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Proposal for an American Space-Based Economy...

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American...

Posted: Thu Oct 15, 2009 5:52 am

Guest

Technocracy that is not fear-based - not spastic - and not
based entirely on the lower needs of the Hierarchy scale[1],
which is the economic enemy of free-market entrepreneuralism,
which is also the enemy of the human race - the enemy of
Solomon's Key to Prosperity - the enemy of the God of Heaven,
and the enemy of the same God of the Universe - has already
prepared for most or all of humankind its place in the
universe as planet earth - and in doing so, has made each
and every one of its humans as created beings, who throughout
all of history have become more and more curious as to our
own origin and purpose in life.

There is one lingering question that still haunts all of
modern humanity: By whose authority does ANY government
represent the interests of an upwardly mobile society of
scientific entrepreneurs, especially when the lines of trade
between prospective orbital, trans-orbital, and earth-based
partners are the only routes of dependency that a privatized
technology must protect?

Of course there are the earth-bound issues which concern
things like the building and maintenance of highway systems,
including the Federal Highway Authority et. al., but do
these things really have anything to do with things like
launch facilities, the AST (Associate Administrator for
Space Transportation) sector of the FAA launch approval
process?

There are extensive environmental impact statements re-
quired to secure launch permission, and even long wait
times to process licenses for launch.

The largest hindrance for private space launches is IMO
the 1998 Strom Thurmond National Defense Authorization
Act, which transferred jurisdiction to the State Department
from the Commerce Department.

The right to private property for individuals, i.e.
space entrepreneurs, to utilize their own engineering
R&D through such a thing as "engineering tinkersmanship",
should never be able to include through political
justification, an extension of property rights to those
that would (unproductively) hinder the exploitation of
those rights - in either the exploration or the
aquisition of off-world resources.

"The righteous will flourish like a palm tree, they will
grow like a cedar of Lebanon, planted in the house
of the Lord, they will flourish in the courts of
our God. They will bear fruit in old age, they will
stay fresh and green, proclaiming, "The Lord is upright;
he is my Rock, and there is no wickedness in him."

- Psalm 92: 12 - 15

Instead of H. Clinton permitting an inspection of our
nuclear launch facilities by Soviet inspectors, which
seems more like what Jane Fonda did with N. Vietnam x 10,000,
(in giving in to Communist totalitarianism), and hence all
the current "green" Republicrats and Demicans - with their
Pol-Pots of the world - American private enterprise should be
developing its own technology for the production of
nuclear pulse units - which is not so outlandish as to
presume that with the proper security in place, as well
as the right kind of nuclear pulse inspectors (which can
be agreed upon between local licensing parties of interest)
- to help drive a massive earth-to-orbit technology
for the future of the human race in space[2].

American

[1]

Maslow's Hierarchy of Needs:

http://en.wikipedia.org/wiki/Maslow's_hierarchy_of_needs

[2]

http://finance.google.com/group/google.finance.660479/msg/df734b1fe9ee3

490

"The need established for utilizing asteroid mining as a
profitable venture is based on a new gold standard for the
colonies of the prospective solar system, just like it was
profitable for explorers in the New World in staking their
claim for God and country. America will never become a third
world country, based upon the 'enlightenment' of technological
subversives.

Cheaper earth-to-orbit technology is already here, yet
the forces that control our economy are still just begin-
ning to take notice of the vast resources that space has
to offer: primary and precious metals by the billions
of tons, extraterrestrial lunar ices, non-invasive,
sterile work environments, synthetic aperture radar map-
ping technology, huge non-radioactive nuclear propulsion
systems - all dependent upon cheaper earth-to-orbit and
orbit-to-orbit technology so that components can be modular-
ized on earth, designed, assembled, tested, and marketed
in space.

[3]

The Dangerous Liberty of Engineering vs. Lukewarm Dominionism

http://groups.google.com/group/sci.space.policy/msg/b5d82fab26537ce0?hl

=en9f81b5c609fe9d6

http://groups.google.com/group/sci.space.policy/msg/d9c626567f45a605?hl

=en9f81b5c609fe9d6

American...

Posted: Fri Oct 16, 2009 4:47 am

Guest

A Gamma Ray Imaging Spectrometer (GRIS) is a device for
studying spectrographic images of gamma ray activity
throughout the universe. Since there is such a wide
spectrum of gamma radiation, there needs to be a defined
set of parameters for narrowing the spectrum down to
useable frequency, magnitude, and count that would image
the precious metal content of an Aten asteroid with a
known location and orbit.

First, the energy level in KeV needs to be established for
the atomic transition level of a gold or platinum molecule
in the gamma ray frequency. There are some interesting graphs
related to GRIS used by NASA that are related to GRIS energy
resolution (Fall/1995) that lists the Frequency Wide Harmonic
Magnitude in KeV from 0KeV to 10KeV verses the energy level
from 0 to 8000KeV, or GRIS GAIN energy calibration accuracy
which lists the error in KeV from -1KeV to 1KeV verses the
energy in KeV from 10KeV to 104KeV, or GRIS continuum back-
ground that is the continuum background in counts from
..00001 to 1 cm^-3 sec^-1 MeV^-1 per energy from 10^-2 MeV
to 10 MeV range. The GRIS background spectrumshows counts
from .00001 to 10 cm^ -3 sec^-1 MeV^-1 per energy from 10
KeV to 10,000 KeV range. Thus there are limitations to the
observable gamma field that need to be referenced when
designing narrowband filters for the desired frequency,
magnitude, and count parameters.

Centrifuge Processing of Extraterrestrial Precious Metal

A rotating cylindrical vessel of volume V with incoming
regolith at inlet #1, and hot dilute NaCN and H2O at inlet
#2 is designated as the feed q_j, which is equal to
( q_NaCN + q_regolith ). The inner centrifuge cylinder
is immersed in the outer centrifuge cylinder of annular
volume V_c, which contains recirculated heated machine
oil at temperature T_hf at a flow rate q_h. The outgoing
pipe contains the mixture of products and the remnant
of the reactants at a flowrate of q = q_NaCN + q_regolith
+ q_reactants . Thus the volume V remains constant.

Some Theory on Precious Metal Spectroscopy

Actual atoms scatter, as they absorb, at frequencies
connected with quantum transitions between energy levels.
The spectra resulting from the excitation of inner electrons
provides a connecting link between optical and gamma ray
spectroscopy. Only one electron needs to alter its quantum
numbers in order to reach the excited state from the ground
state. When this happens, a continuous absorption spectrum
joins the series limit just as a normal series, and also
corresponds to ionization leaving not only the outer shell
of the molecule, but also to the excitation of shells lying
still farther in.

Compton scattering causes the scattered X-ray to be a
different wavelength than the incident X-ray. For this
reason, one needs to know the location of the original
X-ray source and the angle of reflection off the surface
of the asteroid, but not necessarily. If an observer had
a known location, and the asteroids position could be
calculated precisely at one time, with scattered wavelengths
observed, and at a later time, both observer and asteroid
were known withscattered wavelengths observed, the
scattered frequencies could be correlated with existing
transition energies and frequencies of the precious metal,
with maximum likelihood of incidental angle. Of course,
this would depend on initial educated guesswork,
involving the exact intensity, frequency, and location
of existing galactic gamma ray source (e.g. from GRB 971214,
12 billion light years away!)

Gamma ray spectroscopy is more suited to locating precious
metal asteroids since gamma rays can penetrate into the
interior of the asteroid unlike infared spectrometers.
The resolution is also much better, with finer spectro-
graphic data being demonstrated much more dramatically
than with the infared type.

The absorption band varies according to how the intensity
of reflection varies with wavelength. For this reason,
we have different states of metals as they would exist
in asteroids.

Check out the NIST Atomic Spectroscopic Database
(Version 1.0) for information on the spectrum of the
different states for each element - There are hundreds
of states for aluminum! Other sources indicate that
spectral emissivity tends to increase with decreasing
wavelength. The normal spectral emissivity for Platinum
at 1 meter wavelength is approximately 0.25 at 1217 degrees
Kelvin.

However, this emissivity is for polished platinum. IMO the
emissivity would be higher (0.05 maximum variation) for
a less smooth surface. Still, a lower surface temperature
(less than 1217 K for platinum) would tend to raise the
spectral emissivity variation a maximum of 0.025. The
total maximum variation in spectral emissivity would
then be about 0.075. Added to the normal spectral
emissivity would equal 0.25 + 0.075 = 0.325.

American

[1]

Space Resources - Breaking the Bonds of Earth by John S. Lewis and
Ruth A. Lewis, Columbia University Press, Copyright 1987

American...

Posted: Sat Oct 17, 2009 5:47 am

Guest

(from:)

http://www.cfa.harvard.edu/iau/Animations/Animations.html

“This animation hitches a ride on the earth and observes its
near-space environment for a period of one year at daily
intervals starting in July 2007. No objects are displayed that
are more than 20 million km from the earth.

Objects within one-third of this distance are colored red,
objects within two-thirds are colored orange, other objects
are green. Objects below the ecliptic plane are shown as
outline circles, objects above as filled circles.

Objects may appear and disappear in seemingly odd
locations, depending on how their orbits intersect the
sphere enclosing the volume of space within 20 million km
of the earth. Notable close approaches during the
period occur on 2007 Sept. 5 (2007 RS1), Oct. 12
(2007 TX22), Oct. 17 (2007 UN12), Oct. 18 (2007 UD6),
Oct. 30 (2007 US51), Nov. 14 (2007 VF189), Dec. 13
(2007 XB23), Dec. 27 (2007 YP56), 2008 Jan. 31
(2008 BC15), Feb. 7 (2008 CT1), Mar. 9 (2008 EZ7),
Mar. 10 (2008 EM68), Mar. 29 (2008 FP), Apr. 3
(2008 GM2), Apr. 7 (2008 GF1) and May 10 (2008 JL24).

Most of the objects depicted in this animation are recent
discoveries. The symbol representing Earth is not to scale:
at the scale of these plots, the earth would be about a
quarter pixel across on the larger plot and
about a tenth of a pixel on the smaller plot.”
NEA animation:

http://www.cfa.harvard.edu/iau/Animations/EarthRide2008Small.gif

(larger:)

http://www.cfa.harvard.edu/iau/Animations/EarthRide2008.gif

American

American

American...

Posted: Sun Oct 18, 2009 9:30 am

Guest

American...

Posted: Thu Oct 22, 2009 9:50 am

Guest

On Oct 21, 3:04 pm, American <samuelran... at (no spam) comcast.net> wrote:
[quote]On Oct 18, 3:30 pm, American <samuelran... at (no spam) comcast.net> wrote:

(from:)

http://www.cfa.harvard.edu/iau/Animations/Animations.html

“This animation hitches a ride on the earth and observes its
near-space environment for a period of one year at daily
intervals starting in July 2007. No objects are displayed that
are more than 20 million km from the earth.

Objects within one-third of this distance are colored red,
objects within two-thirds are colored orange, other objects
are green. Objects below the ecliptic plane are shown as
outline circles, objects above as filled circles.

Objects may appear and disappear in seemingly odd
locations, depending on how their orbits intersect the
sphere enclosing the volume of space within 20 million km
of the earth. Notable close approaches during the
period occur on 2007 Sept. 5 (2007 RS1), Oct. 12
(2007 TX22), Oct. 17 (2007 UN12), Oct. 18 (2007 UD6),
Oct. 30 (2007 US51), Nov. 14 (2007 VF189), Dec. 13
(2007 XB23), Dec. 27 (2007 YP56), 2008 Jan. 31
(2008 BC15), Feb. 7 (2008 CT1), Mar. 9 (2008 EZ7),
Mar. 10 (2008 EM68), Mar. 29 (2008 FP), Apr. 3
(2008 GM2), Apr. 7 (2008 GF1) and May 10 (2008 JL24).

Most of the objects depicted in this animation are recent
discoveries. The symbol representing Earth is not to scale:
at the scale of these plots, the earth would be about a
quarter pixel across on the larger plot and
about a tenth of a pixel on the smaller plot.”
NEA animation:

http://www.cfa.harvard.edu/iau/Animations/EarthRide2008Small.gif

(larger:)

http://www.cfa.harvard.edu/iau/Animations/EarthRide2008.gif

American

On Apr 19, 7:30 pm, Willie.Moo... at (no spam) gmail.com wrote:

: Rocket engineering is a little more sophistticated, even in
: mthe basics, than you put forth here;

: Check out these articles

:http://www.engineeringatboeing.com/articles/turbopump.htm

Yes, I can see the complexity there, which is why I'm not us-
ing "turbopumps" in the design. There's no "jet" being produced
for "thrust" here - just a magnetohydrodynamic injector for each
pellet blasted into the thrust dome.

No doubt that you've heard of thermoelectric electromagnetic
pumps that pump molten lithium liquid through a heat transport
system. That's the primary heat loop. A virtual slide show of the
heat loop system and control system can be downloaded here:

http://home.comcast.net/~samuel_ransom/pre.zip

INSTALLATION INSTRUCTIONS:

1) unzip pre.zip file in folder you create as "pre".
2) Go to DOS.
3) Go to /pre folder.
4) Type "PRESENTS".
5) Arrow down to "Display Presentation". Press <ENTER>.
6) Press the <F1> key and select with the arrow keys "T2.pre".
7) Press <ENTER>.
Cool

American...

Posted: Wed Oct 28, 2009 1:49 pm

Guest

On Oct 22, 3:50 pm, American <samuelran... at (no spam) comcast.net> wrote:
[quote]On Oct 21, 3:04 pm, American <samuelran... at (no spam) comcast.net> wrote:

On Oct 18, 3:30 pm, American <samuelran... at (no spam) comcast.net> wrote:

(from:)

http://www.cfa.harvard.edu/iau/Animations/Animations.html

“This animation hitches a ride on the earth and observes its
near-space environment for a period of one year at daily
intervals starting in July 2007. No objects are displayed that
are more than 20 million km from the earth.

Objects within one-third of this distance are colored red,
objects within two-thirds are colored orange, other objects
are green. Objects below the ecliptic plane are shown as
outline circles, objects above as filled circles.

Objects may appear and disappear in seemingly odd
locations, depending on how their orbits intersect the
sphere enclosing the volume of space within 20 million km
of the earth. Notable close approaches during the
period occur on 2007 Sept. 5 (2007 RS1), Oct. 12
(2007 TX22), Oct. 17 (2007 UN12), Oct. 18 (2007 UD6),
Oct. 30 (2007 US51), Nov. 14 (2007 VF189), Dec. 13
(2007 XB23), Dec. 27 (2007 YP56), 2008 Jan. 31
(2008 BC15), Feb. 7 (2008 CT1), Mar. 9 (2008 EZ7),
Mar. 10 (2008 EM68), Mar. 29 (2008 FP), Apr. 3
(2008 GM2), Apr. 7 (2008 GF1) and May 10 (2008 JL24).

Most of the objects depicted in this animation are recent
discoveries. The symbol representing Earth is not to scale:
at the scale of these plots, the earth would be about a
quarter pixel across on the larger plot and
about a tenth of a pixel on the smaller plot.”
NEA animation:

http://www.cfa.harvard.edu/iau/Animations/EarthRide2008Small.gif

(larger:)

http://www.cfa.harvard.edu/iau/Animations/EarthRide2008.gif

American

On Apr 19, 7:30 pm, Willie.Moo... at (no spam) gmail.com wrote:

: Rocket engineering is a little more sophistticated, even in
: mthe basics, than you put forth here;

: Check out these articles

:http://www.engineeringatboeing.com/articles/turbopump.htm

Yes, I can see the complexity there, which is why I'm not us-
ing "turbopumps" in the design. There's no "jet" being produced
for "thrust" here - just a magnetohydrodynamic injector for each
pellet blasted into the thrust dome.

No doubt that you've heard of thermoelectric electromagnetic
pumps that pump molten lithium liquid through a heat transport
system. That's the primary heat loop. A virtual slide show of the
heat loop system and control system can be downloaded here:

http://home.comcast.net/~samuel_ransom/pre.zip

INSTALLATION INSTRUCTIONS:

1) unzip pre.zip file in folder you create as "pre".
2) Go to DOS.
3) Go to /pre folder.
4) Type "PRESENTS".
5) Arrow down to "Display Presentation". Press <ENTER>.
6) Press the <F1> key and select with the arrow keys "T2.pre".
7) Press <ENTER>.
Cool

Press <ENTER> again and answer "Y" to loop presentation.
9) <ESC> to exit program.
10) After <ESC>, press X to exit back to DOS.

These are heat loops that center on the actual feed lines
that are able to magnetically blast the pellets at a rate of
120 per second into the thruster, where they become ignited
by the lasers (The fusion technology for applying laser ignition
uses 96 lasers per thruster (3 thrusters in all) that are
capable of focusing relativistic electrons with P-b gas into
magnetic confinement.

:http://space.au.af.mil/primer/rocket_theory.pdf

: These are chemical engines, there are similar articles for
: nuclear thermal rockets. Then, there are nuclear pulse rockets,
: where the mechanisms and numbers re way way different.

I believe it's the magnetohydrodynamic effect of the injection
mechanism that you're referring to, w.r.t. the pellet injector
design that uses a magnetic gun for the injectors (3 in all,
that are fed by feed lines, which are themselves charged
by coils. Grouping numbers of charging units into a single
fuel cell would require the length of the fuel cell to be a
multiple of the length of a single charging unit, that contains
a few hundred coils each - 360 to be exact.)

: Basically if you run an engine continuously, you've got to
: inject propellant against the chamber pressure, and that takes
: a certain rather large percentage (around 3% iirc) of the
: power of the jet. Which becomes MONUMENTALLY huge when
: you are talking about very hish performance high thrust engines.

I gave up the idea of arcjet propulsion when I noticed the
dependency on LOX and LH2 systems resplendent with design
problems such as impeller cavitation in the hydrodynamic
bearings, flow rate instabilities, and high temperature
inefficiencies - the SSME utilizes a design based on a 400
bar combustion chamber of the MBB engine CS50K-H, and
I don't believe that the sophistication of these systems is all
that warranted.

: Furthermore, most regeneratively cooled engines, recycle
: about 1% or more of the thermal energy to keep the throat
: from burning out. This doesn't work so well when you move
: beyond nuclear thermal or chemical engines. In fact the throat
: of a nuclear thermal rocket is cooler than a chemical rocket.
: The major improvement in performance comes from the use of
: liquid hydrogen - which is 1/9th the mass of hydrogen enriched
: steam the next highest performing genreally available rocket
: (when you burn hydrogen and oxygen in a 6:1 ratio)

Not much has been researched w.r.t. magnetic entrainment
in conjunction with coil-induced magnetohydrodynamics. This
is a whole different science - we're talking about coil injection
of the nuclear pellets into the combustion chamber, which is
itself open-space propulsion. Sure, there are electromagnetic
disturbances felt over 100 miles away - so by default this type
of propulsion doesn't require a launch zone within or near popu-
lated areas - a much needed safety and security precaution if
you're trying to stay incognito of surveilance by the compe-
tition anyway.

I'm envisioning an independent launch facility stationed com-
pletely outside the continental U.S., but close enough to be
reached by sea - such as an offshore platform - it's only a
matter of minutes before radio communication could be
restored to a rocket of this magnitude.

: When you talk nuclear gas core rockets with a continuous
: burning - fuhgetaboutit. You're just too hot, and too ener-
: getic to use these sorts of deals. That's what makes nuclear
: pulse so cool.

The feed lines of a magnetohydrodynamic injector can support
a ten minute charge or 600 second total specific impulse. This
would require a total of 111,672 inches of feed line packed
with pellets back-to-back. 75 lines at (no spam) 1,489 inches/line can
provide a maximum pellet repetition rate of 120 pellets/sec
for a ten minute specific impulse.

: First when you have really really fast pulses of energy in-
: teracting with things, you have very little spread of heat
: energy. The classic example is an ember from a burning fire
: falling on your carpet. You try to pick it up, and you get
: burned. You flick it back into the fire and you are safe.
: Why is that?

: Heat transfer is a diffusive process
: Momentum transfer is not

A device employing the utilization of charge entrainment in
an electrohydrodynamic device such as a magnetic injector
requires that the turbulent flow characteristics are calculated
for the fluid in question. A little research I've done yielded an
excellent mathematical model that described flow rate in terms
of both hydrodynamic viscosity, letter "v" (pronounced 'vue')
and (p - p_c), as the hydrodynamic pressure approached critical,
used an eigenvalue equation to solve for the dimensionless flow
rate at critical pressure.

Most of this stuff never got developed beyond theory - its just
waiting for an entrepreneur to come along and validate what's
never been done before - and that is putting it to practice.

: So, that's the answer to dealing with really really high
: energies - you hit something with energy fast enough, all
: the kinetic stuff takes place before heat gets a chance to
: diffuse away. That's why they can use ultra-fast laser
: pulses to machine C4 and not worry about an explsion

: I've calculated

:http://www.galasers.com/pdf/double_pulse_machining.pdf

So the two halves of a sphere of similar stuff are all that's
needed to "wick" the rest of the pulse unit. The core charges
could be mechanically assembled underground, under the close
inspection of the facility by IAEA inspectors to make their
independent judgements, and/or to install security cameras and
recording devices inside a facility for surveillance purposes.

: There is a cool drawing in my rocket text book back in the day,
: which is in my attic in a box, and I don't want to go find it to
: even check the title - anyway - it is a flow diagram showing
: the percentages of energy that are generated in a thrust
: chamber and how they flow around.

If the energy distribution on the surface of a pellet remains
constant for different size pellets, then 3.6 x 10^6 Joules re-
quires a pellet of radius 0.3265 cm. to achieve an equal energy
distribution of 2.685 x 10^6 J/cm^2. D3_He pellets require an
energy density of 1.847 x 10^9 J/cm^2. This is actually 261
times the energy currently provided by state-of-the-art 'silicon
wedge' lasers. We can increase the power to the pellet by in-
creasing the number of lasers, and increasing the power from
each laser, yielding a minimum power input of 2.25 X 10^13
Joules per second per dome, for three domes total. A 3.94 cm.
diameter pellet at (no spam) 250 hz meets the requirement for power input
to achieve subluminal

...

read more »- Hide quoted text -

- Show quoted text -
[/quote]
Why not ignite ejected bomblets with a Krypton-Flouride
laser? The physics involved would be a lot simpler if
the laser was used in conjunction with a bomblet that
was modified to ignite at a specific frequency and
temperature.

http://images6.theimagehosting.com/frame_1.gif

The above diagram is a schematic of the thrust/ring,
ring/chamber, propulsion chamber, and aft fuselage
framing for loading. Thrust framing for the cargo ves-
sel fuselage, fuel cell assembly, and cryogenic supply
system uses general loading analysis technique for the
thrust axial loading, inertial axial loading, and axial
flux distribution. A 3-D structural code is construct-
ed for the space frame program in Fortran. The axial
flux distribution due to thruster loading is dependent
upon the design and stiffness of the thrust ring and
fuel cell structure. An iteration method for estimat-
ing sizing uses a Fortran space frame analysis.

The number of joints in the space truss will yield 3
times as many equations for each summation of forces in
the x, y, and z directions. Each element is assumed to
have axial, bending, and torsional stiffness. The finite
element technique for analysis uses elements pictured in:

http://images6.theimagehosting.com/engr.gif

The thruster framing analysis uses point distribution
loading at each point of intersection between stringers
from a radial direction whose point of origin is the
chamber centerline just outside the outer ignition ring.
Not shown is the ignition ring w/end optics, mid-to-aft
fuselage, fuel cell assembly, bomblet delivery system,
and cryogenic supply system, which I have in schematic:

http://images6.theimagehosting.com/end_beam_1.gif

The laser final optics to the ignition ring pictured
above shows a comparison between free electron ignition
using the blumlein ion particle transmission, and fused
silica wedge optics using high energy focused electron
beams. For each system, there are a total of 96 end
optics, positioned in a ceramic/steel ring designed to
provide the support structure, electronics, and cool-
ing to the entire ignition ring/thruster interface.

http://images6.theimagehosting.com/coil.gif

A total of 18 coils in the injector provide up to 15
Tesla magnetic induction in order to accelerate each
pellet into the propulsion chamber. Superconductive
pellets containing bomblet fuel are stored in 5 second
fuel cells at (no spam) 23.634m/cell. Each cell's outside D=7.5cm.
(w/coolant lines). For a 10 minute specific impulse,
there are a total of 120 cells/thruster. A 1mm machin-
ed spiral surface contour on the inside and outside
covers to the spiral dielectric and magnetic conductor
provide a "seat" for the 1mm SuperMalloy wire, as well
as a "container" for each set of 18 coils. A total of
360 coils are required for each 5 second fuel cell. A
cross section of all fuel cells for each thruster is
approximately 1m2. The charging capacitors are tuned in
order that the self-resonant frequency of each coil's
distributed capacitance does not equal the frequency of
the charging capacitor. Multiples of the resonant fre-
quencies are also discarded from the tuning.

The coil system used for the axial magnetic field uses a
LHe-4 cooling circuit in the complete fuel cell. Assum-
ing that LHe-4 is a perfect coolant when the LHe-4 reaches
the superconductive state, the coil life expectancy has
to increase in order to withstand a specific impulse of
several minutes. The ratio of coil spacing to coil ra-
dius is an important factor in determining coil efficiency.
The minimum coil spacing that would allow rapid acceler-
ation out of the injector and at the same time accept a
17 ft/sec feed rate from the fuel cells has been calcu-
lated according to design specifications for this system.

http://images6.theimagehosting.com/preamp.gif

The above diagram is the preamplifier for the pulse amp:

http://images6.theimagehosting.com/pulse.gif

The pulse power supply generates pulses up to 30 kv. Q1
and Q2 form a multivibrator in conjunction with peri-
pheral components R1 thru R6 and C1, C2, C3, C5, C6,
and D2. R9 adjusts the pulse repetition rate. R2 should
be selected to limit the maximum repetition rate to 20 Hz.
I1 is a type 1156 lamp used as a current limiter. R9 can
be left out and R2 selected to produce a fixed rate, if
desired. Q3 serves as a power amplifier and switch to
drive T1 (magnetic induction coil). NE1 is used as a
pulse indicator and indicates circuit operation. Because
of the high intensity magnetic field generated, a mag-
netoresistive shield is required between the circuit
and coil. (The pulse supply circuitry is protected from
the high energy magnetic field that is induced in the EM
coil and induction tube thru magnetoresistive amorphous
SmFe2 99.26 at. % B 0.74 at. % alloy).

http://images6.theimagehosting.com/Aft1b1.gif

The above diagram shows the 3rd Heat Loop, for which
I have all of the Heat Transfer engineering calculations.

http://images6.theimagehosting.com/Aft1c.gif

The above diagram shows the 3rd heat-loop-to-thruster,
for only 1 thruster pictured.

http://images6.theimagehosting.com/cnduct.gif

Thrust is transmitted through the ring/chamber frame
to the thrust ring framing, and from the thrust ring
framing to the aft fuselage. The initial applied load-
ing from nuke bomblet ignition is directly appled as
shear and axial stress to the ring/chamber frame
connections, and to the aft fuselage framing.

Ablation to the propulsion chamber surface is negligi-
ble, considering the fact that the chamber is large en-
ough in diameter, and the radiation distribution is
handled quite effectively through the use of TZM alloy.

There are three fuel pellet injectors in the bomblet
propulsion system. Coil windings in the magnetic gun are
cooled cryogenically with LH to 20oK. The coil windings
themselves are insulated with lead titanate, which can
sustain a field of over 10**7volts/meter and dielectric
constant of up to 12,000, but where the velocity of
propogation is equal to: Vp = 100 / E, where Vp= Velo-
city of propogation in percentage of the speed of light,
and E = dielectric constant of the insulator. Further,
Vp is calculated from the relationship:

du/dt = (3 /8(mue)_0)(B_g**2/ r_p (density))
where (mue)_0 is the self-inductance per meter length 4 x 10**-7henry/meter, Bg= field strength in Tesla,
r_p = radius of fuel pellet, and (density) = fuel pellet
density in kilograms.

For the coil injector, One oersted exerts a force of one
dyne, and a force of one dyne acting on a mass of one
gram imparts to it an acceleration of 1 cm / sec2. Ap-
proximately 981 dynes = 1 gram weight, therefore, 981,000
dynes = 1 kilogram. The field strength for Nb_3,Sn at the
mixed state* at 4.2oK is 221 kg. The current density for
a 3 mil skin depth on a bomblet of is high - approximately
5.745 x 1015 amps per m2. Assuming the pellets are back-
to-back as they enter the injector, a velocity of 4.728
m/s or 472.8 cm/sec is sustained for 120 pellets to enter
the injector after 1 second. If each pellet weighs
2.26109 grams, then 120 pellets(2.26109) = 271.33 grams
total weight of pellets entering the injector. The force
propelling the pellets must equal 271.33(472. Cool

128,284.82 dynes, so the magnetic force = 128,284.82
oersted. The permeability required for a metal used for
coils that can sustain a magnetic force of 128,284.82
oersted has been calculated as mue = 544.523, which is a
popular value for coil permeability.

Each of 360 coils is packed with 120 back-to-back pellets,
and represents a separate charging unit to the pellet in-
jector. 5 charging units (or a single fuel cell) is
switched on every 5 seconds, and this process continues
until all 120 fuel cells are exhausted. Each cell's
overall diameter is 7.5 cm., and so all 120 cells are
grouped in a cubic arrangement inside a 1m**2 crossection.

During ignition, the density radius product of the implod-
ed pellet is raised beyond a few hundred, with a pellet
density greater than 100,000 times the liquid density.
X-rays are trapped with laser energy outputs of 104 joules,
at 50% efficiency. As the pellet becomes imploded tenfold
in radius (1,000 times in volume), the confinement time is
also reduced tenfold, and the burn time is reduced by a
factor of 1,000. The burn efficiency is therefore in-
creased by a factor of 100 to 10%, yielding 30 times the
laser input energy. About 50% of the initial fireball ex-
plosion is converted into thrust. This means that the
actual working thrust amounts to about 15 times the laser
input energy. The pellets themselves are stratified with
Boron 11, so that the reactants are all non-radioactive.
This is a new technology. For earth-to-orbit technology,
scientists are experimenting with the manufacture of Boron
(B-11) plasma w/ hydrogen "backfill" using pulsed lasers.
For orbital construction of interplanetary spacecraft,
Boron-Lithium nanotubes could also be used as an ablation
material to "reduce" radiative effects of fissionables.

Ablation calculation uses the Zeus MP (MagnetoPlasma) code
for calculating the Sedov blastwave. This is accomplished
by modifying a couple of the input parameter files using
the Fortran object files and dependencies of stblast.o and
stblast.F, respectively. The resulting output files consist
of a header display and a logarithmic density of the region
encompassing the outflowing waveform. The design temperature
of the shockwave is approximately 120,000 °F with a 50,000
lb/in2 (340 Mpa) pressure on the ablating surface.

~

American

American...

Posted: Sun Nov 01, 2009 11:44 am

Guest

1) Need for war/death to enemies
2) Imperialism/Dictatorship

Both of these must exact human life in some way, shape, or form in
order to perpetuate its agenda for (blood or crypt?) superiority.

What is the use of anyone who claims some kind of "space rated"
authority, as some sort of self-righteous intention for space
exploration, if their own righeousness is as filthy rags?

Continued hard work in the application of the physical laws that
support a profoundly cheaper method of space exploration is all that
is required, but every side must claim that *they* are the ones who
are working diligently at providing the best future for anybody
interested in space exploration, and not just for everybody on planet
earth.

Some actually believe that heaven is not "big" enough for most in the
area of actual faith, and so must be content with things like
"international" space stations, orbital satelite technology, and bases
on the moon and mars. Although these are somewhat righteous causes,
the bureaucracy has entrenched itself sooooo far into the procurement
process that any intelligent and wise observer would wonder who was it
that put the halt on the mass marketing of further production, in
short-sighting the future of space exploration.

It turns out to be our own monopolistic bureaucracy as the culprit
that stifles competition by manipulating the approval process - they
do this through vast corporate/state interests and entrenchment in
opposing the technological drive "at the right time".

It is interesting how many of those who would be involved in a
particular approval process for an earth-to-orbit technology would
consider any *alternative* earth-to-orbit process as a threat to their
own, especially when the earth-to-orbit market should seem to be so
broadly based in lobbies for the state-run media complex. Doubtless
this is because the state/media can now command their attack dogs in
the attempt to force things (like aan over 9800 page health care
reform) into the hands of their welfare-state-run captors!

What's to stop them from thinking of themselves as masters of the
universe?

All of this bloodlust rages and portends the ultimate victim as Christ
and the prophets, even though prophecy has already ordained YHWH as
the ultimate victor in the end.

American

- The god of time was Chium in Egypt, or Saturn in the greek world.
Chium is the same as Cain.

Uncle Al...

Posted: Mon Nov 02, 2009 12:04 am

Guest

American wrote:
[snip crap]

[quote]All of this bloodlust rages and portends the ultimate victim as Christ
and the prophets,
[snip rest of crap][/quote]

http://www.mazepath.com/uncleal/jessy.jpg

--
Uncle Al
http://www.mazepath.com/uncleal/
(Toxic URL! Unsafe for children and most mammals)
http://www.mazepath.com/uncleal/qz4.htm

American...

Posted: Mon Nov 02, 2009 7:00 am

Guest

On Nov 2, 6:47 am, Uncle Al <Uncle... at (no spam) hate.spam.net> wrote:
[quote]
[snip crap]

[/quote]
< snip crony [snip crap] indignation at the mention of anything
"religious" >

love http://www.williamhenry.net/stargateCruci.htm

That's your problem, not mine...

American

"Anything else non-interstellar just makes a stuffed-pig-in-progress
a whole lot fatter."

American...

Posted: Wed Nov 04, 2009 9:58 am

Guest

Brainstorming or offering a proposal to design and engineer an
extraterrestrial resource development facility for the purpose of
establishing a permanent presence in space for private enterprise
worldwide:

This article provides a record of a prospective cost analysis in order
to establish performance parameters.

Projective Expenses

With respect to asteroid mining, the cost of delivering a robotic
spacecraft to rendezvous, mine, and return to an orbital docking
facility with scanned soil samples depends upon the technological
commitment to remote operation, simulation, and the interpretation of
real component descriptors affecting allowable performance
parameters.

The following chart lists costs / year to build, operate, and maintain
components of a remote mining system. It is assumed that a power
satellite construction center has already been developed in order to
facilitate a cargo vessel launch and GAMS tracking system.

Cargo Vessel Propulsion System, Navigation System, and Structural
Shell from the years 2010 – 2017 represent a projected cost in
millions from $235M - $375M.

Mehanical Head Boring Tool, Hydraulics, Power Supply, and
Instrumentation represent a projected cost in millions from $25M -
$115M.

Tray Dump Handling System (Retractable Rail, Hydraulics, Cars &
Canopy, Equipment, Power Supplies, Instrumentation) represent a
projected cost in millions from $30M - $92M.

Regolith Processing (Centrifuge, piping, storage tanks, pumps, ROV’s,
instrumentation, electrical) represent a projected cost in millions
from $12M - $58M.

Geosynchronous Asteroid Mapping Satellite (incl. SAR instrumentation,
Booster, ROV mechanical, R&D) represent a projected cost in millions
from $21M - $52M.

The TOTAL COSTS for a project of this magnitude represent a projected
cost in millions from $323M - $692M.

What would be the return on investment? The R.O.I. would actually
DECREASE from 1500% to 1178% in just 7 years!

As one can see, the proposed return on investment for a precious metal
mining mission far outpaces the mission costs. It should be noted,
however, that with the current U.S. Shuttle program, endorsed SLI by
its constituents, the earth-to-orbit costs for delivering modules for
construction would offset the return on investment by as much as 20%,
in addition to the costs of operating and maintaining a Power
Satellite Construction Center, described in an earlier post.

Much of what has been proposed in the NASA 2004 budget is nebulous in
cost compared to the net profits of a precious metal mining mission to
the Asteroids.

American

American...

Posted: Wed Nov 04, 2009 10:24 am

Guest

What this is about:

Brainstorming or offering a proposal to design and engineer an
extraterrestrial resource development facility for the purpose of
establishing a permanent presence in space for private enterprise
worldwide:

This article provides a record of a prospective cost analysis in order
to establish performance parameters.

Projective Expenses

With respect to asteroid mining, the cost of delivering a robotic
spacecraft to rendezvous, mine, and return to an orbital docking
facility with scanned soil samples depends upon the technological
commitment to remote operation, simulation, and the interpretation of
real component descriptors affecting allowable performance
parameters.

The following article lists costs / 7 year interval to build, operate,
and maintain components of a remote mining system. It is assumed that
a power satellite construction center has already been developed in
order to facilitate a cargo vessel launch and GAMS tracking system.
(GAMS referring to here as a Geosynchronous Asteroid Mining Satelite).

Articles for Development:

Cargo Vessel Propulsion System, Navigation System, and Structural
Shell from the years 2010 – 2017 represent a projected cost in
millions from $235M - $375M.

Mechanical Head Boring Tool, Hydraulics, Power Supply, and
Instrumentation represent a projected cost in millions from $25M -
$115M.

Tray Dump Handling System (Retractable Rail, Hydraulics, Cars &
Canopy, Equipment, Power Supplies, Instrumentation) represent a
projected cost in millions from $30M - $92M.

Regolith Processing (Centrifuge, piping, storage tanks, pumps, ROV’s,
instrumentation, electrical)
represent a projected cost in millions from $12M - $58M.

Geosynchronous Asteroid Mapping Satellite incl. SAR instrumentation,
Booster, ROV mechanical, R&D represent a projected cost in millions
from $21M - $52M.

The TOTAL COSTS incurred for all phases of development represent a
projected cost in millions from $323M - $692 M.

The RETURN ON INVESTMENT (ROI) represents a DECREASE IN PERCENTAGE
from 1500% - 1170%!

As one can plainly conclude, the proposed R.O.I. for a precious metal
mining mission far outpaces the mission costs. It should be noted,
however, that with the current I.S.S. (that actually negates the SLI
by its NASA constituents, the earth-to-orbit costs for delivering
modules for construction would offset an R.O.I. by as much as 20%, in
addition to the costs of operating and maintaining a Power Satellite
Construction Center, described in a previous post.

Much of what has been proposed in the world 2009 I.S.S. budget (~50B –
100B) is STILL horribly nebulous in cost compared to the net profits
of a precious metal mining mission to the Asteroids.

American

Uncle Al...

Posted: Thu Nov 05, 2009 12:04 am

Guest

American wrote:
[quote]
What this is about:

Brainstorming or offering a proposal to design and engineer an
extraterrestrial resource development facility for the purpose of
establishing a permanent presence in space for private enterprise
worldwide:
[/quote]
1) You can't visit the asteroid belt and not get fried by
radiation.
2) You can't grab a NEO without getting similarly fried.
3) Robotics suck. You will have no real time control. AI will be
a disaster.
4) The solar system is a dusty place to land. Ceramic
microspherules are fantastic for ruining seals and eroding moving
parts in contact. Lunar astronauht lungs took a beating, too.
5) 99942 Apophis will be within 15,000 miles of Earth's surface on
13 April 2029. Go grab that.

<http://en.wikipedia.org/wiki/File:Apophis_pass.svg>

4) There's nothing there when you get there. How much asteroid
dirt must you e-Bay to cover your Accounts Payables?

[quote]This article provides a record of a prospective cost analysis in order
to establish performance parameters.

Projective Expenses

With respect to asteroid mining, the cost of delivering a robotic
spacecraft to rendezvous, mine, and return to an orbital docking
facility with scanned soil samples depends upon the technological
commitment to remote operation, simulation, and the interpretation of
real component descriptors affecting allowable performance
parameters.
[/quote]
Translation: It will dig a huge red ragged hole brimming with red
ink.

[quote]The following article lists costs / 7 year interval to build, operate,
and maintain components of a remote mining system. It is assumed that
a power satellite construction center has already been developed in
order to facilitate a cargo vessel launch and GAMS tracking system.
(GAMS referring to here as a Geosynchronous Asteroid Mining Satelite).

Articles for Development:

Cargo Vessel Propulsion System, Navigation System, and Structural
Shell from the years 2010 – 2017 represent a projected cost in
millions from $235M - $375M.
[/quote]
That's not an estimate, that's a hallucinatory delusion. Your costs
are short by an order of magnitude.

[quote]Mechanical Head Boring Tool, Hydraulics, Power Supply, and
Instrumentation represent a projected cost in millions from $25M -
$115M.

Tray Dump Handling System (Retractable Rail, Hydraulics, Cars &
Canopy, Equipment, Power Supplies, Instrumentation) represent a
projected cost in millions from $30M - $92M.

Regolith Processing (Centrifuge, piping, storage tanks, pumps, ROV’s,
instrumentation, electrical)
represent a projected cost in millions from $12M - $58M.

Geosynchronous Asteroid Mapping Satellite incl. SAR instrumentation,
Booster, ROV mechanical, R&D represent a projected cost in millions
from $21M - $52M.

The TOTAL COSTS incurred for all phases of development represent a
projected cost in millions from $323M - $692 M.
[/quote]
$8 billion easy - If NASA doesn't explode it at launch. Put in for a
TARP.

[quote]The RETURN ON INVESTMENT (ROI) represents a DECREASE IN PERCENTAGE
from 1500% - 1170%!

As one can plainly conclude, the proposed R.O.I. for a precious metal
mining mission far outpaces the mission costs.
[/quote]
Got your eye on a solid iridium asteroid, chump? All the stuff out
there is undifferentiated. If you brought a tonne of precious metal
its value would plummet.

[quote]It should be noted,
however, that with the current I.S.S. (that actually negates the SLI
by its NASA constituents, the earth-to-orbit costs for delivering
modules for construction would offset an R.O.I. by as much as 20%, in
addition to the costs of operating and maintaining a Power Satellite
Construction Center, described in a previous post.
[snip rest][/quote]

Uncle Al apologizes. You are not hallucinating, you are lying.

--
Uncle Al
http://www.mazepath.com/uncleal/
(Toxic URL! Unsafe for children and most mammals)
http://www.mazepath.com/uncleal/qz4.htm

American...

Posted: Thu Nov 05, 2009 10:32 am

Guest

On Nov 5, 7:26 pm, Uncle Al <Uncle... at (no spam) hate.spam.net> wrote:
[quote]American wrote:

What this is about:

Brainstorming or offering a proposal to design and engineer an
extraterrestrial resource development facility for the purpose of
establishing a permanent presence in space for private enterprise
worldwide:

1) You can't visit the asteroid belt and not get fried by
radiation.
[/quote]
I don't believe that that's true.

From an earlier post:

"The low density gases of space consist of hydrogen, helium, protons,
and alpha particles. The gas pressure of interplanetary space is
10**-18 Newtons/meter2, while interstellar space is 10**-27
Newtons/meter2. Space radiation includes cosmic rays,
electromagnetic,
Van Allen Belt, auroral particles, and solar flare particles.
Hypercharged "killer" electrons radiate from the Sun, as well as from
Jupiter at (no spam) 22.2 Mhz, 300Mhz, and 3 Ghz in the decimeter wavelength
(10 cm. and more), especially during *lower* sunspot activity. The
Van
Allen Belts, which consist of the action of charged subatomic parti-
cles, like solar electrons and protons, on the earth's magnetic
field,
produce X rays, UV, and Gamma rays. Particulate radiation consists of
electrons, protons, neutrons, alpha particles, and others. The energy
in the Van Allen Belt normally reaches 1eV, with a density of 10
particles/cm3. Solar activity that induces magnetic storms on the
earth have been known to cause high energy radiation of 10 to 20 keV,
which in turn can induce arc discharges on dielectric surfaces.

In order for a continued presence to be maintained, how do important
people shield themselves? There was an interesting article in the
March '06 issue of Astronomy, which offered a few interesting points:

1) Reinforced polyethelyne 10 times stronger than aluminum
2) Carbon composite structures
3) Plastics (already on ISS)
4) Electric fields
5) Lighter, more flexible space suits
6) Aerogel
7) Dietary supplements

The Jovian environment is one of the richest in heavy ions. Voyager
observations have led to the identification of three sources
for Jupiter's energetic particles: the Sun, the Jovian ionosphere,
and the Jovian moons.

Radio and Plasma wave data were obtained on 12/3/2000 by the
Cassini Radio and Plasma Wave (RPWS) investigation from a
distance of just over 27 million kilometers from Jupiter: During this
time period, the RPWS captured radio emissions generated in the
vicinity of Jupiter. These emissions included decametric radio
emissions originating in the auroral regions of Jupiter.
(Decametric refers to approximate wavelength of radio emissions
(10 meters). At somewhat lower frequencies, near 1 megahertz, the
hectometric radiation, around 100 meters, is generated as a part
of the auroral process at Jupiter. Lower in frequency, near 100
kilohertz, are examples of two types of kilometric radiation.
(Kilometric refers to wavelengths around 1 kilometer or 1000
meters.) Even though these two types of emissions are centered at
about the same frequency, they are thought to originate in totally
different locations and by totally different mechanisms. The
broadband kilometric radiation near the center of the display is
again believed to be generated on field lines associated with the
aurora and probably generated by the same or similar mechanism as
the decametric and hectometric radiation. The narrowband kilometric
radiation is generated near the outer edge of the Io torus, which
remains on a different orbital path than Europa. Data on Quasi-
periodic bursts below about 10 kilohertz consist of brief bursts
and sometimes occur at about 15-minute spacing, and sometimes at
about 40-minute spacing. Even though these emissions were discov-
ered by Voyager and studied by Ulysses and Galileo. Very little is
known about where and how they are generated.

(From: http://www2.jpl.nasa.gov/galileo/messenger/oldmess/Ion.html):

On Jupiter's moon, Io, volcanoes constantly erupt, spewing forth
oxygen and sulphur, which then settle on Io's surface. The inter-
action of Io with Jupiter's magnetosphere strips the oxygen and
sulphur from Io's surface at the rate of 900 kg (1 ton) per second,
tearing these particles from Io's gravitational influence and expel-
ling them into Jupiter's magnetosphere. These particles become elec-
trically charged and many diffuse outward to 1.5 to 3.6 million
kilometers (0.9 to 2.2 million miles) from Jupiter, where they are
accelerated by an interaction with the massive Jovian magnetic
field. Ed explains, "About 0.2% of the original particles, now
highly energized, diffuse back toward Jupiter. The ions may have
left Io at one-thousandth the speed of light. By the time they have
returned to within 700,000 kilometers (420,000 miles) of the planet
(near Europa's orbit), these ions have accelerated to one-tenth
the speed of light (about 30,000 kilometers/second (18,000 miles per
hour))!" Some of these ions travel along Jupiter's magnetic field
lines and spiral into the planet's polar region. In fact, these
heavy ions falling into Jupiter's atmosphere may be the single
largest contributor to Jupiter's auroras."

Radiation proof polymer fabric interwoven into an intelligent
fabric system has the ability to screen out the harmful
frequency range of color force. Intelligent fabric not only
has the ability to protect, but can also become programmed
to enhance the gene expression in terms of response time to
conscious/explicit/dopamine and unconscious/implicit/seratonin
salient signal triggers in a memory enhancing mechanism that
can be worn for incoming hostile environmental sources as
well as outgoing, programmed environmental response signals
from the fabric itself.

Imagine a foil-like suit that is programmed to absorb a certain
bandwidth of frequencies and then reflect a response signal back
to the environment. There are radiation shield polymers that
are absorbent that can be combined with a sensate type liner
that is used to detect and systematically react to the incoming
EMR with a resonant, phase conjugated dispersion source, e.g. in
the yellow spectrum of 5750 - 5850 A. The EMR is thus eliminated
and 'tagged' by visual inspection. The sensate liner simultan-
eously programs the amplification of gene expression in the
carbon-coated rhenium in response for DNA enhancement of the
chromosphere.

A few interesting links:

http://www.lightparty.com/Peace/MiracleInTheVoid.html

which states:

Perhaps the most astonishing finding from cold fusion
research is the apparent observation of radioactivity
reduction in the process! CETI, one of the first cold
fusion companies, recently announced it had been
awarded a US patent on an electrolytic process for
reducing the radioactivity of thorium and uranium. The
company claims its process can reduce the radioactivity
of *radioactive materials* by over 90 per cent in periods
less than 24 hours - compressing into hours what nature
takes billions of years to do. A demonstration of this
seemingly successful process was included in the same
Good Morning America story which described Patterson's
prototype water heater.

Here is a process of extracting Be-7 for the
purpose of Neutron reflecting:

www.ipm.virginia.edu/people/dam2j/MurdickAU1999.pdf

Interesting, but Be-7 is slightly radioactive, and
must be handled w/ extreme care.

So, if a radiation absorbing medium can be made to be
"appreciably thick", perhaps some of the harmful rad-
iation can be "drained off" using the above methods
w/o any harmful exposure effects.

Another link for gamma radiation-proof solvents:

http://www.rsc.org/Publishing/ChemScience/Volume/2006/07/nuclear_indu...

Maybe some kind of "solvent duct" between shell housings
is the application needed for protection.

Here's a link for a radiation proof polymer:

http://www.hnswp.com/pdfs/polymer_leaflet.pdf

(I like the part "Electronic equipment protection from
electromagnetic
pulses, radio wave effects, and solar
radiation interference when directly applied to the
electronic equipment or component").

Protected body suits, gloves, and boots with Demron:

http://www.radshield.com/

"Radiation Shield Technologies (RST) is proud to offer
DemronTM : the new standard in personal radiation pro-
tection. This revolutionary technology is currently
produced as full body suits, gloves and boots. DemronTM
not only protects against particle ionizing/nuclear
radiation (such as Beta and Alpha), but does what NO
OTHER full body radiation protection can do: shield
against X-ray and low-energy Gamma emissions. DemronTM
is non-toxic and completely Lead-free.

DemronTM suits are constructed from a unique nanotech-
nology that far surpasses the effectiveness (or inef-
fectiveness) of current nuclear-biological-chemical
(NBC) suits that only protect against radioactive
particulate sources."

[quote] 2) You can't grab a NEO without getting similarly fried.
[/quote]
[Research above with projected expenses described in last post].

[quote] 3) Robotics suck. You will have no real time control. AI will be
a disaster.
[/quote]
Not ENTIRELY robotic, given the radiative protection described, and w/
human assist (ref. below:)

"This is where the telerobotics operation comes in. Sensor-
derived, teleoperated "mannequins" can perform operations
on the asteroid that are remotely activated and controlled by
the motion and nerve sensors within a teleoperated "suit",
within the confines of the vessel. This is synonymous with
remote control over the internet.

Objects are "felt" by miniature, inflatable bladders within
each suit - no need for AI - its already "built in" as a
working extension of the teleoperator himself.

What makes this system work even better is the ease of
connecting modules of a mining facility with the teleoperated
"mannequins" assisting the field technicians - shift
work can be rotated on/off the surface for continuous
monitoring of all the production systems."

[quote] 4) The solar system is a dusty place to land. Ceramic
microspherules are fantastic for ruining seals and eroding moving
parts in contact. Lunar astronauht lungs took a beating, too.
[/quote]
Inflatable systems were proposed, and as far as I can tell, there is
absolutely nothing wrong with using a ceramic/steel core, unless of
course you want to introduce moving parts into a completely solid
connection:

"The "Center" would be a place developed from LEO from the inside out
where much of the actual construction of an Asteroid cargo vessel
takes place, with some provision for human living quarters, or
"habitcons" available, so that the first ten people that arrive
must be able to work inside an inflatable "bubble" with ceramic/
steel framing surrounding the core. The core "bubble with
ceramic/steel frame" should be assembled, with fully functional
core "habitcons" in under 100 man hours time. The core consists
of an inflatable toroidal bladder that is restrained against ex-
pansion by a web of straps. The straps are attached to a rigid
ceramic/steel frame using clevice/pin(s) on the internal circum-
ference. Eight men, with rotating crews of four, and the remain-
ing two on standby, each working 25 hours in a weeks time, should
have the core project completed and ready for expansion into the
construction center. Once the core is complete, additional modules
for construction are "unpacked" and assembled on to the core by a
crew of four men. The expanded core now includes a cargo bay
storage area with a cryogenic welding supply system in place, as
well as the habitcons with (20) potable water temperature con-
trolled stowages (one for each man). Now the center becomes a
self-sustaining life support area w/ replenishment food, water,
and air, as well as additional modules for construction for the
space station, as well as for the cargo vessel fuselage,
fuel cells, etc."

[quote] 5) 99942 Apophis will be within 15,000 miles of Earth's surface on
13 April 2029. Go grab that.

[/quote]
You're already dead with that. Why not get out of earth orbit while
there's still time to prepare to go interstellar?

[quote]http://en.wikipedia.org/wiki/File:Apophis_pass.svg

4) There's nothing there when you get there. How much asteroid
dirt must you e-Bay to cover your Accounts Payables?

[/quote]
Ever heard of SAR technology? (Nope) I've described in an earlier post
how delta-V's could be arranged to rendezvous between stops on places
like Phobos or Europa, which are far enough away from the most harmful
radiation to be unaffordable, yet within 'slingshot' distance of a
metal-rich NEA. This is an entirely reasonable prospect, given the
orbits and delta-V windows of opportunity that exist.

[quote]This article provides a record of a prospective cost analysis in order
to establish performance parameters.

Projective Expenses

With respect to asteroid mining, the cost of delivering a robotic
spacecraft to rendezvous, mine, and return to an orbital docking
facility with scanned soil samples depends upon the technological
commitment to remote operation, simulation, and the interpretation of
real component descriptors affecting allowable performance
parameters.

Translation: It will dig a huge red ragged hole brimming with red
ink.
[/quote]
How often does a society revolt in order to ensure the survival of its
own sovereignity using commercial viability? There are literally
legions of legalist TORT aggrandizers - invalidators of free market
enterprise - who need to speak with their invalidating constituents
about what is prospectively "invalid", than prospectively a rich
enterprise such as this.

These "invalidators" do this so as to not upset too many of their
trial lawyer friends with their own asses in a sling.

There's your huckleberry, pilgrim.

[quote]
The following article lists costs / 7 year interval to build, operate,
and maintain components of a remote mining system. It is assumed that
a power satellite construction center has already been developed in
order to facilitate a cargo vessel launch and GAMS tracking system.
(GAMS referring to here as a Geosynchronous Asteroid Mining Satelite).

Articles for Development:

Cargo Vessel Propulsion System, Navigation System, and Structural
Shell from the years 2010 – 2017 represent a projected cost in
millions from $235M - $375M.

That's not an estimate, that's a hallucinatory delusion. Your costs
are short by an order of magnitude.

[/quote]
Sure, barring any involvement from beltway rot, which seems to be
perpetrating worldwide by the minute. Care to relocate to Antarctica?
(didn't think so).

Like I said earlier, all prospects for proposals like these get
underfunded and overlicensed on purpose - too many TORT interests that
want to bring society back into the control of the puppetmasters, so
they will seek at all costs to marginalize any attempt to bring the
spirit of entrepreneurialism into the market.
[quote]
Mechanical Head Boring Tool, Hydraulics, Power Supply, and
Instrumentation represent a projected cost in millions from $25M -
$115M.

Tray Dump Handling System (Retractable Rail, Hydraulics, Cars &
Canopy, Equipment, Power Supplies, Instrumentation) represent a
projected cost in millions from $30M - $92M.

Regolith Processing (Centrifuge, piping, storage tanks, pumps, ROV’s,
instrumentation, electrical)
represent a projected cost in millions from $12M - $58M.

Geosynchronous Asteroid Mapping Satellite incl. SAR instrumentation,
Booster, ROV mechanical, R&D represent a projected cost in millions
from $21M - $52M.

The TOTAL COSTS incurred for all phases of development represent a
projected cost in millions from $323M - $692 M.

$8 billion easy - If NASA doesn't explode it at launch. Put in for a
TARP.

[/quote]
There would be better brains at NASA if their shackles to intuition
were removed and they didn't have so many self-righteous bureaucrats
looking over their shoulder - and that's putting it lightly!

[quote]The RETURN ON INVESTMENT (ROI) represents a DECREASE IN PERCENTAGE
from 1500% - 1170%!

As one can plainly conclude, the proposed R.O.I. for a precious metal
mining mission far outpaces the mission costs.

Got your eye on a solid iridium asteroid, chump? All the stuff out
there is undifferentiated. If you brought a tonne of precious metal
its value would plummet.

[/quote]
Again, from an earlier post:

The feasibility of mining an asteroid is multi: First of all,
we need a way to react quickly to an incoming asteroid if the
need arises. For that to happen, we need nuclear space propulsion
systems "on" and "outside" of high earth orbit for the Hohmann
transfer, as well for establishing a base on the surface of
an asteroid.

Secondly, regarding the exploitation of mineral resources, that
if there was more of a need for macroeconomic ripples, you are
allowed to disagree if you believe that the Federal Reserve sets
the rates for platinum, which it would not if the privateers are
the ones who set the price in the first place. Just because there
is "policing" or "fear" that greed will run amok on earth is no
reason to believe that the privateers are a bunch of pirates,
either. You can arbitrarily set the price of platinum as low as
you want, so the resource for platinum will then just "dry up"
without replenishment." All this means is that outside of earth
orbit, there are advantages to being closer to where the mining
takes place."

Space is a completely different country. We really don't need
globalist invalidators to dictate how to spend our own, and rightfully
deserved standard of trade - that being just one of the fringe
benefits of a more massive earth-to-orbit infrastructure.

[quote] It should be noted,
however, that with the current I.S.S. (that actually negates the SLI
by its NASA constituents, the earth-to-orbit costs for delivering
modules for construction would offset an R.O.I. by as much as 20%, in
addition to the costs of operating and maintaining a Power Satellite
Construction Center, described in a previous post.

[snip rest]

Uncle Al apologizes. You are not hallucinating, you are lying.

[/quote]
No need to apologize - you're WAY TO wrong anyway - the I.S.S. for
America is a whole waste of taxpayer's money - just look at the
equipment racks - they're WAY TOO small to do anything really
INDUSTRIAL - like assembling modules for construction in zero gravity!

What HAS the I.S.S. done to contribute to our overall advancing as a
society? (The state-run media complex sure wouldn't report on anything
technologically advantageous & practically free, now would they?

[quote]--
Uncle Alhttp://www.mazepath.com/uncleal/
(Toxic URL! Unsafe for children and most mammals)http://www.mazepath.com/uncleal/qz4.htm- Hide quoted text -

- Show quoted text -
[/quote]

American

American...

Posted: Fri Nov 13, 2009 6:10 am

Guest

The story begins with how the U.S. government became blindfolded with
fear instead of intuitively seeking atomic security regarding the
original Orion Project, which became, by the late 50's, WAY over-
rhetoricized, and carried down through the years, even to the point of
naming a contemporary program after it - ORION (back to the moon
program).

The lack of large stores of weapons material between the superpowers
does not mean that civilian material might be diverted for
centrifuging into weapons-grade - that is the reason for
organizations supporting:

The Non Proliferation Treaty (NPT), the International Atomic Energy
Agency (IAEA), the International Committee for Radiation Protection
(ICRP), Institute for Nucclear Power Operations (INPO), members of the
Initiative for Propliferation Prevention (IPP), Organization for
Economic Cooperation and Development (OECD), Natural Resources Defense
Council (NRDC), Nuclear Regulatory Commission (NRC), United States
Enrichment Corporation (USEC), United Nations Scientific Committee on
the Effects of Atomic Radiation (UNSCEAR), the United States
Binational Commission (USRBC), Committee on International Security and
Arms Control (CISAC), and the Atomic Energy Commission (AEC).

No problem.

There's nothing like a non-lethal pulse unit to begin with.

It would seem to indicate that for the original Orion program, even
the safe use of nuclear pulse units as "bomblets" gets over-
politicized.

American

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