isp of LOX/Acetylene or LOX/Cyanogen or LOX/carbon subnitride

AIAA Article: (in 2001)

http://arc.aiaa.org/doi/abs/10.2514/2.5833

MIT Technology Review Article: (in 2001)

Pocket Rockets Pack a Punch

First proposed a decade ago, microrocketry is taking off. Before long, dime-sized dynamos may power everything from tiny satellites to "smart dust."

By Alan Leo on May 18, 2001

The rocket ignites. A jet of white-hot flame shoots out below. Its operators increase power and the flame grows-until the rocket explodes in a ball of fire.
Exactly as expected. A dangerous experiment to perform in a lab? Not when the rocket is a dime-sized microelectromechanical system-a so-called MEMS-made of silicon. Laboratories around the country are looking at MEMS rockets and other micropropulsion devices to power a new generation of cheap, tiny satellites and other devices.

Heading for Orbit

The most ambitious project sits in the Massachusetts Institute of Technology's Department of Aeronautics and Astronautics. With NASA support, MIT engineers are building a microrocket that works more or less like the engine on the space shuttle. NASA hopes to use the microrocket for attitude control on future space vehicles, says Alan Epstein, head of MIT's Microengine Project.

MIT's "space cadets," says Epstein, also want to deploy arrays of microrockets to launch tiny satellites about the size of a Coke can. Networks of "nanosats" could support earth observation or satellite maintenance.

The bottom line for an engine is the amount of thrust it generates relative to its own weight. The space shuttle's main engine produces a thrust-to-weight ratio of 70. MIT's microrocket has reached 85, and its builders estimate a potential ratio more than 10 times that-more than enough to launch a satellite into space.

"We're looking at very high thrust-the high-performance end of microrocket engines," Epstein says. That is what sets the MIT project apart from microrocket efforts at the University of California at Berkeley, Caltech and elsewhere, he explained.

Epstein says the MIT project is on track to produce a working, integrated microrocket by the end of 2003. The next milestone comes this September, when Epstein aims to build a working MEMS turbopump, a key component that will inject fuel into the rocket's combustion chamber at very high pressure.

AIAA Article (in 2009 - 5 years ago!)

http://enu.kz/repository/2009/AIAA-2009-4824.pdf

CONSIDER

A sphere of titanium 1.5 meters in diameter equipped with an array of micro-rockets capable of drawing a thrust vector in any direction on the surface of the sphere. The MEMS devices on board also operate as a synthetic aperture optical antenna system that sends and receives in all directions at once, as well as a camera array that looks in all directions at once.

https://www.youtube.com/watch?v=c8xjXqC9m2A

Magnesium oxygen flow batteries have been around since the 1940s. Small MEMS based systems that use the Magnesium oxygen mixture with a patented filtrating electrode provide copious electrical power with no waste heat at very high efficiency (higher than hydrogen oxygen fuel cell efficiencies) producing 3 kWh of electrical energy per kg of propellant.

Propelled by LOX/Magnesium high density monopropellant the titanium sphere carries 2,529.1 kg and masses only 75 kg empty. With an exhaust speed of 4..2 km/sec at sea-level and 4.7 km/sec in vacuum, this is a 34.72 to 1 mass ratio with a top end speed of 16.67 km/sec!

Enough to fly to the moon and back!

Using a 550 nm wavelength, the 1.5 meter diameter antenna forms an Airy disk

384,400,000 * 1.22 * 550e-9/1.5 = 171.95 meters

in diameter.

A similar system on the ground sends data to the space borne system, and helps locate the spacecraft, by sweeping through its expected path, and measuring response times of pings.

Not too shabby.


http://www.nasa.gov/press/2013/octob...s-to-and-from/

Panoramic views of the Apollo landing sites and Lunikhod sites can be taken with recovery of the ship, and return to Earth!

Success with this system, will provide a means to create a piloted system, carrying a 145 kg astronaut - using a long-duration space suit whilst carrying his/her own supply of hydrogen/oxygen - capable of re-entry without a capsule.

Similar to this;

https://www.youtube.com/watch?v=FHtvDA0W34I

Except using small rocket arrays in tiny winglets in the backpack to execute a powered touchdown (and maintain attitude control)

http://www.wired.com/2013/07/lunar-flying-units-1969/

This is less massive than a parachute, more capable as well, while permitting astronauts on the moon to traverse large distances - visiting several Apollo landing sites for example.

Five 1.5 m diameter spheres, each emptying in sequence, carrying a single astronaut, achieves 16.69 km/sec;

13165.5 10561.4 7957.3 5353.2 2749.1 Total Mass
2529.1 2529.1 2529.1 2529.1 2529.1 Propellant Mass
0.1921 0.2394 0.3178 0.4724 0.9199 Propellant Fraction
0.8959 1.1496 1.6064 2.6859 10.6066 Stage Delta Vee
0.8959 2.0456 3.6520 6.3379 16.9446 Total Delta Vee

The spare capacity is used to traverse the lunar surface. With suspended animation a solved problem,and with Ex-Rad radiation drug, we can even go to Mars with this system!

Here's what Wikipedia has to say;

Beryllium is the chemical element with the symbol Be and atomic number 4. Because any beryllium synthesized in stars is short-lived, it is a relatively rare element in the universe. It is a divalent element which occurs naturally only in combination with other elements in minerals. Notable gemstones which contain beryllium include beryl (aquamarine, emerald) and chrysoberyl. As a free element it is a steel-gray, strong, lightweight and brittle alkaline earth metal.

Beryllium improves many physical properties when added as an alloying element to aluminium, copper (notably the alloy beryllium copper), iron and nickel. Tools made of beryllium copper alloys are strong and hard and do not create sparks when they strike a steel surface. In structural applications, the combination of high flexural rigidity, thermal stability, thermal conductivity and low density (1.85 times that of water) make beryllium metal a desirable aerospace material for aircraft components, missiles, spacecraft, and satellites.[3] Because of its low density and atomic mass, beryllium is relatively transparent to X-rays and other forms of ionizing radiation; therefore, it is the most common window material for X-ray equipment and components of particle physics experiments.[3] The high thermal conductivities of beryllium and beryllium oxide have led to their use in thermal management applications.

The commercial use of beryllium requires the use of appropriate dust control equipment and industrial controls at all times because of the toxicity of inhaled beryllium-containing dusts that can cause a chronic life-threatening allergic disease called berylliosis in some people.

* * *

So, yeah, care must be taken, as in most things. I wouldn't use it as a propellant because of its cost and limited production. Toxicity would be a secondary consideration.

That's why I like hydrogen/oxygen rocket and magnesium/oxygen hybrid rocket..

Analysis is the detailed examination of the structure of something. In the case of a rocket based mission you examine the delta vee requirements and capabilities and what that implies for the selected materials and propellants in terms of mass and volume.

Here are some references for those who want more detailed tools than the rocket equation and the delta vee chart for minimum energy transfers between worlds;

http://design.ae.utexas.edu/mission_...n_Planning.pdf

http://www.scisys.co.uk/where-we-wor...-planning.html

In article ,
says...

Graphite nanoparticles in hydrogen peroxide create a cool monopropellant

2 H2O2 + C == 2 H2O + CO2

snip

ignites with the addition of a small quantity of silver laced
water injected into the micro-engine.

snip

http://www.rocketlab.co.nz/propulsio...onopropellant/

Oh look, yet another tiny research project being tested in a lab.
There is never a shortage of research which looks promising. Come back
when this thing actually flies which would demonstrate that these exotic
propellants can be used in a *practical* rocket design.


Coated magnesium nanoparticles suspended in Liquid Oxygen do the
same thing that we did with graphite and hydrogen peroxide.

More exotic rocket propellant excrement.

snip

OMG you're absolutely fracking nuts. You're talking about finding "the
holy grail" of rocket propellants. Better men than you have been trying
to do this since the days of Robert H. Goddard and Wernher von Braun,
and failed. Plus, they actually had reams of experimental data to back
up their assertions. You've got squat other than a link or two to very
small scale lab research.


Look, there are plenty of *theoretical* propellants which give great
performance, but turn out to perform poorly or at best mediocre. Even
worse, some which do look to have promising performance turn out to be
fought with other headaches which make the propellant combination
expensive and/or impractical when the engine/tank/etc. designs are
brought up to full scale (i.e. for an orbital launch vehicle). Small
scale lab experiments with non-flight weight hardware proves little.

Face it, your intellectual masturbation isn't going to result in an
actual launch vehicle unless you start actually building and flying
hardware, which we all know you're not doing.

Jeff
--
"the perennial claim that hypersonic airbreathing propulsion would
magically make space launch cheaper is nonsense -- LOX is much cheaper
than advanced airbreathing engines, and so are the tanks to put it in
and the extra thrust to carry it." - Henry Spencer

http://www.stanford.edu/~cantwell/Re...2013-3899..pdf

https://fenix.tecnico.ulisboa.pt/dow...Tese_48751.pdf

http://nopr.niscair.res.in/bitstream...%20293-310.pdf

Magnesium powder in plastics, form fuel grains that were successfully used with LOX since the 1940s. Lox/lithium formed a very high performance rocket used in drones in the 1960s.

http://www.lpi.usra.edu/publications...1063/Rowan.pdf

Magnesium LOX hybrid rockets are being explored as a means to refuel on Mars, since 8.4% of the Martian soil is magnesium oxide.

The use of this type of rocket on the moon is also the focus of intense study;

https://www.jstage.jst.go.jp/article...080tp/_article


On Tuesday, April 29, 2014 1:58:58 PM UTC+12, William Mook wrote:
Graphite nanoparticles in hydrogen peroxide create a cool monopropellant



2 H2O2 + C == 2 H2O + CO2



So, each kg of mono-propellant requires 850 grams of hydrogen peroxide which occupies 586.2 millilitres of fluid in which 150 grams of graphite nanoparticles are suspended - occupying an additional 67.2 milliliters when fully mixed. This results in a monopropellant that is 1.53 kg/litre and ignites with the addition of a small quantity of silver laced water injected into the micro-engine.



http://www.rocketlab.co.nz/propulsio...onopropellant/



High density storeable monopropellant means very low structural fraction. Exhaust velocity is 3.5 km/sec at Sea Level and rises to 3.8 km/sec in vacuum.



Coated magnesium nanoparticles suspended in Liquid Oxygen do the same thing that we did with graphite and hydrogen peroxide.



For each kilogram of the monopropellant take 409.73 grams of liquid oxygen that oxxupy 359.10 millitres and mix in 590.27 grams of magnesium nanoparticles (coated with an inert layer) which adds another 339.63 millilitres to the monopropellant - bringing its total volume for 1 kg to 698.73 millilitres - obtaining a density of 1.431 kg/litre.



At 90K this isn't too shabby! The coolest part is that the Gibbs free energy is so high that its exhaust velocity is 4.2 km/sec at Earth's surface and 4.7 km/sec in vacuum. Largely matching the performance of hydrogen oxygen with propellant that is more than 4x as dense and not as difficult to store. Also, careful selection of the coating permits the propellant to operate as a hypergolic mixture that bursts into flame when heated to moderately high temperatures.



Another benefit is that the surface of the moon, according to Apollo sampling, is 11.9% magnesium-oxide! That means that we can land a solar powered machine on the moon, isolate the magnesium-oxide, and break the material down into magnesium and oxygen, and mix the two together. This means that the moon is a fuel depot using this propellant!



http://www.nss.org/settlement/nasa/7.../4appendI.html

In article ,
says...
http://www.stanford.edu/~cantwell/Re..._2013-3899.pdf

https://fenix.tecnico.ulisboa.pt/dow...Tese_48751.pdf

http://nopr.niscair.res.in/bitstream...%20293-310.pdf

Magnesium powder in plastics, form fuel grains that were successfully used with LOX since the 1940s. Lox/lithium formed a very high performance rocket used in drones in the 1960s.

http://www.lpi.usra.edu/publications...1063/Rowan.pdf

Magnesium LOX hybrid rockets are being explored as a means to refuel on Mars, since 8.4% of the Martian soil is magnesium oxide.

The use of this type of rocket on the moon is also the focus of intense study;

https://www.jstage.jst.go.jp/article...080tp/_article


All I see is more p0rn for your mental masturbations. Cue the lotion
and tissues... Cleanup needed in Mookie's office!

Jeff
--
"the perennial claim that hypersonic airbreathing propulsion would
magically make space launch cheaper is nonsense -- LOX is much cheaper
than advanced airbreathing engines, and so are the tanks to put it in
and the extra thrust to carry it." - Henry Spencer

MEMS bipropellant rocket
http://www.las.inpe.br/~jrsenna/Aero...av2997p1-7.pdf

Metal LOX Hybrid rocket
http://www.lr.tudelft.nl/organisatie...ockets/hybrid/

MEMS based rockets have 1000 to 1 thrust to weight 20x the SSME and power densities of 400 W/millimeter^3 which is 200x the highest power density reported for macroscopic engines. 416,600 N/m2 (42,500 kg/m2) thrust is extraordinarily high.

LOX/metal hybrid rockets have a long history. Aluminum for example burning with LOX to form Aluminum Oxide (Al2O3) with a free energy of 1582.3 kJ/mol with 101.16928 grams/mol.

N At Wt. litre kg/ltr kg/kg

2 26.98154 0.19587 2.702 0.52925
3 15.9994 0.41293 1.14 0.47075

Total 0.60880 1.642 1.00000

With an efficiency of 70% exhaust speeds of 4661.1 m/sec are attained and propellant densities of 1.6425 kg/litre are achieved.

Consider a 4,764.7 mm diameter sphere containing 93 metric tons of propellant - made of colloidal aluminum coated with an inhibiting agent that is inactivated by heat, floats within liquid oxygen. The tank itself is 5 metric tons. A 450 mm wide strip 3,369.2 mm in diameter at the base of the spherical tank, forming a truncated aerospike nozzle into which the sphere comfortably rests. The engine is capable of producing up to 200,000 kgf thrust. The ring itself masses 0.2 metric tons with another 1.8 metric tons of hardware. This forms a tank with a total mass of 100 metric tons, capable of producing 200 tons of force thrust whilst carrying 93 tons of propellant.

Now consider seven such tanks in a hexagonal close packed array, connected to one another, and equipped with cross feed forming a disk 14,294.2 mm in diameter and 4,764.7 mm tall.


88 payload

93 propellant
7 structure

4.66 km/sec - exhaust velocity

S1 S2 S3 Stage

788 388 188 Stage mass
372 186 93 Propellant mass

0.4720 0.4793 0.4946 Propellant fraction

2.9768 3.0417 3.1807 Stage velocity
2.9768 6.0186 9.1993 Vehicle velocity

The spheres are attached to a mobile vehicle by hold down clamp, and are capable of independent movement. Prior to launch they are loaded up with propellant, connected together and move to their launch position. All engines fire up and the system is released. The mobile vehicle moves to a recovery rail. The vehicle rises, draining propellant from four of the seven tanks, forming the first stage. When empty those tanks are released. Two of the three remaining tanks are emptied, propelling all forward. When empty those two are released. Finally, the last tank is expended accelerating the vehicle to orbital velocity.

This arrangement of spheres places 88 metric tons into LEO whilst consuming $750,000 worth of propellant. The spheres cost a total of $14 million for the set, with improvements, and are highly reusable - 560x implies a $25,000 for CAPEX, and another $225,000 for operational costs.

The tanks slow to subsonic speeds and deploy inflatable winglets. They are snagged by tow planes operating down range. These planes tow the spheres back to the launch center where they are released above a special capture rail. Operating on the rail is a special capture vehicle that matches the speed and position of the sphere as it glides into the rail. The sphere is caught and held by the rail riding vehicle with a hold down clamp. The vehicle then slows to a stop at the end of the rail. The vehicle leaves the rail and moves to a site where the wings are stowed, the sphere is cleaned up, and refilled, ready to be assembled with the other spheres for another launch.

http://www.theguardian.com/world/vid...-carrier-video

A 3,730.7 mm diameter sphere sits atop the central sphere which is part of the payload on orbit. It contains 44,655 kg of propellant and masses 2,345 kg empty. It has a smaller ring of MEMS based rockets. This propels 41,000 kg into a lunar free return trajectory.

Six spherical tanks 1,751.7 mm in diameter situated in a ring whose outer diameter is 4,764.7 mm in diameter sit atop the smaller spherical tank and beneath a hemispherical shell 2,382.4 mm tall. The six tanks carry a total of 27,567.3 kg of propellant. 5,432.7 kg is the inert weight of the six tanks and hemispherical cabin, leaving 8,000.0 kg of payload - that descends to the lunar surface and returns to Earth!

Passenger versions of this vehicle put 20 people on the lunar surface with 5,100 kg of payload. Twenty seats in a ring facing outward - each with its own access door to the outside, and to the interior, occurring in pairs of two. Passengers and crew wear a custom designed biosuit the entire trip, and each has its own supply of food, air, water, waste management, etc., for up to 12 days.

At $2 million each, and 15 paying passenger (with a crew of 5), a first flight pays for the entire system. After that, additional flights earn $30 million each.

With departures 3x daily, the seven launch elements are sufficient to meet the demand. The lunar insertion stage takes 7 days, and so 21 of these stages are required to meet demand. The lunar landing stage takes 11 days and so 33 of these are required to meet demand. Three flights carrying 45 people in total is sufficient to cover the cost of all these elements, plus spares, plus supply chain, plus launch centre. The supply chain builds 7 launch elements every six months - as they reach their 560 flight limit.

Sixty people a day means 21,915 people visit the moon each year earning $43..83 billion each year. According to Credit Suisse there are 29 million people with over $1 million in their bank accounts, 880,000 with more than $5 million in their bank accounts. A 5% market penetration of these high net worth individuals fulfills this demand.

The $100 million+ housing market is expanding.

http://realestate.msn.com/article.as...entid=22710353

There is a growing demand for unique homes $100 million and more. 450 homes per year sold to a handful of the wealthiest lunar travellers earn another $450 billion - and support the supply chain for a lunar city.

Aluminum oxide is plentiful on the moon, and with appropriate hardware, LOX/Aluminum hybrid fuel is easily prepared.