火箭推进

为了解决发动机在恶劣工作环境下点火困难和易熄灭的问题,采用数字电路控制放电频率、固态开关控制放电输出,研制了一种数字变频固态点火装置,该点火装置能够在10～30 V直流宽电压范围内稳定输出,放电频率启动时为6 Hz、启动后自动变换为1 Hz,具有放电火花持续时间长和长时持续工作等优点。所研制的点火装置是国内首台已成功装机应用的具备变频连续点火能力的数字点火装置,自应用以来,故障率明显低于现有点火装置,能够满足地面启动、空中启动和高原等复杂气候环境下的高可靠点火工作。

To solve the problem of difficult ignition and easy flameout of the engine in harsh environment, we developed a digital variable frequency solid-state ignition exciter by using digital circuit to control the discharge frequency and solid-state switch to control the discharge output. This ignition exciter is capable of stable output in a wide voltage range of 10-30 V DC, with discharge frequency of 6 Hz at starting and automatically changing to 1 Hz after starting. It has extended discharge spark duration and longer continuous operation. The ignition exciter developed is the first digital ignition exciter with variable frequency continuous ignition capability that has been successfully installed and applied in China. After its application, the number of failures, the percentage of failed products and the failure rate are all 0, which are significantly lower than the existing ignition exciters. The practical application has shown that the ignition exciter can meet the high reliable ignition requirement under complex climate environment such as ground start, air start and plateau start.

引言
1 工作原理
2 电路设计
3 仿真与测试
4 与现有技术比较
5 结论

图1 点火装置通用工作原理框图<br/>Fig.1 General working principle block diagram of ignition exciter

图1 点火装置通用工作原理框图
Fig.1 General working principle block diagram of ignition exciter

图2 点火电路简化原理图<br/>Fig.2 Simplified schematic of the ignition circuit

图2 点火电路简化原理图
Fig.2 Simplified schematic of the ignition circuit

图3 充电电路简化原理图<br/>Fig.3 Simplified schematic of charging circuit

图3 充电电路简化原理图
Fig.3 Simplified schematic of charging circuit

图4 频率发生器电路<br/>Fig.4 Frequency generator circuit

图4 频率发生器电路
Fig.4 Frequency generator circuit

图5 变频放电控制电路<br/>Fig.5 Variable frequency discharge control circuit

图5 变频放电控制电路
Fig.5 Variable frequency discharge control circuit

图6 放电控制电路<br/>Fig.6 Discharge control circuit

图6 放电控制电路
Fig.6 Discharge control circuit

图7 储能电容器充电波形<br/>Fig.7 Charge waveform of energy storage capacitor

图7 储能电容器充电波形
Fig.7 Charge waveform of energy storage capacitor

图8 不同工作电压下储能电容器充电状态<br/>Fig.8 Charge state of energy storage capacitor at different operating voltage

图8 不同工作电压下储能电容器充电状态
Fig.8 Charge state of energy storage capacitor at different operating voltage

表1 不同工作电压下电容器充电时间<br/>Tab.1 Charge time of storage capacitor at different operating voltage

表1 不同工作电压下电容器充电时间
Tab.1 Charge time of storage capacitor at different operating voltage

表2 放电频率测试<br/>Tab.2 Discharge frequency test

表2 放电频率测试
Tab.2 Discharge frequency test

图9 放电输出电压波形<br/>Fig.9 Discharge output voltage waveform

图9 放电输出电压波形
Fig.9 Discharge output voltage waveform

图10 放电火花能量波形<br/>Fig.10 Discharge spark energy waveform

图10 放电火花能量波形
Fig.10 Discharge spark energy waveform

表3 与现有同类发动机点火装置的性能指标对比<br/>Tab.3 Performance index comparison with existing similar engine ignition exciters

表3 与现有同类发动机点火装置的性能指标对比
Tab.3 Performance index comparison with existing similar engine ignition exciters

表4 与现有点火装置的点火故障数据对比<br/>Tab.4 Comparison of ignition fault data between exciters in this paper and existing exciters

表4 与现有点火装置的点火故障数据对比
Tab.4 Comparison of ignition fault data between exciters in this paper and existing exciters

[1] 蒋志扬.航空发动机电点火原理[M].北京:国防工业出版社,1959.
[2] 王煜锟,王玫,张锋,等.气氧/气甲烷火炬点火器设计及试验[J].火箭推进,2022,48(3):57-62.
[3] 刘昌国,陈锐达,刘犇,等.小推力空间液体火箭发动机夹气启动特性[J].火箭推进,2021,47(3):8-15.
[4] JANKOWIAK A,BLANCHART P.Electrical behaviour of ceramic composite materials for aero-engine igniters[J].Aerospace Science and Technology,2006,10(3):207-216.
[5] GLIDDEN S C,SANDERS H D.Solid state spark gap replacement switches[C]//27th International Power Modulator Symposium.New York:IEEE,2007.
[6] 吴恩会,陈新.应用于航空发动机直流高能点火装置的RCC变换器研究[J].电子测量与仪器学报,2008,22(S2):305-308.
[7] 边靖洲,车延博,冯宝国.一种航空发动机稳频高能点火器[J].应用科技,2015,42(5):14-18.
[8] 赵军,张涛,粟建新,等.航空发动机点火系统改进设计[J].现代电子技术,2013,36(4):102-106.
[9] 李奕新,谭航,杨水银.航空发动机电点火系统现状与发展趋势[J].燃气涡轮试验与研究,2015,28(6):49-54.
[10] 刘正艺,陈溯敏,周孙宇.航空发动机燃烧室点火研究概述[J].燃气涡轮试验与研究,2021,34(6):51-55.
[11] 王兆安,刘进军.电力电子技术[M].5版.北京:机械工业出版社,2009.
[12] 龙轶,高红星,唐军.基于功率MOSFET管的RCC变换器研究[J].船电技术,2007,27(6):351-353.
[13] ERICKSON R W,MAKSIMOVIC D.Fundamentals of power electronics[M].2nd ed.New York:Springer,2013.
[14] RASHID M H,RASHID M H.Power electronics handbook[M].3rd ed.Burlington:Butterworth-Heinemann,2011.
[15] LEUCHTER J,STEKLY V,BLASCH E.Investigation of avionics power switch loading versus aircraft electromagnetic compatibility[J].IEEE Aerospace and Electronic Systems Magazine,2015,30(9):24-34.
[16] 方荣宝.航空发动机用晶体管高能点火装置的计算[R].北京:中国航空科技报告管理办公室,1983.
[17] GRAY P R,HURST P J,LEWIS S H,et al.Analysis and design of analog integrated circuits[M].New York:John Wiley & Sons Inc,2009.
[18] NELSON V P,NAGLE H T.Digital logic circuit analysis and design[M].Englewood Cliffs,NJ:Prentice Hall,1995.
[19] 中国人民解放军总装备部.军用环境试验方法:GJB 150.1A[S].北京:总装备部军标出版发行部,2009.
[20] 国防科技工业局.航空燃气涡轮发动机点火系统电嘴火花能量试验方法:HB 20274[S].北京:中国航空综合技术研究所,2016.
[21] 王俊琦,汪涛.某型辅助动力装置启动失败故障分析[J].工程与试验,2020,60(2):50-52.
[22] 天津航空机电有限公司.变频放电连续输出点火技术研究应用证明[R].天津:天津航空机电有限公司,2018.

备注

引言

1 工作原理

2 电路设计

3 仿真与测试

4 与现有技术比较

5 结论

期刊信息