Structural Design Optimisation and Aerothermoelastic Analysis of LAPCAT A2 Mach 5 Cruise Vehicle

Sharifzadeh, Shayan; Hendrick, Patrick; D'Mello, Shaun; Verstraete, Dries; Thirifay, François

doi:10.2514/6.2014-2294

Cited by 5 publications

(4 citation statements)

References 3 publications

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“…Consequently the vehicle will be subject to significant aeroelastic effects which could result in structural divergence or control instabilities. Cenaero carried out the coupling of ULB preliminary wing (and fuselage) structure model of the Mach 5 A2 vehicle with Cenaero's aero-thermo-elastic platform [10] [11]. The aero-thermo-elastic calculation is shown to be functional and robust.…”

Section: A2 Vehicle Structural Design and Aero-elasticity Assessmentmentioning

confidence: 99%

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Steelant¹,

Varvill²,

Defoort³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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The design of hypersonic airbreathing vehicles is a challenging objective due to the intrinsic complexity of propulsion-airframe integration in combination with an engine cycle design able to operate over a wide Mach number range. This is one of the objectives of EC co-funded project LAPCAT-II aiming to reduce antipodal flights to less than 2 to 4 hours. Among the several studied vehicles in the preceding project LAPCAT-I, only aircraft designs for Mach 5 and 8 flights were retained in the present project. Starting from the available Mach 5 vehicle and its related pre-cooled turbo-ramjet, assumed performance figures of different components were now assessed in more detail numerically and experimentally. Though the cruise flight of the Mach 8 vehicle based on a scramjet seemed feasible, further refinement was needed. In support to the integrated vehicle design, dedicated aerodynamic and propulsive experiments were done for the different components as well as for the complete vehicle. This included also the mutual verification of the windtunnels within Europe. In parallel, modelling implementation and validation on high-speed aerodynamics and propulsion were performed. The validated tools gave confidence to assess the performances of the fully integrated vehicles to comply with the mission goals. Finally, the impact of the emissions onto the climate was evaluated. Nomenclature

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Section: A2 Vehicle Structural Design and Aero-elasticity Assessmentmentioning

confidence: 99%

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Steelant¹,

Varvill²,

Defoort³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…(1) LAPCAT concepts [37]- [39]: MR2.4/M4.5/M8/A2 scenarios. (2) Other hypersonic concepts: HyperSoar 2000 [40], [41], NASP X30 [42], NASA Ma6 Transport/Fighter [43], and recalculated Scale 1 PREPHA Vehicle [38].…”

Section: B Subsystem 1: Structurementioning

confidence: 99%

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

et al. 2019

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In the design of hypersonic cruise vehicles, great effort is demanded to improve the performances of subsystems, namely structure, aerodynamics, and propulsion. Herein, effort demanded to realize a subsystem performance is quantified by technical merit. To achieve a feasible design, excessive technical merit of any one subsystem should be avoided. Accordingly, a lowest-technical-merit (LTM) design methodology has been proposed in this work. By this methodology, the design problem could be interpreted into a parametric optimization. The solution to such an optimization corresponds to the highest feasibility. The methodology has been implemented on two cases: deriving a hydrocarbon-fueled long-range cruiser from Boeing X-51A, and a hydrogen-fueled LAPCAT scenario from PREPHA. The simulation results show that LTM could achieve optimal allocations while satisfying different payload/range performances. The design methodology could help to improve the feasibility of hypersonic cruise vehicles. Furthermore, it could also be used in the design of other systems.

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“…Moreover, the reduction in structural rigidity requires a strong focus on aerothermoelastic deformations in the design and optimization of the aircraft structure. 13) Bhungalia et al developed a thermal protection system design and optimization procedure for the Affordable Responsive Spacelift (ARES) Booster. 14) A novel global optimization strategy using adaptive radial basis functions based on fuzzy clustering developed by Zhu et al was used to optimize a lifting surface.…”

Section: Introductionmentioning

confidence: 99%

“…15) The study of Sharifzadeh et al presented how different sizing, analysis, design and optimization tools were coupled in designing the structure for long-term advanced propulsion concepts and technologies (LAPCAT) A2 vehicle and reported the results of optimizing the A2 canard and wing. 13) Research regarding the multidisciplinary optimization of hypersonic vehicles with uncertainties are relatively insufficient.…”

Section: Introductionmentioning

confidence: 99%

Robust Aeroelastic Design Optimization of Hypersonic Wings Considering Uncertainty in Heat Flux

Wan

Yang

2017

Trans. Japan Soc. Aero. S Sci.

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A robust aeroelastic optimization design methodology for hypersonic wings considering uncertainty in heat flux is presented and applied to a design process of a typical hypersonic low-aspect-ratio wing. An interval analysis method is used to perform the transient heat transfer analysis with uncertainty in heat flux within the newly developed aerothermoelastic framework. A genetic algorithm is used to build the framework for robust optimization, and it is also used to determine the critical thermal load case from an interval temperature field obtained using interval heat transfer analysis. Aerothermoelastic analysis of the hypersonic wing shows that the structure may bear a severely worsening thermal environment when there is uncertainty in heat flux during hypersonic flight. Not merely the average temperature, but also the temperature gradient distribution of the structure rises, which might make designs created using deterministic analysis methods unreliable. Optimization results show that the robust optimization design methodology can provide a relatively light structural design and simultaneously make sure it is capable of satisfying multiple constraints under severe thermal environments with uncertainty.

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Structural Design Optimisation and Aerothermoelastic Analysis of LAPCAT A2 Mach 5 Cruise Vehicle

Cited by 5 publications

References 3 publications

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

Robust Aeroelastic Design Optimization of Hypersonic Wings Considering Uncertainty in Heat Flux

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