At present, RSC Energia has developed a conceptual configuration for the interplanetary orbiter where the crew will work during the entire interplanetary transit. This incorporated the experience of work on space stations.

Based on the analysis of failure statistics for those space stations, a concept was developed for the functional and unit redundancy needed to assure a high level of reliability of the orbiter.	Layout of Interplanetary orbiter sections 800x528 (85 806 bytes)
The lander/ascent module layout and aerodynamic form options have been analyzed.	Lander/ascent module configuration options 800x499 (68 857 bytes) Lander/ascent module operation profile 746x458 (69 196 bytes) Ascent module overall view 800x630 (88 489 bytes)
Interplanetary expedition vehicle assembly plan has been developed.	Interplanetary expedition vehicle assembly plan 800x534 (75 134 bytes)
Basic configurations for long truss structures needed to support film-type solar arrays have been developed. These designs are based on design solutions of the Sofora truss.	Assembly of solar array beams 800x519 (105 214 bytes)
A process has been developed for assembling large solar arrays in orbit.	Installation of film-type photovoltaic cells 800x517 (99 979 bytes)
A program has been developed for building a series of small spacecraft based on the interplanetary vehicle concept with electrical propulsion main engines and solar arrays.	Unmanned spacecraft for developmental testing of engineering solutions for the interplanetary expedition vehicle 800x625 (49 245 bytes)

The first experimental spacecraft (Module-M) is to be delivered to ISS on-board Progress spacecraft, to be subsequently assembled by the crew during an EVA and moved away from the space station. Using electric propulsion main engines, the spacecraft will raise its orbit to 1200 km. This mission will study the effects of long operation of electrical propulsion engines on the equipment.
At present, Energia's manufacturing plant has built the spacecraft structure, virtually all the mechanical units and assemblies have been tested, and the spacecraft support systems and scientific payloads have passed the phase of developmental testing in the lab. However, since the funding for this work has stopped, manufacturing of further elements for the spacecraft is suspended.
The next spacecraft, Module M2, is to be sent to a Lagrangian point (H= 1,500,000 km). Along with developmental testing of solutions to fundamental problems of the interplanetary vehicle flight, this spacecraft is also to be used for early warnings of magnetic storms on Earth caused by the solar activity.
And, finally, Mars-Module is to be sent to Mars to study the planet. It will be the first spacecraft, which, along with the developmental testing of the interplanetary vehicle will be intended for Martian research using remote sensing equipment and landers with the necessary equipment, which it will deliver. It will support the operation of the equipment in Mars orbit for more than two years. If need be, this spacecraft will be capable of returning to low Earth orbit.
Mars-Module will be capable of addressing the following Mars research tasks:

• Study of Mars climate, surface and internal structure;
  
• Global photographic survey of the Martian surface;
  
• Mars remote sensing.

A main feature of the series of spacecraft for developmental testing of the interplanetary vehicle is that they will be de3livered to ISS on-board Progress spacecraft to be assembled by the space station crew.