本文介绍火箭——冲压发动机和火箭发动机的热力计算方法。其中燃烧计算采用改进的怀特法,考虑了气相和凝相组分。平衡组分初值可以任意选取,没有负值组分修正问题。经过计算多种不同类型的贫氧推进剂,证明本方法计算可靠,收敛迅速、有较大的通用性。可在国产中小型计算机上实现火箭——冲压发动机和火箭发动机的热力计算。 This article describes the thermal calculation of rocket-ramjet and rocket motors. Burning calculations using improved White’s law, taking into account the gas phase and condensate components. The balance of the initial value of components can be arbitrarily selected, there is no negative component to correct the problem. After calculating a variety of different types of oxygen-poor propellant, proves that the method is reliable, rapid convergence, have greater versatility. The thermal calculation of rocket-ramjet engines and rocket motors can be realized on domestic small and medium sized computers.