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Home Aerospace & Aeronautics Paste-like propellant rocket propulsion

Paste-like propellant rocket propulsion

Description

The Paste-like Propellant Rocket Propulsion (or PRM) works are conducted in new direction of rocket engine-building development of propulsions using unitary (fuel+oxidizer into one tank) paste-like propellant (non-hardened solid propellant) with its pressure feeding into combustion chamber. The rocket engine on paste-like propellant is in the phase of fire tests (for spacecraft) and test development (for LV march motors). The engine on paste-like propellant is conceptually an updated solid rocket motor (SRM) with new capabilities of deep regulation and multiple restarting while preserving major advantages of SRM and borrowing from SRM some elements of design, materials, solid propellant components, and technologies.

The advanced technology concept has been proposed to commercialize the potentiality of new type of rocket propulsion for wide spectrum of tasks: from small spacecraft attitude correction to large march ones for launch and space vehicles. The PRM will allow reduce the volume of a propulsion plant in the LV and take more on-board payload to high and stationary orbits.

Technical Characteristics

Innovative Aspect and Main Advantages

The engines have unique capabilities of deep thrust regulation (in an experiment 80-times throttling was realized) and multiple restarting. The engines on paste-like propellant, while solving a number of tasks, have mass-dimensional advantages when it is used in reaction control systems and upper stages of LVs. The use of engines on paste-like propellant as main engines for launch vehicles (2nd, 3rd and 4th stages) will allow increase their effectiveness by optimizing the trajectory of payload injection by engine throttling during the whole flight. The use of promptly and deeply regulated engine on paste-like propellant with multiple restarting as a booster, an engine for soft landing on the surface of space objects (planets) and as actuators of reaction control system, while solving a number of tasks, will improve mass-dimensional characteristics of spacecraft.

The use of these new type of motors as regulated main engines and as control system propulsions of launch vehicles and spacecraft will allow increase their power efficiency. Completion of development of the engines on paste-like propellant will allow enter to the market of space hardware and commercial services with a new class of rocket motors allowing to increase the effectiveness of payload injection by light and medium - class launch vehicles. The Laboratory of Advanced Jet Propulsion in co-operation with R&D Power Engineering Institute found new technical solutions on initial and multiple ignitions, combustion of paste-like propellant, regulation of propellant consumption, prevention of flame from coming from the combustion chamber into the feeding system, which effectiveness was confirmed by numerous firing tests of experimental and pilot engines on paste-like propellant. This is a unique scientific-technical experience that together with Yuzhnoye’s developments of solid propellant and liquid rocket motors allows develop the engines on paste-like propellant for different purposes.


General view of artistic and real PRM
Fig. 1 General view of artistic and real PRM

Stage of Development

The PRM plant for spacecraft attitude control was fully completed and many times tested. Currently there is conducting development of three types of the PRM: for space vehicles/tugs and launch vehicles as main ones for upper stages, for planet (in particularly, the Moon and Mars) landing units. The PRM has one joint patent with Yuzhnoye SDO and 3 patents of The LAJP.

Contact Details

Organization: The Laboratory of Advanced Jet Propulsion
Address: #41, Budivel’nykiv str. Dnipropetrovsk, 49008, Ukraine
+ 38 056 716 7861, Fax: + 38 056 716 7861
This e-mail address is being protected from spambots. You need JavaScript enabled to view it

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