| 1. | 10 maximum thrust force of top drive power head 30 kn
10动力头最大给进力30 kn |
| 2. | 10 maximum thrust force of top drive power head 15 kn
10动力头最大给进力15 kn |
| 3. | Maximum thrust force of top drive power head 15 kn
9动力头最大给进力kn 15 |
| 4. | Stand by . we ' re going to maximum thrust
准备，我们要加速了 |
| 5. | Hardware - in - loop simulating system of ifpc is built to research the digital simulations , which are conducted with two optimization modes : maximum thrust mode and minimum fuel consumption mode
构建了实物在回路的飞推综合控制仿真试验系统，进行了最大推力模式和最小油耗模式的优化仿真试验。 |
| 6. | The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation , indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design
表明在引射火箭设计时，应结合引射火箭的结构和流动参数对二次喷管出口面积进行优化设计，以达到最佳推力性能。 |
| 7. | Simulation results presented here demonstrate that during accelerating flight at constant altitude thrust increases up to approximately 12 percent in the maximum thrust mode , and at subsonic cruise specific fuel consumption decreases up to 2 percent in the minimum fuel consumption mode
试验结果表明两种优化模式下，飞推综合控制的优化算法可以显著提高发动机性能，也验证了该优化计算机设计方案是可行的。 |
| 8. | The results indicate that with decrease of exit area of secondary nozzle , the bypass ratio is decreasing , and the static pressure in integrated ejector combustor is increasing , and mixing condition becomes better . there exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector
结果表明：引射能力随着二次喷管出口面积的减小而减小；整体式引射燃烧室压强随着二次喷管出口面积的减小而上升，混合随之更为充分；存在一个最优的二次喷管出口面积，使发动机推力最大。 |
