Parametric Design Method and Lift/Drag Characteristics Analysis for a Wide-Range, Wing-Morphing Glide Vehicle

• Published in: Aerospace Vol. 11; no. 4; p. 257
• Main Authors: Jin, Zikang, Yu, Zonghan, Meng, Fanshuo, Zhang, Wei, Cui, Jingzhi, He, Xiaolong, Lei, Yuedi, Musa, Omer
• Format: Journal Article
• Language: English
• Published: Basel MDPI AG 01.04.2024
• Subjects: aerodynamic shape optimization; Configurations; Deformation; Design; Design and construction; Drag; Drag coefficients; Engineering; Genetic algorithms; hypersonic; Hypersonic planes; Hypersonic vehicles; Lift; Mathematical optimization; Morphing; Optimization; parameter modeling; Payloads; Preliminary designs; Pressure distribution; Shape optimization; UG secondary development; Vehicles; wide range; wing morphing; China
• ISSN: 2226-4310; 2226-4310
• DOI: 10.3390/aerospace11040257

The parametric design method is widely utilized in the preliminary design stage for hypersonic vehicles; it ensures the fast iteration of configuration, generation, and optimization. This study proposes a novel parametric method for a wide-range, wing-morphing glide vehicle. The whole configuration, including a waverider fuselage, a rotating wing, a blunt leading edge, rudders, etc., can be easily described using 27 key parameters. In contrast to the typical parametric method, the new method takes internal payloads into consideration during the shape optimization process. That is, the vehicle configuration can be flexibly adjusted depending on the internal payloads; these payloads may be of random amounts and have different shapes. The code for the new parametric design method is developed using the secondary development tools of UG (UG 10.0) commercial software. The lift and drag characteristics over a wide operational range (H = 6–25 km, M = 2.5–8.5, AOA = 0–10°) were numerically investigated, as was the influence of the retracting angle of the morphing wings. It was found that, for the mode of the fully deployed wings, the lift-to-drag ratio (L/D) remained at a high level (≥4.7) over a Mach range of 4.0–8.5 and an AOA range of 4–7°. For the mode of the fully retracted wings, the drag coefficient remained smaller than 0.02 over a Mach range of 4.0–8.5 and an AOA range of 0–5°. A wide L/D of 0.3–4.7 could be achieved by controlling the retracting angle of the wings, thus demonstrating a good potential for flight maneuverability. The flexible change in L/D proved to be a combined result of varying pressure distribution and edge-flow spillage. This will aid in the further optimization of lift/drag characteristics.