Application of Stationary Plasma Thrusters for the Multispacecraft Constellation Maintenance
- Paper number
IAC-05-C4.4.03
- Author
Dr. Vladimir Obukhov, RIAME MAI, Russia
- Year
2005
- Abstract
APPLICATION OF STATIONARY PLASMA THRUSTERS FOR THE MULTISPACECRAFT CONSTELLATION MAINTENANCE M.S. Konstantinov*, V.G. Petukhov*, V.A. Obukhov*, G.A. Popov*, G.G. Tchernobelskiy** *RIAME MAI, Leningradskoye shosse, 5, Moscow, 125080, P/O box 43. RUSSIA ** “Kometa” Central Research Institute, Velozavodskaya str., 5, Moscow, RUSSIA . Potentialities are studied to use stationary plasma thrusters (SPT) for providing orbit correction for a multispacecraft constellation in high elliptic orbits (HEO). Principles are discussed, which may be used as a basis for the correction of disturbances for an orbital constellation (OC) using thrusters, electric propulsions (EP) being such in general, and SPT in particular. Estimate is made as an example for the characteristic velocity required for the station-keeping of any spacecraft (S/C) of the given OC, when thrusters of SPT-100 (with the thrust of 80 mN) and SPT-140 (with the thrust of 250 mN) types are used. Requirements to the OC configuration keeping are reduced to maintaining three angular values within the given ranges for each spacecraft. SPT ignitions at the apogee, perigee and ascending node of the orbit are the control actions for solving the problem stated. It is assumed that SPT will secure circumferential acceleration or braking in the vicinity of perigee or apogee of the arbitrary orbit and binormal thrust direction (both positive, and negative) in the vicinity of the ascending node of the orbit. S/C with orbital orientation and two pairs of SPT may be considered as one of the possible arrangement options. Thrust vectors of the first pair of thrusters are oriented along the positive and negative transversals. Thrust vectors of the second pair are oriented along the normal to the orbital plane, in the opposite directions also. Electric propulsions of the first pair are used for the acceleration and braking maneuvers, and electric propulsions of the second pair – for changing the S/C orbital plane orientation. Mathematical models of controllers with the feedback in the deviation from the nominal value of controlled parameter and in the rate of controlled parameter change are used for defining the value and direction of control thrust pulses. The desired S/C velocity increments in the apogee, perigee and ascending node are calculated on the basis of the mathematical models for controllers. Duration of SPT operation at these points and values of S/C true anomaly in each point of SPT ignition and shutdown are calculated on the basis of the obtained values for characteristic velocity. It is shown by calculations that with the use of SPT-100 and SPT-140, the required characteristic velocity increases a little bit only comparing to the idealized conic-patched maneuvers. At that, SPT propellant mass, required for the OC maintenance during 7 years, appears to be considerably less than with the use of chemical engines. The required lifetime and number of operations assessed by calculation are secured in the modern SPT models. This allows stating that SPT use for the OC station-keeping in HEO is possible and efficient. Contacting author: Dr. Vladimir A. Obukhov, RIAME, e-mail: riame@sokol.ru RIAME MAI, 5 Leningradskoye shosse, Moscow, 125080, P/O box 43 Fax: +7 (095) 158-0367
- Abstract document
- Manuscript document
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