Solar Radiation Diffuser Satellite (A "Global Warming" correction tool)

After the information accessed regarding high energy Gamma Ray burst, Solar Flare and C.M.E. ( Coronal Mass Ejection), we have determined that solar shielding satellites would be a wise investment. The Gamma Ray burst occur from exploding stars and travel at great rate and speed through space. The design will use the C.M.E. itself to direct the flow of the C.M. E. by force vectoring the solar flare through it's system then aligned with number 3 toward the C.M.E. channeling it through the particle accelerator to then discharge the mass at greater rate re-directing the Earth impaling vector.

The System then will act as an electric parasol (umbrella) to shade the entire planet dropping the total solar gain down to compensate for industrial pollution "falling out" ie... compensates for the "solar dimming effect" due to pollution. Particulate, air pollution, "falling out" of the atmosphere, when converting to clean energy systems, causes solar watt per square meter thermal gain. This satellite design prevents "thermal incline run away effect" due to solar watt per square meter increase. The design will also reduce hurricanes formation. The design is scalable to allowing for multiple craft within a stipulated financial budget.

A transmitter produces an electromagnetic wave that can "carry" a particle... electrons have mass... mass cast a shadow.. a transmitter is an electromagnetic wave producing emitter so by causing a tuned amplitude and frequency interference pattern transmitter "wave" carrying electrons may be able to "de-fract / reflect" sunlight by the satellite's transmitter cone. The system then casting a shadow as large as the earth like a giant umbrella. The design should be able to effectively reduce the solar gain ( watt per square meter) allowing the planets ice caps to self repair....

The actual Gamma ray burst wave is difficult if not impossible to counteract as the incoming vector direction then would require a predetermination and communications to activate protections systems at faster than light speed communication and we are not there yet... so the best thing to do, as a start, is to then deal with the reactivity there after then shielding the planet from the Sun itself as Gamma rays burst waves destroy the upper atmosphere and cause the destruction of the Ozone layer then yielding to much radiation permeating to the earth's surface. The plant life will be effected post Gamma Ray burst wave. Inclined solar radiation would kill most / all plant life in in a matter of weeks and animal life would follow shortly there after. We can address this in a very careful fashion. It requires attention !!!

Following please find a Solar Radiation Diffuser Satellite design system that will contain the hover motors listed at http://www.designdeskinc.com/hover-motor.html with in the spherical positional flight balls along with the Static Compressor engines listed at http://www.designdeskinc.com/static-compressor.html.

The design system then will have the required lift capacity to break Earth's gravity on a fuel less engine system platform.

Electrical power production systems then redundant as well... as are the atmospheric recycling systems within the habitat unit. Design systems listed upon http://www.designdeskinc.com/portfolio.html .

The system allows for gravity spin to cause similar conditions to the ground for elongated habitations with minimal medical atrophy. The habitation also contains a grow room for food production.

The design system may also buy time regarding Global Warming as a direct result of Carbon Dioxide then by reducing the total radiation gain...

*Note - global dimming ! (produced from atmospheric particulate) is then reduced when switching off of fossil fuels.... the incline / effect (warming) , is greater than the world has prepared for... avoid a run away effect with this system applied!

The perma frost locks methane... and increased warming causes a greater atmospheric methane level and rate incline. This yields a rise in ocean temperature. The thermo-haline oceanic currents might alter flow then may warm at greater depth in zones containing methane hydrate (methane ice) and cause inclined release of the methane gas into the atmosphere. The increased addition of temperature and "carbon"

( CO2 - carbon dioxide, and CH4- methane), then effects the acidity level in the oceans, oceanic

Anoxia (oceanic anoxic) would cause the life structure to fail.. it must be avoided.

Within the short time frame where CH4 ( Methane Hydrate) could be released the equatorial stratospheric O3 ( ozone) radiation shielding will then caused the upper atmosphere to gain altitude due to heating and with the feedback "loop" might cause gas gloss also factoring light "lens effect" ( the curvature changes with temperature and atmospheric shape also effected by the rotation of the Earth. The curvature of the earth ( factoring albedo effect) effects the feedback loop in thermal gain. The incline in heating the stratosphere causing gas loss of O3 to outer space will effect the radiation shielding. This must be avoided!!!!

**Additionally, artificial cooling of the Tundra may be required to lock the Methane! By using the following cooling system it may be attained cost effective http://www.designdeskinc.com/storm-protection-balloon.html

Redundancy within the implementation is suggested should component failure occur...

ie... the minimal Sum of 4 "Diffuser " devices. If intending to mitigate gamma ray burst total earth coverage would then be spherical coverage with multitude of craft active 24/7/365.25 days per year incident cone transmission directed not inadvertently effect the asteroid belt.

In the design depicted above there are multiple functionalities. The design can be used for asteroid / comet impact mitigation with the use of multiple craft then using a carbon graphite weave netting ( like a spider's web) with the devices around the circumference.

In addition the design system correctly insulated for radiation exposure ( within number 28 ) is then able to lens solar radiation post result of a Gamma Ray burst ( think particle billiards balls , cone vectored toward the sun)

The electrical inductance cages then surround critical electronics and act as a shield to control electrical charge inductance (conversion of electromagnetism to electricity) to shield the insulated wiring connected to critical systems control circuits.

*Note - The emitter "head" (number 35) also exist in the vector ports about 360 degree polar array venting thru number 37 with a four "bank" system, ie... each of four systems the use 90 degrees about the circumference of the design system. The vector discharge "incident cone" then to be balanced and focused by the lens magnetics , focusing electromagnets), number 20. The intake assembly , number 36, is also then in the same fashion... arrayed at the intake in line with 37, multiple times about 360 degrees. There also exist an re-route system for the particle accelerator' intake should a single particle accelerator fail. The re-route then allows the intake flow system post compression venturi , number 36 to be fed to adjacent particle accelerators to keep the incident cone continuity intact.

Number 17's internal flow cycle then at velocity closed mass in velocity, prior to flare pumping function, then will also be heated also allowing injection of on board chilled (by temperature of outer space) inert noble gas to "regulate" the internal workings of the particle accelerator to "maintain" function within operating service parameters. The "banks" of the particle accelerators will also have the ability to cool the flow by the ambient temperature of outer space dropping the vectoring discharge temperature from the cold side of the craft. The cooling "manifold" is then the cold inert Noble gas injection point located within / upon number 30.

The flight craft is also designed to mitigate C.M.E. (Coronal Mass Ejection...) by then matching the pressure of exhaust.... exceeding the C.M.E. "pressure" and aligning the "wave guide" number 22 toward

the C.M.E. , to then produce a "deflection cone" (think pressure plus increased velocity of emission of the incident cone).

Number 36 then being used as an intake for the particle accelerator for particle density... increased magnetism will occur when this is occurring.... inductance producing electricity will require dissipation systems to safely manage the electrical gain from traversing magnetic fields. The C.M.E. then used to force deflect itself by directing the force of the solar pressure discharge away from an impaling trajectory with the Earth by correct alignment of the flight system.

It is critical to understand the alignment positions of the design ...they differ with function.

The "flight ring" does allow for detachable balls (sum of two) for escape from the ring itself...

Growing algae to produce lubricants in space as well as then being able to "print" tools is an advancement upon a space craft. Algae also then, could grow atmosphere and shield stasis or sleeping chambers with cycling live culture blooms within the hull structure of the chamber then allowing an interior air environment with climate control...

In modern society the electronics we use daily are also able to be effected by E.M.P.

(electromagnetic pulse ) that are tandem with C.M.E.'s (coronal mass ejections). With the above design applied, it may prevent massive fires occurring upon the ground due to the ubiquitous nature of the current electrical power grid, house hold wiring, appliances and automotive products... Granted this would be a rare occurrence but the cost of failing to develop the prevention system would be much greater...

The "Carrington Event" that occurred in 1859 level of C.M.E. / E.M. pulse would be very dangerous today as the electricity grid requires transformers for the domestic current reduction then from the "grid" into the homes...and their damage would take long periods to then restore the transformers should they be damaged by a solar storm..

All of the other engine designs currently in use today (to my knowledge) will not respond in such a given time frame ( ie... from solar flare detection to placing the mitigation technology in place ) is a bit difficult so we are introducing a "Static Compressor" engine system. Please find it at the following link. http://www.designdeskinc.com/static-compressor.html

The engine system should provide the rate of travel for the required response time parameter. Don't forget to shield correctly in growth weep of algae as a shield when high rate of travel refer to

the "Space Farm Starcraft" design system listed at the following link....http://www.designdeskinc.com/space-farm-starcraft.html

Additionally the design may incorporate the following lift system to assist in flight multiple https://www.designdeskinc.com/tilt-drive.html (Internal ceiling mount to also cause launch assistance, and vector differentiation - craft steering), and https://www.designdeskinc.com/levitation-core.html or be used to remote detach to deal with detected N.E.O or Earth impacting asteroids or comets. The detaching system to deal with earth impacting asteroids then also implementing small versions of https://www.designdeskinc.com/cold-plasma-drive-toroid-static-compressor.html

in addition to https://www.designdeskinc.com/hover-motor.html then to travel in efficient manor to mitigate an impactor. Habitation and Flight Ball engine systems at https://www.designdeskinc.com/baton.html

* Note - the farm fuel unit then producing carbon for the systems inductance "cage" capacitors to keep

the internal workings safe during advent. The inductance capacitors then use arc across

nodes upon the exterior of the hull to de-energize the the inductance produced in high

magnetic advent. The farm fuel unit (algae bio reactor) also produced feed stock for plastic

to repair the craft components O2 in the reactor to then combine with carbon to form inert

carbon dioxide.

Note - the antenna, labeled communications only is placed adjacent to the intake accelerator with

sealed compartment lid and inductance cage - redundant transmitter array

Note - the solar "pressure" equivalent must remain constant upon the surface of the Earth,

system's flight then attained by sealed force vectoring hover motors as the ground based

system to then balance the solar radiation diffusion satellite's implementation. The hover

motors then instigating a downward force upon the ground spaced across the land mass

equidistant (circumference), to then attain the solar pressure equivalent down force as measured

without the solar radiation diffusion satellite in operation. This "to then" balance the Earths orbit.

The hover motors listed at https://www.designdeskinc.com/hover-motor.html and response speed

engine systems listed at

https://www.designdeskinc.com/cold-plasma-drive-toroid-static-compressor.html

Note - due to the "thermal stress" upon the surface of the diffuser "ie... the C.M.E. impalement side

of the satellite, the surface must be heated prior to C.M.E. re-direction diffusement function

via electric resistance heating elements to then compensate for the "thermal shock" encountered

when in operation functioning to redirecting a solar flare or coronal mass ejection to maintain the

structural integrity of the material selection."

Note - critical components must be magnetically insulated to prevent unwanted Gauss (induced

magnetism) contained in the satellite..... hull Gauss will occur...

Note - prior to the C.M.E. actual physical impalement with the satellite, the particle accelerators

then at speed closed cycling a stored inert gas upon the craft. The step is required to then

have particle accelerators internal "mass" at full speed upon the instigation point of solar

flare, C.M.E. and solar radiation diffuser satellite collision and redirection. The flare is

then "pulled" from the impalement side and ejected in a cone to redirect the C.M.E.'s

trajectory diffusing it via the incident cone effectively changing the Earth impaling vector.

Note - particle accelerators then the sum of 8, about the circumference, with redundant operating

system within the craft "so that" a "bank" of four will perform the system "requirement function" with

a full independent system in reserve.

Note - When attempting the C.M.E. redirection the operators "depart" the craft in flight balls to

operate the system at range remotely. Redundant navigation of the main craft "pre-set" to return

to predetermined position inductance shielded!

Note - this system may also stop the magnetic Gauss of asteroids causing eventual orbital

trajectory problems should it become required by redirecting C.M.E.'s Asteroid "collision" within

the horizontal "plane" if the magnetic solar discharge would then effect an orbital object

causing a problem (spherical analysis) about the solar "disk".

This would then require minimum of three (triangular placement), craft, to function correctly

with all C.M.E. satellite discharge vectoring away from the asteroid belt or singular

asteroid (circular "quadrant point" satellite discharge then discharging with angle inclination or

declination "to not" effect objects at range).

Note - The incident cone then a divided cone not to then inadvertently cause magnetic induction

upon the opposite side of the Sun effecting the asteroid belt causing asteroid magnetization

(constant "run" solar gain reduction / watt per square meter function) and for C.M.E. function

the emission "cone" emits about 360 degrees.

Note - Gamma Ray Burst deflection is possible if total planetary coverage is attained...

Note - "cone transmitting" (pre impalement diffusion spread), into the on coming flare / C.M.E. then

may also "lens" the intensity and temperature levels making them manageable. The transmitter

"apex lensing" may also be an avenue to explore as it could cause the "on coming" solar flare to

then be "sent" through a distant "focus apex" to transit itself directing the flare outward to cool

or be re-directed preventing the flare from Earth crossing impalement.

The "apex" lens function then upon side same as number 22 with adjustable focus aperture

(polar array number 21 tilt adjusting mounting).

The said transmitter then causing an "hour glass" shape cone with the transmitter and electron

injection system causing a focus point at great distance from the actual satellite. This at first will

condense the solar flare to then "diffuse" it to cause cooling before impalement with the satellite

that will further spread the flare apart with the emission of the particle accelerator system.

*Note- the placement of the system critical for correct functioning... the placement directing the

"incident cone" then toward the North or South pole of the Sun might "lens" the Solar light

then causing a curved lens to reduce the solar watt per meter upon the ground of the Earth.

ie.... placing the incident cone so that it is "broadcasting" perpendicular from the solar planetary

plane.

Production Method... / launch system

Regarding the "scale" depicted the design then constructed / "inflated" in outer space lifted up / out by the four flight balls connected to the flight ball "load ring". The design at depicted scale made rigid in space from within the design. The mechanical bee, (https://www.designdeskinc.com/sonic-automated-pollenator--mechanical-bee-.html ) then at scale to lift the systems components into the dock" located at the base where the main transmitter is located between the retracting magnetic dock guides / landing foot to then allow for air lock mounting internal as the transmitter "dish" retracts to allow for the "off loading" of system components to complete the design. The exterior of the vehicle is constructed by robot to then allow the required thermal capacity vs. weight to allow the system to function. The form "balloon" then packed in the "lift ring" inflated and made rigid in space to "accept" the layering process internal with structural reinforcement and radiation shielding for safe occupancy.

Geoengineering - Climate Change Mitigation

Design Desk Inc.