Aerodynamic and flight dynamic iterative simulation method of a joined wing aircraft
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摘要:
根据连翼布局飞行器气动力和力矩的分布特点，建立了面向其气动部件的飞行力学数学模型。将计算流体力学(CFD)和飞行力学仿真结合，采用时间步长离散，建立了一个能通过气动计算和飞行力学相互迭代来完成仿真全过程的面向连翼布局飞行器气动部件的仿真平台，并且在仿真过程中能全程监测所有部件的气动、动力学、姿态和航迹参数的变化。通过该仿真平台对不同输入信号作用下的动力学响应分析了连翼布局飞行器纵向和横侧向的动力学特性。仿真分析结果表明：该连翼布局飞行器纵向具备静稳定性，但横侧向不具备静稳定性。同时，横向和航向运动耦合明显，符合荷兰滚运动偏航及侧滑振荡明显的主要特征。所提方法可为了解连翼布局飞行器本体及飞行动力学响应特性、飞行品质和飞行安全研究等工作提供分析基础。
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关键词:
- 连翼布局飞行器 /
- 计算流体力学(CFD) /
- 飞行动力学 /
- 动力学特性 /
- 仿真平台
Abstract:An aerodynamic component-oriented flight dynamic model of joined wing aircraft was established based on the joined wing aircraft aerodynamic force and moment distribution characteristic, and a simulation platform is established by combining the computational fluid dynamics and flight dynamic simulation method. The entire simulation is spatially discretized with time steps, and is executed by iterating Computational Fluid Dynamics (CFD) calculation along with the above joined wing aircraft flight dynamic model at each time step. Moreover, the platform is able to output the change of variables of interest, such as aerodynamics, mechanics, attitude and the space track of all components throughout the entire simulation process. Based on the dynamic response of the platform to different input signals, the longitudinal and lateral dynamic characteristics of the joined wing aircraft are analyzed. The simulation results show that the joined wing aircraft is longitudinally stable, but is not laterally stable. Lateral and directional motion couple clearly, and the yaw and side slip motion oscillations are in line with the main characteristics of the Dutch roll. The developed platform can provide a useful guideline for investigating the ontology system model, flight quality, flight safety analysis and flight dynamic response characteristics of the joined wing aircraft.
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图 1 连翼布局飞行器几何模型及坐标系定义
Figure 1. Joined wing aircraft's geometry model and coordinate system definition
图 2 连翼布局飞行器气动计算和飞行力学仿真平台流程
Figure 2. Flowchart of aerodynamic calculation and flight dynamic simulation platform for joined wing aircraft
图 3 连翼布局飞行器气动计算和飞行力学联合仿真流程
Figure 3. Joined wing aircraft's aerodynamic calculation and flight dynamic integrated simulation process
图 5 连翼布局飞行器气动计算验证性算例
Figure 5. Joined wing aircraft aerodynamic calculation verification cases
图 6 升降舵阶跃信号输入下的迭代仿真平台和小扰动线性化动力学响应对比
Figure 6. Comparison of dynamic responses of iterative simulation platform and small disturbance linearization with elevator step signal input
图 7 迭代仿真平台无输入信号时的动力学响应
Figure 7. Dynamic response of iterative simulation platform without input signal
图 8 迭代仿真平台升降舵脉冲信号输入时的动力学响应
Figure 8. Dynamic response of iterative simulation platform with elevator pulse signal input
图 9 迭代仿真平台升降舵阶跃信号输入时的动力学响应
Figure 9. Dynamic response of iterative simulation platform with elevator step signal input
图 10 升降舵脉冲输入下连翼布局飞行器各个气动部件横侧向力矩系数随时间的变化关系(S=1 m2, cA=1 m)
Figure 10. Time history of joined wing aircraft's aerodynamic component lateral moment coefficients under elevator pulse input (S=1 m2, cA=1 m)
表 1 定直平飞配平初始状态参数初值
Table 1. Trimmed parameter values of straightforward and level flight initial condition
参数 数值 α 0.0780802 β 0 u 98.345454 v 0 w 7.6944834 p 0 q 0 r 0 φ 0.001084 θ 0.078080 ψ 0 μ 0.001081 γ 0 χ 9.927×10-4 ue 98.64595 ve 0.097925 we 0 Xe 0 Ye 0 Ze 3000.0 m 6942.922 δe 0.220958 δT 0.400235 δa 6.5767×10-4 δr -0.001217 Err_D -9.0949×10-13 Err_C 1.56319×10-13 Err_L 4.77485×10-13 Err_Lroll -8.8818×10-16 Err_M 6.82121×10-13 Err_N 0 
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表 2 升降舵偏转对连翼布局飞行器各个气动部件的影响
Table 2. Elevator deflection effects on joined wing aircraft's aerodynamic components
气动部件 Cd Cc CL CLroll Cm Cn 前翼 0.0037 0 0.0173 0 0.0159 0 后翼 0.0025 0 0.0429 0 -0.0354 0 连接部 0.00001 0 0 0 0.00001 0 尾翼 0.4169 0 1.2078 0 -8.0913 0 机身 0.0574 0 0.0578 0 0.1087 0
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表 3 副翼偏转对连翼布局飞行器各个气动部件的影响
Table 3. Aileron deflection effects on joined wing aircraft's aerodynamic components
气动部件 Cd Cc CL CLroll Cm Cn 前翼 0.0018 0.0054 -0.0014 -0.4208 0.0062 -0.0109 后翼 0.5108 0.0451 -0.0252 -6.4906 0.0377 0.308 连接部 0.0004 -0.0338 -0.0003 0.0001 0.0008 0.0596 尾翼 0.0001 0.0005 -0.0035 0.012 0.0212 -0.0034 机身 0.0032 0.1007 0.0186 -0.024 -0.0982 -0.3187
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表 4 方向舵偏转对连翼布局飞行器各个气动部件的影响
Table 4. Rudder deflection effects on joined wing aircraft's aerodynamic components
气动部件 Cd Cc CL CLroll Cm Cn 前翼 0.0013 0.0011 0.0039 -0.0059 0.0039 -0.0026 后翼 0.0005 0.0029 0.0144 -0.0043 -0.0294 -0.0007 连接部 0.0003 0.0012 -0.0002 0.0006 0.0007 -0.0016 尾翼 0.1962 0.0058 0.0118 0.3097 -0.068 -0.0348 机身 0.0838 0.6954 0.0238 0.4123 -0.0071 -6.6195
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表 5 定直平飞初始边界条件
Table 5. Straightforward and level flight initial boundary conditions
参数 数值 迎角/(°) 4.474 来流速度/(m·s-1) 98.646 温度/K 268.7 高度/m 3 000 大气密度/(kg·m-3) 0.909 3
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