| 摘要 |
<p>PROBLEM TO BE SOLVED: To provide a burning test method for a rocket combustor, capable of ensuring high accuracy evaluation of operation range characteristics and achieving cost reduction.SOLUTION: Provided is a burning test method for conducting a burning test upon supplying a propellent containing an oxidant and a fuel to a rocket combustor. The burning test is conducted under a plurality of fixed point conditions LL to HH that are conditions set in advance each for a mixture ratio of the oxidant to the fuel in the propellent provided for burning. At a time of acquiring a burning test result, a continuous burning test is conducted for continuously changing at least either a burning pressure or the mixture ratio in one unit burning test and acquiring the burning test result under two or more fixed point conditions among the plural fixed point conditions.</p> |
