Research Papers: Heat and Mass Transfer

Selection and Characterization of Green Propellants for Micro-Resistojets

[+] Author and Article Information
Daduí C. Guerrieri

Space Engineering Department,
Faculty of Aerospace Engineering,
Delft University of Technology,
Delft 2629 HS, The Netherlands
e-mail: D.CordeiroGuerrieri@tudelft.nl

Marsil A. C. Silva, Angelo Cervone, Eberhard Gill

Space Engineering Department,
Faculty of Aerospace Engineering,
Delft University of Technology,
Delft 2629 HS, The Netherlands

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received December 6, 2016; final manuscript received April 19, 2017; published online May 23, 2017. Editor: Portonovo S. Ayyaswamy.

J. Heat Transfer 139(10), 102001 (May 23, 2017) (9 pages) Paper No: HT-16-1787; doi: 10.1115/1.4036619 History: Received December 06, 2016; Revised April 19, 2017

The number of launches of nano- and pico-satellites has significantly increased over the past decade. Miniaturized subsystems, such as micropropulsion, for these classes of spacecraft are rapidly evolving and, in particular, micro-resistojets have shown great potential of applicability. One of the key points to address in the development of such devices is the propellants selection, since it directly influences the performance. This paper presents a methodology for the selection and characterization of fluids that are suitable for use as propellants in two micro-resistojet concepts: vaporizing liquid micro-resistojet (VLM) and the low-pressure micro-resistojet (LPM). In these concepts, the propellant is heated by a nonchemical energy source, in this case an electrical resistance. In total 95 fluids have been investigated including conventional and unconventional propellants. A feasibility assessment step is carried out following a trade-off using a combination of the analytical hierarchy process (AHP) and the Pugh matrix. A final list of nine best-scoring candidates has been analyzed in depth with respect to the thermal characteristics involved in the process, performance parameters, and safety issues. For both concepts, water has been recognized as a very promising candidate along with other substances such as ammonia and methanol.

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Selva, D. , and Krejci, D. , 2012, “ A Survey and Assessment of the Capabilities of Cubesats for Earth Observation,” Acta Astronaut., 74, pp. 50–68. [CrossRef]
Boshuizen, C. R. , Mason, J. , Klupar, P. , and Spanhake, S. , 2014, “ Results From the Planet Labs Flock Constellation,” AIAA Paper No. SSC14-I-1.
Guo, J. , Bouwmeester, J. , and Gill, E. , 2016, “ In-Orbit Results of Delfi-n3Xt: Lessons Learned and Move Forward,” Acta Astronaut., 121, pp. 39–50. [CrossRef]
Ciaralli, S. , Coletti, M. , and Gabriel, S. B. , 2016, “ Results of the Qualification Test Campaign of a Pulsed Plasma Thruster for Cubesat Propulsion (PPTCUP),” Acta Astronaut., 121, pp. 314–322. [CrossRef]
Coletti, M. , Guarducci, F. , and Gabriel, S. , 2011, “ A Micro PPT for Cubesat Application: Design and Preliminary Experimental Results,” Acta Astronaut., 69(3–4), pp. 200–208. [CrossRef]
Köhler, J. , Bejhed, J. , Kratz, H. , Bruhn, F. , Lindberg, U. , Hjort, K. , and Stenmark, L. , 2002, “ A Hybrid Cold Gas Microthruster System for Spacecraft,” Sens. Actuators A, 97–98, pp. 587–598. [CrossRef]
Cheah, K. H. , and Low, K.-S. , 2015, “ Fabrication and Performance Evaluation of a High Temperature Co-Fired Ceramic Vaporizing Liquid Microthruster,” J. Micromech. Microeng., 25(1), p. 015013. [CrossRef]
Kundu, P. , Bhattacharyya, T. K. , and Das, S. , 2012, “ Design, Fabrication and Performance Evaluation of a Vaporizing Liquid Microthruster,” J. Micromech. Microeng., 22(2), p. 025016. [CrossRef]
Cervone, A. , Zandbergen, B. , Guerrieri, D. C. , De Athayde Costa e Silva, M. , Krusharev, I. , and van Zeijl, H. , 2017, “ Green Micro-Resistojet Research at Delft University of Technology: New Options for Cubesat Propulsion,” CEAS Space J., 9(1), pp. 111–125. [CrossRef]
Ketsdever, A. D., and Micci, M. M., 2000, Micropropulsion for Small Spacecraft, Vol. 187, AIAA, Reston, VA.
Mike Meyer, L. J. , 2015, “ NASA Technology Roadmaps, TA 2: In-Space Propulsion Technologies,” NASA, Washington, DC.
ESA, 2015, “ European Space Technology Master Plan,” ESA, Noordwijk, The Netherlands.
Gohardani, A. S. , Stanojev, J. , Demairé, A. , Anflo, K. , Persson, M. , Wingborg, N. , and Nilsson, C. , 2014, “ Green Space Propulsion: Opportunities and Prospects,” Prog. Aerosp. Sci., 71, pp. 128–149. [CrossRef]
Anflo, K. , and Möllerberg, R. , 2009, “ Flight Demonstration of New Thruster and Green Propellant Technology on the PRISMA Satellite,” Acta Astronaut., 65(9–10), pp. 1238–1249. [CrossRef]
Amri, R. , and Gibbon, D. , 2012, “ In Orbit Performance of Butane Propulsion System,” Adv. Space Res., 49(4), pp. 648–654. [CrossRef]
Rankin, D. , Kekez, D. D. , Zee, R. E. , Pranajaya, F. M. , Foisy, D. G. , and Beattie, A. M. , 2005, “ The CanX-2 Nanosatellite: Expanding the Science Abilities of Nanosatellites,” Acta Astronaut., 57(2–8), pp. 167–174. [CrossRef]
Zakirov, V. , Sweeting, M. , Lawrence, T. , and Sellers, J. , 2001, “ Nitrous Oxide as a Rocket Propellant,” Acta Astronaut., 48(5), pp. 353–362. [CrossRef]
Sutton, G. P., and Biblarz, O., 2010, Rocket Propulsion Elements, 8th ed., Wiley, Hoboken, NJ.
Zahedi, F. , 1986, “ The Analytic Hierarchy Process: A Survey of the Method and Its Applications,” Interfaces, 16(4), pp. 96–108. [CrossRef]
Pugh, S. , 1991, Total Design: Integrated Methods for Successful Product Engineering, Addison-Wesley, Harlow, England.
Cervone, A. , Deeb, A. , van Wees, T. , Jansen, E. , Sundaramoorthy, P. , Chu, J. , and Zandbergen, B. , 2015, “ A Micro-Propulsion Subsystem to Enable Formation Flying on the DelFFi Mission,” Eighth International Workshop on Satellite Constellations and Formation Flying (IWSCFF), IAF, Delft, The Netherlands, June 8–10, pp. 1–15.
NFPA, 2010, “ Fire Protection Guide to Hazardous Materials,” National Fire Protection Association, Quincy, MA.
Ketsdever, A. D. , Lee, R. H. , and Lilly, T. C. , 2005, “ Performance Testing of a Microfabricated Propulsion System for Nanosatellite Applications,” J. Micromech. Microeng., 15(12), p. 2254. [CrossRef]
Guerrieri, D. C. , Cervone, A. , and Gill, E. , 2016, “ Analysis of Nonisothermal Rarefied Gas Flow in Diverging Microchannels for Low-Pressure Microresistojets,” ASME J. Heat Transfer, 138(11), p. 112403. [CrossRef]
Cen, J. , and Xu, J. , 2010, “ Performance Evaluation and Flow Visualization of a MEMS Based Vaporizing Liquid Micro-Thruster,” Acta Astronaut., 67(3–4), pp. 468–482. [CrossRef]
Chen, C.-C. , Liu, C.-W. , Kan, H.-C. , Hu, L.-H. , Chang, G.-S. , Cheng, M.-C. , and Dai, B.-T. , 2010, “ Simulation and Experiment Research on Vaporizing Liquid Micro-Thruster,” Sens. Actuators A, 157(1), pp. 140–149. [CrossRef]
Karthikeyan, K. , Chou, S. K. , Khoong, L. E. , Tan, Y. M. , Lu, C. W. , and Yang, W. M. , 2012, “ Low Temperature Co-Fired Ceramic Vaporizing Liquid Microthruster for Microspacecraft Applications,” Appl. Energy, 97, pp. 577–583. [CrossRef]
Guerrieri, D. C. , de Athayde Costa e Silva, M. , Zandbergen, B. T. C. , and Cervone, A. , 2015, “ Development of a Low Pressure Free Molecular Micro-Resistojet for CubeSat Applications,” 66th International Astronautical Congress (IAC), International Astronautical Federation, Jerusalem, Israel.
Lafferty, J. M. , 1998, Foundations of Vaccum Science and Technology, Wiley, Hoboken, NJ.
Ahmed, Z. , Gimelshein, S. F. , and Ketsdever, A. , 2005, “ Numerical Analysis of Free Molecule Micro-Resistojet Performance,” AIAA Paper No. 2005-4262.
Lee, R. , Bauer, A. , Killingsworth, M. , Lilly, T. , Duncan, J. , and Ketsdever, A. , 2007, “ Performance Characterization of the Free Molecule Micro-Resistojet Utilizing Water Propellant,” AIAA Paper No. 2007-5185.
Palmer, K. , Nguyen, H. , and Thornell, G. , 2013, “ Fabrication and Evaluation of a Free Molecule Micro-Resistojet With Thick Silicon Dioxide Insulation and Suspension,” J. Micromech. Microeng., 23(6), p. 065006. [CrossRef]
Linstrom, P. , and Mallard, W. , 2016, “ NIST Chemistry Webbook,” NIST Standard Reference Database No. 69, NIST, Gaithersburg, MD, accessed Apr. 15, 2016, http://webbook.nist.gov
Air Liquide, “ Gas Encyclopedia,” Air Liquide, Paris, France, accessed Apr. 15, 2016, http://encyclopedia.airliquide.com/
Perry, R. H. , and Green, D. W. , 2008, Perry's Chemical Engineers' Handbook, 8th ed., McGraw-Hill, New York.
Green Advanced Space Propulsion, 2011, “ Green Propellant Candidates of GRASP,” European Commission, Brussels, Belgium, accessed May 9, 2017, http://cordis.europa.eu/project/rcn/89683_en.html#top
Díaz, M. E. , Guetachew, T. , Landy, P. , Jose, J. , and Voilley, A. , 1999, “ Experimental and Estimated Saturated Vapour Pressures of Aroma Compounds,” Fluid Phase Equilib., 157(2), pp. 257–270. [CrossRef]
Ferreira, A. , and Lobo, L. , 2009, “ Nitrous Oxide: Saturation Properties and the Phase Diagram,” J. Chem. Thermodyn., 41(12), pp. 1394–1399. [CrossRef]


Grahic Jump Location
Fig. 1

The AHP resulting in the weight ratio for each criterion

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Fig. 2

Results of the Pugh matrix presented as a boxplot, where the middle line of the box represents the median, the upper and lower borders of the box represent the upper and lower quartiles, respectively, the top and bottom lines are the maximum and minimum value, and the crosses represent the outliers

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Fig. 3

Saturation curve. The circles means triple point and the crosses means critical point. The fluid is liquid on the left side of the curve, gaseous on its right side.

Grahic Jump Location
Fig. 4

Delta enthalpy for each propellant, at a chamber pressure of 200 kPa, as a function of the desired final chamber temperature

Grahic Jump Location
Fig. 5

Specific impulse versus heating power for various propellants (VLM case) according to the variations of temperature and pressure considered in Tables 3 and 4

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Fig. 6

Specific impulse versus heating power for various propellants (LPM case) according to the variations of temperature and pressure considered in Table 5

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Fig. 7

ΔV per volume of fluid versus heating power (VLM case)

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Fig. 8

ΔV per volume of fluid versus heating power (LPM case)




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