固体推进剂微推进器的研究进展
|
摘要
总结了固体推进剂微推进器的结构类型、点火装置、材料选择、推进剂配方、测试系统等,并提出未来的发展方向。而硼的质量热值和体积热值大,是火箭冲压发动机固体推进剂的首选燃料。分析含硼推进剂作为微推进器的能量单元,研究其性能规律及改进措施,将为含硼推进剂配方优化和微推进器结构尺寸优化指明方向。
The structure of the solid propellant micro-thruster is simple,the energy density of the solid propellant micro-thruster is high,and the working property of the solid propellant micro-thruster is stable.Theses characteristics are beneficial to the integration of systems. The expected thrust and impulse of the thruster can be obtained by setting the structure and size of the micro thruster and the composition and content of the propellant. So the solid propellant micro-thruster is especially suitable for micro spacecraft to meet the needs of military and civil. However,the chamber of the micro-thruster is small,so the heat loss caused by the larger surface area and the microscale effect are high. Furthermore,the successful,quick ignition and sustained,steady and intense,efficient combustion of fuels in it are difficult,and that is the importance of the study. The structure type,ignition devices,material selection,propellant formulation and test systems,of the solid propellant micro-thruster are summarized,and the development direction isproposed. Boron is considered to be an attractive high-energy metallic fuel for use as the fuel-rich solid propellant because of its high gravimetric and volumetric caloric value during combustion. Therefore,the boron-based propellant as the energy element is selected,and its law of performance and improvement measures is studied. The direction for the optimization of the boron-based propellant formulation and the structure size of the micro thruster will be showed.
The structure of the solid propellant micro-thruster is simple,the energy density of the solid propellant micro-thruster is high,and the working property of the solid propellant micro-thruster is stable.Theses characteristics are beneficial to the integration of systems. The expected thrust and impulse of the thruster can be obtained by setting the structure and size of the micro thruster and the composition and content of the propellant. So the solid propellant micro-thruster is especially suitable for micro spacecraft to meet the needs of military and civil. However,the chamber of the micro-thruster is small,so the heat loss caused by the larger surface area and the microscale effect are high. Furthermore,the successful,quick ignition and sustained,steady and intense,efficient combustion of fuels in it are difficult,and that is the importance of the study. The structure type,ignition devices,material selection,propellant formulation and test systems,of the solid propellant micro-thruster are summarized,and the development direction isproposed. Boron is considered to be an attractive high-energy metallic fuel for use as the fuel-rich solid propellant because of its high gravimetric and volumetric caloric value during combustion. Therefore,the boron-based propellant as the energy element is selected,and its law of performance and improvement measures is studied. The direction for the optimization of the boron-based propellant formulation and the structure size of the micro thruster will be showed.
引文
[1]SATHIYANATHAN K,LEE R,CHESSER H.Solid Propellant Microthruster Design for Nanosatellite Applications[J].Journal of Propulsion and Power,2011,27(6):1288-1294.
[2]SATHIYANATHAN K,LEE R,CHESSER H,et al.Yu SEND-1 solid propellant microthruster design,fabrication and testing[C].24thAnnual AIAA/USU Conference on Small Satellites.
[3]SATHIYANATHAN K,LEE R,STOWE R,et al.Memsbased solid propellant microthruster design for cubesat application[R].
[4]LINDSAY W,TEASDALE D,MILANOVIC V,et al.Thrust and electrical power from solid propellant microrockets.2.Actuators[C]//Micro Electro Mechanical Systems,2001.
[5]TEASDALE D,MILANOVIC V,CHANG P,et al.Microrockets for smart dust[J].Smart Materials and Structures,2001,10(6):1145.
[6]金峰.微型固体发动机组的结构设计及性能检测[D].上海:上海交通大学,2008.
[7]FRANKS A,LUTY M,ROBBIE C,et al.A design study of a microthrust balance for space applications[J].Nanotechnology,1998,9(2):61.
[8]沈瑞琪,叶迎华,戴实之.数字化火工技术的概念和应用[J].火工品,2000,(2):36-38.
[9]ZHANG K L,CHOU S K,ANG S S,et al.A MEMS-based solid propellant microthruster with Au/Ti igniter[J].Sensors and Actuators A:Physical,2005,122(1):113-123.
[10]ZHANG K L,CHOU S K,SIMON S A.Development of a Solid propellant microthruster with chamber and nozzle etched on a wafer surface[J].Journal of Micromechanics and Microengineering,2004,14(6):785-792.
[11]TEASDALE D.Solid propellant microrockets[D].Citeseer,2000.
[12]OKADA T,YAMADA Y,EBISUZAKI H,et al.Explosive Powders for Further Miniaturization of MEMS Rocket[C].The Fourth International Workshop on Micro and Nanotechnology for Power Generation and Energy Conversion Applications,Power MEMS,Kyoto,Japan,2004,56-59.
[13]CHAALANE A,ROSSI C,ESTEVE D.The formulation and testing of new solid propellant mixture(DB+x%BP)for a new MEMS-based microthruster[J].Sensors and Actuators A:Physical,2007,138(1):161-166.
[14]LEE J,KIM K,KWON S.Design,fabrication,and testing of MEMS solid propellant thruster array chip on glass wafer[J].Sensors and Actuators A:Physical,2010,157(1):126-134.
[15]SEO D,LEE J,KWON S.The development of the micro-solid propellant thruster array with improved repeatability[J].Journal of Micromechanics and Microengineering,2012,22(9):94004-94014.
[16]LEE J,KIM T.MEMS solid propellant thruster array with micro membrane igniter[J].Sensors and Actuators A:Physical,2013,190:52-60.
[17]LEWIS JR D H,JANSON S W,COHEN R B,et al.Digital micropropulsion[J].Sensors and Actuators A:Physical,2000,80(2):143-154.
[18]陈旭鹏,李勇,周兆英.采用双弹性元件级联的微小推力测量方法[J].清华大学学报(自然科学版),2004,44(2):205-208.
[19]陈玉华.小型化学能推进器的研究[D].南京:南京理工大学,2006.
[20]PARRA E,PISTER K,FERNANDEZ-PELLO C.Solid-Propellant Micro-Thruster[C].The Sixth International Workshop on Micro and Nanotechnology for Power Generation and Energy Conversion Application.Berkeley,U.S.A.2006:25-28.
[21]ROSSI C,LARANGOT B,LAGRANGE D,et al.Final characterizations of MEMS-based pyrotechnical microthrusters[J].Sensors and Actuators A:Physical,2005,121(2):508-514.
[22]LARANGOT B,ROSSI C,CAMPS T,et al.Solid propellant micro rockets—towards a new type of power MEMS[C].Proc Nanotech AIAA,Houston,TX,USA,2002,9-12.
[23]JU Y,MARUTA K.Microscale combustion:Technology development and fundamental research[J].Progress in Energy and Combustion Science,2011,37(6):669-715.
[24]FERNANDEZ-PELLO A C.Micropower generation using combustion:Issues and approaches[J].Proceedings of the Combustion Institute,2002,29(1):883-899.
[25]MARUTA K.Micro and mesoscale combustion[J].Proceedings of the Combustion Institute,2011,33(1):125-150.
[26]CHOU S K,YANG W M,CHUA K J,et al.Development of micro power generators—A review[J].Applied Energy,2011,88(1):1-16.
[27]毛成立,李葆萱,胡松启,等.热空气中硼粒子点火模型研究综述[J].推进技术,2001,22(1):6-9.
[28]庞维强,张教强,张琼方,等.硼粉的包覆及含包覆硼推进剂燃烧残渣成分分析[J].固体火箭技术,2006,29(3):204-221.
[29]臧令千.硼用作推进剂燃料组分的研究[J].推进技术,1990(4):56-62.
[30]李和平,汪洋,周俊虎,等.微小圆管中B/AP混合物燃料的传热和燃速研究[J].固体火箭技术,2013,36(5):632-636,646.
[31]李和平,杨卫娟,汪洋,等.含硼燃料在微小圆管中的点火燃烧特性研究[J].浙江大学学报(工学版),2014(5):917-922.
[32]刘建忠,梁导伦,汪洋,等.基于MEMS的固体燃料微推进技术研究进展[J].纳米技术与精密工程,2016,14(1):48-54.
[33]LIANG Daolun,LIN Jianzhong,ZHOU Junhu,et al.Combustion Characteristics and Propulsive Performance of Boron/Ammonium Perchlorate Mixtures in Microtubes[J].Journal of Energetic Materials.2016,34:297-317.
[34]李和平,汪洋,杨卫娟,等.草酸对微小圆管中B/AP混合物燃料点火特性的影响[J].固体火箭技术,2013,36(6):780-785.
[35]李和平,王纵涛,汪洋,等.含硼燃料在细管内点火燃烧特性的实验研究[J].推进技术,2014,35(4):559-564.
[36]XI Jianfei,LIN Jianzhong,WANG Yang,et al.Metal Oxides as Catalysts for Boron Oxidation[J].Journal of Propulsion and Power.2014,30(1):47-53.
[37]高丰,杨坤.高氯酸铵基复盐包覆硼粉的制备与表征[J].四川兵工学报,2015,36(9):142-144.
[2]SATHIYANATHAN K,LEE R,CHESSER H,et al.Yu SEND-1 solid propellant microthruster design,fabrication and testing[C].24thAnnual AIAA/USU Conference on Small Satellites.
[3]SATHIYANATHAN K,LEE R,STOWE R,et al.Memsbased solid propellant microthruster design for cubesat application[R].
[4]LINDSAY W,TEASDALE D,MILANOVIC V,et al.Thrust and electrical power from solid propellant microrockets.2.Actuators[C]//Micro Electro Mechanical Systems,2001.
[5]TEASDALE D,MILANOVIC V,CHANG P,et al.Microrockets for smart dust[J].Smart Materials and Structures,2001,10(6):1145.
[6]金峰.微型固体发动机组的结构设计及性能检测[D].上海:上海交通大学,2008.
[7]FRANKS A,LUTY M,ROBBIE C,et al.A design study of a microthrust balance for space applications[J].Nanotechnology,1998,9(2):61.
[8]沈瑞琪,叶迎华,戴实之.数字化火工技术的概念和应用[J].火工品,2000,(2):36-38.
[9]ZHANG K L,CHOU S K,ANG S S,et al.A MEMS-based solid propellant microthruster with Au/Ti igniter[J].Sensors and Actuators A:Physical,2005,122(1):113-123.
[10]ZHANG K L,CHOU S K,SIMON S A.Development of a Solid propellant microthruster with chamber and nozzle etched on a wafer surface[J].Journal of Micromechanics and Microengineering,2004,14(6):785-792.
[11]TEASDALE D.Solid propellant microrockets[D].Citeseer,2000.
[12]OKADA T,YAMADA Y,EBISUZAKI H,et al.Explosive Powders for Further Miniaturization of MEMS Rocket[C].The Fourth International Workshop on Micro and Nanotechnology for Power Generation and Energy Conversion Applications,Power MEMS,Kyoto,Japan,2004,56-59.
[13]CHAALANE A,ROSSI C,ESTEVE D.The formulation and testing of new solid propellant mixture(DB+x%BP)for a new MEMS-based microthruster[J].Sensors and Actuators A:Physical,2007,138(1):161-166.
[14]LEE J,KIM K,KWON S.Design,fabrication,and testing of MEMS solid propellant thruster array chip on glass wafer[J].Sensors and Actuators A:Physical,2010,157(1):126-134.
[15]SEO D,LEE J,KWON S.The development of the micro-solid propellant thruster array with improved repeatability[J].Journal of Micromechanics and Microengineering,2012,22(9):94004-94014.
[16]LEE J,KIM T.MEMS solid propellant thruster array with micro membrane igniter[J].Sensors and Actuators A:Physical,2013,190:52-60.
[17]LEWIS JR D H,JANSON S W,COHEN R B,et al.Digital micropropulsion[J].Sensors and Actuators A:Physical,2000,80(2):143-154.
[18]陈旭鹏,李勇,周兆英.采用双弹性元件级联的微小推力测量方法[J].清华大学学报(自然科学版),2004,44(2):205-208.
[19]陈玉华.小型化学能推进器的研究[D].南京:南京理工大学,2006.
[20]PARRA E,PISTER K,FERNANDEZ-PELLO C.Solid-Propellant Micro-Thruster[C].The Sixth International Workshop on Micro and Nanotechnology for Power Generation and Energy Conversion Application.Berkeley,U.S.A.2006:25-28.
[21]ROSSI C,LARANGOT B,LAGRANGE D,et al.Final characterizations of MEMS-based pyrotechnical microthrusters[J].Sensors and Actuators A:Physical,2005,121(2):508-514.
[22]LARANGOT B,ROSSI C,CAMPS T,et al.Solid propellant micro rockets—towards a new type of power MEMS[C].Proc Nanotech AIAA,Houston,TX,USA,2002,9-12.
[23]JU Y,MARUTA K.Microscale combustion:Technology development and fundamental research[J].Progress in Energy and Combustion Science,2011,37(6):669-715.
[24]FERNANDEZ-PELLO A C.Micropower generation using combustion:Issues and approaches[J].Proceedings of the Combustion Institute,2002,29(1):883-899.
[25]MARUTA K.Micro and mesoscale combustion[J].Proceedings of the Combustion Institute,2011,33(1):125-150.
[26]CHOU S K,YANG W M,CHUA K J,et al.Development of micro power generators—A review[J].Applied Energy,2011,88(1):1-16.
[27]毛成立,李葆萱,胡松启,等.热空气中硼粒子点火模型研究综述[J].推进技术,2001,22(1):6-9.
[28]庞维强,张教强,张琼方,等.硼粉的包覆及含包覆硼推进剂燃烧残渣成分分析[J].固体火箭技术,2006,29(3):204-221.
[29]臧令千.硼用作推进剂燃料组分的研究[J].推进技术,1990(4):56-62.
[30]李和平,汪洋,周俊虎,等.微小圆管中B/AP混合物燃料的传热和燃速研究[J].固体火箭技术,2013,36(5):632-636,646.
[31]李和平,杨卫娟,汪洋,等.含硼燃料在微小圆管中的点火燃烧特性研究[J].浙江大学学报(工学版),2014(5):917-922.
[32]刘建忠,梁导伦,汪洋,等.基于MEMS的固体燃料微推进技术研究进展[J].纳米技术与精密工程,2016,14(1):48-54.
[33]LIANG Daolun,LIN Jianzhong,ZHOU Junhu,et al.Combustion Characteristics and Propulsive Performance of Boron/Ammonium Perchlorate Mixtures in Microtubes[J].Journal of Energetic Materials.2016,34:297-317.
[34]李和平,汪洋,杨卫娟,等.草酸对微小圆管中B/AP混合物燃料点火特性的影响[J].固体火箭技术,2013,36(6):780-785.
[35]李和平,王纵涛,汪洋,等.含硼燃料在细管内点火燃烧特性的实验研究[J].推进技术,2014,35(4):559-564.
[36]XI Jianfei,LIN Jianzhong,WANG Yang,et al.Metal Oxides as Catalysts for Boron Oxidation[J].Journal of Propulsion and Power.2014,30(1):47-53.
[37]高丰,杨坤.高氯酸铵基复盐包覆硼粉的制备与表征[J].四川兵工学报,2015,36(9):142-144.