The invention discloses a three-air-inlet-channel integrated design method considering double waverider front bodies, and relates to integrated design of front bodies/air inlet channels of hypersonic flight vehicles. According to design conditions, double waverider front bodies of internal/external flow integrated pneumatic design, a middle internal contraction air inlet channel and two symmetrical outer side internal contraction air inlet channels are provided, and the middle internal contraction air inlet channel is designed in a three-dimensional internal contraction axial symmetry reference flow field streamline tracking mode. The streamline tracking design is also carried out on the inner contraction air inlet channel which is symmetrical on the outer side by adopting a three-dimensional inner contraction axial symmetry reference flow field, and the inner contraction reference flow field of the inner waverider precursor and the outer contraction flow field of the outer waverider precursor are pneumatically coupled, so that the waverider characteristics of a precursor machine body and the lower surface of the middle inner contraction air inlet channel are kept; the whole aerodynamic performance is maintained, the other two symmetrical outer-side internal contraction air inlet channels are arranged, on the basis that the capture flow is improved, incoming flow is further compressed, and the aerodynamic performance and stability of a machine body are improved; and efficiency and performance requirements are considered.
考虑双乘波前体的三进气道一体化设计方法,涉及高超声速飞行器前体/进气道的一体化设计。根据设计条件给出内/外流一体化气动设计的双乘波前体以及沿着展向并联布置的一个中部内收缩进气道和两个对称的外侧内收缩进气道,中部内收缩进气道采用三维内收缩的轴对称基准流场流线追踪设计,外侧对称的内收缩进气道也采用三维内收缩的轴对称基准流场进行流线追踪设计,内乘波前体的内收缩基准流场与外乘波前体的外收缩流场在气动上进行耦合,使前体机体与中部内收缩进气道下表面均保持乘波特性,维持整体的气动性能,布置另外两个对称的外侧内收缩进气道,在提高捕获流量的基础上,进一步压缩来流,提升机体的气动性能和稳定性;兼顾效率与性能需求。
Three-air-inlet-channel integrated design method considering double waverider precursors
考虑双乘波前体的三进气道一体化设计方法
2024-12-13
Patent
Electronic Resource
Chinese
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