FIELD: machine building.
SUBSTANCE: invention relates to ion-plasma or ionic electric rocket engine used for controlled acceleration of aircraft in space vacuum. Proposed device comprises gas-permeable microporous membrane through which flow of neutral particles of working medium passes. This makes it possible to produce a multi-jet surface charged plasma distributed near the surface of the membrane facing the ion acceleration region.
EFFECT: result is increased efficiency of working medium use, increased speed and area of cross section of ion flare, operation time and speed of movement, reduced cost and complexity of device.
7 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| IONIC ROCKET ENGINE OF SPACECRAFT | 2018 |
|
RU2682962C1 |
| ELECTRIC ROCKET ENGINE (VERSIONS) | 2019 |
|
RU2726152C1 |
| RAMJET RELATIVISTIC ENGINE | 2020 |
|
RU2776324C1 |
| HYBRID WAVE PLASMA ENGINE FOR LOW ORBIT SPACE VEHICLE | 2021 |
|
RU2764487C1 |
| BIDIRECTIONAL WAVE PLASMA ENGINE FOR A SPACE VEHICLE | 2020 |
|
RU2764823C1 |
| METHOD OF CLEANING STATIONARY PLASMA ENGINE ACCELERATION CHANNEL WORK SECTION OF EROSION PRODUCTS | 2011 |
|
RU2458249C1 |
| GAS-ELECTRIC ISOLATION | 2018 |
|
RU2703848C1 |
| MODULE WITH MULTICHANNEL PLASMA PROPULSION SYSTEM FOR SMALL SPACECRAFT | 2020 |
|
RU2741401C1 |
| METHOD FOR CREATING ELECTRIC PROPULSION THRUST | 2016 |
|
RU2635951C1 |
| METHOD OF THRUSTING AND DESIGN OF JET ENGINE | 1997 |
|
RU2169854C2 |
