METHOD FOR MEASUREMENT OF ANGULAR AND ENERGETIC CHARACTERISTICS OF ELECTROJET ENGINE TORCH HEAVY PARTICLES FLOW AND DEVICE FOR ITS REALISATION Russian patent published in 2010 - IPC F03H1/00 

Abstract RU 2388934 C2

FIELD: power engineering.

SUBSTANCE: method consists of electronic current cut-off from plasma of investigated flow and measurement of ion current at various values of ion-braking potential difference in each specified point of flow cross section. After electronic current cut-off from plasma, in specified point density of heavy particles thermal power is measured in various directions in each of two mutually perpendicular planes. Direction of flow motion is detected in specified point by maximum of thermal power density value, which is used to detect total density of heavy particles energy flow. Then ion-braking difference of potentials is changed. At the same time ion current and thermal power are measured in direction of thermal power maximum, which are used to detect density of energy flow carried by neutrals, as well as function of ions distribution by energies and value of their average energy in point of measurement. Device for measurement of angular and energetic characteristics of heavy particles flow in plasma of electrojet engine torch comprises body with inlet window made of electroconductive non-magnetic material. Header, having input lead, is electrically connected to current metre. It is installed in body opposite to inlet window. Collimator is installed in body and is fixed in its inlet window with the possibility of collimator output opening centre displacement along arc of circumference around centre of body inlet window by means of stem hingedly joined to it via connecting rod, besides header is arranged in the form of calorimetre with concave cylindrical surface facing collimator.

EFFECT: invention makes it possible to produce information on neutral component of heavy particles flow, information on charged and neutral components in flow of heavy particles in plasma jet behind electrojet engine cut, to improve accuracy and reliability of measurements.

2 cl, 1 dwg

Similar patents RU2388934C2

Title Year Author Number
MEMBRANE SPACECRAFT ION-PLASMA ROCKET ENGINE 2018
  • Makarov Sergej Borisovich
  • Tsybin Oleg Yurevich
RU2709231C1
IONIC ROCKET ENGINE OF SPACECRAFT 2018
  • Tsybin Oleg Yurevich
  • Makarov Sergej Borisovich
RU2682962C1
RAMJET RELATIVISTIC ENGINE 2020
  • Senkevich Aleksandr Pavlovich
RU2776324C1
SPACECRAFT FOR CLEANING NEAR-EARTH SPACE FROM SPACE DEBRIS 2022
  • Mogulkin Andrei Igorevich
  • Melnikov Andrei Viktorovich
  • Obukhov Vladimir Alekseevich
  • Peisakhovich Oleg Dmitrievich
  • Svotina Viktoriia Vitalevna
  • Pokryshkin Aleksandr Ivanovich
RU2784740C1
HYBRID WAVE PLASMA ENGINE FOR LOW ORBIT SPACE VEHICLE 2021
  • Shumejko Andrej Ivanovich
  • Majorova Vera Ivanovna
  • Telekh Viktor Dmitrievich
RU2764487C1
ELECTRIC ROCKET ENGINE (VERSIONS) 2019
  • Penkov Maksim Mikhajlovich
  • Goncharov Pavel Sergeevich
  • Martynov Viktor Vasilevich
  • Tsybin Oleg Yurevich
RU2726152C1
BIDIRECTIONAL WAVE PLASMA ENGINE FOR A SPACE VEHICLE 2020
  • Shumeiko Andrei Ivanovich
RU2764823C1
WAVE PLASMA SOURCE OF ELECTRONS 2021
  • Shumeiko Andrei Ivanovich
RU2757210C1
PLASMA ENGINE WITH CLOSED ELECTRON DRIFT 2018
  • Bernikova Mira Yurevna
  • Gopanchuk Vladimir Vasilevich
  • Korkunov Mikhail Viktorovich
RU2702709C1
MODULE WITH MULTICHANNEL PLASMA PROPULSION SYSTEM FOR SMALL SPACECRAFT 2020
  • Shumejko Andrej Ivanovich
RU2741401C1

RU 2 388 934 C2

Authors

Chernov Vladlen Aleksandrovich

Dates

2010-05-10Published

2008-07-11Filed