Laser Launchers

http://lasermotive.com
http://www.lightcrafttechnologies.com/rpi_www/
http://ykbcorp.com/tech_precFormation.html

My friends Young Bae, Jordin Kare, and Leik Myrabo have each helped found companies following their tenure with US research in the area of high power laser systems. Lasermotive is using open optical high efficency laser energy as well as fiber optic laser energy to transmit large amounts of energy around efficiently. Leik Myrabo has founded Lightcraft Technologies to develop laser propulsion. Young Bae has founded YKB Corp to develop photonic thruster technology. This technology makes laser light sails useful for interplanetary missions.

Let's consider a 180 kg payload launched for $300,000 - using some variant of this technology.

Myrabo has reported in the literature that exhaust speeds of 20 km/sec are achievable using laser energy to energise propellant. This means that to project an object off the Earth's surface at 10.85 km/sec - with another 1.25 km/sec for air drag and gravity losses - a total of 12.10 km/sec delta vee capacity - requires a propellant fraction of 45.4% or 81.72 kg of the 180 kg system. With a 1.5 gee initial take off acceleration at the Earth's surface, this requires a propulsive force of 2,647.8 Newtons of force. A rocket with an exhaust speed of 20 km/sec requires a propellant mass flow of 0..13239 kg/sec to sustain this force. This requires a power level of 26.48 megawatts of power.

http://www.nlight.net/nlight-files/f...hotonics05.pdf

At 800 W/cm2 optical output and 70% conversion efficiency, and consumes 1,150 W/cm2, a 26.48 megawatt laser requires 196 wafers each 150 mm in diameter. The cost of each wafer is $30 or $5,880. The mask cost is $17,000. The fab cost is $510. A total fo $23,390.

http://phys.org/news/2015-03-team-de...eak-power.html

A 19 inch rack mount system has been developed that has a dozen 150 mm wafers in it (3x4) in a single 1U rack space. A 3U system produces 5.09 MW - and five units provide sufficient power to launch a 180 kg payload at 1.5 gees.

Pneumatic and electrostatic membrane optics is rapidly developing and provides a means to create very large area optics that are very precise and very light weight.

http://proceedings.spiedigitallibrar...ticleid=875235

http://goo.gl/1w02Eo

http://phys.org/news/2014-04-telesco...ics-phase.html

https://str.llnl.gov/content/pages/j...df/01.13.4.pdf

A 20 meter diameter sphere forming a thin film mirror operated on Earth beam energy at 550 nm efficiently to a 12.9 meter diameter receiver on the surface of the moon and a 1.2 meter diameter receiver at Geosynchronous Equatorial Orbit.

A twenty meter diameter sphere of 1 micron thick layer of PET plastic - formed to create a birefringent material of exceptional optical efficiency - masses only 1.8 kg.

https://research.cems.umn.edu/macosk..._shows/gbo.pdf

A film 100 microns thick (about that of common packaging materials) masses 180 kg. This is used on Earth as the source material. The cost of the hardware to form these optical components run another $22,000 approximately.

So, a 180 kg spacecraft consists of a 135 kg lunar lander and a three 15 kg reforming satellites. All are launched into space together and separate as they rise above the atmosphere. The three reforming satellites separate at 35,786 km altitude from each other and the lunar lander. One reforming satellite enters a geostationary orbit above the laser source. Two other reforming satellites enter an orbit around the moon. One flies to L2 and another flies ahead of the moon, and falls into a polar orbit that flies above the nearside farside plane. In this way, all three reforming satellites remain in constant contact with the laser source and the lunar landing satellite - both for power and open optical communications. Meanwhile the lunar lander proceeds to the lunar surface to carry out its mission.

At the end of the mission cycle, the lander returns with samples, and the reforming satellites are retrieved as well. They all rejoing reversing the process by which they were deployed, and the system comes in for a landing at the launch center.

81.72 kg propellant - to take off leaving 53.28 kg for the lander portion and 45.00 kg for the three laser reforming satellites. 11.37 kg of propellant (21.3% propellant fraction) is required to land on the moon and return to Earth. This leaves 41.91 kg for the lander.

At $0.18 per kWh the system requires $930.90 of power to eject 93.09 kg of propellant at 20 km/sec from the vehicle.

It takes 66 hours to deploy the hardware and 66 hours to retrieve it. This leaves a 36 hour window on the lunar surface for exploration and recovery of material, assuming one flight per week.

http://www.dailymail.co.uk/sciencete...away-kids.html

52 flights per year at $300,000 per flight yields $15.6 million per year. The total cost of the system is less than $1 million.

--- laser --- optics --- beam --- GEO reformer --- Lunar reformer -- Lunar Lander

On Friday, July 29, 2016 at 3:35:52 PM UTC+12, William Mook wrote:
http://lasermotive.com
http://www.lightcrafttechnologies.com/rpi_www/
http://ykbcorp.com/tech_precFormation.html

My friends Young Bae, Jordin Kare, and Leik Myrabo have each helped found companies following their tenure with US research in the area of high power laser systems. Lasermotive is using open optical high efficency laser energy as well as fiber optic laser energy to transmit large amounts of energy around efficiently. Leik Myrabo has founded Lightcraft Technologies to develop laser propulsion. Young Bae has founded YKB Corp to develop photonic thruster technology. This technology makes laser light sails useful for interplanetary missions.

Let's consider a 180 kg payload launched for $300,000 - using some variant of this technology.

Myrabo has reported in the literature that exhaust speeds of 20 km/sec are achievable using laser energy to energise propellant. This means that to project an object off the Earth's surface at 10.85 km/sec - with another 1..25 km/sec for air drag and gravity losses - a total of 12.10 km/sec delta vee capacity - requires a propellant fraction of 45.4% or 81.72 kg of the 180 kg system. With a 1.5 gee initial take off acceleration at the Earth's surface, this requires a propulsive force of 2,647.8 Newtons of force. A rocket with an exhaust speed of 20 km/sec requires a propellant mass flow of 0.13239 kg/sec to sustain this force. This requires a power level of 26.48 megawatts of power.

http://www.nlight.net/nlight-files/f...hotonics05.pdf

At 800 W/cm2 optical output and 70% conversion efficiency, and consumes 1,150 W/cm2, a 26.48 megawatt laser requires 196 wafers each 150 mm in diameter. The cost of each wafer is $30 or $5,880. The mask cost is $17,000. The fab cost is $510. A total fo $23,390.

http://phys.org/news/2015-03-team-de...eak-power.html

A 19 inch rack mount system has been developed that has a dozen 150 mm wafers in it (3x4) in a single 1U rack space. A 3U system produces 5.09 MW - and five units provide sufficient power to launch a 180 kg payload at 1.5 gees.

Pneumatic and electrostatic membrane optics is rapidly developing and provides a means to create very large area optics that are very precise and very light weight.

http://proceedings.spiedigitallibrar...ticleid=875235

http://goo.gl/1w02Eo

http://phys.org/news/2014-04-telesco...ics-phase.html

https://str.llnl.gov/content/pages/j...df/01.13.4.pdf

A 20 meter diameter sphere forming a thin film mirror operated on Earth beam energy at 550 nm efficiently to a 12.9 meter diameter receiver on the surface of the moon and a 1.2 meter diameter receiver at Geosynchronous Equatorial Orbit.

A twenty meter diameter sphere of 1 micron thick layer of PET plastic - formed to create a birefringent material of exceptional optical efficiency - masses only 1.8 kg.

https://research.cems.umn.edu/macosk..._shows/gbo.pdf

A film 100 microns thick (about that of common packaging materials) masses 180 kg. This is used on Earth as the source material. The cost of the hardware to form these optical components run another $22,000 approximately.

So, a 180 kg spacecraft consists of a 135 kg lunar lander and a three 15 kg reforming satellites. All are launched into space together and separate as they rise above the atmosphere. The three reforming satellites separate at 35,786 km altitude from each other and the lunar lander. One reforming satellite enters a geostationary orbit above the laser source. Two other reforming satellites enter an orbit around the moon. One flies to L2 and another flies ahead of the moon, and falls into a polar orbit that flies above the nearside farside plane. In this way, all three reforming satellites remain in constant contact with the laser source and the lunar landing satellite - both for power and open optical communications. Meanwhile the lunar lander proceeds to the lunar surface to carry out its mission.

At the end of the mission cycle, the lander returns with samples, and the reforming satellites are retrieved as well. They all rejoing reversing the process by which they were deployed, and the system comes in for a landing at the launch center.

81.72 kg propellant - to take off leaving 53.28 kg for the lander portion and 45.00 kg for the three laser reforming satellites. 11.37 kg of propellant (21.3% propellant fraction) is required to land on the moon and return to Earth. This leaves 41.91 kg for the lander.

At $0.18 per kWh the system requires $930.90 of power to eject 93.09 kg of propellant at 20 km/sec from the vehicle.

It takes 66 hours to deploy the hardware and 66 hours to retrieve it. This leaves a 36 hour window on the lunar surface for exploration and recovery of material, assuming one flight per week.

http://www.dailymail.co.uk/sciencete...away-kids.html

52 flights per year at $300,000 per flight yields $15.6 million per year. The total cost of the system is less than $1 million.

--- laser --- optics --- beam --- GEO reformer --- Lunar reformer -- Lunar Lander

I have been asked what these things look like, and how they work. Each device, with the exception of the terrestrial laser source, and the lunar lander, consist of two 20 meter diameter spheres maintained under pressure via electrostatic pressure. These spheres have one hemisphere that is nearly perfectly reflecting and the other hemisphere that is nearly perfectly transmissive in the wavelength of the laser. A 70% to 80% efficient solid state laser operates at 1 micron wavelength.

http://optics.org/article/19838

The reflective sphere is made of holographically patterned GBO film that focuses light to a precise point without spherical aberration despite the reflective surface being spherical. This holographic correction also provides different focal points for different colours as described in my patent on the subject. This has several applications, allowing communication multiplexing, spectral analysis, hyper efficient solar collection, in addition to very high efficiency laser transmission and reception.

So there is a hemisphere that is transparent and a hemisphere that is reflective. A hyperbolic reflector at the transparent pole. A multi-spectral solid state receiver/transmitter, at the reflective pole. Another great circle passes through the poles at right angles to the plane through which the transparent and reflective hemispheres meet. This great circle has micro-bar-codes imbedded in it and can be driven accurately with piezo drives.

Each 20 meter diameter sphere has a 10 meter ring clamp with two piezo drives located 1339.5 mm from the base of the sphere. This ring rotates 360 degrees along the ring center, and the two piezo drives rotate the sphere at right angles to this axis through 360 degrees along the polar great circle. The ring has microbarcodes as well to accurately position the ring relative to the drives. The 10 meter diameter ring forms the end of a 10 meter diameter cylinder that has a 2679 mm height. At the base of the cylinder is another 10 meter drive ring holding another 20 meter spherical assembly.

This forms the basic optical receiver/transmitter.

Four 20 meter long arms form a cross extending from the center of the 2679 mm tall cylinder. At the ends of the cross are brushless drive motors with a fan above each arm that has a 15 meter diameter rotor. Below each arm at the end is an electrospray ion engine array.

On the lunar lander portion only one 20 meter diameter sphere is carried, with landing struts extending down from the cross beams, and a carrier in the 10 meter diameter by 2.67 m long cylinder.

On the terrestrial beam source, the 10 meter base cylinder is permanently affixed to the ground, and electrical power is fed from a series of mobile gas turbines in the 60 to 180 megawatt range. (2 to 6 units)

http://www.pwps.com/download/factshe...%20Package.pdf

So, electrical power is generated and fed to the terrestrial unit which is beamed to the lower sphere of one of the regenerator units nearby. The power is regenerated and fed to the upper sphere which beams energy to the lower sphere of a second regenerator unit. That second unit beams energy to a third unit. The third unit sends power to the lunar lander unit.

The lunar lander unit takes off as a quad rotor, whilst maintaining the power link through the chain. Then the third unit takes off following it. The second unit follows next. The first unit is last. They all ascend in a chain under computer control.

The power link operates like a LiFi and permits broadband communications throughout the network of drones.

https://www.youtube.com/watch?v=YQIMGV5vtd4

https://www.youtube.com/watch?v=nhYG-IgsRJ0

They all climb to 15,000 meters in an hour.

The terrestrial unit powers the first unit which rises to 15,000 meters and hovers there for the duration of the mission. The other units fire up their ion engines at this altitude and begin accelerating under rocket power whilst shutting down and folding away their rotors. The second unit accelerates to 10.4 km/sec and costs for 5.08 hours to achieve GEO. Another 1.5 km/sec is added at 42,164 km radius to enter GEO above the launch site.

Meanwhile unit three and the lunar lander continue to boost to 10.9 km/sec and arrive at the Earth moon Lagrange Point One within 80 hours following launch. The third unit brakes at the Lagrange Point and the lunar lander continues to descend on the lunar nearside coming to rest on the Lunar surface in another 3 hours - at any point where the satellite is visible.

To land beyond the horizon on the farside an alternative strategy is to enter Lagrange Point 4 or Lagrange Point 5 so the lander may make its way to the lunar far side visible to either of these points.

To extend to points beyond the those visible from Lagrange Point 4 or 5, another alternative is to add a fourth regenerator and have it head for Lagrange Point 2 while the lander lands at a point on the moon's far side only visible from Lagrange Point 2.

http://ssl.mit.edu/publications/thes...sendBlaise.pdf

http://spectrum.ieee.org/tech-talk/a...iny-satellites

At 800 W/cm2 the areal loading of electrospray engines is equivalent to a Cessna 152 at lower performance, and an ultralight at higher performance.

Aircraft Wing load (kg/m2)

Buzz Z3.... 3.9
Fun 160.... 6.3
ASK 21...... 33
Nieuport 17 38
Ikarus C42 38
Cessna 152 49
DC-3......... 123
Spitfire...... 158
Bf-109....... 173
B-17........... 190
B-36.......... 272
Typhoon.... 311
F-104........ 514
A380......... 663
B747.......... 740
MD-11F...... 844

At 800 W/cm2.

Isp (sec) dV (km/sec) mg/sec Force (N/m2) Force (kg/m2)
1000 9.81....... 16.64 1631.55...... 166.37
2000 19.61...... 4.16 815.77...... 83.19
3000 29.42...... 1.85 543.85...... 55.46
4000 39.23...... 1.04 407.89...... 41.59
5000 49.03...... 0.67 326.31...... 33.27
6000 58.84...... 0.46 271.92...... 27.73
8000 78.45...... 0.26 203.94...... 20.80
9000 88.26...... 0.21 181.28...... 18.49
10000 98.07...... 0.17 163.15...... 16.64

On Saturday, July 30, 2016 at 2:28:33 PM UTC+12, William Mook wrote:
On Friday, July 29, 2016 at 3:35:52 PM UTC+12, William Mook wrote:
http://lasermotive.com
http://www.lightcrafttechnologies.com/rpi_www/
http://ykbcorp.com/tech_precFormation.html

My friends Young Bae, Jordin Kare, and Leik Myrabo have each helped found companies following their tenure with US research in the area of high power laser systems. Lasermotive is using open optical high efficency laser energy as well as fiber optic laser energy to transmit large amounts of energy around efficiently. Leik Myrabo has founded Lightcraft Technologies to develop laser propulsion. Young Bae has founded YKB Corp to develop photonic thruster technology. This technology makes laser light sails useful for interplanetary missions.

Let's consider a 180 kg payload launched for $300,000 - using some variant of this technology.

Myrabo has reported in the literature that exhaust speeds of 20 km/sec are achievable using laser energy to energise propellant. This means that to project an object off the Earth's surface at 10.85 km/sec - with another 1.25 km/sec for air drag and gravity losses - a total of 12.10 km/sec delta vee capacity - requires a propellant fraction of 45.4% or 81.72 kg of the 180 kg system. With a 1.5 gee initial take off acceleration at the Earth's surface, this requires a propulsive force of 2,647.8 Newtons of force. A rocket with an exhaust speed of 20 km/sec requires a propellant mass flow of 0.13239 kg/sec to sustain this force. This requires a power level of 26..48 megawatts of power.

http://www.nlight.net/nlight-files/f...hotonics05.pdf

At 800 W/cm2 optical output and 70% conversion efficiency, and consumes 1,150 W/cm2, a 26.48 megawatt laser requires 196 wafers each 150 mm in diameter. The cost of each wafer is $30 or $5,880. The mask cost is $17,000. The fab cost is $510. A total fo $23,390.

http://phys.org/news/2015-03-team-de...eak-power.html

A 19 inch rack mount system has been developed that has a dozen 150 mm wafers in it (3x4) in a single 1U rack space. A 3U system produces 5.09 MW - and five units provide sufficient power to launch a 180 kg payload at 1.5 gees.

Pneumatic and electrostatic membrane optics is rapidly developing and provides a means to create very large area optics that are very precise and very light weight.

http://proceedings.spiedigitallibrar...ticleid=875235

http://goo.gl/1w02Eo

http://phys.org/news/2014-04-telesco...ics-phase.html

https://str.llnl.gov/content/pages/j...df/01.13.4.pdf

A 20 meter diameter sphere forming a thin film mirror operated on Earth beam energy at 550 nm efficiently to a 12.9 meter diameter receiver on the surface of the moon and a 1.2 meter diameter receiver at Geosynchronous Equatorial Orbit.

A twenty meter diameter sphere of 1 micron thick layer of PET plastic - formed to create a birefringent material of exceptional optical efficiency - masses only 1.8 kg.

https://research.cems.umn.edu/macosk..._shows/gbo.pdf

A film 100 microns thick (about that of common packaging materials) masses 180 kg. This is used on Earth as the source material. The cost of the hardware to form these optical components run another $22,000 approximately.

So, a 180 kg spacecraft consists of a 135 kg lunar lander and a three 15 kg reforming satellites. All are launched into space together and separate as they rise above the atmosphere. The three reforming satellites separate at 35,786 km altitude from each other and the lunar lander. One reforming satellite enters a geostationary orbit above the laser source. Two other reforming satellites enter an orbit around the moon. One flies to L2 and another flies ahead of the moon, and falls into a polar orbit that flies above the nearside farside plane. In this way, all three reforming satellites remain in constant contact with the laser source and the lunar landing satellite - both for power and open optical communications. Meanwhile the lunar lander proceeds to the lunar surface to carry out its mission.

At the end of the mission cycle, the lander returns with samples, and the reforming satellites are retrieved as well. They all rejoing reversing the process by which they were deployed, and the system comes in for a landing at the launch center.

81.72 kg propellant - to take off leaving 53.28 kg for the lander portion and 45.00 kg for the three laser reforming satellites. 11.37 kg of propellant (21.3% propellant fraction) is required to land on the moon and return to Earth. This leaves 41.91 kg for the lander.

At $0.18 per kWh the system requires $930.90 of power to eject 93.09 kg of propellant at 20 km/sec from the vehicle.

It takes 66 hours to deploy the hardware and 66 hours to retrieve it. This leaves a 36 hour window on the lunar surface for exploration and recovery of material, assuming one flight per week.

http://www.dailymail.co.uk/sciencete...away-kids.html

52 flights per year at $300,000 per flight yields $15.6 million per year. The total cost of the system is less than $1 million.

--- laser --- optics --- beam --- GEO reformer --- Lunar reformer -- Lunar Lander

I have been asked what these things look like, and how they work. Each device, with the exception of the terrestrial laser source, and the lunar lander, consist of two 20 meter diameter spheres maintained under pressure via electrostatic pressure. These spheres have one hemisphere that is nearly perfectly reflecting and the other hemisphere that is nearly perfectly transmissive in the wavelength of the laser. A 70% to 80% efficient solid state laser operates at 1 micron wavelength.

http://optics.org/article/19838

The reflective sphere is made of holographically patterned GBO film that focuses light to a precise point without spherical aberration despite the reflective surface being spherical. This holographic correction also provides different focal points for different colours as described in my patent on the subject. This has several applications, allowing communication multiplexing, spectral analysis, hyper efficient solar collection, in addition to very high efficiency laser transmission and reception.

So there is a hemisphere that is transparent and a hemisphere that is reflective. A hyperbolic reflector at the transparent pole. A multi-spectral solid state receiver/transmitter, at the reflective pole. Another great circle passes through the poles at right angles to the plane through which the transparent and reflective hemispheres meet. This great circle has micro-bar-codes imbedded in it and can be driven accurately with piezo drives.

Each 20 meter diameter sphere has a 10 meter ring clamp with two piezo drives located 1339.5 mm from the base of the sphere. This ring rotates 360 degrees along the ring center, and the two piezo drives rotate the sphere at right angles to this axis through 360 degrees along the polar great circle. The ring has microbarcodes as well to accurately position the ring relative to the drives. The 10 meter diameter ring forms the end of a 10 meter diameter cylinder that has a 2679 mm height. At the base of the cylinder is another 10 meter drive ring holding another 20 meter spherical assembly.

This forms the basic optical receiver/transmitter.

Four 20 meter long arms form a cross extending from the center of the 2679 mm tall cylinder. At the ends of the cross are brushless drive motors with a fan above each arm that has a 15 meter diameter rotor. Below each arm at the end is an electrospray ion engine array.

On the lunar lander portion only one 20 meter diameter sphere is carried, with landing struts extending down from the cross beams, and a carrier in the 10 meter diameter by 2.67 m long cylinder.

On the terrestrial beam source, the 10 meter base cylinder is permanently affixed to the ground, and electrical power is fed from a series of mobile gas turbines in the 60 to 180 megawatt range. (2 to 6 units)

http://www.pwps.com/download/factshe...%20Package.pdf

So, electrical power is generated and fed to the terrestrial unit which is beamed to the lower sphere of one of the regenerator units nearby. The power is regenerated and fed to the upper sphere which beams energy to the lower sphere of a second regenerator unit. That second unit beams energy to a third unit. The third unit sends power to the lunar lander unit.

The lunar lander unit takes off as a quad rotor, whilst maintaining the power link through the chain. Then the third unit takes off following it. The second unit follows next. The first unit is last. They all ascend in a chain under computer control.

The power link operates like a LiFi and permits broadband communications throughout the network of drones.

https://www.youtube.com/watch?v=YQIMGV5vtd4

https://www.youtube.com/watch?v=nhYG-IgsRJ0

They all climb to 15,000 meters in an hour.

The terrestrial unit powers the first unit which rises to 15,000 meters and hovers there for the duration of the mission. The other units fire up their ion engines at this altitude and begin accelerating under rocket power whilst shutting down and folding away their rotors. The second unit accelerates to 10.4 km/sec and costs for 5.08 hours to achieve GEO. Another 1.5 km/sec is added at 42,164 km radius to enter GEO above the launch site.

Meanwhile unit three and the lunar lander continue to boost to 10.9 km/sec and arrive at the Earth moon Lagrange Point One within 80 hours following launch. The third unit brakes at the Lagrange Point and the lunar lander continues to descend on the lunar nearside coming to rest on the Lunar surface in another 3 hours - at any point where the satellite is visible.

To land beyond the horizon on the farside an alternative strategy is to enter Lagrange Point 4 or Lagrange Point 5 so the lander may make its way to the lunar far side visible to either of these points.

To extend to points beyond the those visible from Lagrange Point 4 or 5, another alternative is to add a fourth regenerator and have it head for Lagrange Point 2 while the lander lands at a point on the moon's far side only visible from Lagrange Point 2.

http://ssl.mit.edu/publications/thes...sendBlaise.pdf

http://spectrum.ieee.org/tech-talk/a...iny-satellites

At 800 W/cm2 the areal loading of electrospray engines is equivalent to a Cessna 152 at lower performance, and an ultralight at higher performance.

Aircraft Wing load (kg/m2)

Buzz Z3.... 3.9
Fun 160.... 6.3
ASK 21...... 33
Nieuport 17 38
Ikarus C42 38
Cessna 152 49
DC-3......... 123
Spitfire...... 158
Bf-109....... 173
B-17........... 190
B-36.......... 272
Typhoon.... 311
F-104........ 514
A380......... 663
B747.......... 740
MD-11F...... 844

At 800 W/cm2.

Isp (sec) dV (km/sec) mg/sec Force (N/m2) Force (kg/m2)
1000 9.81....... 16.64 1631.55...... 166.37
2000 19.61...... 4.16 815.77...... 83.19
3000 29.42...... 1.85 543.85...... 55.46
4000 39.23...... 1.04 407.89...... 41.59
5000 49.03...... 0.67 326.31...... 33.27
6000 58.84...... 0.46 271.92...... 27.73
8000 78.45...... 0.26 203.94...... 20.80
9000 88.26...... 0.21 181.28...... 18.49
10000 98.07...... 0.17 163.15...... 16.64

MW MW Element

30.0 30.0 Lunar lander
65.3 35.3 Third - L1
106.8 41.5 Second - GEO
155.7 48.8 First - Helicopter
183.1 57.5 Terrestrial unit

The first column is the power required at each stage, with all engines running full capacity. The second column is the power required at each stage, with only the lunar lander running, and power beamed through all elements in series.

The AN/SEQ-3 Laser Weapon System or XN-1 LaWS is a 30 kW directed-energy weapon developed by the United States Navy. The weapon was installed on USS Ponce for field testing in 2014. In December 2014, the United States Navy reported that the LaWS system worked perfectly, and that the commander of the Ponce is authorized to use the system as a defensive weapon.

The proposed system above is 6,000x stronger, and is quite capable of providing area defense from 15 km altitude - across a circular region 200 km in diameter centered on the source laser.

The Boeing YAL-1 Airborne Laser Testbed (formerly Airborne Laser) weapons system was a megawatt-class chemical oxygen iodine laser (COIL) mounted inside a modified Boeing 747-400F. It is primarily designed as a missile defense system to destroy tactical ballistic missiles (TBMs) while in boost phase..

The proposed system is 100x stronger, and is capable of providing battle group or area defense over a large region. Located near Mt. Aerosmith at 1.8 km elevation, beaming to a platform at 15 km altitude, the beam source could defend all of South Island New Zealand from invasion or attack. Mt Ngauruhoe at 2.3 km elevation, beaming to a similar platform at 15 km altitude, can defend all of North Island of New Zealand in a similar fashion.

https://www.cnas.org/sites/default/f...April-2015.pdf

Together these two systems could provide 100 missions to the moon and back each year earning their keep while supporting an institute of lunar studies..

* * *

Ultimately, two 180 kg payload spacecraft could carry one person each to the moon and back, provided a long duration spacesuit for extreme exploration was available with a low mass life support system.

http://www.space.com/728-high-tech-s...ploration.html

https://www.youtube.com/watch?v=sgofwf2C76g

https://en.wikipedia.org/wiki/Life_support_system

* * *

Mook on Mook

William Mook wrote:

On Friday, July 29, 2016 at 3:35:52 PM UTC+12, William Mook wrote:


I have been asked what these things look like, and how they work.


By whom? Your good friend Mook?


--
"Ordinarily he is insane. But he has lucid moments when he is
only stupid."
-- Heinrich Heine

On Sunday, July 31, 2016 at 5:40:48 AM UTC+12, Fred J. McCall wrote:
Mook on Mook

William Mook wrote:

On Friday, July 29, 2016 at 3:35:52 PM UTC+12, William Mook wrote:


I have been asked what these things look like, and how they work.


By whom? Your good friend Mook?


--
"Ordinarily he is insane. But he has lucid moments when he is
only stupid."
-- Heinrich Heine

No. By someone you don't get to know. Fact is, if those who questioned me privately wanted to be known to this group they would have asked their question publicly. Fact is, they didn't want to be associated in any way with this group. Which says a lot about what you've turned this group into.

The point is, there are a lot of innovative approaches to low cost space access. Beamed propulsion is one of the most exciting.

http://www.space.com/7067-laser-prop...lly-shine.html
http://www.wired.com/2009/02/beamed-energy-i/
http://www.greentechmedia.com/articl...energy-storage

Boosting from a Megawatt scale to a Gigawatt scale laser that boosts for a period of 15 minutes, may be run by gigawatt scale energy storage charged by the aforementioned 180 MW genset over 8 hours. A laser beam generating a 5 GW rocket exhaust produces 52 metric tons of force with a 2000 sec Isp rocket exhaust.

So, a 26 metric ton vehicle may be boosted at this power level with only Sodium Sulphur batteries added to the power train along with a swap out of higher intensity lasers that are more costly, and have 24,000 Watts/cm2 - 30x the power level per unit area of the less expensive varieties - raises raw capacity from 200 MW to 6000 MW in a hemispherical emitter 2.82 m in diameter and 1.41 m deep - operating at the focal point of the 20 meter diameter thin film mirror. This is done once the system is proven and money is being made with drone systems. Though, individuals might contemplate making a bold adventure to the moon to demonstrate the feasibility of travel there.

High intensity lasers at 24 kW/cm2

http://opticalengineering.spiedigita...icleid=1378749

Thrust Exhaust Efficiency
MTf/5GW Isp (sec)

103.98 1000
51.99 2000
34.66 3000
26.00 4000
20.80 5000
17.33 6000
13.00 8000
11.55 9000
10.40 10000

This is the obvious next step beyond the system described earlier. Lifting a 26 metric ton vehicle at 2 gees with an exhaust possessing an Isp of 2000 sec starting at 15 km altitude implies a very large vehicle compared to the 180 kg vehicle described previously.

This also implies a 41.87% propellant fraction to achieve 10.85 km/sec needed to fly to the moon. That's 10.89 tonnes of propellant leaving 15.11 tonnes of structure and propellant for landing and return.

Using 4000 sec Isp exhaust to slow a 15.11 tonne stage onto the lunar surface and launch back to Earth, requires a 11.75% propellant fraction. This is only 1.78 tonnes of added propellant to be energised by laser. This leaves 13.32 tonnes of structure and payload.

For comparison, the old Douglas DC-3 aircraft has an empty weight of 7.65 tonnes and a gross weight of 11.43 tonnes. A payload capacity of 3.00 tonnes carried 21-32 passengers with a crew of two, or 14 sleeper cabins, which included a crew of four and 12 passengers (hot swapping two of the sleeper cabins for the crew).

So, with 6.0 tonnes aboard a 15.1 tonne vehicle, permits 28 sleeper cabins facing outward across a 6 meter diameter cabin with a 3 meter diameter central section. Very similar to the Aires 1B cabin portrayed in the movie 2001: A Space Odyssey

https://www.youtube.com/watch?v=KJKT-zd3RC0

The experiences will be dramatic for these early explorers... which have the potential to transform the way we see ourselves on Earth and the future we see for ourselves, just as the original explorers transformed the view of our world.

https://www.youtube.com/watch?v=KaOC9danxNo

https://www.youtube.com/watch?v=cYMCLz5PQVw

The ability to haul 10 tonnes one way to the moon twice a week, is awesome. So, is the ability to provide national defense for a country like New Zealand with two gigawatt scale lasers.

On Sunday, July 31, 2016 at 1:16:06 PM UTC+12, William Mook wrote:
On Sunday, July 31, 2016 at 5:40:48 AM UTC+12, Fred J. McCall wrote:
Mook on Mook

William Mook wrote:

On Friday, July 29, 2016 at 3:35:52 PM UTC+12, William Mook wrote:


I have been asked what these things look like, and how they work.


By whom? Your good friend Mook?


--
"Ordinarily he is insane. But he has lucid moments when he is
only stupid."
-- Heinrich Heine

No. By someone you don't get to know. Fact is, if those who questioned me privately wanted to be known to this group they would have asked their question publicly. Fact is, they didn't want to be associated in any way with this group. Which says a lot about what you've turned this group into.

The point is, there are a lot of innovative approaches to low cost space access. Beamed propulsion is one of the most exciting.

http://www.space.com/7067-laser-prop...lly-shine.html
http://www.wired.com/2009/02/beamed-energy-i/
http://www.greentechmedia.com/articl...energy-storage

Boosting from a Megawatt scale to a Gigawatt scale laser that boosts for a period of 15 minutes, may be run by gigawatt scale energy storage charged by the aforementioned 180 MW genset over 8 hours. A laser beam generating a 5 GW rocket exhaust produces 52 metric tons of force with a 2000 sec Isp rocket exhaust.

So, a 26 metric ton vehicle may be boosted at this power level with only Sodium Sulphur batteries added to the power train along with a swap out of higher intensity lasers that are more costly, and have 24,000 Watts/cm2 - 30x the power level per unit area of the less expensive varieties - raises raw capacity from 200 MW to 6000 MW in a hemispherical emitter 2.82 m in diameter and 1.41 m deep - operating at the focal point of the 20 meter diameter thin film mirror. This is done once the system is proven and money is being made with drone systems. Though, individuals might contemplate making a bold adventure to the moon to demonstrate the feasibility of travel there.

High intensity lasers at 24 kW/cm2

http://opticalengineering.spiedigita...icleid=1378749

Thrust Exhaust Efficiency
MTf/5GW Isp (sec)

103.98 1000
51.99 2000
34.66 3000
26.00 4000
20.80 5000
17.33 6000
13.00 8000
11.55 9000
10.40 10000

This is the obvious next step beyond the system described earlier. Lifting a 26 metric ton vehicle at 2 gees with an exhaust possessing an Isp of 2000 sec starting at 15 km altitude implies a very large vehicle compared to the 180 kg vehicle described previously.

This also implies a 41.87% propellant fraction to achieve 10.85 km/sec needed to fly to the moon. That's 10.89 tonnes of propellant leaving 15.11 tonnes of structure and propellant for landing and return.

Using 4000 sec Isp exhaust to slow a 15.11 tonne stage onto the lunar surface and launch back to Earth, requires a 11.75% propellant fraction. This is only 1.78 tonnes of added propellant to be energised by laser. This leaves 13.32 tonnes of structure and payload.

For comparison, the old Douglas DC-3 aircraft has an empty weight of 7.65 tonnes and a gross weight of 11.43 tonnes. A payload capacity of 3.00 tonnes carried 21-32 passengers with a crew of two, or 14 sleeper cabins, which included a crew of four and 12 passengers (hot swapping two of the sleeper cabins for the crew).

So, with 6.0 tonnes aboard a 15.1 tonne vehicle, permits 28 sleeper cabins facing outward across a 6 meter diameter cabin with a 3 meter diameter central section. Very similar to the Aires 1B cabin portrayed in the movie 2001: A Space Odyssey

https://www.youtube.com/watch?v=KJKT-zd3RC0

The experiences will be dramatic for these early explorers... which have the potential to transform the way we see ourselves on Earth and the future we see for ourselves, just as the original explorers transformed the view of our world.

https://www.youtube.com/watch?v=KaOC9danxNo

https://www.youtube.com/watch?v=cYMCLz5PQVw

The ability to haul 10 tonnes one way to the moon twice a week, is awesome. So, is the ability to provide national defense for a country like New Zealand with two gigawatt scale lasers.

http://lae.mit.edu/ehd/

Jets produce 2 Newtons per kW and ionic thrusters produce 110 Newtons per kW. So, a 30 MW system produces 60,000 kiloNewtons - or about 6 tons of thrust using jet power - and 3.3 meganewtons - or 330 tons of thrust using ionic thrusters! (310 kgf as an ion engine operating at 2000 sec Isp).

Now, the point is, that instead of a separate brushless motor and rotor combination, the electrospray ion engine high voltage section can be configured as an ionic thruster - radically reducing power levels to produce lift, and increasing altitude for a given power level - to about 30 km to 45 km - from 15 km.

The same electro static pressure that is used to stabilise optics can also be used to impart motion to surrounding air to provide lift for propulsive and guidance inputs with no separate moving parts.

On Sunday, July 31, 2016 at 1:42:47 PM UTC+12, William Mook wrote:
On Sunday, July 31, 2016 at 1:16:06 PM UTC+12, William Mook wrote:
On Sunday, July 31, 2016 at 5:40:48 AM UTC+12, Fred J. McCall wrote:
Mook on Mook

William Mook wrote:

On Friday, July 29, 2016 at 3:35:52 PM UTC+12, William Mook wrote:


I have been asked what these things look like, and how they work.


By whom? Your good friend Mook?


--
"Ordinarily he is insane. But he has lucid moments when he is
only stupid."
-- Heinrich Heine

No. By someone you don't get to know. Fact is, if those who questioned me privately wanted to be known to this group they would have asked their question publicly. Fact is, they didn't want to be associated in any way with this group. Which says a lot about what you've turned this group into.

The point is, there are a lot of innovative approaches to low cost space access. Beamed propulsion is one of the most exciting.

http://www.space.com/7067-laser-prop...lly-shine.html
http://www.wired.com/2009/02/beamed-energy-i/
http://www.greentechmedia.com/articl...energy-storage

Boosting from a Megawatt scale to a Gigawatt scale laser that boosts for a period of 15 minutes, may be run by gigawatt scale energy storage charged by the aforementioned 180 MW genset over 8 hours. A laser beam generating a 5 GW rocket exhaust produces 52 metric tons of force with a 2000 sec Isp rocket exhaust.

So, a 26 metric ton vehicle may be boosted at this power level with only Sodium Sulphur batteries added to the power train along with a swap out of higher intensity lasers that are more costly, and have 24,000 Watts/cm2 - 30x the power level per unit area of the less expensive varieties - raises raw capacity from 200 MW to 6000 MW in a hemispherical emitter 2.82 m in diameter and 1.41 m deep - operating at the focal point of the 20 meter diameter thin film mirror. This is done once the system is proven and money is being made with drone systems. Though, individuals might contemplate making a bold adventure to the moon to demonstrate the feasibility of travel there.

High intensity lasers at 24 kW/cm2

http://opticalengineering.spiedigita...icleid=1378749

Thrust Exhaust Efficiency
MTf/5GW Isp (sec)

103.98 1000
51.99 2000
34.66 3000
26.00 4000
20.80 5000
17.33 6000
13.00 8000
11.55 9000
10.40 10000

This is the obvious next step beyond the system described earlier. Lifting a 26 metric ton vehicle at 2 gees with an exhaust possessing an Isp of 2000 sec starting at 15 km altitude implies a very large vehicle compared to the 180 kg vehicle described previously.

This also implies a 41.87% propellant fraction to achieve 10.85 km/sec needed to fly to the moon. That's 10.89 tonnes of propellant leaving 15.11 tonnes of structure and propellant for landing and return.

Using 4000 sec Isp exhaust to slow a 15.11 tonne stage onto the lunar surface and launch back to Earth, requires a 11.75% propellant fraction. This is only 1.78 tonnes of added propellant to be energised by laser. This leaves 13.32 tonnes of structure and payload.

For comparison, the old Douglas DC-3 aircraft has an empty weight of 7.65 tonnes and a gross weight of 11.43 tonnes. A payload capacity of 3.00 tonnes carried 21-32 passengers with a crew of two, or 14 sleeper cabins, which included a crew of four and 12 passengers (hot swapping two of the sleeper cabins for the crew).

So, with 6.0 tonnes aboard a 15.1 tonne vehicle, permits 28 sleeper cabins facing outward across a 6 meter diameter cabin with a 3 meter diameter central section. Very similar to the Aires 1B cabin portrayed in the movie 2001: A Space Odyssey

https://www.youtube.com/watch?v=KJKT-zd3RC0

The experiences will be dramatic for these early explorers... which have the potential to transform the way we see ourselves on Earth and the future we see for ourselves, just as the original explorers transformed the view of our world.

https://www.youtube.com/watch?v=KaOC9danxNo

https://www.youtube.com/watch?v=cYMCLz5PQVw

The ability to haul 10 tonnes one way to the moon twice a week, is awesome. So, is the ability to provide national defense for a country like New Zealand with two gigawatt scale lasers.

http://lae.mit.edu/ehd/

Jets produce 2 Newtons per kW and ionic thrusters produce 110 Newtons per kW. So, a 30 MW system produces 60,000 kiloNewtons - or about 6 tons of thrust using jet power - and 3.3 meganewtons - or 330 tons of thrust using ionic thrusters! (310 kgf as an ion engine operating at 2000 sec Isp).

Now, the point is, that instead of a separate brushless motor and rotor combination, the electrospray ion engine high voltage section can be configured as an ionic thruster - radically reducing power levels to produce lift, and increasing altitude for a given power level - to about 30 km to 45 km - from 15 km.

The same electro static pressure that is used to stabilise optics can also be used to impart motion to surrounding air to provide lift for propulsive and guidance inputs with no separate moving parts.


The longitude of New Zealand is centered on 174.88 degrees East. This ranges from 166.42 degrees East to 178.55 degrees East, which is empty at the moment;

166.0°E Intelsat 8 FS-1300 US 4 November 1998, Proton-K
178.0°E Inmarsat-3 F3 UK 18 December 1996, Atlas IIA
180.0°W Intelsat-18 5 October 2011 Zenit
177.1°W Yamal 300K CIS Russia 2 November 2012 Proton-M

http://www.satview.org

Launching two hovering platforms to an altitude of 45 km (147,600 ft) - one above North Island another above South Island, sees out to an horizon 795 km (494 miles) away. That's a region 1590 km (988 miles) in diameter.

Launching two GEO satellites one at 170.0°E another at 174.0°E provides continuous coverage along with the hovering platforms. Then, another two Lagrange Point One satellites are launched. Finally one payload is launched every 8 hours from each of the locations. A total of 2,192 launches per year. A fleet of 42 flight vehicles are required to allow this quantity of flights and two spares for down time.

William Mook wrote:

On Sunday, July 31, 2016 at 5:40:48 AM UTC+12, Fred J. McCall wrote:
Mook on Mook

William Mook wrote:

On Friday, July 29, 2016 at 3:35:52 PM UTC+12, William Mook wrote:


I have been asked what these things look like, and how they work.


By whom? Your good friend Mook?


No. By someone you don't get to know. Fact is, if those who questioned me privately wanted to be known to this group they would have asked their question publicly. Fact is, they didn't want to be associated in any way with this group. Which says a lot about what you've turned this group into.


Let me get this straight. People who don't want to be associated in
any way with this group want you to post TO THIS GROUP. That makes as
much sense as most of the nonsense you post.


The point is, there are a lot of innovative approaches to low cost space access. Beamed propulsion is one of the most exciting.


No, the point is that you're Mookspewing more Mookcrap about yet
another Mookpet.


--
You are
What you do
When it counts.

Mook on Mook on Mook at the request of Mook and his Imaginary Friends
for clarification of Mook on Mook.

William Mook wrote:

On Sunday, July 31, 2016 at 1:42:47 PM UTC+12, William Mook wrote:
On Sunday, July 31, 2016 at 1:16:06 PM UTC+12, William Mook wrote:
On Sunday, July 31, 2016 at 5:40:48 AM UTC+12, Fred J. McCall wrote:
Mook on Mook

William Mook wrote:

On Friday, July 29, 2016 at 3:35:52 PM UTC+12, William Mook wrote:

A moving sidewalk built above the bluffs of Akaroa forming a circle 20.5 km in radius and 128.8 km in circumference from the basis of a city of 26 million people living in the lap of automated luxury.

https://www.scribd.com/doc/212157834/Super-Cities
https://www.scribd.com/doc/212226819/Super-Cities-2

At South Latitude -43.815 degrees and East Longitude 173.017 degrees, and altitude 458 meters just SouthEast of present day Akaroa, a laser launcher is built, which founds the city. Starting first, sending small spacecraft to the moon and returning them to Earth, then sending individuals in long-duration spacesuits to the moon and then back. Finally upgrading the power level of the system, and sending large spacecraft to the moon and back.

Other missions include asteroid mining, space solar power, communications network, global surveillance and mapping, aerial farms, drone delivery and processing of resources.

https://www.scribd.com/doc/212158958/Asteroid-Mining
https://www.scribd.com/doc/117734807/Alinda-Asteroids
https://www.scribd.com/doc/117734816...2-Through-2045
https://www.scribd.com/document/117734864/AIAA-3890-246
https://www.scribd.com/document/1177...der-Digger-Dog
https://www.scribd.com/document/117734981/Appendix
https://www.scribd.com/document/117734923/Itokawa
https://www.scribd.com/document/1304...ower-Satellite
https://www.scribd.com/doc/130451640/Space-Solar
https://www.scribd.com/document/121742582/Aerial-Farms
https://www.scribd.com/document/106112900/Resources

New Zealand's population is presently 4,242,000 people with $166.1 billion per year GDP - $43,940 per year per person (US dollars). In economic might New Zealand is between Iowa and Kansas.

Using an advanced launcher in the mountains surrounding Akaroa, access to space tourism is provided. Later space based infrastructure taps significant revenues for the country.

The global telecom services market is $1,336.53 billion US dollars per year.. Global energy demand is 12.3 trillion watts consuminb 9,301 million tons of oil equivalent worth $1,914.55 billion per year. Global material demand adds another $503.62 billion per year.

http://www.bp.com/en/global/corporat...ld-energy.html

So, together telecom market and energy market combine to generate $3,759.70 billion per year. This is 19.6x the value of the present New Zealand economy.

Adding 21,758,000 people to the New Zealand population, by building a Supercity around the Akroa penninsula as described above, as the off-world infrastructure is constructed, supports a GDP per capita of $144,603.84 per year in US dollars. This approaches Quatar on a per capita basis. The falls between Germany and Japan in raw GDP, despite the small population!

Self replicating machinery that consists of 14.73 um diameter spherical cells occupying 1675 um3, and massing 1.675 nanograms. The cell intercepts 170.4 nanowatts of solar power on a sunny day. This is 101,731 Watts/kg. It takes 2.5 minutes of exposure to sunlight on Earth's surface, for the cell to receive sufficient power to replicate itself. Thus, 24 replications takes place per hour of sunlight. One cell grows in size to 16.78 million cells in an hour. 281.48 trillion cells in two hours. 4.72 sextillion cells in three hours.

1 hour - 28.1 milligrams
2 hours - 471.47 kg
3 hours - 7.91 million metric tons.

For 26 million persons and 70 tonnes per person, it takes 3 hours 11 minutes to grow from a single cell to the city described at the outset here. The energy 90.4 billion watts sufficient for 26 million persons, is supplied by a single solar power satellite orbiting above the city. Another 21 minutes grows the city to encompass 7.5 billions throughout the world.

Subterranean and subocean tunnels connect the major population centers of the world, totalling 1.6 million km. A 20 meter diameter tunnel this length displaces 502.65 billion cubic meters of Earth comprising 1.41 trillion metric tons of material. 187.65 tonnes per person is mined, and from this extracted the raw materials needed to build the infrastructure required for all persons.

https://worldlandbridge.com

Once the infrastructure is in place, people are well housed and free to move around the planet. There are a dozen space ports located around the world and 20 million per year, per space port, find their way off world, mostly to Mars.

At 40 persons per launch, and one launch per minute - from each of the dozen sites - 240 million people per year are dispatched into space. People travel into orbit and are placed in suspended animation once in a parking orbit. There they wait until their destination, Mars, is properly placed. This occurs once every 2.15 years. Those who choose to wait 2.15 years pay a discounted price. Those who launch nearer the day of departure, pay a premium. Those who remain animated, pay a super premium.

Ships are all dispatched in a few weeks around the synodic period between worlds.

An icosohedron has 12 vertices, 30 edges and 20 triangular regions. So, we have 30 meglev tracks each 4,190.27 km long connecting a dozen cities at their centres. Each city is covered by a dome 583.4 km in diameter housing up to 1.25 billion persons each. 15 billion urban dwellers total.

Mars' atmosphere consists of 24.37 trillion tonnes of carbon dioxide, 445.31 trillion tonnes of argon gas, and 305.26 trillion tonnes of nitrogen gas. Water ice is abundant on the planet. Extracting nitrogen from the air, and pressurising it to Earth normal pressure, and extracting oxygen from water mined from the Martian surface, and using more water to bring water vapour to Earth normal levels, permits covering 3.207 million sq km of land with Earth normal atmosphere. Divided among a dozen cities this is 267,322 sq km per city. A disc 583.4 km in diameter. A single dome 170 meters tall at the centre and 30 meters tall at the periphery.

http://orig01.deviantart.net/48d5/f/...la-d89cu7g.jpg

http://www.worldometers.info/world-population/

7.44 billion people alive today, growing at 1.1227% per annum, with 240 million leaving Earth each year for Mars, we have;

Year Earth Mars

2016 7,440.0
2017 7,523.5
2018 7,368.0 240.0 -- 20 million per city
2019 7,210.7 482.7

2020 7,051.7 728.1
2021 6,890.8 976.3
2022 6,728.2 1,227.2 ---100 million per city
2023 6,563.7 1,481.0
2024 6,397.4 1,737.7

2025 6,229.3 1,997.2
2026 6,059.2 2,259.6
2027 5,887.2 2,525.0
2028 5,713.3 2,793.3
2029 5,537.5 3,064.7

2030 5,359.6 3,339.1
2031 5,179.8 3,616.6 --- 300 million per city
2032 4,998.0 3,897.2
2033 4,814.1 4,180.9
2034 4,628.1 4,467.9

2035 4,440.1 4,758.0 — Mars exceeds Earth
2036 4,249.9 5,051.4
2037 4,057.6 5,348.1
2038 3,863.2 5,648.2
2039 3,666.6 5,951.6

2040 3,467.7 6,258.4
2041 3,266.7 6,568.7
2042 3,063.4 6,882.4
2043 2,857.7 7,199.7 --- 600 million per city
2044 2,649.8 7,520.5

2045 2,439.6 7,845.0
2046 2,227.0 8,173.0
2047 2,012.0 8,504.8 --- 50% design capacity
2048 1,794.6 8,840.3
2049 1,574.7 9,179.5

2050 1,352.4 9,522.6
2051 1,127.6 9,869.5
2052 900.2 10,220.3
2053 670.3 10,575.1
2054 437.9 10,933.8

2055 202.8 11,296.5 — Immigration Ends (75% full)