IEPC and. Takashi Wakizono 6 High Serve 780-7, Tomehara, Akiruno, Tokyo , Japan

Transcription

1 Flowfield Simulation and Pefomance Measuement of Electothemal Pulsed Plasma Thustes onboad Osaka Institute of Technology PROITERES Nano-Satellite Seies IEPC Pesented at the 33d Intenational Electic Populsion Confeence, The Geoge Washington Univesity Washington, D.C. USA Masato Tanaka 1, Rikio Muaoka, Shuya Kisaki 3, Chen Huanjun 4, Hiokazu Tahaa 5 Osaka Institute of Technology , Omiya, Asahi-Ku, Osaka 535*8585, Japan and Takashi Wakizono 6 High Seve 780-7, Tomehaa, Akiuno, Tokyo , Japan Abstact: The Poject of Osaka Institute of Technology Electic-Rocket-Engine onboad Small Space Ship (PROITERES) was stated at Osaka Institute of Technology in 007. In PROITERES, a nano-satellite with electothemal pulsed plasma thustes (PPTs) was successfully launched on Septembe 9 th, 01 by Indian PSLV launche C-1. The main mission is poweed flight of small/nano satellite by electic thuste. The PPT pefomance in the 1st PROITERES eached 5.0 Ns with no miss-fiing in gound expeiments. An unsteady numeical simulation was caied out to investigate physical phenomena in the PPT dischage system including plasma and dischage electic cicuit and to pedict pefomance chaacteistics fo small/nano satellites like PROITERES satellites. The calculated Mach numbe intensively inceased downsteam fom the dischage cavity exit; that is, the supesonic flow was established in the nozzle cathode. Both the calculated impulse bit and mass shot ageed well with the measued ones. The calculated esults of 40,000-shot enduance test also ageed with the measued ones. Futhemoe, the eseach and development of the nd PROITERES satellite with high-powe and lage-total-impulse PPT system ae intoduced. C e E i j J Nomenclatue = electic capacitance = intenal enegy o electon chage = coesponding voltage of ionization = cuent density = dischage cuent 1 Gaduate Student, Gaduate School Majo in Mechanical Engineeing, and tahaa@med.oit.ac.jp. Gaduate Student, Gaduate School Majo in Mechanical Engineeing, and tahaa@med.oit.ac.jp. 3 Gaduate Student, Gaduate School Majo in Mechanical Engineeing, and tahaa@med.oit.ac.jp. 4 Gaduate Student, Gaduate School Majo in Mechanical Engineeing, and tahaa@med.oit.ac.jp. 5 Pofesso, Depatment of Mechanical Engineeing, and tahaa@med.oit.ac.jp. 6 Reseache, Electic Populsion R&D Section, and tahaa@med.oit.ac.jp. 1

2 k = Boltzmann facto o heat conductivity L = electic inductance m = paticle mass M = momentum flux n = numbe density p = pessue q = heat flux Q = electic chage Q j = Joule heat = adial coodinate R = electic esistance t = time T = numbe density V = velocity z = axial coodinate = degee of ionization = paticle numbe flux = density p = electic esistance e-n = coss-section of electon-neutal collision = mass flux = tempeatue 0 = initial e = electon i = ion n = neutal = adial diection s = suface z = axial diection I. Intoduction HE Poject of Osaka Institute of Technology Electic-Rocket-Engine onboad Small Space Ship (PROITERES) Twas stated at Osaka Institute of Technology (OIT) in In PROITERES, a nano-satellite with electothemal pulsed plasma thustes (PPTs) was successfully launched by the Indian PSLV C-1 launche on Septembe 9 th, 01. The main mission is to achieve poweed flight of a nano-satellite by an electic thuste and to obseve Kansai distict in Japan with a high-esolution camea. Figue 1 and Table 1 show the specification and photo, espectively, of the flight model (FM) and launching of the PROITERES satellite. Just now, the PROITERES satellite is unde opeation; that is, the special FM command of PPT fiing is tansmitted to the satellite fom the gound station at OIT. Pulsed plasma thustes ae expected to be used as a thuste fo small/nano satellites The PPT has some featues supeio to othe kinds of electic populsion. It has no sealing pat, simple stuctue and high eliability, which ae benefits of using a solid popellant, mainly Teflon (poly-tetafluooethylene: PTFE). At Osaka Institute of Technology, the PPT has been studied since 003 in ode to undestand physical phenomena and impove thust pefomances with both expeiments and numeical simulations. We mainly studied electothemal-acceleation-type PPTs, which geneally had highe thust-to-powe atios (impulse bit pe unit initial enegy stoed in capacitos) and highe thust efficiencies than electomagnetic-acceleation-type PPTs. Although the electothemal PPT has lowe specific impulse than the electomagnetic PPT, the low specific impulse is not a significant poblem as long as the PPT uses solid popellant, because thee is no tank no valve fo liquid o gas popellant which would be a lage weight popotion of a thuste system. At OIT, the poject of nd PROITERES, as shown in Fig. and Table was stated in 010. The nd PROITERES satellite aims at poweed flight with longe distance, i.e. changing km in altitude on neaeath obits, than that of the 1st PROITERES. We ae developing high-powe and high-total-impulse PPT systems, in which conceptual designs of PPT system and initial pefomances ae investigated fo high-powe and high-totalimpulse opeations. In this pape, we intoduce numeical simulation poject to pedict pefomance of PPT systems fo PROITERES satellite seies at OIT. 5-31

3 Table 1. Specification of 1st PROITERES Satellite. Specifications Mass Dimensions Electical powe Altitude Development peiod Life time Obit Launch vehicle Value 14.5kg Cube, 300mm on a side 10W 670km 4yea Moe than one yea Sun-synchonous obit PSLV Fig. 1. Photos of 1st PROITERES satellite FM and launching. Table. Specification of nd PROITERES satellite. Specifications Mass Dimensions Electical powe Development peiod Life time Value 50kg Cube, 500mm on a side 6W 3yea Moe than one yea Launching due date The second half of 014 Main missions Long-distance powe flight Fig.. Illustation ofnd PROITERES satellite. II. Thust Measuement System Figue 3 shows a thust stand in a vacuum chambe fo pecise measuement of an impulse bit The PPT and capacitos ae mounted on the pendulum, which otates aound fulcums of two knife edges without fiction. The displacement of the pendulum is detected by an eddy-cuent-type gap senso (non-contacting mico-displacement mete) nea the PPT, which esolution is about ±0.5 m. The electomagnetic dampe is used to suppess mechanical noises and to decease quickly the amplitude fo the next measuement afte fiing the PPT. It is useful fo a sensitive thust stand because it is non-contacting. The dampe consists of a pemanent magnet fixed to the pendulum and two coils fixed to the suppoting stand. The contol cicuit diffeentiates the output voltage of the displacement senso and supplies the cuent popotional to the diffeentiated voltage to the coil. Accodingly, the dampe woks as a viscosity esisto. The dampe is tuned off just befoe fiing the PPT fo measuements without damping, and tuned on afte the measuement to pepae fo the next measuement. Figue 4 shows a typical signal of displacement in measuement of impulse bit. Sensitiveness of the thust stand is vaiable by changing the weight mounted on the top of the pendulum as shown in Fig. 5. A calibation of the thust stand is caied out by collisions of balls to the pendulum with vaious balls fom vaious distances coesponding to Ns. Figue 6 shows a vacuum chambe 1.5 m in length and 0.6 m in inne diamete, which is evacuated using a tubo-molecula pump with a pumping speed of 3,000 l/s. The pessue is kept below 1.0x10 - Pa duing PPT opeation. 3

4 Amplitude pe Impulse bit, μ m/μ Ns Displacement, μ m Fig. 3. PPT expeimental system Time, s PPT dischage -100 Dampe ON Dampe OFF Fig. 4. Typical signal of displacement in measuement of impulse bit Additional weight, kg Fig. 5. Sensitiveness of thust stand vs top weight. Fig. 6. PPT expeimental system installed in vacuum chambe III. Numeical Calculation A. Calculation model An unsteady numeical simulation is caied out to investigate physical phenomena in the PPT dischage system including plasma and dischage electic cicuit and to pedict pefomance chaacteistics. -31 Figue 7 shows the calculation model of the PPT system. The calculation simultaneously simulates unsteady phenomena of dischage in the cicuit, heat tansfe to the PTFE, heat conduction inside the PTFE, ablation fom the PTFE suface and plasma flow. The calculation domain of the dischage chambe, as shown in Fig. 8, in the nozzle cathode and in the cylindical cavity made of PTFE (Teflon). The length and diamete of the cavity ae changed consideing opeational conditions. 4

5 PPT R p Fluid Continuity equation Eule equation Enegy equation L c Popellant Heat equation Capacito Popellant-plasma Heat tansfe Ablation C R c L tan R tan Tansmission line Plasma Ionization Joule heating LCR cicuit Cicuit equation Fig. 7. Calculation model fo PPT system. Fig. 8. Calculation domain. B. Govening equations The axisymmetic two-dimensional unsteady flowfield equations, consevation equations of mass, momentum and enegy, ae witten as follows: Mass: 1 M (1) M z M t z Momentum (Eule Eqs.): -diection: z-diection: Enegy: M t M t z M M M z 1 M p z M M M e t z M z 1 M M p z M z z e p e p e p Q j whee, p, and e ae density, pessue and intenal enegy of flow, espectively, and M and M z ae momentum fluxes of aidial and axial diections, espectively. Q j is Joule heat. Ionization equilibium is assumed as follows: Saha Eq.: 5/ 3/ kt (m qe (5) e) i.6 exp 3 1 p h kt whee and T ae degee of ionization and tempeatue of flow, espectively, and E i is coesponding voltage of ionization, in which the aveage ionization voltage of PTFE decomposed atoms (cabon and hydogen etc.) ae used. The Joule heat is witten as follows: (6) Q j p j ln p T 3/ m n e ee ln ln[1n ( kt / e n ) e en 3/ 0 e ] whee p is electic esistance coesponding electon-ion and electon-neutal collisions, in which n e and n n ae densities of electon and neutal, espectively, and j is cuent density in axial diection. 5 z 1 M 3kT n n me 1/ () (3) (4)

6 Figue 9 shows the model of heat fluxes fom plasma to PTFE suface in the cavity, and thei heat fluxes and the inteaction ae witten as follows: Heat convection: (7) qh, conv ai i n kt h, w Ts Heat conduction: Inteaction Eq.: q h, cond Th, k w (8) q h, conv qh, cond (9) whee i and n ae paticle numbe fluxes of ion and neutal, espectively, to PTFE suface. In evapoation of PTFE on the cavity wall, we uses the following equations: Langmui s law: Evapoation heat flux: Γ m n kt s 1 p p vap pc exp Tc / Ts ( ) p c = Pa T c = 0815 K qab kt m n s whee and q ab ae mass and heat fluxes, espectively, fom PTFE suface, and p va and T s ae evapoation pessue and PTFE suface tempeatue, espectively. In heat conduction inside the PTFE block, the heat conduction equation and the bounday condition ae witten as follows: t 0 PTFE C p ( Q whee is tempeatue inside the PTFE. Finally, we close the equation system by using the following electic cicuit equation: Fom Fig. 7: vap 1 z conv Q ab ) (10) (11) (1) Q ( L L ) Q ( R R R ) Q tan c tan c p 0 C J Q (13) Initial condition: Q0 CV 0 6

7 Tempeatue he,w Te,w T Te=ThT (LTE) PTFE ne(=ni), nn Th,w Ts Plasma Knudsen laye ne(=ni), nn,w Fig. 9. Heat tansfe inside PTFE. C. Calculation pocedue and conditions Afte all equations wee nomalized, the flowfield equations ae numeically solved by TVD-MacComack scheme and aveage of Roe. In the calculation pocess, the electic cicuit equation is solved by Runge-Kutta method, and the axial cuent density is obtained. The bounday conditions shown in Fig. 10 ae assumed. Fo calculation stat, a vey low density plasma is distibuted just befoe the calculation. The calculation gid sizes ae 0.5 mm in axial diection and 0.05 mm in adial diection, and the time step is 10-9 s. The expeimental and calculation conditions ae shown in Tables 3-5. The dischage enegies pe one shot ae 14.6 and.4 J/shot; that is, the capacitance is changed. Accodingly, the length and diamete of dischage cavity ae changed to find pefeable cavity configuation. The dischage enegy pe one shot is loweed to.4 J/shot fo the nano satellite. B. C 1 B. C B. C 3 B. C 4 0 z 0 z 0 z M z M M M ab M M z z M z M z M z M z e e 0 z e 0 z e 0 e Q ab Q conv Fig. 10. Bounday conditions. 7

8 Table 3. Expeimental and calculating condition with dischage enegy pe one shot of 14.6 J/s. Dischage chambe Length, mm 19 Diamete, mm.5, 3.0, 3.5 Nozzle Length, mm 3 Half angle, degee 0 Chaging voltage, V 1800 Capacitance, μf 9.0 Table 4. Expeimental and calculating condition with dischage enegy pe one shot of.4 J/s. Dischage chambe Length, mm 9.0 Diamete, mm 1.0, 1.5,.0,.5 Nozzle Length, mm 3 Half angle, degee 0 Chaging voltage, V 1800 Capacitance, μf 1.5 Table 5. Expeimental and calculating condition of enduance test. Dischage chambe Length, mm 10.0 Diamete, mm 1.0 Nozzle Length, mm 3 Half angle, degee 0 Capacitance, μf 1.5 Chaging voltage, V 1800 Inductance, μh 0.35 Resistance, Ω 0.05 IV. Results and Discussion A. Physical featue in dischage chambe Figue 11 shows typical measued and calculated dischage cuent signals with a dischage enegy of 14.6 J/s. The calculated cuent signal agees with the measued one. Figue 1 shows the calculated Mach numbe distibution just afte 3 s fom the dischage stat with 14.6 J/s. The Mach numbe intensively inceases downsteam fom z=19mm; that is, the supesonic flow is established. At z=35mm, the Mach numbe dastically deceases downsteam, esulting fom stuctue of shock wave. Figue 13 shows the calculated time histoies of nomalized density, thust, ablated mass and Joule heating at =1.5mm and z=9.5mm with 14.6 J/s. The Joule heating begins at appoximately 1 s; it is completed by 7 s, and the ablation fom the PTFE suface elays about 1- s fom the Joule heating. The density gadually inceases fom about s; it has a peak at 9 s, and then it deceases. The thust gadually inceases fom 4 s, and it has a peak at 13 s. Accodingly, The thust is geneated until ove 0 s. Thust geneation is expected to be elated to incease in density. Figue 14 shows axial the calculated distibutions of nomalized density, velocity and ablation flux nea the cavity wall just afte 10 s fom the dischage stat with 14.6 J/s. The velocity linealy inceases fom the upsteam end to the cavity exit although the density gadually deceases. An axial decease in ablation flux is due to the axial decease in density because of loweing heat convection to the PTFE suface. 8

9 Nomalized density, thust, Density, velocity and ablation flux Dischage cuent [A] Expeimental Numeical Time [s] Fig. 11. Dischage cuent signal Fig. 1. Mach numbe distibution. ablated mass and Joule heating Density Thust Ablated mass Joule heating Density Velocity Ablation flux Time [s] Fig. 13. Nomalized density, thust, Joule heating and ablated mass z position [mm] Fig. 14. Nomalized density, velocity and ablation flux. B. Compaisons with expeimental esults Figue 15 shows measued and calculated impulse bit and mass shot dependent on cavity diamete with a constant cavity length of 19 mm with a dischage enegy pe one shot of 14.6 J/s. Both the impulse bit and the mass shot decease with inceasing cavity diamete egadless of calculation and expeiment. The calculated impulse bit oughly agees with the measued one although with a small diamete of.5 mm it is slightly highe. On the othe hand, the calculated mass shot agees with the measued one, and its eo is within 10 % although it is lowe with all cavity diametes. Figue 16 shows measued and calculated impulse bit and mass shot dependent on cavity diamete with a constant cavity length of 9 mm with a dischage enegy pe one shot of.4 J/s. Both the calculated impulse bit and mass shot ageed with the measued ones even with low dischage enegies. C. Calculated enduance test esults We simply calculated epetitive opeation modes, i.e., enduance tests of the PPT system by using a onedimensional model with the same assumptions of the axisymmetic model. Figue 17 shows the calculated esults. Both the impulse bit and the mass shot have the maximum eos of 5 % compaed with the measued ones in the ange up to 0,000 shots. Howeve, they agee well with the measued ones in the long opeation above 0,000 shots. 9

10 Impulse bit [ Ns] Mass shot [ g] Impulse bit [ Ns] Mass shot [ g] Impulse bit [ Ns] Mass shot [ g] Expeimental Numeical Expeimental Numeical Cavity diamete [mm] Cavity diamete [mm] (a) (b) Fig. 15. Expeimental and numeical esults with dischage enegy pe one shot of 14.6 J/s. a) Impulse bit; b) Mass shot Expeimental Numeical 40 Expeimental Numeical Cavity diamete [mm] Cavity diamete [mm] (a) (b) Fig. 16. Expeimental and numeical esults with dischage enegy pe one shot of.4 J/s. a) Impulse bit; b) Mass shot Expeimental Numeical Expeimental Numeical Shot numbe [shot] Shot numbe [shot] (a) (b) Fig. 17. Expeimental and numeical esults of enduance test with.4 J/s. a) Impulse bit; b) Mass shot

11 Impulse bit, μns Mass shot, μg Mass shot, μg V. PPT Pefomance Pediction fo nd PROITERES Satellite The chaging enegy is changed fom.4 J/s fo the 1st PROITERES satellite to 31.6 J/s fo the nd PROITERES one. D. Cavity length dependence The calculation was caied out fo single shot (initial condition) and 400 shots with a constant cavity diamete of 5 mm and changing lengths of 10-5 mm. As shown in Figs. 18 and 19, both the impulse bit and the mass shot incease with cavity length. The pefomance with single initial shot is highe than that afte 400 shots. The maximum impulse bit of about 1.5 Ns was pedicted with a cavity length of 5 mm shot 400 shots Cavity length, mm Fig. 18. Cavity length dependence of impulse bit. Fig. 19. Cavity length dependence of mass shot. E. Cavity diamete dependence With a cavity length of 10 mm, the cavity diamete was changed fom.4 to 5 mm. As shown in Figs. 0 and 1, both the impulse bit and the mass loss linealy decease with inceasing cavity diamete. This is expected because of deceasing pessue in the cavity when inceasing cavity diamete. Of couse, the pefomance with single initial shot is highe than that afte 400 shots. The maximum impulse bit aound Ns was pedicted with a cavity diamete of.4 mm shot 400 shots 1 shot 400 shots Cavity diamete, mm 4 6 Cavity diamete, mm Fig. 0. Cavity diamete dependence of impulse bit. Fig. 1. Cavity diamete dependence of Mass shot. 11

12 Impulsebit,μNs Mass Shot[μg] F shot enduance test pefomance In calculation fo enduance, the cavity length and diamete wee set to 5 mm and 5 mm, espectively, with a constant chaging enegy of J/shot. The calculation esult of shots is shown in Fig.. Both the impulse bit and mass consumption deceases with inceasing shot numbe. This is expected because the cavity diamete becomes lage with inceasing shot numbe Shot Numbe (a) Shot numbe[shot] (b) Fig.. Numeical esults of enduance test with J/s. a) Impulse bit; b) Mass shot. VI. Summay The Poject of Osaka Institute of Technology Electic-Rocket-Engine onboad Small Space Ship (PROITERES) was stated at Osaka Institute of Technology in 007. In PROITERES, a nano-satellite with electothemal pulsed plasma thustes (PPTs) was launched on Septembe 9 th, 01 by Indian PSLV launche C-1. The main mission is poweed flight of small/nano satellite by electic thuste. The PPT pefomance in 1st PROITERES eached 5.0 Ns with no miss-fiing. An unsteady numeical simulation was caied out to investigate physical phenomena in the PPT dischage system including plasma and dischage electic cicuit and to pedict pefomance chaacteistics fo small/nano satellites like PROITERES satellites. The calculated Mach numbe intensively inceased downsteam fom the dischage cavity exit; that is, the supesonic flow was established in the nozzle cathode. Both the calculated impulse bit and mass shot ageed well with the measued ones. The calculated esults of 40,000-shot enduance test also ageed with the measued ones. Futhemoe, the eseach and development of the nd PROITERES satellite with high-powe and lage-total-impulse PPT system wee investigated. The pefomance was pedicted with changing cavity length and diamete, and the enduance test was also calculated. The maximum impulse bit of 1-.5 Ns was pedicted. Refeences 1 Ikeda, T., Yamada, M., Shimizu, M., Fujiwaa, T., Tahaa, H. and Satellite R&D Team of Students and Faculty Membes of OIT, Reseach and Development of an Attitude Contol System fo Osaka Institute of Technology Electic-Rocket-Engine onboad Small Space Ship, 7th Intenational Symposium on Space Technology and Science, Tsukuba, Japan, 009, Pape No. ISTS 009-s-0f. Yamada, M., Ikeda, T., Shimizu, M., Fujiwaa, T., Tahaa, H. and Satellite R&D Team of Students and Faculty Membes of OIT, Pogess of Poject of Osaka Institute of Technology Electic-Rocket-Engine onboad Small Space Ship, 7th Intenational Symposium on Space Technology and Science, Tsukuba, Japan, 009, Pape No. ISTS 009-s-05f. 3 Yamada, M., Ikeda, T., Fujiwaa, T. and Tahaa, H., Poject of Osaka Institute of Technology Electic-Rocket-Engine onboad Small Space Ship, 31st Intenational Electic Populsion Confeence, Univesity of Michigan, Ann Abo, Michigan, USA, 009, Pape No. IEPC Aaki, S., Ikeda, T., Ozaki, J., Nishizawa, M,. Inoue, Y., Iguchi, T. and Tahaa, H., Development of an Attitude Contol System fo Nano-Satellite PROITERES, 8th Intenational Symposium on Space Technology and Science, Okinawa Convention Cente, Ginowan-City, Okinawa, Japan, 011, Pape No. ISTS 011-j-1s. 1

13 5 Nishizawa, M., Ikeda, T., Ozaki, J., Tahaa, H., Watanabe, Y., Enoguchi, A. and Takyama, N.," Development of a High- Resolution Camea System onboad Nano-Satellite PROITERES," 8th Intenational Symposium on Space Technology and Science, Okinawa Convention Cente, Ginowan-City, Okinawa. Japan, 011, Pape No. ISTS 011-n Ikeda, T., Ozaki, J., Aaki, S., Nishizawa, M., Inoue, Y., Iguchi, T., Tahaa, H., and Watanabe, Y.," Reseach and Development of Nano-Satellite PROITERES Seies at Osaka Institute of Technology," 8th Intenational Symposium on Space Technology and Science" Okinawa Convention Cente, Ginowan-City, Okinawa, Japan, 011, Pape No. ISTS 011-j-1. 7 Ozaki, J., Ikeda, T., Aaki, S., Nishizawa, M., Inoue, Y., Iguchi, T., Tahaa, H. and Watanabe, Y.," Development of Nano- Satellite PROITERES with Electic Rocket Engines at Osaka Institute of Technology," 8th Intenational Symposium on Space Technology and Science, Okinawa Convention Cente, Ginowan-City, Okinawa, Japan, 011, Pape No. ISTS 011-b Ozaki, J., Ikeda, T., Fujiwaa, T., Nishizawa, M., Aaki, S., Tahaa, H. and Watanabe, Y.," Development of Osaka Institute of Technology Nano-Satellite PROITERES with Electothemal Pulsed Plasma Thustes," 3nd Intenational Electic Populsion Confeence, Kuhaus, Wiesbaden, Gemany, 011, Pape No. IEPC Inoue, Y., Ozaki, J., Ikeda, T., Tahaa, H. and Watanabe, Y.," Reseach and Development of Osaka Institute of Technology Nano-Satellite PROITERES with Electothemal Pulsed Plasma Thustes," Asian Joint Confeence on Populsion and Powe 01, Gand New Wold Hotel, Xi'an, China, 01, Pape No. AJSPP Egami, N., Inoue, Y., Nakano, S., Ikeda, T. and Tahaa, H., Reseach and Development of Nano-Satellite PROITERES with Electic Rocket Engines at Osaka Institute of Technology, 8th IEEE Vehicle Powe and Populsion Confeence, Olympic Paktel, Seoul, Koea, 01, Pape No. SS Kamimua, T., Yamasaki, K., Egami, N., Matsuoka, T., Sakamoto, M., Inoue, Y., Ikeda, T. and Tahaa, H.," Final Checking Pocess and Launch of the Osaka Institute of Technology 1 st PROITERES Nano-Satellite Using Indian PSLV Rocket C-1," 9th Intenational Symposium on Space Technology and Science, Nagoya Congess Cente, Nagoya-City, Aichi, Japan, 013, Pape No. ISTS 013-f-48p. 1 Egami, N., Matsuoka, T., Sakamoto, M., Inoue, Y., Ikeda, T. and Tahaa, H., R&D, Launch and Initial Opeation of the Osaka Institute of Technology 1st PROITERES Nano-Satellite and Development of the nd and 3d Satellites," 9th Intenational Symposium on Space Technology and Science, Nagoya Congess Cente, Nagoya-City, Aichi, Japan, 013, Pape No. ISTS 013-f Egami, N., Matsuoka, T., Sakamoto, M., Inoue, Y., Ikeda T. and Tahaa, H., R&D, Launch and Initial Opeation of the Osaka Institute of Technology 1st PROITERES Nano-Satellite with Electoothemal Pulsed Plasma Thustes and Development of the nd satellite, 33nd Intenational Electic Populsion Confeence, Geoge Washington Univesity, Washington, D.C., USA, 013, Pape No. IEPC Takagi, H., Yamamoto, T., Ishii, Y. and Tahaa, H., Pefomance Enhancement of Electothemal Pulsed Plasma Thustes fo Osaka Institute of Technology Electic-Rocket-Engine onboad Small Space Ship, 7th Intenational Electic Populsion Confeence, Tsukuba, Japan, 009, Pape No. ISTS 009-b Takagi, H., Yamamoto, T., Ishii, Y. and Tahaa, H., Pefomance Enhancement of Electothemal Pulsed Plasma Thustes fo Osaka Institute of Technology Electic-Rocket-Engine onboad Small Space Ship, 31th Intenational Electic Populsion Confeence, Univesity of Michigan, Ann Abo, Michigan, USA, 009, Pape No. IEPC Naka, M., Tanaka, M., Tahaa, H., Watanabe, Y. and Wakizono, T.," Development of Electothemal Pulsed Plasma Thuste System Flight-Model onboad Nano-Satellite PROITERES," 8th Intenational Symposium on Space Technology and Science" Okinawa Convention Cente, Ginowan-City, Okinawa, Japan, 011, Pape No. ISTS 011-b Naka, M., Hosotani, R., Tahaa, H. and Watanabe, Y.," Development of Electothemal Pulsed Plasma Thuste System Flight-Model fo the PROITERES Satellite," 3nd Intenational Electic Populsion Confeence, Kuhaus, Wiesbaden, Gemany, 011, Pape No. IEPC Kawamua, T., Fujiwaa, K., Uemua, K., Muaoka, R., Chen, H., Kisaki, S., Tanaka, M., Tahaa, H. and Wakizono, T.," Reseach and Development of Electothemal Pulsed Plasma Thuste Systems fo Osaka Institute of Technology PROITERES Nano-Satellite Seies," 9th Intenational Symposium on Space Technology and Science, Nagoya Congess Cente, Nagoya-City, Aichi, Japan, 013, Pape No. ISTS p. 19 Muaoka, R., Chen, H., C., Kisaki, S., Tanaka, K., Tahaa, H. and Wakizono, T.," Pefomance Chaacteistics of Electothemal Pulsed Plasma Thuste Systems onboad Osaka Institute of Technology PROITERES Nano-Satellite Seies," 9th Intenational Symposium on Space Technology and Science, Nagoya Congess Cente, Nagoya-City, Aichi, Japan, 013, Pape No. ISTS 013-b Kisaki, S., Muaoka, R., Chen, H., Tanaka, M., Egami, N., Ikeda, T., Tahaa, H. and Wakizono, T.," Reseach and Development of Osaka Institute of Technology PROITERES Nano-Satellite Seies with Electothemal Pulsed Plasma Thuste Systems," 9th Intenational Symposium on Space Technology and Science, Nagoya Congess Cente, Nagoya-City, Aichi, Japan, 013, Pape No. ISTS 013-b Kisaki, S., Muaoka, R., Chen, H., Tanaka, M., Tahaa, H., Wakizono, T., Reseach and Development of 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L., Pefomance and Heat Loss of a Coaxial Teflon Pulsed Thuste, 7th Intenational Electic Populsion Confeence, Pasadena, Califonia, USA, 001, Pape No. IEPC Buton, R. L. and Tuchi, P. J., Pulsed Plasma Thuste, Jounal of Populsion and Powe, Vol.14, No.5, 1998, pp

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