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.

Plasma cathodes for micro Hall and ion thrusters of unprecedented power efficiency, low cost, compactness, are provided. The cathodes employ, for example, a very small planar scandate cathode as electron source, delivering over 350 ma of discharge from an emitter area as small as only 0.012 cm2.

A propulsion apparatus for space vehicles, includes a solid state oxygen-rich source layer, means for extracting oxygen from said solid state oxygen-rich source layer, means for accelerating correspondingly extracted oxygen ions into vacuum. A stack includes the solid state oxygen-rich source layer, an active layer being deposited above the solid state oxygen-rich source layer, in contact with the solid state oxygen rich source layer, the active layer being formed with a material different from the solid state oxygen-rich source layer, the material being an oxide presenting impedance hysteresis behavior.

An ion beam generator includes an emission electrode, an extraction electrode, and an electricity generator. The emission electrode includes a substrate and a plurality of nanowires extending away from the substrate, substantially towards the extraction electrode, the nanowires having a length of 50 nm to 50 m. The emission electrode has a source of ions including a sheet of ionic liquid formed on the substrate and at least partially immersing the nanowires. The nanowires and the substrate are electrically insulating or semiconducting, and the electricity generator is connected to the sheet of ionic liquid. The emission electrode is thus capable of sending ion beams from the ionic liquid to the extraction electrode.

A system and method for generating a force from a voltage difference applied across at least one electrically conductive surface. The applied voltage difference creates an electric field resulting in an electrostatic pressure force acting on at least one surface of an object. Asymmetries in the resulting electrostatic pressure force vectors result in a net resulting electrostatic pressure force acting on the object. The magnitude of the net resulting electrostatic pressure force is a function of the geometry of the electrically conductive surfaces, the applied voltage, and the dielectric constant of any material present in the gap between electrodes. The invention may be produced on a nanoscale using nanostructures such as carbon nanotubes. The invention may be utilized to provide a motivating force to an object. A non-limiting use case example is the use of electrostatic pressure force apparatus as a thruster to propel a spacecraft through a vacuum.

A polarity-selectable high voltage direct current power supply including a first drive assembly that transforms a first low voltage DC input into a first medium voltage alternating current output; a first HV output assembly that transforms the first LV AC output into a first HV DC output, wherein the first HV output assembly defines a first input stage; a polarity selector coupled between the second output junction of the first drive assembly and the first and second input stages of the first HV output assembly, the polarity selector operable between a first configuration and a second configuration; wherein in the first configuration the first HV DC output has a positive polarity; and wherein in the second configuration the first HV DC output has a negative polarity.

Plasma cathodes for micro Hall and ion thrusters of unprecedented power efficiency, low cost, compactness, are provided. The cathodes employ, for example, a very small planar scandate cathode as electron source, delivering over 350 ma of discharge from an emitter area as small as only 0.012 cm2.

A plasma generation apparatus, and a plasma thruster configured to use the plasma generation apparatus are disclosed. The plasma generation apparatus includes a discharge vessel, a light-emitting monitor, a probe measuring instrument, a control device, and an optical axis driving unit. The discharge vessel is configured to ionize gas which is introduced to an inside thereof so as to generate plasma. The light-emitting monitor is configured to measure electron density of the plasma by emission spectra of the plasma. The probe measuring instrument is configured to measure the electron density of the plasma by a probe in the discharge vessel.

An ion beam generator includes a discharge chamber with a backplate and tubular sidewalk A source of propellant, for example, Xenon gas is provided to the discharge chamber. First and second annular magnets are disposed on or near the backplate, and configured with alternating polarities such that a pair of ring-cusps form on the backplate, without any magnetic ring-cusp formation on the sidewalk A cathode assembly extends into the discharge chamber to provide primary electrons to ionize the propellant.

The dipole drive is a new propulsion system which uses ambient space plasma as propellant, thereby avoiding the need to carry any of its own. The dipole drive is constructed from two parallel screens, one charged positive, the other negative, creating an electric field between them with no significant field outside. Ambient solar wind protons entering the dipole drive field from the negative screen side are reflected out, with the angle of incidence equaling the angle of reflection, thereby providing lift if the screen is placed at an angle to the plasma wind. Protons entering from the positive side are accelerated out the negative screen, producing thrust. The dipole drive can achieve more than 3 mN/kWe in interplanetary space and better than 10 mN/kWe in Earth, Venus, Mars, or Jupiter orbit and offers potential as a means of achieving ultra-high velocities necessary for interstellar flight.