152
A. V. Bogatiy et al.
Fig. 11.6 Calculated
dependence of APPT-based
CEPS total mass on the
discharge energy [18]
Fig. 11.7 APPT-based
CEPS thrust cost as a
function of discharge energy
[18]
a new APPT-350 thruster, the discharge energy was reduced compared with APPT155 and APPT-95 thrusters, down to 50 J, which allowed to reduce the total mass of
the electric propulsion system with a propellant store down to 8 kg. The calculated
characteristics of APPT-350 EPS are given in Table 11.4.
11.7 Conclusions
In this chapter, the current state of work on flight models of pulsed plasma propulsion
systems is considered. It is shown that the primary application area for propulsion
systems based on an ablative pulsed plasma thruster is the station-keeping of small
A. V. Bogatiy et al.
Fig. 11.6 Calculated
dependence of APPT-based
CEPS total mass on the
discharge energy [18]
Fig. 11.7 APPT-based
CEPS thrust cost as a
function of discharge energy
[18]
a new APPT-350 thruster, the discharge energy was reduced compared with APPT155 and APPT-95 thrusters, down to 50 J, which allowed to reduce the total mass of
the electric propulsion system with a propellant store down to 8 kg. The calculated
characteristics of APPT-350 EPS are given in Table 11.4.
11.7 Conclusions
In this chapter, the current state of work on flight models of pulsed plasma propulsion
systems is considered. It is shown that the primary application area for propulsion
systems based on an ablative pulsed plasma thruster is the station-keeping of small