Radiative heat transfer is a significant heat transfer mechanism in the formation of engine exhaust plumes, resulting in varied effects on the exhaust plume flow field and infrared radiation characteristics. In this work, simulation model is used to simulate exhaust plume flow of solid-propellant rocket motor, with consideration given to the recombination effects of 9 species and 10 elementary reactions. The study investigates the impact of radiative heat transfer on the exhaust plume flow field at different altitudes. Furthermore, a narrow-band model and the Line of Sight (LOS) approach are employed to calculate the infrared radiation characteristics of the flow field. It is indicated that radiative heat transfer affects the temperature of the flow field and the distribution of intermediate products such as CO and OH. Notably, at flight altitudes of 10km, the impact of radiative heat transfer is relatively weak, while at an altitude of 60km, the effect is more pronounced, which is attributed to the rarified air conditions prevalent in high-altitude regions, where molecular collisions are less frequent, thereby radiative heat transfer plays a significant role in heat conduction. Furthermore, radiative heat transfer also exerts a noticeable impact on the infrared characteristics of the flow field.