Asteroid redirection facilitated by cosmic ray and muon-catalyzed fusion

Abstract

Asteroid redirection systems are provided that use cosmic ray and muon-catalyzed micro-fusion. These systems include a micro-fusion propulsion system providing thrust for redirecting an asteroid, as well as micro-fusion electrical generation powering an ion drive. The systems deploy deuterium-containing fuel material as a localized cloud interacting with incoming ambient cosmic rays to generate energetic fusion products. Dust or other particulate matter in the fuel material converts some cosmic rays into muons that also catalyze fusion. The fusion products provide thrusting upon the asteroid, or when produced near turbines facilitates electrical generation, which can then power an ion drive.

Claims

1. An ion thruster comprising: a source of deuterium-containing fuel material disposed on an asteroid surface; a reaction volume directed upward from the asteroid surface and open at the top; a flue coupled to the source and reaction volume for dispersing fuel material into the reaction volume; a set of turbines arranged around the reaction volume, wherein the set of turbines are directly exposed to the dispersed fuel material in the reaction volume a set of electrical generators coupled to the respective set of turbines to convert mechanical motion of the set of turbines into electricity; and an ion thrust engine powered by the generated electricity for producing thrust in a specified direction.

2. The generator as in claim 1, wherein the reaction volume is a cylinder with an opening at an upper end.

3. The generator as in claim 1, wherein the turbines are arranged radially around the circumference of the cylinder reaction volume.

4. The generator as in claim 1, wherein turbines are stacked vertically in multiple layers along a length of the cylinder reaction volume.

5. The generator as in claim 1, wherein one or more fans are provided in the reaction volume to maintain the dispersed fuel material in suspension within the reaction volume.

6. The generator as in claim 1, wherein the deuterium-containing micro-fusion particle fuel material comprises Li.sup.6D.

7. The generator as in claim 1, wherein the deuterium-containing micro-fusion particle fuel material comprises D.sub.2O.

8. The generator as in claim 1, wherein the deuterium-containing micro-fusion particle fuel material comprises D.sub.2.

9. The generator as in claim 1, wherein the deuterium-containing micro-fusion particle fuel material is in solid powder form.

10. The generator as in claim 1, wherein the deuterium-containing micro-fusion particle fuel material is in pellet form.

11. The generator as in claim 1, wherein the deuterium-containing micro-fusion particle fuel material is in frozen form.

12. The generator as in claim 1, wherein the deuterium-containing micro-fusion particle fuel material is in liquid droplet form.

13. The generator as in claim 1, wherein the deuterium-containing micro-fusion particle fuel material also contains up to 20% by weight of added particles of fine sand or dust.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is a side plan view of a thrust engine attached to an asteroid surface showing deployment of micro-fusion fuel via projectiles.

(2) FIG. 2 is schematic sectional view of one possible projectile package or shell for containing and dispersing the micro-fusion fuel material.

(3) FIG. 3 is a schematic plan view of a micro-fusion-driven turbine generator apparatus in accord with the present invention, shown operating on the surface of an asteroid to supply electrical power for driving an ion thruster and/or obtaining ore samples from the asteroid.

(4) FIG. 4 is a top plan view of the reaction volume of the turbine generator apparatus as in FIG. 3 showing an arrangement of turbines and generators circumferentially around a reaction volume.

(5) FIG. 5 is a side plan view of the reaction volume of a turbine generator apparatus as in FIG. 3 showing the turbines and generators in a vertically stacked arrangement along a length of the reaction volume.

(6) FIG. 6 is a graph of cosmic ray flux at the Earth surface versus cosmic ray energy, after very significant cosmic ray absorption by Earth's atmosphere has occurred.

DETAILED DESCRIPTION

(7) Cosmic-ray and muon-catalyzed micro-fusion can be employed in the invention to redirect an asteroid to a location closer to Earth, such as in lunar orbit. Cosmic ray flux naturally present in interstellar space is used to power nuclear micro-fusion events (via particle-target micro-fusion and muon-catalyzed micro-fusion) that will propel the asteroid.

(8) With reference to FIG. 1, one propulsion technique to propel an asteroid upon a desired trajectory, is to project the micro-fusion target material in a specified direction outward from the asteroid surface 11, i.e. toward the rear of its intended trajectory from a set of gun-like engines 13 attached at various points onto the asteroid 11. The engines 13 have a supply vault 14 for the projectiles 15 and a gun 16 for firing them outward. For example, one may shoot fuel packages (chips, pellets, powder) loaded in a series of projectiles 15, at a specified rate (e.g. once per second), which can then disperse the micro-fusion material as a localized cloud 17, much like artillery from an antiaircraft gun or the shooting of fireworks.

(9) The space propulsion system works in the presence of an ambient flux 19 of cosmic rays and/or muons which interact with the cloud 17 and trigger the nuclear micro-fusion of the particle target material, either by particle-target micro-fusion or muon-catalyzed micro-fusion or both. The micro-fusion fuel releases as a cloud 17 from the projectiles 15 can be solid Li.sup.6D in powder form, D-D or D-T inertial-confinement-fusion-type pellets, D.sub.2O ice crystals, or droplets of (initially liquid) D.sub.2. Fusion products 21 having significant kinetic energy (e.g. alpha particles) are generated and are received upon the asteroid surface 11 to produce thrust against the asteroid. The thrust results in acceleration (or deceleration) of the asteroid along a specified trajectory.

(10) Stored fuel packages 15 associated with the attached engine 13 will be shielded, at least within the casing of the projectiles themselves, to reduce or eliminate premature fusion events until delivered and dispersed as a cloud adjacent to the asteroid. Some small amount of metal for the engine 13 could be used for shielding, if needed. (For example, the Juno spacecraft to Jupiter contains radiation vaults of 1 cm thick titanium to shield its electronics from external radiation. A similar type of vault 14 might be used in this case for the shielding of the stored fuel.) One need not eliminate cosmic rays or their secondary particles (pions, muons, etc.) to zero, but merely reduce their numbers and energies sufficiently to keep them from catalyzing sufficiently large numbers of fusion events in the stored target particle material. After being shot from the gun 16, the casing of the projectiles 15 themselves will continue to provide some shielding until dispersal of the target particle material as a cloud 17.

(11) A variety of known pyrotechnic or artillery shell structures might be employed, the difference being in the content of the material to be dispersed. As seen in FIG. 2, one possible structure comprises a shell 15 having a shell wall 23 containing the micro-fusion fuel material 31 and attached at the back to a cartridge case 25 with solid-chemical-fuel propellant 27 for launching the shell to a targeted location. Within the shell wall 23, for example at or near its tip is a fuse 33 for triggering the release and dispersal of the material 31, e.g. by explosive means including a central ignition tube 34 leading to a shell-bursting charge 35. The fuse 33 can be based upon timing, barometric pressure, a determined position, or other known mechanisms to ensure that dispersal of the fuel material 31 occurs at an optimal altitude over the targeted location.

(12) Soon after the projectile has reached a desired distance from the asteroid the fuel package releases its particle target material. For example, a chemical explosion can be used to locally disperse the micro-fusion material. The shells or other form of package should disperse the micro-fusion fuel elements at a desired altitude (i.e. distance from the asteroid surface) for optimal dispersal of the fuel material relative to the asteroid. Various mechanisms for triggering a chemical explosion of the package could be employed. Triggering technologies can include any one or more of (1) a timer, (2) a location detector, or (3) laser or microwave beam(s) directed at the package from one or more surface bases or nearby spacecraft. Optimal distance for dispersing the material may depend upon asteroid size and composition.

(13) The dispersed cloud of target material will be exposed to both cosmic rays and to their generated muons. To assist in the formation of muons for muon-catalyzed fusion, especially when D.sub.2O or D.sub.2 is used, the target package may contain up to 20% by weight of added particles of fine sand or dust. As cosmic rays collide with both micro-fusion target material and dust, they form muons that are captured by the deuterium and that catalyze micro-fusion. Likewise, the cosmic ray collisions themselves can directly trigger particle-target micro-fusion.

(14) Besides D-D micro-fusion reactions, other types of micro-fusion reactions may also occur (e.g. D-T, using tritium generated by cosmic rays impacting the lithium-6; as well as Li.sup.6-D reactions from direct cosmic ray collisions). For this latter reaction, it should be noted that naturally occurring lithium can have an isotopic composition ranging anywhere from as little as 1.899% to about 7.794% Li.sup.6, with most samples falling around 7.4% to 7.6% Li.sup.6. Although LiD that has been made from natural lithium sources can be used in lower thrust applications or to inhibit a runaway macro-fusion event, fuel material that has been enriched with greater proportions of Li.sup.6 is preferable for achieving greater thrust and efficiency.

(15) The micro-fusion reactions in the dispersed cloud creates a kind of external combustion engine that will provide thrust against one side of the asteroid. The asteroid effectively acts as the equivalent of a piston in an external combustion engine and the volume of the continuous slow micro-fusion creates high velocity fusion products (alpha particles, etc.) that bombard the asteroid surface. Even the photon radiation generated by micro-fusion events supplies pressure to help accelerate the asteroid. The required rate of firing will depend on the amount of acceleration required, the amount of fusion obtained from the ambient cosmic ray and/or muon flux, the dispersal rate of the fuel cloud from in front of the asteroid, and the efficiency of the transfer of the fusion products into thrust, but could be expected to be as much as one shell per second for the duration of the thrusting period. The amount of energy generated depends upon the quantity of fuel released and the quantity of available cosmic rays and muons. Assuming most of the energy can be captured and made available for thrust, an estimated 10.sup.15 individual micro-fusion reactions (less than 1 g of fuel consumed) per second would be required for 1 kW output. But as each cosmic ray can create hundreds of muons and each muon can catalyze 100 micro-fusion reactions, the available cosmic ray flux in interplanetary space is believed to be sufficient for this asteroid thrusting purpose following research, development, and engineering efforts.

(16) The number of micro-fusion thrust engines needed will depend upon the size (i.e. mass) of the asteroid to be redirected and upon the acceleration required. Additionally, if the asteroid has any amount of rotation relative to its trajectory, the operation of the various engines will need to be coordinated so that only those engines located (at any given point in time) where they can provide the desired thrust direction are active. When the asteroid rotates, some engines will shut off and others turned on, as needed, to maintain the target thrusting in the correct direction.

(17) In another embodiment shown in FIG. 3, each engine may have one or more micro-fusion-based turbine electric generators 41, where the turbines are driven by the fast helium nuclei micro-fusion products generated from dispersed lithium-6 deuteride or other deuterium-containing micro-fusion target material exposed to the cosmic rays. Micro-fusion fuel packages would be delivered to the vicinity of each of the turbines, where the micro-fusion reaction products can turn the turbines to generate electricity for powering an ion thruster and/or obtaining ore samples. For example, a cloud of deuterium-containing micro-fusion target fuel 43, e.g. particles of Li.sup.6D, can be dispersed from a flue 44 into a volume 45 between two or more helium-wind turbines 46. Specifically, a generator assembly 41 includes a source 40 of deuterium-containing micro-fusion particle fuel material 42. This material could be blown 43 through a flue 44 (e.g. by means of a fan with a gas source at the source 40 or by other means depending on the form that the fuel material takes), and then dispersed from the flue 44 into a reaction volume 45. The micro-fusion target fuel material 43 is dispersed in proximity to turbines 46 arranged around the reaction volume 45, and then exposed to ambient cosmic rays 49 and muons that enters the volume 45 and interacts with the dispersed fuel material 43 to cause nuclear micro-fusion events. High-energy cosmic rays 49 entering the volume 45 interact with the micro-fusion target fuel material 43 to cause nuclear fusion events. Fusion products, mainly high energy helium nuclei (alpha particles), direct kinetic energy to the turbine blades 46 to turn the turbines and generate electricity. A wind of micro-fusion products made up of energetic helium (alpha products) impinge upon and direct kinetic energy to the turbine blades 46 to turn the turbines and drive the associated generators 47 to produce electricity which can then be supplied via electric cables 48 to ion propulsion equipment and/or ore-sample mining equipment. If necessary, a set of one or more fans 50 in the reaction volume 45 may help keep the fuel material in suspension (against the acceleration) and near the turbines 46.

(18) The electricity may be used to power one or more ion drives to produce thrust. Ion thrusters are currently in use by NASA for a variety of geosynchronous satellites, as well as for the Dawn spacecraft (launched in 2007) for exploring the asteroid belt (including Ceres and Vesta). In an ion thruster, propellant (e.g. xenon) is ionized by electron bombardment to create a plasma and the positive ions in the plasma are then accelerated from the thruster chamber to produce thrust. Whether powered, as describe here, by fusion-driven turbine generators, or by any other means, a sufficient reserve of propellant will be needed for the duration of the desired thrusting. Depending upon the asteroid composition, material from the asteroid itself might be used as a propellant source for the ion thrusters.

(19) As seen in FIG. 4, in one possible generator configuration, the turbines 46 may be arranged around the circumference of the reaction volume 45, which can be cylindrical or any other equivalent columnar shape. While typically four in number, there can anywhere from as few as two up to 20 or more such turbines 46 (eight are seen here), depending on the space available, the size of the fusion reaction cloud, and the size and arrangement of the turbines themselves about the chamber 45. Alternatively, or in addition, as seen in FIG. 5, the turbines 46 may be arranged in multiple stacks along the length of the cylindrical reaction volume 45. Turbines are connected, e.g. through gearboxes, to corresponding induction generators 47. The generators 47 may be equal in number to the corresponding turbines 46 (1:1 correspondence), or multiple turbines may drive any given generator (n:1 correspondence).

(20) As seen in FIG. 3, the chamber may be arranged with its cylindrical or columnar axis pointing in a vertical direction, since cosmic rays and generated muons will be arriving from above, and the asteroid itself will shield in-coming cosmic rays from below, such that the chamber should be located and pointed in a direction that maximizes receipt of cosmic rays onto the cloud of fusion target material within the chamber.

(21) As with the micro-fusion thrusters, the deuterium fuel for a generator may be supplied in the form of clouds of solid lithium-6 deuteride powder, pellets or chips, or even frozen heavy water (D.sub.2O) or liquid droplets of D.sub.2, to a reaction chamber 45, where it is exposed to incoming cosmic rays 49 and muons , as seen in FIG. 3. One technique for creating the cloud of fusion target material is to shoot fuel packages as a series of projectiles into the reaction chamber, which can then disperse the fusion material as a localized cloud, much like fireworks or artillery. For this purpose, one or more gun tubes may be located below the chamber and loaded with the packages for introduction into the chamber. Alternatively, packages may be dropped into the chamber from near the top via a slide dispenser. The fuel within the projectile packages can be solid Li.sup.6D in powder form, D-D or D-T inertial-confinement-fusion-type pellets, or D.sub.2O ice crystals. To assist muon formation, especially when D.sub.2O is used, the target package may contain up to 20% by weight of added particles of fine sand or dust. Packages will be shielded, at least within the casing of the projectiles themselves, to reduce or eliminate premature fusion events until delivered and dispersed as a cloud in the reaction chamber. Soon after the projectile has reached the desired dispersal location within the chamber, the package releases its target material. For example, a chemical explosion can be used to locally disperse the fusion material. For a typical cloud of Li.sup.6D in powder form it may be desired to disperse the material near the top of the chamber to allow maximum usage of the material while it settles toward the bottom of the chamber. In the case of very large asteroids, it might be advantageous to provide one or more fans 50 at the bottom of the chamber 45 (seen in FIG. 3) to keep the cloud of target material suspended in the chamber as long as possible, but most asteroids will have sufficiently low, even negligible, gravity so that fuel settling would not be a concern.

(22) The present invention achieves nuclear micro-fusion using deuterium-containing target material, and the ambient flux of cosmic rays and generated muons that are already naturally present. The dispersed cloud of target material will be exposed to both cosmic rays and to their generated muons. As cosmic rays collide with fusion targets and dust, they form muons that are captured by the deuterium and that catalyze fusion. Likewise, the cosmic ray collisions themselves can directly trigger particle-target fusion. Muonic deuterium, tritium or lithium-6 can come much closer to the nucleus of a similar neighboring atom with a probability of fusing deuterium nuclei, releasing energy. Once a muonic molecule is formed, fusion proceeds extremely rapidly (on the order of 10.sup.10 sec). One cosmic ray particle can generate hundreds of muons, and each muon can typically catalyze about 100 fusion reactions before it decays (the exact number depending on the muon sticking cross-section to any helium fusion products). For example, a particularly desired reaction is Li.sup.6+D.fwdarw.2He.sup.4+22.4 MeV, where much of the useful excess energy is carried as kinetic energy of the two helium nuclei (alpha particles). The alpha particles then provide a motive force to turbine blades for the generation of electricity. Other fusion reactions also create energetic fusion products that can drive the turbines.

(23) Additionally, any remaining cosmic rays can themselves directly stimulate a fusion event by particle-target fusion, wherein the high energy cosmic ray particles (mostly protons, but also helium nuclei) bombard the cloud of target material. When bombarded directly with cosmic rays, the lithium may be transmuted into tritium which could form the basis for some D-T fusion reactions. Although D-D fusion reactions occur at a rate only 1% of D-T fusion, and produce only 20% of the energy by comparison, the freely available flux of cosmic rays and their generated muons should be sufficient to yield sufficient fusion energy output for practical use.

(24) The optimum concentration of the cloud of target material for the particle-target and muon-catalyzed fusion may be determined experimentally based on the particular abundance of cosmic rays with a view to maintaining a chain reaction of fusion events for producing adequate thrust against the turbine blades, while avoiding any possibility of runaway fusion.

(25) The present invention achieves muon-catalyzed nuclear fusion using deuterium-containing target material, and muons that are naturally created from ambient cosmic rays. Most cosmic rays are energetic enough to create multiple muons (often several hundred) by successive collisions with dust or with the atoms in a target. In fact, most cosmic rays have GeV energies, although some extremely energetic ones can exceed 10.sup.18 eV and therefore potentially generate millions of muons. The optimum concentration of the target material for the muon-catalyzed fusion may be determined experimentally based on the particular abundance of cosmic rays with a view to maintaining a chain reaction of fusion events for driving the electrical generating turbines.

(26) Because both particle-target fusion and muon-catalyzed fusion, while recognized scientifically, are still experimentally immature technologies (since measurements have only been conducted to date on Earth using artificially accelerated particles and generated muons from particle accelerators), various embodiments of the present invention can have research utility to demonstrate feasibility in environments beyond Earth's protective atmosphere and/or geomagnetic field. First, a satellite platform in Earth orbit (for example, on the International Space Station) and then later a lander on the surface of the Moon are both conveniently close to Earth to place experimental modules in order to determine optimum parameters (e.g. dimensions of the chamber, and cloud density for different fuel types) in order to adequately drive the turbines.