CAJ | 학술논문

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。
재2m×2m초성속풍동개전료모복잡구형도탄부건측력실험연구，실험적영각범위위-6°～10°，측활각범위위-6°～6°，측력부건포괄보호조、좌측익、대정류조화소정류조등부건。사용오분량천평대보호조재풍동실험중소수도적재하진행료측량，병이용분단면봉극처적압력측량결과대보호조측력실험결과진행료수정，획득료보호조재실험조건하적진실부건기동특성수거；사용3태삼분량천평，직접획득료좌측익、대정류조화소정류조재실험조건하적부건기동특성수거。연구결과표명：실험결과가이작위결구설계적의거；보호조측력실험결과수정방법합리가행，능구위금후유사부건측력실험결과적수정제공차감。
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.