Small Satellite Community Research Articles

Micro-propulsion based on vacuum arcs

Micropropulsion systems are rapidly gaining attention from the small satellite community as they can increase the mission lifetime and allow the satellite to perform complex maneuvers and precise attitude control. These systems need to be fully operational with the low power available on satellites. Various thruster concepts based on vacuum arcs are currently under development, predominantly in the pulsed regime due to the power constraints on small spacecraft. Pulsed vacuum arc thrusters are capable of efficiently producing highly-ionized supersonic plasma at very low average power. This Perspective article provides a critical analysis and a review of various aspects of electric propulsion technology based on vacuum arcs. Furthermore, we give a personal assessment of the present status and provide an outlook on the field, including the growing role in small satellites such as CubeSats. Vacuum arc micropropulsion systems could play an important role in mitigating the problem of space debris. Such a system could be integrated with a satellite so that, at the end of its mission and using metal components as solid fuel, it will lower the satellite’s orbit and accelerate reentrance into the atmosphere faster than by its natural decay rate.

Miniature X-Ray Solar Spectrometer: A Science-Oriented, University 3U CubeSat

The miniature x-ray solar spectrometer is a three-unit CubeSat developed at the Laboratory for Atmospheric and Space Physics at the University of Colorado, Boulder. Over 40 students contributed to the project with professional mentorship and technical contributions from professors in the Aerospace Engineering Sciences Department at University of Colorado, Boulder and from Laboratory for Atmospheric and Space Physics scientists and engineers. The scientific objective of the miniature x-ray solar spectrometer is to study processes in the dynamic sun, from quiet sun to solar flares, and to further understand how these changes in the sun influence the Earth’s atmosphere by providing unique spectral measurements of solar soft x rays. The enabling technology providing the advanced solar soft x-ray spectral measurements is the Amptek X123, a commercial off-the-shelf silicon drift detector. The Amptek X123 has a low mass ( after modification), modest power consumption (), and small volume (), making it ideal for a CubeSat. This paper provides an overview of the miniature x-ray solar spectrometer mission: the science objectives, project history, subsystems, and lessons learned, which can be useful for the small-satellite community.

Survey of Inter-Satellite Communication for Small Satellite Systems: Physical Layer to Network Layer View

Small satellite systems enable a whole new class of missions for navigation, communications, remote sensing, and scientific research for both civilian and military purposes. As individual spacecraft are limited by the size, mass, and power constraints, mass-produced small satellites in large constellations or clusters could be useful in many science missions such as gravity mapping, tracking of forest fires, finding water resources, etc. The proliferation of small satellites will enable a better understanding of the near-Earth environment and provide an efficient and economical means to access the space through the use of multi-satellite solution. Constellation of satellites provide improved spatial and temporal resolution of the target. Small satellite constellations contribute innovative applications by replacing a single asset with several very capable spacecraft, which opens the door to new applications. Future space missions are envisioned to become more complex and operate farther from Earth, and will need to support autonomous operations with minimal human intervention. With increasing levels of autonomy, there will be a need for remote communication networks to enable communication between spacecraft. These space-based networks will need to configure and maintain dynamic routes, manage intermediate nodes, and reconfigure themselves to achieve mission objectives. Hence, inter-satellite communication is a key aspect when satellites fly in formation. In this survey, we present the various research being conducted in the small satellite community for implementing inter-satellite communications based on the open system interconnection (OSI) model. This survey also reviews the various design parameters applicable to the first three layers of the OSI model, i.e., physical, data link, and network layer. Based on the survey, we also present a comprehensive list of design parameters useful for achieving inter-satellite communications for multiple small satellite missions. Specific topics include proposed solutions for some of the challenges faced by small satellite systems, enabling operations using a network of small satellites, and some examples of small satellite missions involving formation flying aspects.

Design, Development and Operation of a Laboratory Pulsed Plasma Thruster for the First Time in West Asia

Although the pulsed plasma thruster (PPT) was first utilized on a space mission in 1964, after more than four decades, it is still a space-rated technology which has performed various propulsion tasks, from station-keeping to three-axis attitude control for a variety of former missions. With respect to the rapid growth in the small satellite community and the growing interest for smaller satellites in recent years, the PPT is one of the promising electric propulsion devices for small satellites (e.g., CubeSats) due to the following advantages: simplicity, lightweight, robustness, low power consumption, low production cost and small dimensions. Therefore, a laboratory benchmark rectangular breech-fed pulsed plasma thruster using a self-inductor as a coupling element was designed, developed and successfully tested in a bell-type vacuum chamber at 10-4 Pa for the first time in west Asia (Iran). The PPT has been tested using a 35 μF, 2.5 kV oil-filled capacitor, producing an impulse bit varying from 300 μN-s to 1.3 mN-s at a maximum specific impulse of 1100 s. As a result a research program in Iran was initiated for working on PPTs and the miniaturization of PPTs while increasing the performance parameters. The present paper briefly reviews the PPT design and development.

ASAP 5—Low-cost access to space for auxiliary payloads

Arianespace, the leading space transportation company, has always played a major role in the small satellite community. The development and success of the ASAP 4 system has allowed it to become a reference, and the arrival of ASAP 5 with its increased payload capabilities will ensure that Arianespace will continue to provide high-quality, low-cost access to space.

Orbital launch systems

This paper provides an update on Orbital's space launch systems and the innovative approaches taken to provide reliable and cost effective launch services to meet the operational requirements of today's small spacecraft. Current operational systems addressed include the Pegasus® XL and Taurus® launch vehicles along with recent new developments for access to space. Specific topics to be presented include the following: • /bb General description and unique capability of each launch vehicle • /bb Payload accommodations and launch site capabilities • /bb Multiple spacecraft launch accommodations for greater utility and cost efficiency • /bb Flight experience and results to date • /bb Launch System Group organization and expertise As an experienced provider of commercial launch services Orbitals launch systems have lead the way in serving the small satellite community. Our experience and proven performance record enables us to continue serving our customers into the next millennium with reliable and cost effective launch opportunities.