为研究飞/发一体化设计中后体对S弯喷管红外辐射特性的影响，本文通过采用S形喷管飞翼布局飞行器后机身的缩比试验模型，结合分区测量方法，开展了后半球空间典型探测面的红外辐射特性试验研究。结果表明：分区测量方法解决了大角度探测下尾喷流核心区无法覆盖的难题，试验验证该方法在下探测面内可将喷流辐射贡献测量误差降低23.8%；后体对S形喷管原有的红外辐射特征有显著影响：正尾向（α=0°）因后体受热成为次生辐射源，导致辐射强度峰值较无后体模型提升12.3%；侧向（α>5°）则通过遮蔽高温喷流与壁面，使后机身试验件在水平、下探测面内辐射强度比S弯喷管平均降低10.52%、40.51%。
To investigate the influence of the rear fuselage on the infrared radiation characteristics of S-shaped nozzles in integrated flight/launch vehicle designs, this study employed a scaled test model of the rear fuselage from an S-shaped nozzle flying wing aircraft. Utilizing a partitioned measurement method, experiments were conducted to characterize infrared radiation properties across representative detection surfaces in the rear hemispherical space. Results indicate that the partitioned measurement method resolves the challenge of covering the core region of the tail exhaust plume during wide-angle de-tection. Testing verifies that this method reduces measurement errors attributable to plume radiation by 23.8% within the lower detection plane. The rear fuselage significantly alters the original infrared radiation characteristics of the S-shaped nozzle: At the forward tail direction (α=0°), the heated rear body acts as a secondary radiation source, increasing the peak radiation intensity by 12.3% compared to the model without a rear body. At lateral angles (α>5°), the rear body shields the high-temperature exhaust and wall surfaces, reducing the radiation intensity of the rear fuselage test speci-men by an average of 10.52% and 40.51% on the horizontal and downward detection planes, respectively, compared to the S-shaped nozzle.
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