In this work, the ignition of HMX propellants by a radiant source is investigated. The results of onedimensional numerical simulations using quasi-steady Zeldovich-Novozhilov theory with simplified kinetics are presented. Effects of radiant flux and absorption coefficient on the ignition process are considered. In addition, the region of self-sustaining deflagration after de-radiation is mapped, and compared to Summerfield's classical go/no-go mapping. Two critical flux levels, which bound the upper limit of this go/no-go region, are identified. Additionally, the variation of this ignition corridor with absorption coefficient and pressure is examined. Comparison to several relevant experimental results is included to validate the capability of this model. In general, the results showed that while further refinement is needed (especially for the simplified gas phase kinetics), modeling of the go/no-go behavior seems to be strongly dependent on thermal relaxation processes in the solid phase.