Patent ID: 7747361

Claim:
A method for injecting a plurality of spacecraft escaping from a gravitational sphere of the earth, into at least two different interplanetary orbits in a single launch and then loosing said plurality of spacecraft toward respective, different targets, comprising the steps of: injecting said plurality of spacecraft into an interplanetary orbit in a state of being coupled to a single assist module for assisting a space flight thereof, wherein said interplanetary orbit has a periodicity of six months, one year, or an integer number of years synchronous with the earth's revolution period or has a period having a rational or irrational number ratio with respect to the earth's revolution period; making a thrust-powered initial orbital correction to the assist module of about several m/sec in a sequential order with respect to each of said plurality of spacecraft, to control the closest-approach point relative to the earth for each of the spacecraft in conformity to a target orbit for each of the spacecraft, to drastically change a subsequent escape path for each of the spacecraft during said initial orbital correction, beginning a half month to several days before the closest-approach; and after making said orbital correction, loosing each of said spacecraft from said assist module in a sequential order toward respective, different targets.