An ion propulsion device including emission modules in an emission plane, each module having an insulating support, an emission electrode on the support, and a conductive liquid with a microfluidic channel depositing conductive liquid on the electrode; an extraction electrode common to the emission modules and facing the modules; and a control unit, in which each module is configured to emit an ion beam when an electric field is applied to the liquid; each control unit controls an ion emission current emitted by applying a potential difference between each emission electrode and the extraction electrode; the emission electrodes are spaced apart by a linear distance that is greater than a distance between two adjacent emission electrodes separated by an empty space; and a length of the insulating support between the electrodes is greater than a propagation distance of an electric leakage current by charge jumping along the support between the electrodes.

Levitation and Propulsion Unit-2 (LPU-2) is a thrust generating device able to generate resultant force to create motion without mass flow and/or momentum exchange. The technology primarily uses electromagnetic energy, permanent magnetic repulsive energy and kinetic energy, to generate internal resultant thrust or motion. This thrust generating device comprises of one or two rapid action enable and high driving force electromagnet moving magnet linear actuators with minimum moving parts. The technology mainly leverages on compression and expansion of compressed repulsive magnetic flux. Through regulation and systematic control of current to each electromagnet, the device is able to generate resultant force or motion without external interaction.

A mass propelled device is described. The mass propelled device includes an evaporation chamber. The evaporation chamber has at least one transparent substrate configured to receive light on a first surface and a plurality of nanostructures disposed on a second surface opposite the first surface. The plurality of nanostructures excite electrons in response to light being provided to the first surface. The mass propelled device also includes propellent storage to store propellent and a propellent delivery system to provide propellent from the propellent storage component to the evaporation chamber. The evaporation chamber is configured to heat the propellent using electrons. The mass propelled device also includes at least one nozzle configured to exhaust heated propellent from the evaporation chamber in order to produce thrust.

Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, an apparatus for collecting solar energy and simultaneously protecting against damage from a resulting energy beam includes a solar energy collection system including at least one concentrator and a target configured to use, store, or convert the solar energy, the collection system configured to cause solar energy to focus on the target, at least one sensor configured to detect misalignment of the concentrator by determining that some or all of the collected solar energy is offset from the target, and a safety system configured to redirect the energy or interpose a safety structure for shielding other non-target systems from receiving too much solar energy from the collection system.

Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, an apparatus for collecting solar energy and simultaneously protecting against damage from a resulting energy beam includes a solar energy collection system including at least one concentrator and a target configured to use, store, or convert the solar energy, the collection system configured to cause solar energy to focus on the target, at least one sensor configured to detect misalignment of the concentrator by determining that some or all of the collected solar energy is offset from the target, and a safety system configured to redirect the energy or interpose a safety structure for shielding other non-target systems from receiving too much solar energy from the collection system.

Ion booster for thrust generation. The invention pertains to electrical propulsion generated by the rapid acceleration of ions between asymmetrical electrodes. The invention is applicable for propulsion generation in atmospheric and space environments.

Systems and methods for providing a heaterless hollow cathode for use in electric propulsion devices is presented. According to one aspect the cathode includes a thermionic emitter having a constricted upstream inlet compared to a downstream outlet of the emitter. The emitter is arranged downstream a hollow cathode tube. Constriction of the upstream inlet is provided by an inner cylindrical hollow space at an upstream region of the emitter having a diameter that is smaller compared to a diameter of an inner cylindrical hollow space at a downstream region of the emitter. A hollow transition region having a varying diameter connects the upstream region to the downstream region. According to another aspect, a ratio of the diameters of the two cylindrical hollow spaces reduces penetration of electric field, and therefore of electric discharge, into the upstream region of the emitter during operation.

A deformable support apparatus includes a deformable body configured to transition between at least an extended state and a contracted state where a stiffness of the deformable body in the extended state is greater than a corresponding stiffness of the deformable body in the contracted state. The deformable body includes a first member and a second member coupled to and in opposition to the first member, and arranged about a longitudinal axis. In the extended state, the first member has at least a first curved portion and the second member has at least a second curved portion. The at least a first curved portion is a positive curved portion with respect to the longitudinal axis and the at least a second curved portion is a negative curved portion with respect to the longitudinal axis.

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

A microthruster for controlling small spacecraft and methods for manufacturing the same are disclosed. Embodiments of the microthruster include one or more nozzle throats with cross sectional areas of at most 20 μm.sup.2, and some with 6 μm.sup.2. Some embodiments include heaters that heat water in one or more reservoirs to increase pressure in the reservoirs and eject the water from the one or more nozzle throats. Some embodiments are manufactured by etching channels into one or more layers of material, and still further embodiments are manufactured by forming the nozzle throats and/or the reservoirs between two layers of material. Some microthruster embodiments are flat in shape with the nozzle throats ejecting water out the thin sides of the microthruster. Still further embodiments are formed by etching channels into one layer of material, printing a heater onto another layer of material, and bonding the two layers together.