|
RU2398208C1
|
|
Device for investigation of structural materials for ignition in medium of gaseous oxidant, containing particles of various materials (versions)
|
|
RU2391548C1
|
|
Test device for liquid propellant engines (versions)
|
|
RU2400644C1
|
|
Low-thrust rocket engine running on non-self-igniting gaseous oxidiser and liquid fuel, and method of its starting
|
|
RU2375559C1
|
|
Oil production method
|
|
RU2373419C1
|
|
Multi-chamber sustainer with jet nozzle
|
|
RU2369766C1
|
|
Thruster (rdmt) chamber working on two-component anergolic gaseous fuel (versions)
|
|
RU2365809C1
|
|
Multiple cavity high pressure balloon
|
|
RU2366865C1
|
|
Heat accumulator for working medium heating
|
|
RU2364742C1
|
|
Liquid-propellant rocket engine of multiple start-up (versions)
|
|
RU2363932C1
|
|
Method for measurement of lateral component of elecrojet engine thrust vector and device for its realisation
|
|
RU2374791C1
|
|
Electric arc ac plasmotron
|
|
RU2364741C1
|
|
Cruise multi-chamber propulsion system with nozzle extension (versions)
|
|
RU2370739C1
|
|
Device for determining lateral components of thrust vector of electrojet engine
|
|
RU2370740C1
|
|
Device for determining laterial components of thrust vector electrojet engines
|
|
RU2350052C1
|
|
Plasma jet
|
|
RU2359145C1
|
|
Hybrid rocket engine
|
|
RU2366122C1
|
|
Plasmatron for application of coatings
|
|
RU2364842C1
|
|
Method for calibration of gas flow metre and device for its realisation
|
|
RU2348828C1
|
|
Low-thrust rocket engine that operates on non-self-ignitable gaseous oxidant and liquid fuel and method of its start
|
|
RU2346079C1
|
|
Method for treatment of fur hair
|
