Latin hypercube sampling applied to reliability-based multidisciplinary design optimization of a launch vehicle

The performance requirements for the next generations of airliners are stringent and require invention and design of unconventional configurations departing from the classical Cayley functional dec 

Towards a unified framework using CPACS for geometry management in aircraft design

Advanced studies have been undertaken using Multidisciplinary Design Optimization (MDO) on the retrofitting of an outboard morphing wing system to an existing conventionally designed commercial passenger jet. Initial studies focusing on the single objective of specific air range improvement for a number of flight phases revealed increases of approximately 4-5% over the baseline aircraft with wing fences across each case. This validated the advantage of re-optimizing the geometric schedules for off-design conditions in comparison with fixed winglets, for which negative effects were observed. Due to the high number of design sensitivities of the outboard wing geometry it has now become necessary to conduct refined studies to analyse the effects of the wing system on additional operational performance metrics, such as take-off, initial climb, approach-climb and landing performance parameters, in order to ascertain a truly holistic representation of the benefits of morphing wing technology. In addition, further effort has been expended to couple the effects of each phase within a multiobjective framework. Thus, refined studies have been performed, incorporating a number of multiobjective optimization methods into a high-end, low fidelity aero-structural-control analysis together with a full engine model and integrated operational performance algorithm. Furthermore, updated aeroelastic functionality and improved aero-structural wing sizing allows for investigation of C-wing configurations. Results reveal the potential for significant field length reductions and climb performance enhancements, while maintaining improvements in cruise performance throughout the entire flight envelope and across multiple stage lengths.

/pdf/multi-objective-optimization-for-the-multiphase-design-of-42nlzhysm5.pdf

Multi-objective optimization for the multiphase design of active polymorphing wings

In the scope of this thesis, a methodology for modeling of entire system architectures of commercial transport aircraft is presented. The author’s approach facilitates technology assessment of innovative system technology on aircraft-level in conceptual and early preliminary aircraft design. It closes the existing gap of sound systems modeling in early aircraft design synthesis. The proposed methodology uses a strictly function-driven approach for sizing of the single aircraft systems according to the dedicated aircraft-level functions. System weight and maximum as well as mission dependent power off-takes are estimated. The principle of energy balance is used to derive the power demand of the single systems. A modular and flexible approach has been chosen that allows for fast variation of the system architecture. Thus, investigation of large design spaces is possible. For integration and assessment of innovative systems technology, a probabilistic framework is introduced that incorporates remaining uncertainties. The proposed system model has been integrated into the Institute’s of Aeronautics and Astronautics (ILR) Multidisciplinary Integrated Conceptual Aircraft Design and Optimization (MICADO) environment. Thus, repercussions of system integration, e.g. on aircraft efficiency or performance, can be captured in a highly integrated environment. The proposed systems model is a valuable tool for sound assessment of innovative system technology on overall aircraft-level already in conceptual aircraft design. The proposed systems model has been validated against two commercial transport aircraft. Additionally, comprehensive sensitivity studies show dependencies and identify the main design drivers of the single systems. Two case studies show the added-value of integration of the proposed systems model into early aircraft design synthesis. The first case study concentrates on evaluation of the impact of engine power off-takes on aircraft performance and efficiency. The second design study focuses on integration of innovative technology into the overall system architecture and on application of the proposed probabilistic framework for considering the remaining uncertainties in design and technology assessment.

Integration of aircraft systems into conceptual design synthesis

Composite structures can lower the weight of an airliner significantly. The increased production cost, however, requires the application of cost-effective design strategies. Hence, a comparative va ...

/pdf/cost-weight-optimization-of-aircraft-structures-1slqxd2paj.pdf

Cost/Weight Optimization of Aircraft Structures

Research into the improvement of the Aircraft ConceptualDesign process by the application of MultidisciplinaryOptimization (MDO) is presented. Aircraft conceptual designanalysis codes were incorpor ...

/pdf/enhancing-aircraft-conceptual-design-using-multidisciplinary-4d3c0b2ekl.pdf

Enhancing Aircraft Conceptual Design using Multidisciplinary Optimization

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Enhancing Aircraft Conceptual Design using Multidisciplinary Optimization