Design of a Hybrid CubeSat Orbit Insertion Motor

Jens, Elizabeth T.; Karp, Ashley C.; Nakazono, Barry; Eldred, Daniel B.; Devost, Matthew; Vaughan, David

doi:10.2514/6.2016-4961

Cited by 21 publications

(4 citation statements)

References 5 publications

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“…Furthermore, for a Mars aero-capture manoeuvrer, the hybrid propulsion option would be an alternative to the hydrazine mono-propellant [37]. For propulsive Mars orbit insertion, CubeSats (25-100 kg) with hybrid engine solutions can outperform the liquid mono-propellant reference by 6% payload mass [38]. Similar results have been found by Ingenito et al [39] for 24U CubeSats (less than 30 kg) that can be captured for Mars orbit using a 200 N class N 2 O/paraffin motor.…”

Section: In-space Propulsionmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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Hybrid rocket propulsion, first demonstrated by the Russian GIRD-09 rocket in 1933, combines liquid oxidizer and solid fuel for thrust generation. Despite numerous advantages, such as enhanced safety, controllability, and potential environmental benefits, hybrid propulsion has yet to achieve its full potential in space applications. In recent years, the research on hybrid propulsion has gained enormous momentum in both academia and industry. Recent accomplishments such as the altitude record for student rockets (64 km), the launch of the first electric pump-fed hybrid rocket, and a successful 25 s hovering test highlight the potential of hybrid rockets. However, although the hybrid community is growing constantly, industrial utilizations and in-space validations do not yet exist. In this work, we reassess the possibilities of hybrid rocket engines by presenting potential fields of applications from the literature. Most importantly, we identify the technical challenges that hinder the breakthrough of hybrid propulsion in the space sector and evaluate the technologies and approaches necessary to bridge the gaps in hybrid rocket development.

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Section: In-space Propulsionmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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“…A regulated pressure-fed system is utilized as the thrust must be precise and constant [33]. Gaseous nitrogen GN 2 is used as the pressurant.…”

Section: E System Sizing and Feedmentioning

confidence: 99%

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Mani

Cervone

Topputo

2019

Journal of Spacecraft and Rockets

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Stand-alone interplanetary CubeSats require primary propulsion systems for orbit maneuvering and precise trajectory control. The current work focuses on the design and performance characterization of the combined chemical-electric propulsion systems that shall enable a stand-alone 16U CubeSat mission on a hybrid high-thrust-low-thrust trajectory from a Supersynchronous Geostationary Transfer Orbit to a circular orbit about Mars. The high-thrust chemical propulsion is used to escape Earth and to initiate stabilization at Mars. The low-thrust electric propulsion is used in heliocentric transfer, ballistic capture, and circularization. For chemical propulsion, design and performance characteristics of a monopropellant thruster and feed system utilizing ADN-based FLP-106 propellant are presented. For electric propulsion, a performance model of an Iodine-propelled inductively coupled miniature radiofrequency ion thruster is implemented to calculate the variation of thrust, specific impulse and efficiency with input power. A power constrained low-thrust trajectory optimization utilizing the thruster performance model is pursued to calculate the transfer time, ∆V and the required propellant mass for fuel-optimal and time-optimal transfers. Overall, the combined chemical-electric systems yield a feasible propulsion solution for stand-alone CubeSat missions to Mars that balances propellant mass and transfer time.

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“…Though much of the work concerning hybrids is aimed at larger applications such as sounding rockets and small launch vehicles, recent research explores using HRE as a space thruster for different missions, including upper stages [5,6], geostationary satellite orbit insertion [7], deep space exploration [8,9], and Mars ascent vehicles [10,11]. This shift is driven by the market's need for greener and more cost-effective propulsion options.…”

Section: Introduction 1hybrid Rocket Engines For In-space Applicationsmentioning

confidence: 99%

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

Palacz,

Cieślik

2023

Aerospace

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The paper is part of the research aimed at determining if the vortex flow pancake (VFP) hybrid rocket engine is feasible as green in-space chemical propulsion. The objective of this study is to test an N2O/HDPE VFP hybrid ignited with N2O/C3H8 torch igniter. The N2O is used in self-pressurizing mode, which results in two-phase flow and varying inlet conditions, thus better simulating real in-space behavior. The study begins with characterizing the torch igniter, followed by hot-fire ignition tests of the VFP. The results allow for the improved design of the torch igniter and VFP hybrid. The axial regression rate ballistic coefficients are reported for the N2O/HDPE propellants in the VFP configuration.

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Design of a Hybrid CubeSat Orbit Insertion Motor

Cited by 21 publications

References 5 publications

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter

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