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Microcosm - Pressure Fed Launcher



 
 
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  #1  
Old August 29th 16, 02:58 AM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default Microcosm - Pressure Fed Launcher

http://citeseerx.ist.psu.edu/viewdoc...=rep1&type=pdf

https://www.youtube.com/watch?v=wn6SVH6hWmo

http://smad.com

The paper describes Microcosm’s approach to developing low-cost, pressure-fed launch vehicles. While the pressure-fed designs have historically been relatively heavy compared to the traditional pump-fed designs, Microcosm's enabling critical technologies for composite tanks, high performance pressurization system, and low-cost ablative engines allow them to provide pressure-fed design solutions at a significantly lower cost and higher reliability compared to the pump-fed options while meeting the specific performance criterion of pump fed systems.

The critical technologies have been qualified. All these technologies are scalable and thus can be easily integrated to progressively larger vehicles to meet the evolving payload requirements of various defense and commercial programs.

Microcosm's approach of designing for low cost by exploiting the pressure-fed technologies has the potential to revolutionize space transportation and enable the next generation of expendable launch vehicles at greatly reduced cost.

Zero Boil Off Cryogenic Storage
http://bit.ly/2c1krI8

MEMS Cryocooler
https://pure.tue.nl/ws/files/2111874/Metis212774.pdf

MEMS Fuel Cell
http://techportal.eere.energy.gov/te....do/techID=487

MEMS Overview (use in PLSS)
http://www.eolss.net/sample-chapters...-152-07-00.pdf

A fiberglas tank that's 5.4 meters in diameter and 54 meters long contains 62,557 kg of liquid hydrogen in a 39.0 meter long section aft, and 344,068 kg of LOX in a 13.2 meter long section forward with a common bulkhead between. All bulkheads and tank ends are hemispherical and open upward like a bowl. A central LOX suction line passes from the central bulkhead to the base of the hydrogen fuel tank. LH2 suction line enclosed the LOX suction line. Two worm screw jacks each drive a separate tank bulkhead liner that is lowered as the tank drains to maintain positive displacement in each tank with no sloshing. The liner is also equipped with cryocooler driven heat exchangers to reliquefy gaseous ullage in each tank. The area forward of the LOX tank is equipped with a composite skirt and cover for the equipment to maintain zero boil off and pressure for the tanks - and has the loading and venting hardware. This also houses cross feed lines for cross feeding the engines from an external tank during flight.

The base of the hydrogen tank is surrounded by a ring of 30 composite nozzles with replaceable liner, feeding a composite aerospike engine. Each nozzle is fed from a header which has independent control of propellant into each nozzle to provide directional control fo the system.

The structural weight of each tank is 14,320 kg.

An additional 6,000 kg provides thermal protection system on the forward skirt and inflatable wings for extended cross-range glide following re-entry and slowing to subsonic speeds. The system is also equipped with advanced guidance system allow the tank to pull to a nose up orientation and land on its tail at a prepared site.

Ryan X-13 Vertijet - 1957
https://www.youtube.com/watch?v=6-T_-4nEA_M

Inflatable aircraft
https://www.youtube.com/watch?v=x3a19wDzSwU
https://www.youtube.com/watch?v=2gGygxDIJX0

Inflatable heat shield
https://www.youtube.com/watch?v=ojgDZZIsWA4

A 7 element system, is capable of placing 350,000 kg of payoad into Low Earth Orbit (LEO).

A 29.7 meter long tank pair with a 22.2 meter long LH2 tank section and a 7..5 meter long LOX tank section, contains 118,980.5 kg of LOX and 35,541.5 kg of LH2 - and is sufficient to take 118,980.5 kg payload to Low Lunar Orbit and Back.

The kick stage is topped by a passenger section consisting of 4 decks each 2.6 meters deck height - with a 2.3 meter free space between decks. Each section is 5.4 meters in diameter and has 18 seats facing radially outward, through its own transparent canopy. 72 seats in all. 60 passengers and 12 crew. Each passenger has their own biosuit, life support and rocket belt as well as AI computer. The canopy can be made opaque and used as an autostereoscopic display and cameras connected to the computer permit gesture, facial, and pattern recognition. Each passenger has an inner suit and an outer suit, and during the flight they may leave their acceleration couch with outer suit - to interact with other passengers in the 10.2 meter long by 3.4 meter cabin interior.

There is sufficient propellant on board to allow all 72 travellers to visit the moon 7x while in lunar orbit.

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

The system flies to Lunar Orbit, and then back to Earth. Astronauts travel to the lunar surface on their own rocket belts and return, spending up to 11 hours at each of 7 sites on the lunar surface.

At $0.08 per kWh it takes $1.49 million to fill up all 8 flight elements with LH2 and LOX made from water. With one launch per week, and one booster, it takes two kickstages and spacecraft. These are all built at a cost of $70 million. Another $0.12 million per flight is used to pay CAPEX, and another $0.39 million is used for maintenance and operations. A total of $2.00 million per flight. $27,800 per person. Spacesuit, and other services, cost $22,200 - a total of $50,000 per person per flight. Total cost per person is $150,000 - generating $100,000 per person in free cash flow before taxes. That's $7.2 million per launch profit. $374.4 million.

52 * 60 = 3,120 people per year. With a 3% market penetration we have a target audience of 104,000 persons. There are 172,850 people who have more than $30 million in assets in the world.

http://www.investopedia.com/terms/u/...uals-uhnwi.asp

Charging them 5% of their networth for a once in a lifetime opportunity, that's $1.5 million per flight. This generates over $3 billion in free cash flow per year. This earns $72 million per launch, which is more in keeping with the size of the launcher...

The launcher, with 35 satellites at 10,000 kg per satellite, in a same polar plane, and with 18 orbital planes, with 18 launches, to 630 satellites - providing global wireless internet via LiFi open optical communications. This allows capture of a good portion of the world's $1.2 trillion per year telecom marketplace.

The launcher can put into orbit a 7.7 GW power station, and 2,000 of these can capture a good portion of the world's $3 trillion per year energy market.

http://lasermotive.com



  #2  
Old August 30th 16, 05:18 AM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default Microcosm - Pressure Fed Launcher

702 SP satellite


In 2005, Boeing offered a Xenon Electrostatic ion thruster System (XIPS) option for the 702 satellite system. XIPS is 10 times more efficient than conventional liquid fuel systems. On a XIPS equipped 702 satellite, four 25 cm (9.8 in) thrusters provide economical station-keeping, needing only 5 kg (11 lb) of fuel per year, "a fraction of what bipropellant or arcjet systems consume". An XIPS-equipped satellite can be used for final orbit insertion, conserving even more payload mass, as compared to using a traditional on-board liquid apogee engine.

Beginning in 2012, Boeing began manifesting all-electric propulsion commsats on the 702SP XIPS propulsion bus for eventual location in Geosynchronous orbit. These satellites were the first which were to be launched with the intent to fully position the satellites using electric propulsion, thus requiring four to six months following launch to ready the satellite for its communication mission, but at substantial reduction in launch mass and, therefore, launch cost.[2][15]

As of March 2014, Boeing had sold four of the 702SP satellites to Asia Broadcast Satellite (ABS) of Hong Kong and Mexico's SatMex, with the first two commsats planned for a paired launch in early 2015.

In November 2014, Boeing released information that two of the 702SP satellites they have built—ABS-3A and Eutelsat 115 West B—had completed manufacture and had been stacked conjoined as they prepared for a launch on a SpaceX Falcon 9 vehicle in early 2015. This was to be Boeing's first-ever conjoined launch of two commsats. The two commsats were launched aboard a SpaceX rocket from Cape Canaveral, Florida, at 3:50AM UTC on 2 March 2015 (10:50PM EST on 1 March 2015).

These satellites were 650 kg each. A 350,000 kg payload capability gives the ability to launch 520 satellites per launch that are 673.1 kg each.

A Sun-synchronous orbit (SSO, also called a heliosynchronous orbit) is a geocentric orbit that combines altitude and inclination in such a way that the satellite passes over any given point of the planet's surface at the same local solar time. Such an orbit can place a satellite in constant sunlight and is useful for imaging, spy, and weather satellites. More technically, it is an orbit arranged in such a way that it precesses once a year. The surface illumination angle will be nearly the same every time that the satellite is overhead. This consistent lighting is a useful characteristic for satellites that image the Earth's surface in visible or infrared wavelengths (e.g. weather and spy satellites) and for other remote sensing satellites (e.g. those carrying ocean and atmospheric remote sensing instruments that require sunlight). For example, a satellite in sun-synchronous orbit might ascend across the equator twelve times a day each time at approximately 15:00 mean local time. This is achieved by having the osculating orbital plane precess (rotate) approximately one degree each day with respect to the celestial sphere, eastward, to keep pace with the Earth's movement around the Sun.

The uniformity of Sun angle is achieved by tuning the inclination to the altitude of the orbit (details in section "Technical details") such that the extra mass near the equator causes the orbital plane of the spacecraft to precess with the desired rate: the plane of the orbit is not fixed in space relative to the distant stars, but rotates slowly about the Earth's axis. Typical sun-synchronous orbits are about 600–800 km in altitude, with periods in the 96–100 minute range, and inclinations of around 98° (i.e. slightly retrograde compared to the direction of Earth's rotation: 0° represents an equatorial orbit and 90° represents a polar orbit).

Special cases of the sun-synchronous orbit are the noon/midnight orbit, where the local mean solar time of passage for equatorial longitudes is around noon or midnight, and the dawn/dusk orbit, where the local mean solar time of passage for equatorial longitudes is around sunrise or sunset, so that the satellite rides the terminator between day and night. Riding the terminator is useful for active radar satellites as the satellites' solar panels can always see the Sun, without being shadowed by the Earth. It is also useful for some satellites with passive instruments that need to limit the Sun's influence on the measurements, as it is possible to always point the instruments towards the night side of the Earth. The dawn/dusk orbit has been used for solar observing scientific satellites such as Yohkoh, TRACE, Hinode and PROBA2, affording them a nearly continuous view of the Sun.

Sun-synchronous orbits can happen around other oblate planets, such as Mars..

The 702SP satellite costs $85 million. So, 520 of them costs $44,200 million! Costs could drop in this quantity by a large factor, to about $20 million each - reducing the fleet costs to $10,400 million!

The market capitalisation of Boeing is $82.91 billion.

Potential for Value Creation from Divestitu Boeing in 1998

While it is difficult to make judgments about individual investments that firms might have and their capacity to generate continuing value, you can make some observations about the potential for value creation from divestitures and liquidation by looking at the cost of capital and the return on capital earned by different divisions of a firm. For instance, Boeing earned a return of capital of 5.82% in 1998, while its cost of capital was 9.18%. Breaking down Boeing’s return by division we obtain the numbers in the following table:

Aircraft Information Firm
Space &
Defense

Operating
Income $75 $1,576 $1,651

Capital
Invested $18,673 $9,721 $23,394

After tax
Return on
Capital 0.40% 16.21% 5.82%


At Boeing’s annual meeting in 1999, Phil Condit, Boeing’s CEO, was candid in admitting that 35% of Boeing’s capital was in investments that earned less than the cost of capital.

The Space division by these numbers is worth $10.3 billion and if it were sold for say $11.0 billion it would be a net benefit to Boeing stockholders.

Today, the Boeing Company's corporate headquarters are located in Chicago and the company is led by Chairman and CEO James McNerney. Boeing is organized into five primary divisions: Boeing Commercial Airplanes (BCA), Boeing Defense, Space & Security (BDS), Engineering, Operations & Technology, Boeing Capital and Boeing Shared Services Group.

The weak link in the chain is the Space and Defense sector.

$90,762 sales $8,860 earnings, 160,000 emp: Boeing Total

Divisions: -

$30,881, sales $3,133 earnings 50,000 emp: Boeing Defense, Space and Security
$13,511 sales $1,304 earnings - Boeing Military Aircraft
$ 8,003 sales $ 698 earnings - Network & Space Systems
$ 9,367 sales $1,131 earnings - Global Services & Support

$59,990 sales $5,411 earnings 83,000 emp: Boeing Commercial Airplanes

Boeing Capital Corporation
Boeing Shared Services Group
Boeing Engineering, Operations & Technology

Total Debt is $9,964 million
LT Debt $8,721 million
Due in 5 yrs: $4,588 million

68% of Capital ($14,653 million (huge write down from 1998))

Pension Assets: $56.5 billion
Pension Liabilities: $74.4 billion


Inventory: $46.8 billion

Accts pay: $24.0 billion
Debt: $ 0.9 billion
Other: $31.8 billion
Total: $56.7 billion

Though operating conditions are rather favorable for the core commercial business, this is not the case for Boeing’s smaller defense unit. In fact, reductions in U.S. defense spending continue to hamper results across the Defense, Space & Security division. This situation won't be reversing anytime soon, especially considering the push in Washington for more budgetary cuts.

By making inroads abroad and streamlining its overhead Boeing can cust costs. Boeing has already made strides beefing up its international business (overseas sales tend to be pretty high-margined), which currently accounts for about 23% of the defense segment’s total revenues and 40% of its work backlog. What’s more, the company maintains its goal of eventually shedding $2.5 billion from the cost structure.

The point is, anyone that organised sufficient capital to buy 520 satellites from Boeing's Space Division would be better off BUYING THE DIVISION for $15.4 billion and integrating its capabilities with an improved launcher.

Better yet, BUY THE WHOLE COMPANY, spin off the stronger pieces, and use the profits to fund a reinvention of the Space Division as a whole. Boeing could be purchased for $90 billion and its division not useful for space operations and telecommunications, could likely be sold for $110 billion - paying for the transaction costs and the development of the $1.2 trillion per year revenue stream from the global telecommunications marketplace.

* * *

RKK Energia is worth 3.96 billion rubles. USD$61.3 million market capitalisation!

Energia is the largest company of the Russian space industry and one of its key players. It is responsible for all operations involving human spaceflight and is the lead developer of the Soyuz and Progress spacecraft, and the lead developer of the Russian end of the International Space Station. In the mid-2000s, the company employed 22,000—30,000 people.

  #3  
Old August 30th 16, 07:10 AM posted to sci.space.policy
William Mook[_2_]
external usenet poster
 
Posts: 3,840
Default Microcosm - Pressure Fed Launcher

On Monday, August 29, 2016 at 1:58:59 PM UTC+12, William Mook wrote:
http://citeseerx.ist.psu.edu/viewdoc...=rep1&type=pdf

https://www.youtube.com/watch?v=wn6SVH6hWmo

http://smad.com

The paper describes Microcosm’s approach to developing low-cost, pressure-fed launch vehicles. While the pressure-fed designs have historically been relatively heavy compared to the traditional pump-fed designs, Microcosm's enabling critical technologies for composite tanks, high performance pressurization system, and low-cost ablative engines allow them to provide pressure-fed design solutions at a significantly lower cost and higher reliability compared to the pump-fed options while meeting the specific performance criterion of pump fed systems.

The critical technologies have been qualified. All these technologies are scalable and thus can be easily integrated to progressively larger vehicles to meet the evolving payload requirements of various defense and commercial programs.

Microcosm's approach of designing for low cost by exploiting the pressure-fed technologies has the potential to revolutionize space transportation and enable the next generation of expendable launch vehicles at greatly reduced cost.

Zero Boil Off Cryogenic Storage
http://bit.ly/2c1krI8

MEMS Cryocooler
https://pure.tue.nl/ws/files/2111874/Metis212774.pdf

MEMS Fuel Cell
http://techportal.eere.energy.gov/te....do/techID=487

MEMS Overview (use in PLSS)
http://www.eolss.net/sample-chapters...-152-07-00.pdf

A fiberglas tank that's 5.4 meters in diameter and 54 meters long contains 62,557 kg of liquid hydrogen in a 39.0 meter long section aft, and 344,068 kg of LOX in a 13.2 meter long section forward with a common bulkhead between. All bulkheads and tank ends are hemispherical and open upward like a bowl. A central LOX suction line passes from the central bulkhead to the base of the hydrogen fuel tank. LH2 suction line enclosed the LOX suction line. Two worm screw jacks each drive a separate tank bulkhead liner that is lowered as the tank drains to maintain positive displacement in each tank with no sloshing. The liner is also equipped with cryocooler driven heat exchangers to reliquefy gaseous ullage in each tank. The area forward of the LOX tank is equipped with a composite skirt and cover for the equipment to maintain zero boil off and pressure for the tanks - and has the loading and venting hardware. This also houses cross feed lines for cross feeding the engines from an external tank during flight.

The base of the hydrogen tank is surrounded by a ring of 30 composite nozzles with replaceable liner, feeding a composite aerospike engine. Each nozzle is fed from a header which has independent control of propellant into each nozzle to provide directional control fo the system.

The structural weight of each tank is 14,320 kg.

An additional 6,000 kg provides thermal protection system on the forward skirt and inflatable wings for extended cross-range glide following re-entry and slowing to subsonic speeds. The system is also equipped with advanced guidance system allow the tank to pull to a nose up orientation and land on its tail at a prepared site.

Ryan X-13 Vertijet - 1957
https://www.youtube.com/watch?v=6-T_-4nEA_M

Inflatable aircraft
https://www.youtube.com/watch?v=x3a19wDzSwU
https://www.youtube.com/watch?v=2gGygxDIJX0

Inflatable heat shield
https://www.youtube.com/watch?v=ojgDZZIsWA4

A 7 element system, is capable of placing 350,000 kg of payoad into Low Earth Orbit (LEO).

A 29.7 meter long tank pair with a 22.2 meter long LH2 tank section and a 7.5 meter long LOX tank section, contains 118,980.5 kg of LOX and 35,541.5 kg of LH2 - and is sufficient to take 118,980.5 kg payload to Low Lunar Orbit and Back.

The kick stage is topped by a passenger section consisting of 4 decks each 2.6 meters deck height - with a 2.3 meter free space between decks. Each section is 5.4 meters in diameter and has 18 seats facing radially outward, through its own transparent canopy. 72 seats in all. 60 passengers and 12 crew. Each passenger has their own biosuit, life support and rocket belt as well as AI computer. The canopy can be made opaque and used as an autostereoscopic display and cameras connected to the computer permit gesture, facial, and pattern recognition. Each passenger has an inner suit and an outer suit, and during the flight they may leave their acceleration couch with outer suit - to interact with other passengers in the 10.2 meter long by 3.4 meter cabin interior.

There is sufficient propellant on board to allow all 72 travellers to visit the moon 7x while in lunar orbit.

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

The system flies to Lunar Orbit, and then back to Earth. Astronauts travel to the lunar surface on their own rocket belts and return, spending up to 11 hours at each of 7 sites on the lunar surface.

At $0.08 per kWh it takes $1.49 million to fill up all 8 flight elements with LH2 and LOX made from water. With one launch per week, and one booster, it takes two kickstages and spacecraft. These are all built at a cost of $70 million. Another $0.12 million per flight is used to pay CAPEX, and another $0.39 million is used for maintenance and operations. A total of $2.00 million per flight. $27,800 per person. Spacesuit, and other services, cost $22,200 - a total of $50,000 per person per flight. Total cost per person is $150,000 - generating $100,000 per person in free cash flow before taxes. That's $7.2 million per launch profit. $374.4 million.

52 * 60 = 3,120 people per year. With a 3% market penetration we have a target audience of 104,000 persons. There are 172,850 people who have more than $30 million in assets in the world.

http://www.investopedia.com/terms/u/...uals-uhnwi.asp

Charging them 5% of their networth for a once in a lifetime opportunity, that's $1.5 million per flight. This generates over $3 billion in free cash flow per year. This earns $72 million per launch, which is more in keeping with the size of the launcher...

The launcher, with 35 satellites at 10,000 kg per satellite, in a same polar plane, and with 18 orbital planes, with 18 launches, to 630 satellites - providing global wireless internet via LiFi open optical communications. This allows capture of a good portion of the world's $1.2 trillion per year telecom marketplace.

The launcher can put into orbit a 7.7 GW power station, and 2,000 of these can capture a good portion of the world's $3 trillion per year energy market.

http://lasermotive.com


http://www.eucia.eu/userfiles/files/...ort_grpcrp.pdf

https://www.hydrogen.energy.gov/pdfs...mao_2012_p.pdf

There are a large number of vendors that can produce superior strength tanks that are substantially lighter and stronger than conventional tanks, built on the scale described. Each flight article will cost $319,050 a total of $2,552,400 for all eight elements per lunar vehicle. $27.7 million per article for tehnical improvements to the core airframe. A total of $28 million per article - $224 million per lunar rocket system.



 




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