1. A method comprising:
patterning a substrate with a plurality of chemically contrasted alignment features; and
depositing a block copolymer having a magnetic component and a non-magnetic component onto the substrate, the block copolymer self-assembling into a sequence of magnetic domains responsive to the alignment features, the period of the alignment features being between about 2 times and about 10 times the period of the magnetic domains.
2. The method of claim 1, wherein the patterning step comprises applying a polymer brush layer to the substrate, coating the brush layer with a photoresist layer and applying a lithographic process to form the plurality of chemically contrasted alignment features.
3. The method of claim 1, in which the magnetic domains are spherical.
4. The method of claim 1, in which the magnetic domains are characterized as cylinders.
5. The method of claim 1, in which the alignment features comprise a regular pattern in a data area and a non-regular pattern in a servo area.
6. The method of claim 1, in which the magnetic domains are formed by the magnetic component of the copolymer and the method further comprises subsequently removing the non-magnetic component of the copolymer.
7. The method of claim 1, wherein the alignment features are smaller than the magnetic domains.
8. A method comprising:
forming a photoresist layer on a disc-shaped rigid substrate having a polymer brush layer thereon;
using a lithographic process to form a first plurality alignment features in a servo Area and a second plurality of alignment features in a bit area of the photoresist layer; and
depositing a self-assembling copolymer material comprising a magnetic component and a non-magnetic component on at least a portion of the bit area, the position of curvilinearly shaped domains of the self-assembled material directed by the second plurality of alignment features to form a nanostructure pattern in the bit area having a period from two to ten times a period of the second plurality of alignment features, the curvilinearly shaped domains formed by the magnetic component of the copolymer material.
9. The method of claim 8, wherein the first plurality of alignment features define servo data to facilitate recording of data to the domains defined by the nanostructure pattern.
10. The method of claim 8, further comprising using the bit area to store data and the servo area to provide servo positioning information on a bit patterned medium (BPM) rotatable data recording disc in a data storage device.
11. The method of claim 8, further comprising using the bit area and the servo area as a template to form a population of nominally identical bit patterned medium (BPM) rotatable data recording discs.
12. The method of claim 8, wherein the brush layer has a thickness of from about 1 nanometer (nm) to about 10 nm and the photoresist layer has a thickness of from about 20 nm to about 50 nm.
13. The method of claim 8, further comprising removing the non-magnetic component of the self-assembling material.
14. The method of claim 8, wherein the curvilinearly shaped domains are spherical.
15. The method of claim 8, in which the curvilinearly shaped domains are characterized as cylinders.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A method of changing at least one of an inclination and an altitude of a first object including at least one of a space vehicle, satellite and rocket, using a computer implemented and assisted process, comprising the sequential or non-sequential steps of:
(a) generating a first transfer for convergence of first target variables at a first target including at least one of a first planet, first planet orbit and first location in space;
(b) traveling, by the first object, to a vicinity of the first target using the first transfer;
(c) rendezvousing, by the first object, with the first target where a second object including at least one of a second object, second planet, spaceship and comet, has undergone, is undergoing or will undergo a resonant hop or other resonance, said rendezvousing including substantially matching conditions of the second object including velocity;
(d) optionally performing an inclination change at the second object responsive to the second object undergoing the resonant hop or other resonance; and
(e) traveling from the second object to a third target including at least one of a third planet, third planet orbit and third location in space, at a predetermined arbitrary altitude and an optional inclination responsive to said rendezvousing step (c) and said optionally performing step (d).
2. A method according to claim 1, wherein at least one of said generating step (a), said rendezvousing step (c) and performing step (d) are dynamically generated in the first object.
3. A method according to claim 1, wherein at least one of said generating step (a), said rendezvousing step (c) and performing step (d) are dynamically generated in a central controller remote from the first object.
4. A method according to claim 1, wherein at least one of said generating step (a), said rendezvousing step (c) and performing step (d) are generated in the first object.
5. A method according to claim 1, wherein at least one of said generating step (a), said rendezvousing step (c) and performing step (d) are generated in a central controller remote from the first object.
6. A method according to claim 1, wherein said steps (a)-(e) are used in a navigational system to navigate the first object to rendezvous with the first target.
7. A computer program memory, storing computer instructions for changing at least one of an inclination and an altitude of a first object including at least one of a space vehicle, satellite and rocket, using a computer implemented and assisted process executing the computer instructions, the computer instructions and computer assisted process including the sequential or non-sequential functions of:
(a) generating, by the computer instructions, a first transfer for convergence of first target variables at a first target including at least one of a first planet, first planet orbit and first location in space;
(b) traveling, by the first object, to a vicinity of the first target using the first transfer;
(c) rendezvousing, by the first object, with the first target where a second object including at least one of a second object, second planet, spaceship and comet, has undergone, is undergoing or will undergo a resonant hop or other resonance, said rendezvousing including substantially matching conditions of the second object including velocity;
(d) optionally performing, by the computer instructions, an inclination change at the second object responsive to the second object undergoing the resonant hop or other resonance; and
(e) traveling from the second object to a third target including at least one of a third planet, third planet orbit and third location in space, at a predetermined arbitrary altitude and an optional inclination responsive to said rendezvousing step (c) and said optionally performing step (d).
8. A method of a first object including at least one of a space vehicle, satellite and rocket, rendezvousing with a second object including at least one of another object, another space vehicle, another satellite, another rocket, a planet, a planet orbit and a first location in space, using a computer implemented and assisted process, comprising the sequential or non-sequential steps of:
(a) generating a first transfer for convergence of first target variables substantially at the second object;
(b) traveling, by the first object, to a vicinity of the second object using the first transfer;
(c) rendezvousing and transferring, by the first object, with the second object which has undergone, is undergoing or will undergo a resonant hop or other resonance, said rendezvousing including substantially matching conditions of the second object including velocity and resonance, thereby facilitating the efficient use of at least one of fuel, energy and propellant.
9. A method according to claim 8, wherein said rendezvousing step (c) is performed by the first object at a weak stability boundary (WSB) of the second object.
10. A method according to claim 8, wherein said rendezvousing step (c) is performed by the first object at a weak stability boundary (WSB) of the second object comprising a larger planetary body or object than the first object.
11. A method according to claim 8, wherein said rendezvousing step (c) is performed by the first object at a weak stability boundary (WSB) of the second object comprising a larger planetary body or object than the first object, where the first object has a negligible gravitational effect on the second object.
12. A method of a second object ejecting from a first object including at least one of a planet, planetary orbit and first location in space, using a computer implemented and assisted process, comprising the sequential or non-sequential steps of:
(a) generating a first transfer for convergence of first target variables at the first object;
(b) traveling, by the second object, to a vicinity of the first object using the first transfer where the first object has undergone, is undergoing or will undergo a resonant hop or other resonance;
(c) increasing energy of the second object responsive to said traveling step (b) when the first object has undergone or is undergoing the resonant hop or the other resonance;
(d) ejecting, by the second object from the first object using the increased energy responsive to said increasing step (c), thereby facilitating the efficient use of at least one of fuel, energy and propellant of the second object.
13. A method according to claim 12, wherein said traveling step (b) is performed by the second object at a velocity such that the second object is in a weak stability boundary of the first object for ejection therefrom, while facilitating the efficient use of at least one of fuel, energy and propellant of the second object.
14. A method according to claim 12, wherein said traveling step (b) is performed by the second object at a hyperbolic excess velocity such that the second object is in a weak stability boundary of the first object for ejection therefrom, and the second object does not transition into a resonant ellipse.
15. A method according to claim 12, wherein said traveling step (b) is performed by the second object such that the second object settles into an orbit about the Sun reaching an apoapsis of an ellipse about the Sun, substantially at the end of said ejecting step (d).
16. A method according to claim 12, wherein said increasing step (c) increases at least one of the E3 and C3 energy of the second object.
17. A method of a second object being captured by a first object including at least one-of a planet, planetary orbit and first location in space, using a computer implemented and assisted process, comprising the sequential or non-sequential steps of:
(a) generating a first transfer for convergence of first target variables at the first object;
(b) traveling, by the second object, to a vicinity of the first object using the first transfer where the first object has undergone, is undergoing or will undergo a resonant hop or other resonance;
(c) decreasing energy of the second object responsive to said traveling step (b) when the first object has undergone or is undergoing the resonant hop or the other resonance;
(d) capturing, by the first object the second object via the decreased energy responsive to said decreasing step (c), thereby facilitating the efficient use of at least one of fuel, energy and propellant of the second object.
18. A method according to claim 17, wherein said traveling step (b) is performed by the second object at a velocity such that the second object is in a weak stability boundary of the first object for capture thereby, while facilitating the efficient use of at least one of fuel, energy and propellant of the second object.
19. A method according to claim 17, wherein said traveling step (b) is performed by the second object at a hyperbolic excess velocity such that the second object is in a weak stability boundary of the first object for capture thereby, and the second object does not transition into a resonant ellipse.
20. A method according to claim 17, wherein said decreasing step (c) decreases at least one of the E3 and C3 energy of the second object.
21. A method of placing a satellite into orbit around the earth and optionally changing at least one of an inclination and an altitude of the satellite, using a computer implemented process, comprising the sequential or non-sequential steps of:
(a) traveling, by the satellite, from the earth or the earth orbit to a weak lunar capture in the WSB or the WSB orbit at a first target including at least one of a first planet, first planet orbit and first location in space;
(b) traveling, by the satellite, to a vicinity of the first target;
(c) rendezvousing, by the satellite with the first target where the first target has undergone, is undergoing or will undergo a resonant hop or other resonance, said rendezvousing including substantially matching conditions of the first target by the satellite including velocity;
(d) optionally performing, by the satellite, at least one substantially negligible maneuver or maneuver, and optionally performing an inclination change at the WSB or the WSB orbit; and
(e) traveling, by the satellite, from the WSB or the WSB orbit to the earth or the earth orbit at a predetermined arbitrary altitude and optionally at the inclination change, responsive to said rendezvousing step (c) and said optionally performing step (d).
22. A method of a first object including at least one of a space vehicle, satellite and rocket, rendezvousing with a second object including at least one of another object, another space vehicle, another satellite, another rocket, a planet, a planet orbit and a first location in space, using a computer implemented and assisted process, comprising the sequential or non-sequential steps of:
(a) traveling, by the first object, to a vicinity of the second object; and
(b) rendezvousing and transferring, by the first object, with the second object which has undergone, is undergoing or will undergo a resonant hop or other resonance, said rendezvousing including substantially matching conditions of the second object including velocity and resonance, thereby facilitating the efficient use of at least one of fuel, energy and propellant.