Electric Thrusters for Transportation Electric Propulsion System of the Nuclear Powered Spacecraft
- Paper number
IAC-04-R.3.07
- Author
Mr. V.N. Akimov, Keldysh Research Center, Russia
- Year
2004
- Abstract
Complication and growth of number of the tasks which are carried out by satellites, increase in their active existence duration, as well as extension of near-earth space pollutions give rise to situation when it is necessary to execute maneuver for performing the satellite functions, for example, with the purpose of reduction of probability of collision with other space object or maintenance of coordinated movement in the group of satellites. Significant number of scientific papers is devoted to optimization of maneuvering of space vehicles (SV) with engines of low tractive force of a constant value; and majority of such papers includes an assumption of the central gravitational field and absence of aerodynamic resistance. Investigations of maneuvers of inter-orbital transitions, maintenance of average height of an orbit, its eccentricity and other parameters correction were carried out. For an evasion maneuver during one revolution, dependence of distance at the predicted moment of time between SV and the center of a dangerous zone from the radial acceleration’s value created by thruster, eccentricity of an origin orbit and true anomaly of the maneuver’s start, is obtained. For reduction of a number of the thruster switching, correction of SV-position on an orbit is desirable to conduct so that orbital period, eccentricity and argument of a pericenter remain constant after the end of maneuver. Small acceleration of radial direction created by thruster (up to 5 % of gravitational one) as a first approximation does not change focal parameter of an orbit, but for maintenance of its form, directions of an apses axis and an orbital period, it is necessary to provide for eccentricity constancy and argument of a pericenter. The report offers the calculation algorithm of the program of maneuver for correction of the satellite position in an orbit in the range of heights 600 – 2500 km. The thruster creates constant, by value, acceleration of a radial direction on the boost path. The mathematical model of SV-movement takes into account non-central gravitational field of the Earth and resistance of the atmosphere. An orbital period, eccentricity and argument of a pericenter remain constant with specified accuracy after the maneuver end. The obtained results can be used for making a decision to choose the method of maneuvering with the purpose of correction of SV-position in an orbit.
- Abstract document
- Manuscript document
IAC-04-R.3.07.pdf (🔒 authorized access only).
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