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 at earth or earth orbit to arrive at a weak stability boundary (WSB) or WSB orbit at or near the moon or moon orbit and generating a second Hohmann transfer for the object emanating at the WSB or the WSB orbit to return to the earth or the earth orbit, 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 earth or the earth orbit from the WSB or the WSB orbit;
• and
• (c) navigating the object from a first altitude relative to the earth or the earth orbit to a weak lunar 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 earth or the earth orbit 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 at earth or earth orbit to arrive at a weak stability boundary (WSB) or WSB orbit at or near the moon or moon orbit and generating a second Hohmann transfer for the object emanating at the WSB or the WSB orbit to return to the earth or the earth orbit 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 earth or the earth orbit to a weak lunar capture in the WSB or the WSB orbit;
• (c) generating the second Hohmann transfer for convergence of second target variables at the earth or the earth orbit 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 earth or the earth orbit 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 the earth or the earth orbit to a weak lunar 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 earth or the earth orbit 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 the earth or the earth orbit to a first periapsis at a weak lunar capture in a weak stability boundary (WSB) or WSB orbit using a first Hohmann transfer;
• (b) maneuvering around the moon 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 earth or the earth orbit 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 the moon or the moon orbit to a weak lunar 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 moon or the moon orbit 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 a first planet or first planet orbit to a weak lunar 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 and a second planet and a second planet orbit 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 earth or earth orbit to arrive at the moon or moon orbit 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 earth or the earth orbit to the moon or the moon orbit.

A method of generating a transfer for an object emanating substantially at a first heavenly object or first heavenly object orbit to arrive at a second heavenly object or second heavenly object orbit, 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 second heavenly object or the second heavenly object orbit from the first heavenly object or the first heavenly object orbit;
• and
• (c) iterating step (b) until sufficient convergence to obtain the transfer from the first heavenly object or the first heavenly object orbit to the second heavenly object or the second heavenly object orbit.