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PROJECTS

PASTE-LIKE PROPELLANT ROCKET PROPULSION

The Slurry-type Propellant Rocket Propulsion (SPRP) or simply Slurry Rocket Motor (SRM) works are conducted at a new direction of rocket engine-building-development of propulsions on unitary slurry-type propellant (or gel, that is a non-hardened solid propellant) with its pressure feeding into combustion chamber.
This unique technology is based on a combination of two main components: caoutchouc as a fuel and ammonium perchlorate as an oxidizer. The result is a propulsion technology that blends the simplicity of solid rockets with the re-start and throttle ability of liquid-fueled propulsion.

The most significant aspect is that rockets with SRMs are much safer than other rocket technologies. The unitary fuel mixed with oxidizer at one tank makes it particularly well suited for human spaceflight and for applications that require a safer propulsion technology that can be, and is, safely, commercially transported and handled.
The rocket engine on slurry-type propellant is in the phase of post-fire tests. The engine on slurry-type propellant is conceptually an updated Solid Rocket Motor (SRM) with new capabilities … More >

IMPULSE DETONATION PROPULSION

The thrust at impulse propulsion is being generated discretely by air-blast doing by micro- explosion into combustion chamber. There are two types of the detonation propulsion: air-jet using atmosphere oxygen - PDE (Pulse Detonation Engine) and rocket - PDRE (Pulse Detonation Rocket Engine).
The power plants of the first type use hydro-carbon fuels and can operate effectively from take-off till rates М=3-4 that is doing them especially attracted for the use at fighting winged rockets. The Pulse Detonation Rocket Engines are mean for space flights. The PDRE technology is one of several propulsion alternatives being developed by the LAJP to dramatically reduce the cost of space transportation …

HOLLOW CATHODE MICRO-THRUSTER

Electric propulsion systems, utilising Gridded Ion Engines and Hall Effect Thrusters, are commonly used on Geostationary Communications Satellites to perform orbit top-up and/or  manoeuvres (eg. Boeing 602HP, Boeing 702 and Astrium E3000). These systems offer significant propulsion system mass savings over conventional all chemical propulsion systems. However, at present auxiliary chemical propulsion systems are still required to perform other AOCS functions, adding to the mass and complexity of the overall propulsion systems.
The possibility of an “all electric” satellite, using only electric propulsion systems to perform all the orbit top-up and AOCS functions was suggested some time ago. Such an approach would require either an unconventional thruster accommodation (which may be non-optimal for some or all of the AOCS manoeuvres) or an auxiliary electric propulsion system must be used, which may in itself be complex and may not offer any significant advantage over a conventional chemical system.
Alternatively, if a simpler auxiliary propulsion system could be devised, which utilised the existing infrastructure of the primary electric propulsion system (tank, power supplies, gas feed systems), then significant mass and complexity savings could be made, and the “all-electric” satellite might become a reality. Cold gas thrusters and resistojet have been considered for this function, but the use of Xenon limits the performance of these systems to between 20 – 50 seconds specific impulse, which makes them uncompetitive.
In recent years the possibility of using a Hollow Cathode device as a thruster has been investigated … More >

MICRO LIQUID MONO-PROPELLANT PROPULSION

The Liquid Mono-Propellant Propulsion (LMPP) has essential working principle of the mono-propellant thruster is that it uses hydrogen peroxide or hydrazine with catalytic decomposition. There are jet systems using thermal decomposition for hydrazine. The hydrazine has some advantages before hydrogen peroxide: it is more stable and has specific impulse Isp up to 230 s.
We proposed the combined jet system – the motor using liquid mono-propellant and plasma accelerator … More >

 

 

 

MICROSATELLITE

The huge number of debris in space due to the human activities since the launch of Sputnik in 1957 is a major problem. Of 4 700 space missions that have taken place since that time, just ten account for a third of the current debris. Space debris in orbit around the Earth due to the upper stages of launchers, elements of satellites, other artificial fragments present a potential collision risk for the satellites. Despite the reduction in the number of launches, it is a major problem for satellites set on Low Earth Orbit and Geo-stationary Earth Orbit (14000 catalogued objects, 400 000 debris larger than 1cm, 135 millions debris larger than 1mm). The interest of the space agencies to prevent accidents and to clean the space is notable … More >