[ Engineering design of fuel tanks, performing volumetric calculations, strength calculations, etc ]
[ Engineering design of power circuits for launch vehicles and spacecrafts, strength calculation, determination of the optimal design option according to the strength / weight / dimensions criteria ]
[ Development of pneumatic and hydraulic schemes of liquid-propellant rocket propulsion systems and performing hydraulic calculations ]
[ Performing the layout of the product (liquid propulsion system, launch vehicle, spacecraft, etc.) through the development of a three-dimensional model (SolidWorks, NX Unigraphics, Autodesk Inventor) ]
[ Development of a complete package of engineering design documentation for the product - specification, assembly drawing, outline drawing, part drawings, manufacturing specifications, specification sheet, list of purchased products, incoming inspection sheet, operation manual, comprehensive experimental development program ]
[ Writing technical specifications for product development ]
[ Design and release of design documentation for dry compartments made of metal or carbon composites for space launch vehicles, satellites, habitation module of orbital stations ]
[ Engineering design and release of design documentation for transition systems for placing payload on the space launch vehicles ]
[ Release of engineering design documentation for elements of fuel and electrical systems - fuel tanks, installation of pipelines, installation of sensors, instruments, units, etc ]
[ Issuing of documentation for hull elements of satellites and installation of various units and devices ]
[ Issue of documentation for habitation modules, installation of equipment, elements of mechanical systems, external power elements, units and instruments of orbital stations ]
[ Engineering calculations for strength ]
Three-dimensional model of the second stage of a light space launch vehicle. The payload is 500 kg, into a LEO of 200 km. The stage layout is based on the results of strength, hydraulic, volumetric and other engineering calculations.
Engineering design of a liquid rocket engine on kerosene and hydrogen peroxide (85%) with a thrust of 1000 N.
Liquid rocket engine on environmentally friendly fuel components with an electric pump feed system, a power system for electronic control of pumps, a pneumatic or electrical system for a thrust vector control (due to the possibility of rotation of the combustion chamber in a hinged suspension). The main elements of the engine could be made using additive technologies.
A liquid rocket engine powered by hydrogen peroxide with a thrust of 3000 N has been designed and is being manufactured.
Engineering design a small amateur rocket with 4 solid rocket boosters for testing the guidance system on grid fins.