PPT Development for Nanosatellite Applications: Experimental Results
In this paper, the design and performances of a pulsed plasma thruster (PPT) for nanosatellite applications will be presented. The breadboard model PPT presented in this paper will be a part of six PPTs propulsion system designed to provide attitude and translational control for a 20-kg nanosatellite for a total delta-V of 40 m/s. The thruster performances have been characterized in terms of electrical parameters, mass bit, impulse bit, and specific impulse. The thruster was found to be compliant with the mission requirement. Moreover, preliminary electromagnetic noise interference measurements have been performed. The spark plug discharge was found to be the main source of noise as already found by previous authors. From the collected data, it can be inferred that the noise is mostly radiated.
The MOMENT Magnetic Mapping Mission Martian Science on a Nanosatellite Platform
MOMENT (Magnetic Observations of Mars Enabled by Nanosatellite Technology) will obtain high-resolution maps of remnant-magnetic fields over Mars’ southern highlands. A sub-nanotesla magnetometer employed in a highly-elliptical and low-nightside-periapsis (100 km) orbit will provide greater spatial resolution and anomaly delineation than is available from Mars Global Surveyor. During the aerobraking phase of that mission, low-altitude measurements were corrupted by solar wind because they were acquired in sunlight, where solar winds interacted with the crustal-magnetic field. During the mapping phase, spatial resolution was limited to about 400 km. Improving upon these limitations, MOMENT’s mapping strategy will allow detailed studies of regional tectonics and core-dynamo history. MOMENT’s design is based on the Space Flight Laboratory’s Generic Nanosatellite Bus. Developed for the BRITE and CanX-4&5 missions, MOMENT re-uses this technology to provide a rapid and cost-effective mission. Implementation of the mission requires payload space on a larger carrier spacecraft and use of Martian communication relays to transfer information to and from Earth; MOMENT is otherwise fully autonomous. This paper describes the conceptual MOMENT mission (funded by the Canadian Space Agency) and illustrates that nanosatellite technology is a relatively-simple and cost-effective means to enhance solar system exploration.
Pulsed plasma microthruster propulsion system for synchronous orbit satellite
A pulsed plasma microthruster system was designed, built, flight qualified, and delivered to the Massachusetts Institute of Technology (MIT) Lincoln Laboratory for installation in the LES-6 satellite. The system was designed to meet the requirements for east-west stationkeeping of the spin stabilized, synchronous orbit satellite. Four valveless pulsed plasma microthrusters using solid Teflon as the propellant are spaced on the satellite periphery. The flight qualification and acceptance program was successful in meeting environmental constraints and indicated that RFI was not a serious problem in the application of the thruster to the communication satellite. East-west stationkeeping was functionally performed in more than 16 months of space operation.