Parametric Analysis of High-Delta-V CubeSat Missions with a Miniature Ion Thruster

Samples, Stephen; Wirz, Richard E.

doi:10.2514/1.a34827

“…A 6U ABEP CubeSat shown in Figure 17 can be directly compared to a conventional EP 6U spacecraft using the same bus. This analysis is similar to the analysis of a high ∆V CubeSat [51].…”

Section: Comparison Between Conventional Ep and Abepmentioning

confidence: 59%

“…This leaves 2.9U for propellant and payload. The propellant tank is assumed to be at a temperature of 322 K and pressure of 161 bar [51]. As the propellant requirements grow, the propellant tank grows as a sphere until it is 9 cm in diameter, then it becomes stretched to become a cylinder [51].…”

Section: U Cubesat With Conventional Epmentioning

confidence: 99%

“…The propellant tank is assumed to be at a temperature of 322 K and pressure of 161 bar [51]. As the propellant requirements grow, the propellant tank grows as a sphere until it is 9 cm in diameter, then it becomes stretched to become a cylinder [51]. Figure 19 shows the effect on payload volume vs spacecraft altitude and mission lifetime.…”

Section: U Cubesat With Conventional Epmentioning

confidence: 99%

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Air-Breathing Electric Propulsion: Mission Characterization and Design Analysis

Crandall

¹

,

Wirz

²

2022

Preprint

0

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Air breathing electric propulsion (atmosphere-breathing electric propulsion) (ABEP) has attracted significant interest as an enabling technology for long duration space missions in very low Earth orbit (VLEO) altitudes below about 300 km. The ABEP spacecraft and mission analysis model developed allows parametric characterization of key spacecraft geometry and thruster performance parameters such as spacecraft length-to-diameter, the ratio of solar array span to spacecraft diameter, thrust-to-power, effective exhaust velocity, and inlet efficiency. For the missions analyzed ABEP generally outperforms conventional electric propulsion (EP) below 250 km altitude. Using a 6U spacecraft architecture the model shows that below 220 km ABEP is the only viable propulsion option for desirable mission lifetimes. Parametric evaluations of key spacecraft and ABEP characteristics show that the most significant technological improvements to ABEP spacecraft performance and range of applicability for VLEO missions will come from advancements in inlet efficiency, low drag materials, solar array efficiency, and thrust-to-power.

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“…17 can be directly compared to a conventional EP 6U spacecraft using the same bus. This analysis is similar to the analysis of a high ΔV CubeSat [51].…”

Section: Comparison Between Conventional Ep and Abepmentioning

confidence: 61%

“…The propulsion unit is assumed to occupy 1.6U of volume based on commercial CubeSat EP thrusters [52]. COMMS, ADCS, and EPS are estimated to occupy 1.5U of volume in the spacecraft [51]. EPS mass is estimated to be 0.14 kg [53].…”

Section: U Cubesat With Conventional Epmentioning

confidence: 99%

Air-breathing electric propulsion: mission characterization and design analysis

Crandall

¹

,

Wirz

²

2022

View full text Add to dashboard Cite

Air breathing electric propulsion (atmosphere-breathing electric propulsion) (ABEP) has attracted significant interest as an enabling technology for long duration space missions in very low Earth orbit (VLEO) altitudes below about 300 km. The ABEP spacecraft and mission analysis model developed allows parametric characterization of key spacecraft geometry and thruster performance parameters such as spacecraft length-to-diameter, the ratio of solar array span to spacecraft diameter, thrust-to-power, effective exhaust velocity, and inlet efficiency. For the missions analyzed ABEP generally outperforms conventional electric propulsion (EP) below 250 km altitude. Using a 6U spacecraft architecture the model shows that below 220 km ABEP is the only viable propulsion option for desirable mission lifetimes. Parametric evaluations of key spacecraft and ABEP characteristics show that the most significant technological improvements to ABEP spacecraft performance and range of applicability for VLEO missions will come from advancements in inlet efficiency, low drag materials, solar array efficiency, and thrust-to-power.

show abstract