Green micro-resistojet research at Delft University of Technology: new options for Cubesat propulsion

Cervone, Angelo; Zandbergen, B.T.C.; Guerrieri, Daduí Cordeiro; Silva, M. De Athayde Costa e; Krusharev, I.; Zeijl, Henk van

doi:10.1007/s12567-016-0135-3

Cited by 28 publications

(16 citation statements)

References 13 publications

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“…The microresistojets are composed of three main parts: a nozzle, a vaporizing chamber, and a heater. Each of these parts have different designs [17]. 38 Ω respectively according to the following equation:…”

Section: Design Descriptionmentioning

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: Design Descriptionmentioning

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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“…Furthermore, this altitude is required for a spatial resolution of less than 4 m. To have a sustained momentum wheel rotation, the wheel is spun upon magnetic bearings to minimize friction and S/C instabilities throughout its lifetime (S.3). The momentum wheel, as a totally decoupled subsystem, will be spun-up once (blowdown system) with a set of TU Delft resisto-jets for technology demonstration (S.4) [5]. The magnetic bearings require a minimum of 5000 rpm of the momentum wheel to function.…”

Section: System Design and Payload Pointing Accuracymentioning

confidence: 99%

A cutting edge 6U CubeSat ADCS design for Earth observation with sub-meter spatial resolution at 230–380 km altitude

Kuiper

Dolkens

2020

CEAS Space J

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A 6U CubeSat for Earth observation in 230–350 km orbits with sub-meter resolution is presented. The proposed Stable and Highly Accurate Pointing Earth-Imager (SHAPE) system’s attitude determination and control system (ADCS) is composed of a single momentum bias wheel with magnetic bearings at rotational speeds of 6000–7000 rpm and refined magnetorquers. Reaction wheels as instability source are absent. The ADCS stabilizes the spacecraft attitude by counteracting the torques from external disturbances in the thermosphere down to < 1° pointing accuracy and < 0.1° instability. The momentum wheel was sized to an angular momentum of 1 Nms based on the worst-case atmospheric density of the next solar cycle. The 0.5 Am2 magnetorquer dipole moment provides with low power consumption, mass and cost, high reliability and sufficient torque. The ADCS initialisation study revealed three stable start-up modes, while the all-spun state is achieved using a set of thrusters. De-tumbling analysis show that the magnetorquers reduce the tumbling rates with magnitudes of up to 35°/s to mean motion values in less than an orbit using a static gain B-dot controller. A 3U camera design capable of sub-meter spatial resolution at 230 km altitude is presented which complies with the SHAPE spacecraft system design. The instrument has a single deployable primary mirror enabled by a deployment hinge design with hysteresis < 0.5 μ. This payload combined with air-breathing electric propulsion technology at 230 km nominal altitude boosts the SHAPE system Earth observation potential down to sub-meter spatial resolution and enables tuning of the mission lifetime by orbit keeping.

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“…The FMMR can also provide a thrust level ranged from several μN to a few mN. The FMMR thruster based on MEMS has the advantages of simple structure, lightweight, fast response, low cost, high reliability, high integration capability [118], and so on. Moreover, in the study of Berg et al [112], experimental measurements of the electrospray emission and beam properties of the double salt ionic liquid propellant [Emim][EtSO 4 ]-HAN were described.…”

Section: Free Molecular Micro-resistojet (Fmmr)mentioning

confidence: 99%

“…The FMMR can also provide a thrust level ranged from several µN to a few mN. The FMMR thruster based on MEMS has the advantages of simple structure, lightweight, fast response, low cost, high reliability, high integration capability [118], and so on.…”

Section: Free Molecular Micro-resistojet (Fmmr)mentioning

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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Green micro-resistojet research at Delft University of Technology: new options for Cubesat propulsion

Cited by 28 publications

References 13 publications

Vaporizing Liquid Microthrusters with integrated heaters and temperature measurement

Vaporizing Liquid Microthrusters with integrated heaters and temperature measurement

A cutting edge 6U CubeSat ADCS design for Earth observation with sub-meter spatial resolution at 230–380 km altitude

Recent Advances in MEMS-Based Microthrusters

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