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Infinite stages



 
 
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  #1  
Old May 1st 16, 06:37 PM posted to sci.space.policy
William Mook[_2_]
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Posts: 3,840
Default Infinite stages


http://www.spaceatdia.org/uploads/ma...lisse%2012.pdf

A lenticular aeroshell like the Pye Wackett LDM planned for th XB-70 Valkyrie filled with 1 cm diameter lox liquid hydrogen nested spheres with a propulsive skin of MEMS rocket array and an interconnection link that passes propellant between spheres is an infinite stage rocket.

A 15 m diameter disk that's 3 m thick masses 80 tons and carries 2 tons to the moon and back.
  #2  
Old May 2nd 16, 01:00 AM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default Infinite stages

On Monday, May 2, 2016 at 5:37:48 AM UTC+12, William Mook wrote:
http://www.spaceatdia.org/uploads/ma...lisse%2012.pdf

A lenticular aeroshell like the Pye Wackett LDM planned for th XB-70 Valkyrie filled with 1 cm diameter lox liquid hydrogen nested spheres with a propulsive skin of MEMS rocket array and an interconnection link that passes propellant between spheres is an infinite stage rocket.

A 15 m diameter disk that's 3 m thick masses 80 tons and carries 2 tons to the moon and back.


This works like utility fog for rockets.

http://www.nanotech-now.com/images/foglet2-large.jpg

http://www.nanotech-now.com/images/foglet1-large.jpg

So, the 15 m x 15 m x 3 m oblate spheroid, contains 449 million spheres close packed in a hexagonal close pack (HCP) array. This reduces the propellant density from 340.1 kg/m3 to 240.7 kg/m3 with an O:F ratio of 5.5 due to spherical packing. A total 85,070.6 kg limit within the oblate spheroid described. The surface of each 'foglet' is equipped with an array of MEMS based LOX/LH2 rocket engine along with 12 telescoping connecting arms, that are retracted at lift off. Each sphere contributes up to 2.76 kgf - which drops to 20 tonnes of force for each square meter of exposed surface area for a fully dense array.

Each foglet is a 1 cm diameter sphere that carries 150.7 milligrams of LOX in a 6.32 mm diameter sphere, and 27.3 milligrams of LH2 in a 10.00 mm diameter sphere enclosing the first. The foglet itself masses 12 milligrams.

In addition to MEMS based rocket arrays, the system also contains MEMS based sensors, fuel cells, and a host of other useful items like cryogenic coolers and solar cells.

A spherical cabin atop the center of the oblate spheroid, similar in size and shape to the Vostok/Soyuz spherical capsule, connected to the disk beneath that changes shape during boost.

http://imgur.com/oiydQwC

At lift off, 6 square metres of surface near the rim of the oblate spheroid fire, and as the tiny spheres empty, they drop off. Remaining spheres adjust their spacing to maintain the desired surface shape of the spacecraft, during ascent, a ring 15 m in diameter and 8.5 cm wide. As the ship ascends, millions of 1 cm diameter spheres drop off and make their way back to the launch center, to re-assemble awaiting to be refilled.

https://www.youtube.com/watch?v=ZXpkG93KzdY

With a 4.5 km/sec exhaust speed, and a 16.6 km/sec total delta vee, we can compute propellant fraction;

u = 1 - 1/exp(16.6/4.5) = 0.9750

With 85,000 kg of useable propellant, this means we have 87,179.4 kg take off weight, permitting 2,179.4 kg payload.

While each of the 449 million cells are similar, they need not be identical! Each can be equipped to maximise performance. For example, smooth aerodynamic surfaces can be deployed from each micro-armature, or jets can replace rockets in the lower atmosphere, and interact with aerodynamic surfaces to produce lift, or through the Coanda effect, thrust.

https://www.youtube.com/watch?v=lYQc60rXrLg

This increases payload for a given take off mass, or reduces take off mass.

An oblate spheroid that is 3 meters by 5 meters by 45 meters - is more winglike - than disc like. It has the ability to take off VTOL fashion, using jet power, and transition to wing lift during early acceleration. This reduces gravity loss associated with a balllistic ascent. Using atmospheric oxygen rather than oxygen carried on board, reduces impact of air drag. Induced drag giving lift reduces air drag losses during ascent as well.

As the spacecraft accelerates it ascends. As it does this, it rotates like a scissor wing or oblique wing aircraft,

https://www.youtube.com/watch?v=BIr_lZ2-rp4

https://www.youtube.com/watch?v=XV-eTXIyYYQ

But by rotating thrust vectors on the oblique wing surface, with no 'stationary' surface - excepting of course the inhabitated 2.5 m diameter payload.

In this way, the spacecraft improves efficiency over a pure ballistic system.

Another opportunity for a utility fog infinite stage spacecraft is to separate and reform to maximise efficiency.


87.2 ton take off weight at Earth can land an astronaut on the moon 20x with the same propellant used to land the entire spacecraft and return to Earth, merely by reforming as a rocket belt like attachment around each astronaut.

Weight dV Ve u Weight

87.20 9.20 4.35 0.88 76.68
10.52 2.95 4.45 0.48 5.10
5.42 2.30 4.45 0.40 2.19
3.23 2.30 4.45 0.40 1.30
3.23 SdV 16.75
2.23 payload
1.00 surplus


  #3  
Old May 3rd 16, 03:54 PM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default Infinite stages

On Monday, May 2, 2016 at 12:00:03 PM UTC+12, William Mook wrote:
On Monday, May 2, 2016 at 5:37:48 AM UTC+12, William Mook wrote:
http://www.spaceatdia.org/uploads/ma...lisse%2012.pdf

A lenticular aeroshell like the Pye Wackett LDM planned for th XB-70 Valkyrie filled with 1 cm diameter lox liquid hydrogen nested spheres with a propulsive skin of MEMS rocket array and an interconnection link that passes propellant between spheres is an infinite stage rocket.

A 15 m diameter disk that's 3 m thick masses 80 tons and carries 2 tons to the moon and back.


This works like utility fog for rockets.

http://www.nanotech-now.com/images/foglet2-large.jpg

http://www.nanotech-now.com/images/foglet1-large.jpg

So, the 15 m x 15 m x 3 m oblate spheroid, contains 449 million spheres close packed in a hexagonal close pack (HCP) array. This reduces the propellant density from 340.1 kg/m3 to 240.7 kg/m3 with an O:F ratio of 5.5 due to spherical packing. A total 85,070.6 kg limit within the oblate spheroid described. The surface of each 'foglet' is equipped with an array of MEMS based LOX/LH2 rocket engine along with 12 telescoping connecting arms, that are retracted at lift off. Each sphere contributes up to 2.76 kgf - which drops to 20 tonnes of force for each square meter of exposed surface area for a fully dense array.

Each foglet is a 1 cm diameter sphere that carries 150.7 milligrams of LOX in a 6.32 mm diameter sphere, and 27.3 milligrams of LH2 in a 10.00 mm diameter sphere enclosing the first. The foglet itself masses 12 milligrams.

In addition to MEMS based rocket arrays, the system also contains MEMS based sensors, fuel cells, and a host of other useful items like cryogenic coolers and solar cells.

A spherical cabin atop the center of the oblate spheroid, similar in size and shape to the Vostok/Soyuz spherical capsule, connected to the disk beneath that changes shape during boost.

http://imgur.com/oiydQwC

At lift off, 6 square metres of surface near the rim of the oblate spheroid fire, and as the tiny spheres empty, they drop off. Remaining spheres adjust their spacing to maintain the desired surface shape of the spacecraft, during ascent, a ring 15 m in diameter and 8.5 cm wide. As the ship ascends, millions of 1 cm diameter spheres drop off and make their way back to the launch center, to re-assemble awaiting to be refilled.

https://www.youtube.com/watch?v=ZXpkG93KzdY

With a 4.5 km/sec exhaust speed, and a 16.6 km/sec total delta vee, we can compute propellant fraction;

u = 1 - 1/exp(16.6/4.5) = 0.9750

With 85,000 kg of useable propellant, this means we have 87,179.4 kg take off weight, permitting 2,179.4 kg payload.

While each of the 449 million cells are similar, they need not be identical! Each can be equipped to maximise performance. For example, smooth aerodynamic surfaces can be deployed from each micro-armature, or jets can replace rockets in the lower atmosphere, and interact with aerodynamic surfaces to produce lift, or through the Coanda effect, thrust.

https://www.youtube.com/watch?v=lYQc60rXrLg

This increases payload for a given take off mass, or reduces take off mass.

An oblate spheroid that is 3 meters by 5 meters by 45 meters - is more winglike - than disc like. It has the ability to take off VTOL fashion, using jet power, and transition to wing lift during early acceleration. This reduces gravity loss associated with a balllistic ascent. Using atmospheric oxygen rather than oxygen carried on board, reduces impact of air drag. Induced drag giving lift reduces air drag losses during ascent as well.

As the spacecraft accelerates it ascends. As it does this, it rotates like a scissor wing or oblique wing aircraft,

https://www.youtube.com/watch?v=BIr_lZ2-rp4

https://www.youtube.com/watch?v=XV-eTXIyYYQ

But by rotating thrust vectors on the oblique wing surface, with no 'stationary' surface - excepting of course the inhabitated 2.5 m diameter payload.

In this way, the spacecraft improves efficiency over a pure ballistic system.

Another opportunity for a utility fog infinite stage spacecraft is to separate and reform to maximise efficiency.


87.2 ton take off weight at Earth can land an astronaut on the moon 20x with the same propellant used to land the entire spacecraft and return to Earth, merely by reforming as a rocket belt like attachment around each astronaut.

Weight dV Ve u Weight

87.20 9.20 4.35 0.88 76.68
10.52 2.95 4.45 0.48 5.10
5.42 2.30 4.45 0.40 2.19
3.23 2.30 4.45 0.40 1.30
3.23 SdV 16.75
2.23 payload
1.00 surplus


Reducing the size of the rocket elements, increases the number of stages beyon 449 million. Operating much like the Thermian interstellar pod in the 1999 movie "Galaxy Quest"

Its a great comedy, and had some creative moments.

The Thermian interstellar pod is a mode of transportation that sends a single person across a very large region of space in a small amount of time. The pod is composed of a pad, a rocket within the pad and a gel to protect the person in question. The method by which the pod is prepared and transported is as follows:

1. A white pad appears underneath the feet of the person to be transported.

2. A blue gel emerges from the edges of the pad and moves towards the center.
 




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