| 柳亚冰1，符大伟2，蔡常鹏2，孙丰勇1，张海波2.轴对称矢量喷管空间运动学建模仿真[J].航空发动机,2020,46(6):33-40 |
| 轴对称矢量喷管空间运动学建模仿真 |
| Modeling and Simulation of Spatial Kinematics of Axisymmetric Vectoring Nozzle |
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| DOI： |
| 中文关键词: 轴对称矢量喷管 空间运动学建模 动态偏转轨迹 偏转规律 航空发动机 |
| 英文关键词:axisymmetric vectoring nozzle spatial kinematics modeling dynamic deflection trajectory deflection law aeroengine |
| 基金项目:国家自然科学基金（51576096）、中央高校科研业务费重大人才培育项目（NF2018003）资助 |
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| 中文摘要: |
| 为了获得轴对称矢量喷管动态偏转轨迹的最优路径，提出了1 种基于运动学位移解算的解决方法。通过空间运动约束
分析建立了描述轴对称矢量喷管复杂空间运动的平衡方程，经解算建立了描述矢量角与作动筒位移映射关系的2 维插值模型。基
于运动学模型仿真中喷管喉道截面与出口截面几何中心距离不变的结论，建立矢量角与中心坐标的简化关系并设计各控制周期下
矢量角动态指令偏转规律。仿真结果表明：该解决方案基本可以保证动态偏转下矢量轨迹满足预期要求。 |
| 英文摘要: |
| In order to obtain the optimal path of the dynamic deflection trajectory of axisymmetric vectoring nozzle ，a solution was
proposed based on kinematic displacement calculation. An equilibrium equation describing complex spatial motion of axisymmetric
vectoring nozzle was established by space motion constraint analysis. A 2-D interpolation model describing the mapping relationship
between vector angle and actuator displacement was established by solving the equations. Based on the conclusion that the geometric center
distance between nozzle throat section and outlet section was constant in kinematics model simulation，the simplified relationship between
vector angle and center coordinate was established and the deflection law of vector angle dynamic command was designed in each control
cycle. The simulation results show that the solution can basically ensure that the vector trajectory meets the expected requirements under
dynamic deflection. |
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