Conceptual Design optimization of a Blended Wing Body (BWB) Aircraft Using Flying and Handling Qualities Assessment

The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs. At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities using an engineering flight simulator and as such, to identify potential design solutions which will enhance its controllability and manoeuvrability characteristics. This aircraft is aimed toward the commercial sector with a range of 3,000 nautical miles, carrying a payload of 20,000kg. In the engineering flight simulator a flight test was undertaken; first, to determine the BWB design’s static stability through a standard commercial mission profile, and then to determine its dynamic stability characteristics through standard dynamic modes. Its flying qualities suggested its stability with a static margin of 8.652% of the Mean Aerodynamic Chord (MAC) and consistent response from the pilot input. In addition, the aircraft achieved a maximum lift-to-drag ratio of 28.1; a maximum range of 4,581 nautical miles; zero-lift drag of 0.005; and meeting all the requirements of the dynamic modes.

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

Aerospace ◽

10.3390/aerospace7050051 ◽

2020 ◽

Vol 7 (5) ◽

pp. 51 ◽

Cited By ~ 3

Author(s):

Clayton Humphreys-Jennings ◽

Ilias Lappas ◽

Dragos Mihai Sovar

Keyword(s):

Static Stability ◽

Flight Simulator ◽

Handling Qualities ◽

Stability And Control ◽

Flying Qualities ◽

Blended Wing Body ◽

And Control ◽

Drag Ratio ◽

Lift To Drag Ratio ◽

Mission Profile

The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs. At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities using an engineering flight simulator and as such, to identify potential design solutions which will enhance its controllability and manoeuvrability characteristics. This aircraft is aimed toward the commercial sector with a range of 3000 nautical miles, carrying 200 passengers. The BWB design was flight tested at an engineering flight simulator to first determine its static stability through a standard commercial mission profile, and then to determine its dynamic stability characteristics through standard dynamic modes. Its flying qualities suggested its stability with a static margin of 8.652% of the mean aerodynamic chord (MAC) and consistent response from the pilot input. In addition, the aircraft achieved a maximum lift-to-drag ratio of 28.1; a maximum range of 4,581 nautical miles; zero-lift drag of 0.005; while meeting all the requirements of the dynamic modes.

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GROUND BASED VARIABLE STABILITY FLIGHT SIMULATOR

Aviation ◽

10.3846/aviation.2021.13564 ◽

2021 ◽

Vol 25 (1) ◽

pp. 22-34

Author(s):

Kamali Chandrasekaran ◽

Vijeesh Theningaledathil ◽

Archana Hebbar

Keyword(s):

Autonomous Navigation ◽

Optimization Techniques ◽

Flight Mechanics ◽

Pilot Training ◽

Flight Simulator ◽

Fighter Aircraft ◽

Training Requirements ◽

Stability And Control ◽

Flying Qualities ◽

And Control

This paper discusses the development of a ground based variable stability flight simulator. The simulator is designed to meet the pilot training requirements on flying qualities. Such a requirement arose from a premier Flight-Testing School of the Indian Air Force. The simulator also provides a platform for researchers and aerospace students to understand aircraft dynamics, conduct studies on aircraft configuration design, flight mechanics, guidance & control and to evaluate autonomous navigation algorithms. The aircraft model is built using open source data. The simulator is strengthened with optimization techniques to configure variable aircraft stability and control characteristics to fly and evaluate the various aspects of flying qualities. The methodology is evaluated through a series of engineer and pilot-in-the-loop simulations for varying aircraft stability conditions. The tasks chosen are the proven CAT A HUD tracking tasks. The simulator is also reconfigurable to host an augmented fighter aircraft that can be evaluated by the test pilot team for the functional integrity as a fly-through model.

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Design and Fabrication of a Dual Rotor-Embedded Wing Vertical Take-Off and Landing Unmanned Aerial Vehicle

Unmanned Systems ◽

10.1142/s2301385021500096 ◽

2020 ◽

Vol 09 (01) ◽

pp. 45-63

Author(s):

Seng Man Wong ◽

Hann Woei Ho ◽

Mohd Zulkifly Abdullah

Keyword(s):

Low Cost ◽

Estimation Method ◽

Design Parameters ◽

Stability And Control ◽

Flying Qualities ◽

Vtol Uav ◽

Final Design ◽

Aerial Vehicle ◽

And Control ◽

Drag Ratio

The interest in building hybrid Unmanned Aerial Vehicles (UAVs) is increasing intensively due to its capability to perform Vertical Take-Off and Landing (VTOL), in addition to forward flight. With this capability, the hybrid UAVs are highly on demand in various industries. In this paper, a fixed-wing VTOL UAV with a novel configuration of a dual rotor-embedded wing was designed and developed. The methodology used in the design process adopted the traditional sizing and aerodynamic estimation method with advanced computational simulations and estimation approaches. The design was determined based on a thorough analysis of weight contribution, aerodynamics, propulsion, and stability and control. The results show that the UAV’s preliminary design has successfully reached a total weight of 1.318 kg, achieved a high lift-to-drag ratio of approximately 4, and ensured stable flights with Level 1 flying qualities. A fixed-wing VTOL prototype was developed and fabricated based on the final design parameters using a low-cost hand lay-up process.

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Method for designing multi-input system identification signals using a compact time-frequency representation

CEAS Aeronautical Journal ◽

10.1007/s13272-021-00499-6 ◽

2021 ◽

Author(s):

Mathias Stefan Roeser ◽

Nicolas Fezans

Keyword(s):

System Identification ◽

Design Method ◽

Flight Test ◽

Compact Representation ◽

Time Frequency ◽

Stability And Control ◽

Frequency Representation ◽

Aerodynamic Parameters ◽

Definition Of ◽

And Control

AbstractA flight test campaign for system identification is a costly and time-consuming task. Models derived from wind tunnel experiments and CFD calculations must be validated and/or updated with flight data to match the real aircraft stability and control characteristics. Classical maneuvers for system identification are mostly one-surface-at-a-time inputs and need to be performed several times at each flight condition. Various methods for defining very rich multi-axis maneuvers, for instance based on multisine/sum of sines signals, already exist. A new design method based on the wavelet transform allowing the definition of multi-axis inputs in the time-frequency domain has been developed. The compact representation chosen allows the user to define fairly complex maneuvers with very few parameters. This method is demonstrated using simulated flight test data from a high-quality Airbus A320 dynamic model. System identification is then performed with this data, and the results show that aerodynamic parameters can still be accurately estimated from these fairly simple multi-axis maneuvers.

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Rotorcraft Lateral-Directional Oscillations: The Anatomy of a Nuisance Mode

Journal of the American Helicopter Society ◽

10.4050/jahs.66.042009 ◽

2021 ◽

Author(s):

Dheeraj Agarwal ◽

Linghai Lu ◽

Gareth D. Padfield ◽

Mark D. White ◽

Neil Cameron

Keyword(s):

Simulation Model ◽

Simulation Models ◽

Flight Test ◽

Flight Simulation ◽

Stability And Control ◽

Systems Research ◽

Control Derivatives ◽

Research Aircraft ◽

Level Of Understanding ◽

And Control

High-fidelity rotorcraft flight simulation relies on the availability of a quality flight model that further demands a good level of understanding of the complexities arising from aerodynamic couplings and interference effects. One such example is the difficulty in the prediction of the characteristics of the rotorcraft lateral-directional oscillation (LDO) mode in simulation. Achieving an acceptable level of the damping of this mode is a design challenge requiring simulation models with sufficient fidelity that reveal sources of destabilizing effects. This paper is focused on using System Identification to highlight such fidelity issues using Liverpool's FLIGHTLAB Bell 412 simulation model and in-flight LDO measurements from the bare airframe National Research Council's (Canada) Advanced Systems Research Aircraft. The simulation model was renovated to improve the fidelity of the model. The results show a close match between the identified models and flight test for the LDO mode frequency and damping. Comparison of identified stability and control derivatives with those predicted by the simulation model highlight areas of good and poor fidelity.

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Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

MATEC Web of Conferences ◽

10.1051/matecconf/201925602004 ◽

2019 ◽

Vol 256 ◽

pp. 02004

Author(s):

Nornashiha Mohd Saad ◽

Wirachman Wisnoe ◽

Rizal Effendy Mohd Nasir ◽

Zurriati Mohd Ali ◽

Ehan Sabah Shukri Askari

Keyword(s):

Unmanned Aerial Vehicle ◽

Cfd Simulation ◽

Lift Coefficient ◽

Angle Of Attack ◽

Flight Test ◽

Longitudinal Direction ◽

Static Stability ◽

Pitching Moment ◽

Aerial Vehicle ◽

Blended Wing Body

This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended Wing Body-Unmanned Aerial Vehicle Prototype (BWB-UAV Prototype) equipped with horizontal stabilizers. Flight tests have been conducted and as the result, BWB experienced overturning condition at certain angle of attack. Horizontal stabilizer was added at different location and size to overcome the issue during the flight test. Therefore, Computational Fluid Dynamics (CFD) analysis is performed at different configuration of horizontal stabilizer using Spalart - Allmaras as a turbulence model. CFD simulation of the aircraft is conducted at Mach number 0.06 or v = 20 m/s at various angle of attack, α. The data of lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM) is obtained from the simulations. The data is represented in curves against angle of attack to measure the performance of BWB prototype with horizontal stabilizer. From the simulation, configuration with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft.

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Some Stability and Control Aspects of Airframe/Propulsion System Interactions on the YF-12 Airplane

Journal of Engineering for Industry ◽

10.1115/1.3438447 ◽

1974 ◽

Vol 96 (3) ◽

pp. 820-826 ◽

Cited By ~ 2

Author(s):

D. T. Berry ◽

G. B. Gilyard

Keyword(s):

Static Stability ◽

Propulsion System ◽

Jet Propulsion ◽

Stability And Control ◽

The Stability ◽

And Control ◽

Large Aircraft

Airframe/propulsion system interactions can strongly affect the stability and control of supersonic cruise aircraft. These interactions generate forces and moments similar in magnitude to those produced by the aerodynamic controls, and can cause significant changes in vehicle damping and static stability. This in turn can lead to large aircraft excursions or high pilot workload, or both. For optimum integration of an airframe and its jet propulsion system, these phenomena may have to be taken into account.

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The Correlation of Wind-Tunnel and Flight-Test Stability and Control Data For an SB2C-1 Airplane

Journal of the Aeronautical Sciences (Institute of the Aeronautical Sciences) ◽

10.2514/8.11490 ◽

1948 ◽

Vol 15 (1) ◽

pp. 5-17

Author(s):

MARION T. HOCKMAN ◽

ROBERT E. EISIMINGER

Keyword(s):

Wind Tunnel ◽

Flight Test ◽

Control Data ◽

Stability And Control ◽

And Control

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Estimation of Lateral/Directional Static Stability Characteristics of a Turboprop Aircraft at one Engine Inoperative Condition

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.842.208 ◽

2016 ◽

Vol 842 ◽

pp. 208-216 ◽

Cited By ~ 1

Author(s):

Ratna Ayu Wandini ◽

Taufiq Mulyanto ◽

Hari Muhammad

Keyword(s):

Short Distance ◽

Fuel Efficiency ◽

Aircraft Design ◽

Static Stability ◽

Slip Angle ◽

High Fuel Efficiency ◽

Stability And Control ◽

Conceptual Design Phase ◽

The Stability ◽

And Control

Twin engines turboprop aircraft provides the most beneficial solution to meet the needs of short distance flight due to high fuel efficiency [1]. One of the emergency conditions which has to be considered for this type of the aircraft when one engine is out operating or one engine inoperative because it involves the safety of flight. Furthermore, a safe flight with one engine inoperative is regulated by FAR/CASR Part 25 and has to be complied during certification .Stability and control characteristics of a turboprop aircraft will change significantly if one engine inoperative condition occurs during cruise phase. The rudder and/or aileron deflections to counter the yawing and rolling moments due to the thrust of the operating engine must satisfy. Recognizing the importance of that consideration, this research will estimate the stability and control characteristics of lateral/directional in one engine inoperative condition on new turboprop 80-pax aircraft design concept.This paper presents procedures for estimating the lateral/directional static stability characteristics of a 80-pax turboprop aircraft during the conceptual design phase. The size of the rudder and aileron have to be iterated to fullfil the requirements at a condition when one engine is not operative. The rudder and the aileron deflections are estimated as functions of airspeed, roll angle, side slip angle and thrust setting. It will be shown in this paper that the required rudder deflection as well as aileron deflection can satisfy to balance the forces and moments due to asymmetrical thrust condition and the minimum control speed of the aircraft can be maintained as well.

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