FIELD: space engineering. SUBSTANCE: thrust of the engine is a function of voltage and current of the anode proportional to the flow rate of the working fluid. The thrust is stabilized so that the product of the anode voltage and square of anode current is constant. The device has one stabilizing circuit only. The circuit consists of current and voltage pickups, two signal amplifiers, one of which is square-law amplifier, multiplier, comparator, source of reference voltage, and controller of supplying working fluid. The reference voltage is proportional to the square of the nominal thrust of the engine. EFFECT: improved accuracy of thrust stabilizing and simplified engine control. 3 cl, 1 dwg
Title | Year | Author | Number |
---|---|---|---|
METHOD OF AND DEVICE FOR REGULATION OF THRUST OF ELECTRIC ROCKET PLASMA ENGINE | 2001 |
|
RU2206787C2 |
METHOD OF AND DEVICE FOR ELECTRIC SUPPLY OF ELECTRIC PLASMA- JET ROCKER ENGINE | 2001 |
|
RU2220322C2 |
METHOD OF STABILIZATION OF TRACTION FOR ELECTROJET PLASMIC ENGINES AND DEVICE FOR IMPLEMENTATION OF THIS METHOD | 2006 |
|
RU2324841C1 |
METHOD OF CONTROLLING ELECTRIC-JET PLASMA ENGINE ANODE CURRENT AND DEVICE TO THIS EFFECT | 2006 |
|
RU2339846C2 |
SIMULATOR OF ELECTRIC ROCKET PLASMA PROPULSION PLANT | 2009 |
|
RU2395716C1 |
METHOD OF CONTROL OF POWER OF SPACECRAFT POWER PLANT AND DEVICE FOR REALIZATION OF THIS METHOD | 2003 |
|
RU2249546C2 |
DYNAMIC SIMULATOR OF STATIONARY PLASMA ENGINES | 2015 |
|
RU2610623C1 |
METHOD FOR TIGHTNESS DETECTION OF SYSTEM FOR WORKING FLUID SUPPLY TO SOURCE OF PLASMA, PREFERABLY UNDER VACUUM CONDITIONS | 2008 |
|
RU2377522C1 |
METHOD FOR DEFINITION OF FLOW RATE OF SYSTEM FOR SUPPLY OF WORKING MEDIUM TO PLASMA SOURCE | 2008 |
|
RU2392589C2 |
METHOD OF LAUNCH AND POWER SUPPLY OF ELECTROJET PLASMA ENGINE (VERSIONS) AND DEVICE FOR ITS IMPLEMENTATION (VERSIONS) | 2008 |
|
RU2366123C1 |
Authors
Dates
1995-09-27—Published
1993-07-13—Filed