http://www.jeccomposites.com/news/co...ressure-vessel
https://www.youtube.com/watch?v=xNXqK_bpE4s
https://www.youtube.com/watch?v=qkGI6JeNY0E

A 600 kg composite cryogenic tank carries 3,349 kg of liquid hydrogen in 47,843 cubic meter composite tank with a common bulkhead separating it from a LOX tank 16,158 cubic meters in size carrying 18,420 kg of LOX. A total propellant weight of 21,769 kg. 2.76% structure weight. At 21 bar pressure.

The tank is 2,257mm in diameter (7.40 ft) and 17,147 mm (56.25 ft) long. A hemispherical end, separated by 672 mm from an opposite facing hemispherical common bulkhead, separated by a 11,961 mm long cylinder with another hemispherical end facing the same way as the bulkhead.

http://www.astronautix.com/a/aerospi...arbooster.html
https://www.youtube.com/watch?v=-0Y0FS8Z1Qk

A pressure fed annular aerospike engine on this composite tank produces 28,470 kgf of thrust and weighs 406 kg. Added to the composite tank produces an inert stage weight of 22,775 kg and the system produces 1.25 gees at take off and the system rises at 2.45 m/s2 at take off, and accelerates as propellant is burned off.

The system produces 120% maximum thrust at lift off, and scales back to maintain 1.25 gees - even with full payload - for a short period of time. It then flies an optimal Goddard trajectory from surface to its desired orbit during ascent.

Seven tanks, equipped with cross-feed between tanks, creates a three-stage system;

(1) (2)
(3) (4) (5)
(6) (7)

Where 6 and 1 feed 3 and 3 feeds 4
and 7 and 2 feed 5 and 5 feeds 4.

1,2,6,7 burn off first.
3,5 burn off next
4 burns off last.

Now, a single stage to orbit is possible with this system, when carrying 2200 kg payload. A three element two stage to orbit system is possible as well, when carrying 7900 kg payload. A seven element three stage to orbit system carries 19,300 kg payload to orbit.

In its three stage configuration the first four tanks separate at 2.25 km/sec, the two second stage tanks separate at 4.95 km/sec, and the payload and third stage, achieve 7.95 km/sec - after air drag and gravity losses are taken into account. (when launched from 45 degrees north or south latitude into an easterly direction.

The equivalent of two composite tanks, made into a lifting body shape 2,257 mm in height and 4,514 mm in width, and 18,000 mm long, displace a volume of 128,000 litres (128 m3, 4,517.8 cubic feet) whilst massing 1,300 kg - leaving 18,000 kg payload capacity.

The value of this is $50.0 million per launch.

Hybrid carbon fibre composites are extremely strong, lightweight, and capable of being shaped into aerodynamic shapes and maintain their strength and performance when exposed to extreme re-entry conditions.

http://www.hindawi.com/journals/jcomp/2014/825607/

Ultra lightweight inflatable lifting surfaces, that deploy at subsonic speeds, give tremendous glide and maneuverability as well.

https://www.youtube.com/watch?v=zQ11l9F3sNY
https://www.youtube.com/watch?v=4SBi9Bffbb4
https://www.youtube.com/watch?v=x3a19wDzSwU

Any flight system that attains speeds of 2.25 km/sec or more is capable of flying back to its launch centre.

http://ufxufo.org/german/antiplofer.html

Landing of the tanks takes place by climbing to a vertical attitude, and landing on the rocket thrust - like the tail-sitter aircraft of the 1950s and 60s updated with today's technology.

https://www.youtube.com/watch?v=6-T_-4nEA_M
https://www.youtube.com/watch?v=kZcpg70Ewbw
https://www.youtube.com/watch?v=f_01KpRCdGA

Lifting body shape of the payload section;

https://www.youtube.com/watch?v=F-8AQnBR1tg
https://www.youtube.com/watch?v=50dDWT48b9M

* * *

A lunar upper stage on this system, consists of a lifting body just described, carries 11,878 kg of propellant masses 1,422 kg empty and carries 6,000 kg of payload. The propellant tanks occupy 35 cubic meters and leave 93 cubic meters for payload. The system boosts from low earth orbit to a translunar trajectory by applying 2.9 km/sec to its 7.95 km/sec orbital speed. This puts it into a trans-lunar free return trajectory that arrives at the moon in 3.7 days. It enters low lunar orbit, and has sufficient propellant once in low lunar orbit, to exist low lunar orbit and return to Earth in 3..7 days, re-enter the Earth's atmosphere, and glide to the launch center for a powered touchdown.

When in low lunar orbit, 8 passengers and 4 crew members, each wearing a long duration biosuit and equipped with a MEMS based rocket belt, jumps down to the lunar surface and returns. An adult male in a biosuit, with sufficient supplies for 36 hours, masses 90 kg. A 6 kg MEMS based rocket belt and high pressure tank set, three tanks carrying 243 litres of liquid hydrogen and 81 litres of LOX in a single tank. All tanks being 537 mm diameter and carrying 81 litres of liquid.

https://www.youtube.com/watch?v=FbazOdEQxuE
http://www.wired.com/2013/07/lunar-flying-units-1969/
https://www.youtube.com/watch?v=iaJPtxK9wzs
https://www.youtube.com/watch?v=P58b0qaFPnk

Travellers fly individually on their own rocket belts to the lunar surface and return to the orbiting spacecraft. Guidance systems are built into their suits, heads up displays in the helmet, with voice interaction and gesture and facial recognition, control. They document the journey of each user as they explore the lunar surface.

http://www.dpreview.com/articles/641...-degree-camera
http://www.wired.com/2015/05/lily-robotics-drone/

A half dozen small self propelled camera sets that give 4K HD views all around and software provides editing into a superior travel film for each user..

The cost of each ticket for the eight passengers is $6.3 million. Cost of suit and other hardware, an additional $0.7 million.

* * *

A launch every 56 hours - 2d 8h - 7 shifts - produces 3 flights per week and 156 flights per year. $7800 million at $50 million per flight. Four lifting bodies and eight tanks are required. These cost $8 million each, and altogether $96 million.

* * *

Solar ion booster - an 18,000 kg solar power ion system that produces 22,000 Watts/kg - generates 396 MW and when using a 54 km/sec exhaust speed. It consists of four 305 m diameter inflatable concentrators, that power a 748 kgf thrust ion engine.

https://tec.grc.nasa.gov/past-projec...concentrators/
http://web.mit.edu/aeroastro/labs/spl/research_ieps.htm

A delta vee of 4.12 km/sec - lifting 16,000 kg to GEO from LEO, and bringing the 18,000 kg ion booster back using 2,022 kg of propellant. Using Liquid Hydrogen and the 2,257 mm diameter cylinder with spherical end caps, this is a 300 kg tank that's 7,974 mm long with a 5,717 mm long cylindrical section. A total of 22,868 litres. This leaves over 125,000 litres of volume (125 cubic meters) for a payload.

So, $50 million to send 18,000 kg (39,700 lbs) to Low Earth Orbit. In conjunction with the solar ion stage, we offer 16,000 kg to Geosynchronous Orbit, with return of the ion stage - for $60 million.

* * *

The ion booster with 2,880 kg of hydrogen is also adapted to take 15,120 kg of payload to LLO and return to Earth! Another 1,084 kg of hydrogen brakes the ion booster - a total that's equal to the hydrogen tank alone in the all chemical system above, and the hydrogen booster tank described for the GEO mission. The lifting body payload enters the Earth's atmosphere as it separates from the ion booster, which slows into parking orbit again.

This increases the payload on Low Lunar Orbit by 9,000 kg! Sufficient to add 18 passengers! A total of 26 passengers and 4 crew members. Dividing 26 passengers into $60 million obtains $2.3 million per passenger plus $0.7 million for suit and services. $3.0 million for a trip to the moon. Each passenger gets one landing, and sufficient propellant for another 20 landings are carried along and auctioned off on lunar orbit.

Five ion engines
Five shuttles
Seven boosters
Seven transfer tanks

Give mastery over the space launch business - and capture $8 billion per year.

* * *

Communications satellite network - five 3.6 ton satellites - per launch - at $10 million per launch, and $20 million per satellite - with 22 MW of power - per satellite - provide 720 satellites that

* a global wireless hotspot for 20 billion broadband channels,
* live google earth feed - high resolution - with memory,
* cloud processing and storage,
* global financial services,

https://www.youtube.com/watch?v=W2mGhfZCemg
https://www.youtube.com/watch?v=KP6pBS6uptE

This will permit secure and free communications that generates $2.4 trillion per year. Well worth the 144 launches and $21.6 billion in overall cost.

* * *

Power satellite network, at 396 million watts per satellite - at $100 million per satellite and $50 million per launch - $150 million per satellite - beaming solar pumped lasers to receivers on Earth at $0.11 per kWh this produces $381 million per year. This adds 61.2 GW per year - per launcher - and as power supplies are added, launchers are purchased and enlarged.

https://vimeo.com/37102557

With copious amounts of laser energy beamed from space, we are then able to revamp the construction of spacecraft - separating the power generation portion from the accelerated payload - and radically improving efficiencies.

http://ykbcorp.com/downloads/Bae_pho...ulation..pd f

https://www.youtube.com/watch?v=XhUasBcoj-Q

https://www.youtube.com/watch?v=33_-teBjZ4w

We use laser thermal jet to energise air when rising in the troposphere, and stratosphere, and use laser thermal rocket to energise propellant in the exosphere, and photonic thruster, recycling photons when we attain orbit. In this way we only use propellant to impart 6 km/sec whilst ejecting it at 12 km/sec. So, only 39.4% take off weight is propellant to get to orbit from Earth.

Given the atmosphere of Mars and its lower lapse rate, it takes no propellant since we can use the atmosphere through orbital velocity and photonic thrusting thereafter.

Given the low surface gravity of the Moon and asteroids and the moons of Mars, we can use photonic thrusting throughout!

Awesome!

Inert fluids, like water, which is abundant across the solar system, can be used with lasers to provide high thrust where its needed. So, its not really a problem.

* * *

Putting very large power satellites near or on the solar surface, radically improves performance of laser based systems, making it possible to gather sufficient energy to make sensible quantities of positronium - which transforms the efficiency of space travel yet again!

https://www.linkedin.com/pulse/20140...e-in-our-reach

https://www.linkedin.com/pulse/indus...mp-reader-card

* * *

Fifty years back from 2019 - man first landed on the moon. Fifty years forward from 2019 - a century after man landed on the moon - we will have left the solar system by and large and the present world situation will be radically transformed with fewer than 500 million living on Earth and over 10 billions traveling among the stars!