Design, Development and Validation of a Cessna Citation X Aerodynamic Model using OpenVSP Software

Segui, Marine; Ghazi, Georges; Botez, Ruxandra Mihaela; Thompson, Emily

doi:10.2514/6.2018-3256

Cited by 6 publications

(1 citation statement)

References 9 publications

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“…It gives very fast and accurate enough results for the initial design phase [18][19][20]. Detailed verification of DATCOM methods are also studied in the literature [21,24,25]. To conclude, Digital DATCOM program is considered as an effective way to estimate the wing-body aerodynamics with acceptable accuracy since the main focus of the study is not detailed aerodynamic modeling.…”

Section: Forward Flight Aerodynamic Model: Wing-body Aerodynamics At ...mentioning

confidence: 99%

Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi

Suiçmez,

Kutay

2023

Aeronaut. j.

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On-demand urban air transportation gains popularity in recent years with the introduction of the electric VTOL (eVTOL) aircraft concept. There is an emerging interest in short/medium range eVTOL air taxi considering the critical advantages of electric propulsion (i.e. low noise and carbon emission). Using several electric propulsion systems (distributed electric propulsion (DEP)) has further advantages such as improved redundancy. However, flight controller design becomes more challenging due to highly over-actuated and coupled dynamics. This study defines and resolves flight control problems of a novel DEP eVTOL air taxi. The aircraft has a fixed-wing surface to have aerodynamically efficient cruise flight, and uses only tilting electric propulsion units to achieve full envelope flight control via pure thrust vector control. The aircraft does not have conventional control surfaces such as aileron, rudder or elevator. Using pure thrust vector control has some design benefits, but the control problem becomes more challenging due to the over-actuated and highly coupled dynamics (especially in transition flight). A preliminary flight dynamics model is obtained considering the dominant effects at hover and high-speed forward flight. Hover and forward flight models are blended to simulate the transition dynamics. Two central challenges regarding the flight control are significant nonlinearities in aircraft dynamics during the transition and proper allocation of the thrust vector control specifically in limited control authority (actuator saturation). The former challenge is resolved via designing a sensor-based incremental nonlinear dynamic inversion (INDI) controller to have a single/unified controller covering the wide flight envelope. For the latter one, an optimisation-based control allocation (CA) approach is integrated into the INDI controller. CA requires special attention due to the pure thrust vector control’s highly coupled dynamics. The controller shows satisfactory performance and disturbance rejection characteristics. Moreover, the CA plays a vital role in guaranteeing stable flight in case of severe actuator saturation.

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Section: Forward Flight Aerodynamic Model: Wing-body Aerodynamics At ...mentioning

confidence: 99%

Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi

Suiçmez,

Kutay

2023

Aeronaut. j.

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High-fidelity aerodynamic modeling of an aircraft using OpenFoam – application on the CRJ700

et al. 2021

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This study is focused on the development of longitudinal aerodynamic models for steady flight conditions. While several commercial solvers are available for this type of work, we seek to evaluate the accuracy of an open source software. This study aims to verify and demonstrate the accuracy of the OpenFoam solver when it is used on basic computers (32–64GB of RAM and eight cores). A new methodology was developed to show how an aerodynamic model of an aircraft could be designed using OpenFoam software. The mesh and the simulations were designed only using OpenFoam utilities, such as blockMesh, snappyHexMesh, simpleFoam and rhoSimpleFoam. For the methodology illustration, the process was applied to the Bombardier CRJ700 aircraft and simulations were performed for its flight envelope, up to M0.79. Forces and moments obtained with the OpenFoam model were compared with an accurate flight data source (level D flight simulator). Excellent results in data agreement were obtained with a maximum absolute error of 0.0026 for the drag coefficient, thus validating a high-fidelity aerodynamic model for the Bombardier CRJ-700 aircraft.

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Morphing Winglet Design for Aerodynamic Performance Optimization of the CRJ-700 Aircraft. Part 1 – Structural Design

et al. 2021

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This study aims to design a morphing winglet structure for the CRJ-700 regional transport aircraft. The morphing technology is applied on winglets to demonstrate a significant increase of the aerodynamic performance of aircraft. From the aerodynamic data of the LARCASE Virtual Research Simulator VRESIM, the aerodynamic benefits in the cruising phase were obtained through a study on the ParaView software. The morphing winglet design was drawn using CATIA V5; this new concept included several structural components, as well as a simple and light mechanism allowing to orientate the winglet angles between 90° and -90° of inclination. The structural model was exported to HyperMesh structural analysis software. Maximum stresses were obtained, and the model demonstrated its resistance to maximum aerodynamic loads as well as load factors of -2G to 7G.

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Design, Development and Validation of a Cessna Citation X Aerodynamic Model using OpenVSP Software

Cited by 6 publications

References 9 publications

Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi

Full envelope nonlinear flight controller design for a novel electric VTOL (eVTOL) air taxi

High-fidelity aerodynamic modeling of an aircraft using OpenFoam – application on the CRJ700

Morphing Winglet Design for Aerodynamic Performance Optimization of the CRJ-700 Aircraft. Part 1 – Structural Design

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