|
|
|
|
|
Janis Dalbins, Kristo Allaje, Hendrik Ehrpais, Iaroslav Iakubivskyi, Erik Ilbis, Pekka Janhunen, Joosep Kivastik, Maido Merisalu, Mart Noorma, Mihkel Pajusalu, Indrek Sünter, Antti Tamm, Hans Teras, Petri Toivanen, Boris Segret and Andris Slavinskis
Nanosatellites have established their importance in low-Earth orbit (LEO), and it is common for student teams to build them for educational and technology demonstration purposes. The next challenge is the technology maturity for deep-space missions. The ...
ver más
|
|
|
|
|
|
|
|
|
|
|
Aleksander Olejnik, Lukasz Kiszkowiak, Piotr Zalewski and Adam Dziubinski
In recent decades, the rapid development of alternative methods for launching satellites into space has been observed. The main purpose of this work is to obtain reliable information about aerodynamic properties, which will be useful in the preliminary d...
ver más
|
|
|
|
|
|
|
|
|
|
|
Sarmad Dawood Salman Dawood, Ahmad Salahuddin Mohd Harithuddin and Mohammad Yazdi Harmin
Mass reduction is a primary design goal pursued in satellite structural design, since the launch cost is proportional to their total mass. The most common mass reduction method currently employed is to introduce honeycomb structures, with space qualified...
ver más
|
|
|
|
|
|
|
|
|
|
|
Sarmad Dawood Salman Dawood and Mohammad Yazdi Harmin
Satellite systems undergo several operational phases during their service life, including the assembly phase, ground transportation phase, the launch phase, and the in-orbit operation phase. Among these phases, the one that imposes the highest level of l...
ver más
|
|
|
|
|
|
|
|
|
|
|
Paolo Marzioli, Fabio Santoni and Fabrizio Piergentili
Time Difference of Arrival (TDOA) networks could support spacecraft orbit determination or near-space (launcher and suborbital) vehicle tracking for an increased number of satellite launches and space missions in the near future. The evaluation of the ge...
ver más
|
|
|
|
|
|
|
|
|
|
|
Paulo Renato Silva, Ivanildo Silva Abreu, Paulo Almeida Forte, Henrique Mariano Costa do Amaral
Pág. 150 - 161
For proper attitude control of space-crafts conventional optimal Linear Quadratic (LQ) controllers are designed via trial-and-error selection of the weighting matrices. This time consuming method is inefficient and usually results in a high order complex...
ver más
|
|
|
|
|
|