Solid Propellant Microthruster Design for Nanosatellite Applications

Sathiyanathan, Kartheephan; Lee, Regina; Chesser, Hugh; Dubois, Charles; Stowe, Robert; Farinaccio, Rocco; Ringuette, Sophie

doi:10.2514/1.b34109

Cited by 36 publications

(9 citation statements)

References 14 publications

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“…Besides the above studies, Lewis et al [26] in 2000, You et al [52] in 2005, Rossi et al [53] in 2005, Sathiyanathan et al [54] in 2011, and Shen et al [55] in 2014 also developed different SPM arrays. The vertical design has advantages of high integration level and convenient expansion.…”

Section: Summary Of Spm and Spm Arraysmentioning

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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Section: Summary Of Spm and Spm Arraysmentioning

confidence: 99%

Recent Advances in MEMS-Based Microthrusters

Liu

Yang

et al. 2019

Micromachines

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“…Due to the complex structure and operation of microthrusters with liquid propellants [43,44], the solid propellants are preferred, which have advantages such as simplicity, adequate functionality, safety, etc. The impulse control should be in mNs resolution [45]. The burning time of propellant in micro chamber is a few milliseconds, as the charge mass is in order of micrograms to milligrams.…”

Section: Nano-energetic Micropropulsion Systemsmentioning

confidence: 99%

Tuning the Reactivity of Nano-energetic Gas Generators Based on Bismuth and Iodine Oxidizers

Hobosyan

Martirosyan

2018

Energy, Environment, and Sustainability

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There is a growing interest on novel energetic materials called Nanoenergetic Gas-Generators (NGGs) which are potential alternatives to traditional energetic materials including pyrotechnics, propellants, primers and solid rocket fuels. NGGs are formulations that utilize metal powders as a fuel and oxides or hydroxides as oxidizers that can rapidly release large amount of heat and gaseous products to generate shock waves. The heat and pressure discharge, impact sensitivity, long term stability and other critical properties depend on the particle size and shape, as well as assembling procedure and intermixing degree between the components. The extremely high energy density and the ability to tune the dynamic properties of the energetic system makes NGGs ideal candidates to dilute or replace traditional energetic materials for emerging applications. In terms of energy density, performance and controllability of dynamic properties, the energetic materials based on bismuth and iodine compounds are exceptional among the NGGs. The thermodynamic calculations and experimental study confirm that NGGs based on iodine and bismuth compounds mixed with aluminum nanoparticles are the most powerful formulations to date and can be used potentially in microthrusters technology with high thrust-to-weight ratio with controlled combustion and exhaust velocity for space applications.The resulting nano thermites generated significant value of pressure discharge up to 14.8 kPa m 3 /g. They can also be integrated with carbon nanotubes to form laminar composite yarns with high power actuation of up to 4700 W/kg, or be used in other emerging applications such as biocidal agents to effectively destroy harmful bacteria in seconds, with 22 mg/m 2 minimal content over infected area.

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“…Microsolid propellant thrusters (MSPT) consisting of micronozzles and microigniters have great potential applications in the small space vehicles due to their advantages, such as having no movable components and no liquid leakage [1–6]. Especially, the MSPT array including multiple thruster units has become more favourable since it can satisfy the flexible thrust configuration requirements [7–11].…”

Section: Introductionmentioning

confidence: 99%

Silicon‐on‐insulator‐based microsolid propellant thruster array

Shen

Yuan

et al. 2015

Micro & Nano Letters

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A silicon-on-insulator (SOI)-based microelectromechanical system solid propellant thruster array is presented. The micronozzle layer and microigniter layer of the array are formed on both surfaces of the SOI wafer, respectively. The layout design rules can properly distribute the heat produced by the microigniter below the solid propellant inside the chamber. Test results show that the highest temperature of the microigniter is located under the propellant. When one unit in the array is ignited by a DC voltage of 7.9 V, other units around it are not ignited. Moreover, the ignition resistors can work again, which means that the array can be used repeatedly when the solid propellant is refilled.

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Solid Propellant Microthruster Design for Nanosatellite Applications

Cited by 36 publications

References 14 publications

Recent Advances in MEMS-Based Microthrusters

Recent Advances in MEMS-Based Microthrusters

Tuning the Reactivity of Nano-energetic Gas Generators Based on Bismuth and Iodine Oxidizers

Silicon‐on‐insulator‐based microsolid propellant thruster array

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