| ...Impulse Engine Configurations | |
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The main impulse engine is normally located along the centerline of the spacecraft. Four individual impulse engines are grouped together to form the MIE, and two groups of two engines form the engines on saucer modules. Each engine consists of three basic components: impulse reaction chamber(three per engine), accelerator\generator, driver coil assembly, and vectored exhaust director. The IRC is an armored sphere six meters in diameter, designed to contain the energy released in a conventional deuterium-fusion reaction. It is constructed of eight layers of dispersion-strengthened hafnium excelinide with a total wall thickness of 674 cm. A replaceable inner layer of crystalline galium flouride 40cm thick protects the structural sphere from heat and radiation effects. Penetrations are made into the sphere for reaction exhaust, pellet injectors, standard fusion initiators and sensors. Slush deuterium from the main cryo tank is heated and fed to interium supply tanks where the heat energy is removed, bringing the deuterium down into a frozen state, where it is formed into pellets. Pellets can range in size from .5cm to 5cm, depending on the desired energy output per unit time. A standing pulsed fusion shock front is created by the laser initiators ranged around the forward inner surface of the sphere. The total instantaneous output of the IRC is throttleable from 10^8 to 10^11 megawatts. High-Energy plasma created during engine operation is exhausted through a central opening in the sphere to the accelerator\generator. This stage is generally cylindrical, 3.1 meters long and 5.8 meters in diameter, constructed of an integral single-crystal duranium frame and pryovunide exhaust accelerator. During propulsion operations, the accelerator is active, raising the velocity of the plasma and passing it on to the third stage. The third stage of the engine is the driver coil assembly. The DCA is 6.5 meters long and 5.8 meters in diameter and consists of a series of 6 split toroids, each manufactured from cast verterium cortenide 934. Energy from the accelerated plasma, when driven through the toroids, creates the necessary combined field effect that (1) reduces the apparent mass of the spacecraft at its inner surface and (2) facilitates the slippage of the continuum past the spacecraft at its outer surface. The final stage is the vectored exhaust director. The VED consists of a series of moveable vanes and channels designed to expel exhaust products in a controlled manner. The VED is capable of steerable propulsive and nonpropulsive modes. -Muon-Proton Fusion Impulse The main impulse engine is normally located along the centerline of the spacecraft. Four individual impulse engines are grouped together to form the MIE, and two groups of two engines form the engines on saucer modules. Each engine consists of four basic components: impulse reaction chamber(three per engine), muon generator\injector, accelerator\generator, driver coil assembly, and vectored exhaust director. The IRC is an armored oblate spheroid six meters in diameter, designed to contain the energy released in the enhanced muon-aided reaction. It is constructed of eight layers of dispersion-strengthened hafnium excelinide with a total wall thickness of 654 cm. A replaceable inner layer of crystalline galium flouride 70cm thick protects the structural sphere from heat and radiation effects. Penetrations are made into the sphere for reaction exhaust, pellet injectors, high-energy pulse laser fusion initiators, muon particle-beam injectors and normal sensors. Slush deuterium from the main cryo tank is heated and fed to interium supply tanks where the heat energy is removed, bringing the deuterium down into a frozen state, where it is formed into pellets. Pellets can range in size from .5cm to 5cm, depending on the desired energy output per unit time. A standing pulsed fusion shock front is created by the laser initiators ranged around the forward inner surface of the sphere. Then muons are injected from a adjacent particle accelerator dedicated to the production of these particles. The total instantaneous output of the IRC is throttleable from 10^11 to 10^16 megawatts. High-Energy plasma created during engine operation is exhausted through a central opening in the sphere to the accelerator\generator. This stage is generally cylindrical, 3.5 meters long and 6.3 meters in diameter, constructed of an integral single-crystal duranium frame and pryovunide exhaust accelerator. During propulsion operations, the accelerator is active, raising the velocity of the plasma and passing it on to the third stage. The third stage of the engine is the driver coil assembly. The DCA is 6.5 meters long and 5.8 meters in diameter and consists of a series of 7 split toroids, each manufactured from cast verterium cortenide 934. Energy from the accelerated plasma, when driven through the toroids, creates the necessary combined field effect that (1) reduces the apparent mass of the spacecraft at its inner surface and (2) facilitates the slippage of the continuum past the spacecraft at its outer surface. The final stage is the vectored exhaust director. The VED consists of a series of moveable vanes and channels designed to expel exhaust products in a controlled manner. The VED is capable of steerable propulsive and nonpropulsive modes. -CBFR Impulse Engine- The main impulse engine is normally located along the centerline of the spacecraft. Four individual impulse engines are grouped together to form the MIE, and two groups of two engines form the engines on saucer modules. Each engine consists of three basic components: impulse reaction chamber(three per engine), accelerator\generator, driver coil assembly, and vectored exhaust director. The IRC is an armored cylinder 6 meters long, 5.2 meters in diamter, designed to contain the energy released in a boron^11-hydrogen reaction. It is constructed of 12 layers of dispersion-strengthened hafnium excelinide with a total wall thickness of 512 cm. A replaceable inner layer of crystalline galium flouride 40cm thick protects the structural cylinder from heat and radiation effects. At either end are two magnetic field generators, constructed from cobalt-lanthanide-boronite, which set up the magnetic mirror configuration for proper fuel burnup. Penetrations are made into the cylinder for reaction exhaust, hydrogen injectors, ionized boron-beam injectors and sensors. Solid boron from the main storage facility is heated until molten, where it is then pumped down into ionization chambers via ceramic-lined pressure tubes. Once the boron is ionized by the high-energy electron beams in the ionization chambers it is fed into the IRC cylinder, which whirls it around at a constant 97% of the speed of light. Slush hydrogen from the main cryo tank is heated and fed to interium supply tanks, where thin rivulets are measured out and fed into synchrotron accelerators. This proton beam is fed directly into the reactor, going in the opposite direction of the boron beam. The total instantaneous output of the IRC is throttleable from 10^8 to 10^11 megawatts. High-Energy plasma created during engine operation is exhausted through a central opening in the sphere to the accelerator\generator. This stage is generally cylindrical, 3.1 meters long and 5.8 meters in diameter, constructed of an integral single-crystal duranium frame and pryovunide exhaust accelerator. During propulsion operations, the accelerator is active, raising the velocity of the plasma and passing it on to the third stage. The third stage of the engine is the driver coil assembly. The DCA is 5 meters long and 4 meters in diameter and consists of a series of 8 split toroids, each manufactured from cast verterium cortenide 934. Energy from the accelerated plasma, when driven through the toroids, creates the necessary combined field effect that (1) reduces the apparent mass of the spacecraft at its inner surface and (2) facilitates the slippage of the continuum past the spacecraft at its outer surface. The final stage is the vectored exhaust director. The VED consists of a series of moveable vanes and channels designed to expel exhaust products in a controlled manner. The VED is capable of steerable propulsive and nonpropulsive modes. 
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