Integrated Design of a Model-Scale Gas Turbine Powered Flapless Demonstrator Aircraft: A Case Study

Wilde, Paul; Gill, Kenneth J.; Michie, Stephen; Sparks, Richard H.; Crowther, William

doi:10.2514/6.2007-7727

Cited by 5 publications

(3 citation statements)

References 2 publications

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“…Second, this moment is converted into a required momentum coefficient using historical understanding of typical achievable control gains, and third, a valid slot geometry is defined that is able to deliver the required momentum whilst meeting requirements for control efficiency and effectiveness, and manufacturing constraints. The data used to inform the sizing process comes from various sources, including subscale wind tunnel experiments (6,18,21,24,25) , data sheets (26)(27)(28) , 1d flow pipe simulation (29) , theoretical analysis (14,21,24,30) and heuristics based on previous successful flow control implementations (3,7,14,15,24,(31)(32)(33)(34)(35) .…”

Section: Fluidic Thrust Vectoring Design Variablesmentioning

confidence: 99%

Towards Integrated design of fluidic flight controls for a flapless aircraft

Crowther¹,

Wilde

Gill

et al. 2009

Aeronaut. j.

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Fluidic flight controls enable forces and moments for flight vehicle trim and manoeuvre to be produced without use of conventional moving surface controls. This paper introduces a methodology for the design of Circulation Control (CC) and Fluidic Thrust Vectoring (FTV) as fluidic controls for roll and pitch. Work was undertaken as part of the multidisciplinary FLAVIIR project, with the goal of providing full authority fluidic flight controls sufficient for a fully flapless flight of an 80kg class demonstrator aircraft known as DEMON. The design methodology considers drag, mass, volume and pneumatic power requirements as part of the overall design cost function. It is shown that the fundamental flow physics of both CC and FTV are similar, and hence there are strong similarities to the design approach of each. Flight ready CC and FTV hardware has been designed, manufactured and ground tested. The CC system was successfully wind tunnel demonstrated on an 85% scale half model of the DEMON. The design condition of a control ΔC L of 0⋅1 was achieved with a blowing coefficient of 0·01, giving a useable control gain of 10. The FTV system was static tested using a micro gas turbine source. The control characteristic was 'N' shaped, consisting of an initial high gain response in a negative sense (gain = -30) followed by a low gain response in a positive sense (gain = +3) at higher blowing rate. CC and FTV control hardware directly contributes to around 6% to the overall mass of the flight vehicle, however provision of pneumatic power carries a significant mass penalty unless generated as part of an integrated engine bleed system.

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Section: Fluidic Thrust Vectoring Design Variablesmentioning

confidence: 99%

Towards Integrated design of fluidic flight controls for a flapless aircraft

Crowther¹,

Wilde

Gill

et al. 2009

Aeronaut. j.

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“…Meanwhile, SACCON is also under development [17]. Other works include Santos UAV [18] and JAVA UAV from [19][20][21]. Ref.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Aerodynamic Characteristics of an Active Jets-Matrix Serving as Pitch Control Surface

2022

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To facilitate future Hypersonic Flight Vehicle (HFV) implementation with high maneuverability throughout its reentry trajectory, an Active Jets-Matrix (AJM) is designed to serve as the flapless pitch control surface. The AJM consists of four control groups composed in total of 48 supersonic nozzles. The AJM aims to utilize the jet flow-interaction-induced additional control moment to improve the control efficiency during atmospheric entry. A comparative research method is employed to study the eight simulation cases for three different HFV configurations (baseline, mechanical control surface with 30° deflection, and the AJM configuration) and two AJM control moment adjustment strategies (nozzle chamber pressure regulation and discretized nozzle group on–off control). A conventional in-house computational fluid dynamics (CFD) solver with the two-equation SST turbulence model is employed to undertake the simulation tasks. Simulation results indicate that: (a) only the AJM configuration is capable of trimming the HFV in pitch channel; (b) nonlinearity exists between the augmentation moment and the specific control variable from respective adjustment strategies; (c) the chamber pressure regulation strategy bears higher overall efficiency, while the discretized control strategy induces more intense local jet-flow interaction. With a maximum control moment augmentation of 1.58, the AJM presents itself as a competitive candidate for future HFV flapless control methods.

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“…Schematic diagrams of typical flow control methods are shown in Figs 1(a) and (b). Further details regarding the actuation technology can be found in references [4] to [6].…”

Section: Introductionmentioning

confidence: 99%

Computational investigation of the DEMON unmanned air vehicle thrust vectoring system

Buonanno

Drikakis

Papachristou

et al. 2009

Proceedings of the Institution of Mechanical Engineers, Part G:

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A computational investigation of the interaction of the vectored primary jet from the main engine with the subsonic flow around a tailless unmanned air vehicle (UAV) configuration, with a cropped diamond wing planform, has been carried out. An initial study has been completed using Reynolds-averaged Navier-Stokes methods in conjunction with the shear-stress transport k-ω model. Various sets of simulations were performed on the basis of quantifying the thrust vectoring (TV) jet entrainment effects by means of aerodynamic forces and moments when key factors are combined, such as angles of thrust velocity deflection at different jet Mach number and angles of attack. It was found that reaction forces induced by the modified pressure on the integrated boundary of the body results in an enhancement of the TV effectiveness in producing the forces and moments required for the flight vehicle trim and manoeuvring. Those reaction forces were found to be independent of the angle of attack.

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Integrated Design of a Model-Scale Gas Turbine Powered Flapless Demonstrator Aircraft: A Case Study

Cited by 5 publications

References 2 publications

Towards Integrated design of fluidic flight controls for a flapless aircraft

Towards Integrated design of fluidic flight controls for a flapless aircraft

Numerical Investigation on Aerodynamic Characteristics of an Active Jets-Matrix Serving as Pitch Control Surface

Computational investigation of the DEMON unmanned air vehicle thrust vectoring system

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