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对工作在设计点Ｍａ＝６，高度为２４．４ｋｍ的高超音速飞行器（即战术导弹）采用固体燃料双模态冲压发动机（ＤＭＲＪ）的可行性进行了研究。分析表明，在接近燃料空气理论混合比且不考虑超音速燃烧室中热损失和壁剪切层损失的情况下，超音速燃烧效率达到９０％。初步的实验室展示了这种ＤＭＲＪ系统的工作状态，包括在超音速燃烧室中建立的持续燃烧。
The feasibility of using a solid fuel dual mode ramjet engine (DMRJ) for a hypersonic vehicle (ie, a tactical missile) operating at a design point Ma = 6 and a height of 24.4 km was studied. The analysis shows that the supersonic combustion efficiency reaches 90% at a theoretical mixing ratio close to the fuel air and without considering the heat loss in the supersonic combustion chamber and the loss of the wall shear layer. The preliminary lab showed the working status of this DMRJ system, including the continuous combustion established in the supersonic combustion chamber.