Monitoring device for combustion transient characteristics of solid rocket engine igniter

The invention belongs to the technical field of small tactical missile solid rocket engines, and particularly relates to a solid rocket engine igniter combustion transient characteristic monitoring device which is provided with a preformed hole and two glass windows. Pressure intensity data, infrared heat radiation data and ignition tool combustion images in the device can be collected at the same time when the ignition tool is combusted. A traditional open type igniter test is easily interfered by the environment, the pressure rise in a limited space cannot be simulated, and the test result is inaccurate. However, an igniter test in a product engine is inconvenient to observe, the engine needs to be subjected to windowing modification, the cost is high, and the operation is tedious. The monitoring device has the advantages of being capable of simulating the pressure establishing process in a solid engine combustion chamber, capable of collecting temperature and pressure data and combustion images at the same