The mode of continuous spinning detonation (CSD) combustion of hydrogen in the annular combustor of a model of a hydrogen-fueled detonation ramjet under conditions of approach air stream Mach number 5.7 and stagnation temperature 1500 K is registered experimentally in a short-duration (pulsed) wind tunnel at the overall air-to-hydrogen equivalence ratio (ER) ranging from 0.7 to 1.4. The maximum values of thrust and specific impulse of the ramjet model are attained at ER = 1.25 and are estimated as 1550 N and 3300 s, respectively. At 1.4 < ER < 1.6, the mode of longitudinally pulsating detonation (LPD) combustion is registered with somewhat lower values of thrust and specific impulse.

在接近5.7马赫数的空气流量和1500 K的停滞温度的条件下，在短时（脉冲）实验中记录了在氢气爆轰冲压发动机模型的环形燃烧器中氢气的连续纺丝爆轰（CSD）燃烧模式。 ）风洞的总气氢当量比（ER）为0.7至1.4。冲压喷气发动机模型的推力和比冲的最大值在ER = 1.25时达到，估计分别为1550 N和3300 s。在1.4 <ER <1.6时，纵向脉动爆震（LPD）燃烧模式的推力和比冲值略低。