某复杂构型导弹高速风洞部件测力实验研究
The component characteristics test study of a missile model with complexity configuration in high speed wind tunnel
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摘要: 在2m×2m超声速风洞开展了某复杂构型导弹部件测力实验研究,实验的迎角范围为-6°~10°,侧滑角范围为-6°~6°,测力部件包括保护罩、左侧翼、大整流罩和小整流罩等部件。使用五分量天平对保护罩在风洞实验中所受到的载荷进行了测量,并利用分断面缝隙处的压力测量结果对保护罩测力实验结果进行了修正,获得了保护罩在实验条件下的真实部件气动特性数据;使用3台三分量天平,直接获得了左侧翼、大整流罩和小整流罩在实验条件下的部件气动特性数据。研究结果表明:实验结果可以作为结构设计的依据;保护罩测力实验结果修正方法合理可行,能够为今后类似部件测力实验结果的修正提供借鉴。Abstract: The component characteristics test of the missile model was conducted in the FL-28 wind tunnel.The missile’s configuration is complicated.The angels of attack ranged from-6°to 10°,and angels of sideslip were from-6°to 6°.Protective cover,left wing and rectifier covers were involved in the test.A 5-component balance was used to obtain force and moment data of protective cover,and the component characteristics was acquired when the test data were correc-ted by the result of pressure measurement of the aperture.Three 3-component balances were used directly to obtain component characteristics data of left wing and rectifier covers.The test result can be applied for structure design of those components.The correction method for the da-ta of protective cover is verified,and it could provide some experience for the later tests.
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