Trajectory analysis for small satellite payload recovery from low earth orbit

2001 ◽  
Author(s):  
Hyungwon Kim ◽  
Frank Lu ◽  
Larry McNay
Keyword(s):  
Trajectory Analysis ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Small Satellite

scholarly journals In Situ Measurement of Carbon Fibre/Polyether Ether Ketone Thermal Expansion in Low Earth Orbit

Aerospace ◽  
2020 ◽  
Vol 7 (4) ◽  
pp. 35 ◽  
Author(s):  
Farhan Abdullah ◽  
Kei-ichi Okuyama ◽  
Isai Fajardo ◽  
Naoya Urakami
Keyword(s):  
Thermal Expansion ◽  
Carbon Fibre ◽  
Material Science ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Small Satellite ◽  
Polyether Ether Ketone ◽  
Ether Ketone ◽  
Orbit Data

The low Earth orbit (LEO) environment exposes spacecraft to factors that can degrade the dimensional stability of the structure. Carbon Fibre/Polyether Ether Ketone (CF/PEEK) can limit such degradations. However, there are limited in-orbit data on the performance of CF/PEEK. Usage of small satellite as material science research platform can address such limitations. This paper discusses the design of a material science experiment termed material mission (MM) onboard Ten-Koh satellite, which allows in situ measurements of coefficient of thermal expansion (CTE) for CF/PEEK samples in LEO. Results from ground tests before launch demonstrated the feasibility of the MM design. Analysis of in-orbit data indicated that the CTE values exhibit a non-linear temperature dependence, and there was no shift in CTE values after four months. The acquired in-orbit data was consistent with previous ground tests and in-orbit data. The MM experiment provides data to verify the ground test of CF/PEEK performance in LEO. MM also proved the potential of small satellite as a platform for conducting meaningful material science experiments.

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 Nonlinear analysis of thermal behavior for a small satellite in Low Earth Orbit using many-node model

2017 ◽  
Vol 20 (K2) ◽  
pp. 66-76
Author(s):  
Chung Ngoc Pham ◽  
Anh Dong Nguyen ◽  
Hieu Nhu Nguyen
Keyword(s):  
Temperature Limit ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Solar Irradiation ◽  
Solar Array ◽  
Earth Orbit ◽  
Small Satellite ◽  
Simulation Purpose ◽  
Allowable Temperature ◽  
Cover Plates

In this paper, nonlinear thermal responses of a small satellite in Low Earth Orbit (LEO) are analyzed using many-node model. The main elements of primary structure of the satellite include six rectangular cover plates and a solar array linking with satellite's body. These elements can be modeled as different lumped thermal nodes. We use an eight-node model for estimating temperatures at nodal elements i.e. six nodes for cover plates, and two nodes for front and rear surfaces of the solar array. The nodes absorb three major heat energy sources from the space environment consisting of solar irradiation, Earth’s albedo and infrared radiation. The established system of thermal balance equations for nodes is nonlinear and is solved by a numerical algorithm. For simulation purpose, it is assumed that the satellite always remains Earth-pointing attitude during motion. Temperature evolutions of nodes in time are explored in details. The obtained results show that the predictive temperature values of nodes are within the allowable temperature limit range of the satellite.

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.

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