The Research Center of stability and non-linear dynamics

Mechanical Engineering Institute of À.À.Blagonravov’s name

Russian Academy of Sciences

Dmitriya Uliyanova, 5, Moscow, 117333, Russia

tel.: (095) 132 01 47, fax: (095) 752 78 67; 146 76 77

The analysis of the state of the problem of the convenient lift construction in space, shows the absence of a commonly acceptable concept that would satisfy everybody and would promote also the removal of moral responsibility freight from the out-of-time projects’ authors.

Unlike the conventional approach, as the design imperative in the given aerospace system is chosen not the power engineering of the spacecraft, but simplification and cheaping of the aerospace system employment with finishing of this design feature up to the aviational systems level.

In this connection, some of the suggested solutions, when reviewing the design from the point of view of local power positions, appear to be non-optimal. It is suggested to compensate the appearing deficit of the power with the fuel.

The aerospace system comprises a spacecraft with two manned stages, the first is the accelerating one, the second - the space one, and a special ground launching complex. The service, loading, docking of stages to each other and to the launching device are horizontal. The propellant loading and the rocket start of the spacecraft are performed in the vertical position. Landing of the stages is horizontal - onto a usual air station of “B” type (the range is 2500 m).

The stages of the aerospace system spacecraft have similar own aerodynamic shapes, they are constructed from the unified rocket units: the first stage has three such blocks, the second - two and a cargo compartment. The units of accelerating and space stages have one unified liquid-fuel rocket engine. The unification makes available the consiberable expanding of the front activities.

The selection of the aerospace system fuel is optimized also from the conditions of the employment simplicity and a minimal cost. The fuel pair oxygen-propane or oxygen-liquefied natural gas (LNG) satisfies these conditions.

In the whole cost of one kilogram of payload launching, the part of the fuel is only 0.15%. It is suggested to reducing the part of the operating costs (more than 90% in the whole cost of a launching), using the simplifying of the service. Namely, this design imperative is the base of of the suggested aerospace system conception.

It is expedient to perform the aerospace system creation using the base of the available capabilities of several countries by forming an international consortium for that purpose.

The suggested aerospace system design provides the fulfilment of all main requirements to the modern international project, including ecology, economy and military-political aspects.

The availability of the international system of space services will stimulate the termination of disputable actions of the countries on the rocket technology spread, on the double-purpose rocket systems creation.

In this case the rocket danger in the world will be reduced.