This paper studies the problem of tradeoff optimization between damage of reusable liquid propellant rocket engine's turbine blade and control input sequences during the start-up process.
针对可重复使用液体火箭发动机起动过程，研究了系统控制输入序列的变化对以涡轮叶片为代表的关键部件累积损伤的影响。
The multiple objective optimization approach is applied to GP and provides a tradeoff between the solution performance and the complexity.
文章在遗传规划中引入了多目标优化方法，寻求在解的性能和复杂度之间的均衡。
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