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    • The Use Of The Aerodynamic Parameters Of The Launch Vehicle Last Stage To Inject Satellite To The Earth Orbit

    Paper number

    IAC-07-D2.3.08

    Author

    Dr. Alexey Galaktionov, Central Research Institute of Machine Building (TSNIIMASH), Russia

    Coauthor

    Dr. Valery Dineev, Central Research Institute of Machine Building (TSNIIMASH), Russia

    Coauthor

    Dr. Vasiliy Kubyshkin, Central Research Institute of Machine Building (TSNIIMASH), Russia

    Coauthor

    Mr. Alexander Muhin, Central Research Institute of Machine Building (TSNIIMASH), Russia

    Coauthor

    Mr. Daniil Fofonov, Central Research Institute of Machine Building (TSNIIMASH), Russia

    Year

    2007

    Abstract
    The set of  projects are known today to inject payload to Space (sea-launch, air-launch)  which are alternative to convenient method.  The main task of these projects is decreasing the power losses during injection of the payload to the orbit by shift of the launch place.
In this connection it is considered a new concept of the injection to the space the payload, which allows to arrange the satellite orbit by using the lift-to-drag-ratio lift-to-drag (LD) of the launch vehicle (LV) last stage. According to this concept the LV last stage is fulfilled as a vehicle with great LD and this vehicle realizes a long flight in upper atmosphere with  azimuth angle variation. It allows to form the orbit plane during fly in atmosphere and to refuse the convenient dynamic maneuvers in the space. In this connection the trajectory optimization problem is considered, the optimal aerodynamic shapes are determined and the features of hypersonic viscous flow round last stage is examined. 
	According to fulfilled calculations the payload mass injected to space from Russian launch place Plisetsk may be increased in 1.5 times in comparison with convenient method. If the height of the equatorial round orbit is more then four Earth radiuses the convenient method is more effective.
	The results of the ballistic and aerodynamic calculations are presented. 
The work was supported by Russian Foundation of Basic Researcher project 06-01-00236.
    Abstract document

    IAC-07-D2.3.08.pdf

    Manuscript document

    IAC-07-D2.3.08.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.