【摘要】 目的　研究火箭发动机高喷口参数燃气尾流噪声的抑制技术及其预测方法，以降低发射效应，改善发射环境； 方法　应用小孔消声和微穿孔消声原理提出发射噪声和冲击波超压的抑制方案，并在给出流场计算方法的基础上，运用喷气噪声理论给出发射尾流噪声的理论预测方法； 结果　该抑制方案降低了超压值４９．６％ ，理论与试验结果符合较好； 结论　抑制装置结构简单实用，能显著降低噪声和冲击波超压，理论预测方法能较准确地满足预测要求；更多还原

【Abstract】 Aim To study suppression and prediction methods for high spout parameter jet noise of missile for suppressing launching effect and improving launching environment. Methods The theory of micropore muffler and microperforated panel construction was used in suppressing launching noise and shock wave, and the jet noise theory was used in theoretic prediction of sound field on the basis of fluid calculation. Results The suppression method is successful to depress 49 6% superpressure and the prediction results are in good accordance with the experimentation results. Conclusion The suppression device which is simple and functional can markedly depress noise and shock wave superpressure, and the theoretic prediction methods can accurately meet the requirement.更多还原