## 固体火箭发动机气动参数计算与实现

关键词 固体火箭发动机，气体动力学函数，拉瓦尔喷管参数计算
Title      Solid rocket engine aerodynamic parameter calculation and realization
Abstract：In solid rocket propellant combustion, gas generated by the combustion
chamber from the nozzle channel high speed charge discharge. The gas is very complex
in the combustion chamber of the flow, the flow boundary is burning surface and the
combustion chamber charge all or part of the inner surface of the gas, the gas flow is
closely related with the charge combustion process, and mutual influence. The nozzle is
an important component of the rocket engine, the one-dimensional steady assumption,
the gas flow equations will be no quality add conditions into the combustion chamber, 源自六/维\论]文[网!加7位QQ324.9114 www.lwfree.cn
can get the control equations of gas flow in the nozzle.  In this paper according to the
task, according to the relationship between parameters of gas flow and velocity
coefficient method, and programming to calculate the gas dynamics function. Followed
by the relationship between the speed coefficient and the channel length, design the
airflow parameter calculation program distribution along the charge length. Velocity
coefficient by using continuity equation can obtain nozzle arbitrary section, on the basis
of this design program can calculate the velocity function of arbitrary cross section in a
nozzle and the thrust coefficient.
Key words: Solid propellant rocket engine, Gas dynamics function, the Calculating of
Lawal parameters nozzle

1 绪论.  1
1.1 燃气在燃烧室中的流动过程    1
1.2 装药燃速的侵蚀燃烧效应    2
1.3 燃气在喷管中的流动过程    2
1.4 本文主要研究内容    3
2．气体动力学函数计算  .  4
2.1 软件开发与设计    4
2.2 静总参数函数    5
2.3 流量函数q(λ)  .  7
2.3 冲量函数f(λ)，r(λ)  .  9
3. 气流参数延装药长度计算  .  11
3.1 理论计算    11
3.2 某固体火箭发动机通道流动参数绘图    16
3.3 软件开发  16
4．燃气在喷管中的流动过程  .  17
4.1 流动参数与速度系数的关系    17
4.2 速度系数与面积比的关系    18
4.3 拉瓦尔喷管面积比与压强比的关系    19
4.4 拉瓦尔喷管的排气速度    20

4.4 软件开发  21
5.推力系数  .  22
5.1 推力系数定义    22
5.2 推力系数的物理意义    23 固体火箭发动机气动参数计算与实现:http://www.lwfree.cn/jixie/20180110/19053.html
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