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USA to return to Moon



 
 
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  #1  
Old May 9th 16, 02:15 AM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default USA to return to Moon

The External Tank sized flight system, using LOX/LNG combination, with aerospike, thermal protection system, and recovery hardware attached... similar to a Falcon-R booster. Looking first at the Space Shuttle External Tank:

Technical specifications
SLWT Specifications

Length: 153.8 ft (46.9 m)
Diameter: 27.6 ft (8.4 m)
Empty Weight: 58,500 lb (26,500 kg)
Gross Liftoff Weight: 1,680,000 lb (760,000 kg)
LOX tank

Length: 54.6 ft (16.6 m)
Diameter: 27.6 ft (8.4 m)
Volume (at 22 psig): 19,541.66 cu ft (146,181.8 US gal; 553,358 l)
LOX mass (at 22 psig): 1,387,457 lb (629,340 kg)
Operation Pressu 20-22 psi (140-150 kPa) (gauge)
Intertank

Length: 22.6 ft (6.9 m)
Diameter: 27.6 ft (8.4 m)
LH2 tank

Length: 97.0 ft (29.6 m)
Diameter: 27.6 ft (8.4 m)
Volume (at 29.3 psig): 52,881.61 cu ft (395,581.9 US gal; 1,497,440 l)
LH2 mass (at 29.3 psig): 234,265 lb (106,261 kg)
Operation Pressu 32-34 psi (220-230 kPa) (absolute)
Operation Temperatu -423 °F (-252.8 °C)

So, the LOX tank is 553.4 cubic meters. The LH2 tank is 1,497.5 cubic meters. The intertank is 382.4 cubic meters. A total of 2,413.3 cubic meters. A common bulkhead between LOX and LNG makes the extra volume available for propellant. At 830 kg/m3 the total propellant weight is 2,003,039 kg. 527,115.6 kg of LNG aft of the bulkhead and 1,475,923.4 kg of LOX forward of the bulkhead.

Total mass of the tank is less than the SWLT figures becuase
a) LNG is less difficult to keep cool than LH2,
b) common bulkhead between tanks is lighter than two separate tanks with intertank.

Conservatively let's keep the 26,500 kg for the tank mass.

A Raptor LOX/LNG engine produces 230,000 kgf of thrust and has a 3.6 km/sec exhaust speed in vacuum. 14 of these engines produce 3,220,000 kgf thrust with a 3.4 km/sec exhaust speed at sea level, when arranged around an aerospike engine at the base of the External Tank.

The weight of this arrangement is 26,850 kg. Another 21,700 kg of mass is used for the recovery system and landing gear. A total of 75,000 kg of inert mass per element.

Take off Weight: 2,078,039 kg
Empty Weight: 75,000 kg
Thrust Max: 3,220,000 kgf
Exhaust (sl) 3,400 m/sec
Exhaust (vac) 3,600 m/sec


Vf = 3,500 * LN( 2,078,039 / 75,000 ) = 11,625.9 m/sec

It can lift 80,830 kg into LEO as a SSTO.

Three tanks operated in two stages, with the two outboard tanks feeding the central set of engines during boost, and then falling away, to be recovered down range, are capable of lifting 391,000 kg into LEO.

Tanking an external tank of the size just described, and removing 25,000 kg of engines and insulation, reduces mass to 50,000 kg. Carrying 274,247.4 kg of propellant in a small set of tanks at its base, the tank becomes a version of Skylab - only larger. It is capable of carrying 66,752.6 kg of payload to low lunar orbit and back.

As a cruise ship, each person masses an average of 80 kg, and has another 60 kg allocated to them. A total of 140 kg. Another 619.2 kg of propellant to power rocket belts, provide the ability to take 88 people to the moon and back, and allow them to visit three spots anywhere on the lunar surface!

http://rocketbelt.nl/pogos/nasa-lunar-transport

https://airandspace.si.edu/research/...inding_Aid.pdf

The recurring cost, with reusable ships and propellant costs of $0.16 per kg, is around $15,000 per person. The flight could be filled at $515,000 per person, earning $44 million per month.



  #2  
Old May 9th 16, 02:42 AM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default USA to return to Moon

On Monday, May 9, 2016 at 1:15:47 PM UTC+12, William Mook wrote:
The External Tank sized flight system, using LOX/LNG combination, with aerospike, thermal protection system, and recovery hardware attached... similar to a Falcon-R booster. Looking first at the Space Shuttle External Tank:

Technical specifications
SLWT Specifications

Length: 153.8 ft (46.9 m)
Diameter: 27.6 ft (8.4 m)
Empty Weight: 58,500 lb (26,500 kg)
Gross Liftoff Weight: 1,680,000 lb (760,000 kg)
LOX tank

Length: 54.6 ft (16.6 m)
Diameter: 27.6 ft (8.4 m)
Volume (at 22 psig): 19,541.66 cu ft (146,181.8 US gal; 553,358 l)
LOX mass (at 22 psig): 1,387,457 lb (629,340 kg)
Operation Pressu 20-22 psi (140-150 kPa) (gauge)
Intertank

Length: 22.6 ft (6.9 m)
Diameter: 27.6 ft (8.4 m)
LH2 tank

Length: 97.0 ft (29.6 m)
Diameter: 27.6 ft (8.4 m)
Volume (at 29.3 psig): 52,881.61 cu ft (395,581.9 US gal; 1,497,440 l)
LH2 mass (at 29.3 psig): 234,265 lb (106,261 kg)
Operation Pressu 32-34 psi (220-230 kPa) (absolute)
Operation Temperatu -423 °F (-252.8 °C)

So, the LOX tank is 553.4 cubic meters. The LH2 tank is 1,497.5 cubic meters. The intertank is 382.4 cubic meters. A total of 2,413.3 cubic meters. A common bulkhead between LOX and LNG makes the extra volume available for propellant. At 830 kg/m3 the total propellant weight is 2,003,039 kg. 527,115.6 kg of LNG aft of the bulkhead and 1,475,923.4 kg of LOX forward of the bulkhead.

Total mass of the tank is less than the SWLT figures becuase
a) LNG is less difficult to keep cool than LH2,
b) common bulkhead between tanks is lighter than two separate tanks with intertank.

Conservatively let's keep the 26,500 kg for the tank mass.

A Raptor LOX/LNG engine produces 230,000 kgf of thrust and has a 3.6 km/sec exhaust speed in vacuum. 14 of these engines produce 3,220,000 kgf thrust with a 3.4 km/sec exhaust speed at sea level, when arranged around an aerospike engine at the base of the External Tank.

The weight of this arrangement is 26,850 kg. Another 21,700 kg of mass is used for the recovery system and landing gear. A total of 75,000 kg of inert mass per element.

Take off Weight: 2,078,039 kg
Empty Weight: 75,000 kg
Thrust Max: 3,220,000 kgf
Exhaust (sl) 3,400 m/sec
Exhaust (vac) 3,600 m/sec


Vf = 3,500 * LN( 2,078,039 / 75,000 ) = 11,625.9 m/sec

It can lift 80,830 kg into LEO as a SSTO.

Three tanks operated in two stages, with the two outboard tanks feeding the central set of engines during boost, and then falling away, to be recovered down range, are capable of lifting 391,000 kg into LEO.

Tanking an external tank of the size just described, and removing 25,000 kg of engines and insulation, reduces mass to 50,000 kg. Carrying 274,247.4 kg of propellant in a small set of tanks at its base, the tank becomes a version of Skylab - only larger. It is capable of carrying 66,752.6 kg of payload to low lunar orbit and back.

As a cruise ship, each person masses an average of 80 kg, and has another 60 kg allocated to them. A total of 140 kg. Another 619.2 kg of propellant to power rocket belts, provide the ability to take 88 people to the moon and back, and allow them to visit three spots anywhere on the lunar surface!

http://rocketbelt.nl/pogos/nasa-lunar-transport

https://airandspace.si.edu/research/...inding_Aid.pdf

The recurring cost, with reusable ships and propellant costs of $0.16 per kg, is around $15,000 per person. The flight could be filled at $515,000 per person, earning $44 million per month.


A seven element booster consisting of four first stage elements, two second stage elements and a single central third stage element, lifts 995,000 kg into LEO. Landing the tank plus 181,460 kg on the lunar surface.

This seven element system also puts up a 21.8 GW solar power satellite.

  #3  
Old May 9th 16, 08:29 AM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default USA to return to Moon

On Monday, May 9, 2016 at 1:15:47 PM UTC+12, William Mook wrote:
The External Tank sized flight system, using LOX/LNG combination, with aerospike, thermal protection system, and recovery hardware attached... similar to a Falcon-R booster. Looking first at the Space Shuttle External Tank:

Technical specifications
SLWT Specifications

Length: 153.8 ft (46.9 m)
Diameter: 27.6 ft (8.4 m)
Empty Weight: 58,500 lb (26,500 kg)
Gross Liftoff Weight: 1,680,000 lb (760,000 kg)
LOX tank

Length: 54.6 ft (16.6 m)
Diameter: 27.6 ft (8.4 m)
Volume (at 22 psig): 19,541.66 cu ft (146,181.8 US gal; 553,358 l)
LOX mass (at 22 psig): 1,387,457 lb (629,340 kg)
Operation Pressu 20-22 psi (140-150 kPa) (gauge)
Intertank

Length: 22.6 ft (6.9 m)
Diameter: 27.6 ft (8.4 m)
LH2 tank

Length: 97.0 ft (29.6 m)
Diameter: 27.6 ft (8.4 m)
Volume (at 29.3 psig): 52,881.61 cu ft (395,581.9 US gal; 1,497,440 l)
LH2 mass (at 29.3 psig): 234,265 lb (106,261 kg)
Operation Pressu 32-34 psi (220-230 kPa) (absolute)
Operation Temperatu -423 °F (-252.8 °C)

So, the LOX tank is 553.4 cubic meters. The LH2 tank is 1,497.5 cubic meters. The intertank is 382.4 cubic meters. A total of 2,413.3 cubic meters. A common bulkhead between LOX and LNG makes the extra volume available for propellant. At 830 kg/m3 the total propellant weight is 2,003,039 kg. 527,115.6 kg of LNG aft of the bulkhead and 1,475,923.4 kg of LOX forward of the bulkhead.

Total mass of the tank is less than the SWLT figures becuase
a) LNG is less difficult to keep cool than LH2,
b) common bulkhead between tanks is lighter than two separate tanks with intertank.

Conservatively let's keep the 26,500 kg for the tank mass.

A Raptor LOX/LNG engine produces 230,000 kgf of thrust and has a 3.6 km/sec exhaust speed in vacuum. 14 of these engines produce 3,220,000 kgf thrust with a 3.4 km/sec exhaust speed at sea level, when arranged around an aerospike engine at the base of the External Tank.

The weight of this arrangement is 26,850 kg. Another 21,700 kg of mass is used for the recovery system and landing gear. A total of 75,000 kg of inert mass per element.

Take off Weight: 2,078,039 kg
Empty Weight: 75,000 kg
Thrust Max: 3,220,000 kgf
Exhaust (sl) 3,400 m/sec
Exhaust (vac) 3,600 m/sec


Vf = 3,500 * LN( 2,078,039 / 75,000 ) = 11,625.9 m/sec

It can lift 80,830 kg into LEO as a SSTO.

Three tanks operated in two stages, with the two outboard tanks feeding the central set of engines during boost, and then falling away, to be recovered down range, are capable of lifting 391,000 kg into LEO.

Tanking an external tank of the size just described, and removing 25,000 kg of engines and insulation, reduces mass to 50,000 kg. Carrying 274,247.4 kg of propellant in a small set of tanks at its base, the tank becomes a version of Skylab - only larger. It is capable of carrying 66,752.6 kg of payload to low lunar orbit and back.

As a cruise ship, each person masses an average of 80 kg, and has another 60 kg allocated to them. A total of 140 kg. Another 619.2 kg of propellant to power rocket belts, provide the ability to take 88 people to the moon and back, and allow them to visit three spots anywhere on the lunar surface!

http://rocketbelt.nl/pogos/nasa-lunar-transport

https://airandspace.si.edu/research/...inding_Aid.pdf

The recurring cost, with reusable ships and propellant costs of $0.16 per kg, is around $15,000 per person. The flight could be filled at $515,000 per person, earning $44 million per month or $88 million per month with two ships and one launcher.


At $90 million each, a total of 9 elements, (7 launch elements, 2 flight elements) a total of $810 million.

Flight element - carrying 88 passengers and 20 crew members - contain a small set of tanks at the base of the 8.4 m diameter tank propelling a small number of Kestrel engines, to boost the tank carrying 88 passengers from Low Earth Orbit to a Lunar Trajectory, and then entering a Low Lunar Orbit. There are 44 airlocks with 2 rocket belts each, refuelled from the central tank located around the base. Passengers are automatically ferried down to the lunar surface and back, aboard these rocket belts. Three landings for each of the 88 passengers translate to 264 landings at up to 256 sites on the lunar surface.

The spacecraft enters sun synchronous polar orbit and departs that orbit 3.5 days prior to half moon. Two trips are made per month. Half moon is the 14 and 30 of May in 2016. So, departure from SSO is on the 10th and 26th of May. It takes 3.5 days to get there, and the craft spends 2 weeks in polar orbit and takes 3.5 days to get back. A second payload is boosted to the Moon as the first one comes back.

During the two week stay at the moon, the 88 people on board pick wherever they would like to land over the two week period.

176 people fly to the moon per month and land at up to 528 sites.

There are 8 levels each 2.4 meters tall, and a central corridor 3.6 m in diameter at the center of an 8.4 meter diameter cylinder. There are 11 rooms that are 1.06 m wide at the central wall (3.6 m diam) and 2.4 m wide at the 8.4 m wall. There is a 1 m wide hall with a 1.6 m wide central shaft the runs the length of the tank. At the front of the tank are two levels with outward facing ejection seats, each behind its own window - 44 seats on two levels. These are the acceleration couches the passengers sit in during ascent and re-entry. These are built into their own capsules, which double as airlocks. Passengers can sit in these any time and can arrange to take a space walk and do vacuum training in their suits during the journey out and back. Behind the row of outward facing seats in each capsule, is a large 5.6 m wide 4.8 m tall common area where food and drinks are served.

Beneath the large common area is a shaft to 88 rooms below - each assigned to a passenger for their personal use. Forward of the common area are crew quarters and command.

Aft of the 8 levels of passenger cabins are mechanical and supplies and entertainment areas.

Each passenger has a room that's 2.4m tall and 2.4 m wide and 2.4 m deep, that is wedge shaped and only 1.06 meters wide at the narrow end. The large 2.4m x 2.4 m wall is equipped with an autostereoscopic projected display on the 2.4 m x 2.4 m convex wall. This is where each passenger may spend private time alone or with others.

https://www.youtube.com/watch?v=PjP4SvHjkdo

Before departure and during transit, passengers arrange to visit three sites of interest to them on the lunar surface. There are standard tours, but custom tours may be arranged and are in fact encouraged.

Upon entring lunar orbit, passengers arrange to depart to their points of interest and return. Three sites may be visited during the two week stay in lunar orbit, by each passenger.

There are dozens of interesting historical sites to visit;

https://en.wikipedia.org/wiki/List_o...ts_on_the_Moon

Hundreds of mysteries to explore according to some.

http://www.cavinessreport.com/ad3.html

This can all be made to build interest in buying tickets.

 




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