新型高效微推进技术研究
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摘要
微小卫星组网编队飞行可以完成许多复杂昂贵的大卫星所无法完成的工作,其关键在于卫星编队的形成与保持。因此,对微小卫星间相对轨道位置的保持、高精度的姿态控制提出较高的要求。所需推力小,精度高,一般为毫牛,甚至微牛量级。本文针对百公斤级微小卫星姿控的需求,以研制一个高效双氧水化学微推力系统原理样机为目标,研究内容包括自增压燃料箱,基于MEMS的微型推进器及其真空微推力性能测试,芯片内部流动光学可视化观测等。
推进系统占卫星总体质量比重较大,传统系统通常包含高压气瓶,减压阀等,系统部件比较多,质量大,难于微型化。本文发明了一种自增压燃料箱,使用小加热器控制NH_4HCO_3分解产生气体的方式进行燃料箱的增压。该系统结构简单,重量轻,易于微型化。
优化设计了一款MEMS推进器芯片B,该芯片的流道采用S型流道非对称结构,增加工质在腔体内滞留时间;催化腔采用密排微柱结构,大大增加了催化面积,使双氧水催化反应更为充分。在硅芯片背面直接加工金属薄膜加热器。整个芯片B结构紧凑,充分利用反应热,减少热损失。
搭建了真空微推力测试实验台。采用杠杆力的放大原理进行微推力测量,使用真空油阻尼系统降低环境噪音干扰。通过实验发现了只要测力探头足够大,喷嘴喷出的气流对探头的冲击力随着冲击距离的增大而出现一个高平台区。在该区内冲击力几乎维持不变,而且与喷嘴的推力大致相等。从而找到了一种采用合适大小的测力探头在高平台区的距离范围内进行冲击力测量来间接测量微型冷气推进器微推力的方法,避免了推进器引线干扰的问题。
最后以芯片A为喷口,外加Pt丝增加催化表面和电辅助加热的方法研制了一款微型双氧水推进器。该推进器克服了硅芯片与其它金属管道部件的密封连接问题。并进行了推进性能测试实验。采用液柱压差法测量了微流量。经测试表明该款微型双氧水推进器在入口绝压为2～3bar时获得4～6mN的平均推力;加热仅为2～3w的情况下获得的200s左右的比冲,达到了预期的研制目标。
Multiply small satellites can make up of a team of formation flying and then accomplish a mission that an expensive big satellite can not. It is crucial for Formation flying of small satellites to keep in very precise position and orientation. Then small satellites need to control their track and attitude precisely. They need very small thrust, usually milli-Newton. even micro-Newton.In this article our objective is to develop a high efficient hydrogen dioxide micro-propulsion system aim to apply on a nano-satellite of tens of kilogram. The research includes a self-pressurizing fuel tank, fabrication of a MEMS-based microthruster and thrust measurement in vacuum, using optical microscope and high-speed camera to observe the flow field in the chip, etc.
Propulsion system usually takes up a large fraction of weight of a satellite. The traditional propulsion system contains many components such as high pressure pressurant bottle, pressure regulator and so on. It is hard to microminiaturize traditional propulsion system. In this article a self-pressurizing fuel tank is invented. It use a micro-heater to heat to decompose NH4HCO3 and generate gas to increase the pressure of the fuel tank. This structure of the system is simple and the weight is light. It is easy to be microminiaturized.
In this article, we design a MEMS microthruster chip B. This chip's fluid path is not straight and symmetry, as usually, instead, it has a S shap of flow path. This design make the fuel stay more time in the chip; the catalyse chamber is made up of micro-pillar array. The micro-pillar array greatly enlarges the catalystic area, and increase the decomposition rate. The whole chip B is compact, can use the reaction heat efficiently, and reduces the heat loss.
A micro-thrust test stand in vacuum was setup. It adopts a lever to enlarge the micro-thrust force and a vacuum oil damping system to reduce the noise from surrounding. Through experiments, we found that the impinging force reaches a plateau section with the increase of impinging distance if only the impinging plate is big enough. In the plateau section, the impinging force is almost equal to the thrust force. Then, one can measure the impinging force instead of the direct thrust force measurement. By this method, the disturbance of connecting lines is avoided completely.
At last, we use chip A as nozzle, adding Pt silk as accessorial catalystic surface, and equipped with electronic heater, to prepare a H_2O_2 micro-thruster. The problem of the silicon chip connected with stainless steel component is addressed. Then the micro-thruster is tested. The micro-flow rate of the micro-thruster is measured by liquid column differential pressure method. The test result show that this kind of micro-thruster can produce 4～5 mN thrust force with 2～3 bar inlet pressure; the specific impulse reach about 200 s with 2～3 w heating power.
推进系统占卫星总体质量比重较大,传统系统通常包含高压气瓶,减压阀等,系统部件比较多,质量大,难于微型化。本文发明了一种自增压燃料箱,使用小加热器控制NH_4HCO_3分解产生气体的方式进行燃料箱的增压。该系统结构简单,重量轻,易于微型化。
优化设计了一款MEMS推进器芯片B,该芯片的流道采用S型流道非对称结构,增加工质在腔体内滞留时间;催化腔采用密排微柱结构,大大增加了催化面积,使双氧水催化反应更为充分。在硅芯片背面直接加工金属薄膜加热器。整个芯片B结构紧凑,充分利用反应热,减少热损失。
搭建了真空微推力测试实验台。采用杠杆力的放大原理进行微推力测量,使用真空油阻尼系统降低环境噪音干扰。通过实验发现了只要测力探头足够大,喷嘴喷出的气流对探头的冲击力随着冲击距离的增大而出现一个高平台区。在该区内冲击力几乎维持不变,而且与喷嘴的推力大致相等。从而找到了一种采用合适大小的测力探头在高平台区的距离范围内进行冲击力测量来间接测量微型冷气推进器微推力的方法,避免了推进器引线干扰的问题。
最后以芯片A为喷口,外加Pt丝增加催化表面和电辅助加热的方法研制了一款微型双氧水推进器。该推进器克服了硅芯片与其它金属管道部件的密封连接问题。并进行了推进性能测试实验。采用液柱压差法测量了微流量。经测试表明该款微型双氧水推进器在入口绝压为2～3bar时获得4～6mN的平均推力;加热仅为2～3w的情况下获得的200s左右的比冲,达到了预期的研制目标。
Multiply small satellites can make up of a team of formation flying and then accomplish a mission that an expensive big satellite can not. It is crucial for Formation flying of small satellites to keep in very precise position and orientation. Then small satellites need to control their track and attitude precisely. They need very small thrust, usually milli-Newton. even micro-Newton.In this article our objective is to develop a high efficient hydrogen dioxide micro-propulsion system aim to apply on a nano-satellite of tens of kilogram. The research includes a self-pressurizing fuel tank, fabrication of a MEMS-based microthruster and thrust measurement in vacuum, using optical microscope and high-speed camera to observe the flow field in the chip, etc.
Propulsion system usually takes up a large fraction of weight of a satellite. The traditional propulsion system contains many components such as high pressure pressurant bottle, pressure regulator and so on. It is hard to microminiaturize traditional propulsion system. In this article a self-pressurizing fuel tank is invented. It use a micro-heater to heat to decompose NH4HCO3 and generate gas to increase the pressure of the fuel tank. This structure of the system is simple and the weight is light. It is easy to be microminiaturized.
In this article, we design a MEMS microthruster chip B. This chip's fluid path is not straight and symmetry, as usually, instead, it has a S shap of flow path. This design make the fuel stay more time in the chip; the catalyse chamber is made up of micro-pillar array. The micro-pillar array greatly enlarges the catalystic area, and increase the decomposition rate. The whole chip B is compact, can use the reaction heat efficiently, and reduces the heat loss.
A micro-thrust test stand in vacuum was setup. It adopts a lever to enlarge the micro-thrust force and a vacuum oil damping system to reduce the noise from surrounding. Through experiments, we found that the impinging force reaches a plateau section with the increase of impinging distance if only the impinging plate is big enough. In the plateau section, the impinging force is almost equal to the thrust force. Then, one can measure the impinging force instead of the direct thrust force measurement. By this method, the disturbance of connecting lines is avoided completely.
At last, we use chip A as nozzle, adding Pt silk as accessorial catalystic surface, and equipped with electronic heater, to prepare a H_2O_2 micro-thruster. The problem of the silicon chip connected with stainless steel component is addressed. Then the micro-thruster is tested. The micro-flow rate of the micro-thruster is measured by liquid column differential pressure method. The test result show that this kind of micro-thruster can produce 4～5 mN thrust force with 2～3 bar inlet pressure; the specific impulse reach about 200 s with 2～3 w heating power.
引文
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[4]A.P.London,A.A.Ayon,A.H.Epstein,et al.,Microfabrication of a high pressure bipropellant rocket engine[J].Sensors and Actuators A,2001,92:351-357.
[5]D.Platt,A Monopropellant milli-newton thruster system for attitude control of nanosatellites,16th Annual USU Conference on Small Satellites,2002,SSC02-Ⅶ-4.
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[9]T.Ishikawa,S.Satori,H.Okamoto,et al.,Status of nanosatellite development for mothership daughtership space experiment by Japanese universities,14th Annual USU Conference on Small Satellites,2000,SSC00-Ⅱ-7.
[10]C.Phipps,J.Luke,Diode Laser-driven microthrusters:a new departure for micropropulsion[J].AIAA Journal,2002,40(2):310-318.
[11]E.V.Mukerjee,A.P.Wallace,K.Y.Yan,et al.,Vaporizing liquid microthruster[J],sensors and actuators A,2000,83:231-236.
[12]D.H.Lewis Jr,S.W.Janson,R.B.Cohen,et al.Digital micropropulsion[J].Sensors and Actuators A,2000,80(2):143-154.
[13]K.Takahashi,H.Ebisuzaki,H.Kajiwara,et al.Design and testing of mega-bit microthruster arrays[J].Nanotech AIAA 2002-5758,Houston.
[14]C.Rossi,B.Larangot,T.Camps,et al.Solid propellant micro-rockets-towards a new type of power MEMS[J].Nanotech AIAA 2002-5758,Houston.
[15]Andrew D Ketsdever,Riki H Lee et al.,Performance testing of a microfabricated propulsion system for nanosatellite applications[J].J.Micromech.Microeng.2005,15:2254-2263.
[16]Robert L.Bayt,Analysis,fabrication and testing of a MEMS-based micropropulsion system[D].[Ph.D.].Cambriage,MA:Massachusetts Institute of Technology,1999.
[17]Chen Xupeng,Li Yong,Zhou Zhaoying,Fan Ruili,A homogeneously catalyzed micro-chemical thruster[J].Sensors and Actuators A,2003,108:149-154.
[18]Ye X Y,Tang F,Ding H Q,Zhou Z.Y,Study of a vaporizing water micro-thruster[J].Sensors and Actuators A,2001,89:159-165.
[19]蔡建.激光微推进的原理和应用研究[D].合肥:中国科学技术大学,2007.
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