一、前言 众所周知,在推进剂组成一定时火箭推力室的理论性能和热力气动参数以及喷管面积比是由三个决定参数,即推进剂初焓h_c、室压P_c和喷管压力膨胀比ε(=P_c/P)确定的,可表示为 (?)=(?)(h_c,P_c,δ) (1)在实际使用中往往需要广泛决定参数范围和相当小决定参数间隔的推力室性能和气动参数,或这些参数随决定参数的变化,若都采用通常的热力计算方法来获得则是很麻烦的。由于 I. Preface As we all know, in the propellant composition of a certain rocket thrust chamber theoretical performance and thermal aerodynamic parameters and nozzle area ratio is determined by the three parameters, namely the initial propellant enthalpy h_c, pressure P_c and nozzle pressure expansion ratio ε Can be expressed as (?) = (?) (H_c, P_c, δ) (1) In practice, it is often necessary to determine the parameter range and the performance of the thrust chamber with relatively small decision parameter intervals Pneumatic parameters, or changes in these parameters depending on the parameters to be determined, are troublesome if they are obtained using the usual thermodynamic method. due to