Numerical Simulation of Radiating Re-Entry Flows around Orbital Space Vehicle: Comparison with Observed Data

Author(s):  
Sergey Surzhikov
2021 ◽  
Vol 150 (4) ◽  
pp. A214-A214
Author(s):  
Samuel A. Olausson ◽  
Michael S. Bassett ◽  
Griffin Houston ◽  
Logan T. Mathews ◽  
Mark C. Anderson ◽  
...  
Keyword(s):  

2009 ◽  
Vol 40 (2) ◽  
pp. 131-149 ◽  
Author(s):  
A. V. Vaganov ◽  
S. M. Drozdov ◽  
A. P. Kosykh ◽  
G. G. Nersesov ◽  
I. F. Chelysheva ◽  
...  

2021 ◽  
Vol 2094 (4) ◽  
pp. 042083
Author(s):  
Yu V Kaun ◽  
N A Brykov ◽  
M V Chernyshov

Abstract The development of a reusable launch system is one of the most promising directions in the development of cosmonautics. World rocket companies are striving to create a space vehicle with improved tactical and technical characteristics. The main task is to ensure the most efficient flight mode of the reusable spacecraft from the point of view of the full load of the injection system. Since the main costs are spent on transporting the fuel of the rocket and its own design, the developers strive to fully load such a system not only when sending into orbit, but also when returning back. The implementation of the idea of a reusable spacecraft entails large energy losses, which suggests the idea of creating a single-stage reusable launch system.


2009 ◽  
Vol 00 (00) ◽  
pp. 090904073309027-8
Author(s):  
H.W. Wang ◽  
S. Kyriacos ◽  
L. Cartilier

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