Low temperature co-fired ceramic vaporizing liquid microthruster for microspacecraft applications

Kandasamy, Karthikeyan; Chou, S.K.; Khoong, L.E.; Tan, Y.M.; Lu, Chuanhe; Yang, Wenbo

doi:10.1016/j.apenergy.2011.11.078

Cited by 33 publications

(13 citation statements)

References 16 publications

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“…Tests were performed using water as propellant and it was found that the ceramic thruster is slightly more efficient than some silicon thrusters with respect to power consumption and delivered thrust. Authors in [6] present the details of fabrication and test of a low temperature co-fired ceramic (LTCC) micro-thruster. They analyze the results for pressure, temperature, power and thrust and also present some comments about the relation between the temperature of the chamber and the vaporization of the propellant.…”

Section: Introductionmentioning

confidence: 99%

Vaporizing Liquid Microthrusters with integrated heaters and temperature measurement

Silva

Guerrieri

Zeijl

et al. 2017

Sensors and Actuators A: Physical

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This paper presents the results of design, manufacturing and characterization of Vaporizing Liquid Microthrusters (VLM) with integrated heaters and temperature sensing. The thrusters use water as the propellant and are designed for use in CubeSats and PocketQubes. The devices are manufactured using silicon based MEMS (Micro Electro Mechanical Systems) technology and include resistive heaters to vaporize the propellant. The measurements of the heaters' resistances are used to estimate the temperature in the vaporizing chamber. The manufacturing process is described as well as the characterization of the thrusters' structural and electrical elements. In total 12 devices with different combinations of heaters and nozzles have been assessed and four of them have been used to demonstrate the successful operation of the thrusters. Results show a performance close to the design parameters and are used to validate the thrusters.

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Section: Introductionmentioning

confidence: 99%

Vaporizing Liquid Microthrusters with integrated heaters and temperature measurement

Silva

Guerrieri

Zeijl

et al. 2017

Sensors and Actuators A: Physical

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“…Then, the thrust was calculated by a series of relations Besides silicon being used as the substrate material of VLM, ceramic has also been used in the fabrication of the VLM and microsystem [78]. LTCC technology has been successfully used for the first time in the designing of VLM in the study of Karthikeyan et al [79]. After the experimental testing, the VLM with a nozzle throat size of 220 μm × 200 μm produced a thrust ranged from 34 μN to 68 μN and an average specific impulse ranged from 3.4 s to 6.9 s at a flow rate of 1 mg/s with an input power ranged from 7.1 W to 9.2 W. In addition, Cheah et al [80] reported a study of a MEMSscaled VLM fabricated based on the high-temperature co-fired ceramic (HTCC) technology.…”

Section: Vlm With Internal Microheatermentioning

confidence: 99%

Recent Advances in MEMS-Based Microthrusters

Liu

Yang

et al. 2019

Micromachines

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With the development of micro/nano satellites and formation flying, more advanced spatial propulsion technology is required. In this paper, a review of microthrusters developments that based on micro electromechanical systems (MEMS) technology adopted in microthrusters is summarized. The microthrusters in previous research are classified and summarized according to the types of propellants and the working principles they utilized. The structure and the performance including the thrust, the impulse and the specific impulse of various microthrusters are compared. In addition, the advantages and the disadvantages of these microthrusters presented in the paper are discussed.

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“…Concerning the material used for fabrication and the process itself, silicon is the main choice but low temperature co-fired ceramic (LTCC) is an interesting choice for being simpler to manufacture and cheaper [41], [42].…”

Section: Vaporizing Liquid Micro-thruster -Vlmmentioning

confidence: 99%

A review of MEMS micropropulsion technologies for CubeSats and PocketQubes

et al. 2018

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CubeSats have been extensively used in the past decade as scientific tools, technology demonstrators and for education. Recently, PocketQubes have emerged as an interesting and even smaller alternative to CubeSats. However, both satellite types often lack some key capabilities, such as micropropulsion, in order to further extend the range of applications of these small satellites. This paper reviews the current development status of micropropulsion systems fabricated with MEMS (micro electro-mechanical systems) and silicon technology intended to be used in CubeSat or PocketQube missions and compares different technologies with respect to performance parameters such as thrust, specific impulse, and power as well as in terms of operational complexity. More than 30 different devices are analyzed and divided into 7 main categories according to the working principle. A specific outcome of the research is the identification of the current status of MEMS technologies for micropropulsion including key opportunities and challenges.

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Low temperature co-fired ceramic vaporizing liquid microthruster for microspacecraft applications

Cited by 33 publications

References 16 publications

Vaporizing Liquid Microthrusters with integrated heaters and temperature measurement

Vaporizing Liquid Microthrusters with integrated heaters and temperature measurement

Recent Advances in MEMS-Based Microthrusters

A review of MEMS micropropulsion technologies for CubeSats and PocketQubes

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