Thanks for the thumbs up and hearty welcome Tom2Mars and StarLab. Good to be aamong friends and fellow manned space enthusiasts.


Actually the path to my warp drive began with a few simple steps. In 1963, I
read a signed 1955 work of Albert Einstein correcting the public
misconception that he taught of a universal light speed limit. He said he
never taught that as it was possible that a machine, other than a particle
accelerator, could be found to exceed light speed. I went looking for that
machine with out knowing if I was a victim a faked signature hoax or if he
was right or wrong.

Any how I lost the reference in 1968 so I found this reference some 40 years later.................
Therefore I conclude Einstein indeed denied ever making a light speed limit for mass claim or ever constructing such a mechanics as Henry Poincare suggested in 1904 perhaps must be constructed.

In high school in 1966, I calculated that if a object of mass was dropped into
a hypothetical constant one g gravity field of unlimited size for >355.25 days
of 1 g acceleration it would exceed light speed regardless of the mass and
energy as Velocity=Acceleration times time without mass and energy being
in the calculation.

Of course the 1 g field of unlimited size does not exist in nature, so one has
to create an artificial 1 g field using Einstein's equivalence principal of general
relativity combing gravity with inertia stating the effects of equal acceleration
and gravity are equal and indistinguishable from each other.

Looking at chemical rockets in production, I found one capable of perhaps 15
g of acceleration for perhaps 15 minutes which is the the same power as a
constant 1 g acceleration for several or more hours (3.75). Doing a little
ballpark math as there are 8544 hours at 1 g to light speed and dividing that
by 3.75 hours returns 2278.4. I therefore I would need 2278.4 times the time
of acceleration of chemical rockets to date hence 2,238 times the power.

It was clear I would need an atomic powered rocket.

Atomic power has 10^7 (fission) and 10^9 (fusion) times the power (enmergy density) of equal masses of chemical rocket engines when both operate near 100 percent efficiency. Therefore ideally I could accelerate at 1 g times 10,000,000 times 3.75 hours - 1,000,000,000 times 3.75 hours = warp speed 4389 to 438900

As both fission and fusion reactions are present in all known atomic powered
machines then a hybrid fission/fusion engine at 10^8 times the power of
equal mass of chemical rocket would reach warp speed 43890 in 42778
years and since I only need 49 years ship time at 1 g wrt ship to reach the
edge of the observable universe than a very inefficient atomic rocket at .1%
efficiency would do the job. If I could only get 1 g wrt earth I could still reach
all stars withing 43,000 light years distance from earth.

Calculating the efficiency (output power / (output power plus power losses)
known atomic rockets with best calculated trip time to near star at 45 years

such as:

Project Orion (pulse drive)
=.00025 %
Nuclear electric Propulsion (NEP)(ion drive - Project Vasimar)
.001 % efficiency
Nuclear thermal Propulsion (NTP) (solid core - Project Nerva)
= .0001 % efficiency
reference http://www.islandone.org/APC/Nuclear/chemnuke.gif
www.islandone.org/APC/

Therefore I needed to invent an engine operating near 100% as that is
common with chemical rockets. An necessity is indeed the mother of invention. I became a mom giving birth to a new invention so to speak. Easy to do as I was a teenager, but painful as I spent the next 33 years convincing others I was not crazy as I lost the signed Einstein work.

As Mass times velocity of exhaust = mass times velocity of rocket I just reduce the the 100,000 tons of the Mars rocket mass to 100 tons to achive warp speed 1.7


For the sample mars trip..
Trip length: 1.1521E-5 light years(ly).
Acceleration: 1.0 g.
Time on earth: 0.006683627669698874 years. (1.73 days)
Time on ship: 0.00668361442242196 years.

Velocity wrt earth = 0.0017237644838045070670356650784331
Velocity wrt ship = warp speed 0.0017237679003967890619212280596506

As the engineering constants have not been calculated
by physical measurement from 100's of atomic Rocket
engine tests like they have been measured and calculated
for chemical rockets I cannot just calculate
them looking up some values in engineering constant tables
as they do not exist yet for atomic engines.

Therefore I have to use analytic methods to calculate them
based on empirical equations.

Quote:
--------------------------------------------------------------------------------
Einstein-At times like this when physical evidence
is not available one can rely on closeness to
experience (empirical evidence)"
--------------------------------------------------------------------------------

In Little boy bomb tests the ideal shape for the gunpowder chamber was an elliptical cavity of eccentricity if 1/4 of width to length, In that manner the minimum volume of gun powder was found to accelerate the uranium disk (10kg) 70%U235 and it's tamper (40kg)99%U238 to some 3,000 miles per hour to collide with a fixed 70%U235 disk.

Giving a disk face Force of impact (Fi)=MVR with R being a constant of rigidity twixt zero and one with one being diamond Uranium being .98 Guinness world record pressure was achieved.

I use the same shape for my plasma chamber with the super critical mass at one focus and the liquid reduction nozzle at the other as any ray or particle of water or steam heated gaining velocity in any direction from the metal plasma's temperature of above 50,000 Kelvin will bounce (reflect) off the chambers walls arriving at the exhaust convergent nozzle entrance. Likewise the balancing force of all the pressure reflected from the chamber walls arrives at the plasma wall of a magnitude psi = x(surface area of plasma chamber) / 2(surface area of plasma).

This keeps it solid and in position as if it moves then the pressure opposite the direction it moves to drops and the low pressure and the local chamber pressure the direction it moves to increases and therefore the unbalanced force accelerate the plasma ball back to it's focus.

The constant 1/2 is in the above equation as half the chamber wall pressure is on one focus and half on the other.

Using just the exhaust velocity required for the Mars ship, I can now build my engine from the exhaust port forward like they did the Redstone sounding rocket knowing just the exhaust velocity required.

Total impulse 1000 tons Ve= 481299839.94 feet/sec times 1000 tons

Using a 1000 :1 reduction nozzle the velocity of average exhaust particle mass of a hydrogen atom, the mass flow rate and thus pressure remains the same at the entrance and exits with the in and out area of 1000 :1

The velocity of the mass it the entrance area of a plane intersecting the chamber at the aft focus is 481299 feet/sec and since this area is approx. 1/16 the surface area of the chamber the average velocity a typical particle colliding with the wall is 30081 feet per second or approx Mach 29 with Mach = speed of sound.

Convergent nozzles for A titanium circulating band saw using a band of sandy water flash heated to steam obtains an exhaust velocity of Mach seven to cut the titanium. The steam than cools back to water and reheated circulating like the continuous loop band in a metal band saw.

Chemical rockets chamber velocities are limited to Mach one at the convergent divergent nozzle choke point as the shock wave from breaking the sound barrier blocks the chamber causing the chamber to explode at higher velocities therefore they use the divergent nozzle outside the chamber
to get supersonic exhaust velocities.

When these rockets as Polaris missiles were fired underwater from a submarine launch tube, the water blocked the divergent nozzle causing the internal chamber pressure to build up making the rocket explode like a bomb. They solved the problem by ejecting the rockets from the launch tube with large amounts of steam or air creating gas large bubbles around the exhaust port to keep the exhaust nozzle open and at low pressure. Once the engine starts it works fine underwater.

Likewise for atom rocket exhaust velocities exasperating the problem, air itself will block the nozzle with the same effect. Therefore atomic rockets of my design must be started from a launch tube underground in which most of the air has been removed.

Putting my head in a Saturn 5 exhaust nozzle, I observed how flimsy the nozzle and chamber were consisting of relative thin structures to keep the mass required to a minimum. Atomic rockets do not have this mass constraint.

Spherical pressurized oxygen chambers used in buzz bombs of world war II have the thin iron walls wrapped with iron wire so they can be highly pressurized.

My engine therefore would be approx 100 tons 20 feet long (10 foot plasma chamber plus 10 foot reduction nozzle) with walls two feet thick of water cooled cast iron as it has one of the strongest molecular binding energy known. It is then wrapped with two feet thick 1/4 inch Iron wire topped with 900 ton tank of water propellant.

I will then test three 1/5 scale models to destruction with incrementally higher super critical masses until its operational limits are determined and measured expecting it to obtain the required exhaust velocities building one same scale flight test engine with 50% more engine mass added providing a safety factor of 50%. I will then build operate the full scale engine at 50% max rated power, to extend it's life and number of firings. I then will place all the mass (approx 100,000 tons) I can get on it while maintaining a constant one g acceleration for manned flights or (approx 7692 tons) at 13g for unmanned flights.

__________________
Thomas Hulon Jackson
Scientist/Engineer/Technician