ELECTRIC ROCKET ENGINE INSTALLATION Russian patent published in 2003 - IPC

Abstract RU 2208702 C2

FIELD: space engineering. SUBSTANCE: invention relates to space propulsion systems, mainly to cruise electric rocket engine plants of space vehicles and complexes. In proposed electric rocket engine plant containing solar or nuclear power source, electric current converter, engine module and bus made of conducting material depending on working temperature and connecting output of electric power source with input of electric current converter, blacking coating is applied to outer surface of bus and each bus is made in form of electric conductor of rectangular section areas S, sq.m., of section being chosen from equation S = {N[ργp]1/2}/{U[T4fδd]1/2}, where , d = 0,6T4-0,8T3/α+0,8ToT3+0,2T4o

, ρ, (Ohm. m) is specific resistance of bus material; N (W) is electric power transmitted along heat radiating bus from electric power source to electric current converter; To(K) (K) is temperature of by bus t no current, T(K) is working temperature of bus; δ (kg/m3) kg/cu.m is density of bus material; α (K-1) is temperature coefficient of bus material electric resistance; γ (kg/Wt) (kg/W) is specific mass of electric power source, f≤1, is coefficient; V (V) is working voltage of electric power source. Ratio of thickness h to width b of bus outer surface is chosen from equation h/b = [A+(A2-S)1/2]2/S, where A=A = {N[δρd]1/2}/{4Uσε[fT4pγ]1/2}, σ, (Wt/m2K4)) is Stefan-Biltzmann constant, ε is emissivity factor of bus radiating surface. Aluminum or beryllium is used as material for bus operating at temperature from 300 K to 600 K, copper, molybdenum or niobium is used at temperatures from 600 K to 800 K, molybdenum is used at temperatures from 800 K to 1100 K and lithium filled niobium tube is used at temperatures from 1100 to 2000 K. Invention improves efficiency of electric rocket engine plants owing to optimization of energy transmission from power source to electric rocket engines along buses featuring enlarged range of working voltages and power transmission range. EFFECT: improved efficiency of electric rocket engine installations. 5 cl, 2 dwg

Similar patents RU2208702C2

Title Year Author Number
METHOD FOR OPERATING DUAL-PURPOSE SPACECRAFT NUCLEAR POWER PLANT WITH THERMIONIC CONVERTER REACTOR AND ADDITIONAL HEAT-TO-ELECTRICITY CONVERTER 2000
  • Sinjavskij V.V.
  • Juditskij V.D.
RU2173898C1
ELECTRIC ROCKET ENGINE PLANT AND METHOD OF ITS OPERATION 2005
  • Ostrovskij Valerij Georgievich
RU2308610C2
METHOD OF TESTING ELECTROMAGNETIC COMPATIBILITY OF ELECTRIC PROPULSION SYSTEM WITH INFORMATION ONBOARD SYSTEMS OF SPACE OBJECT, SYSTEM OF RECORDING AND PLAYBACK OF CHARACTERISTICS OF DISCHARGE CURRENT OF ELECTRIC PROPULSION ENGINES OF ELECTRIC PROPULSION SYSTEM FOR IMPLEMENTING SAID METHOD 2015
  • Pishchulin Vladimir Alekseevich
  • Ostrovskij Valerij Georgievich
RU2605277C2
METHOD FOR DETERMINING ELECTRIC STRENGTH OF COLLECTOR PACK IN THERMIONIC POWER-GENERATING ASSEMBLY 1998
  • Sinjavskij V.V.
RU2159480C2
SOLAR-TO-ELECTRIC ENERGY CONVERTER 1999
  • Grishin V.K.(Ru)
  • Vecher Alim Aleksandrovich
  • Sinjavskij V.V.(Ru)
RU2158048C1
MAGNETOPLASMADYNAMIC ENGINE AND METHOD OF ITS OPERATION 2007
  • Ostrovskij Valerij Georgievich
RU2351800C1
THERMIONIC CONVERTER REACTOR 2000
  • Sinjavskij V.V.
  • Juditskij V.D.
RU2172041C1
ELECTRIC ROCKET ENGINE (VERSIONS) AND METHOD OF OPERATION OF SUCH ENGINE 2005
  • Ostrovskij Valerij Georgievich
RU2309293C2
STACK-ARRANGEMENT THERMIONIC CONVERTER REACTOR 2000
  • Sinjavskij V.V.
  • Juditskij V.D.
RU2168794C1
ENGINE WITH CLOSED DRIFT OF ELECTRONS 2012
  • Shcherbina Pavel Aleksandrovich
  • Ostrovskij Valerij Georgievich
RU2524315C2

RU 2 208 702 C2

Authors

Onufriev V.V.

Sinjavskij V.V.

Dates

2003-07-20Published

2001-10-10Filed