Multi-Points Integrated Airframe/Engine Configuration Optimization of Hypersonic Vehicle
- Paper number
IAC-16,C4,9,13,x32413
- Coauthor
Ms. Qing Wang, College of Mechanical and Electrical Engineering, Xi'an Polytechnic University, China
- Year
2016
- Abstract
Integration design and optimization of airframe/engine is a remarkable characteristic for hypersonic vehicle. Furthermore, engine is required to work efficiently through a wide envelop of Mach numbers (Ma) usually. As a result, conventional single-point based design method will be not proper for airframe/engine design and new design methods are needed badly. Aiming at solving this problem, the paper focuses on an integrated airframe/engine configuration design and optimization, using a multi-point design method. Based on this methodology, an optimal integrated airframe/engine configuration, which works well over a range of flight conditions, can be searched. Chosen coefficients of thrust, lift and moment as objective functions, a three-point optimization was done and an optimal integrated airframe/engine configuration was found, based on Design of Experiment (DOE) and surrogate model. Then, performances of the optimal configuration were computed in a wide envelop of Mas and angles of attack (AOAs). Comparing performances of the optimal configuration with a baseline one optimized on a single-point, it’s found that optimal integrated airframe/engine configuration has a better performances through a wide flight envelop than the baseline one. It confirmed the effectiveness and superiority of multi-points optimization method used in integrated airframe/engine configuration design.
- Abstract document
- Manuscript document
(absent)