A utility aircraft for remote sensing missions with a high-precision automatic flight control system

Luckner, Robert; Dalldorff, Lothar; Reichel, Reinhard

doi:10.1109/icares.2014.7024378

Cited by 5 publications

(2 citation statements)

References 2 publications

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“…In October of 2010, flight tests proved the successful implementation of the flight control system. Since then, automatic takeoff and landing, as well as gust load alleviation functions, have been demonstrated [35].…”

Section: A Aircraftmentioning

confidence: 99%

Experimental Validation of a Flight Simulation Model for Slightly Flexible Aircraft

Silvestre

Luckner

2015

AIAA Journal

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The paper presents a methodology for modeling the coupled flight dynamics with aeroelasticity in the time domain. The equations of motion are based on linearized mean-axes formulation. Unsteady, incremental aerodynamics due to elastic deformations are modeled in the time domain, applying the strip theory and a indicial function. The methodology is demonstrated with a prototype of the utility aircraft Stemme S15. Comparisons between the simulation and the flight-test data regarding the added aeroelastic dynamics have indicated that the model is suited for the flight control law and aircraft design, and that care must be taken in modeling the control surface lift slope for lowaspect-ratio lifting surfaces. Nomenclature A SIM ∕A FT = ratio of acceleration amplitudes from simulation and from flight test b = wingspan, m c = chord, m c = wing aerodynamic mean chord, m F C A , F NC A = vectors of circulatory and noncirculatory aerodynamic forces, N F ext = vector of external forces, N G = gravity acceleration vector, m∕s 2 J = inertia tensor, kg · m 2 l C , l NC = circulatory and noncirculatory lift per unit span, N∕m M C A , M NC A = vectors of circulatory and noncirculatory aerodynamic moments, N · m M ext = vector of external moments, N · m m = mass, kg m C , m NC = circulatory and noncirculatory pitch moments per unit span, N · m∕m n e = number of elastic modes O A G = global aerodynamic reference frame (origin at the aircraft center of gravity) O A L = local aerodynamic reference frame O B G = global body reference frame (origin at the aircraft center of gravity) O B L = local body reference frame O I = inertial reference frame p = position of a mass element relative to the center of gravity, m p d = elastic displacement (p − p r ), m p r = undeformed position of a mass element relative to the center of gravity, m p, q, r = nondimensional angular rates Q η = vector of generalized loads, N ⋅ m R = position of a mass element relative to the origin of O I , m R 0 = position of the center of gravity relative to the origin of O I , m r EA = position vector of the elastic axis of a wing section relative to the origin of O B L , m S = reference (wing) area, m 2 S 1.1 : : : S 7.1 = accelerometers of measurement set 1 S 1.2 : : : S 7.2 = accelerometers of measurement set 2m∕s V = velocity vector, m∕s w f 3∕4 = downwash caused by elastic displacements at the three-quarter-chord, m∕s X = 1 α β p q r T X flex = vector of states in the flexible model X RB = vector of states in the rigid-body model x AC , x EA , x 3∕4 = x positions of the aerodynamic center, the elastic axis, and the three-quarter-chord in O B L , m α L = local angle of attack, rad β L = local sideslip angle, rad γ EA k = equivalent kth modal torsion at elastic axis positive in pitch down, rad Δϕ = response phase difference between flight test and simulation, deg η = vector of modal amplitudes Λ= dihedral angle, rad λ 1 , λ 2 = aerodynamic lag states, m/s μ = diagonal matrix of modal masses, kg · m 2 ξ = diagonal matrix of structural modal damping ratios ξ SIM ∕...

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Section: A Aircraftmentioning

confidence: 99%

Experimental Validation of a Flight Simulation Model for Slightly Flexible Aircraft

Silvestre

Luckner

2015

AIAA Journal

Self Cite

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“…In this station, the aircraft must undergo a series of verification tests of its assembly before commissioning [1]. In addition, once the aircraft is in production, it is also necessary to check routinely for faults and to perform various tests to verify its correct operating status [2][3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

A Research Study for the Design of a Portable and Configurable Ground Test System for the A400M Aircraft

Larios

Barbancho

Biscarri

et al. 2019

International Journal of Aerospace Engineering

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This paper presents a study of the most suitable ground test equipment for the Airbus A400M aircraft aimed at optimizing a design that combines portability, flexibility, and configurability. The study is based on current trends in the configuration of the different parts that are involved in the process of designing Aircraft Interface Modules (AIMs). Researches have been conducted facing the real problems of data acquisition and control in the assembly, maintenance, and repair processes of aircraft. In this sense, the number of signals used simultaneously in historical tests has been determined to be a parameter that plays an important role in the analysis. This work is within the framework of a project that our working group of the Department of Electronic Technology has carried out together with the company Airbus Defense and Space (Airbus DS). Thus, all the analyses and researches for the different configurations of the test equipment have been validated for the company. Some state-of-the-art systems have been considered in the process of designing the structure of the test system while analyzing the main advantages and drawbacks. Every hardware or software component was identified and justified according to its importance with respect to the use case. A comparison of how every approach meets the requirements was taken into account to define a methodology for designing a portable and configurable ground testing system. Thus, the conclusions of our study are being used by Airbus DS for the design of a prototype for the next generation of AIMs in A400M.

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Fly-by-Wire/Light Demonstrators

Hamel¹

2017

In-Flight Simulators and Fly-by-Wire/Light Demonstrators

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A utility aircraft for remote sensing missions with a high-precision automatic flight control system

Cited by 5 publications

References 2 publications

Experimental Validation of a Flight Simulation Model for Slightly Flexible Aircraft

Experimental Validation of a Flight Simulation Model for Slightly Flexible Aircraft

A Research Study for the Design of a Portable and Configurable Ground Test System for the A400M Aircraft

Fly-by-Wire/Light Demonstrators

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