Comparison of In-Flight and Ground Based Simulations of Large Aircraft Flying Qualities

Field, Edmund; Armor, James; Rossitto, Kenneth F.; Schroeder, Jeffery A.; Weingarten, Norman

doi:10.2514/6.2002-4800

Cited by 7 publications

(1 citation statement)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…10 Therefore, much attention is being directed to the correct implementation of the GLT model in SIMONA and to the quality of the cues provided. 11 Piloted frequency sweeps were used to determine the control inceptor dynamics.…”

Section: Delft University Of Technology Simona Research Simulatormentioning

confidence: 99%

Flying Qualities Applications of Frequency Responses Identified from Flight Data

Field

Rossitto

Hodgkinson³

2004

Journal of Aircraft

View full text Add to dashboard Cite

Despite increasingly accurate modeling technologies, it is still necessary to validate aircraft models with flight data. One area where this is especially critical is for flight control system development and flying qualities appraisals. Consistent with the frequency domain specification of flying qualities requirements, the method discussed is the identification of an aircraft's frequency responses from piloted frequency sweeps performed in flight. Pilotgenerated frequency sweeps were performed on a range of transport aircraft, research aircraft, and simulators. The time histories from the sweeps were transformed into the frequency domain to yield frequency responses that were used for a variety of applications. In some applications, further analyses with the Low-Order Equivalent Systems method were used to identify dominant modes of the bare airframe and of elements of the aircraft's flight control system, as well as those of the augmented aircraft, which were applied to flying qualities criteria. In other applications, the frequency responses from one aircraft were compared to those from other aircraft to support handling qualities assessments in support of same type ratings and minor design changes. The techniques used in the analyses are summarized and several of these applications are reported. Nomenclature C= cost F = control inceptor force, lb G = gain, dB K = weighting function gain n z = normal load factor, g q = pitch rate, deg/s s = Laplace variable T = (equivalent) time delay, record length, s δ = control inceptor deflection, in. or deg ζ = damping ratio of a second-order LOES τ = time constant, s φ = phase angle, deg ω = frequency of a second-order low-order equivalent system (LOES) rad/s Subscripts CC = control column HOS = high-order system ICR = instantaneous center of rotation i = iteration number LOES = low-order equivalent system min = minimum ph = aircraft phugoid oscillation

show abstract

Section: Delft University Of Technology Simona Research Simulatormentioning

confidence: 99%