This paper presents a few alternative, still ballistic, realization of short-period and highly inclined orbits by utilizing Venus and Earth swing-bys. This paper presents therefore different new approaches. The use of VEGA (Venus-Earth Gravity Assist) strategy lowers the departure escape velocity from Earth. The initial escape v-infmity velocity is only 4.2 km/sec and the strategy enables 37 degrees inclination with respect to the ecliptic plane. At the same time, the paper presents also a derivative strategy, co-use of Delta-VEGA (Delta-V Earth Gravity Assist) strategy for shorter realization. The results are amazing and significantly relaxes the propulsion requirement enhancing the payload mass in comparison with what was shown last year.