Small Satellite LEO Maneuvers with Low-Power Electric Propulsion

2008 ◽  
Author(s):  
Scott King ◽  
Mitchell Walker ◽  
Craig Kluever
Keyword(s):  
Low Power ◽  
Electric Propulsion ◽  
Small Satellite

Development of low power electric propulsion aiming for small satellite applications

2001 ◽  
Author(s):  
Shin Satori ◽  
Hiroyuki Okamoto ◽  
Ted Sugiki ◽  
Yoshinori Aoki ◽  
Atsushi Nagata ◽  
...  
Keyword(s):  
Low Power ◽  
Electric Propulsion ◽  
Small Satellite ◽  
Satellite Applications

scholarly journals A Review of Low-Power Electric Propulsion Research at the Space Propulsion Centre Singapore

Aerospace ◽  
2020 ◽  
Vol 7 (6) ◽  
pp. 67 ◽  
Author(s):  
George-Cristian Potrivitu ◽  
Yufei Sun ◽  
Muhammad Wisnuh Aggriawan bin Rohaizat ◽  
Oleksii Cherkun ◽  
Luxiang Xu ◽  
...  
Keyword(s):  
Low Power ◽  
Electric Propulsion ◽  
Form Factors ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Small Satellite ◽  
Space Propulsion ◽  
Propulsion Systems ◽  
Small Satellites ◽  
Plasma Thruster

The age of space electric propulsion arrived and found the space exploration endeavors at a paradigm shift in the context of new space. Mega-constellations of small satellites on low-Earth orbit (LEO) are proposed by many emerging commercial actors. Naturally, the boom in the small satellite market drives the necessity of propulsion systems that are both power and fuel efficient and accommodate small form-factors. Most of the existing electric propulsion technologies have reached the maturity level and can be the prime choices to enable mission versatility for small satellite platforms in Earth orbit and beyond. At the Plasma Sources and Applications Centre/Space Propulsion Centre (PSAC/SPC) Singapore, a continuous effort was dedicated to the development of low-power electric propulsion systems that can meet the small satellites market requirements. This review presents the recent progress in the field of electric propulsion at PSAC/SPC Singapore, from Hall thrusters and thermionic cathodes research to more ambitious devices such as the rotamak-like plasma thruster. On top of that, a review of the existing vacuum facilities and plasma diagnostics used for electric propulsion testing and characterization is included in the present research.

scholarly journals Design of a high-stability heterogeneous clock system for small satellites in LEO

GPS Solutions ◽  
2021 ◽  
Vol 25 (3) ◽  
Author(s):  
Damon Van Buren ◽  
Penina Axelrad ◽  
Scott Palo
Keyword(s):  
Low Power ◽  
High Stability ◽  
Time Frame ◽  
System Stability ◽  
Small Satellite ◽  
Crystal Oscillator ◽  
Small Satellites ◽  
Clock System ◽  
Wide Range

AbstractWe describe our investigation into the performance of low-power heterogeneous timing systems for small satellites, using real GPS observables from the GRACE Follow-On mission. Small satellites have become capable platforms for a wide range of commercial, scientific and defense missions, but they are still unable to meet the needs of missions that require precise timing, on the order of a few nanoseconds. Improved low-power onboard clocks would make small satellites a viable option for even more missions, enabling radio aperture interferometry, improved radio occultation measurements, high altitude GPS navigation, and GPS augmentation missions, among others. One approach for providing improved small satellite timekeeping is to combine a heterogeneous group of oscillators, each of which provides the best stability over a different time frame. A hardware architecture that uses a single-crystal oscillator, one or more Chip Scale Atomic Clocks (CSACs) and the reference time from a GPS receiver is presented. The clocks each contribute stability over a subset of timeframes, resulting in excellent overall system stability for timeframes ranging from less than a second to several days. A Kalman filter is used to estimate the long-term errors of the CSACs based on the CSAC-GPS time difference, and the improved CSAC time is used to discipline the crystal oscillator, which provides the high-stability reference clock for the small satellite. Simulations using GRACE-FO observations show time error standard deviations for the system range from 2.3 ns down to 1.3 ns for the clock system, depending on how many CSACs are used. The results provide insight into the timing performance which could be achieved on small LEO spacecraft by a low power timing system.

Small satellite electric propulsion options

1994 ◽  
Author(s):  
Roger Myers ◽  
Steven Oleson ◽  
Francis Curran
Keyword(s):  
Electric Propulsion ◽  
Small Satellite

scholarly journals A Thrust Stand for Low-Power Electric Propulsion

2003 ◽  
Vol 51 (593) ◽  
pp. 270-275
Author(s):  
Hiroyuki Koizumi ◽  
Akira Kakami ◽  
Kimiya Komurasaki ◽  
Yoshihiro Arakawa
Keyword(s):  
Low Power ◽  
Electric Propulsion ◽  
Thrust Stand

A3 Development of the Electric Propulsion for Small Satellite

2002 ◽  
Vol 2002.10 (0) ◽  
pp. 9-12
Author(s):  
Hirouyki OKAMOTO ◽  
Mitsuteru SUGIKI ◽  
Shin SATORI
Keyword(s):  
Electric Propulsion ◽  
Small Satellite
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