Magnetic Elevator

[belovelife]

nice thats my friends from the space generation advisory council

this was a pic from the international space agency (uhhh)

but either way

it is a series of pictures

i think 100km long electromagnetic launch system that

is desighned to get into LEO

although it would work it would cost alot and need alot of land

but on the moon if we used it, it would basically be able to launch to any destination in our solarsystem using not only the orbital momentum of the moon and its minimal gravity, but you could shoot through the solar system and use the planets for additional gravity boost...etc..etc..etc..

 

either way it works like the proposed under-ocean train from JAPAN to the US

with switching electromagnetic "rails"it turn on and off magnets similar to a particle accelerator, so you can achieve supersonic speeds

and with enough distance it won't crush our delicate ( :doh: )

bodies

 

 

ooops......see next post

[belovelife]

The core propulsion element of the proposed IASL System will be based on Electromagnet Repulsor Technology used only as a Propulsion Element, and "NOT" to Levitate or Suspend the EM Launch Sled & RLV/SSTO Space Plane during the launch sequence. No need to waste limited money and resources to try to manipulate and control this very precise and very hard to control approach of Levitation or Suspension, especially at Mach 1 or 2, which must be achieved! The use of Electromagnetic Repulsor Technology for “Propulsion Only” is a relatively simple application, and is very straight forward, at least from a control standpoint. Turn the power level up and get more thrust; and, turn the power level down and get less thrust. The use of Electromagnetic Forces as the Core Propulsion Element means that "NO" Reaction Fuel (Liquid or Solid) and the Related Structure which would be required to house this Reaction Fuel and the Engine or Nozzle Elements that would be needed to Translate the Reaction Fuel into Propulsion Forces. This all adding up to great Mass, Bulk, and Complexity to the EM Launch Sled, RLV/SSTO Vehicle, and will also translate into much greater Loads/Stress on the EM Launch Sled, RLV/SSTO Vehicle, and Indeed on the IASL Ramp Structure which will be required to bear the Shear Mass & Weight of all this Reaction Fuel, Extra Structure, and Propulsion System whatever that may be; and as well, will bear the dramatically increased and induced Stress and Loads as a result of all this extra Mass on board. Using a Electromagnetic Repulsor Based Propulsion system means the Thrust or Propulsion Forces generated will be limited only by the amount of power that can be generated & transmitted to, and through, the IASL Ramp System & EM Launch Sled; and that "NO" Reaction Mass, Extra Structure, or Complex Propulsion System is required; so, the IASL System & EM Launch Sled would “ONLY” need to carry the Repulsor Coils & Structure to support the RLV/SSTO Space Plane, Only! This means Dramatically Less Onboard Mass, which will translate into a Dramatic Reduction in Mass & Complexity of the IASL System & EM Launch Sled, and related Stress & Forces on the Entire IASL System & Ramp Structure. This Electromagnetic Repulsor System would be able to provide a variety of Acceleration Forces and Release Speeds, just like an Aircraft Carrier Catapult System does on a smaller scale. Each RLV/SSTO Space Plane or Launch Vehicle, would have very different launch acceleration force & release speed requirements and specifications based on the vehicles mission parameters and cargo sensitivity to acceleration G-forces. Human & G-Sensitive Cargo Missions for "Low-G" Launch; and Non-Human & Non-G-Sensitive Cargo Missions for "High-G" Launch. Just exactly like a modern Aircraft Carrier Catapult launches a wide range of Aircraft Types, Sizes, and Weight; at a wide range of Acceleration G-Forces and Release Speeds.

 

Also, as far as the IASL Ramp Launch Location and Configuration! A Location on the Earths Equator or as Close as Possible; and to use a Mountain Site which can provide a near constant slope or grade as close to 45 degrees as possible; and to have a total Track Length between 4 and 7 miles. This Launch Site will have a large airfield able to support a wide range of operations; both commercial passenger & cargo, and launch operations and related air traffic needs. RLV/SSTO Space Plane or Launch Vehicles can be built or serviced or received from orbit, from anywhere in the world, and then shuttled to the Orbital Launch Site with small intercontinental ferry trips, for launch preparation and orbital launch, at the primary IASL site, or sites. Brazil and Ecuador, would be good locations.

 

Also, as far as the RLV/SSTO Vehicle, we are using the X-33 Venture Star as a “BASE LINE” vehicle. Other similar Space Plane efforts in Russia, Europe, India could also be used as potential candidates for the IASL System as RLV/SSTO ISP Launch Vehicles, such as AVATAR, BE Sanger 600, and others as well. We don’t want to reinvent the wheel, and so intend to utilize what is here now!

 

* Keep it as simple, noncomplex, and straightforward as possible, using as much off the shelf technology & knowledge as possible!

 

* Develop, Construct, and Operate the ISP Program & IASL System in an Airbus Industries like Management Model, with a Philosophy of “Pay As You GO” & “Launch For Hire”, backed by Multi-National Government Core Infrastructure and Supported & Used By Private Sector Organizations & Entrepreneurial Investment & Uses. A Core Focus of Providing 10 to 20 launches Per Day!

 

Directives & Objectives & Base Line: ISA – ( ISP ) Program & ( IASL ) System

 

*This is what the International Space Plane (ISP) & International Assisted Space Launch (IASL) System Program is all about!

 

01) Electromagnetic Repulsor Propulsion Based System - Onsite Nuclear or Conventional Power Station, Transmission, Storage.

 

02) Launch Ramp Length - 4? to 7? Miles ( ¿ Mile Horizontal, ¿ Mile Transition Horizontal to 45 Degrees, 3 miles at 45 Degrees )

 

03) Launch Ramp Angle - As Near To 45 Degrees As Possible.

 

04) Launch Ramp Location - Earths Equator or as close as possible and the Highest Mountain Site able to obtain or access.

 

05) RLV/SSTO Launch Vehicle - Use of X-33 as System Base Line, but we are reviewing numerous other USA, Russian, European,

Indian RLV/SSTO Vehicles as potential ISP/IASL Program candidates.

 

06) ISP/IASL Program - Conducted in a Airbus Industries like Management Model, using “PAY AS YOU GO” & “LAUNCH FOR

HIRE” strategies, through Multi-National Government & Private Sector Collaborative/Cooperative Infrastructure & Programs.

 

07) ISP/IASL Program - would be conducted through the ISA Organization & Charter and Treaty Based. Non-Military Program.

 

08) ISP/IASL Program - from Start to Full Operation will be planned to be completed in 5 to 7 years, and able to maintain a routine

daily launch schedule of between 10 to 20 launches per day, as its base line operation goals.

 

09) Once the ISP/IASL Program is in full operation - Second site near by, or other location on Earths Equator, will start to be

implemented, and will then offer two fully operational ISP/IASL systems, so as to have Program redundancy and back up in

case of mishap, or down time for conducting routine maintenance, regular upgrades, and safety checks.

 

10) Orbital Refueling Capability - would be a major element of ISP/IASL Program. Allowing wider range of Orbital Orbital Break Options & Capabilities. Excess power at Launch Site will be used to crack water into H2 & O2 for RLV/SSTO Fuel needs.

 

Dr. Kenneth House, Scientist & Researcher, NASA, Marshall Space Flight Center – My research has primarily investigated the use of linear induction motors as the launch-assist propulsion. From the maglev trains and emals catapult developments, it appears that the technology is available to move large masses at subsonic speeds. A trade study was done in the mid-90's that showed an optimum speed of ~ 300 - 400 nts with decreasing returns as the launch-assist speed went higher due to the aerodynamic loads. The ramp concept does require an additional thrust component from the motor for the gravity load, which requires more electrical power and weight in the track. The failure mode of losing power and rolling back down into your launch facility must be considered. Electrical Power Generation (such as flywheel alternators to supply power); Power Conditioning Equipment (AC to the DC Bus Voltage); Variable Frequency Inverters for the linear motor; Closed-Loop Position Feedback Controller; Release Mechanism and Controller; Carrier Vehicle - Logistics, Handling, Maintenance; Flight Vehicle - Logistics, Handling, Storage, Maintenance, Fueling, Loading, Command & Control Center. Should reference John Suter & Gordon Woodcock's ARTS concept. The EM technology exists for subsonic transport of massive objects, but I am unaware of any research that indicates it would work for MACH 1 or 2, or higher, which is the regime in which you propose to operate. The NASA EMLA working group has its own agenda & strategy for research, you are invited to join them. See what they are doing and how you can participate & contribute. Contact Michael Wright at Goddard.

 

Mr. Jerald Schneider, PE, SE, President & CEO, Schneider Structural Engineering, Inc. – The structural design would not be exceptional in materials. Special regard for non-magnetic materials and consideration of thermal effects if rocket assisted acceleration is used. Design within high magnetic field environments can be accomplished with minimal or no new technology. Analysis & design of the structure under high dynamic loads is within the current available technology. Selecting a site away from the areas that significant technical prowess will greatly affect the efficiency and expense of operations. Environmental studies & impact studies will be required and must be considered in the selection of the site. Costs of construction will greatly increase as the location becomes increasingly remote. Quality Control of all elements of the ramp construction, maintenance, and operation will increase as the site becomes increasingly remote. Regular inspection of the ramp structure will be required. Sensors could be included in the initial design of the structure to aid in determining the health and ongoing safety of the structure.

 

Dr. Alexander Bolonkin, Scientist ( Russia & USA ) - I think, it will useful to consider the researching a cable-fly-wheel propulsion system as the alternative and supporting propulsion (thrust) system. The final speed is not much (M=2) and launcher does not have to totally depend on the electromagnetic system thrust. The cable-fly-wheel thrust system is a cheap thrust system and used as aircraft catapults in aircraft carriers and glider fields. The cable-fly-wheel could be located up-range with the cables attached to either side of the launch sled and could pull the sled and vehicle up the 45 degree incline, and add additional thrust forces in addition to the Electromagnetic Thrust. Not necessary to do the installation near equator. The profit is small (about 100 m/s), but that creates a lot of problems with foreign countries. The latitude may be 30 degree from equator. Design of any NEW installation is begun with the TEORETICAL RESEARCHS, ESTIMATIONS, and COMPUTATIONS. That must be the goal of STAGE 1. This Stage 1 outline requests 6-12 months of time for completion, and will be cost a minimum of around $500,000. That is the basis for all the next Stages and research. Results will be the main parameters of future system. If not done at this stage, proposal supporters will not know what technology & manufacturing is needed. Stage 1 allows for final decision about possibility, cost, and profit of the proposed system.

 

INTERNATIONAL SPACE PLANE ( I. S. P.) PROGRAM

International Assisted Space Launch ( I. A. S. L. ) System

http://www.international-spaceplane-program.org