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Three - stage, completely reusable spaceplane, reaching not onlyLEO, but Moon, Mars, asteroids.



 
 
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  #1  
Old July 17th 16, 11:11 PM posted to sci.space.policy
William Mook[_2_]
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Default Three - stage, completely reusable spaceplane, reaching not onlyLEO, but Moon, Mars, asteroids.

With 5700 Bishop Ring Habitats at 2.8 AU from Sol, we have a separation of 461,428 km between the centres of each of the 2,000 km diameter stations, forming rings 500 km wide. Each is equipped with a 2,000 km diameter concentrator that collects sunlight at ambient levels 174 Watts/m2 and projects an average fo 260 W/m2 from the center of the ring, to replicate day/night cycle on Earth equivalent to the Temperate regions of Earth.

Shuttles fly between the open air rings in 3.81 hours. A shuttle starting out at one ring and travelling continually in the same direction, comes back to its starting position after boosting for 2.56 years. Add in the time for vehicle service and visiting each location, and you have the time it takes to 'walk' around the sun.

A future movie, and a future incarnation of the 'walkabout'.

Part of training for interstellar voyages.

5700 take offs and landings, and 5700 relatively easy navigations.

Agressive participants will gradually increase the gee loading from 1 gee to 2.5 gees at the end, this will shorten the total walkabout to 2.00 years plus reconnoiter and repair times.



  #2  
Old July 19th 16, 12:59 AM posted to sci.space.policy
William Mook[_2_]
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Posts: 3,840
Default Three - stage, completely reusable spaceplane, reaching not onlyLEO, but Moon, Mars, asteroids.

An object projected along a hyperbolic trajectory at 11.8 km/sec from the Earth's surface, will intersect the moon in 9 hours, arriving on the surface at 4.3 km/sec. The same object projected along a hyperbolic trajectory from the lunar surface at 4.3 km/sec will travel back to Earth arriving at 11..8 km/sec again, again in 9 hours. Total impulse required, assuming aerobraking upon return, is 20.4 km/sec.

An electrospray rocket with an exhaust velocity of 54.0 km/sec requires a propellant fraction of 31.5% its take off weight to carry out a 20.4 km/sec mission delta vee. A person in a biosuit equipped with a few days of supplies, and a full recycling of air and water, masses 120 kg. A 120 kg payload implies a 176 kg take off weight, which means 56 kg propellant fraction. Using an inert propellant such as water, this is 56 litres of water. A sphere 475 mm in diameter. Or two spheres 377 mm in diameter. Or three spheres 330 mm in diameter.

352 kgf (3,452 Newtons) produced by a rocket with a 54 km/sec exhaust requires a mass flow rate of 64 grams per second of propellant. This requires 93.2 megawatts of jet power at the engine!

http://www.energy-parts.com/aeroderi...inventory.aspx

http://spectrum.ieee.org/transportat...rough-the-dark

http://www.gizmag.com/worlds-highest...-arrays/36535/

http://www.dtic.mil/dtic/tr/fulltext/u2/a410726.pdf

http://www.niac.usra.edu/files/studi...416Palisoc.pdf

A 250 MW aeroderivative power plant, powering 100 megawatt array of lasers, controlled by a thin film beam director 120 meter in diameter to be received by a 2 meter receiver to power a lightweight MEMS array of electrospray thrusters - is sufficient to project a person to the moon and return them to Earth in 32 hours. A 9 hour outbound transfer - and a 9 hour inbound transfer 15 hours later.

With a two hour launch window, a half dozen people or payloads can be projected to the moon and returned.



  #3  
Old July 19th 16, 03:57 AM posted to sci.space.policy
William Mook[_2_]
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Posts: 3,840
Default Three - stage, completely reusable spaceplane, reaching not onlyLEO, but Moon, Mars, asteroids.

On Tuesday, July 19, 2016 at 11:59:39 AM UTC+12, William Mook wrote:
An object projected along a hyperbolic trajectory at 11.8 km/sec from the Earth's surface, will intersect the moon in 9 hours, arriving on the surface at 4.3 km/sec. The same object projected along a hyperbolic trajectory from the lunar surface at 4.3 km/sec will travel back to Earth arriving at 11.8 km/sec again, again in 9 hours. Total impulse required, assuming aerobraking upon return, is 20.4 km/sec.

An electrospray rocket with an exhaust velocity of 54.0 km/sec requires a propellant fraction of 31.5% its take off weight to carry out a 20.4 km/sec mission delta vee. A person in a biosuit equipped with a few days of supplies, and a full recycling of air and water, masses 120 kg. A 120 kg payload implies a 176 kg take off weight, which means 56 kg propellant fraction.. Using an inert propellant such as water, this is 56 litres of water. A sphere 475 mm in diameter. Or two spheres 377 mm in diameter. Or three spheres 330 mm in diameter.

352 kgf (3,452 Newtons) produced by a rocket with a 54 km/sec exhaust requires a mass flow rate of 64 grams per second of propellant. This requires 93.2 megawatts of jet power at the engine!

http://www.energy-parts.com/aeroderi...inventory.aspx

http://spectrum.ieee.org/transportat...rough-the-dark

http://www.gizmag.com/worlds-highest...-arrays/36535/

http://www.dtic.mil/dtic/tr/fulltext/u2/a410726.pdf

http://www.niac.usra.edu/files/studi...416Palisoc.pdf

A 250 MW aeroderivative power plant, powering 100 megawatt array of lasers, controlled by a thin film beam director 120 meter in diameter to be received by a 2 meter receiver to power a lightweight MEMS array of electrospray thrusters - is sufficient to project a person to the moon and return them to Earth in 32 hours. A 9 hour outbound transfer - and a 9 hour inbound transfer 15 hours later.

With a two hour launch window, a half dozen people or payloads can be projected to the moon and returned.


Launch takes place with a reusable hydrogen peroxide/rp-1 propellant mixture with a 3.8 km/sec exhaust speed. Carrying 90 kg of propellant, and boosting the astronaut to an altitude of 90 km deploying the 2 m receiver at 70 km altitude and acquiring a power beam to continue acceleration along the hyperbolic trajectory. The power beam is acquired again 9 hours later, in the vicinity of the moon, where the astronaut is slowed to a landing zero speed at zero altitude. The beam is used again to lift the astronaut off the moon and return them to Earth.

At $20 million per person margin, and one flight per week, we have $120 million per week free cash flow, or $6 billion per year in pretax earnings! A substantial return on investment! The beam steering devices also double as overwhelmingly large observatories with not otherwise in use and making them available along with budgets to do significant astronomical research is a positive PR campaign.

This tech also advertises beaming power the other way from space!

With a propellant density of 1.72 kg per litre, only 465 mm diameter tank is needed for the mono-mixture temperature stabilised monopropellant.

The clamshell rocket body opens to admit the astronaut who stands inside the 3 meter tall, 800 mm wide tear drop shaped rocket body. He steps atop a platform 600 mm above ground level, and the clamshell closes around them. The interior inflates to hold the astronaut in place. The rocket then lights off, and accelerates upward at two gees! At 70 km altitude the clamshell doors open and eject the astronaut forward, as braking rockets are applied, and the rocket begins its descent back to the launch centre. By the time the astronaut reaches 90 km, the inflatable laser receiver is inflated, and contact is made with the beam steering unit on the ground. 100 MW of power is transmitted, and the electrospray ion rocket is energised, accelerating the astronaut along a hyperbolic trajectory at 11.8 km/sec - and 200 km altitude - intersecting with the moon.

9 hours later, the beam makes contact again and causes the astronaut to slow to zero speed at zero altitude on the lunar surface. The astronaut has 15 hours of time to stay on the lunar surface. Up to six astronauts are landed in this way, over the next 2 hours. After 15 hours, the astronaut receives the beam yet again, and is returned to Earth in 9 hours - coming in to the launch point 33 hours after launch.

* * *

Money is used to acquire undervalued aerospace assets throughout the world, and assemble a commercial aerospace company of tremendous capacity.

One approach would be to send swarms of free flying subsatellites that self assemble into a single larger satellite. 72 satellites per 24 hour period each 300 kg - 21.6 tonnes per day. 480 megawatts of beam energy may be assembled at GEO each day. Quadrupling the 120 MW of power described above, each day. This is two doubling periods.

Using the beam energy from space, to augment the power of the beam steering device, means that we can grow from 120 MW to 120 GW in a week.

Day 1 120 -- 240 -- 480
Day 2 480 -- 960 -- 1920
Day 3 1920 -- 3840 -- 7680
Day 4 7680 -- 15360 -- 30720
day 5 30720 -- 61440 -- 122880

Increasing payloads from 120 kg to 120 metric tons.

An array of elements totalling 15 km in diameter at Geosynch above the beam steerer.

This proves the technology, and puts the company in a position to;

(1) deploy an array of communications satellites to provide global telecom,
(2) deploy power satellites to provide global power,

Three flights daily from Earth to Moon - carrying 120 tons of useful load - with return of the vehicle within 48 hours - mean that six vehicles provide this level of service.

A freighter, using a lower exhaust velocity, is capable of projecting 576 tons three times per day, and is refuelled on the moon.

  #4  
Old July 19th 16, 04:50 AM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default Three - stage, completely reusable spaceplane, reaching not onlyLEO, but Moon, Mars, asteroids.

On Tuesday, July 19, 2016 at 2:57:54 PM UTC+12, William Mook wrote:
On Tuesday, July 19, 2016 at 11:59:39 AM UTC+12, William Mook wrote:
An object projected along a hyperbolic trajectory at 11.8 km/sec from the Earth's surface, will intersect the moon in 9 hours, arriving on the surface at 4.3 km/sec. The same object projected along a hyperbolic trajectory from the lunar surface at 4.3 km/sec will travel back to Earth arriving at 11.8 km/sec again, again in 9 hours. Total impulse required, assuming aerobraking upon return, is 20.4 km/sec.

An electrospray rocket with an exhaust velocity of 54.0 km/sec requires a propellant fraction of 31.5% its take off weight to carry out a 20.4 km/sec mission delta vee. A person in a biosuit equipped with a few days of supplies, and a full recycling of air and water, masses 120 kg. A 120 kg payload implies a 176 kg take off weight, which means 56 kg propellant fraction. Using an inert propellant such as water, this is 56 litres of water. A sphere 475 mm in diameter. Or two spheres 377 mm in diameter. Or three spheres 330 mm in diameter.

352 kgf (3,452 Newtons) produced by a rocket with a 54 km/sec exhaust requires a mass flow rate of 64 grams per second of propellant. This requires 93.2 megawatts of jet power at the engine!

http://www.energy-parts.com/aeroderi...inventory.aspx

http://spectrum.ieee.org/transportat...rough-the-dark

http://www.gizmag.com/worlds-highest...-arrays/36535/

http://www.dtic.mil/dtic/tr/fulltext/u2/a410726.pdf

http://www.niac.usra.edu/files/studi...416Palisoc.pdf

A 250 MW aeroderivative power plant, powering 100 megawatt array of lasers, controlled by a thin film beam director 120 meter in diameter to be received by a 2 meter receiver to power a lightweight MEMS array of electrospray thrusters - is sufficient to project a person to the moon and return them to Earth in 32 hours. A 9 hour outbound transfer - and a 9 hour inbound transfer 15 hours later.

With a two hour launch window, a half dozen people or payloads can be projected to the moon and returned.


Launch takes place with a reusable hydrogen peroxide/rp-1 propellant mixture with a 3.8 km/sec exhaust speed. Carrying 90 kg of propellant, and boosting the astronaut to an altitude of 90 km deploying the 2 m receiver at 70 km altitude and acquiring a power beam to continue acceleration along the hyperbolic trajectory. The power beam is acquired again 9 hours later, in the vicinity of the moon, where the astronaut is slowed to a landing zero speed at zero altitude. The beam is used again to lift the astronaut off the moon and return them to Earth.

At $20 million per person margin, and one flight per week, we have $120 million per week free cash flow, or $6 billion per year in pretax earnings! A substantial return on investment! The beam steering devices also double as overwhelmingly large observatories with not otherwise in use and making them available along with budgets to do significant astronomical research is a positive PR campaign.

This tech also advertises beaming power the other way from space!

With a propellant density of 1.72 kg per litre, only 465 mm diameter tank is needed for the mono-mixture temperature stabilised monopropellant.

The clamshell rocket body opens to admit the astronaut who stands inside the 3 meter tall, 800 mm wide tear drop shaped rocket body. He steps atop a platform 600 mm above ground level, and the clamshell closes around them. The interior inflates to hold the astronaut in place. The rocket then lights off, and accelerates upward at two gees! At 70 km altitude the clamshell doors open and eject the astronaut forward, as braking rockets are applied, and the rocket begins its descent back to the launch centre. By the time the astronaut reaches 90 km, the inflatable laser receiver is inflated, and contact is made with the beam steering unit on the ground. 100 MW of power is transmitted, and the electrospray ion rocket is energised, accelerating the astronaut along a hyperbolic trajectory at 11.8 km/sec - and 200 km altitude - intersecting with the moon.

9 hours later, the beam makes contact again and causes the astronaut to slow to zero speed at zero altitude on the lunar surface. The astronaut has 15 hours of time to stay on the lunar surface. Up to six astronauts are landed in this way, over the next 2 hours. After 15 hours, the astronaut receives the beam yet again, and is returned to Earth in 9 hours - coming in to the launch point 33 hours after launch.

* * *

Money is used to acquire undervalued aerospace assets throughout the world, and assemble a commercial aerospace company of tremendous capacity.

One approach would be to send swarms of free flying subsatellites that self assemble into a single larger satellite. 72 satellites per 24 hour period each 300 kg - 21.6 tonnes per day. 480 megawatts of beam energy may be assembled at GEO each day. Quadrupling the 120 MW of power described above, each day. This is two doubling periods.

Using the beam energy from space, to augment the power of the beam steering device, means that we can grow from 120 MW to 120 GW in a week.

Day 1 120 -- 240 -- 480
Day 2 480 -- 960 -- 1920
Day 3 1920 -- 3840 -- 7680
Day 4 7680 -- 15360 -- 30720
day 5 30720 -- 61440 -- 122880

Increasing payloads from 120 kg to 120 metric tons.

An array of elements totalling 15 km in diameter at Geosynch above the beam steerer.

This proves the technology, and puts the company in a position to;

(1) deploy an array of communications satellites to provide global telecom,
(2) deploy power satellites to provide global power,

Three flights daily from Earth to Moon - carrying 120 tons of useful load - with return of the vehicle within 48 hours - mean that six vehicles provide this level of service.

A freighter, using a lower exhaust velocity, is capable of projecting 576 tons three times per day, and is refuelled on the moon.


Solid state lasers, and laser driven electrospray arrays, attain energy densities of 25 kW/cm2. That's 250 MW per square meter. With a 54 km/sec exhaust speed, this is 944 kgf per square meter. This is a loading greater than an MD-11 or a B-747 or a fighter jet! (F-104 Starfighter has 517 kgf/m2 wing load) So, we can imagine a relatively compact system!

A 3 meter diameter concentrator that focuses light on to a 755 mm diameter disk that produces over 423 kgf of lift and generates two gees of acceleration at altitude.

https://www.nasa.gov/pdf/501329main_...-Nov2010-A.pdf

http://web.mit.edu/neboat/tooling/ST...borneLaser.pdf

A 1 meter diameter LED array operates at the focal point of a 120 meter diameter parabolic mirror beam steering device then directs the beam to the distant receiver - providing stable reception from 90 km up to 384,400 km away!

Using phase conjugate optics...

https://www.youtube.com/watch?v=gAy39ErqV34

 




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