scholarly journals Telecommunication Systems for Small Satellites Operating at High Frequencies: A Review

Information ◽  
2020 ◽  
Vol 11 (5) ◽  
pp. 258
Author(s):  
Alessandra Babuscia
Keyword(s):  
New Technologies ◽  
Cost Savings ◽  
Low Earth Orbit ◽  
Lessons Learned ◽  
Small Satellite ◽  
High Frequencies ◽  
Small Satellites ◽  
Telecommunication Systems ◽  
X Band ◽  
Final System

Small Satellites and in particular CubeSats are becoming extremely popular platforms with which to perform space research. They allow for rapid prototyping with considerable cost savings with respect to traditional missions. However, as small satellite missions become more ambitious in terms of destinations to reach (from Low Earth Orbit to interplanetary) and in terms of the amount of data to transmit, new technologies need to be developed to provide adequate telecommunication support. This paper aims to review the telecommunication systems that have been developed at the Jet Propulsion Laboratory for some of the most recent CubeSat missions operating at different frequency bands: ASTERIA (S-Band), MarCO (X-Band and UHF) and ISARA (Ka-Band and UHF). For each of these missions: the telecommunication challenges and requirements are listed; the final system design is presented; the characteristics of the different hardware components are shown; and the lessons learned through operations are discussed.

scholarly journals Introduction to Plasma Based Propulsion System: Hall Thrusters

2021 ◽  
Author(s):  
Sukhmander Singh ◽  
Sanjeev Kumar ◽  
Shravan Kumar Meena ◽  
Sujit Kumar Saini
Keyword(s):  
Electric Propulsion ◽  
Low Earth Orbit ◽  
Current Status ◽  
Earth Orbit ◽  
Hall Thrusters ◽  
Small Satellite ◽  
Propulsion Systems ◽  
Small Satellites ◽  
Long Time ◽  
The Cost

Technically, there are two types of propulsion systems namely chemical and electric depending on the sources of the fuel. Electrostatic thrusters are used for launching small satellites in low earth orbit which are capable to provide thrust for long time intervals. These thrusters consume less fuel compared to chemical propulsion systems. Therefore for the cost reduction interests, space scientists are interested to develop thrusters based on electric propulsion technology. This chapter is intended to serve as a general overview of the technology of electric propulsion (EP) and its applications. Plasma based electric propulsion technology used for space missions with regard to the spacecraft station keeping, rephrasing and orbit topping applications. Typical thrusters have a lifespan of 10,000 h and produce thrust of 0.1–1 N. These devices have E→×B→ configurations which is used to confine electrons, increasing the electron residence time and allowing more ionization in the channel. Almost 2500 satellites have been launched into orbit till 2020. For example, the ESA SMART-1 mission (Small Mission for Advanced Research in Technology) used a Hall thruster to escape Earth orbit and reach the moon with a small satellite that weighed 367 kg. These satellites carrying small Hall thrusters for orbital corrections in space as thrust is needed to compensate for various ambient forces including atmospheric drag and radiation pressure. The chapter outlines the electric propulsion thruster systems and technologies and their shortcomings. Moreover, the current status of potential research to improve the electric propulsion systems for small satellite has been discussed.

scholarly journals Spectral Correlation for Signal Presence Detection and Frequency Acquisition of Small Satellites

Aerospace ◽  
2021 ◽  
Vol 8 (2) ◽  
pp. 57
Author(s):  
Jonas Hofmann ◽  
Andreas Knopp ◽  
Chad M. Spooner ◽  
Giovanni Minelli ◽  
James Newman
Keyword(s):  
Real World ◽  
Measurement Data ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Small Satellite ◽  
Signal To Noise ◽  
Satellite Mission ◽  
Spectral Correlation ◽  
Small Satellites ◽  
Cyclostationary Signal

Challenges in interference-limited satellite detection arising from the low-earth orbit (LEO) and the Industrial, Scientific and Medical (ISM) frequency bands are addressed. In particular, a novel signal presence detector based on cyclostationary signal properties is proposed and analyzed for a low signal-to-noise-plus-interference ratio (SINR) regime. The performance of the proposed detector, which is applicable to various small-satellite scenarios, is evaluated on both simulated and real-world measurement data. This measurement data has been collected from the scientific satellite mission “Picosats Realizing Orbital Propagation Calibrations using Beacon Emitters” (PROPCUBE).

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 Research on the Technological Development of GSO Small Satellite

2019 ◽  
Vol 288 ◽  
pp. 02003
Author(s):  
Geng Jie ◽  
Gong Jinggang ◽  
Wang Zuowei ◽  
Lyu Nan
Keyword(s):  
Technology Development ◽  
Technological Development ◽  
Development Trend ◽  
Low Earth Orbit ◽  
Small Satellite ◽  
Small Satellites ◽  
Development Status ◽  
Satellite Technology ◽  
Large Satellite ◽  
The Development Trend

The application and technological development of geosynchronous orbit(GSO) small satellite are researched in this paper. Firstly the application field and application value of GSO small satellites are analysed. Secondly, the technology development status of foreign GSO small satellites is overviewed. Then the differences and similarities among GSO small satellite, traditional large satellite and low earth orbit(LEO) small satellite are compared, and characteristic and key technique are systematically studied. Finally, for China’s future military and civilian needs, combined with the development trend of modern small satellite technology, the preliminary proposal for the development of China’s GSO small satellite are given.

scholarly journals Analysis of Methods for CubeSat Mission Design Based on in-orbit Results of KRAKsat Mission

2021 ◽  
Vol 15 ◽  
pp. 295-302
Author(s):  
Alicja Musiał ◽  
Dominik Markowski ◽  
Jan Życzkowski ◽  
Krzysztof A. Cyran
Keyword(s):  
Best Practices ◽  
Success Rate ◽  
Lessons Learned ◽  
Mission Design ◽  
Small Satellite ◽  
Small Satellites ◽  
Satellite Missions ◽  
The University

The success rate of currently performed CubeSat missions shows that despite their popularity, small satellites are still not as reliable as larger platforms. This research was conducted to analyse in-orbit experience from the KRAKsat mission and discuss methods for mission design and engineering that can increase CubeSats reliability and prevent their failures. The main purpose was to define best practices and rules that should be followed during mission development and operations to ensure its success based on the overview of the lessons learned from KRAKsat and problems encountered during its mission. This paper summarizes the experiences obtained and provides methods that can be used while carrying out future robust CubeSat projects. It was written to prove that there are some parts of the small satellite missions that are often neglected in the university-led projects and, by ensuring proper testing and planning before the actual mission, its reliability can increase. The following analysis could be used as a guide during the development of the next CubeSat projects.

scholarly journals Synthetic Aperture Radar for Small Satellite

2019 ◽  
Vol 9 (2) ◽  
pp. 3435-3440
Keyword(s):  
Frequency Band ◽  
New Technologies ◽  
Sensor System ◽  
Frequency Change ◽  
Small Satellite ◽  
Small Satellites ◽  
System Parameters ◽  
Trade Offs ◽  
Antenna Length ◽  
Mass Size

Small satellites are growing because they have shorter development cycles, lower cost, new technologies, and more frequent access to space. Sensors for Small satellites come with trade-offs to allow them fit within the mass, size, power and weight constraints imposed by the platform, these trade-offs between sensor system parameters can affect the mission requirements. Considering traditional SAR mission, each frequency band has different capability of penetration and special image characteristics, so the final SAR application will determine the appropriate bands needed. Small satellites come with constraints on the SAR sensor, so an analysis of SAR sensor system parameters (antenna length, antenna width and average transmitted power) at L, C and X band given a determined performance parameters is presented to analyze the effect of these frequency change on the system parameters and to determine the frequency band that is more suitable to fit within the small satellite SAR sensors constraints.

scholarly journals Design, Implementation, and Operation of a Small Satellite Mission to Explore the Space Weather Effects in LEO

Aerospace ◽  
2019 ◽  
Vol 6 (10) ◽  
pp. 108 ◽  
Author(s):  
Isai Fajardo ◽  
Aleksander Lidtke ◽  
Sidi Bendoukha ◽  
Jesus Gonzalez-Llorente ◽  
Rafael Rodríguez ◽  
...  
Keyword(s):  
Space Weather ◽  
Low Cost ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Small Satellite ◽  
Satellite Mission ◽  
Particle Detectors ◽  
Small Satellites ◽  
Environment Effects ◽  
Institute Of Technology

Ten-Koh is a 23.5 kg, low-cost satellite developed to conduct space environment effects research in low-Earth orbit (LEO). Ten-Koh was developed primarily by students of the Kyushu Institute of Technology (Kyutech) and launched on 29 October 2018 on-board HII-A rocket F40, as a piggyback payload of JAXA’s Greenhouse gas Observing Satellite (GOSAT-2). The satellite carries a double Langmuir probe, CMOS-based particle detectors and a Liulin spectrometer as main payloads. This paper reviews the design of the mission, specifies the exact hardware used, and outlines the implementation and operation phases of the project. This work is intended as a reference that other aspiring satellite developers may use to increase their chances of success. Such a reference is expected to be particularly useful to other university teams, which will likely face the same challenges as the Ten-Koh team at Kyutech. Various on-orbit failures of the satellite are also discussed here in order to help avoid them in future small spacecraft. Applicability of small satellites to conduct space-weather research is also illustrated on the Ten-Koh example, which carried out simultaneous measurements with JAXA’s ARASE satellite.

A lifecycle cost model considering both component and system burn-in for operationally unrepairable systems

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Kah How Teo ◽  
Kang Tai ◽  
Vincenzo Schena ◽  
Luca Simonini
Keyword(s):  
System Reliability ◽  
Cost Model ◽  
Cost Savings ◽  
Large System ◽  
Content Type ◽  
Small Satellites ◽  
Procedure Cost ◽  
Warranty Costs ◽  
Final System ◽  
Minimum System

PurposeThis study presents a lifecycle cost model considering multi-level burn-in for operationally unrepairable systems including assembly and warranty costs. A numerical method to obtain system reliability under component replacement during burn-in is also presented with derived error bounds.Design/methodology/approachThe final system reliability after component and system burn-in is obtained and warranty costs are computed. On failure during operation, the system is replaced with another that undergoes an identical burn-in procedure. Cost behaviours for a small and large system are shown in a numerical example.FindingsThere are more cost savings when system burn-in is conducted for a large system whereas a strategy focusing on component burn-in only can also result in cost savings for small systems. In addition, a minimum system burn-in duration is required before cost savings are achieved for these operationally unrepairable systems.Originality/valueThe operationally unrepairable system is a niche class of systems which small satellites fall under and no such study has been conducted before. The authors present a different approach towards the testing of small satellites for a constellation mission.

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.

Development and flight qualification of a small satellite X-band spherical membrane antenna

2021 ◽  
Author(s):  
Aman Chandra ◽  
Terrance Pat ◽  
Juan Carlos Lopez Tonazzi ◽  
Christopher K. Walker
Keyword(s):  
Small Satellite ◽  
X Band
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