航天推进技术研究院主办
LIU Wan-long,NIU Xiang-nan,LI Quan-ling,et al.Design of a ground test control system for attitude and orbital control engine[J].Journal of Rocket Propulsion,2015,41(02):114-117.
一种姿轨控发动机地面试验控制系统设计
- Title:
- Design of a ground test control system for attitude and orbital control engine
- Keywords:
- rocket engine; ground test; control system
- 分类号:
- V433.9-34
- 文献标志码:
- A
- 摘要:
- 控制系统在试车过程中发出指令信号,使发动机和试车台各工艺系统按照预定的程序完成规定试车任务。为了适应某型号姿轨控发动机试验对控制精度要求的提高,需要对现有控制系统进行改造,基于现场可编程门阵列和高速固态继电器设计了一种新的控制系统,其控制模块用于操作人员对试验系统上的各路电磁阀进行手动与自动控制,其复记模块可以实时记录系统状态以便于指挥人员了解系统工作状况,并能够进行数据分析判断。该系统建成后可以满足该型号姿轨控发动机试验的要求,控制精度为0.1 ms。
- Abstract:
- In the test, the control system gives command signal to make the engine and test process systems complete a predetermined test task according to certain procedures. In order to adapt to the high-accuracy control requirement of a new attitude and orbital control engine, it is necessary to improve the existing control system. Therefore, a new control system was designed based on field programmable gate array and high-speed solid-state relay. Its control module can be used for operators to control various electromagnetic valves in the test system manually and automatically. Its record module can be used to record the status of the system, so that the command staff know the working status of the system. The system can meet the testing requirements of the new attitude and orbital control engine. The control precision is 0.1 ms.
参考文献/References:
[1] 郭霄峰. 液体火箭发动机试验[M]. 北京: 中国宇航出版社, 1990.
[2] 谢龙, 李海涛, 沈赤兵. 火箭发动机试验通用自动测试系统研究[J]. 计算机测量与控制, 2007, 15(4): 491-495.
[3] 马爱华. 发动机试验数据自动采集处理系统研究与开发[J]. 计算机测量与控制, 2007, 15(7): 978-980.
[4] 张志红. 可编程控制器(PLC)在发动机冷调试验中的应用[J]. 火箭推进, 2007, 33(1): 59-61.
[5] 班超. FPGA高精度时间测量[D]. 北京: 北京邮电大学, 2013.
[6] 张朗. 基于FPGA的高精度测时仪研制[D]. 南京: 南京理工大学, 2012.
[7] 戴彦, 申彦春, 王金红. FPGA在小卫星姿态控制系统中的应用[J]. 电光与控制, 2009, 16(7): 76-79.
[8] 李锦清, 刘文定, 赵鹏. FPGA在卫星AOCS测试中的应用[J]. 测控技术, 2013, 32(12): 41-44.
[9] 钱金川, 金林升. 固态继电器简介[J]. 机床电器, 2004, 31(4): 58-59.
[10] 朱英明, 周长刚. 固态继电器(SSR)原理及应用中一些问题的探讨[J]. 机床电器, 2006, 33(1): 9-10.
[11] 王昌华. 固态继电器及其应用[J]. 西北电力技术, 2004, 32(5): 9-52.
[12] 邹进和, 李守明. 新型大电流直流固态继电器的设计[J]. 沈阳师范大学学报: 自然科学版, 2004, 22(4): 268-270.
相似文献/References:
[1]霍世慧,袁军社,徐学军,等.双推力室机架快速优化设计方法研究[J].火箭推进,2015,41(04):55.
HUO Shihui,YUAN Junshe,XU Xuejun,et al.A rapid optimization design method for frame structure
of double thrust chambers[J].Journal of Rocket Propulsion,2015,41(02):55.
[2]沈传兵,苏 杭,朱子勇.基于PLC和WinCC的火箭发动机热真空试验控制系统[J].火箭推进,2015,41(03):93.
SHEN Chuan-bing,SU Hang,ZHU Zi-yong.Control system for liquid rocket engine heat-vacuum
test based on PLC and WinCC[J].Journal of Rocket Propulsion,2015,41(02):93.
[3]段文浩,于 涛,杨 莹.辐射式热流测量系统及其应用[J].火箭推进,2014,40(01):85.
DUAN Wen-hao,YU Tao,YANG Ying.Radiant heat flux measuring system and its application[J].Journal of Rocket Propulsion,2014,40(02):85.
[4]朱子环,耿卫国,管 理,等.某型号大推力火箭发动机试验推力测量不确定度评定[J].火箭推进,2012,38(05):81.
ZHU Zi-huan,GENG Wei-guo,GUAN Li,et al.Assessment of thrust measurement uncertainty for test of large thrust rocket engine[J].Journal of Rocket Propulsion,2012,38(02):81.
[5]周奎,吴伟亮,张玫宝.火箭发动机喷雾均匀性数值分析[J].火箭推进,2010,36(02):26.
Zhou Kui,Wu Weiliang,Zhang Meibao.Numerical analysis on uniformity of spray in rocket engines[J].Journal of Rocket Propulsion,2010,36(02):26.
[6]张涛,唐虎,周江平,等.可贮存推进剂泵压式液体火箭发动机多次起动系统研究[J].火箭推进,2010,36(03):15.
Study on the multi-start system of turbopump-fed rocket engine with storable propellants[J].Journal of Rocket Propulsion,2010,36(02):15.
[7]刘小勇,李君,周云端.液体火箭发动机声振环境试验及统计能量分析研究[J].火箭推进,2010,36(03):49.
Liu Xiaoyong,Li Jun,Zhou Yunduan.Measurement and analysis of noise field of rocket engine based on statistical energy analysis[J].Journal of Rocket Propulsion,2010,36(02):49.
[8]刘永兴,王 魁,曹再勇.RBCC推进系统主火箭发动机气氧/煤油推力室研究[J].火箭推进,2009,35(06):23.
Liu Yongxing,Wang Kui,Cao Zaiyong.Investigation of GO2/kerosene thrust chamber of the main rocket engine for the RBCC propulsion system[J].Journal of Rocket Propulsion,2009,35(02):23.
[9]曹智程,费立森.小流量气体流量的测量方法及应用[J].火箭推进,2009,35(03):34.
Cao Zhicheng,Fei Lisen.The method and application of
small gaseous mass flow rate measurement system[J].Journal of Rocket Propulsion,2009,35(02):34.
[10]袁晓峰,许化龙,徐志高.液体火箭发动机诊断知识挖掘系统设计[J].火箭推进,2008,34(03):44.
Yuan Xiaofeng,Xu Hualong,Xu Zhigao.Design of diagnostic knowledge mining system for liquid
propellant rocket engine[J].Journal of Rocket Propulsion,2008,34(02):44.
备注/Memo
收稿日期:2014-10-07;修回日期:2014-12-12 作者简介:刘万龙(1982—),男,博士,工程师,研究领域为火箭发动机试验及测试技术