Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same

A navigational system for changing at least one of an inclination and an altitude of an object including at least one of a space vehicle, satellite and rocket by generating a first Hohmann transfer for the object emanating substantially from at least one of earth, earth orbit and a first heavenly location to arrive at a weak stability boundary (WSB) or WSB orbit at or near at least one of the moon, moon orbit and a second heavenly location and generating a second Hohmann transfer for the object emanating at the WSB or the WSB orbit to at least one of the earth, the earth orbit, first heavenly location and a third heavenly location, using a computer, wherein the computer implements the sequential or non-sequential functions of:

• (a) generating the first Hohmann transfer for convergence of first target variables at the WSB or the WSB orbit;
• (b) generating the second Hohmann transfer for convergence of second target variables at the at least one of the earth, the earth orbit, the first heavenly location and the third heavenly location from the WSB or the WSB orbit;
• and
• (c) navigating the object from a first altitude relative to the at least one of earth, the earth orbit and the first heavenly location to a weak capture in the WSB or the WSB orbit using the first Hohmann transfer, and navigating the object from the WSB or the WSB orbit to the at least one of the earth, the earth orbit, the first heavenly location and the third heavenly location at a predetermined arbitrary altitude different from said first altitude using the second Hohmann transfer;
• and
• wherein said first and said second transfers are generated using a forward targeting method.

A computer program memory, storing computer instructions for changing at least one of an inclination and an altitude of an object by generating a first Hohmann transfer for the object emanating substantially from at least one of earth, earth orbit and a first heavenly location to arrive at a weak stability boundary (WSB) or WSB orbit at or near at least one of moon, moon orbit and a second heavenly location and generating a second Hohmann transfer for the object emanating at the WSB or the WSB orbit to return to at least one of the earth, the earth orbit, the first heavenly location and a third heavenly location_using a computer, the computer instructions including:

• (a) generating the first Hohmann transfer for convergence of first target variables at the WSB or the WSB orbit;
• (b) iterating step (a) until sufficient convergence to obtain the first Hohmann transfer from a first altitude relative to the at least one of the earth, the earth orbit and a first heavenly location to a weak capture in the WSB or the WSB orbit;
• (c) generating the second Hohmann transfer for convergence of second target variables at the at least one of the earth, the earth orbit, the first heavenly location and the third heavenly location from the WSB or the WSB orbit;
• and
• (d) iterating step (c) until sufficient convergence to obtain the second Hohmann transfer from the WSB or the WSB orbit to the at least one of the earth, the earth orbit, the first heavenly location and the third heavenly location for changing the at least one of the inclination and the first altitude;
• and
• wherein said first and said second transfers are generated using a forward targeting method.

A method of changing at least one of an inclination and an altitude of an object including at least one of a space vehicle, satellite and rocket, using a computer implemented process, comprising the sequential or non-sequential steps of:

• (a) traveling from a first altitude relative to at least one of the earth, the earth orbit, and a first heavenly location to a weak capture in a weak stability boundary (WSB) or WSB orbit using a first Hohmann transfer;
• (b) performing at least one of a maneuver and a negligible maneuver, and optionally performing an inclination change at the WSB or the WSB orbit;
• and
• (c) traveling from the WSB or the WSB orbit to the at least one of the earth, the earth orbit, the first heavenly location and a third heavenly location at a predetermined arbitrary altitude different from said first altitude and optionally at the inclination change using a second Hohmann transfer;
• and
• wherein said first and said second transfers are generated using a forward targeting method.

A method of changing at least one of an inclination and an altitude of an object including at least one of a space vehicle, satellite and rocket, using a computer implemented process, comprising the sequential or non-sequential steps of:

• (a) traveling from a first altitude relative to at least one of the earth, the earth orbit and a first heavenly location to a first periapsis at a weak capture in a weak stability boundary (WSB) or WSB orbit using a first Hohmann transfer;
• (b) maneuvering by performing a first negligible maneuver at the WSB or the WSB orbit;
• (c) optionally performing an inclination change at the WSB or the WSB orbit;
• (d) ejecting from the WSB or the WSB orbit by performing a second negligible maneuver;
• and
• (e) traveling from the WSB or the WSB orbit to a second periapsis at the at least one of the earth, the earth orbit, the first heavenly location and a third heavenly location at a predetermined arbitrary altitude different from said first altitude and optionally at the inclination change using a second Hohmann transfer;
• and
• wherein said first and said second transfers are generated using a forward targeting method.

A method of changing at least one of an inclination and an initial altitude of an object including at least one of a space vehicle, satellite and rocket, using a computer implemented process, comprising the sequential or non-sequential steps of:

• (a) traveling from at least one of the moon, the moon orbit and a first heavenly location to a weak capture in a weak stability boundary (WSB) or WSB orbit using a first Hohmann transfer;
• (b) performing at least one of a maneuver and a negligible maneuver, and optionally performing an inclination change at the WSB or the WSB orbit;
• and
• (c) traveling from the WSB or the WSB orbit to the at least one of the moon, the moon orbit, the first heavenly location and a third heavenly location at a predetermined arbitrary altitude different from said initial altitude and optionally at the inclination change using a second Hohmann transfer;
• and
• wherein said first and said second transfers are generated using a forward targeting method.

A method of changing at least one of an inclination and an altitude of an object including at least one of a space vehicle, satellite and rocket, using a computer implemented process, comprising the sequential or non-sequential steps of:

• (a) traveling from a first altitude relative to at least one of a first planet, first planet orbit and a first heavenly location to a weak capture in a weak stability boundary (WSB) or WSB orbit using a first Hohmann transfer;
• (b) performing at least one of a maneuver and a negligible maneuver, and optionally performing an inclination change at the WSB or the WSB orbit;
• and
• (c) traveling from the WSB or the WSB orbit to at least one of the first planet or the first planet orbit, the first heavenly location and a second heavenly location at a predetermined arbitrary altitude different from said first altitude and optionally at the inclination change using a second Hohmann transfer;
• and
• wherein said first and said second transfers are generated using a forward targeting method.

A method of generating a transfer for an object emanating substantially at at least one of earth, earth orbit and a first heavenly location to arrive at at least one of the moon, moon orbit and a second heavenly location using a computer implemented process, comprising the steps of:

• (a) entering parameters for said method of generating the transfer;
• (b) implementing at least one of a forward targeting process and a forward transfer process by varying the parameters for convergence of target variables at the moon;
• and
• (c) iterating step (b) until sufficient convergence to obtain the transfer from the at least one of earth, the earth orbit and the first heavenly location to the at least one of the moon, the moon orbit and the second heavenly location.

A method of generating a transfer for an object emanating substantially at at least one of a first heavenly object, first heavenly object orbit and a first heavenly location to arrive at at least one of a second heavenly object, second heavenly object orbit and a second heavenly location, comprising the sequential, non-sequential or sequence independent steps of:

• (a) entering parameters for said method of generating the transfer;
• (b) implementing at least one of a forward targeting process and a forward transfer process by varying the parameters for convergence of target variables at the at least one of the second heavenly object, the second heavenly object orbit_and the second heavenly location from the first heavenly object, the first heavenly object orbit and the first heavenly location;
• and
• (c) iterating step (b) until sufficient convergence to obtain the transfer from the at least one of the first heavenly object, the first heavenly object orbit and the first heavenly location to the at least one of the second heavenly object, the second heavenly object orbit and the second heavenly location.