Overview of Commercial Small Satellite Systems in the “New Space” Age

2020 ◽  
pp. 69-86
Author(s):  
Timothy J. Logue ◽  
Joseph N. Pelton
Aerospace ◽  
2021 ◽  
Vol 8 (6) ◽  
pp. 149
Author(s):  
Seong-Cheol Kwon ◽  
Ji-Hae Son ◽  
Sung-Chan Song ◽  
Jin-Han Park ◽  
Kyung-Rae Koo ◽  
...  

The Small SAR Technology Experimental Project (S-STEP) mission aims to develop a new (space-based 80 kg-class active X-band synthetic aperture radar (SAR)) satellite with a main imaging mode of 1 m resolution stripmap. In the S-STEP mission, to achieve the design goal of developing faster, cheaper, better, and lighter small SAR satellite systems, innovative thermo-mechanical design approaches have been proposed and investigated. The major design approaches are the bus-payload integrated flat plate-type structure, multifunctional transmit/receive (TR) module, and dedicated vibration-free orbit deployer (VFOD) with the function of whole spacecraft vibration isolation. To validate the feasibility of the innovative mechanical design of S-STEP, a structural analysis considering launch and on-orbit environments is performed. In addition, development test results are presented to confirm the effectiveness of the proposed design approach for VFOD.


2021 ◽  
Author(s):  
Sarah Hardacre

The desire to bring space travel to a wider range of missions and uses has driven the market to using smaller and thus more affordable satellite systems. The Canadian Space Agency is completing the design and construction of a small satellite named QuickSat, which will utilize a magnetometer as one of its attitude and orbit determination instruments. A test bed comprised of three pairs of Helmholtz coils was used for hardware in the loop testing of the magnetometer. Testing was initially completed to prove the capabilities of the test bed, and then was completed to demonstrate the capabilities of the flight qualified magnetometer. The three pairs of Helmholtz coils were driven by data calculated from a spherical harmonic model of the Earth's magnetic field The coils were controlled using a robust controller and the magnetometer was used to drive the B-dot control law in the QuickSat simulation. The Ryerson Attitude and Control Experiment (RACE), which is a small satellite sized platform, free to spin about one axis on a near frictionless air bearing, was utilized to develop and test a system to deal with redundancy of satellite sensors. The possibility of missing, noisy or erroneous output during flight requires that a filter be applied to a satellite's flight code to determine with accuracy the attitude and orbit of the spacecraft. It was thus decided that a Kalman Filter be applied to RACE. The Kalman filter was applied to the RACE simulation successfully and initial hardware testing was carried out.


Author(s):  
P. Srinivas ◽  
Kumar Rahasyam ◽  
N. Beebamma ◽  
PSR Srinivasa Sastry

Author(s):  
Cassandra Steer ◽  
Matthew Hersch

The creation of the U.S. Space Force at the end of 2019, France’s steps toward creating a similar dedicated military body, and NATO’s formal recognition of space as a military operational zone integral to international security were all markers of the beginning of a new era as of the second decade of this century. Although space-based technologies have been utilized by world militaries since the beginning of the space age in the 1960s, the militarization of space has not been on the public radar to the extent it now is, and the likelihood of space-based conflict has never been greater. At the same time, popular awareness of civil and commercial uses of space has also increased. In short, we are in a New Space Age, one that is equal parts commercial and political, and one which—arguably even more so than the first Space Age—has national and international security interests at its center. The need for ethically sound policy and law at this time is irrefutable, and it is in answer to this need that our contributing authors have tackled various challenging issues, applying their exceptional expertise. In addition to agreement as to current and future threats to national and global security stemming from the use—and misuse—of the space environment, there are many suggested measures for ameliorating the risk of conflict in space. A central theme in all of the chapters is that the best way to avoid capricious use of the space environment in wartime is to create a set of norms in peacetime, recognizing that shared use, rather than dominance, is the preferred outcome for all spacefaring nations.


2020 ◽  
Vol 143 (1) ◽  
Author(s):  
Steven A. Isaacs ◽  
Caelan Lapointe ◽  
Peter E. Hamlington

Abstract With easier access to space and the growing integration of power-dense components, small-scale thermal management solutions are increasingly in demand for small satellite systems. Due to the strict mass and volume requirements commanded by such power-dense small spacecraft, heat pipes with thin and flat architectures provide nearly ideal solutions for the efficient transfer and dissipation of heat. Unlike traditional heat pipes, however, the performance of thin heat pipes is heavily dependent on details of the internal heat pipe structure, including the vapor core geometry and structural mechanical characteristics. In this study, the development and testing of a new computational modeling and optimization tool are presented for the design of thin flat heat pipes. The computational model is described in detail and includes parameters that define properties of the liquid wick, vapor core, and structural case. The model is coupled to a gradient-based optimization procedure that minimizes a multi-objective cost function for a range of operating conditions. The cost function is expressed as the weighted sum of the total temperature drop, the liquid/vapor pressure ratio, the total mass of the heat pipe, and the structural deflection of the heat pipe during operation. The combined computational modeling and optimization tool is then used to design a copper-methanol flat heat pipe for a small satellite mission, where the optimization is performed with respect to both cold and hot orbital conditions. Validation of the optimized heat pipe is performed using computational fluid dynamics (CFD) simulations of the initial and final designs.


Physics World ◽  
1999 ◽  
Vol 12 (7) ◽  
pp. 3-3
Keyword(s):  

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