摘要
为了研究低功率氩电弧喷射推力器中的辐射损失,采用辐射模型和非辐射模型对其工作过程进行了对比数值模拟分析。采用二阶精度无波动、无自由参数的耗散差分格式(NND格式)数值求解耦合电磁源项和辐射源项的N-S方程组,并采用隐式残差光滑法加速收敛;采用有限控制容积积分方法离散求解椭圆型偏微分电磁场方程,并采用逐点超松弛迭代方法加快收敛速度。数值模拟结果对比给出了辐射模型和非辐射模型流动分布情况,并比较了两种模型推力器推力、比冲和推进效率。研究结果表明,与非辐射模型相比,辐射模型比冲低0.137%,推进效率低1.03%,辐射对低功率电弧喷射推力器性能影响比较小。
To investigate radiation loss inside the low power argon Arcjet thruster, numerical simulations and analyses were carried out by using radiation and no radiation models contrastively. Non-oscillatory and non-free-parameters dissipative finite difference scheme with second order accuracy was employed to solve Navier-Stokes equations coupled with electromagnetic and radiant source terms, and implicit residual-smoothing technique was adopted to accelerate numerical converging. Finite control volume integral approach was developed to discrete elliptic partial differential equation of electromagnetic field, and successive over relaxation method was introduced to expedite numerical converging. By virtue of numerical simulations, flow distributions within the thruster, thrust, specific impulse and thrust efficiency of the thruster in radiation and no radiation models are presented. Results of the study show that 0.137% lower specific impulse and 1.03% lower thrust efficiency are obtained in radiation model as compared with no radiation model, and radiation loss has little effect on performance of low power Arcjet thrusters.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2004年第6期873-878,共6页
Journal of Aerospace Power
基金
国家自然科学基金资助项目(50086001)
国防基础科研项目(K1201060711)
博士生创新性研究基金
关键词
航空、航天推进系统
电弧喷射推力器
氩
数值模拟
辐射损失
性能
Argon
Computer simulation
Differential equations
Electric arcs
Electromagnetic fields
Finite difference method
Navier Stokes equations
Partial differential equations
Performance
Radiation
