Structural Aluminum Foil

On 6/01/2015 7:20 PM, William Mook wrote:
http://www.shanghaimetal.com/Aluminu...--pds6796.html

8011 aluminum Thickness:0.08 x 119 mm square Weight: 3.07 grams
Temper:H22 O - strain hardened annealed Cost: $10.75 per thousand
sheets + shipping & handling

Aluminium / aluminum 8011 alloy is a wrought alloy.

Chemical Composition

The following table shows the chemical composition of aluminium /
aluminum 8011 alloy.

Element Content (%) Aluminum, Al 97.3 - 98.9 Iron, Fe 0.60 - 1
Silicon, Si 0.50 - 0.90 Manganese, Mn ≤ 0.20 Zinc, Zn ≤ 0.10
Copper, Cu ≤ 0.10 Titanium, Ti ≤ 0.080 Chromium, Cr ≤ 0.050
Magnesium, Mg ≤ 0.050 Remainder (each) ≤ 0.050 Remainder (total) ≤
0.15 Physical Properties

The physical properties of aluminium / aluminum 8011 alloy

Properties Metric.... Imperial Density 2.71 g/cm³ 0.0979 lb/in³


What's its modulus of elasticity?

Sylvia.

On Sunday, January 11, 2015 at 12:36:27 AM UTC+13, Sylvia Else wrote:
On 6/01/2015 7:20 PM, William Mook wrote:
http://www.shanghaimetal.com/Aluminu...--pds6796.html

8011 aluminum Thickness:0.08 x 119 mm square Weight: 3.07 grams
Temper:H22 O - strain hardened annealed Cost: $10.75 per thousand
sheets + shipping & handling

Aluminium / aluminum 8011 alloy is a wrought alloy.

Chemical Composition

The following table shows the chemical composition of aluminium /
aluminum 8011 alloy.

Element Content (%) Aluminum, Al 97.3 - 98.9 Iron, Fe 0.60 - 1
Silicon, Si 0.50 - 0.90 Manganese, Mn ≤ 0.20 Zinc, Zn ≤ 0.10
Copper, Cu ≤ 0.10 Titanium, Ti ≤ 0.080 Chromium, Cr ≤ 0.050
Magnesium, Mg ≤ 0.050 Remainder (each) ≤ 0.050 Remainder (total) ≤
0.15 Physical Properties

The physical properties of aluminium / aluminum 8011 alloy

Properties Metric.... Imperial Density 2.71 g/cm³ 0.0979 lb/in³


What's its modulus of elasticity?

Sylvia.

8011 Aluminum Sheet

Youngs modulus is 70,000 MPa.
Yield stress is 180 MPa
Ultimate Tensile Strength 190 MPa.

Titanium Sheet

Youngs modulus 110,000 MPa
Yield Stress is 225 MPa
Ultimate Tensile Strength 270 MPa

For the size of the tanks shown, maximum internal pressure is 3 atmospheres for the Aluminium variety and 3.7 atmospheres for the Titanium variety. Actual operation will be below this figure - 1.5 to 2.8 atmospheres.

The LOX tank on the Space Shuttle ET operated at 1.5 atmospheres and the LH2 tank on the Space Shuttle ET operated at 2.4 atmospheres.

Pressurization adds to stiffness and strength.

The vessel is small enough to implement an engineered multi-layer insulator approach where reflective and insulating layers are alternatively applied to the finished tank - which is then covered with an ablative thermal protection layer.

http://www.google.com/patents/US8703259

With an inner vessel temperature of 24.3 K (H2 vapor liquid equilibrium at
275 kPa) and outer vessel temperature of 298 K, the total heat leak for the final hydrogen tank is 275 W on the ground- this gives a two day hold time..

On the ground 2.19 kg hydrogen per hour cycled through a MEMS based fuel cell and MEMS based cryocooler, recycles a major portion of the hydrogen (and oxygen) to provide longer term storage.

On Sunday, January 11, 2015 at 2:03:38 PM UTC+13, William Mook wrote:
On Sunday, January 11, 2015 at 12:36:27 AM UTC+13, Sylvia Else wrote:
On 6/01/2015 7:20 PM, William Mook wrote:
http://www.shanghaimetal.com/Aluminu...--pds6796.html

8011 aluminum Thickness:0.08 x 119 mm square Weight: 3.07 grams
Temper:H22 O - strain hardened annealed Cost: $10.75 per thousand
sheets + shipping & handling

Aluminium / aluminum 8011 alloy is a wrought alloy.

Chemical Composition

The following table shows the chemical composition of aluminium /
aluminum 8011 alloy.

Element Content (%) Aluminum, Al 97.3 - 98.9 Iron, Fe 0.60 - 1
Silicon, Si 0.50 - 0.90 Manganese, Mn ≤ 0.20 Zinc, Zn ≤ 0.10
Copper, Cu ≤ 0.10 Titanium, Ti ≤ 0.080 Chromium, Cr ≤ 0.050
Magnesium, Mg ≤ 0.050 Remainder (each) ≤ 0.050 Remainder (total) ≤
0.15 Physical Properties

The physical properties of aluminium / aluminum 8011 alloy

Properties Metric.... Imperial Density 2.71 g/cm³ 0.0979 lb/in³


What's its modulus of elasticity?

Sylvia.

8011 Aluminum Sheet

Youngs modulus is 70,000 MPa.
Yield stress is 180 MPa
Ultimate Tensile Strength 190 MPa.

Titanium Sheet

Youngs modulus 110,000 MPa
Yield Stress is 225 MPa
Ultimate Tensile Strength 270 MPa

For the size of the tanks shown, maximum internal pressure is 3 atmospheres for the Aluminium variety and 3.7 atmospheres for the Titanium variety. Actual operation will be below this figure - 1.5 to 2.8 atmospheres.

The LOX tank on the Space Shuttle ET operated at 1.5 atmospheres and the LH2 tank on the Space Shuttle ET operated at 2.4 atmospheres.

Pressurization adds to stiffness and strength.

The vessel is small enough to implement an engineered multi-layer insulator approach where reflective and insulating layers are alternatively applied to the finished tank - which is then covered with an ablative thermal protection layer.

http://www.google.com/patents/US8703259

With an inner vessel temperature of 24.3 K (H2 vapor liquid equilibrium at
275 kPa) and outer vessel temperature of 298 K, the total heat leak for the final hydrogen tank is 275 W on the ground- this gives a two day hold time.

On the ground 2.19 kg hydrogen per hour cycled through a MEMS based fuel cell and MEMS based cryocooler, recycles a major portion of the hydrogen (and oxygen) to provide longer term storage.

Combined cycle engine, one which uses air to augment thrust at lift off to improve performance;

http://ntrs.nasa.gov/archive/nasa/ca...0110003575.pdf

A compressor blade operated by a ramjet built into the blade. A more advanced version of this;

https://www.youtube.com/watch?v=qs7WlNrHRmA

A supersonic rotor

In the 40s
https://www.youtube.com/watch?v=UFhSzReWTgs

In the 80s
https://www.youtube.com/watch?v=c0Icfopt8Yw

Lifting the spacecraft straight up at 1.5 gees to reach 1 km/sec requires 203.95 seconds of thrust equal to 14.71 Newtons for each kg of take off weight. With an exhaust speed of 1 km/sec for the fan you need 14.71 grams per second to produce that thrust. 14.71 grams per second times 203.95 seconds is 3 kg of air. 3 kg of air moving at 1 km/sec contains 1.5 MJ of energy.. With a prop efficiency of 85% we must add 1.765 MJ to the fan.

This requires 12.45 grams of hydrogen burned in air over the 203.95 seconds for each kg of take off weight.

Which puts you way ahead of a straight rocket take off.

Now, accelerating at 1/2 gee for 203.95 seconds allows the rocket to traverse an arc length of 102 km. A quarter ellipse that is 80 km downrange and 48 km altitude and moving horizontally at 1 km/sec.

The rocket then accelerates another 6.9 km/sec

For each kg of take off weight;

12.45 g - rotor propellant
796.50 g - booster propellant
120.00 g - inert weight
71.05 g - payload

For each 1000 kg of payload weight;

175.23 kg - rotor propellant - 2,504 litres
11,210.42 kg - booster propellant 32,972 litres
1,688.95 kg - inert weight
1,000.00 kg - payload weight.

1.7 m diameter - rotor propellant tank (sphere)
2.1 m diameter booster tank
11.7 m length booster tank

475 kW electrolysis unit in combination with 525 kW cryogenic unit fills tank in 1 week's time.