为了探索冲压发动机用低燃速贫氧推进剂燃气发生器端面燃烧的规律，采用X射线荧屏分析技术对全尺寸燃气发生器端面燃烧规律进行了诊断研究。试验成功采集了燃气发生器药柱燃面随时间的退移图像，图像数据表明低燃速贫氧推进剂药柱沿轴线方向以近似“三维”锥面体进行退移，在45s左右逐渐形成相对稳定的锥顶角68.5°。试验数据还表明，锥面效应一方面引起燃气发生器药柱燃速由1.60mm/s增大到1.80mm/s；另一方面引起装药燃烧室压强由初始平衡压强0.89MPa爬升到最大工作压强1.75MPa。工作结束后喷管喉径固体线性沉积率为2.68μm/s。

In order to explore transient end burning law for gas generator with low burning velocity fuel-rich propellant used in ramjet，transient diagnosis research is conducted in the full-scale gas-generator with X-ray screen analytical technique by which the grain end burning images are obtained successfully in the experiment. Images show that end burning of approximative 3D conical body shrinks back along the center axis direction. The near constant cone angle is 68.5° that begins to be formed at 45s. The test data also show that the conical burning action increases the grain burning velocity from 1.60mm/s to 1.80mm/s，while it increases the chamber pressure from 0.89MPa to 1.75MPa. Solid linear deposition rate of nozzle throat is 2.68μm/s after working. Diagnostic research of gas generator end burning law is obtained.