Conceptual Design, Flying, and Handling Qualities Assessment of a Blended Wing Body (BWB) Aircraft by Using an Engineering Flight Simulator

Humphreys-Jennings, Clayton; Lappas, Ilias; Sovar, Dragos Mihai

doi:10.3390/aerospace7050051

Cited by 16 publications

(7 citation statements)

References 28 publications

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“…Previous research concludes that the Dutch roll mode is unstable and that the lateral-directional controllability of the aircraft is limited in the case of One Engine Inoperative (OEI) at low speeds [8]. The unstable Dutch roll behaviour obtained from previous research was confirmed during a flight test with a small scale model of the aircraft * and is also in coherence with previous research on the undesirable lateral-directional behaviour of flying wings [9,10]. In preparation for this flight test, wind tunnel experiments have been performed on a half-span small scale model of the Flying-V.…”

Section: Introductionsupporting

confidence: 78%

Modelling and Handling Quality Assessment of the Flying-V Aircraft

Overeem

Wang

Kampen

2022

AIAA SCITECH 2022 Forum

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Considerable growth in the number of passengers and cargo transported by air is predicted. Besides that, aircraft noise and climate impact become increasingly important factors in aircraft design. These existing challenges in aviation boost interest in the design of innovative aircraft configurations. One of these configurations is a V-shaped flying wing named the Flying-V. This work aims at developing a flight dynamic simulation model of the Flying-V based on aerodynamic data obtained from the Vortex Lattice Method and wind tunnel experiments. The simulation model is used to assess the stability and handling qualities for certification and qualification purposes. Prior work has shown an assessment of the stability and handling qualities based on a linear aerodynamic model. However, to capture the longitudinal undesired behaviour of the Flying-V it is necessary to use a nonlinear aerodynamic model. Therefore, this paper illustrates how a flight dynamic simulation model, based on combined aerodynamic data from the Vortex Lattice Method and wind tunnel experiments, is used for certification and qualification purposes. The stability and handling qualities are assessed by analysing the aircraft dynamic modes and analysing nonlinear system handling qualities based on linearisation for both the cruise and approach condition.

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Section: Introductionsupporting

confidence: 78%

Modelling and Handling Quality Assessment of the Flying-V Aircraft

Overeem

Wang

Kampen

2022

AIAA SCITECH 2022 Forum

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“…The Flying-V is a new prototype, and the criteria (such as the MIL-STD) designed for standard aircraft might not be suitable for the evaluation of its handling qualities. On this topic, some attempts have been made to link the most commonly used criteria to the handling qualities of a flying wing (e.g., Ehlers [18], or Humphreys-Jennings, Lappas and Mihai Sovar [19]), and more in general to specialize the criteria on the evaluation of handling qualities in final approach and landing (e.g., Frost, Franklin, and Hardy [20], Stoliker [21], Field and Rossitto [22]).…”

Section: Piloted Simulation Evaluation Of Handling Qualitiesmentioning

confidence: 99%

Piloted Simulator Evaluation of Low-Speed Handling Qualities of the Flying-V

Torelli

Stroosma

Vos

et al. 2023

AIAA SCITECH 2023 Forum

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The Flying-V novel aircraft design aims at reducing fuel consumption by an innovative low-drag, fuselage-free geometry. Possible issues related to certification requirements have been noted, however, regarding longitudinal handling qualities at low speed, the pull-up manoeuver, and the flight-path-angle response. This study aims at investigating these issues through a pilot-in-theloop experiment. Starting with a mathematical model of the Flying-V, based on the vortex lattice method, a preliminary off-line analysis of the handling qualities is conducted. A sensitivity analysis is considered over the proposed operational center-of-gravity range, approach speed (between 0.225 and 0.3 Mach, 149 and 198 knots indicated airspeed, respectively), maximum deflection of the control surfaces (between 20 and 30 degrees), and flight control system (Direct Law or Pitch-Rate Command). The pilot-in-the-loop experiment, its design guided by results from the analytical assessment, shows that the handling qualities provided by the current design of the Flying-V with Direct Law at 0.3 Mach are satisfactory with minor improvements related to aircraft responsiveness. For lower speeds (0.225 Mach), the handling qualities degrade due to a sluggish response, high compensation workload, insufficient control authority, insufficient sight angle, and tendency to pilot induced oscillations. Shifting the center of gravity away from the nose provides larger control authority at the expense of a minor reduction of responsiveness. Control augmentation proves to be very effective at improving the handling qualities. It is expected that the go-around certification standards will be satisfied, but approach speed will remain critical for controllability and safety.

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“…The extrapolation of stability derivatives is illustrated for a V-tailed single-aisle jetliner design but can be applied not only to V-tailed aircraft [11][12][13][14][15] but to other configurations [16][17][18][19], such as blended-wing bodies [20][21][22][23][24][25][26][27][28][29][30][31][32][33][34][35][36][37][38][39] and joined wings [40,41], that can have large number of control surfaces changing their geometry. The effort of determination of each stability derivative for a given airspeed could be reduced from one full table (combinations of the AoA and AoS) to (a) a list (dependence on one extrapolated to the other) or (b) a single value (extrapolation from given AoA and AoS).…”

Section: Introductionmentioning

confidence: 99%

On the Extrapolation of Stability Derivatives to Combined Changes in Airspeed and Angles of Attack and Sideslip

Campos

Marques

2022

Aerospace

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The variation in stability derivatives with airspeed and angles of attack and sideslip is determined using only the dependence of the aerodynamic forces and moments on the modulus and direction of the velocity. Analytic extrapolation factors are obtained for all 12 longitudinal plus 12 lateral stability derivatives of linear decoupled motion. The extrapolation factors relate the stability derivatives for two flight conditions with different airspeeds, angles of attack (AoA), and angles of sideslip (AoS). The extrapolation formulas were validated by comparison with results of computational fluid dynamics (CFD) using Reynolds-averaged Navier–Stokes (RANS) equations. The comparison concerns the extrapolated full longitudinal–lateral stability matrix from one landing and one takeoff condition of a V-tailed aircraft, to 10 other landing and takeoff flight cases with different airspeeds, AoAs, and AoSs. Thus, 420 comparisons were made between extrapolated stability derivatives and CFD–RANS results demonstrating the achievable levels of accuracy.

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Conceptual Design, Flying, and Handling Qualities Assessment of a Blended Wing Body (BWB) Aircraft by Using an Engineering Flight Simulator

Cited by 16 publications

References 28 publications

Modelling and Handling Quality Assessment of the Flying-V Aircraft

Modelling and Handling Quality Assessment of the Flying-V Aircraft

Piloted Simulator Evaluation of Low-Speed Handling Qualities of the Flying-V

On the Extrapolation of Stability Derivatives to Combined Changes in Airspeed and Angles of Attack and Sideslip

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