中文摘要：

对某吸气式高超声速导弹的爬升和巡航段航程进行了优化设计。该导弹为面对称构形,采用火箭基组合循环（RBCC）动力系统。利用非均匀有理B样条（NURBS）对设计变量进行参数化描述,得到非线性参数优化问题,并采用遗传算法求解。对马赫数为5、6、7的3种不同巡航速度下的计算结果进行了分析。结果表明,对于燃油经济性而言,该高超声速导弹的巡航速度不宜太高,在相同燃油消耗总量条件下,马赫数为5巡航时的航程最远。

英文摘要：

The trajectory of an air-breathing hypersonic missile with slender body and thin airfoil is opti- mized. The missile is powered by a rocket based combined cycle （RBCC） system which combines modes of rocket and ramjet. The design objective is to maximize the cruise range for a given amount of fuel con- sumption. The design variables are parameterized by using non-uniform rational B-spline（NURBS）. Con- sequently, the original optimal control problem is converted into an equivalent nonlinear parameter opti- mization problem which is then solved by using genetic algorithm. Results for three different cruise speeds, i.e. 5, 6 and 7 Ma, are obtained and compared. The results show that, for fuel economy, the cruise speed of the missile should not be too high. For the missile considered, under the condition of the same amount of fuel consumption, the alternative with the cruise speed of 5 Ma is able to attain the longest range.