Aircraft Fuel Systems

Langton, Roy; Clark, C. S.; Hewitt, Martin; Richards, Lonnie

doi:10.2514/4.479632

Cited by 29 publications

(16 citation statements)

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“…Concorde) aircraft are commonly required for being able to artificially move CG through pumping fuel forward and backward in equilibrium fuel tanks, which can be easily implemented by automatic control of computers. 43 In the present case, artificially adjusting the CG b would result in significant movement of the CG t , and the effects of the CG b movement on the stability and lift-to-drag ratios will be demonstrated in the ''Conclusions'' section. In addition, no any flexibility of wings was considered in the investigation, which is worth studying in the future.…”

Section: Movement Of Center-of-gravitymentioning

confidence: 75%

Aerodynamic evaluation of an unmanned aerial vehicle with variable sweep and span

Gong

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Morphing aircraft can achieve optimum performances at multiple flight conditions through large geometry deformations. However, to obtain the optimum configurations, optimization design studies are required. A study on aerodynamic optimization of a morphing aircraft was conducted to obtain corresponding optimal configurations at various flight speeds. Firstly, an optimization framework being suitable to a morphing aircraft with larger deformations was established by integrating existing codes, in which aerodynamic forces for the optimization are calculated by an Euler-based solver and friction/form drag estimation code. The solver is based on a Cartesian method in which configurations are modeled in terms of components of aircraft, hence large deformations of morphing aircraft can be performed during the optimization. A surrogate-based model was employed for fitting aerodynamic forces, thus reducing computational cost in a global optimization. A generic morphing aircraft with variable sweep and span was investigated at subsonic, transonic, and supersonic conditions through the optimization process. The target of optimization is to obtain maximum lift-to-drag ratios subject to lift, trim, and static stability constrains at each flight condition. The movement of center-of-gravity of the aircraft was also considered in optimization. The results indicate that the center-of-gravity has an important effect on the optimum configurations obtained, and the aerodynamic performance will be enhanced significantly if the center-of-gravity is moved backward at transonic and supersonic cases. In the case of movable center-of-gravity, the optimum sweep angles increase with the increase in flight speeds, and the optimum spans at transonic and supersonic speeds are smaller than the subsonic case.

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Section: Movement Of Center-of-gravitymentioning

confidence: 75%

Aerodynamic evaluation of an unmanned aerial vehicle with variable sweep and span

Gong

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…In cases such as loss of cabin pressure where the aircraft needs to descend rapidly to a breathable altitude, the venting system must be able to handle the large mass flow rate of air in order to avoid large pressure differences between the tank and the atmosphere (Langton et al. 2009).…”

Section: Aircraft Fuel Systemmentioning

confidence: 99%

ADOPT: An augmented set-based design framework with optimisation

et al. 2019

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During the early stages of any system design, a thorough exploration of the design space can prove to be challenging and computationally expensive. The challenges are further exacerbated when dealing with complex systems, such as an aircraft, due to the high dimensionality of their design space. Arising from the Toyota Product Development System, set-based design allows parallel evaluation of multiple alternative configurations in the early design stages. At the same time, optimisation methods can be employed at later stages to fine-tune the engineering characteristics of design variants. Presented in this paper, is the Augmented set-based Design and OPTimisation (ADOPT) Framework that introduces a novel methodology for integrating the two areas. This allows for a thorough design-space exploration while ensuring the optimality of the selected designs. The framework has been developed using a process-independent and tool-agnostic approach so that it can be applied to the design process of varying kinds of systems. To demonstrate the implementation and potential benefits, the framework has been applied to the design of a generic aircraft fuel system. The results from the case study and the framework itself are discussed, with a number of areas for further development and future work being identified and presented.

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“…Table 1 shows the properties 15 and the values calculated by employing equations (3) to (8). In Table 1, the content rate indicates the concentration of the The errors between the values of equation (3) and the ones of experiment are presented in Table 2. Even for the liquid of ¼ 302 cP, the maximum relative error is 6.0% at Q ¼ 1.1 Â 10 À5 m 3 /s.…”

Section: Bubble Diametermentioning

confidence: 99%

“…This contributes to the increase of the volatility of fuel and possibility of ignition. 3 Considering the accident and hazard assessment, CS 25.981 sets the requirement for aircraft to minimise the flammability of the fuel vapour and to avoid catastrophic failure due to ignition of fuel or gas. 4 For over ten years, on-board inert gas generation system (OBIGGS), which generates and injects inert gas into the fuel tank, has been developed to help aircraft satisfy the regulation.…”

Section: Introductionmentioning

confidence: 99%

Analytical investigation into the effects of nitrogen enriched air bubbles to improve aircraft fuel system water management

Terada

Lawson

Shahneh

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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In the aircraft fuel system, water–ice contamination within fuel tanks has been one of the most serious challenges. This issue was highlighted in 2008 by an accident triggered by restricted fuel flow due to the ice formation within the system. The on-board inert gas generation system, which is already installed on some aircraft to prevent the outbreak of fire in the fuel tank, is a potentially feasible method to improve the water management. This paper focuses on the impact of bubbles from the on-board inert gas generation system system on water in the fuel tank. In order to explore the bubble effect, the relationship between orifice configuration and bubble parameter was investigated by means of mathematical models and existing experimental data. Moreover, by combining a MATLAB code and the introduced bubble model, the effect of bubble size and rising speed on the water contamination in the fuel tank was observed. For the water absorption process, a new model was introduced using a mass transfer coefficient. Finally, this article concludes that the amount of accumulated water is dependent on the bubble size and rising speed, and an optimal bubble size or speed is predictable once the coefficient has been obtained.

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Aircraft Fuel Systems

Cited by 29 publications

References 0 publications

Aerodynamic evaluation of an unmanned aerial vehicle with variable sweep and span

Aerodynamic evaluation of an unmanned aerial vehicle with variable sweep and span

ADOPT: An augmented set-based design framework with optimisation

Analytical investigation into the effects of nitrogen enriched air bubbles to improve aircraft fuel system water management

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