to those that would be observed from a cloud formed by release of a liquid from a spacecraft.

关键词： Optical Properties Sounding Rocket Vehicle Propulsion System flight test programme Dual Thrust Internal Pressure Hydroxyl Terminated Polybutadiene NASA Goddard Space flight Center Solid Propellant Rocket Hybrid Rocket Engines

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Current Methods Modeling and Simulating Icing Effects on Aircraft Performance, Stability, Control

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JOURNAL OF AIRCRAFT 2010年第1期47卷 201-211页

作者： Ratvasky, Thomas P. Barnhart, Billy P. Lee, Sam NASA John H Glenn Res Ctr Lewis Field Icing Branch Cleveland OH 44135 USA Bihrle Appl Res Inc Hampton VA 23666 USA ASRC Aerosp Corp Icing Branch Cleveland OH 44135 USA

Icing alters the shape and surface characteristics of aircraft components, which results in altered aerodynamic forces and moments caused by air flow over those iced components. The typical effects of icing are increased drag, reduced stall angle of attack, and reduced maximum lift. In addition to the performance changes, icing can also affect control surface effectiveness, binge moments, and damping. These effects result in altered aircraft stability and control and flying qualities. Over the past 80 years, methods have been developed to understand how icing affects performance, stability, and control. Emphasis has been on wind-tunnel testing of two-dimensional subscale airfoils with various ice shapes to understand their effect on the flowfield and ultimately the aerodynamics. This research has led to wind-tunnel testing of subscale complete aircraft models to identify the integrated effects of icing on the aircraft system in terms of performance, stability, and control. Data sets of this nature enable pilot-in-the-loop simulations to be performed for pilot training or engineering evaluation of system failure impacts or control system design.

关键词： Icing Conditions Aircraft Performance Aerodynamic Characteristics Elevator Deflection Aeroplane Control Surfaces flight Training Device Icing Wind Tunnel Business Jet flight test programme

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