| 引用本文: | 严旭飞,陈仁良.倾转旋翼机短距起飞单发失效着陆的轨迹优化[J].哈尔滨工业大学学报,2017,49(10):38.DOI:10.11918/j.issn.0367-6234.201604113 |
| YAN Xufei,CHEN Renliang.Trajectory optimization of tilt-rotor aircraft landing in short takeoff after one engine failure[J].Journal of Harbin Institute of Technology,2017,49(10):38.DOI:10.11918/j.issn.0367-6234.201604113 |
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| 摘要: |
| 为进一步改善倾转旋翼机短距起飞单发失效后着陆轨迹优化的操纵策略，建立适用于倾转旋翼机单发失效后轨迹优化的增广飞行动力学模型并进行计算分析.首先，在基本纵向刚体模型的基础上建立关于操纵量的代数方程和微分方程组，形成增广飞行动力学模型，从而能反映出旋翼拉力系数、后倒角与驾驶员操纵杆量之间的关系，同时也能在轨迹优化中考虑到操纵系统特性对操纵量变化速度的限制，避免操纵量在优化过程中跳跃不连续；然后，采用直接转换法将着陆过程中的最优操纵策略和最优轨迹问题转化为非线性规划问题，并使用序列二次规划算法进行求解；最后，以XV-15倾转旋翼机为例，计算了短距起飞单发失效后安全着陆的最优解，并与相关文献数据进行对比.结果表明, 在飞行路径、地速、旋翼转速和俯仰角的变化趋势与文献基本一致的情况下，需用功率、拉力系数与纵向周期变距杆位移等变化更加柔和，此外优化结果还包含了现有方法无法得到的操纵量和操纵速率信息.由增广飞行动力学模型得到的轨迹优化结果可以为单发失效时驾驶员实施安全着陆提供更多有用的依据.
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| 关键词: 倾转旋翼机 单发失效 轨迹优化 飞行动力学模型 序列二次规划 |
| DOI：10.11918/j.issn.0367-6234.201604113 |
| 分类号:V212.4 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(11672128) |
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| Trajectory optimization of tilt-rotor aircraft landing in short takeoff after one engine failure |
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YAN Xufei,CHEN Renliang
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(National Key Laboratory of Rotorcraft Aeromechanics (Nanjing University of Aeronautics and Astronautics), Nanjing 210016, China)
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| Abstract: |
| The augmented flight dynamic model for trajectory optimization is built to improve the optimal control strategy of trajectory optimization for tilt-rotor aircraft landing in short takeoff after one engine failure. The longitudinal rigid-body flight dynamic model is augmented with a set of algebra equations describing the relationship between the aerodynamic forces and controls in the cockpit, and a set of differential equations describing the control rates to avoid jump discontinuities of controls in the trajectory optimization. The trajectory optimization problem is transformed into a nonlinear programming problem and solved by a sparse sequential quadratic programming. The XV-15 tilt-rotor aircraft is taken as a sample for the investigation. The optimal solutions are calculated and compared with those obtained in the relevant reference. The results indicate that the augmented flight dynamic model can provide more longitudinal control information such as the collective control input, the root collective pitch, the longitudinal cycle pitch and the rates of control variables. In addition, the time histories of power required, thrust coefficient and longitudinal stick are more relatively gentle. Therefore, the presented method can provide pilots more useful references to perform the landing procedure.
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| Key words: tiltrotor one engine failure trajectory optimization flight dynamic model sparse sequential quadratic programming |
