IEEE Organizations related to Small Satellites

Back to Top

No organizations are currently tagged "Small Satellites"



Conferences related to Small Satellites

Back to Top

No conferences are currently tagged "Small Satellites"


Periodicals related to Small Satellites

Back to Top

No periodicals are currently tagged "Small Satellites"


Most published Xplore authors for Small Satellites

Back to Top

Xplore Articles related to Small Satellites

Back to Top

Micro/Nano-satellite-based Planetary Exploration: Study of noble gases in the lunar exosphere using CHACE mass spectrometer in the Moon Impact Probe (MIP) in Chandrayaan-1

2019 URSI Asia-Pacific Radio Science Conference (AP-RASC), 2019

In 2008, a microsatellite called Moon Impact Probe (MIP) was launched as a piggyback to the Chandrayaan-1 orbiter during India's first lunar mission. MIP was an impactor, which weighed ~35 kg, and was a half-meter sized cuboid, with its own propulsion system. It studied the Moon from a close range, during its travel from 100 km lunar altitude, till the ...


Spectrum Considerations for Satellites and Ramifications for RF Interference

2019 IEEE International Symposium on Electromagnetic Compatibility, Signal & Power Integrity (EMC+SIPI), 2019

Choosing the right frequencies is critical to proper operation of small satellites and essential to reducing RF interference.


IMPLEMENTATION OF A HDL-CODER BASED TELECOMMAND RECEIVER APPLICATION FOR MICROSATELLITE COMMUNICATION

2018 IEEE Global Conference on Signal and Information Processing (GlobalSIP), 2018

In this paper the development and implementation of a Telecommand (TC) receiver application for microsatellite communication is presented. The TC receiver application is executed and operated by a highly integrated Generic Software-Defined Radio (GSDR) platform. This platform architecture is designed for the reliable operation of multiple radio frequency applications on spacecraft. For the development and implementation process of the TC ...


Initial Radiance Validation of On-orbit MicroMAS-2A Data

2019 United States National Committee of URSI National Radio Science Meeting (USNC-URSI NRSM), 2019

Constellations of nanosatellites allow increased observations, improved revisit time, and expanded spatial coverage. Miniaturized microwave radiometers are particularly well-suited to nanosatellite constellations given the relatively wide receive beamwidth and high impact of their contribution to weather forecasting [1]. The Micro-sized Microwave Atmospheric Satellite (MicroMAS)-2A is a 3U CubeSat that launched on January 11, 2018, and provided the first CubeSat microwave ...


Sensor Webs of Earth Science Instruments to Improve our Understanding of Natural Phenomena and Physical Processes

IGARSS 2018 - 2018 IEEE International Geoscience and Remote Sensing Symposium, 2018

The demonstration of high quality scientific observations from small satellites has signaled the opportunity to employ new Earth science observing strategies using constellations or swarms of these relatively inexpensive platforms. While replacement of the existing observing strategies with those based on smallsats is not indicated, they do offer the promise of completely new observing strategies that can measure characteristics of ...


More Xplore Articles

Educational Resources on Small Satellites

Back to Top

IEEE-USA E-Books

  • Micro/Nano-satellite-based Planetary Exploration: Study of noble gases in the lunar exosphere using CHACE mass spectrometer in the Moon Impact Probe (MIP) in Chandrayaan-1

    In 2008, a microsatellite called Moon Impact Probe (MIP) was launched as a piggyback to the Chandrayaan-1 orbiter during India's first lunar mission. MIP was an impactor, which weighed ~35 kg, and was a half-meter sized cuboid, with its own propulsion system. It studied the Moon from a close range, during its travel from 100 km lunar altitude, till the surface, covering a latitude range of 40 deg N to 89 deg S, along the 14 deg E meridian. In the history of India's planetary exploration, so far, that was the only microsatellite launched.

  • Spectrum Considerations for Satellites and Ramifications for RF Interference

    Choosing the right frequencies is critical to proper operation of small satellites and essential to reducing RF interference.

  • IMPLEMENTATION OF A HDL-CODER BASED TELECOMMAND RECEIVER APPLICATION FOR MICROSATELLITE COMMUNICATION

    In this paper the development and implementation of a Telecommand (TC) receiver application for microsatellite communication is presented. The TC receiver application is executed and operated by a highly integrated Generic Software-Defined Radio (GSDR) platform. This platform architecture is designed for the reliable operation of multiple radio frequency applications on spacecraft. For the development and implementation process of the TC receiver application, a new model-based development workflow by Matlab/Simulink is used and evaluated.

  • Initial Radiance Validation of On-orbit MicroMAS-2A Data

    Constellations of nanosatellites allow increased observations, improved revisit time, and expanded spatial coverage. Miniaturized microwave radiometers are particularly well-suited to nanosatellite constellations given the relatively wide receive beamwidth and high impact of their contribution to weather forecasting [1]. The Micro-sized Microwave Atmospheric Satellite (MicroMAS)-2A is a 3U CubeSat that launched on January 11, 2018, and provided the first CubeSat microwave atmospheric sounder data from orbit. MicroMAS-2A has a 1U 10-channel passive microwave radiometer with channels near 90, 118, 183, and 206 GHz for moisture and temperature profiling and precipitation imaging [2]. MicroMAS-2A is a pathfinder for the future mission Time-Resolved Observations of Precipitation structure and storm Intensity with a Constellation of Smallsats (TROPICS), which is projected to launch in 2020. In this work, we provide an initial radiance validation assessment of MicroMAS-2A data.

  • Sensor Webs of Earth Science Instruments to Improve our Understanding of Natural Phenomena and Physical Processes

    The demonstration of high quality scientific observations from small satellites has signaled the opportunity to employ new Earth science observing strategies using constellations or swarms of these relatively inexpensive platforms. While replacement of the existing observing strategies with those based on smallsats is not indicated, they do offer the promise of completely new observing strategies that can measure characteristics of natural phenomena and physical processes that were not possible with the monolithic Battlestar Galactica type systems. Distributed Spacecraft Missions (DSM) are starting to take shape, as described in this Session. Variations in configurations are possible including geometry and composition and the degree of autonomy in operations. A number of sensor web information technologies have been matured, but mostly focused on ground based systems. Some useful technologies have also matured in other domains, such as machine learning and the Internet of Things. New technology development is needed, guided by a framework to prioritize new investments. Such a framework would also encourage division of labor and collaboration among Governments, companies and educational institutions.

  • Simulation Approach to Determine Position of the Fixed Installed Deployable Solar Panel

    The popularity, development and promising performance in orbit for small satellite make it's trends of mission to be run by the satellite become more complex. Since the small satellites may brought payload with higher power requirement to run its mission. This payload may not be able supported by the power system, in which is a combination of solar panel with batteries. Small satellite also has size and mass constraints which made it won't be able to bring active motion mechanism for the solar panel. A natural question to be answered is where the best installation position (placement) of the deployable solar panel with respect to the body satellite such that the power system can acquire maximal solar energy. This paper proposes simulation based method to determine placement (position) of the fixed installed deployable solar panel system such that maximal power can be provided. To validate this method, simulations data summary is presented in this paper where concerns in two different orbits of satellites and eleven cases that accommodates. Based in the simulation results, options for the position of the fixed installed deployable solar panel is provided.

  • Microplasma Jet Device For Plasma Thruster

    Summary form only given. Recently, nanosatellites (nanosats) electric propulsion systems have attracted attention to researchers due to very simple structure and low delivery cost1. However, present electric propulsion system, such as hall effect thruster, arcjets, and plasma thrusters, have low thrust, short lifetime, no flexibility2. Among various thruster systems, the plasma thruster has versatile advantages such as high specific impulse and small size for future nanosats. However, it is difficult to generate high thrust because the plasma, which is produced by conventional devices, has low energy. In addition, these conventional plasma thrusters also are difficult to change direction because these thrusters have limited flexibility. New solutions must be offered to space mission designers to overcome these limitations. Here, we have proposed the highly energetic intense coupled microplasma with a single bundle of three hollow-core optical fibers to obtain both the high thrust and flexibility. The proposed flexible microplasma thruster, which has a protruded optical-fiber, can generate the highly energetic intense coupled microplasma with a strong plasma emission and a high thrust. The detailed novel microplasma device, microplasma physics, discharge and thrust characteristics, currents, fluid simulation, high-speed intensified charge-coupled device (ICCD) images, and more detailed mechanism are studied and will be discussed in detail. This research contributes to better understanding on the novel structure and design of future microplasma thruster system by analyzing microplasma phenomena.

  • Measurement and Validation of SVOM Satellite VHF Board to ground interface

    VHF subsystem is an important information link for the science location message of SVOM satellite. The test plan and measurement methods of SVOM satellite VHF band board to ground interface validation are elaborated. Through the validation between the engineering model of on board equipment and the prototype of ground station, the effectiveness of the RF link and dataflow compatibility are validated.

  • Design of Gimbal Control System for Miniature Control Moment Gyroscope

    The agility of small satellites is the critical parameter, to the viewpoint of application field expansion and mission return maximization. The control moment gyroscope (CMG) shows better performances in terms of torque-power and mass-torque characteristics, which make it a key actuator for agile, precise attitude control. In this paper, a gimbal control system for miniature CMGs is developed for better control performance, with constrains on volume and mass. The system with both encoder and resolver as the position determination devices are designed and tested on Miniature CMG test platform developed by BICE.

  • Design of Transparent Patch Antenna for Smallsats

    Recent years, small satellites have become popular. We studied the design of a transparent circularly polarized patch antenna mounted on those solar panels. Firstly, we summarized the requirements for antennas for small satellites and studied the antenna structure and performance to satisfy them. We compared antenna characteristics of transparent conductor and mesh pattern, and finally designed circular polarized patch antenna of the latter structure in simulation.



Standards related to Small Satellites

Back to Top

No standards are currently tagged "Small Satellites"


Jobs related to Small Satellites

Back to Top