Geoengineering - Climate Change Mitigation
Design Desk Inc.
The Lunar Orbit Stabilization System
The Lunar Orbit Stabilization System melts lunar surface regolith via Carbon Dioxide laser, to then act as an anchor then tethering a sealed force vectoring electric hyper jet that applies lift to the surface of the moon. The design then intended to arrest the moon's orbital escape. The design uses a fuel less electricity generator to power it's systems.
Parts List
1. motorized engine mounting "rotator ring"
2. engine mounting "hub" contains sealed bearing races and thru bore current (electrical)
transfer "slip ring - multi track
3. rotator "ring" inverse electric motor (the field coil rotates the armature is stationary)
4. transmitter communications "Bay" to "allow" for spherical transmission of communications
5. multi wire wire"bus" ribbon wire connector encased within insulates and hazard projectile shock casing
6. center mounting rotator post "horizontal plane full rotation 360 degrees
7. ribbon wire docking receptacle
8. ribbon wire - multi wire
9. carbon dioxide laser power unit - fuel less high voltage production Ac current (alternating current)
10. horizontal plane center post armature of the drive electric motor
11. center rotating post position indicator sensor - aids in flight control
12. navigation / communications / electricity generator / engine control and thermal heating central core
13. center post disk break
14. center post disk break calipers (hydraulic pressure system actuated by electric solenoid)
15. high voltage generator "bay" contains https://www.designdeskinc.com/cross-pump-generator.html within
a noble gas pressurized chamber using argon or other suitable inert Noble Gas (non electrically conductive with
plasma box static electricity dissipation to control unwanted electrical inductance) - feeds craft's
system electricity
16. electric wench and heated carbon fiber insulated "rope" high tensile strength"
17. heater insulated carbon fiber "rope"
18. "rope" guide hoop
19. proximity sensor (radio) and primary melt bore to anchor the auger - spectrometer mass analyzer
20. shock casing shielded laser electronics and instrumentation for the radio proximity sensor
21. electric motorizes servo hinge
22. robotic clasp electric actuation (additional latch hoop upon the clasp fingers)
23. hydraulic piston upon the robotic "arm"
24. electric hinge servo
25. robotic arm hydraulic piston extender
26. 360 degree electric servo motor of the robotic arm
27. carbon dioxide laser servo "hinge" - electric motor with position sensor to then tilt the laser to cause the
melt anchor circle of lunar Regolith
28. carbon dioxide laser (5000 degrees Celsius capacity)
29. carbon dioxide rotation track assembly - the laser is power motivated about 360 degrees about the
horizontal plane to then melt the lunar Regolith in a disk shape to anchor the flight system
30. laser travel "track" thru bore current transfer slip ring
31. valve control solenoid
32. divergence valve changes the inert Noble Gas (Argon) flow direction
33. pneumatic perpendicular noble gas flow "coil" pipe
34. top assembly noble gas flow manifold
35. engine lamp system marker lamps and lamp electronics
36. top assembly noble gas flow manifold
37. noble gas impeller circumference electric motor
38. pressurized hydraulic draft accelerator speed incline system with hydraulic oil pressure ratio gear set
counter tilt tandem rotating the the out put rotation of the units intern brush less electric drive motor that
is the input rotation to the units 1:20 ratio gear set - internal hall effect r.p.m. (revolutions per minute)
sensor reports to logic mapping circuits
39. high speed noble gas compressor propeller circumference brush less electricity generator voltage
regulation in the engine control unit within number 12 - feeds electricity to the hyper jet electric
circumference motors number 44
40. noble gas one way gas fill valve with pressure sensor ( reports to logic mapping system control electronics),
and noble gas control unit...that "de-energizes" / controls unwanted electrical inductance. ie... controls static
electricity within the noble gas flow
41. electric noble gas "pressure sensor" information to the engine control logic electronic circuits
42. primary "return" noble gas flow pipe - perpendicular "return" off sets the force "static" in the force
equation producing usable "sealed" direction thrust
43. noble gas collection "feed chamber" - feeds gas to the primary electric compound hyper sealed flow
electric jet engine containing numbers 44, 46, and 48
44. high speed noble gas transonic compressor propeller and brush less circumference electric motor
45. hall effect r.p.m. (revolutions per minute) sensor
46. pressurized hydraulic draft accelerator speed incline system with hydraulic oil pressure ratio gear set
counter tilt tandem rotating the the out put rotation of the units intern brush less electric drive motor that
is the input rotation to the units 1:20 ratio gear set - internal hall effect r.p.m. (revolutions per minute)
sensor reports to logic mapping circuits. Letter "A" internal jet fan compressor speed up upon their inert
Noble gas displacement to the remain in the engines operating service parameter.
47. main electric jet venturi decompression noble gas flow pipe - a venturi safety system to keep
the venturi at correct operating pressure levels
48. noble gas impeller and electrical "generator" about the noble gas flow impeller circumference
49. noble gas compression venturi "funnel"
50. venturi safety valve - a dampener valve coil spring with electric solenoid force opening position should
the p.s.i. (pounds per square inch) become excessive - the dampener valve contains an electric p.s.i. sensor
reporting to the mapping logic electronic circuits
51. venturi "throttle" valve control unit
52. shutter valve / throttle valve adjustable noble gas flow
53. primary noble gas "return coil" flow pipe
54. primary noble gas "return coil" flow pipe
55. noble gas flow pipe feeds "pressure" to the vacuum electric that produces negative pressure in
the engine system
56. vacuum electric jet impeller circumference electric brush less electric motor
57. vacuum electric jet hall effect r.p.m. sensor - reports to the units logic mapping control electronic circuits
58. 1:10 ratio gear set high side tandem rotating with the vacuum jets "noble gas compressor number 60
59. thru bore electricity transfer slip ring
60. vacuum jet high speed "noble gas flow compressor"
61. union bolt plate - sum of 24 about 360 degrees equal spacing
62. noble gas return manifold
63. circumference "electrical" current "pick up" voltage regulation in the engine control unit within number 12 - feeds
electricity to the hyper jet electric circumference motors number 44
64. main generator bay contains https://www.designdeskinc.com/cross-pump-generator.html
65. robotic "arm control bay"
66. carbon fiber "rope" anchor auger
67. vacuum electric jet same components and alignment mirror line to cause negative pressure post main venturi
68. top electric jet intake manifold
69. deep bore lander transmitter / receiver antenna
70. communications electronics
71. motorized engine "hinge"
72. electric hyper jet assemble same as letter labeled as letter "A"
73. landing gear hydraulic systems
74. laser control systems
75. craft generator bay "sealed chamber https://www.designdeskinc.com/cross-pump-generator.html
76. landing gear "bay"
77. insulated laser guide chamber
78. marker / work lamp
79. thrust / pressure port
80. main carbon dioxide laser
81. surface proximity sensor
82. landing gear
83. landing "foot"
Letter "A" = sealed force vector electric hyper jet
Letter "B" = hub rotator electric positioning system (servo) contains position sensor to assist navigation
Letter "C" = deep bore lander - melts angled bore in Regolith to assist in anchoring the Regolith anchor disk
Description
The flight system will melt a bore into the Regolith to then "sink" the auger and let the bore cool... then the main carbon dioxide laser, number 28 will melt the Regolith in a circular format to produce a homogeneous "disk" to act as the lift system anchor. The unit labeled letter "C" then landing upon the disk to deep bore melt angled retainers to increase the disk stability. The six engine lift craft will then ascend to zero gravity with the anchor tethered and apply the thrust required to in time stabilize the moon's escape. Multiple craft required to obtain the objective.
The total system is then of multitude of craft about the total circumference of the moon as per required to then stabilize the moon's escape. The system makes a circular melt by carbon dioxide laser to a depth of 12" - 18" with the circular disk then 18' to 36' diameter circle with letter "C" then landing atop the melt circle to produce an anchor lock / deep melt angular shape. The tether then 50 miles with twice the rated max tensile strength rated for the low temperature of outer space. It may not be required to full extend the tether but the length required to then be able to be used in other application such as neo / asteroid mitigation.
This design system is required due to the moon escaping it's Earth locked orbit factoring the effects of orbital elongation (perigee, apogee, Apsis) over long time spans... factoring equatorial atmospheric altitude increase due to global warming , earth spin rate, Earth and lunar gravity factoring type of atmospheric gas (water vapor Ch4 methane , CO2) and the projected trends due to infrastructure and population.
The lunar "escape" ( temporal "procession"), "perigee" then causes a closer proximity to Earth's high altitude atmosphere. Global warming then adding mass to the high altitude atmosphere due to increased water uptake causing a center point offset gravity increase. It's slight but occurring. The moon's orbit is elliptical not circular. Factoring the off set Earth center of gravity due to increased cloud water vapor formation due to climate change also changes the Earth's gravimetric center point.
The Apsis in the escape trajectory causing closer proximity to the earth in its orbital cycle. Gravity "changes with density" or loss there of.... Is Earth bleeding Ozone into outer space due to heating and lunar orbit effecting the equatorial Ozone layer?... lowering the altitude at it's poles? The moon's escape is slow... effecting Earth's climate slightly... an "aspect" of Climate Change factoring sea level rise and the fluid nature of atmosphere (tides in the skies). Granted the approximate one and one half inch per year is a small distance but the rate of orbital deformation can change with other advent such as lunar asteroid / comet impact. The design can be modified with electromagnetic field "bearings" in lieu of standard sealed bearings for long running.
The multitude of craft then of light weight low cost construction using a blend cold temperature plastic carbon graphite and non metal electrical conductive in lieu of motor wire, to lessen the cost. The components then derived from systems such as
https://www.designdeskinc.com/solar-assist-carbon-dioxide-sequestration-system.html
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Disclaimer - If attempting to produce these design yourself additional engineering may be required.. Design Desk Inc. will not be held liable. If you proceed with construction your self it's at your own risk... by use of "free to use systems" you acknowledge and accept the terms.. ( Please note not all systems contained here in have been released ).
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