Study of vector trust control efficiency for advanced space transportation systems
- Paper number
IAC-08.D2.5.10
- Author
Dr. Alexey Galaktionov, TSNIIMASH, Russia
- Coauthor
Mr. Alexander Butkov, TSNIIMASH, Russia
- Year
2008
- Abstract
Choice of the flight control system for heavy launchers influences significantly on efficiency of the space transportation system in whole, and, consequently, on competitiveness of the launcher on the international market of space services. Existing projects of launchers (“Angara”, Space shuttle, KSLV, etc.) have moving nozzles for flight control at ascent trajectory that are more advantageous than aerodynamic control surfaces. Determination of hinge moments is a complicated scientific and technological problem due to non-stationary flow at the base region of the launchers, where these nozzles are attached. Real flight conditions for operation of moving nozzles can’t be simulated in full on-ground. That is why TSNIIMASH carries out complex theoretical and experimental investigations. In order to analyze the flow in details and to develop the application software there were carried out a number of fundamental experimental researches at TSNIIMASH wind tunnels, and the results are discussed in the present paper. Experimental investigations were conducted for Mach number range from 0.2 to 10 and Reynolds number from 7x10E4 to 2x10E8. Experimental errors were analyzed. Numerical simulation was conducted using the high level mathematical models – total Navier-Stocks equations with the turbulence models as closure conditions, and verification was based on experimental investigations with hot engine jets in TSNIIMASH facilities and flight tests.
- Abstract document
- Manuscript document
IAC-08.D2.5.10.pdf (🔒 authorized access only).
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