Longitudinal maneuver simulation of an X-51A-like aircraft based on numerical virtual flight
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摘要:
吸气式高超声速飞行器在机动过程中，由于构型复杂，气动特性呈现强烈的非定常特性。传统基于数据库或气动力模型的飞行仿真不能准确描述机动过程中复杂的气动特性和运动规律。针对这一问题，基于现代软件分布式、模块化的发展趋势，建立了一个高效的数值虚拟飞行仿真平台。利用该平台，对一种类X-51A外形的吸气式高超声速飞行器开展了纵向机动闭环数值仿真，并与工程方法的结果进行了对比。研究发现：对于类X-51A外形的吸气式高超声速飞行器，在纵向拉起时，工程方法给出的结果可能不能完全反映非定常效应的影响。此时，应该采用更为精确的虚拟飞行方法来研究飞行器的闭环响应特性。此外，借助该仿真平台还研究了舵回路时间常数对控制系统的影响，为控制律设计提供了一定的参考。
Abstract:In the maneuvering process of air-breathing hypersonic vehicles, the aerodynamic characteristics show strong unsteady characteristics due to the complicated configuration. Traditional flight simulations based on database or aerodynamic models cannot exactly describe the complex aerodynamic characteristics and motion characteristics in the maneuvering process. To solve this problem, a numerical virtual flight simulation platform is established based on the distributed and modular development trend of modern software. With this coupled platform, longitudinal maneuvering simulations of an X-51A-like aircraft is carried out and the results are compared with those of the engineering method. It is found that For the X-51A-like air breathing hypersonic vehicle, the results given by the engineering method may not fully reflect the influence of unsteady effects when it pitches up longitudinally. In this case, the more accurate virtual flight method should be used to study the closed-loop response characteristics of the vehicle.In addition, the influence of the rudder loop time constant on the control system is also studied with the aid of the simulation platform, which provides a certain reference for the design of the control law.
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图 1 不同环境下gRPC实现过程
Figure 1. Schematic diagram of gRPC implementation process in different environments
图 2 Simulink/MICFD数值虚拟飞行仿真平台流程图
Figure 2. Flowchart of Simulink/MICFD numerical virtual flight simulation platform
图 4 挂载物气动力系数、气动力矩系数随时间变化曲线
Figure 4. Time history of aerodynamic coefficients and aerodynamic moment coefficients for store
图 5 挂载物线位移、角位移随时间变化曲线
Figure 5. Time history of linear and angular displacement for store
图 7 不同时刻控制舵与机身动态重叠边界示意图
Figure 7. Schematic diagram of dynamic overlapping boundary of control rudder and airframe at different moments
图 10 机动过程中典型时刻的流场结构(Td=0.1)
Figure 10. Typical-moment flow field structure during maneuvering process (Td=0.1)
图 14 不同时间常数下迎角响应过程
Figure 14. Response process of angle of attack under different time constants
图 15 不同时间常数下舵偏角响应过程
Figure 15. Response process of rudder deflection angle under different time constants
图 16 不同时间常数下俯仰力矩时间历程
Figure 16. Time history of pitching moment under different time constants
表 1 不同Td下控制系统的性能指标
Table 1. Performance indexes of control system under different Td
Td td tr tp ts(±5%) σ% 0 0.355 0.430 0.808 0.59 4.20 0.05 0.366 0.361 0.749 1.44 5.96 0.1 0.388 0.326 0.856 2.01 16.0 0.2 0.382 0.320 0.787 6.02 31.6 
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