End-to-End Analysis of Solar-Electric-Propulsion Earth Orbit Raising for Interplanetary Missions

Bonin, Grant; Kaya, Tarik

doi:10.2514/1.28670

Cited by 4 publications

(3 citation statements)

References 8 publications

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“…14 SEPDOC was recently used to obtain optimal orbit-raising maneuvers for an SEP tug for transferring a payload from LEO to a high-energy orbit. 15 Fortunately, the low-thrust maneuvers investigated in this paper are considerably easier to compute than the transfers computed by Kluever and Oleson as well as Bonin and Kaya. 14,15 All maneuvers presented in this paper involve continuous thrust, where we assume that power can be maintained at a constant level throughout the transfer, even during Earth-shadow arcs.…”

Section: Low-thrust Orbital Mechanics Computationsmentioning

confidence: 88%

“…15 Fortunately, the low-thrust maneuvers investigated in this paper are considerably easier to compute than the transfers computed by Kluever and Oleson as well as Bonin and Kaya. 14,15 All maneuvers presented in this paper involve continuous thrust, where we assume that power can be maintained at a constant level throughout the transfer, even during Earth-shadow arcs. Secondly, the maneuvers considered in this paper either involve dedicated thrusting in the orbital plane (for an increase or decrease in altitude), or dedicated thrusting normal to the orbital plane (for plane changes).…”

Section: Low-thrust Orbital Mechanics Computationsmentioning

confidence: 88%

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Small Satellite LEO Maneuvers with Low-Power Electric Propulsion

King¹,

Walker²,

Kluever³

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Chemical propulsion currently provides the means for near-Earth satellite orbit maneuvers. As electric propulsion (EP) devices become more accepted and flight qualified, EP may enable increases in satellite payload mass while decreasing satellite propellant mass. The Air Force Operationally-Responsive Space (ORS) program proposes the use of commercially available and readily configurable satellite buses with masses of approximately 500 kg for near-Earth missions. This paper discusses three orbital maneuvers considered important in the characterization of EP use for satellites in near-Earth orbits. The first maneuver changes an orbit from low-Earth orbit (LEO) at 800 km to medium-Earth orbit (MEO) at 20,000 km. The second maneuver changes the inclination of an orbit at LEO by 90°, while the third maneuver rephases a satellite in LEO orbit by 180°. Each maneuver considers thruster specific impulse, I sp , from 1,000 to 3,000 s and thruster power from 100 W to 1.5 kW for a 500 kg satellite to obtain propellant mass and transfer time. In general, as I sp increases the transfer time increases and the propellant mass decreases. These transfer times range from hours to years, but mission constraints will define appropriate levels of I sp and power. Analysis of these maneuvers finds that EP is beneficial to near-Earth satellites for altitude and phase changes. EP is not currently beneficial to missions requiring large inclination changes, but identifies a key interest in future low-power EP devices.

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Section: Low-thrust Orbital Mechanics Computationsmentioning

confidence: 88%

Section: Low-thrust Orbital Mechanics Computationsmentioning

confidence: 88%

Small Satellite LEO Maneuvers with Low-Power Electric Propulsion

King¹,

Walker²,

Kluever³

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

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“…A number of solar storms have lead to malfunctions or damage of infrastructure in space and even on earth via charging and uncontrolled voltage buildup (Lu et al, 2019;Bonin et al, 2010). Satellite 1 This provisional PDF is the accepted version.…”

Section: Introductionmentioning

confidence: 99%

Ionic liquid coating for charge mitigation of solar modules in space: Electron microscopy on insulating nanosphere lithography patterned surfaces

Wendt,

Dorn,

Lange

et al. 2024

J. Space Weather Space Clim.

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Surfaces of satellites and spacecrafts are exposed to high energy charged particles from the solar wind, especially during space weather events. This can lead to differential charging, which is a common reason for hardware degradation and sensor errors. Solutions like coatings are required to avoid excessive cost and weight. Mimicking the electron part of space-like environments in ultra-high vacuum (UHV) chambers can be achieved by using electrons emitted by a scanning electron microscope (SEM). As a performance test for the discharge capabilities we use the quality of electron microscopy images on otherwise insulating substrates such as glass, structured by nanosphere lithography and coated with an ionic liquid (IL). Additionally, the surface potential was measured by Kelvin Probe Force Spectroscopy. The IL film (BMP DCA) was applied ex situ and a thickness of 12.8 ($\pm$0.8)\,nm was determined by reflectometry and confirmed by dynamic atomic force microscopy. Such a film of ionic liquid would lead to additional mass of below 20\,mg and negligible additional material costs. The light absorption and influence of ionic liquid coatings on the current output of an actual solar cell were investigated. The results indicate, that these coatings are promising candidates for surface charge mitigation with a high potential for application

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Getting There and Back

Rapp

2023

Human Missions to Mars

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End-to-End Analysis of Solar-Electric-Propulsion Earth Orbit Raising for Interplanetary Missions

Cited by 4 publications

References 8 publications

Small Satellite LEO Maneuvers with Low-Power Electric Propulsion

Small Satellite LEO Maneuvers with Low-Power Electric Propulsion

Ionic liquid coating for charge mitigation of solar modules in space: Electron microscopy on insulating nanosphere lithography patterned surfaces

Getting There and Back

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