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Flanged Connection for Space Launchers

#0360


Flanged Connection with a Static Spherical Bearing.

Tech Area / Field

  • SAT-STM/Spacecraft Trajectories and Mechanics/Space, Aircraft and Surface Transportation

Status
8 Project completed

Registration date
24.01.1995

Completion date
25.03.1998

Senior Project Manager
Urezchenko V M

Leading Institute
NPO EnergoMash, Russia, Moscow reg., Khimki

Collaborators

  • European Space Agency / European Space and Technology Center / YMM, The Netherlands, Noordwijk\nSEP (Société Européenne de Propulsion), France, Vernon

Project summary

The project is aimed at increasing reliability, improving characteristics and updating the advanced liquid propellant rocket engines with possible reusability. The availability in rocket engines of a large number of rigid ducts, connected between each other and with units by means of tight connections requires for engine mounting the implementation of complicated from the point of design and technology, bulky, heavy expansion joints, making the engine design more complicated and its characteristics worse. In the first place it is disposed to high pressure large-size connections through which highly flammable liquids are conveyed and slight leakage of which may result in fire or explosion.

The SEP and NPO Energomash propose to develop a new kind of fluid and gas connections which exhibit high pressure tightness, reliability and allow to assemble the engine with numerous rigid lines without the help of heavy and unreliable expansion joints.

These connections are supposed to use spherical contact surfaces and specific seals with double sealing barriers; in this case the first barrier will be a self-sealing with elastic elements and the second one will be in a form of a tight thrust bearing. It will eliminate almost any risk of leakage as well as any risk of overheating and fretting-wear of surfaces that is most important to eliminate the connection fire hazard.

Such connection allows its operability diagnostics, leakage monitoring between the two sealing barriers and organized leakage drain at all stages of the engine manufacture, assembly and operation (these procedures could be possible without the engine pressurization).

The project may be usefully implemented not only in scope of space transportation, but in other fields of activity like chemical or oil industry, nuclear power plants, air or sea transportation (mainly submarines) and other engineering fields in which operability diagnostics and the line flange connections reliability increasing lead to the important improvement of human and environmental protection and decreasing of metal capacity provides the mass and overall dimensions decreasing.

The project is executed by NPO Energomash in a period of 18 months. The project work amount will be 650 person/month.

This will include theoretical analysis, design-technological and material-science justification file, designing, documentation issue, preliminary and qualification tests, summary report issue on the results of work.

SEP will provide the issue of the coordinated Technical Task, will participate in discussing and coordinating the documentation, test plan, programs and results, the project summary report and also will consider the questions on the project results specific further implementation.


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