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| 燃烧时滞对小推力高室压动力系统响应特性的影响 | |
| 引用本文： | 沈赤兵,吕志信,陈启智. 燃烧时滞对小推力高室压动力系统响应特性的影响[J]. 航空动力学报, 1997, 12(1): 61-65,108 |
| 作者姓名： | 沈赤兵 吕志信 陈启智 |
| 作者单位： | Aerospace Technology Dept.National University of Defense Technology, Changsha 410073 |
| 摘 要： | 对小推力高压燃烧室动力系统各部件建立了数学模型,并对此系统进行了数值计算,分析了燃烧时滞对此系统的影响。计算结果表明,在燃烧时滞较大时,高室压动力系统响应较慢,发动机性能参数的超调量较大,达到稳态所需的时间较长,轨控发动机与姿控发动机共用同一个供应系统,姿控发动机受燃烧时滞的影响更大。 |
| 关 键 词： | 液体推进剂火箭发动机 燃烧室 响应分析 燃烧时间 |
| 收稿时间： | 1996-03-01 |
| 修稿时间： | 1996-05-01 |
INFLUENCE OF COMBUSTION TIME DELAY ON RESPONSE OF LOW-THRUST POWER SYSTEM WITH HIGH COMBUSTOR PRESSURE |
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| Shen Chibing,Lu Zhixin and Chen Qizhi. INFLUENCE OF COMBUSTION TIME DELAY ON RESPONSE OF LOW-THRUST POWER SYSTEM WITH HIGH COMBUSTOR PRESSURE[J]. Journal of Aerospace Power, 1997, 12(1): 61-65,108 | |
| Authors: | Shen Chibing Lu Zhixin Chen Qizhi |
| Affiliation: | Aerospace Technology Dept.National University of Defense Technology, Changsha 410073 |
| Abstract: | The mathematical model of a low-thrust power system with high combustor pressure is set up.The numerical computation for this system and analysis of the influence of combustion time delay on this system have been carried out with the characteristic method and the fourth-order Runge-Kutta method.The computed results show that the response of the power system becomes slower,the overshoot of engine performance parameter becomes greater and the time required for reaching the steady state becomes longer,if the combustion time delay is greater.When orbit control and attitude control rocket engines share the same propellant feed system,thus attitude-control rocket engine is affected more greatly by the combustion time delay.Finally,some methods are proposed to decrease the combustion time delay.The conclusions drawn in this paper provide the basis for improving its response characteristics. |
| Keywords: | Combustion chambers Burning time Liquid propellant rockets Response analysis |
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