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RISS 인기검색어
- 검색키워드
- 저자 : Xiongqing Yu (검색결과 4 건)
- 무료
- 기관 내 무료
- 유료
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A Study on Blended Inlet Body Design for a High Supersonic Unmanned Aerial Vehicle
You, Lianxing,Yu, Xiongqing,Li, Hongmei The Korean Society for Aeronautical and Space Scie 2016 International Journal of Aeronautical and Space Sc Vol.17 No.2
The design process of blended inlet body (BIB) for the preliminary design of a near-space high supersonic unmanned aerial vehicle (HSUAV) is presented. The mass flow rate and cowl area of inlet at a design point are obtained according to the cruise condition of the HSUAV. A mixed-compression axisymmetric supersonic inlet section with a fixed geometry reasonably matching the high supersonic cruise state is created by using the inviscid theory of aerodynamics. The inlet section is optimized and used as a baseline section for the BIB design. Three BIB concepts for the HSUAV are proposed, and their internal aerodynamic characteristics of inlet are evaluated using Euler computational fluid dynamics (Euler CFD) solver. The preferred concept is identified, in which the straight leading edge of the baseline HSUAV configuration is modified into the convex leading edge to accommodate the inlet and meet the requirements of the cowl area to capture the sufficient air flow. The total recovery of inlet for the preferred BIB concept and the aerodynamic characteristics of the modified HSUAV configuration are verified using Navier-Stokes computational fluid dynamics (NS CFD) solver. The validation indicates that the preferred BIB concept can meet both the requirements of the inlet and aerodynamic performance of the HSUAV.
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A Study on Blended Inlet Body Design for a High Supersonic Unmanned Aerial Vehicle
Lianxing You,Xiongqing Yu,Hongmei Li 한국항공우주학회 2016 International Journal of Aeronautical and Space Sc Vol.17 No.2
The design process of blended inlet body (BIB) for the preliminary design of a near-space high supersonic unmanned aerial vehicle (HSUAV) is presented. The mass flow rate and cowl area of inlet at a design point are obtained according to the cruise condition of the HSUAV. A mixed-compression axisymmetric supersonic inlet section with a fixed geometry reasonably matching the high supersonic cruise state is created by using the inviscid theory of aerodynamics. The inlet section is optimized and used as a baseline section for the BIB design. Three BIB concepts for the HSUAV are proposed, and their internal aerodynamic characteristics of inlet are evaluated using Euler computational fluid dynamics (Euler CFD) solver. The preferred concept is identified, in which the straight leading edge of the baseline HSUAV configuration is modified into the convex leading edge to accommodate the inlet and meet the requirements of the cowl area to capture the sufficient air flow. The total recovery of inlet for the preferred BIB concept and the aerodynamic characteristics of the modified HSUAV configuration are verified using Navier-Stokes computational fluid dynamics (NS CFD) solver. The validation indicates that the preferred BIB concept can meet both the requirements of the inlet and aerodynamic performance of the HSUAV.
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Layout Optimization for Blended Wing Body Aircraft Structure
Wensheng Zhu,Xiongqing Yu,Yu Wang 한국항공우주학회 2019 International Journal of Aeronautical and Space Sc Vol.20 No.4
Structural layout design of blended wing body (BWB) aircraft in the preliminary design phase is a challenging optimization problem due to large numbers of design variables and various constraints. A two-loop optimization strategy is proposed to solve the BWB aircraft structural layout design problem considering constraints of the displacement, stress, strain, and buckling. The two-loop optimization consists of an inner loop and an outer loop. The inner loop is to optimize each stiffened panel of the BWB aircraft structure, and outer loop is to find the best layout design. To improve computational efficiency, an equivalent finite element model is applied to BWB aircraft structure analysis, and an analytical method is used for buckling and static analysis of the stiffened panels. The proposed method can efficiently solve the structural layout optimization problem of a notional BWB aircraft with acceptable computational burden. The result indicates the mass of main load-carrying structure of the BWB aircraft is reduced by 9.28% compared to that of the initial structural layout.
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A Holistic Method Determining Takeoff Field Length Requirement for Commercial Aircraft
Zhouwei Fan,Xiongqing Yu 한국항공우주학회 2022 International Journal of Aeronautical and Space Sc Vol.23 No.3
The takeoff field length (TOFL) requirement is one of the top-level aircraft requirements. This requirement has a direct impact on airport compatibility, and also has a significant impact on aircraft direct operating cost (DOC) and airport environmental issues. A holistic method is proposed to determine the TOFL requirement of commercial aircraft, in which targeted operation airports, DOC and environmental issues are all considered rationally. The major steps of the method include normalizing runway lengths of the targeted operation airports, aircraft concept design and analysis, TOFL and DOC tradeoff through the multi-objective optimization. A case study for notional wide-body commercial aircraft is used to illustrate and verify the proposed method. The TOFL requirement is determined logically according to the procedure of the method. As a result, the most reasonable TOFL requirement for this case study should be less than 2400 m. Under this TOFL requirement, the aircraft can takeoff at 95% of the targeted operation airports with maximum takeoff weight as well as meet environmental requirements. Compared to the concept with TOFL of 2700 m, the airport compatibility is increased by 10.5% with 2.4% DOC penalty.
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